空间发射装置管口缓冲特性与参数影响

doi:10.7527/S1000-6893.2025.32328

Abstract

Abstract:

To address the issues of strong impact force and significant vibration at the launch canister of a space launch device， this study proposes a launch canister energy-absorbing structure. The aim is to reduce the impact force generated by the projectile at the launch canister and mitigate launch canister vibration， thereby further enhancing launch accuracy. An internal ballistic model served as the loading condition to establish a launch dynamics model under varying loads. Both simulations and experiments demonstrate that the deformed state of the energy-absorbing ring consistently exhibited a petal-shaped inward deformation. The deformation height error was 14.23%， the recoil force peak error was 0.30%， the forward impact force peak error was 10.72%， the velocity error was 4.14%， and the acceleration peak error was 4.88%， verifying the model's accuracy. Based on this validated model， the influence of key structural parameters on the forward impact force and pitch displacement was analyzed. Results indicate that an energy-absorbing ring inclination angle of 35° yields optimal energy absorption. At this angle， the peak forward impact force is reduced by 9.22% compared to the pre-optimized state， and the minimum launch tube pitch displacement amplitude is 3.45 mm， representing a 1.71% reduction. When the collision contact surface radius between the energy-absorbing piston and the energy-absorbing ring is 7.5 mm， the peak forward impact force decreases by 6.83% compared to a radius of 5.5 mm， with the change in radius having a relatively minor effect overall. This research provides theoretical support and practical engineering reference for the design of high-efficiency space debris removal payloads.

Key words: space debris, forward impact force, structure parameter, dynamics model, energy-absorbing ring

CLC Number:

V476.5

Zihao WANG, Wanxiang WANG, Chenglong WU, Junyu SHAN, Shuai YUE, Zhonghua DU, Lei ZHAO. Buffering characteristics and parameter influence of launch canister of space launch devices[J]. Acta Aeronautica et Astronautica Sinica, 2026, 47(4): 232328.

Figures/Tables 25

Fig.1

Table 1

Fig.2

Fig.3

Fig.4

Table 2

Primary material parameters of 2A12-T4 aluminum alloy［29］

密度 $ρ / k g · m - 3$	弹性模量 $E / G P a$	泊松比 $μ$
2 770	71.7	0.33

Table 2

Table 3

Johnson-Cook constitutive model parameters

A/MPa	B/MPa	$n$	C	$m$
400	424	0.35	0.001	1.426

Table 3

Table 4

Fig.5

Fig.6

Fig.7

Fig.8

Fig.9

Fig.10

Fig.11

Fig.12

Table 5

Peaks of forward impact force for different θ

$θ$ /（°）	前冲力峰值/N
10	622.17
20	480.09
35	435.84
50	651.99
65	652.45

Table 5

Fig.13

Table 6

Peaks of pitch displacement for different θ

$θ$ /（°）	最大俯仰位移/mm
10	3.57
20	3.51
35	3.45
50	3.59
65	3.61

Table 6

Fig.14

Table 7

Peaks of forward impact force of different R

$R$ /mm	前冲力峰值/N
3.5	487.55
5.5	480.09
7.5	447.28
+∞	546.04

Table 7

Fig.15

Table 8

Peaks of pitch displacement for different R

$R$ /mm	最大俯仰位移/mm
3.5	3.60
5.5	3.51
7.5	3.45
+∞	3.70

Table 8

Table 9

Sensitivity results for θ

$θ$ /（°）	$Δ F F r e f / %$	$S θ F$	$Δ D D r e f / %$	$S θ D$
10	+29.59	-0.59	+1.71	-0.034
35	-9.22	-0.12	-1.71	-0.023
50	+35.80	+0.24	+2.39	+0.016
65	+35.90	+0.16	+2.96	+0.013

Table 9

Table 10

Sensitivity results for R

$R$ /mm	$Δ F F r e f / %$	$S R F$	$Δ D D r e f / %$	$S R D$
3.5	+1.55	-0.043	+2.50	-0.069
7.5	-6.83	-0.188	-1.65	-0.045
+∞	+13.94	+0.139	+5.50	+0.055

Table 10

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序号	部件	材料	质量/g
1	压盖	30CrMnSiA	17
2	吸能环	2A12-T4	1
3	发射管	TC4	38
4	牵引体	12Cr18Ni9	0.87
5	前定心	PA66	5.91
6	后定心	7075-T6	0.22
7	吸能活塞	7075-T6	1
8	密封圈	NBR	0.2
9	螺堵	7075-T6	1.5
10	药室	7075-T6	80
11	点火器		2

Buffering characteristics and parameter influence of launch canister of space launch devices

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