International Journal of Aerospace Engineering
Volume 2018 (2018), Article ID 7806036, 10 pages
https://doi.org/10.1155/2018/7806036

Research Article

A Novel Technique for Predicting the Thermal Behavior of Stratospheric Balloon

Yunpeng Ma, Jun Huang, and Mingxu Yi

School of Aeronautic Science and Technology, Beihang University, Beijing 100191, China

Correspondence should be addressed to Yunpeng Ma; yunpengma@163.com

Received 8 June 2017; Revised 22 October 2017; Accepted 7 November 2017; Published 8 February 2018

Academic Editor: Paul Williams

Copyright © 2018 Yunpeng Ma 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.

This paper is devoted to introduce a novel method of the operational matrix of integration for Legendre wavelets in order to predict the thermal behavior of stratospheric balloons on float at high altitude in the stratosphere. Radiative and convective heat transfer models are also developed to calculate absorption and emission heat of the balloon film and lifting gas within the balloon. Thermal equilibrium equations (TEE) for the balloon system at daytime and nighttime are shown to predict the thermal behavior of stratospheric balloons. The properties of Legendre wavelets are used to reduce the TEE to a nonlinear system of algebraic equations which is solved by using a suitable numerical method. The approximations of the thermal behavior of the balloon film and lifting gas within the balloon are derived. The diurnal variations of the film and lifting gas temperature at float conditions are investigated, and the efficiency of the proposed method is also confirmed.

1. Introduction

Stratospheric balloons or airships have been paid attention since they can provide persistent observation platforms by keeping on station at an altitude about 20~30 km for a long time. They have some potential advantages, such as station keeping, long endurance, low cost, broadcasting, and telecommunication relay [1–3]. When the balloons stay at an altitude about 20~30 km, they should be filled with a huge gas volume of several hundred thousand cubic meters. Even a small temperature variation between the inner gas and the outer environment can lead to a huge buoyancy difference. So the thermal behavior of the stratospheric balloon should have attracted some interest from all over the world [4, 5].

It is important to predict the thermal behavior of the stratospheric balloon before it launches. Understanding the temperature variation of the stratospheric balloon will be helpful for balloon design and flight prediction. During the research of the thermal behavior of the stratospheric balloon, the average film and lifting gas temperature are the main focus. Carlson et al. [6] studied the trajectory and thermal behavior of the high-altitude balloons. Stefan [5] used a two-node model to solve the day-night airship temperature numerically. Farley [7] established a code to calculate the ascent and float thermal behavior of the stratospheric balloon. Dai et al. [8] developed a simulation program to investigate the thermal performance of a super pressure balloon by using the thermal models and dynamic models. Yao et al. [9] proposed a multinode heat transient model for stratospheric airships to predict the thermal behaviors of the ascent and descent processes. In these articles, the thermal models are established for different conditions. The thermal performance of the film and lifting gas can be obtained by solving TEE. The main method to solve these equations is discrete collocation method. The computation efficiency is low when the number of surface elements of film are very large.

In this paper, we adopt the thermal models given by Xia et al. [10] and present a novel technique to solve the TEE. The thermal performance of the film and lifting gas will be got by applying the method to solve the TEE. The method is based on Legendre wavelet integration operational matrix method. In the proposed method, the TEE is reduced to a system of nonlinear algebraic equations, which can be solved easily. The proposed method is of high computing efficiency and simple operation.

2. Thermal Model

In this section, the same thermal environment and assumptions of the stratospheric balloon shown in [11, 12] will be considered. The thermal environment (shown in Figure 1) of the high-altitude stratospheric balloon includes infrared radiation, solar radiation, and convection. The balloon film is so thin that the conductive resistance can be neglected.

Figure 1: Thermal environment of a stratosphere balloon.

The transient temperature distribution of the film is expressed by the following [10]:

where are the film thickness, density, and specific heat, respectively. and are the convective heat transfer coefficients for the external and internal surfaces of the film. are the film temperature, atmosphere temperature, and lifting gas temperature, respectively. are the absorbed direct solar radiation, the absorbed diffuse solar radiation, and the absorbed reflected solar radiation. and are the external and internal emissivities of the film. denotes the internal absorptivity. is the total irradiation falling on the film. is the Stefan Boltzmann constant.

The total irradiation at the internal film segment can be obtained by the following:

where is the angle factor from element to element . is the total number of surface elements of the balloon. is the infrared radiation away from the internal surface, and it can be calculated as follows:

Then the average temperature of the lifting gas is written in the following equation [8]:

where is the specific heat. is mass of the lifting gas.

2.1. Atmosphere Model

The relation between the atmosphere temperature, pressure, and the altitude are given by the following [13]:

where is the altitude of the balloon.

