International Journal of Aerospace EngineeringVolume 2011 (2011), Article ID 937629, 18 pagesdoi:10.1155/2011/937629

Review Article

Survey of European and Major ISC Facilities for Supporting Mars and Sample Return Mission Aerothermodynamics and Tests Required for Thermal Protection System and Dynamic Stability

Mathilde Bugel,¹ Philippe Reynier,¹ and Arthur Smith²

¹Ingénierie et Systèmes Avancés, 16 avenue Pey Berland, 33600 Pessac, France²Fluid Gravity Engineering Ltd., Emsworth PO10 7DX, UK

Received 6 December 2010; Revised 13 April 2011; Accepted 19 May 2011

Academic Editor: C. B. Allen

Copyright © 2011 Mathilde Bugel et al. This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.

Abstract.

In the frame of future sample return missions to Mars, asteroids, and comets, investigated by the European Space Agency, a review of the actual aerodynamics and aerothermodynamics capabilities in Europe for Mars entry of large vehicles and high-speed Earth reentry of sample return capsule has been undertaken. Additionally, capabilities in Canada and Australia for the assessment of dynamic stability, as well as major facilities for hypersonic flows available in ISC, have been included. This paper provides an overview of European current capabilities for aerothermodynamics and testing of thermal protection systems. This assessment has allowed the identification of the needs in new facilities or upgrade of existing ground tests for covering experimentally Mars entries and Earth high-speed reentries as far as aerodynamics, aerothermodynamics, and thermal protection system testing are concerned.

1. Introduction

Some of the future missions, investigated by the European Space Agency in the frame of the Exploration [1] and Science Programmes, focus on sample return missions to Mars, asteroids, and comets. The main challenges of these missions are the Mars entry of large vehicles, the high-speed Earth reentry of return capsules, and the dynamic stability of blunt bodies during entry and descent.

Several issues are related to Mars entry of large vehicles. The nominal composition of Mars and Earth atmospheres retained for the study is listed in Table 1. First, since Mars atmosphere is mostly composed of carbon dioxide, the facilities have to be capable of operating with this gas and of reproducing flight conditions typical of a Martian entry, in terms of heat flux and pressure. Then, the ground tests have to be able to simulate the turbulence flow conditions occurring during entry, induced by the vehicle, by the possible presence of steps over the heat-shield, and strongly coupled with heat shield ablation. A peculiar point of sample return missions to Mars is the Mars ascent. For covering this aspect of the mission, the utilization of ground test facilities capable of reproducing Mars ascent trajectory conditions, and Mars initial conditions for engine ignition are required.

Table 1: Mars and Earth atmosphere compositions.

Species
Mars (%)
Earth (%)

CO₂
95.3
0.03

N₂
2.7
78.1

Ar
1.6
0.93

O₂
0.13
20.9

CO
0.07
0.000007

H₂O
0.03
0.1

High-speed Earth reentries, like those performed by NASA for Genesis [2] and Stardust [3, 4] missions and the one performed by NASDA for Hayabusa [5], are characterized by high heat fluxes [6] as shown in Figure 1 for different entry trajectories (E1 to E4) corresponding to different initial entry conditions in terms of flight path angle and velocity.

Figure 1: Total heat flux versus time for different entry trajectories during EVD mission [6].

Another point concerning entries of space probes is the ground capabilities for reproducing flow conditions as function of Reynolds number, as well as the capabilities to simulate flow phenomena such as dissociation and ionisation. Related to nonequilibrium thermochemistry, chemical kinetics is also an issue, particularly for the high-speed Earth reentry. To summarize, of particular relevance are the following processes.(i)Simulation of turbulence in hot compressible gas.(ii)Simulation of reentry flows in radiation environment.(iii)Thermochemical kinetics.(iv)Ablation and ionisation.(vi)Simulation of the influence of dust on flow properties.

A common point to Mars and Earth entries is the stability of the capsule which has to be ensured for hypersonic, supersonic, and subsonic regimes. For Mars entry, the dynamic stability has to be kept until the parachute deployment, for the Earth return capsule; due to the capsule size, the use of a parachute would be a penalty in term of mass budget and perhaps reliability. As a consequence, the experimental facilities allowing the investigation of stability and more particularly of dynamic stability have been included in this paper.

While various studies have previously reviewed the availability and adequacy of ground testing facilities and instrumentations for Earth orbital entry simulations, to our knowledge there was no exhaustive study on the same topic for planetary or sample return missions, with a systematic review of their adequacy for Mars ascent/descent and Earth high-speed entry. In the past, IABG [7] has performed a review on TPS qualification and thermomechanical testing but this paper essentially focused on mechanical testing and did not cover in details aerodynamic aspects, particularly if a superorbital entry is considered. Moreover, the survey presented was not complete since major companies had declined to provide information. ONERA [8] dedicated an effort focused on aerothermodynamics which is an excellent and complete review, but did not provide precise data on achievable performance of most of the facilities. Additionally, this paper essentially focused on suborbital entry. Lu and Marren [9] have gathered a collection of papers from some of the major facilities illustrating some of their operational aspects, but that does not allow establishing their readiness and adequacy for sample return missions.

Here, the paper mostly focused on the main experimental capabilities in Europe [10]. The main facilities available in the ISC (Independent State Community) and Australia (since Australian scientists are involved in ESA research programmes), as well as the ballistic ranges in Australia and Canada (since Canada is an ESA associated member state) for the assessment of dynamic stability have been also incorporated. From the inputs gathered in the literature, on the different websites, during a dedicated Workshop on Facilities held at ESTEC on 28 March 2008, those provided by the different experimentalist teams, the main characteristics of the different ground tests have been obtained. The analysis of the different aspects retained for the paper with the actual capabilities and the potential needs for additional capabilities for ensuring the success of sample return missions are reported hereafter.

2. Mars Entry

Mars atmosphere is mostly composed of carbon dioxide which has thermodynamic properties different from oxygen and nitrogen. From an experimental point of view, the main challenge for Mars entry is the presence of a CO₂ atmosphere. Most of the existing facilities in Europe have been developed for testing in air atmosphere, and their adaptation to CO₂ is not straightforward. In fact, the usual performance envelope is different, and the presence of large fraction of CO for medium range enthalpy has to be considered [11]. As a consequence, test facilities have to be capable of operating with carbon dioxide and of reproducing flight conditions typical of Martian entry and ascent. The main features for investigating experimentally a Martian entry are listed below.

(i)Capabilities of existing facilities to operate with Mars atmospheric conditions (95% of CO₂) and to cover a Mars entry trajectory in terms of heat flux and pressure.(ii)Simulation of fully turbulent flows in high-enthalpy facilities for Martian entry of large vehicles.(iii)Capabilities of existing facilities to operate with CO₂ flows in presence of particles for hydroerosion and heat-flux assessment.(iv)Available measurements techniques for Mars atmosphere.

In the frame of the Mars Premier Programme [12] and the recent ESA TRP [13] (Technology and Research Programme) on CO₂, testing activities have been carried at ONERA, EADS, IRS, MIPT, DLR [14], and VKI for CO₂ environments. Earlier studies were also conducted at IUSTI, CORIA, IPM, DLR (in HEG), and PROMES. The results have demonstrated the capabilities of some of the aerothermodynamics facilities to operate with a Martian atmosphere. However, the tests have highlighted some problems. For example, in arc-driven facilities, the use of a gas different from air has a strong impact on the arc chamber and notably on the arc performance which is notably reduced: at least 30% for CO₂ when comparing against air. The carbon dioxide molecules start to be dissociated inside the arc chamber with some consequences on the nozzle flow.

The aim of ESA TRP activities was to investigate the thermochemistry of high-enthalpy CO₂ flows, in order to improve the existing analytical and numerical engineering capabilities for future exploration missions. The facilities retained for those experiments from one team were the ONERA high enthalpy wind tunnel F4, VKI Plasmatron and Minitorch facilities, and DLR arc-heated facility L2K. The three facilities that have been used by one team within this study complement each other almost ideally, since they cover a wide range of thermochemical regimes:(i)the flow field in Plasmatron and Minitorch is subsonic, and it is expected to be close to thermochemical equilibrium;(ii)F4 is a hot-shot facility that provides a hypersonic nonequilibrium flow;(iii)DLR L2K facility with a chemically almost frozen environment at low temperature levels (<1000 K) in the free stream and high temperatures (up to 5500 K) behind the bow shock.

While the other team retained, a mix of facilities from shock tube through small arc-heated facility to larger industrial facility:(i)VUT-1 shock tube at MIPT (also used in mid 90’s study of CO₂ chemistry under TRP);(ii)PWK ISR plasma wind tunnel;(iii)SIMOUN industrial arc heater used for Mars TPS qualification at ASTRIUM-ST.

Another point is the potentiality of a turbulent flow for the Martian entry of a large vehicle (and/or driven by TPS ablation), for which the presence of turbulence could strongly increase the heat flux, by roughly 60% if the surface remains smooth [15].

A last problem is the potential presence of dust particles during reentry. Their presence is due to massive storms that characterize the dynamic of Mars atmosphere. Even during the quiet season (with much less storms), the probability of a storm is never null and a local one can evolve in a global storm within few days. The presence of the particles would increase TPS recession and overheating [16, 17] of the substructure material.

Radiation is present during Mars entry, but this phenomenon plays a second order role. It is still an issue but not a sizing phenomenon for a TPS, at least for orbital or scientific hyperbolic entry; it may need to be reassessed for short duration flight-manned missions.

