Method for simulating takeoff stages of single shot included angle type rocket boosted unmanned aerial vehicles

Abstract

The invention discloses a method for simulating takeoff stages of single shot included angle type rocket boosted unmanned aerial vehicles. The method comprises the following steps of: firstly analyzing locomotion mechanisms of three stages such as in-orbit sliding, rocket disengaging and rising to a safety height, and speed flight, so as to determine force and moment, acting on an airplane, of each flight stage; establishing a mathematic model by utilizing a three-state locomotion mechanism equation set; completing digital-analog simulation by utilizing a Matlab simulation environment so as toobtain reliable unmanned aerial vehicle safe launch envelope. According to the method, powerful technical support is provided for safe launch of unmanned aerial vehicles.

Description

technical field [0001] The invention relates to the technical field of unmanned aerial vehicle take-off simulation, and in particular to a simulation method for the unmanned aerial vehicle's take-off stage of a single-engine angle rocket booster launch. Background technique [0002] The UAV launch system is an important functional system of the UAV, and the safe launch envelope of the UAV is the core parameter of the UAV launch system, which aims to ensure the smooth launch of the UAV to achieve a safe height and speed flight. [0003] For unmanned aerial vehicles that use rocket-assisted launch, the failure rate is high during the take-off stage and the risk is high. Therefore, in order to ensure flight safety, it is necessary to provide a safe launch envelope for unmanned aerial vehicles. A set of mature rocket-assisted unmanned aerial vehicles The simulation method of the take-off and launching section of the aircraft is very important. Since the booster rocket provides...

AI Technical Summary

Problems solved by technology

[0004] 1) Separate research is conducted on a single or partial stage. Although the force and moment characteristics of a certain or partial stage can be obtained, it is difficult to grasp the flight characteristics of the entire launch and take-off stage as a whole. It is also possible to safely climb to a safe altitude and speed. Every stage is very important. Only by continuous consideration can we understand the flight characteristics of the aircraft as a whole and grasp the safety envelope. Obviously, it is not enough to only consider the flight characteristics of a certain or part of the stage;

[0005] 2) A lot of simplified assumptions are made on the three-state airframe dynamics equations, such as ignoring the frictional force of the guide rail acting on the aircraft, the reaction force of the front and rear brackets, and the change of mass, etc., which seriously reduces the fidelity of the model. Sexual analysis, those with high sensitivity cannot be simplified, and ignoring low sensitivity will easily lead to insufficient precision;

[0006] 3) For the processing of the on-orbit taxiing stage, it ignores that the aircraft is restrained by the traction of the launcher before decoupling or unlocking. cause model distortion; in addition, for the control law design with the pitch rate as input, ignoring the traction constraint can neither simulate the real flight situation nor be conducive to guiding the flight

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