2.2. Solar Position and Solar Radiation Models

Before we introduce the solar radiation models, the computational method of solar position should be given as follows.

Suppose that denotes the solar altitude angle and denotes the solar azimuth angle, then we have the solar direction vector

The solar altitude angle and the solar azimuth angle can be expressed by the following [14]:

where is the local latitude, is the declination of the sun, and is the hour angle of the sun. They are defined as

where is solar day angle and is the value of time correction. The calculate method will be

where is the day of the year.

The absorbed direct solar radiation heat flux is shown as [15]

where is the index which considers the self-shadowing and is the direct solar radiation; otherwise, . is the solar absorptivity of the external surface. is the atmosphere transmissivity. is the solar constant. is the included angle between the solar radiation and surface external normal.

The absorbed diffuse and reflected solar radiation heat flux is written as [16]

where is the empirical diffuse coefficient. is the Earth’s reflectivity. is the angle factor between the film and the Earth.

The infrared radiation heat flux from the Earth and atmosphere can be given by [16]

where is the absorptivity of the external surface in the infrared spectrum. is the transmissivity of the atmosphere in the infrared spectrum. is the Earth’s atmosphere infrared flux.

2.3. Convective Heat Transfer Coefficient Models

Convective heat transfer happens to both inner and external surfaces of the balloon hull. For the inner surface, the heat convection is usually considered as a natural convection. For the external surface, the heat convection is either a forced one or natural one. It depends on the relative speed of the balloon and the atmosphere characteristic. According to the theory of Leland and Walter [17], the convective heat transfer coefficients for both inner and external surfaces are calculated by

where is the Nusselt number, is the thermal conductivity of the gas, and is the length of the balloon.

For the inner surface, the Nusselt number is

For the external surface, natural convection case, Nusselt number is

For the external surface, forced one, Nusselt number is

where is Rayleigh number and is Reynolds number. They can be obtained by

where is the Grashof number, is Prandtl number, is the gravitational acceleration, and are the coefficient of thermal expansion and the kinematic viscosity, respectively, is the temperature difference between the surface and the gas, and is the airspeed of the balloon. The kinematic viscosity can be got as follows:

where is the dynamic viscosity. The computational method of these parameters () for helium and air will be found in [18].

3. Legendre Wavelets and Their Properties

The Legendre wavelet polynomials are defined on the interval as [19]

where , , is the degree of the Legendre polynomials and is a fixed positive integer, and are the Legendre polynomials of degree .

For any function may be expressed by the Legendre wavelets as follows:

where are the Legendre wavelet coefficients and is the inner product of and .

If (20) is truncated, then it can be rewritten as

where and are column vectors, given by

We can also rewrite (21) as

where and . The index is determined by the relation . Then, we have

To illustrate the effectiveness of (23), we have shown the theorem as follows.

Theorem 1. Suppose that the function obtained by using Legendre wavelets is the approximation of and is with bounded second derivative, say ; then the series converges uniformly to the function ; that is,

Proof. See [20].

Next, we will derive the operational matrix of integration of Legendre wavelets. In order to do this, another basis set of Block pulse functions should be considered as follows [21]:

with a positive integer value for and .

Let . Suppose that

where is called the Block pulse operational matrix of integration [21] and

The Legendre wavelets may be expanded into an term Block pulse function as

where , , and .

The integration of the vector function can be expressed as

where is the operational matrix of integration. It is known (see [22]) that the matrix can be approximated by

Then we have

The integrations of the function and are selected to verify the effectiveness of matrix . The integrations of and are obtained as follows and . Take , the results are shown in Figure 2 and Figure 3, respectively.

Figure 2: Integration of .

Figure 3: Integration of .

From Figure 2 and Figure 3, we can find that the matrix is very credible to calculate the integration of any functions.

4. Solution Procedure for TEE (1) and (4)

In this section, the proposed method based on the Legendre wavelet expansion together with their operational matrices of integration to obtain numerical solutions of the TEE (1) and (4) is described. To obtain such numerical approximate solution, we apply the following steps:

(1)Let , then , .(2)Express on and in the following form:

where and are unknown vector and is the vector which is defined in (25). By using initial conditions and integrating (34) and (35), we have

(3)Expand the initial and by wavelets as follows:

 Since , from (36) to (37) we have

which can be written as

(4)Let and ; then we have

 By using the disjointness of Block pulse functions, we get [21]

(5)Substituting (34), (38), (40), and (44) into (1), we obtain

where . Using and (42), we have

Discreting (46) by collocation points, we can get a nonlinear system of algebraic equations for the unknown vector as follows:

where

The nonlinear system (47) can be solved by applying the Newton iteration method. Therefore, as the solution of (1) is given by .