2.1. Facilities Survey

In Europe, the following facilities are running with CO₂. (i)HEAT high-enthalpy arc-jet at ALTA (Pisa).(ii)Reentry chamber for material testing at ARC (Seibersdorf in Austria).(iii)SIMOUN mostly used for TPS qualification at ASTRIUM-ST (Aquitaine);(iv)Arc-jet, inductively coupled plasma torch and low-power radio frequency plasma torch at relevant for aerochemistry at CORIA (Rouen).(v)HEG shock tunnel and LBK arc-heated facility at DLR (Cologne and Göttingen) for aerothermodynamics and TPS qualification.(vi)HHK Ludwieg shock tube at HEG (Göttingen).(vii)PHEDRA arc-jet for aerochemistry at ICARE (Orléans).(viii)PWK facilities at IRS (Stuttgart) for material and plasma characterization and heat-shield testing.(ix)Shock tube at ISL (Saint-Louis) for dynamic stability and aerothermodynamics.(x)ICP plasma torch at LAEPT (Clermont-Ferrand) for radiation.(xi)F4 hot-shot arc-jet at ONERA (Le Fauga near Toulouse) for aerothermodynamics.(xii)MESOX at PROMES (Odeillo in the French Pyrénées) for material characterization, catalysis, and radiation.(xiii)TH2 shock tunnel at RWTH (Aachen) for aerothermodynamics.(xiv)HSST hypersonic wind tunnel, ST-DC shock tube and HST2 shock tunnel at UMIST (Manchester) for aerothermodynamics.(xv)SPES arc heated at UNINA (Naples) for aeroheating and ablation tests.(xvi)Longshot-driven piston for aerothermodynamics and Plasmatron for material testing at VKI (Bruxelles).

To this list, TCM2 shock-tube from IUSTI Marseille that is now closed will be also considered for the review since it has provided a large amount of data for European projects like Huygens and was a key facility for research in chemical kinetics since it has produced a large part of the European data related to planetary entry in this field [18]. The Gun tunnel at the University of Oxford has also been closed. This facility was used for Beagle2 heating studies.

According to the previous list, quite a lot of European facilities can be operated with a Mars-like atmosphere. However, the review of their capabilities is not easy since the performance envelopes for most of the facilities have not been provided. Capabilities and main characteristics of some of these facilities are listed in Tables 2 and 3.

Table 2: Capabilities of some available European installations for investigation of aerothermodynamics during a Martian entry.

Facility
Running time
Flow regime
Mach
P₀ (Pa)
T₀ (K)
Heat flux (MW/m²)
Re
Comments

HEG, DLR
1 to 5 ms
High enthalpy
8.4 to 10.7 (4.6–6.2 km/s)
35 to 90 × 10⁶
6600 to 9700
1–22
0.2 to 1.1 × 10⁶
High enthalpy condition: 11–23 MJ/Kg DLAS

L3K, DLR
Up to 30 mn
High enthalpy, laminar flow
5 to 10
0.15 to 1.8 × 10⁶
Up to 7000
Up to 4
Up to 10⁵
Enthalpy up to 25 MJ/Kg DLAS

TH2, RWTH
2 to 10 ms
Cold hypersonic
6 to 12
4 to 60 × 10⁴
1500 to 7400
0.7 to 20
Up to 10⁷
Detonation driver mode for high enthalpy condition No DLAS

Longshot, VKI
25 to 70 ms
Cold hypersonic
10 to 20
1 to 4 × 10⁸
1500 to 3500
n.a.
At , 5 × 10³ to 15 × 10⁶
No DLAS

F4, ONERA
Up to 200 ms
High enthalpy
7 to 21
2 to 10 × 10⁷
1500 to 7500
n.a.
5 × 10⁶ () to 10⁶ ()
DLAS

SIMOUN, ASTRIUM
Up to 5 mn
High enthalpy
4 (flat plate)–4.5 stag. point
Up to 10⁴
n.a.
Up to 1.3 (stag. point)–0.7 (flat plate)
n.a.
DLAS

HHK, HTG
100 ms
Cold hypersonic
7 (5.7 km/s)
30 to 350 × 10²
Up to 900
n.a.
3 to 5 × 10⁶
No DLAS

STA-STB, ISL
4 ms
Hypersonic, low enthalpy
3.5 to 10 (3.5 km/s)
Up to 10⁶
n.a.
Up to 10
10⁶ for
Higher Mach number possible No DLAS

HST2, UMIST
Up to 10 ms
Hypersonic, low enthalpy
5.75 to 12
n.a.
n.a.
n.a.
n.a.
No DLAS

Table 3: Characteristics of European facilities for TPS testing.

Name
Heat-flux (MW/m²)
Stagnation pressure (bar)
Running time
Model size (mm)
Measurements
Remarks

SIMOUN (for CO₂)
Stagnation point: up to 1.3 Flat plate: up to 0.7
Up to 0.1
Up to 5 min
Stagnation point: 70 Flat plate: 300 300 150 thick
Behaviour of sample specimen under flux and pressure constraints
The flux and pressure can be stationary as well as dynamic. Dust-loaded flows possible

L3K (for air)
Up to 4
n.a.
<1800 s
280 350 70
Total enthalpy, pressure, entry relevant gas composition, velocity gradient, shear stresses
High enthalpy flow properties Dust-loaded flows possible

Plasmatron (air)
Up to 2.9
Up to 0.15
Up to 1 hour
50
Static pressure, stagnation pressure, temperature, heat flux
Aerothermal testing of TPS elements. Ageing tests of reusable thermal protection materials

In ISC, the following facilities can be operated with CO₂ or Mars-like atmospheres.(i)Plasma Hall generator at HMTI (Minsk).(ii)IPG-4 Plasmatron at IPM (Moscow).(iii)Wind-tunnel AT303 and hot-shot wind-tunnel IT-302M at ITAM (Novosibirsk).(iv)Shock tube VUT-1 at MIPT (Moscow) used for chemical kinetics studies.(v)Hot-shot IT-2, vacuum wind-tunnel VAT-3, and shock tunnel UT-1M at TSAGI (Zhukovsky).(vi)Piston gas dynamic units U-11 and U-7, U-1T shock tunnel, and U-13 high-frequency Plasmatron at TSIINMASH (Korolev).

HTMI can be used for TPS validation, and IPG-4 has already been used for catalysis and ablative tests. At ITAM, AT-303 and the hot-shot wind-tunnel IT-302M can be used for aerothermodynamics (aerodynamics and heat-flux distribution over reentry vehicles). The shock-tube VUT-1 seems to be well suited to Mars applications, and it is quite attractive for chemical kinetics and radiation studies. At TSAGI, IT-2 and VAT-3 and UT-1M are mostly used for general aerothermodynamics. Particles can be injected in UT-1M. At TSIINMASH, U-11, U7, and U-1T are used for aerothermodynamics and U-13 for TPS testing.

During the review, no available results obtained for facility running with CO₂ were found in Canada. The expansion tubes of the University of Queensland [19, 20] have already been run for Mars like atmosphere in the frame of an ESA TRP study; as a consequence, some of the elements available on these facilities, particularly the measurement techniques developed, have been accounted for the paper.

2.2. Aerothermodynamics

The accuracy of the experimental simulation of reentry conditions strongly depends on the ability to determine the flow conditions. Hypersonic forces and stability data may be obtained with good accuracy [21] on the basis of Reynolds or Mach numbers or other appropriate similitude parameters. But, this is not the case for some other aerodynamics characteristics: the correct simulation of dissociation and ionization requires the duplication of actual flight conditions; heat flux depends strongly on flow enthalpy and density; base pressure is strongly dependent on real gas effects [21]. The minimum set of parameters which has to be duplicated during the tests is the specific enthalpy of the gas, the stagnation pressure, the heat flux, and the Reynolds number.

Some characteristics of several European facilities available for aerothermodynamics are listed in Table 2. For most of the facilities, data were only provided for air and no performance envelope was available for CO₂ (even if they have been already operated with CO₂).

First tests in Europe with CO₂ were performed in the frame of the 1st Aerochemistry TRP [22] in HEG for Viking type forebody, in shock tubes at MIPT and IUSTI for kinetics, and at CORIA and IPM (from 1991 to 1996) for material catalycity. Later, F4 studies were undertaken in the frame of the Mars Premier Programme [12]. From the activities already performed for Mars entry, it appears that arc-jet facilities (such as LBK, SIMOUN, and F4) lose a lot of efficiency (around 30% for F4). However, from the work performed in the frame of Mars Premier and ESA projects it is clear that there are still some margins for improving the state of the art with the existing facilities. Progresses are particularly needed to improve the knowledge of the flow conditions when running facilities with CO₂. With the inputs provided during the review, it can be concluded that Mars entry trajectories are partially covered [23] with the existing ground tests in Europe. The coverage of the entry trajectory depends on initial entry conditions such as velocity; it decreases for the high velocities due to the power losses in the arc-jet test chambers when using CO₂ mixtures.

Several ISC facilities (see list in previous section) can be operated with CO₂. Those from TSAGI, ITAM, and TSIINMASH are relevant for Mars entry since most of them have been already run for such conditions in the frame of ISTC [24] studies. Here also, the performance envelopes for CO₂ were not available.

It is unclear if the European facilities are able or not to cover a whole Mars entry trajectory with the available information; however, arc-jet facilities are usually too low in pressure already for Earth suborbital reentry. The conclusions might not be very optimistic for Mars entry due to the large loss of power when using CO₂. Since the potentialities of the existing ground tests have not yet been exhausted, it does not seem a priority to develop a facility dedicated to Mars entry. Additionally, the potential gaps could be filled by using ISC facilities or by adapting existing facilities (such as SCIROCCO) to CO₂ flows. A last point is that we should keep in mind that NASA developed successfully the Viking mission in the seventies without having a facility running with CO₂.

