An integrated simulation system for operating solar sail spacecraft

doi:10.23919/JSEE.2021.000102

Journal of Systems Engineering and Electronics ›› 2021, Vol. 32 ›› Issue (5): 1200-1211.doi: 10.23919/JSEE.2021.000102

• SYSTEMS ENGINEERING • Previous Articles Next Articles

An integrated simulation system for operating solar sail spacecraft

Yaru ZHENG(), Qinglong LI(), Ming XU*(), Yunfeng DONG()

¹ School of Astronautics, Beihang University, Beijing 100191, China

Received:2020-08-08 Online:2021-10-18 Published:2021-11-04
Contact: Ming XU E-mail:zheng_yaru@outlook.com;liqnlong@buaa.edu.cn;xuming@buaa.edu.cn;sinosat@buaa.edu.cn
About author:|ZHENG Yaru was born in 1995. She received her B.S. degree in automation engineering from the Ocean University of China in 2017, and her M.S. degree in aerospace engineering from Beihang University in 2020. Her research interests include computational mission analysis and system design in satellite/rocket engineering, and trajectory design for rockets. E-mail: zheng_yaru@outlook.com||LI Qinglong was born in 1998. He received his B.S. degree in aerospace engineering from Beihang University in 2018. He is currently working toward his M.S. degree in aerospace engineering in the School of Astronautics, Beihang University. His research interests include satellite formation flying, sequential and batch estimations of orbital elements, and flight control. E-mail: liqnlong@buaa.edu.cn||XU Ming was born in 1981. He received his Ph.D. degree in aerospace engineering from Beihang University in 2008. He worked for China Academy of Space Technology as a system engineer until joining School of Astronautics, BUAA in 2011. He has been a professor in aerospace engineering since 2020. His research interests include computational mission analysis and system design in satellite engineering, Hamiltonian system, and its application into astrodynamics. E-mail: xuming@buaa.edu.cn||DONG Yunfeng was born in 1965. He received his B.S., M.S., and Ph.D. degrees in aerospace engineering from Beihang University in 1987, 1990, and 2005 respectively. He is a professor in aerospace engineering in the School of Astronautics, Beihang University. His research interests include aerospace mission design, astrodynamics, and control. E-mail: sinosat@buaa.edu.cn
Supported by:
This work was supported by the National Natural Science Foundation of China (11772024)

Abstract

Abstract:

An integrated simulation system for solar sail spacecraft with individually controllable elements (SSICE) is investigated in this paper, including the modelling of power management, thermal control, attitude control, umbra prediction, and orbit prediction subsystems. Considering the self-control and reactivity subsystems, an agent based method is applied to develop the subsystem models. Each subsystem is an individual agent component, which manages itself autonomously and reacts to the requirements from other agents. To reduce computing burden on a specified computer and improve the suitability and flexibility of the integrated simulation system, a distributed framework is employed in the system by deploying agent components on different computers. The data transmission among agents is based on the transmission control protocol/Internet protocol (TCP/IP). A practical example of sun pointing is used to test the operating effect of the integrated system and the working condition of subsystems. The simulation results verify that the integrated system has higher sun pointing accuracy, quicker dynamical response to variations of the lighting, attitude and temperature and fewer computing resources with effective and accurate subsystems. The integrated system proposed in this paper can be applied to solar sail design, operation, and mission planning.

Key words: solar sail spacecraft, integrated system, agent, distributed simulation, individually controllable element

Yaru ZHENG, Qinglong LI, Ming XU, Yunfeng DONG. An integrated simulation system for operating solar sail spacecraft[J]. Journal of Systems Engineering and Electronics, 2021, 32(5): 1200-1211.

Figures/Tables 24

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References 28

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Variable	Definition	Unit	Variable	Definition	Unit
a	Semi-major axis	m	K_p2, K_d2	Pitching control coefficient	?
A	Exponential voltage	V	K_p3, K_d3	Yawing control coefficient	?
A_s-p, F_S	Area parameters	m²	R, R_m	Resistance	Ω
B	Exponential capacity	Ah^-1	R, R₁, R₂	Position vector	m
C_m	Capacitance	C	S	Solar direction vector	m
C_S, C_N	Hear capacity of nodes	J/K	SOC, SOC₀	State of charge	?
e	Eccentricity	?	T	Control torque	N·m
h_NS, ε_NS	Thermal coefficient	?	T_i	Internal node temperature	°C
i	Orbit inclination	(°)	T_o	External node temperature	°C
I,I_mpr, I_scr	Electric current	A	U, U_m0, U_mpr, U_ocr	Busbar voltage	V
M	Mean anomaly	(°)	V, V₁, V₂	Velocity vector	m/s
n_g	Power supply array coefficient	?	ω	Angular velocity	rad/s
n_c	Power charging array coefficient	?	Ω	Right ascension of the ascending node (RAAN)	(°)
Q	Rated capacity	Ah	φ, θ, ψ	Rotation angle	(°)
K	Polarization voltage	V	$ {\bar{\varepsilon }}_{h},{\bar{\alpha }}_{s} $	Surface coefficient	?
K_p1, K_d1	Rolling control coefficient	?

Element	Value
Epoch time	12:00:00, January 1, 2022 (UTC)
Semi-major axis a/m	6878140
Eccentricity e	0.0012
Orbit inclination i/(°)	97.3994
Argument of perigee ω/(°)	90
Right ascension of the ascending node Ω/(°)	78.8307
Mean anomaly M/(°)	150
Regressive period/d	5

Parameter		Value
Initial power system	U_m0/V	50
Initial power system	SOC₀/%	78
Parameters of solar cell	I_mpr/A	0.2348
	I_scr/A	0.2480
	V_mpr/V	0.8802
	V_ocr/V	1.0180
Parameters of single solar cell array	n_p	10
	n_s	52
	R/Ω	1.6
Parameters of the accumulator	K	0.3135
	Q/Ah	70
	A/V	1.98962
	B/Ah^?1	0.193 16
	R_i/Ω	0.036
Power supply array/Charging	n_g	6
Power supply array/Charging	n_c	4
Parameters of the bus bar	C_m/C	1.099
Parameters of the bus bar	R_m/Ω	1000

Parameter		Value
Initial temperature of the nodes	T_S0/°C	12
Initial temperature of the nodes	T_N0/°C	12
Area parameters	F_S/m²	31
Area parameters	A_s-p/m²	7.45
Surface parameters	${\bar{\epsilon } }_{h}$	0.44
Surface parameters	$ {\bar{\alpha }}_{s} $	0.42
Hear capacity of the nodes	C_S/(J/K)	30000
Hear capacity of the nodes	C_N/(J/K)	20000
Thermal parameters	h_NS	0.105
Thermal parameters	ε_NS	0.105×10^?6
Other parameters	F_h-s	0.5
Other parameters	Q_N/W	26.5

Parameter		Value
Controller parameter	Roll channel	K_p1=0.05, K_d1=3.2
	Pitch channel	K_p2=0.1, K_d2=5
	Yaw channel	K_p3=0.1, K_d3=5
Initial attitude angle/(°)		φ=0.5, θ=0.3, ψ=0.5
Initial angular velocity/(°/s)		ω_b = [0.02 0.02 0.02]

An integrated simulation system for operating solar sail spacecraft

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