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Research on parameter matching characteristics of pneumatic launch systems based on co-simulation

Published online by Cambridge University Press:  19 August 2021

Z. Zhang Open the ORCID record for Z. Zhang [Opens in a new window] ,
Y. Peng ,
X. Wei ,
H. Nie ,
H. Chen  and
L. Li
Z. Zhang
Affiliation:
Key Laboratory of Fundamental Science for National Defense-Advanced, Design Technology of Flight Vehicle, Nanjing University of Aeronautics and Astronautics, Nanjing, Jiangsu, China and State Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing, Jiangsu, 210016, China
Y. Peng
Affiliation:
Key Laboratory of Fundamental Science for National Defense-Advanced, Design Technology of Flight Vehicle, Nanjing University of Aeronautics and Astronautics, Nanjing, Jiangsu, China and State Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing, Jiangsu, 210016, China
X. Wei*
Affiliation:
Key Laboratory of Fundamental Science for National Defense-Advanced, Design Technology of Flight Vehicle, Nanjing University of Aeronautics and Astronautics, Nanjing, Jiangsu, China and State Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing, Jiangsu, 210016, China
H. Nie
Affiliation:
Key Laboratory of Fundamental Science for National Defense-Advanced, Design Technology of Flight Vehicle, Nanjing University of Aeronautics and Astronautics, Nanjing, Jiangsu, China and State Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing, Jiangsu, 210016, China
H. Chen
Affiliation:
Key Laboratory of Fundamental Science for National Defense-Advanced, Design Technology of Flight Vehicle, Nanjing University of Aeronautics and Astronautics, Nanjing, Jiangsu, China and State Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing, Jiangsu, 210016, China
L. Li
Affiliation:
Key Laboratory of Fundamental Science for National Defense-Advanced, Design Technology of Flight Vehicle, Nanjing University of Aeronautics and Astronautics, Nanjing, Jiangsu, China and State Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing, Jiangsu, 210016, China
*
wei_xiaohui@nuaa.edu.cn
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Abstract

Pneumatic launch systems for Unmanned Aerial Vehicles (UAVs), including mechanical and pneumatic systems, are complex and non-linear. They are subjected to system parameters during launch, which leads to difficulty in engineering research analysis. For example, the mismatch between the UAV parameters and the parameter design indices of the launch system as well as the unclear design indices of the launching speed and overload of UAVs have a great impact on launch safety. Considering this situation, some studies are presented in this paper. Taking the pneumatic launch system as a research object, a pneumatic launcher dynamic simulation model is built based on co-simulation considering the coupling characteristics of the mechanical structure and transmission system. Its accuracy was verified by laboratory test results. Based on this model, the paper shows the effects of the key parameters, including the mass of the UAV, cylinder volume, pressure and moment of inertia of the pulley block, on the performance of the dynamic characteristics of the launch process. Then, a method for matching the parameter characteristics between the UAV and launch system based on batch simulation is proposed. The set of matching parameter values of the UAV and launch system that satisfy the launch take-off safety criteria are calculated. Finally, the influence of the system parameters of the launch process on the launch performance was analysed in detail, and the design optimised. Meaningful conclusions were obtained. The analysis method and its results can provide a reference for engineering and theoretical research and development of pneumatic launch systems.

Keywords

Pneumatic launchCo-simulationDynamics analysisMatching envelopeOptimisation design
Type
Research Article
Information
The Aeronautical Journal , Volume 126 , Issue 1296 , February 2022 , pp. 381 - 400
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Copyright
© The Author(s), 2021. Published by Cambridge University Press on behalf of Royal Aeronautical Society