2.2.1. Measurement Techniques

Parallel to the material testing, diagnostic methods, intrusive probes, and nonintrusive optical diagnostics have to be qualified and applied for detailed investigations on high-enthalpy plasma flows and material behaviour during the tests. The measurement techniques available in Europe are the following.(i)Electrostatic probes for the determination of electron properties.(ii)Mass spectrometer to characterize plasma flows (temperature and plasma composition).(iii)Radiation probes (extensively used at IRS).(iv)Fabry-Perot interferometry for spectroscopy.(v)Emission spectroscopy for measurements of temperature and concentration profiles [25, 26].(vi)Holographic interferometry, nonintrusive method for investigating density field [27].(vii)Laser techniques (laser-induced fluorescence and laser absorption) for radiation measurements [28].

A high expertise on measurement techniques for diverse flow parameters and more particularly for radiation investigation is available at IRS [23]. During previous studies, different probes have been developed to measure these flow parameters. Furthermore, electrostatic probes are in use for the determination of electron properties and a mass spectrometer can be positioned as a probe in the plasma flow. Besides the intrusive diagnostic methods, optical measurement techniques are also applied. For the detection of the overall plasma radiation, which has an important influence on the heat flux for high-speed entry missions like Galileo or Huygens, a radiation probe can be used at IRS. Fabry-Perot interferometry (used for spectroscopy), emission spectroscopy, and laser techniques such as laser-induced fluorescence and laser absorption are also available [23]. Combining these optical techniques, state selective information about all radiating states and the ground state can be obtained.

On its side, ONERA has extensively developed the DLAS (diode laser absorption spectroscopy) technique [29] for CO₂ flows. Among the existing DLAS spectrometers, the one of F4 seems to be indispensable as it has the particularity of having two diodes: one for CO and another for CO₂. Now, several European facilities, as shown in Table 2, are equipped with this technique [30, 31].

Through TRP activities, slow progresses have been made to determine temperatures, concentration, velocity, and gas composition of the free-stream flow, using nonintrusive laser-based spectroscopic techniques. Laser-induced fluorescence (LIF) measurements were performed on NO, CO, and O particles, and DLAS was used to probe CO and CO₂. Furthermore, emission spectroscopy was applied. In addition, cold wall heat fluxes and shock standoff distances have been measured in dependence of the enthalpy level. Major attention has been paid to a simultaneous use of these techniques, in order to eliminate any negative effects of the repeatability of the facility flow parameters. So, the facilities were improved in their understanding and instrumentation:(i)L2K with LIF for measuring NO, O, and CO, and CO diode laser absorption spectroscopy;(ii)VKI Plasmatron and Minitorch: high-speed imaging of plasma flow, improved understanding of stability, O Two photon Absorption Laser-Induced Fluorescence (TALIF) [32];(iii)DLAS feasibility for simultaneous CO and CO₂ measurements in F4 and SIMOUN.

In the frame of TRP activities, the feasibility of measuring some species (CO and CO₂) densities in SIMOUN arc-jet by DLAS has also been demonstrated, as well as the measurement of velocity and temperature. This was done thanks to a fruitful cooperation between ASTRIUM-ST and ONERA and was intended to bridge the gap between research and industrial facilities to be used on ExoMars validation.

For future activities, it would be relevant to extend the capabilities of nonintrusive techniques. The application of DLAS for measuring atomic oxygen would be a valuable contribution. A way for improving the state of the art in nonintrusive techniques could be the development of holographic interferometry. The application of these techniques to measurements in expansion tubes, performed recently at the University of Queensland [33] seems to be very promising. The improvement of the measurement techniques for ionic species and electron density would also be of high interest to improve ionization predictions and blackout estimation during entry.

It has to be noted that, as discussed during the Workshop on Facilities held at ESTEC on 28 March 2008, due not only to cost reason but also to their expertise, facilities available in the research institutes and more particularly universities (such as IRS, LAEPT, ICARE, CORIA, and UMIST) have a strong role to play for the development of new experimental and diagnostic methods.

2.2.2. Chemical Kinetics

Shock tubes are attractive for investigating chemical kinetics and thermal relaxation. In the perspective of a Martian entry, facilities have to be able to reproduce entry trajectory with entry velocities between 4.0 and 7.5 km/s and to work with a CO₂ environment. In order to improve the knowledge on chemical kinetics, several shock tubes (and shock tunnels) are available in Europe, among them we can cite.(i)HEG at DLR Göttingen;(ii)TH2 shock tunnel at RWTH Aachen;(iii)HHK Ludwieg shock tube at HEG Göttingen;(iv)GDLich at GDL;(v)STA and STB at ISL;(vi)TU Braunschweig Ludwieg shock tube.

Most of these facilities (mainly the shock tunnels) are dedicated to aerodynamic investigation (force measurements and stability). TCM2 at IUSTI (Marseille) was the only shock tube used to perform experiments on chemical kinetics and thermal relaxation for planetary entry. It was a very attractive facility due to its capabilities for Mars and Titan entries. This facility has given a valuable contribution on chemical kinetics in a CO₂ environment [35]. Unfortunately, TCM2 has been stopped for safety reason and a part of the operating team has already left. For investigations on chemical kinetics, the loss of TCM2 capabilities highlights the lack of shock tubes in Europe with the capability to cover planetary entries. The shock tunnels TH2 (RWTH) and HEG (at DLR) could fill at least partially the gap, but these facilities are more suitable for Earth suborbital entry as shown in Figure 2 where the performance map in terms of similitude parameter (ρ ∞L) and velocity are compared to Earth orbital reentry trajectories.

Figure 2: Performance envelopes (binary scaling parameter as function of velocity) of HEG, TH2, F4 and Longshot (VKI) for Earth suborbital reentry according to Kordulla et al. [34].

The other facilities, STA and STB at ISL, HHK at HEG, and the Ludwieg tube of TU Braunschweig, are mostly used for aerodynamics and stability investigations. The shock tube from UMIST does not seem to fit, at least if the Mach number is considered, with the requirements of a Mars entry.

If a Mars entry is considered, these shock tunnels (TH2 and HEG) might be too low in pressure to be representative since the flow is expanded in a nozzle to reach higher Mach numbers. Usually, significant dissociation and ionization levels can be present under reservoir conditions attainable in shock tunnels and this results [21] in a free stream of different energy and composition than the desired ones (frozen flow). Due to this issue, these facilities are more adapted to Reynolds-Mach number simulation than to chemical kinetics. As a consequence, the development of such a facility for Mars entry should be envisaged.

For the time being, investigations on chemical kinetics could be performed in university laboratories:(i)for CO₂ dissociation at CORIA (but very low pressure);(ii)at ICARE with PHEDRA that can run for Mars atmosphere: measurements of population excited states, ionization, vibrational, and electronic temperature;(iii)LAEPT with ICP plasma torch;(iv)IRS for plasma dissociated and temperature measurements.

Another possibility for the study of chemical kinetics during a Martian entry would be to use a facility from the ISC. The available shock tubes and tunnels, working with a CO₂ environment, are the following:(i)UT-1M shock-tube from TSAGI in Zhukovsky;(ii)VUT-1 from MIPT in Moscow;(iii)U-12 from TSNIIMASH in Korolev.

VUT-1 is the most attractive since it is used for chemical kinetics while the two others are dedicated to force measurements and aerothermodynamics. This shock tube can investigate the kinetic data of nonequilibrium dissociation and recombination processes and other chemical reactions. It is designed for Mach numbers from 5 to 25 and allows investigation of a wide range of experimental conditions. A velocity between 4 and 8 km/s can be reached during experiments with a CO₂-N₂-Ar mixture. This facility was retained for the ESA CO₂ TRP study [13] and has provided significant results using emission spectroscopy, absorption spectroscopy, and microwave interferometry to investigate chemical kinetics, thermal relaxation, and electron densities. This facility has looked at realistic velocity (enthalpy) and pressure and has provided the first European electron density measurements in a shock tube.

2.2.3. Radiation and Ionization

There are several European facilities that can be used for investigating radiation and ionization during Mars entry. Among them, the following can be cited.(i)For CO₂ (and air) dissociation at CORIA (but at low pressures) [36].(ii)At ICARE with PHEDRA that can run for Mars atmosphere, measurements of population excited states, ionization, vibrational, and electronic temperatures can be carried out.(iii)IRS facilities for plasma dissociation, temperature measurements, and radiation.(iv)ICP plasma torch at LAEPT for plasma emission [37].(v)MESOX at PROMES is mainly used for catalysis investigation, but this facility has some potential for radiation investigations.

In ISC, the following capabilities are available for investigating radiation and ionization during Mars entry.(i)Plasma Hall accelerator at HTMI that is a powerful facility for radiation investigation.(ii)VUT-1 at MIPT for radiation and ionization.(iii)Measurements of electron and ion concentrations in hot-shot IT-2 at TSAGI.

Using the facilities available in Europe, radiation studies are well covered for a Mars entry except the gap due to the stop of TCM2 shock tube. Few studies have been carried out for ionization investigations related to CO₂ plasma flows; however, this might be feasible using the IT-2 hot shot at TSAGI.

2.2.4. Turbulence

On this point, there is really a lack of aerothermodynamics capabilities in Europe related to a Mars entry. From the inputs provided during this review, the only facility capable of simulating turbulent flows for a CO₂ environment is Longshot at VKI. This facility is far from being able to cover a whole Mars trajectory, while turbulence assessment during Mars entry is really a key issue [38] for the design of the heat shield. In ISC, the shock-tunnel UT-M1 from TSAGI is capable to simulate transitional and turbulent flows.

If the entry of a large vehicle into Mars atmosphere has to be prepared, there is really a gap in turbulent flows. Another issue is the presence of the ablative TPS that has a strong impact on turbulence due to the blowing of pyrolysis gas during entry. This has a complexity when assessing the turbulence onset that cannot be determined with a critical Reynolds number for a smooth surface. Both capabilities of Longshot and UT-M1 are not able to cover a Mars entry. To fill this gap, some modifications of existing capabilities such as F4, SIMOUN, LBK, and SCIROCCO should be explored. The flat plate model used in SIMOUN may be tripped to turbulent flow in its present configuration and, in the short, term may offer the best potential for surface effects studies.

