Thrust vector unmanned aerial vehicle based on ducted fan
An unmanned aerial vehicle, thrust vectoring technology, applied in aircraft, aircraft parts, high-efficiency propulsion technology, etc., can solve the problems of slow thrust response of turbojet engines, low thrust level stability, limited application scenarios, etc., to avoid thermal effects, The effect of improving adaptability and increasing response bandwidth
Active Publication Date: 2022-04-05
HARBIN INST OF TECH
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Problems solved by technology
The aircraft solves many shortcomings of hybrid aircraft through thrust vectoring, but the turbojet engine has problems such as slow thrust response, low thrust level stability, difficult thermal management, and high noise level, so the application scenarios are limited
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[0032] The present invention will be further described below in conjunction with the accompanying drawings.
[0033] Such as figure 1 As shown, a thrust vectoring unmanned aerial vehicle based on a ducted fan is composed of a thrust vectoring unmanned aerial vehicle body, support components on the body, a thrust vectoring power unit and a flight control system; wherein, the thrust vectoring unmanned aerial vehicle body It includes a frame (101) and a frame plate (102); the supporting parts on the body include a ducted fan support (1011), an elbow support (1012), a steering gear support (1013), an electric adjustment support seat (1014), battery box (1015), aluminum plate one (1016), aluminum plate two (1017), isolation column one (1018), isolation column two (1019); the thrust vector power unit includes a ducted fan (103 ), L-shaped elbow (104), brushless steering gear (105), electronic governor (106), battery (107), connecting rod one (1020), connecting rod two (1021), rudde...
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The invention discloses a thrust vector unmanned aerial vehicle based on ducted fans, and relates to a thrust vector unmanned aerial vehicle. The invention aims to solve the problems that an existing aircraft cannot vertically take off and land, hover at fixed points and fly horizontally, and is poor in maneuvering performance and the like. The technical key points are as follows: the aircraft comprises a thrust vector unmanned aircraft body, four thrust vector power units, a flight control system and a power supply; the thrust vector unmanned aerial vehicle body comprises a rack and a rack flat plate mounted on the rack; the four corners of the rack flat plate are each provided with one thrust vector power unit, and the flight control system is installed in the middle of the rack flat plate. The navigation computer data transmission module is used for providing navigation information for the small flight control computer; the small flight control computer is used for controlling the starting, stopping and rotating speed of each ducted fan through the corresponding electronic speed regulator; and the small flight control computer is also used for controlling the action of each brushless steering engine. The unmanned aerial vehicle has the functions of vertical take-off and landing, spot hover and horizontal flight, and has the super-maneuverability of instantaneously changing the flight attitude and trajectory.
Description
technical field [0001] The invention relates to a thrust vectoring unmanned aerial vehicle, in particular to a thrust vectoring unmanned aerial vehicle based on a ducted fan, and belongs to the technical field of aircraft equipment. Background technique [0002] Existing aircraft are mainly divided into two categories: horizontal take-off and landing aircraft (such as fixed wings), vertical take-off and landing aircraft (such as helicopters and multi-rotors) and hybrid aircraft (such as tilting rotors). The traditional horizontal take-off and landing aircraft has the advantages of fast flight speed and low energy consumption, but has the disadvantages of high take-off and landing requirements and long take-off and landing distance; the traditional vertical take-off and landing aircraft has the advantages of convenient take-off and landing, but has the disadvantages of high energy consumption , low safety factor, poor load capacity, and slow horizontal flight speed; the curre...
Claims
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IPC IPC(8): B64C27/20B64D27/24B64D31/00
CPCY02T50/60
Inventor 白成超郭继峰唐浩楠张培康
Owner HARBIN INST OF TECH