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References

REFERENCES

DA FORM 2397-U.Unmanned Aircraft System Accident Report (UASAR).Google Scholar
Siddiqui, B.A., Rahman, H.U., Kumar, C., Solen, M.A. and Bashir, U.D. Computer Aided Modeling and Simulation of Pneumatic U.A.V. Catapult Mechanism. 7th International Mechanical Engineering Congress. 2017, 24–25.Google Scholar
The Editors of“The Whole UAVs in the World”. The Whole UAVs in the World. Beijing: Aviation Industry Press, 2004:288-296. (in Chinese)Google Scholar
Kondratiuk, M. and Ambroziak, L. Design and dynamics of kinetic launcher for unmanned aerial vehicles. Appl. Sciences, 2020, 10, 2949. doi: 10.3390/app10082949.CrossRefGoogle Scholar
Jastrzebski, G. Impact of opening time of the take-off pneumatic launcher main valve on take-off pressure losses, J. KONES, 2016, 23, (4), 175–182.Google Scholar
Szczepaniak, P. and Jozko, M. (2017). Research of Pneumatic Distributors for Launcher of Unmanned Aerial Vehicle (UAV). J. KONBiN, 43, 249–276. doi: 10.1515/jok-2017-0049.CrossRefGoogle Scholar
Min, H., Cheng, H. and Jinhua, P. Dynamic Analysis and Optimization of Pneumatic Wedge-Shaped Launcher for UAV. Trans. Nanjing Univ. Aeronaut. Astronaut., 2018, (5), 866–873.Google Scholar
Xiao Long, L., Shenggang, M.. Simulation research on launch performance of UAV pneumatic launch system. J. Zhengzhou Univ. (Eng. Sci.), 2013, 34, (5), pp 56–58.Google Scholar
Khadr, A., Houidi, A. and Romdhane, L. Development of Co-simulation Environment with ADAMS/Simulink to Study Maneuvers of a Scooter, Berlin, Heidelberg, 2013. Springer Berlin Heidelberg, 2013.CrossRefGoogle Scholar
Zheng, D., Ren, L., Wu, Y. and Liu, J. Research on Multi-physical Modeling and Co-simulation of Aircraft, Cham. Proceedings of the 16th Chinese CAE Engineering Analysis Technology Annual Conference, 2020, 5.Google Scholar
Liu, Z., Zhan, H. and Wang, S. Parameter Matching Characteristics and Safe Set of Carrier Aircraft during Landing Process. 7th Asia-Pacific International Symposium on Aerospace Technology, 2015.Google Scholar
Liu, X., Xu, D. and Wang, L. Match characteristics of aircraft-carrier parameters during catapult takeoff of carrier-based aircraft. Acta Aeronaut. Astronaut. Sin., 2010, 31, (1), pp 102–108.Google Scholar
Wei, L., Xiaoping, M., Ming, Z. and Yang, H. Dynamic simulation and optimization of UAV pneumatic launching. J. Northwestern Polytech. Univ., 2014, 32, (6), 865–871.Google Scholar
Li, Rui., Pei, Jinhua.. Dynamic numerical simulation of the pneumatic and hydraulic launching of UAV. J. Mech. Eng., 2011, 47, (8), 183–190(in Chinese).CrossRefGoogle Scholar
Aquilen-Gomez, E. and Lara-Lopez, A. dynamic of a pneumatic system modeling simulation and experiments. Int. J. Robot. Autom., 1999, 14, (1), pp 39–43.Google Scholar
Jian Fan, L. Pneumatic Transmission System Dynamics, South China University of Technology Press, 1991.Google Scholar
LMS Imagine. Lab AMESim: AMEsim Users’ Guide. LMS International. 2015, Belgium.Google Scholar
LMS Virtual. Lab Motion: VL Motion Users’ Guide. LMS International. 2015, Belgium.Google Scholar
Simulia Isight: ISIGHT Users’ Guide. Dassault Systems, 2016, Paris.Google Scholar
Munk, D.J., Auld, D.J., Steven, G.P. and Vio, G.A. On the benefits of applying topology optimization to structural design of aircraft components. Struct. Multidisc. Optim., 2019, 60, (3), pp 1245–1266.CrossRefGoogle Scholar
Lucas, C.B. Catapult criteria for a carrier based airplane. AD702814, 1968.Google Scholar
Li, K. The Research of Ejection Takeoff and Skyhook Technology of Small UAVs, Nanjing University of Aeronautics and Astronautics, 2019.Google Scholar
Chen, H., Fang, X., Zhang, Z., Xie, X., Nie, H. and Wei, X. Parameter optimisation of a carrier-based UAV drawbar based on strain fatigue analysis, Aeronaut. J., 1–20. doi: 10.1017/aer.2021.1 CrossRefGoogle Scholar