For the ExoMars programme, tests are being undertaken in DLR’s TMK and H2K facilities with smooth and rough walls. Although Mach number is only just hypersonic, Reynolds numbers are sufficiently high for both natural transition and roughness-induced bypass transition studies. Nevertheless, truly high-enthalpy high Reynolds number flows cannot be simulated in Europe as stated above and this leaves rather a large space for extrapolation to flight conditions from CFD verification studies.

2.2.5. Dust Particles

The Martian atmosphere is always dust loaded; the amount of loading is temporarily changing. With a probability that depends on the season, a local dust storm can grow in a few days and becomes a global storm in only few weeks (most likely during the summer in the southern hemisphere). The planet is thereby enveloped much or all in a dense shroud of dust. As a consequence, the presence of dust particles in the mid-latitudes atmosphere has to be accounted for the assessment of erosion and potential overheating during Mars exploration missions. Studies with dust particles have been performed in the frame of the Mars Premier Programme at VKI [39] and ESA TRP [40]. The extrapolations, done in the frame of an ESA TRP project [40], lead to a recession of 1 mm for a clear day up to 6 mm for the worst case.

In Europe and the ISC, the following facilities can operate using dust particles and CO₂ atmosphere:(i)SIMOUN (ASTRIUM-ST);(ii)L2K (DLR);(ii)Minitorch (VKI);(iv)UT-1M (TSAGI).

SIMOUN, due to the recent developments, is particularly adapted to Martian reentry simulation as it can work in CO₂ environment with a powder-seeded flow to simulate hydroerosion during Mars entry. Some tests have been performed in the frame of ExoMars in stagnation point configuration for heat-fluxes higher than 1.3 MW/m². Tests have also been performed at DLR in L3K which has also been significantly upgraded for this purpose. Two types of particles were injected in the flow: SiO₂ and Al₂O₃. The free-stream velocity of the SiO₂ particles was 1987 m/s while the one of Al₂O₃ was 1903 m/s. The deceleration depends on particle type and size. Results obtained in LBK show a heat flux decrease of 10% at the stagnation point when the flow is loaded with particles (may be due to less surface catalysis).

Concerning ISC facilities, an investigation of the Martian dust-loading effects was performed in the frame of ISTC [17]. During this project, influence of solid particles of various size and different composition on heat exchange at the stagnation point of blunted body was studied. For the first time, the distribution of particles concentration in the compressed gas layer (behind the shock wave) was experimentally investigated near a body surface. For this study, the UT-1M facility from TSAGI was used in the Ludwieg regime (), with air as test gas.

Experimental measurements show that the velocities of particles did not exceed 2000 m/s which is far to be representative of a Mars entry (beyond 3 km/s). The particles are seeded in the plasma flow and therefore cannot be injected with higher velocity. Due to this technical restriction, it will be difficult to go beyond this velocity (2000 m/s) for the time being.

2.3. TPS Qualification

For TPS qualification of materials in a CO₂ environment, several points have to be accounted for. First, the ground test has to reproduce Martian entry conditions in terms of heat flux, enthalpy, and pressure. It means that the facility has to reach a heat flux up to 2 MW/m² for a large vehicle [38], this for a static pressure below 10 mbar (stagnation pressure ~0.1 bars). It is also important to look at the shearing, roughness, and blowing of materials as well as to take into account the presence of turbulence during entry as it can considerably increase the heat flux. Moreover, the design of the TPS depends on the flight path angle since the maximum heat flux to be endured by the TPS depends on this parameter. So, it is important to take into account the flux profiling as a function of time during entry. In addition to that, the facility has to provide the capabilities to test materials for stagnation conditions and to qualify TPS assembling and joints.

Among the existing European facilities, the ones which can be used for TPS testing in a CO₂ environment are(i)SIMOUN (ASTRIUM-ST);(ii)LBK (DLR);(iii)PWK’s (IRS);(iv)MESOX (PROMEX);(v)Plasmatron (VKI); (vi)SPES (UNINA).

The main capabilities of some European facilities usable for TPS testing in a CO₂ environment are summarized in Table 3. SIMOUN is well adapted to blunt body planetary entries needs and has already been used for the qualification process of many probes heat shields, like OREX, BEAGLE2, ARD, and HUYGENS. The facility can run for two kinds of configurations: stagnation point and flat plate. For a CO₂ environment, it can reach a heat flux of 1300 KW/m² for a stagnation point configuration and up to 700 kW/m² for a flat plate configuration. Moreover, TPS testing can also be done in a dust-loaded flow. Some results with alumina particles have already been obtained.

DLR facility L3K is able to simulate heat flux up to 4 MW/m² in air high-enthalpy flows (up to 25 MJ/kg), but the extension to CO₂ requires a large effort on safety grounds (CO treatment). Since, in the stagnation point configuration, the performance of SIMOUN decreases from 2.5 to 1.3 MW/m² from air to CO₂, a similar behaviour for LBK can be expected, with a maximum heat flux that should be close to 2 MW/m² with CO₂ (250 to 650 kW/m² was used in CO₂ and Martian dust TRP’s in the lower power L2K). L3K can run for two configurations: stagnation point and wedge. Like SIMOUN, it is also possible to inject particles in the flow to simulate the effects of the dust on TPS material.

IRS PWK’s can reach heat-fluxes characterizing a Mars entry; however, these facilities are quite low in pressure. VKI Plasmatron can be also a good alternative to perform TPS validation as it can reach quite high heat flux, with a pressure fitting the conditions required. MESOX at PROMES could be also used for material validation as well as SPES from UNINA.

Another possibility for TPS testing would be to use a facility from the ISC community. The plasma Hall accelerator of HMTI is able to test heatproof materials and is working with CO₂, but there is no available information about its technical features for CO₂. Ablation tests and catalysis studies can also be performed at IPM Moscow [41]. Characteristics are available for the IPG-4 Plasmatron, located at IPM. It can reach a heat flux of 2 MW/M² and a pressure from 0.01 bars to 0.2 bars, with an enthalpy up to 40 MJ/kg for a stagnation point configuration and a CO₂ atmosphere. It has already been used for catalycity experiments in CO₂ under ESA TRP in the early 90’s.

From the review, it appears that European facilities are sufficient to validate a material for a Mars entry vehicle. TPS assembling tests can be performed in SIMOUN or L2K (laminar only). Since the stagnation point pressure during Mars entry is much lower than 1 bar, the existing facilities should be sufficient for ablation tests and material qualification. Note however that cold smooth wall fluxes and shear need to be distinguished from hot rough wall fluxes and shear during numerical rebuilding of the turbulent plate flows used for the qualification of the conical/expansion corner TPS regions.

2.4. Descent

An important issue of Mars missions is the descent into the atmosphere. After the breaking of the vehicle during the entry, the descent of the capsule occurs in a tenuous atmosphere. Since Mars atmosphere is not perfectly known, the descent can occur in a cold or hot spot and variations of density can shorten the descent time endangering the mission success. Usually, descent modules use two parachutes, a drogue and then a main parachute. The testing of the descent system is important to guarantee the mission; however, for the time being, there is no facility in Europe allowing the testing of parachute for Mars entry.

If an inflatable device is used, the problem is more complex since there is also no ground testing for simulating experimentally inflation at high altitude for Mars and Earth entry conditions. In this case, the failure of the inflatable device can lead to an unsuccessful mission. This was more likely the cause IRDT-2R failure during its mission [42, 43].

2.5. Summary

To summarize the review for Mars entry, some existing gaps have been identified in the capabilities of the European facilities:(i)a shock tube for the chemical kinetics;(ii)a facility for the testing of parachutes;(iii)improving experimental hypersonic capabilities for turbulence simulation;(iv)adapting existing facilities such as SCIROCCO, for aerothermodynamics studies and TPS validation in CO₂ flows, would be an asset, but perhaps at large cost. The performance reached by facilities like F4 and LBK is not fully representative of a Mars entry (too low in pressure or in Mach number);(v)need to pursue the effort on measurement techniques (DLAS, holographic interferometry);(vi)dust erosion: particle velocity is not representative of Mars entry.

Among these different gaps, the two most critical points are the lack of a shock tube for kinetic studies and the need to improve hypersonic capabilities for turbulence simulation.

3. Mars Ascent

In the frame of a sample return mission to Mars, the sample collected into Mars soil has to be sent back to Earth using the return module orbiting around Mars. For this objective, the lander shall carry a return vehicle equipped with a propulsion system. The launcher capability has to be ensured after a long trip from Earth to Mars. Additionally, the propulsion system has to support the high g-loads encountered during the Mars entry. The robustness of the on-board small launcher will be one of the issues for the mission success. An example of Mars ascent trajectory is shown in Figure 4. From this picture, it is clear that, due to the velocity range, the ascent vehicle will not be affected by thermochemistry effects before entering in the rarefied regime.

Another point is to ensure the launching capabilities of this propulsion system which shall ignite in a CO₂ atmosphere, at low pressure, less than 10 mbar, and at temperature in between the day and night Martian temperatures.

Among the European test facilities that could simulate, in close conditions to the Martian environment, the ignition of a propulsion system, the CAEPE’s facility SESAME is attractive since it is capable to simulate the pressure range corresponding to the working conditions of a Martian ascent trajectory. A potential improvement would be to adapt this facility to a CO₂ atmosphere. This facility has already been used for the testing of the ATV propulsion system.

