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 demonstrated that the deformed state of the energy-absorbing ring consistently exhibited a petal-shaped inward deformation. The deformation height error was 3.89 %, 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 validat-ed 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 was reduced by 9.2 % compared to the pre-optimized state, and the minimum launch tube pitch displacement am-plitude was 3.45 mm, representing a 1.71 % reduction. When the collision contact surface radius between the energy-absorbing piston and the energy-absorbing ring was 7.5 mm, the peak forward impact force decreased 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 practi-cal engineering reference for the design of high-efficiency space debris removal payloads.
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