Design and Analysis of a New Reusable Lander

Shan JIA; Rujie HU; Xianghua ZHOU; Shaoyang LIU; Mingyang WU; Jinbao CHEN

doi:10.3969/j.issn.1009-8518.2024.02.001

Journals >Spacecraft Recovery & Remote Sensing >Volume 45 >Issue 2 >Page 1 > Article

Spacecraft Recovery & Remote Sensing
Vol. 45, Issue 2, 1 (2024)

Design and Analysis of a New Reusable Lander

Shan JIA^1,3,4, Rujie HU^1,2, Xianghua ZHOU¹, Shaoyang LIU¹..., Mingyang WU¹ and Jinbao CHEN^1,3,4|Show fewer author(s)

Author Affiliations

¹Academy of Astronautics, Nanjing University of Aeronautics and Astronautics, Nanjing 211106, China

²Shenyang Aircraft Design and Research Institute, Shenyang 110035, China

³Laboratory of Aerospace Entry, Descent and Landing Technology, Nanjing 211106, China

⁴Key Laboratory of Deep Space Star Catalog Detection Mechanism Technology, Ministry of Industry and Information Technology, Nanjing 211106, China

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DOI: 10.3969/j.issn.1009-8518.2024.02.001 Cite this Article

Shan JIA, Rujie HU, Xianghua ZHOU, Shaoyang LIU, Mingyang WU, Jinbao CHEN. Design and Analysis of a New Reusable Lander[J]. Spacecraft Recovery & Remote Sensing, 2024, 45(2): 1 Copy Citation Text

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i	${\alpha _{i - 1}}$	${a_{i - 1}}$	${d_i}$	$ {\theta} $
1	0	0	0	${\theta _{\rm{AB}}}$
2	0	L₁	0	${\theta _{\rm{BD}}}$
3	0	L₂	0	0

Table 1. D-H parameter table of support leg mechanism

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构件1名称	构件2名称	运动副名称
主体	上横杆	转动副
主体	下横杆	转动副
上横杆	竖直杆	转动副
下横杆	竖直杆	转动副
下横杆	柔性腿	固定副
足垫	柔性腿	球铰
上转轴	下转轴	移动副

Table 2. Campaign sub-setting situation

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时间/s	模型	$ \boldsymbol{\mathit{f}}_{\mathrm{Bx}}/\text{N} $	$ \boldsymbol{\mathit{f}}_{\mathrm{By}}/\text{N} $	$ \boldsymbol{\mathit{f}}_{\mathrm{Dx}}/\text{N} $	$ \boldsymbol{\mathit{f}}_{\mathrm{Dy}}/\text{N} $
0.1	理论模型	−0.392 9	780.362 9	−585.272 3	−0.067 6
0.1	ADAMS	−0.392 8	780.363 0	−585.272 3	−0.067 6
1.3	理论模型	−82.479 2	774.953 1	−584.030 5	−16.771 6
1.3	ADAMS	−82.478 9	774.952 9	−583.901 6	−17.293 1
1.8	理论模型	−157.163 8	760.479 3	−580.699 4	−31.557 4
1.8	ADAMS	−155.234 4	757.234 8	−578.239 4	−32.342 3

Table 3. Comparison table of parameters

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着陆模式	工况	坡度/rad	横向速度/（m·s⁻¹）	纵向速度/（m·s⁻¹）	足垫距着陆面最小距离/m
4腿同时着陆	1	0	0	3	0.03
	2	0	0.5	3	0.03
	3	0	−0.5	3	0.03
“2-2”着陆模式	4	0.175	0	3	0.03
	5	0.175	0.5	3	0.03
	6	0.175	−0.5	3	0.03
“1-2-1”着陆模式	7	0.175	0	3	0.03
	8	0.175	0.5	3	0.03
	9	0.175	−0.5	3	0.03

Table 4. Simulation conditions in ADAMS

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着陆模式	工况	出现峰值时刻/s	本体加速度/（m·s²）	稳定时间/s	最大过载
4腿同时着陆	1	0.013	29.091	≈0.610	<3g_n
	2	0.020	28.429	≈0.650	<3g_n
	3	0.020	28.429	≈0.650	<3g_n
“2-2”着陆模式	4	0.020	54.468	≈0.820	<6g_n
	4	0.125	26.578	≈0.820	<3g_n
	5	0.020	50.821	≈0.850	<6g_n
	5	0.143	32.920	≈0.850	<4g_n
	6	0.020	66.104	≈0.810	<7g_n
	6	0.123	38.732	≈0.810	<4g_n
“1-2-1”着陆模式	7	0.030	8.068	≈0.650	<1g_n
		0.083	20.570		<3g_n
		0.110	52.961		<6g_n
	8	0.020	10.736	≈0.650	<2g_n
		0.825	65.767		<7g_n
		0.106	27.966		<3g_n
	9	0.016	12.829	≈0.550	<13g_n
		0.080	20.890		<3g_n
		0.120	29.062		<3g_n

Table 5. Simulation results of landing

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参数名称	数值
抗弯强度/MPa	1 646
弹性模量/（10⁴ MPa）	11.76
密度/（g·cm⁻³）	4.5

Table 6. Titanium alloy mechanical properties parameters

Shan JIA, Rujie HU, Xianghua ZHOU, Shaoyang LIU, Mingyang WU, Jinbao CHEN. Design and Analysis of a New Reusable Lander[J]. Spacecraft Recovery & Remote Sensing, 2024, 45(2): 1

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