An asset of SESAME is the capability to test a full size engine and to vary the pressure during the test. Conjointly, additional capabilities, existing in other research centres, could be used. According to the inputs provided for this paper, some additional tests could be performed at ISL to assess the small launcher stability along the ascent trajectory. Since real gas effects will not influence the ascent vehicle, usual facilities can be used to investigate its aerodynamic, keeping in mind the low pressure of the Mars atmosphere. As a consequence, facilities capable to run for high-altitude Earth conditions shall be useful for the validation of an ascent vehicle trajectory.

From the European facilities reviewed, the followings are of interest for a Mars ascent vehicle if we consider its aerodynamics and stability:(i)DLR wind tunnels VMK and TMK;(ii)FOI wind tunnels;(iii)HHK Ludwieg tube from HTG;(iv)ISL shock tubes STA and STB;(v)ONERA wind tunnels S2, S3, and S4;(vi)TU Braunschweig Ludwieg tube;(vii)UMIST facilities;(viii)VKI wind tunnels.

Among these facilities, ISL shock tubes can operate at low pressures corresponding to an Earth altitude of 70 km as shown in Figure 5. They could cover a large part of a Mars ascent trajectory. From the different facilities listed above, even if performance maps have not been provided, a Mars ascent trajectory should be fully covered (with more likely some duplication of capabilities). To refine this analysis, more details on a Mars entry trajectory would be necessary. For this, the evolution of Reynolds number, Mach number range, and stagnation pressure along the trajectory would be required.

Since one of the main problems of a launcher is the ignition, this point shall be a key issue for such a propulsion system. A potential activity could be to upgrade a facility like SESAME to test the engine working conditions in a CO₂ environment.

4. High-Speed Earth Reentry

A sample return mission involves a direct high-speed Earth reentry with a velocity higher than 10 km/s and high heat fluxes (more than 8 MW/m²) at peak heating as shown in Figure 1. The consequence is that the level of heat flux will be around one order of magnitude higher than for an orbital entry for which most of European facilities have been designed. The maximum stagnation pressure and the stagnation pressure at peak heating for the trajectories plotted in Figure 1 are listed in Table 4; the distributions of stagnation pressure are shown in Figure 3.

Table 4: Maximum stagnation pressures for an EVD mission [6].

Trajectory
Stagnation pressure at max. heat flux (Pa)
Maximum stagnation pressure (Pa)

E1
70396
131500

E2
138037
277339

E3
48534
80300

E4
26687
41180

Figure 3: Stagnation Pressure for EVD mission [6].

Figure 4: Typical Mars ascent trajectory [6].

Figure 5: Capabilities of ISL shock tubes STA and STB (credit ISL).

For a high-speed reentry, phenomena like ionization, ablation, and radiation that are of second order for an orbital entry cannot be neglected: radiation level is around several MW/m² as shown in Table 5 where convective and radiative heat-fluxes at peak heating are listed for different entry trajectories (see Figure 1). TPS ablation [5] can be up to 1 cm with a capsule shape change that might affect its stability. Ground tests play an important role for the understanding of these phenomena, for the validation of analysis tools and for the development and qualification of hypersonic vehicles.

Table 5: Maximum heat fluxes for EVD mission [6].

Trajectory
Convective flux kW/m²
Radiative flux kW/m²
Total flux kW/m²
Total heat load MJ/m²

E1
11500
7500
18800
106.9

E2
15700
18100
33800
178.3

E3
9350
4550
13900
243.2

E4
7000
1900
8900
154.6

4.1. Chemical Kinetics

Shock tubes are attractive for investigating chemical kinetics and thermal relaxation. As a consequence, in the perspective of a high-speed Earth reentry, such facilities have to be able to reproduce entry trajectory with high velocities: around 12.6 km/s for Stardust. In order to improve the knowledge on chemical kinetics, several shock tubes (and tunnels) are available in Europe, among them we can cite(i)HEG at DLR Göttingen;(ii)TH2 at RWTH Aachen;(iii)LONGSHOT at VKI.

Other facilities exist at GDL and UMIST in UK, at TU Braunschweig and HTG in Germany and Institut Saint-Louis in France. Unfortunately, most of these facilities have been developed for suborbital entries [8] as shown in Table 6 and Figure 6 and do not fit with the flow conditions characteristic of a high-speed Earth entry. In fact, TCM2 that was previously available at IUSTI Marseille was the most attractive but this facility has been closed for safety reason: indeed, it was broken when testing superorbital reentry conditions at just over 9 km/s.

Table 6: Capabilities of some available European installations for investigating chemical kinetics and aerothermodynamics related to Earth reentry.

Name
Flow regime
Run time
Test section (m)
Mach number
Re 10–5 (1 m)
(K)
(MPa)
Measured quantities
Use in projects

F4 (ONERA)
High enthalpy
Up to 200 ms
0.7 to 1.2
6 to 20
0.06 to 23
2000 To 7000
20 to 50
Forces, moments, pressures, heat transfer, Schlieren, LIF, DLAS
Hermes, MSTP, ARD

HEG (DLR)
High enthalpy
Short Duration ~1 ms
0.41 to 0.88
~8 4.7–6.2 km/s conical nozzle
2 to 6.7
7000 To 9900
35 to 90
Heat transfer and pressure, Schlieren and shadowgraph, holographic interferometry, DLAS, LIF
Hermes, Hope, MSTP, ARD, TETRA

TH2 (RWTH)
Cold and hot hypersonic
2 to 10 ms
0.586
6 to 12 (conic.) 7 (contoured)
2 to 160
1500 to 7500
6.5 to 80
Pressure and heat fluxes, infrared thermography, forces and moments, Schlieren
Hermes, MSTP, FESTIP

Figure 6: Capabilities (Mach/(Re)1/2 as function of Mach number) of different facilities (F4, HEG, TH2) comparing to suborbital entries of different vehicles [8].

Due to these limitations in Europe, the only alternative is to develop a new facility or to use a facility from ISC. These facilities have already been used for studies on high-speed Earth reentry in the frame of the ISTC programme [24]. For such purpose, the following facilities could be attractive since they are running with air and capable of reproducing severe entry conditions:(i)VUT-1 from the Moscow State University;(ii)ADST from TSAGI Zhukovsky.

Due to the measurement techniques already available and the available expertise of the operating team, VUT-1 shock tunnel is attractive but the velocity within the tube cannot be higher than 9 km/s, which is a little bit weak for an Earth superorbital reentry. As far as chemical kinetics are concerned, the facility fitting the best requirements of an EVD seems to be the ADST shock tunnel from TSAGI. This facility allows the investigation of ionisation/radiation processes behind a shock wave from 8 up to 14 km/s. ADST has been used in the frame of an ISTC project [24]; however, few details are available on this facility which can be used to measure electron concentration and temperature behind a shock wave and radiation intensity.

For superorbital entries, an alternative could be to use Australian facilities (or others); several shock tunnels are available at the University of Queensland providing high velocities:(i)X1 free piston-driven expansion tube: up to 10.8 km/s;(ii)X2 free piston-driven expansion tube: up to 10.3 km/s;(iii)X3 expansion tube: up to 10 km/s.

These three facilities can reach velocities in the range of superorbital Earth re-entry; they have been successfully used in the frame of an ESA TRP [19, 33] focusing on Earth high-speed reentry (and Titan entry). Moreover, since there is no equivalent in Europe for the time being, they could be used alternatively or conjunctly to ISC facilities. However, when running at 10.3 km/s in an expansion tube like X2, the free-stream pressure is 0.033 atmosphere and Mach number 7.3. As a consequence, expansion tubes could be too low in pressure to really simulate EVD reentry conditions.

4.2. Aerothermodynamics

The flow around a sample return capsule is characterized by high levels of ionization and radiation. Other important issues are turbulence and ablation which are closely linked. All these phenomena have some consequences on flow topology (shock standoff, boundary layer) and heat-flux level during reentry.

As for chemical kinetics, the best way to investigate ionization and radiation would be a shock-tube fitting with superorbital reentry conditions. For an Earth return capsule, ablation is a key issue (one centimetre recession for Stardust). Related to ablation and to the blowing in the boundary layer, turbulence is another issue since it can completely counterbalance the blockage due to the blowing effect [44].

There is no facility capable of reproducing all these phenomena in Europe for the time being. The facilities that might have performances close to those required are the following:(i)The PWK’s facilities at IRS (sufficiently high heat flux and enthalpy but low pressure);(ii)LBK at DLR with its new nozzle (it can reach heat fluxes of 10 MW/m² at 1 atm stagnation pressure but flow conditions have to be confirmed);(iii)SCIROCCO after adaptation (measurements at the throat to cover EVD reentry trajectory in terms of heat flux and pressure);(iv)SIMOUN is going to be extended for reaching heat flux up to 4 MW/m²;(v)MESOX at PROMES and VKI Plasmatron are of interest for investigating radiation.

Most of these facilities (excepting IRS PWK’s which were used for SEPCORE TPS studies for a comet return capsule) have not yet been tested for EVD reentry conditions. Many of them need to be upgraded for reaching heat-flux levels representative of an EVD re-entry; additionally flow conditions are not known and might not be in the correct ranges of pressure and Mach number. At the exception of MESOX (and may be VKI Plasmatron but this has to be confirmed) that can reach high radiative heat-fluxes, none of the other facilities has the capability to simulate flows with high levels of radiation. It is not demonstrated that these facilities can simulate flow conditions representing high-speed Earth reentry. When considering the flow aerothermodynamics of an EVD re-entry, it is clear that a huge gap has to be covered. This will request an extensive utilization of the existing facilities and a strong effort in analysis of flow conditions and numerical rebuilding. With its current capabilities, Europe has not the complete capability to validate the aerothermodynamics of a sample return capsule.

