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Dynamics of the manned spacecraft's main parachute outlet |
| WANG Yongbin1,2,3, ZHANG Yajing2,3, HUANG Xuejiao2,3, YIN Sha4, CHEN Dianhao4, WANG Qi2,3, LEI Jiangli2,3, JIA He1,2,3, CHEN Jinbao1,3 |
1. College of Astronautics, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;
2. Beijing Institute of Space Mechanics & Electricity, Beijing 100094, China;
3. Laboratory of Aerospace Entry, Descent and Landing Technology, China Aerospace Science and Technology Corporation, Beijing 100094, China;
4. School of Transportation Science and Engineering, Beihang University, Beijing 100191, China |
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Abstract [Objective] China's new-generation manned spacecraft test ship uses two deceleration parachutes and three main parachutes for pneumatic deceleration recovery. The main parachute bag is separated and pulled out after the deceleration parachute has completed its work. The main parachute bag is then pulled out from the parachute cabin as a key and important link in parachute deceleration in the design of the recovery landing system. The pullout process of the main parachute bag involves multibody coupling, such as slings, parachute bags, and hatch covers. Thus, the process is relatively complicated and theoretical calculations are generally used. Accurately describing the process, which could lead to countless errors in the actual process, is difficult.[Methods] This paper propose a finite element analysis method to establish a dynamic analysis model for the main parachute out of the cabin to solve the aforementioned problem and accurately understand the changes produced in this process. In addition, the actual parachute and rope system calculation model is established to quantify the relative motion and load of each component accurately in the pullout process of the main parachute, and the load distribution of different connecting parts is obtained, providing support for the system design and evaluation. The parachute aerodynamic deceleration model is simplified on the basis of the aerodynamic load dynamic matching control method, which affects the initial speed of the main parachute out of the cabin. Influencing factors, such as the tensile force of the heat shield and the quality of the hatch cover, are comprehensively analyzed and compared. The response characteristics of the load, speed, and overload of the main parachute bag out of the cabin are obtained, and the entire process of the main parachute bag out of the cabin is intuitively described.[Results] The method for the main parachute out of the cabin demonstrated the following results:1) The main parachute pullout process based on finite element analysis technology could accurately describe the coupling relationship between parachute components and simplify the aerodynamic calculation of parachutes. The dynamic iterative aerodynamic load subroutine could reduce the calculation amount and provide an efficient analysis means for the dynamic analysis of the reentry capsule. 2) With the increase in the initial speed in the pullout process of the main parachute, the time required for the complete pullout of the main parachute was short, the load on each sling increased, and the overload of the entire cabin also showd a rising trend. Therefore, the initial drawing boundary conditions should be strictly controlled. 3) The mass of the main umbrella covered considerably affected the peak force of the total towing load curve of the umbrella and would increase with the mass. Thus, the weight of the main umbrella cover should be strictly controlled in the scheme design to reduce the load of the umbrella towing.[Conclusions] This method effectively guides the design of the recovery system for a new generation of manned spacecraft test ships and provides theoretical support for subsequent formal flight missions.
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| Keywords
new spacecraft
return cabin
main parachute bag
exit cabin
overload
impact
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Issue Date: 04 March 2023
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2023,
Vol. 63
