Tandem vector dual-rotor electric vertical take-off and landing unmanned aerial vehicle and control method thereof
A technology for vertical take-off and landing and unmanned aerial vehicle, which is applied to vertical take-off and landing aircraft, rotorcraft, unmanned aerial vehicles, etc., can solve the problems of high production cost and complicated rotor control mechanism, and achieve the effect of simple and reliable mechanism.
Pending Publication Date: 2018-11-13
北京天宇新超航空科技有限公司
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[0004] Chinese patent application No. CN201610245385 and patent application No. CN201810083492 proposed the layout of tandem dual-rotor vertical take-off and landing aircraft, but these two schemes have the problems of complicated rotor control mechanism and high production cost, and only provide horizontal flight state and vertical flight state The reference scheme of the control method does not discuss and explain the controllability of the UAV in the transition state and transition state of the scheme
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[0042] The present invention will be further described below through specific embodiments in conjunction with the accompanying drawings.
[0043] The embodiment of the present invention provides a specific tandem vector dual-rotor electric drive vertical take-off and landing UAV, which includes: a front rotor 1, a rear rotor 2, a fuselage 3, a wing 4, a vertical tail 5 and a horizontal tail 6. Wherein, the present embodiment specifically adopts a biaxially tilted front rotor 1 and a single-axis tilted rear rotor 2 , which are respectively arranged in tandem at the front and rear positions of the fuselage 3 . The fuselage 3 is connected to various components of the drone and can accommodate flight loads.
[0044] The aircraft should be able to fly in three flight states, including: vertical flight state, transition and transition state and level flight state. figure 1 It is a schematic diagram of the level flight state of the unmanned aerial vehicle according to the embodiment...
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The invention discloses a tandem vector dual-rotor electric vertical take-off and landing unmanned aerial vehicle, and belongs to the field of design of vertical take-off and landing aircrafts. The unmanned aerial vehicle has two flight states of vertical take-off and landing, hovering (vertical flight state) and high-speed forward flight (horizontal flight state), and can effectively solve the flight control problems of vertical flight, horizontal flight (transition state) and horizontal flight (slew state) through vector thrust rotor wings. The unmanned aerial vehicle comprises a fuselage, wings respectively positioned on the left side and the right side of the fuselage, and a front rotor and a rear rotor respectively positioned on the front side and the rear side of the fuselage; the front rotor and the rear rotor are positioned on the axis of the fuselage and are longitudinally arranged; and at least one of the front rotor and the rear rotor is a dual-shaft tilt rotor system. Compared with the prior art, the double-shaft tilt rotor system can realize attitude control of the unmanned aerial vehicle in the whole process, and the unmanned aerial vehicle has the advantages of simple mechanism, controllable transition state and high structural pneumatic efficiency.
Description
technical field [0001] The invention belongs to the field of vertical take-off and landing aircraft design, in particular to a vertical take-off and landing aircraft with a tandem double-rotor layout. Background technique [0002] A vertical take-off and landing aircraft is an aircraft that combines the inherent vertical take-off and landing advantages of a helicopter with the high-speed level flight performance of a fixed-wing propeller aircraft. Traditional more mature vertical take-off and landing aircraft include thrust-steering British Harrier, Soviet Yak 35 and American F35 fighter jets, and tilt-rotor V22 Osprey transport aircraft. This type of aircraft does not need to run during takeoff and landing, and can also achieve a relatively fast flight speed during level flight. Therefore, this type of aircraft basically gets rid of the dependence on the runway, the cost of takeoff and landing is very low, it can realize rapid deployment and maneuver, and can solve the pro...
Claims
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Login to View More IPC IPC(8): B64C27/22B64C29/00B64C27/52
CPCB64C27/22B64C27/52B64C29/00B64U10/00B64U10/25B64U50/19
Inventor 胡龙王一博
Owner 北京天宇新超航空科技有限公司