空间微小载荷在轨发射动力学特性及影响因素

doi:10.12305/j.issn.1001-506X.2025.08.27

Abstract

Abstract:

Aiming at the dynamic characteristics of in-orbit launch of space micro-load based on solid thrusters, a dynamic model of a in-orbit launch system considering the inertia spindle shift and additional disturbance torque is established based on the multi-rigidbody theory. A method of calculating the contact internal force between the load and the satellite platform using the boundary conditions is proposed to solve the dynamic parameters. The accuracy of the dynamic model and solution method is verified through numerical simulations and comparisons with auxiliary software simulation results. Meanwhile, focusing on the motion coupling effect between the payload and the platform, the analysis considers the impact of payload installation position, thrust eccentricity, and friction coefficient on the initial disturbance during launch, using the established dynamic model. Relevant requirements for the design parameters of the payload launch system are proposed, providing theoretical guidance for the engineering practice of in-orbit launching of space micro payloads.

Key words: space micro-load, solid thruster, in-orbit launch, launch dynamics, initial disturbance

CLC Number:

V 412.4

Zengqiao TAN, Haibo YANG, Wenhe LIAO, Zhengliang LU, Xiaoyu TAO. Dynamic characteristics and influence factors of in-orbit launch for space micro-load[J]. Systems Engineering and Electronics, 2025, 47(8): 2696-2705.

Figures/Tables 12

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References 30

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参数名称	符号	参数值
卫星平台质量/kg	$ {m_{\text{B}}} $	81.2
卫星平台转动惯量/（$ \text{kg}\cdot{\text{m}}^{2} $）	$ {{\boldsymbol{J}}_{\text{B}}} $	$ \left[ {\begin{array}{*{20}{c}} {8.86}&0&0 \\ 0&{6.93}&0 \\ 0&0&{6.79} \end{array}} \right]\; $
空间微小载荷质量/kg	$ {m_{\text{L}}} $	9.9
空间微小载荷转动惯量/（$ \text{kg}\cdot{\text{m}}^{2} $）	$ {{\boldsymbol{I}}_{\text{L}}} $	$ \left[ {\begin{array}{*{20}{c}} {0.032}&0&0 \\ 0&{0.276}&0 \\ 0&0&{0.276} \end{array}} \right] $
载荷质心位置矢径/m	$ {{\boldsymbol{r}}_{\text{L}}} $	$ {[0,\;\; - 0.2,\;\;0]^{\text{T}}} $
推力作用点位置矢径/m	$ {{\boldsymbol{r}}_{{\text{LT}}}} $	$ {[ - 0.3,\;\;0,\;\;0]^{\text{T}}} $
前定心部位置矢量/m	$ {{\boldsymbol{r}}_{{\text{LN1}}}} $	$ {[0.015,\;\;0,\;\;0]^{\text{T}}} $
后定心部位置矢量/m	$ {{\boldsymbol{r}}_{{\text{LN2}}}} $	$ {[ - 0.225,\;\;0,\;\;0]^{\text{T}}} $
轨道角速度/（rad/s）	$ {{\boldsymbol{\omega }}_{{\text{oi}}}} $	$ {[0,\;\; - 0.001\;5,\;\;0]^{\text{T}}} $
推力器侧向力矢量	$ {\boldsymbol{e}} $	$ {{{[0}},\;\;{{1}},\;\;{{1]}}^{{{\mathrm{T}}}}} $
推力偏心角/（°）	$ \alpha $	0.25
仿真时长/ms	$ t $	30
步长/ms	$ i $	0.1
摩擦系数	$ \mu $	0.2

参数	设计变量	数值仿真	ADAMS仿真
载荷分离速度/（m·s⁻¹）	$ x $	26.042 7	26.044 5
	$ y $	0	−0.000 2
	$ z $	0	−0.000 1
载荷分离角速度/（°/s）	$ x $	0	0.007 6
	$ y $	1.553 9	1.436 9
	$ z $	−1.000 5	−1.036 8
平台分离角速度/（°/s）	$ x $	−1.011 8	−0.992 2
	$ y $	1.553 9	1.437 1
	$ z $	−1.000 5	−1.036 5

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Dynamic characteristics and influence factors of in-orbit launch for space micro-load

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