Ball-borne unmanned aerial vehicle system launching section guidance law design method based on dynamic pressure compensation

Abstract

The invention provides a ball-borne unmanned aerial vehicle system launching section guidance law design method based on dynamic pressure compensation. The method comprises the steps that a standard dynamic pressure generator generates standard dynamic pressure values at different altitudes on line and outputs the standard dynamic pressure values to a standard dynamic pressure comparator; the standard dynamic pressure comparator calculates the ratio of the dynamic pressure at the current moment to the standard dynamic pressure as the input of the dynamic pressure compensator; the dynamic pressure compensator processes the input value according to a preset rule and then inputs the input value to the guidance instruction generator as a feedforward item, and the guidance instruction generatorsuperposes the input values of the dynamic pressure compensator to generate a guidance instruction and outputs the guidance instruction to the attitude controller. According to the ball-borne unmanned aerial vehicle system launching section guidance law design method based on dynamic pressure compensation, the dynamic pressure value is introduced into guidance instruction feedback to reduce the overload and the maximum speed value of the aircraft in the throwing and pulling process so that the safety of the aircraft in the level flight stage after ball-borne throwing is guaranteed, the dynamic pressure value is measurable, the guidance law curve is continuous, and the actual engineering application is facilitated.

Description

technical field [0001] The invention relates to the field of unmanned aerial vehicles, in particular to a design method of a guidance law for high-altitude ball-borne delivery of solar unmanned aerial vehicles based on dynamic pressure compensation. Background technique [0002] Generally speaking, the mission cycle of UAVs includes the following stages: ground roll, takeoff, cruise, descent and landing. But for UAVs in near space, in order to reduce the structural weight of the UAV itself and reserve space for the assembling load, at present, engineering also considers the use of an aerostat platform for take-off. For UAVs that use an aerostat platform to take off, their mission cycle is different from that of previous UAVs, and usually includes the following stages: ball-borne take-off, delivery to level flight, cruise, descent and landing. process. The ball-borne take-off process mainly depends on the control of the aerostat platform, while the process of launching to l...

AI Technical Summary

Problems solved by technology

[0004] At present, there is no existing technology on the design method of the ball-borne delivery guidance law in China. In the existing guidance law design, the design method of directly introducing the overload into the guidance loop is usually adopted for the rigid-body aircraft that performs large maneuvers. Although the aircraft's Overload can be measured directly by inertial sensors, but overload measurements are too noisy

For solar-powered drones, there are factors such as elastic deformation, and the direct introduction of overload feedback during the launch and pull-up process will cause a large jitter in the guidance command. The direct result of feedback to the attitude controller loop is the elevator. Vibration is more frequent, which will affect the actual flight effect

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