UAV minimum altitude protection control system
A low-altitude, unmanned aerial vehicle technology, applied in the direction of control/adjustment system, aircraft control, vehicle position/route/height control, etc., can solve the problems of not being able to control the minimum flight height, not being able to troubleshoot, etc., and achieve track control accuracy Improve and reduce the effect of damage
Active Publication Date: 2011-02-16
CHENGDU AIRCRAFT INDUSTRY GROUP
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Problems solved by technology
In order to overcome the deficiency that existing unmanned aerial vehicle self can not control the minimum flying altitude and self can not troubleshoot, this
Method used
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[0018] FIG. 1 depicts a computer (hereinafter referred to as control
Computer) is the control center and is electrically connected to the height sensor, rudder control system, throttle control system and / or parachute landing system,
It is composed of a fault handling system that controls the lowest altitude of the drone. among them,
[0019] Control computer with timing interrupt function: calculate the angle of the rudder surface according to the height signal provided by the height sensor
And the throttle opening of the engine are transmitted to the rudder control system and the throttle control system. When the altitude exceeds the minimum boundary, it can be
Control the aircraft to automatically parachute and land. Control the computer.
[0020] Altitude sensor: Collect the altitude signal of the aircraft, and provide the altitude value of the aircraft to the control computer, the sampling rate is not low
At 50Hz and passed to the flight control system.
[0021] Rudder surf...
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The invention relates to an automatic protection control system for the lowest altitude of an unmanned aerial vehicle in the technical field of unmanned aerial vehicles. A control system with a computer as the control center and an altitude sensor electrically connected to the computer, a rudder surface control system, a throttle control system and / or a parachute system, the computer is equipped with a small-height fault handling program component that is started by timing interruption, and the program component Including: low-altitude over-boundary control module and low-altitude fault handling control module. It judges whether it is necessary to control the altitude of the aircraft according to the altitude provided by the high-speed sensor. When the altitude is lower than the minimum boundary, it automatically controls the flight altitude of the aircraft and forcibly resumes normal flight. The invention can adjust the throttle opening of the engine through the fault handling program components to increase the flight speed of the aircraft and restore normal flight. Even in the case of strong interference, it can accurately measure and control the height of the UAV, and implement autonomous flight beyond the line of sight. It solves the defect that the existing drones do not have the minimum flight altitude control and are prone to stall and cause flight accidents.
Description
Technical field of UAV minimum height protection control system [0001] The present invention relates to the technical field of unmanned aerial vehicles, and in particular to an unmanned aerial vehicle minimum altitude protection control system. Background technique [0002] In the future high-tech warfare, drones will become a very effective and indispensable weapon equipment. Receive more More and more countries are paying attention. At present, the military of many countries puts drones as a priority for development. Drone is a Reusable aircraft, unlike manned aircraft, drones fly at a predetermined altitude and need to monitor aircraft The flight parameters of the aircraft control the flight of the aircraft, and the autonomous control ability is poor, and the malfunction cannot be eliminated by itself. Make instantaneous adjustments, Usually they have to return to the base, which is prone to crash accidents. There are few sensors carried by itself, and the accuracy of a...
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Login to View More IPC IPC(8): G05D1/00B64C39/02B64C19/00
Inventor 夏斌李涛宋承志
Owner CHENGDU AIRCRAFT INDUSTRY GROUP