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| Landing Adaptability Simulation Analysis of Airbag Recovery System |
| Received:May 11, 2018 Revised:September 25, 2018 |
| View Full Text View/Add Comment Download reader |
| DOI：10.7643/ issn.1672-9242.2018.09.011 |
| KeyWord:airbag calculation simulation modeling dynamic model |
| Author | Institution |
| ZHAO Bing-qi |
1. State Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing, , China |
| XU Zhen-liang |
2. Research and Development Center of China Launch Vehicle Technology Research Institute, Beijing, , China |
| WU Sheng-bao |
2. Research and Development Center of China Launch Vehicle Technology Research Institute, Beijing, , China |
| HE Huan |
1. State Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing, , China;3. Institute of Vibration Engineering Research, Nanjing University of Aeronautic and Astronautic, Nanjing, , China |
| CHEN Guo-ping |
1. State Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing, , China;3. Institute of Vibration Engineering Research, Nanjing University of Aeronautic and Astronautic, Nanjing, , China |
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| Abstract: |
| Objective To propose an airbag landing buffer equivalent analysis method, combine the finite element simulation and the theory analysis and have rapid assessment of the landing buffer impact performance of the airbag recovery system based on advantages of theoretical analysis. Methods Firstly, the finite element model of the airbag was established. The load-compression curve was obtained by finite element analysis. The relationship between the contact load and the airbag compression was fitted according to the curve. At the same time, the surface of a slope was simulated with a Gaussian function. A mass (simulated spacecraft) attached to an airbag impacted the slope surface with an initial velocity. Only the impact of the grade and the surface roughness on the airbag load were considered. Finally, the center difference method was used to calculate the displacement, velocity and acceleration. Results When the impact point slopes were 0°, 20.27°, and 31.24°, the theoretical maximum overload in the horizontal and vertical directions was obtained after calculation. Compared the results with the simulation outputs, within the allowable error range, the theoretical and simulation results were nearly the same. Horizontal and vertical maximum overload and the angular velocity of the airbag under the slope of different impact points were analyzed and compared. When the impact point slope was 0°, the maximum overload in the horizontal direction was 0. As the impact point slope increased, the maximum overload in the horizontal direction gradually increased. When the impact point slope was 0°, the maximum overload in the vertical direction was the maximum- 224.5 m/s2. The maximum overload in the vertical direction gradually decreased as the impact point slope increased. When the impact point slope was 0°, the angular velocity was 0, and the angular velocity of the airbag gradually increased and increased larger between 0° and 20°. Conclusion The calculated results of the air bag landing buffer equivalent analysis method are consistent with the simulation results, which verifies the validity of the theoretical calculation method. Therefore, this method can be used to quickly evaluate the impact performance of the cushion air bag. |
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