Flying wing unmanned aerial vehicle large overload steady disk maneuvering control method

An unmanned aerial vehicle, high overload technology, applied in the field of aviation flight control, to achieve the effect of simplifying the design work and clear control logic

Inactive Publication Date: 2020-09-29
CHENGDU AIRCRAFT INDUSTRY GROUP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] The main purpose of the present invention has: 1. Propose a kind of control method that the large overload of flying-wing unmanned aerial vehicle is stable circling maneuver;

Method used

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  • Flying wing unmanned aerial vehicle large overload steady disk maneuvering control method
  • Flying wing unmanned aerial vehicle large overload steady disk maneuvering control method
  • Flying wing unmanned aerial vehicle large overload steady disk maneuvering control method

Examples

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Effect test

Embodiment 1

[0044] The large overload stabilization maneuver control method of the flying-wing unmanned aerial vehicle of the present invention includes the stabilization maneuver control logic and the closed-loop control mode of the engine gauge speed, the altitude maintenance control mode, and the roll angle control mode;

[0045] The logic of the maneuvering control for stabilizing the plate is as follows:

[0046] Stable and level flight before the stable slope is established, vertically call the altitude hold mode, and the altitude control target is the current altitude; horizontally call the roll angle hold mode; the engine calls the gauge speed closed-loop control mode, and the control target is the current gauge speed;

[0047] Steady maneuver stage: vertically call the altitude hold mode, and the height control target is the altitude when entering the steady maneuver; laterally call the roll angle hold mode, and the roll angle control target is the proposed set value; the engine c...

Embodiment 2

[0053] The maneuvering control method of the flying-wing unmanned aerial vehicle with large overload of the present invention includes the method of calling the control law mode of the maneuvering control process of the stabilizing plate, the closed-loop control mode of the engine speed, the altitude maintenance control mode, and the roll angle control mode:

[0054] ① Steady maneuvering control logic

[0055] Stabilize and level flight for 2 seconds before establishing a stable slope, call the altitude hold mode vertically, and the altitude control target is the current altitude; call the roll angle hold mode horizontally, and the roll angle command is 0°; call the closed-loop control mode of the engine speed, and control the target is the current gauge speed.

[0056] Steady maneuvering stage: call the altitude hold mode vertically, and the altitude control target is the height when entering the steady maneuver; call the roll angle hold mode laterally, and the roll angle con...

Embodiment 3

[0073] When the UAV of the present invention is flying, the longitudinal control mode, the lateral control mode, the engine control mode, and the course control mode need to be called at the same time, and the course in the present invention always calls the stabilization control mode.

[0074] Such as figure 1 As shown, the main flow of the modal scheduling logic is:

[0075] The first stage: first switch from the current state to the level flight state, that is, vertically call the altitude control mode, and the control target is the height before turning to the level flight state; the engine control calls the airspeed control mode, and the control target is to turn to the level flight state The airspeed before the state; the roll angle control mode is called laterally, and the control target is 0°;

[0076] The second stage: establish the roll slope, when the flying height of the aircraft enters the tolerance zone of the given height ±30m (should be selected according to t...

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Abstract

The invention discloses a flying wing unmanned aerial vehicle large overload steady disk maneuvering control method. The method comprises a steady disk maneuvering control logic, an engine surface speed closed-loop control mode, a height keeping control mode and a roll angle control mode. The method is applied to a flying wing layout unmanned aerial vehicle and provides an automatic control methodfor each control channel in a stable circling maneuvering process. According to the method, a gradient of the unmanned aerial vehicle can be established by calling the roll angle control mode, fixed-height flight is realized by calling the height keeping control mode, and fixed-speed flight is realized by calling the engine surface speed closed-loop control mode so that the stable circling maneuvering action of the unmanned aerial vehicle is completed. By reasonably and automatically controlling the engine and a control surface, stable circling maneuvering flight of the flying wing layout unmanned aerial vehicle can be achieved, and a flight direction of the unmanned aerial vehicle can be rapidly changed.

Description

Technical field: [0001] The present invention relates to the technical field of aviation flight control, and more specifically, the present invention relates to the maneuvering flight control of a flying-wing unmanned aerial vehicle. Background technique: [0002] UAVs have the characteristics of small size, flexible maneuverability, easy operation, low cost of use, high efficiency, and long battery life. It can be accompanied by combat troops, and independently perform reconnaissance, surveillance, fire attack, interference and other combat tasks in its own system, which greatly reduces the casualties caused by war. It is one of the weapons and equipment favored by various military powers in the world today. [0003] The flying wing layout UAV cancels the tail, which leads to poor longitudinal and directional control performance of the aircraft, and the control surface must be controlled reasonably to generate sufficient control torque. The elevon is a function that can re...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C19/00
CPCB64C19/00B64U10/25
Inventor 唐瑞卿陈伟刘宇佳崔庆梁张延荣
Owner CHENGDU AIRCRAFT INDUSTRY GROUP
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