Rocket-assisted unmanned aerial vehicle launching process multi-field coupling simulation analysis method

Abstract

The invention provides a rocket-assisted unmanned aerial vehicle launching process multi-field coupling simulation analysis method. The method comprises the following steps: (1) dividing the rocket-boosted unmanned aerial vehicle launching process into five stages of fixing the unmanned aerial vehicle on the frame, sliding the unmanned aerial vehicle along the frame, completely separating the unmanned aerial vehicle from the launching frame until the booster finishes working, finishing the work of the booster until the booster is completely separated, and continuously flying the unmanned aerial vehicle; (2) establishing a six-degree-of-freedom kinetic equation set of the unmanned aerial vehicle, and on the basis, establishing a multi-rigid-body kinetic model of the unmanned aerial vehiclelaunching system in ADAMS software; (3) based on the aerodynamic blowing data, establishing an aerodynamic force calculation model capable of calculating aerodynamic force and an aerodynamic moment calculation model capable of calculating aerodynamic moment under different flight attitudes in real time; (4) establishing a flight control system model in the launching process of the unmanned aerialvehicle; and (5) building an unmanned aerial vehicle launching section multi-field coupling joint simulation data interaction platform.

Description

technical field [0001] The invention relates to a multi-field coupling simulation analysis method for a rocket-assisted unmanned aerial vehicle launch process, belonging to the field of rocket-assisted unmanned aerial vehicle launch simulation analysis. Background technique [0002] UAVs use rocket-assisted launch methods, which have the advantages of convenience, speed, low requirements for launch sites, and are suitable for field environments, and have been widely used; however, the launch safety of UAVs that use rocket-assisted launch methods is limited. There are many influencing factors, including: launcher interference, booster suspension deviation, booster thrust temperature characteristic interference, booster installation and separation before and after the impact on the center of mass of the assembly, turbojet engine thrust on the aircraft attitude, Interference before and after the release of the locking force, etc. [0003] In order to improve the launch safety ...

AI Technical Summary

Problems solved by technology

[0003] In order to improve the launch safety of the rocket-assisted UAV, the flight control system usually intervenes during the launch phase of the UAV to actively control the attitude of the launch end of the aircraft; it can be seen that the launch process of the rocket-assisted UAV involves When it comes to system structure design-aerodynamic characteristics-flight control design and other aspects, it is a typical multi-physics field coupling problem; the current single-type simulation method (mathematical model simulation method, dynamics simulation method) commonly used in the launch section cannot realize the rocket High-precision simulation of boosting UAV launch process

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