Substituting (35), (40), and (41) into (4), we get

Applying and (43), we have

Discreting (50) by the same collocation points, we can acquire a linear system of algebraic equations for the unknown vector as follows:

where

is the area of the balloon.

Solving this system, we can obtain the approximation of (4).

5. Error Analysis

To show the effectiveness of , we discuss error analysis of Legendre wavelets. Let be the approximation of , . Then, .

Theorem 2. Suppose that the function obtained by using Legendre wavelets are the approximation of , and is with bounded second derivative; then one has the following estimation.

where , , and is double gamma function.

Proof. Let be a function in the interval such that

where is a positive constant.

Using the property ( is the identity matrix), we have

where ; then we can obtain

Let ; then

Suppose

Therefore,

where . Using Cauchy-Schwarz inequality

Then

Thus,

where

Since

then

Therefore, we have

Then we get

namely,

From Theorem 2, we can find that when is fixed and .

6. Numerical Implementation of Legendre Wavelet Method for Solving TEE

In order to show the validation of the proposed method, the same stratospheric balloon model [10] at float condition is selected. A spherical balloon with radius is shown in Figure 4. The film of the balloon is divided into 3018 elements by the software ANSYS 14.0. Other parameters in this part are for , , and . The surface density is 150 g/m², and the specific heat is 1500 J/(kg·K). The lifting gas is helium and the wind speed is 10 m/s. The floating altitude is 20 km. The floating latitude and longitude are 40 degrees and 120 degrees, respectively. The balloon was launched during daytime on Spring Equinox 2010.

Figure 4: The geometric model of the stratospheric balloon.

Figure 5 shows the day-night variation of the film element temperature for and compares it with the measured data. The degree of the Legendre polynomials is 3. From Figure 5, we can see that the predicted data obtained by our method are in good agreement with measured data [23], which indicates the validation to simulate thermal behavior of the balloon. Due to the solar irradiation, the actual balloon temperature begins to increase before sunrise and after sunset it continues to decrease. The maximum and minimum temperatures are 274 K and 229 K. The variation of the actual balloon temperature is as high as 45 K.

Figure 5: The comparison of the temperature of the film.

The predicted data of the temperature day-night variation for are shown in Figure 6. From Figure 6, we can conclude that the temperature of the film varies nonlinearly with time. The reason for this variation is that the solar irradiation appeared at 6 o’clock and vanished at 18 o’clock.

Figure 6: The comparison of the temperature of the film for different .

The comparison between the predicted data for and the measured data is displayed in Figure 7. Table 1 reveals the CPU time on examples 1–4 for different . From Table 1, it is seen that the CPU time on examples 1–4 are less than 1 minute, which implies high efficiency for the method. It can be seen from Figure 7 that the proposed method can predict the thermal behavior of stratospheric balloon effectively, and the simulated results are more credible with increasing. Table 1 reveals the CPU time on simulation for different . From Table 1, it is seen that the CPU time are less than 20 seconds, which implies high efficiency for the method.

Figure 7: The comparison of the film’s temperature for different .

Table 1: CPU time (in seconds) for different .

CPU time

15.881

18.254

Figure 8 shows the comparison of day-night variation of helium temperature obtained by our proposed method and Xia et al.’s [10] method, respectively. From Figure 8, we may find that the maximum and minimum helium temperatures are 262.2 K and 229.1 K, respectively. We can also see that the calculated results are close to Xia et al.’s results by taking a closer look at Figure 8. The effectiveness of the proposed method is demonstrated by the coincidence.

Figure 8: The comparison of day-night variation of helium temperature.

Comparing Xia et al.’s results with ours, there exist some divergences in Figure 8. These are mainly due to the influence of computational errors by using (51). The errors consist of two parts: one is the approximation of the film’s area and the other is the inverse of matrices product. The difference, on the other hand, comes from the number of comparisons.

In summary, the main characteristics of the wavelet-based approach which leads to a sparse matrix are (1) the vanishing moments property and (2) having a small interval of support. In fact, the sparseness of the system coefficient and good adaptation in dealing with continuous functions are good advantages of using Legendre wavelets, as shown by numerical example. What is more, the approximate explicit expressions of the temperatures of lifting gas and balloon film are obtained generally, which can calculate the temperatures at any time.

7. Conclusion

In the proposed method, we used the properties of the Legendre wavelets to reduce TEE to solve a system of algebraic equations. The temperatures of lifting gas and balloon film will be got by solving the linear and nonlinear system of algebraic equations. The solution is expressed as a truncated Legendre wavelet series and so it can be easily evaluated for arbitrary values of time using any computer program. From the illustrative example, we can conclude that using this approach obtains very satisfactory results. To illustrate the validity and the great potential of the technique, comparisons are made between the predictions obtained by ours and results obtained in previous literature. The proposed method is not only simple but also practical.