In ISC, the following facilities are of interest for investigating the aerothermodynamics of an EVD capsule. In the frame of ISTC [24], ablation tests were performed using IPG-4 Plasmatron at IPM Moscow and U-13 Plasmatron from TSIINMASH. This gave the opportunity to investigate the boundary layer of an ablative material. If the hypersonic flow corresponding to an EVD reentry is considered, no facility capable to reproduce such conditions has been found in the ISC.

4.3. TPS Testing

For TPS testing of materials to be used for high-speed Earth reentry, three points are of importance. (i)Facilities have to be able to reproduce convective and radiative heat-fluxes.(ii)Testing has to be done for turbulent conditions since the flow at the leading edge of the capsule could be turbulent.(iii)Ground tests have to provide the capabilities to test material for stagnation conditions, and to qualify TPS assembling and joints.

If an EVD reentry is considered, the retained facility has to reach a heat flux of at least 8 MW/m² and a stagnation pressure up to 0.5 atm. The characteristics of European facilities which can be used for TPS testing of an EVD capsule are summarized in Table 7. The European facilities that can reach the relevant range of heat flux are(i)GLADIS at the Max Planck Institute in Garching;(ii)JP 200 (ASTRIUM-ST);(iii)LBK at DLR;(iv)PWK 1-2-4 (IRS);(v)SCIROCCO (CIRA).

Table 7: Characteristics of facilities for TPS testing at high heat-fluxes.

Name
Heat-flux (MW/m²)
Stagnation pressure (bar)
Running time
Model size (mm)
Measurements
Remarks

JP200
5–25
1.5–9
60 s
Flat plate: 200 40 mm Thickness: 10–25 mm
Recession rate, heat flux, pressure and surface temperature
Turbulent flow. Test of tiles, gaps, and steps. Dynamic and static

SCIROCCO
0.26–3 Throat: Up to 21
0.005–0.11 Throat: up to 1.5
1800 s20 s
800 For 20 mm MW: 25 For 100 mm:  8 MW
static pressure, stagnation pressure, temperature, heat-flux
TPS assembly

PWK1-2-4
Up to 15
20–5000 Pa
Max 3 h
320
Heat flux, pressure, oxygen partial pressure, dissociation degree, Mach number
Material characterization, high-enthalpy entry simulations, heat shield testing

GLADIS
4–45
Near vacuum conditions
Pulse of 1 ms, to 45 s pulses per hour
70
Heat-flux, temperature
Test of large components. Testing of full-scale ITER divertor targets. Hydrogen beam facility

LBK
10
Up to ~1 bar with short nozzle
<1800 s
?
Pressure, temperature, heat flux, dissociation, emission
Aerodynamic heating studies, TPS qualification

GLADIS [45] can reach very high heat-fluxes (up to 55 MW/m²) and is used to test large elements of ITER facility such as tiles of CFC (carbon fibre reinforced composite). However, GLADIS operates at nearly vacuum conditions and the use of this ground test for reentry applications would require some upgrades and modifications of the facility. Additionally, this facility runs with He and H₂. Tests with air are not possible due to the presence of oxygen. Testing with nitrogen would be possible at higher pressure but at reduced heat-fluxes. The main interest of this facility is its capability to reproduce high radiative heat-fluxes. GLADIS is, indeed, one of the rare European ground tests (with may be MESOX and VKI Plasmatron) able to reach the level of radiative heat flux characterizing an EVD reentry. However, for such an objective, the facility has to be able to operate with air at around 0.5 atm which is not the case.

JP200 can reach the heat-flux range for an EVD reentry and is able to qualify tiles, gaps, steps, and seals for a capsule TPS. It is an open facility, and the stagnation pressure cannot go below 1.5 atm. This means that a TPS qualification with this facility under these conditions would be oversized. Other advantages of JP200 are its capabilities to simulate turbulent flows and to account for the dynamic aspect of the entry. Concerning IRS PWK1-2-4 facilities, they can reach heat-fluxes up to 15 MW/m² (the peak heat flux for Stardust was below this level) which could be sufficient for some EVD reentry trajectories (at least for the high-altitude part), but for a very low pressure. SCIROCCO in its standard configuration is not able to cover an EVD reentry trajectory. A possibility would be to move the test model near the nozzle throat, and then most of the points of Table 5 could be tested in terms of stagnation pressure and heat flux. LBK has a new nozzle and can now reach 10 MW/m². However, the corresponding flow conditions are not fully known.

Figure 7 compares the performance envelopes of some European facilities for TPS testing and Stardust reentry trajectory. In this figure, it is clear that only the end of the reentry at lower altitudes can be duplicated experimentally; this corresponds to the low enthalpy range of the reentry trajectory. From the material gathered in this paper, it appears that, among the available facilities, the most capable of reproducing the TPS conditions corresponding to an EVD trajectory are PWK4, LBK (but capabilities of LBK need to be confirmed), and SIMOUN. JP200 is too high in pressure, but could be used for reaching the level of heat flux while SCIROCCO would need to be modified to cover EVD trajectory requirements.

Figure 7: Stagnation point envelopes of some European facilities for TPS testing and reentry trajectory of Stardust (for a European standard model of 50 mm at the exception of JP 200).

However, there is a critical issue for the TPS qualification: the radiative heat flux. For such an entry, it is an important phenomenon that cannot be skipped. Today, there is no facility in Europe capable of reproducing both convective and radiative heat flux for an EVD trajectory. The most performing facility for radiation in air environment is, for the time being, MESOX from PROMES. Since GLADIS cannot operate with air, an alternative is to use a facility from ISC or to upgrade an existing facility.

If ISC is considered, the following facilities are relevant for the qualification of an EVD capsule TPS:(i)plasma Hall generator at HMTI (Minsk);(ii)IPG-4 at IPM Moscow;(iii)U13 Plasmatron at TSIINMASH;(iv)U-15T-2 arc-jet at TSIINMASH.

Among these facilities, U-15T-2 is a powerful arc jet of 40 MW. The plasma Hall generator from Minsk can generate high radiative and convective heat-fluxes. This facility is unique and fits very well with the requirements of an EVD reentry.

An alternative would be to use lasers (as in GLADIS) to reach high radiative heat-fluxes. They can be used for initial material screening tests and spallation tests, as done during the Galileo project. A potential upgrade (or a new facility to be built) would be to combine an existing arc heater with a laser to cope with the requirements in terms of convective and radiative heat-fluxes for an EVD reentry.

4.4. Summary

To summarize the survey, some existing gaps have been identified in the capabilities of European facilities to cover a high-speed Earth re-entry.(i)A shock tube for the chemical kinetics (actually the development of a kinetic shock tube has been initiated).(ii)A strong effort has to be done for aerothermodynamics using and/or upgrading existing facilities for nonequilibrium flows, ionization, turbulence, radiation, and ablation. A large research program will be needed to fit the requirements of an EVD re-entry.(iii)For the TPS material, Europe has the means to validate a material for high-speed reentry but not in all required conditions at the same time; however, a gap exists for radiation. A new facility or the upgrade of an existing facility will be necessary to achieve that. An alternative would be to use a facility from the ISC.

5. Assessment of Dynamic Stability

Another issue for exploration missions is the stability of the capsule during entry and descent: not only static stability has to be ensured but also dynamic stability. During the different regimes of the entry and descent, the stability of the capsule has to be guaranteed for the mission success and there is no phase of the flight where stability can be taken for guaranteed.

At very high altitude, in the transition regime from free molecular to continuum, many capsules are statically unstable but the moments are sufficiently small that they can be counteracted with a reaction control system or by applying sufficient spin. At lower altitudes, the real gas effects can affect the stability of blunt bodies. This is particularly the case for Mars entry in between Mach numbers 16 and 30 for a 70° sphere cone where the sonic line moves from the edge to the nose of the capsule, while on the windward side it remains attached to the edge. This induces some pressure effects and therefore static instability. This phenomenon was noted in Viking ballistic range tests and flight data [46] and rediscovered in the CFD predictions and flight data of Pathfinder [47]. In the low supersonic Mach number range, the static pitching moment coefficient of many capsules decreases with decreasing Mach number.

Ablation and resulting shape changes can also influence stability by altering mass properties, trim, and spin rate. This point is more relevant for a high-speed Earth reentry than for a Mars entry. TPS recession for a Mars entry is small (from 1 to 3 mm), and the shape does not change when considering the vehicle diameter, while, for an EVD capsule, recession can be up to 1 cm for a much smaller size of the capsule.

Dynamic instability affects all blunt bodies. Since this occurs after the peak in dynamic pressure, the decreasing dynamic pressure combines with the decreasing pitching moment coefficient to produce an amplification of the angle of attack oscillations. This phenomenon appears at low hypersonic Mach number, around Mach 4 for the first effects, and becomes more and more critical with the decrease of the Mach number, while the influence of the wake on the rear shell causes pitch damping coefficients to become destabilising (from Mach 2.5 to 0.8). This phenomenon is difficult to understand. Some progresses in the understanding were made in the early 70’s by Jaffe [48, 49]. According to this author, dynamic stability is produced by the wake hysteresis even at small angle of attack. The corresponding Strouhal number of the phenomenon is very small, around 0.002, and might be produced by some pressure effects on the rear part of the capsule [50].

For a Mars entry, dynamic stability has to be ensured until the parachute deployment which occurs around Mach 1.8. If a high-speed Earth reentry is considered, this problem is more critical. Due to its small size and ultrahigh reliability requirements, the return capsule might have to brake and descend in the atmosphere without parachute [51]. This particular aspect of the system has some consequences on the capsule design. Without parachute, the dynamic stability of the capsule at terminal velocity becomes an important technological issue of the mission [52].

5.1. Facilities for Stability Studies

For this part of the survey, the facilities for stability testing in Europe, ISC, and also Australia and Canada have been accounted for. This effort has included open test ranges and ballistics tunnels.

