Research on the Concept and Evaluation Method for Reconfigurability of Launch Vehicles

doi:10.3873/j.issn.1000-1328.2023.09.004

Abstract

Abstract:

The concept of ‘system reconfiguration’ have been widely applied in various walks of life, however there are no unified understanding about its definition, objectives and methods. Based on the definitions from some industry organized in this paper, the concept of system reconfiguration is discussed along with the concept of system. Then the concept of reconfigurable launch vehicle is discussed. The objectives of reconfigurable launch vehicle are proposed. The characteristics of reconfigurable launch vehicle are summarized. The evaluation method of launch vehicle reconfigurability is also proposed and the effectiveness of the method is validated by simulation. Finally, suggestions for follow-up work of reconfigurable launch vehicle are proposed.

Key words: Launch vehicle, System reconfiguration, Reconfigurability evaluation

CLC Number:

V475.1

ZHANG Zhi, MA Ying, ZHU Haiyang, DU Haoyu, MIAO Xinyuan. Research on the Concept and Evaluation Method for Reconfigurability of Launch Vehicles[J]. Journal of Astronautics, 2023, 44(9): 1305-1316.

Figures/Tables 13

Fig.1 Flow chart of the accessible domain evaluation method

Fig.2 Comparison of flight altitude before and after reconfiguration

Fig.3 Comparison of velocity before and after reconfiguration

Fig.4 Comparison of pitching angle before and after reconfiguration

Fig.5 Comparison of yawing angle before and after reconfiguration

Table 1 The effectiveness on control moment of the azimuth angle of servo

方位角/(°)	M_x最大净力矩/ (N·m)	M_y最大净力矩/ (N·m)	M_z最大净力矩/ (N·m)	体积/m³	俯仰偏航平面最大剩余控制能力/(N·m)
15	±6.24	±132.08^*	±28.38	9 844.7	28.38
30	±7.43	±111.64	±55.01	161 151.4	53.47
45	±8.74	±96.69	±77.92	220 136.9	72.31
60	±10.91^*	±83.73	±95.48	241 727^*	83.73^*
75	±8.91	±70.78	±106.44	220 136.9	70.78
90	±6.30	±55.82	±110.03^*	161 151.4	55.82
105	±3.26	±35.39	±105.93	80 575.7	35.39
120	0	0	±96.63	0	0
135	±2.34	±48.34	±76.97	58 985.5	41.52
150	±3.71	±96.69	±55.82	80 575.7	47.52
165	±4.57	±132.08^*	±28.17	58 985.5	27.85

Fig.6 AMS and control moment projection when azimuth angle of servo is 30°

Fig.7 AMS and control moment projection when azimuth angle of servo is 60°

Fig.8 AMS and control moment projection when azimuth angle of servo is 120°

Fig.9 Ellipsoid view of system controllability

Table 2 Evaluating indicators of system controllability

项目	Frobenius范数	椭球体积
值	0.176 5	7.460 5×10^-4

Fig.10 View of the region of attraction of launch vehicle in longitudinal movements

Fig.11 State and control quantity curves of the boundary points of the region of attraction

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