Conflicts of Interest

The authors declare that they have no conflict of interest.

References

A. Colozza and J. L. Dolce, “High-altitude, long-endurance airships for coastal surveillance,” 2005, NASA/TM-2005 e213427.

Z. Zheng and Z. Wu, “Global path following control for underactuated stratospheric airship,” Advances in Space Research, vol. 52, no. 7, pp. 1384–1395, 2013.

L. Jamison, G. S. Sommer, and I. R. Porche, “High-altitude airships for the future force army,” Tech. Rep., RAND Corporation Technical Report, Santa Monica, CA, USA, 2005.

H. M. Cathey, “Advances in the thermal analysis of scientific balloons,” in 34th Aerospace Science Meeting and Exhibit, Reno, NV, USA, January 1996.

K. Stefan, “Thermal effects on a high altitude airship,” in 5th Lighter-Than Air Conference, Anaheim, CA, USA, July 1983.

L. A. Carlson and W. J. Horn, “New thermal and trajectory model for high-altitude balloons,” Journal of Aircraft, vol. 20, no. 6, pp. 500–507, 1983.

R. E. Farley, “BalloonAscent: 3-D simulation tool for the ascent and float of high-altitude balloons,” in AIAA 5th ATIO and 16th Lighter-Than-Air Sys Tech. and Balloon Systems Conferences, Arlington, Virginia, September 2005.

Q. Dai, X. Fang, X. Li, and L. Tian, “Performance simulation of high altitude scientific balloons,” Advances in Space Research, vol. 49, no. 6, pp. 1045–1052, 2012.

W. Yao, X. C. Lu, C. Wang, and R. Ma, “A heat transient model for the thermal behavior prediction of stratospheric airships,” Applied Thermal Engineering, vol. 70, no. 1, pp. 380–387, 2014.

X. L. Xia, D. F. Li, C. Sun, and L. M. Ruan, “Transient thermal behavior of stratospheric balloons at float conditions,” Advances in Space Research, vol. 46, no. 9, pp. 1184–1190, 2010.

O. A. Louchev, “Steady state model for the thermal regimes of shells of airships and hot air balloons,” International Journal of Heat and Mass Transfer, vol. 35, no. 10, pp. 2683–2693, 1992.

M. F. Modest, Radiative Heat Transfer, McGraw-Hill, New York, NY, USA, 1993.

A. Colozza, “Initial feasibility assessment of a high altitude long endurance airship,” 2003, NASA/CR-2003-212724.

S. H. Jui, Solar Energy Engineering, Prentice-Hall Inc., Upper Saddle River, NJ, USA, 1986.

H. Ran, R. Thomas, and D. Mavtis, “A comprehensive global model of broadband direct solar radiation for solar cell simulation,” in 45th AIAA Aerospace Sciences Meeting and Exhibit, Reno, NV, USA, January 2007.

X. J. Li, X. D. Fang, and Q. M. Dai, “Research on thermal characteristics of photovoltaic array of stratospheric airship,” Journal of Aircraft, vol. 48, no. 4, pp. 1380–1386, 2011.

A. C. Leland and J. H. Walter, “A unified thermal and vertical trajectory model for the prediction of high altitude balloon performance,” 1981, NASA-CR-156884.

F. Kreith and J. Kreider, Principles of Solar Engineering, Hemisphere Publishing Corp, New York, NY, USA, 1978.

H. Jafari and S. A. Yousefi, “Application of Legendre wavelets for solving fractional differential equations,” Computers & Mathematics with Applications, vol. 62, no. 3, pp. 1038–1045, 2011.

N. Liu and E. B. Lin, “Legendre wavelet method for numerical solutions of partial differential equations,” Numerical Methods for Partial Differential Equations, vol. 26, no. 1, pp. 81–94, 2010.

Y. L. Li and N. Sun, “Numerical solution of fractional differential equations using the generalized block pulse operational matrix,” Computers & Mathematics with Applications, vol. 62, no. 3, pp. 1046–1054, 2011.

M. Ur Rehman and R. Ali Khan, “The Legendre wavelet method for solving fractional differential equations,” Communications in Nonlinear Science and Numerical Simulation, vol. 16, pp. 4163–4173, 2011.

Y. Q. Yang, Research on the Pressure Resistance Ability of Stratospheric Aerostats Based on Multi-Field Coupling Method, Beihang Univeristy, Beijing, China, 2014.