Free flight tests can be carried out in open ranges or in ballistic tunnels; among the facilities reviewed for that, three provide this capability:(i)ballistic tunnel at CEEM Valcartier in Canada;(ii)free flight test in open range at ISL;(iii)Woomera test range in Australia.

All these different facilities can be used for testing free flight models. The ballistic tunnel of Valcartier runs with air only. ISL free flight range has already been used for AURORA technology activities [53] and is currently in use for ExoMars tests. In this facility, capsule models equipped with sensors are shot with a gun and all flight parameters are measured. Woomera test range is mainly used to test sounding rockets and full size reentry demonstrators [54].

A lot of classic facilities (wind tunnels, shock tubes, and tunnels) are available in Europe for investigating stability. The following ground tests are relevant for stability studies.(i)TMK tunnel at DLR (free and forced oscillations).(ii)Wind-tunnels TM500 and HYP500 at FOI (free and force oscillations).(iii)ISL supersonic wind tunnel.(iv)ISL shock tubes (above Mach 3 in air, can run for CO₂).(v)ONERA wind tunnels in Modane (France).(vi)Shock-tube facility with discharge chamber at UMIST.(vii)VKI S1 wind tunnel (free to tumble mounting system).(viii)University of Oxford CO₂ suck-down facility (free oscillation, used for Beagle2).(ix)In the ISC, the following tunnels could be used:(x)ITAM hypersonic wind-tunnel T313;(xi)TSAGI hypersonic wind-tunnel T-116;(xii)TSIINMASH gas dynamics units TT-2, U-15T-2 and wind-tunnel U-306.

As far as dynamic stability is concerned, the problem with wind tunnels is the presence of the model support that does not allow duplicating exactly the model behaviour in flight. An alternative is to force the oscillation of the model as done in some facilities such as S1 at VKI. Instead of wind tunnels, the use of shock tubes could be very attractive as demonstrated at ISL. A reduced model is maintained in the tube by some filaments that are cut at the beginning of the run, and then the model is in free flight inside the tube. This technique might be very attractive to investigate dynamic stability for Mars entry since a shock tube can be operated with CO₂ at low pressure. Another possibility to get rid of the model support is to use the electromagnetic suspension as done at the University of Oxford in the low-density facility [55].

Other ISC facilities for low supersonic and subsonic flows have not been included in the paper since there are a lot of similar means already available in Europe.

5.2. Assessment for Mars and Earth Reentries

For Huygens, dynamic stability was investigated in the ballistic tunnel of ISL. This facility is now closed, but since it was working with air, similar experiments could be done in free flight tests keeping the correct velocities and using the similitude in Reynolds number. Other tests for Huygens were also carried out at ARA Bedford (now closed) and at FOI. Tests could also be performed in wind tunnels as done at VKI [50] in the frame of Mars Premier. Since it is not possible to use an open range to duplicate exactly free flight conditions in Mars atmosphere, a possibility would be to use shock tubes running with CO₂. This would complete the free flight and wind-tunnel tests using CO₂ flow conditions. To date, from the available information, the only dynamic stability testing with CO₂ in Europe was carried out for Beagle2 at the University of Oxford [56].

From the results obtained for an EVD model at ISL [53], the free flight tests seem to be ideal for the investigations on dynamic stability for Earth reentry. Additionally, tests can be performed in several European wind tunnels.

From the survey, capabilities for experimental campaigns on dynamic stability appear to be very mature in Europe. The use of the existing facilities should be sufficient for sample return missions. A ballistic tunnel capable to run at low pressure would be an additional advantage but the work load required for such missions would not be sufficient to ensure a full-time activity.

6. Conclusion

In the frame of past programmes such as Hermes and X38, Europe has developed strong experimental capabilities for suborbital Earth reentry. If now, sample return missions are envisaged; the existing experimental means will not be sufficient to cover the technical requirements for such missions.

The most critical issue is the chemical kinetics: as a consequence, the development of a powerful clean shock tube has been started to cover the chemical kinetics characterizing Mars entry and Earth high-speed reentry.

Concerning the development of nonintrusive methods, progress has been done but with a low rhythm. This effort should be intensified and new approaches developed or improved with the support of university laboratories. For the aerothermodynamics of both Mars entry and Earth high-speed reentry, before building a new facility, the existing ones should be upgraded and the experimental efforts increased since the potential of the existing facilities is far to have been fully exploited. An effort will have to be done for radiation during Earth high-speed reentry: a facility should be upgraded to cover this point.

Surprisingly, the Mars ascent is quite well covered with the existing ground tests. Here, the heritage from military activities related to missile applications is an advantage.

Dynamic stability is also well covered particularly for Earth reentry. For Mars entry, the Reynolds similitude can be used and tests performed in Earth atmosphere or a ballistic tunnel built. However, such a facility has a huge cost and will difficulty live with only the support coming from space missions.

Nomenclature

M: | Mach number
Re: | Reynolds number
T₀: | Stagnation temperature (K)
P₀: | Stagnation pressure (Pa).

Acronyms

ARD: | Atmospheric reentry demonstrator
ATV: | Automated transfer vehicle
CFC: | Carbon fibre reinforced composite
CFD: | Computational fluid dynamics
DLAS: | Diode laser absorption spectroscopy
EVD: | Earth vehicle demonstrator
ITER: | International thermonuclear experimental reactor
LIF: | Laser-induced fluorescence
TALIF: | Two-photon absorption laser-induced fluorescence
TPS: | Thermal protection system
TRP: | Technology and Research Programme.

Acknowledgments

The authors are grateful to ESA for its support provided in the frame of Contract no. 20932/07/NL/PA. They would like to thank also all the participants to the Workshop on Facilities held at ESTEC on March 28, 2008 and all the experimentalists from Australia, Europe, and Russia who have provided the inputs for this paper. The results of this paper have been partially presented at the 6th European Symposium on Aerothermodynamics for Space Vehicles held in Versailles in November 2008.

References

Technologies for Exploration, “Aurora Programme Proposal: Annex D,” ESA SP-1254, 2001

C. Y. Tang and M. J. Wright, “Analysis of the forebody aeroheating environment during genesis sample return capsule reentry,” in Proceedings of the 45th AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nev, US, January 2007, AIAA Paper 2007-1207.

R. N. Gupta, “Aerothermodynamic analysis of stardust sample return capsule with coupled radiation and ablation,” in Proceedings of the 37th Aerospace Sciences Meeting, Reno, Nev, US, January 1999, AIAA Paper 99-0227.

D. Olynick, Y. K. Chen, and M. E. Tauber, “Aerothermodynamics of the stardust sample return capsule,” Journal of Spacecraft and Rockets, vol. 36, no. 3, pp. 442–462, 1999.

H.-K. Ahn and C. Park, “Preliminary study of the MUSES-C reentry,” in Proceedings of the 35th AIAA Aerospace Sciences Meeting and Exhibit, January 1997, AIAA Paper 97-0278.

CDF Study Report, “MSR Mars sample return the second aurora flagship mission,” Report CDF-16(A), ESA-ESTEC, 2003.

“Inventory of thermo-mechanical test facilities in Europe for TPS qualification,” Final study report IABG B-TA 4034, Ottobrun, Germany, 2005.

J. C. Traineau, C. Pélissier, V. M. Fomin, A. M. Kharitonov, V. I. Lapygin, and V. A. Gorelov, “Review of European facilities for space aerothermodynamics,” Tech. Rep. RT 1/06302, DMAE, ONERA, 2003.

F. K. Lu and D. E. Marren, “Advanced hypersonic test facilities,” in Progress in Astronautics and Aeronautics, p. 198, AIAA, 2002.

M. Bugel, P. Reynier, and A. Smith, “Review of European aerodynamics and aerothermodynamics capabilities for sample return missions,” in Proceedings of the 6th European Symposium on Aerodynamics for Space Vehicles, Versailles, France, November 2008, ESA SP-658.

V. Marieu, P. Reynier, L. Marraffa, D. Vennemann, S. Caristia, and F. De Filippis, “Evaluation of SCIROCCO plasma wind-tunnel capabilities for entry simulations in CO2 atmospheres,” Acta Astronautica, vol. 61, no. 7-8, pp. 604–616, 2007.

J.-M. Charbonnier, “Interplanetary and atmospheric trajectories. Focus on Mars atmospheric entries in the frame of Mars exploration,” EUROAVIA, Von Karman Institute, Rhode-St Genèse, Beljum, Nov. 5, 2002

J. Beck, “CFD validation in a CO₂ environment: synthesis report,” FGE CR012/08, Emsworth, United Kingdown, 2008.

B. Esser and A. Gülhan, “ESA/ESTEC technical research programme: CFD validation in CO₂ environment,” Final report DLR-CO2 TRP-FR, Köln, Germany, 2008.

J.-M. Charbonnier, J. Perraud, W. Dieudonné, M. Spel, and J. Couzi, “Evaluation of the aerothermal heating on the front shield of the Netlander probe during Mars atmosphere entry,” in Proceedings of the 3rd International AAAF Symposium on Atmospheric Reentry Vehicles and Systems, Arcachon, France, March 2003.

P. Papadopoulos, M. E. Tauber, and I.-D. Chang, “Heatshield erosion in a dusty Martian atmosphere,” Journal of Spacecraft and Rockets, vol. 30, no. 2, pp. 140–151, 1993.

E. B. Vasilevskii, A. V. Chirikhin, and A. N. Osiptsov, “Heat transfer to a stagnation region of a blunt body in a hypersonic gas flow with an admixture of solid particles,” in Proceedings of the 3rd European Symposium on Aerothermodynamics for Space Vehicles, (ESTEC '98), Noordwijk, The Netherlands, November 1998, ESA SP-426.

