两级入轨航天器级间分离姿态精确控制

doi:10.7527/S1000-6893.2023.29270

Abstract

Abstract:

Precise attitude control of the orbiter and the booster is particularly important for the interstage separation of the Two-Stage-to-Orbit （TSTO） vehicle. Numerical simulation can accurately predict interstage separation， which is a multi-body separation problem for aircraft. We use the unstructured overset grid technique and the dual-time method to couple the fluid control equations and the rigid body motion equations to solve the interstage separation process of the TSTO at an angle of attack of -2°， Mach number 6， and an altitude of 30 km， and develop a technique to optimise the attitude of the orbiter and the booster during the interstage separation process. The technique obtains the aerodynamic data of the orbiter and the booster without rudder deflection angle with the relaxation iteration method and， based on these data， designs the pitching moments to be provided by the aerodynamic and gas rudders to bring the kinematic attitudes of the orbiter and the booster closer to the design target. The numerical simulation results show that strong aerodynamic interference will exist between the two stages of the TSTO during the separation process， seriously affecting the attitude control of the two stages. The technology developed can provide a reference for the design of the aerodynamic rudder motion and gas rudder operating state of the orbiter and the booster during the separation process of the TSTO， so as to improve the efficiency and safety of the interstage separation of the TSTO.

Key words: two-stage-to-orbit, multibody separation, hypersonic, overset grid, relaxation factor metho

CLC Number:

Quanfeng JIANG, Shusheng CHEN, Hua YANG, Zuotai LI, Zhenghong GAO. Precise control of interstage separation attitude of two⁃stage⁃to⁃orbit vehicle[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(13): 129270.

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带舵外挂物参数	取值
质量/kg	907.2
转动惯量I_xx /（kg·m²）	27.12
转动惯量I_yy /（kg·m²）	488.09
转动惯量I_zz /（kg·m²）	488.09
前弹射力位置/mm	1 237
前弹射力大小/kN	10.67
后弹射力位置/mm	1 746
后弹射力大小/kN	42.67
弹射力作用距离/mm	100
挂架与弹体间距/mm	36

参数	助推级	轨道级
长度/m	80.0	36.6
翼展/m	60.5	24.0
平均气动弦长/m	43.1	20.6
质心坐标/m	47.0，0，-2.5	47.0，0，3.0
参考面积/m²	1 949.8	341.1
质量/kg	360 000	110 000
转动惯量I_xx /（kg·m²）	1.23×10⁷	2.41×10⁵
转动惯量I_yy /（kg·m²）	8.43×10⁷	4.19×10⁶
转动惯量I_zz /（kg·m²）	9.53×10⁷	4.26×10⁶

飞行器种类		C_L	C_m	F_N /（10⁶ N）
轨道级	组合体	0.023 3	-0.011 6	-0.843 5
轨道级	孤立	-0.059 8	-0.014 7	-1.679 6
助推级	组合体	-0.046 0	0.006 8	-6.172 5
助推级	孤立	-0.020 4	0.005 9	-4.700 7

迭代方式	轨道级∆q/（rad·s^-1）
迭代步1（不引入ω）	0.061 9
迭代步2（不引入ω）	0.016 6
迭代步1，ω=1.5	0.014 0
迭代步1，ω=2.0	0.032 5
迭代步1，ω=3.0	0.078 9

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Precise control of interstage separation attitude of two⁃stage⁃to⁃orbit vehicle

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