A generalized instruction generator and instruction generation method for variable flight mode unmanned aerial vehicle

A command generation and generator technology, applied in the field of UAV flight control, can solve the problems of automatic mode conversion limitation, insufficient trim information output, poor stability, etc.

Inactive Publication Date: 2011-12-21
BEIHANG UNIV
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AI Technical Summary

Problems solved by technology

[0005] Many researchers often use the trial and error method to realize the trimming during the mode transition process of the variable flight mode UAV. The trimming process does not consider the comprehensive optimization of the attitude angle and the deflection angle of the control surface, the stability is poor, and the

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  • A generalized instruction generator and instruction generation method for variable flight mode unmanned aerial vehicle
  • A generalized instruction generator and instruction generation method for variable flight mode unmanned aerial vehicle
  • A generalized instruction generator and instruction generation method for variable flight mode unmanned aerial vehicle

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Embodiment Construction

[0149] Below in conjunction with accompanying drawing, the present invention is described in further detail:

[0150] The present invention proposes a variable flight mode unmanned aerial vehicle generalized command generator, such as figure 1 As shown, it includes the guide command generator, the controlled state command generator, the state reference value generator and the generalized control surface reference command generator.

[0151] After the mode transition command TL and time t enter the guidance command generator, the tilt angle command τ for guidance mode transition is generated according to the tilt angle generation function τ(TL, t), and the airspeed generation function V kg (TL, t) Generate airspeed command V kg , and the tilt angle command τ and the airspeed command V kg All are sent to the controlled state command generator, the state reference value generator and the generalized control surface reference command generator.

[0152] The controlled state com...

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Abstract

The invention provides a macro instruction generator for an unmanned aerial vehicle with a variable flying mode and an instruction generation method for the macro instruction generator. The instruction generator comprises a guide instruction generator, a controlled state instruction generator, a state reference value generator and a macro control surface reference instruction generator. Balancing of a mode conversion process is equivalent to the balancing of various combined states in a sequence consisting of tilt angles and desired pitching angles; and in a specific tilt angle and desired pitching angle combined state, iterative optimization balancing is instructed by a cost function, so that balanced values of a state vector and a control vector of the macro control surface are changed stably along with the tilt angle and an air speed instruction. All inner functions of the guide instruction generator, the controlled state instruction generator, the state reference value generator and the macro control surface reference instruction generator are established by adopting a segmental curve fitting method according to a balanced result sequence. The iterative optimization balancing and the curve fitting are realized efficiently and accurately by using matrix laboratory (matlab) math software.

Description

technical field [0001] The invention belongs to the technical field of flight control of unmanned aerial vehicles, and in particular relates to a generalized instruction generator and an instruction generation method for an unmanned aerial vehicle with variable flight modes. Background technique [0002] The variable flight UAV is a thrust / pull vector device added on the basis of a conventional fixed-wing aircraft. Dependence, and efficient execution of tasks, has broad application prospects. [0003] Tiltable rotors and vectoring nozzles are typical forms of thrust / pull vectoring. It can be seen that the thrust / pull vector may contain multiple control quantities. In addition to the throttle control, some control quantities mainly produce the effect of pitch operation, some control quantities mainly produce the effect of yaw operation, and some control quantities mainly produce the effect of roll operation . Therefore, the thrust / pull vector control surface and the aerody...

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Application Information

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IPC IPC(8): G05B17/00G05D1/00
Inventor 王勇刘智
Owner BEIHANG UNIV
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