D. Ramjaun, “TC2: definition of shock tunnel test cases for gas radiation prediction in a planetary atmosphere,” in Proceedings of the International Workshop on Radiation of High Temperature Gases in Atmospheric Entry, Lisbon, Portugal, October 2003, ESA SP-533.

D. F. Potter, T. Eichmann, A. Brandis, R. G. Morgan, P. A. Jacobs, and T. J. McIntyre, “Simulation of radiating CO2-N2 shock layer experiments at hyperbolic entry conditions,” in Proceedings of the 40th AIAA Thermophysics Conference, Seattle, Wash, USA, June 2008, AIAA Paper 2008-3933.

T. J. McIntyre, T. N. Eichmann, C. Jacobs, et al., “Shock-tube testing and expansion tunnel measurements of high temperature radiating flows,” in Proceedings of the 4th International Workshop on Radiation and High Temperature Gases in Atmospheric Entry, Lausanne, Switzerland, October 2010, ESA-SP 669.

J. Lukasiewicz, “A series of monographs,” in Experimental Methods of Hypersonics (Gasdynamics), P. P. Wegener, Ed., vol. 1973, Marcel Dekker, New York, NY, USA, 1973.

A. Smith, “Aerochemistry in hypersonic flows,” Final Report FGE TR016/97, 1997.

G. Herdrich, M. Dropmann, T. Marynowski, S. Löhle, and S. Fasoulas, “Atmospheric entry simulation capabilities of the IRS plasma wind tunnel PWK3 for Mars and Venus,” in Proceedings of the 7th International Planetary Probe Workshop, (IPPW '10), Barcelona, Spain, June 2010.

G. G. Chernyi and S. A. Losev, “Problems of aerothermoballistics, radiation gasdynamics, heat and mass transfer for planet sample return missions,” Final Project Technical Report 1549-00, 2003.

M. Balat-Pichelina, J.-M. Badie, R. Berjoan, and P. Boubert, “Recombination coefficient of atomic oxygen on ceramic materials under earth re-entry conditions by optical emission spectroscopy,” Chemical Physics, vol. 291, no. 2, pp. 181–194, 2003.

H. Riascos, G. Zambrano, and P. Prieto, “Plasma characterization of pulsed-laser ablation process used for fullerene-like CNx thin film deposition,” Brazilian Journal of Physics, vol. 34, no. 4B, pp. 1583–1586, 2004.

J.-M. Desse and J.-L. Tribillon, “Real-time three-color reflection holographic interferometer,” Applied Optics, vol. 48, no. 36, pp. 6870–6877, 2009.

A. M. Keesee, E. E. Scime, and R. F. Boivin, “Laser-induced fluorescence measurements of three plasma species with a tunable diode laser,” Review of Scientific Instruments, vol. 75, no. 10, pp. 4091–4093, 2004.

A. K. Mohamed and M. Lefebvre, “Laser absorption spectroscopy to probe chemically reacting flows,” AerospaceLab, no. 1, pp. 1–12, 2009.

A. Mohamed, J.-L Vérant, J. Soutadé, P. Viguier, B. Van Ootogem, and P. Tran, “Mid-infrared diode laser absorption spectroscopy measurements in CO/CO₂ hypersonic flows of F4 and Simoun,” in Proceedings of the 6th European Symposium on Aerothermodynamics for Space Vehicles, Versailles, France, November 2008, ESA SP-659.

U. Koch, J. Riehmer, B. Esser, and A. Gülhan, “Laser induced fluorescence and diode laser absorption spectroscopy measurements of CO/CO₂ hypersonic flows of LBK,” in Proceedings of the 6th European Symposium on Aerothermodynamics for Space Vehicles, Versailles, France, November 2008, ESA SP-659.

G. D. Stancu, M. Janda, F. Kaddouri, et al., “Two-photon absorption laser induced fluorescence study of repetitively pulsed nanosecond discharges in atmospheric pressure air,” in Proceedings of the 39th AIAA Plasmadynamics and Lasers Conference, Seattle, Wash, USA, June 2008, AIAA Paper 2008-3882.

T. J. McIntyre, T. N. Eichmann, M. Mallon, et al., “The generation and measurement of high enthalpy radiating flows in a high enthalpy pulsed facility,” in Proceedings of the 3rd International Workshop on Radiation of high Temperature Gases in Atmospheric Entry, Heraklion, Greece, October 2008, ESA-SP-667.

W. Kordulla, X. Bouis, and G. Eitelberg, “Wind tunnels for space applications at DLR and ONERA,” in Proceedings of the 1st International Symposium on Atmospheric Reentry Vehicles and Systems, Arcachon, France, March 1999.

P. Boubert and C. Rond, “Nonequilibrium radiation in shocked martian mixtures,” Journal of Thermophysics and Heat Transfer, vol. 24, no. 1, pp. 40–49, 2010.

S.-Y. Hyun, N. Brémare, and P. Boubert, “Spectroscopic study of air plasma inductively coupled plasma wind tunnel,” in Proceedings of the 4th International Workshop on Radiation and High Temperature Gases in Atmospheric Entry, Lausanne, Switzerland, October 2010, ESA-SP 669.

S. Löhle, D. Vacher, S. Menecier, et al., “Measurement campaigns on Mars entry plasmas using ICP torches. Characterization by emission spectroscopy and probes techniques,” in Proceedings of the 4th International Workshop on Radiation and High Temperature Gases in Atmospheric Entry, Lausanne, Switzerland, October 2010, ESA-SP 669.

K. T. Edquist, A. A. Dyakonov, M. J. Wright, and C. Y. Tang, “Aerothermodynamic environments definition for the mars science laboratory entry capsule,” in Proceedings of the 45th AIAA Aerospace Sciences Meeting, January 2007, AIAA Paper 2007-1206.

O. Chazot and E. Boschek, “Plasmatron facility for combined particle-impact and aero-heatingtests,” AIAA Paper 2003-4040, 2003

Anon, “Experimental and theoretical study of Mars dust effects,” Summary Report MDUST-HPS-RP-001, HPS, Braunschweig, Germany, 2007.

A. F. Kolesnikov, I. S. Pershin, S. A. Vasil'evskii, and M. I. Yakushin, “Study of quartz surface catalycity in dissociated carbon dioxide subsonic flows,” Journal of Spacecraft and Rockets, vol. 37, no. 5, pp. 573–579, 2000.

D. E. Boutamine, L. Marraffa, F. Mazoué, and P. Reynier, “IRDT trajectory: reconstruction of flight data,” in Proceedings of the European Space Research and Technology Centre, ESA, Noordwijk, The Netherlands, November 2005.

P. Reynier and D. Evans, “Postflight analysis of inflatable reentry and descent technology blackout during Earth reentry,” Journal of Spacecraft and Rockets, vol. 46, no. 4, pp. 800–809, 2009.

R. N. Gupta, “Aerothermodynamic analysis of stardust sample return capsule with coupled radiation and ablation,” AIAA Paper 99-0227, 1999

H. Greuner, B. Boeswirth, J. Boscary, and P. McNeely, “High heat flux facility GLADIS: operational characteristics and results of W7-X pre-series target tests,” Journal of Nuclear Materials, vol. 367–370, pp. 1444–1448, 2007.

D. B. Kirk, P. F. Intrieri, and A. Seiff, “Aerodynamic behavior of the Viking entry vehicle—ground test and flight results,” Journal of Spacecraft and Rockets, vol. 15, no. 4, pp. 208–212, 1978.

P. A. Gnoffo, R. D. Braun, K. J. Weilmuenster, R. A. Mitcheltree, W. C. Engelund, and R. W. Powell, “Prediction and validation of Mars pathfinder hypersonic aerodynamic database,” Journal of Spacecraft and Rockets, vol. 36, no. 3, pp. 367–373, 1999.

P. Jaffe, “Non-planar tests using the wind tunnel free-flight technique,” Journal of Spacecraft and Rockets, vol. 10, no. 7, pp. 435–442, 1973.

P. Jaffe, “Vehicle flight scaling with aerodynamic flow hysteresis,” Journal of Spacecraft and Rockets, vol. 7, no. 2, pp. 209–210, 1970.

Ö. Karatekin, Aerodynamics of a planetary entry capsule at low speeds, Ph.D. thesis, Université Libre de Bruxelles, Bruxelles, Belgium, 2002.

R. A. Mitcheltree and S. Kellas, “A passive Earth-entry capsule for Mars sample return,” in Proceedings of the International Symposium on Atmospheric Reentry Vehicles and Systems, Arcachon, France, March 1999.

F. McNeil-Cheatwood, G. L. Winchenbach, W. Hathaway, and G. Chapman, “Dynamic stability testing of the Genesis sample return capsule,” AIAA Paper 2000-1009, 2000

C. Berner, V. Fleck, and E. Sommer, “Aerodynamic coefficients of entry vehicle demonstrator from free flight range testing,” in Proceedings of the 6th European Symposium on Aerodynamics for Space Vehicles, C. Berner, V. Fleck, E. Sommer, and P. Tran, Eds., Versailles, France, November 2008, ESA SP-658.

I. R. Tuohy, “Advantages of the Woomera test facility for hypersonic flight programs,” AIAA Paper 2006-7909, 2006

A. K. Owen and F. K. Owen, “Magnetic suspension and balance testing in support of Hyper-X,” in Proceedings of the 12th AIAA International Space Planes and Hypersonic Systems and Technologies, Norfolk, Virginia, December 2004, AIAA Paper 2003-6958.

S. I. Burnell, P. Liever, A. Smith, and G. Parnaby, “Prediction of the beagle 2 static aerodynamic coefficients,” in Proceedings of the 2nd Inernational Conference on Atmospheric Reentry Vehicles and Systems, Arcachon, France, March 2001.