Twin-engine push-back canard rotor/fixed-wing compound vertical take-off and landing aircraft
A vertical take-off and landing, push-type duck technology, applied in vertical take-off and landing aircraft, aircraft, rotorcraft and other directions, can solve the problems of complex conversion control of vertical take-off and landing aircraft, low overall structural rigidity, unfavorable high-speed flight, etc., to achieve good high-speed The effects of flight survivability, large combat radius, and smooth transition transitions
Active Publication Date: 2018-09-11
BEIHANG UNIV
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Problems solved by technology
[0003] 1. The conversion control of vertical take-off and landing aircraft based on tilt rotor technology is complex
[0004] 2. The rotor of vertical take-off and landing aircraft based on stalled rotor technology is the main load-bearing component in the level flight mode, and the rotor generally has a relatively large span, and the overall structural stiffness is lower than that of a general fixed wing surface, which is easy to fly when the flying speed is fast. Flutter and other aeroelastic problems occur, which is not conducive to high-speed flight
Method used
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Embodiment Construction
[0017] The present invention will be described in detail below in conjunction with the accompanying drawings and embodiments.
[0018] The invention provides a dual-engine push-back canard rotor / fixed-wing composite vertical take-off and landing aircraft, such as figure 1 As shown, the main components are a special rotor 1, a canard 2, a rear wing 3, a vector propulsion propeller 4 and a fuselage 5. The special type rotor 1 is installed on the top of the fuselage 5 middle part, and is a double-blade layout. The plane shape and selected airfoil are different from the common helicopter rotor, and provide lift in different forms in different flight modes of the aircraft. The planar shape of the blade of special rotor 1 is an isosceles trapezoid, and the blade aspect ratio 6-10 (the described width refers to the average width), is wider than the conventional helicopter rotor blade (length-width ratio 15-20), and the tip The root ratio is about 0.6, and the front and rear symmetri...
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The invention discloses a double-engine rear-propelling type duck type rotor / fixed wing combined type vertical take-off and landing aircraft and belongs to the field of aviation aircraft design. The aircraft comprises a special-shaped rotor, duck wings, rear wings, vector propellers and an aircraft body. The vector propellers are symmetrically arranged on the rear edges of the rear wings on the two sides of the aircraft body and can rotate up and down by 20 degrees relative to the plane of the aircraft body. The aircraft has the vertical take-off and landing capacity and the high-speed flat flying capacity at the same time, and the two modes can be switched in the air. The special-shaped rotor is similar to a rotor of a conventional helicopter and has the same flight efficiency, the vertical take-off and landing flight performance and the low-speed flight performance of the aircraft are similar to those of the conventional helicopter, and the flat flying speed, the voyage and the endurance are improved by about 50% compared with those of the conventional helicopter. The larger operation range and the higher operation capacity are achieved, and the helicopter can be replaced with the aircraft in future.
Description
technical field [0001] The invention belongs to the field of aviation vehicle design, and in particular relates to a double-engine push-back type canard rotor / fixed wing composite vertical take-off and landing aircraft. Background technique [0002] At present, the outstanding feature of helicopters is that they can perform low-altitude (a few meters from the ground), low-speed (starting from hovering) and maneuvering flight with the same nose direction, especially vertical take-off and landing in small areas. However, there are speed obstacles in helicopters, and high-speed flight cannot be achieved. Currently mature vertical take-off and landing aircraft has the following deficiencies: [0003] 1. The conversion control of the vertical take-off and landing aircraft based on the tilt rotor technology is complicated. [0004] 2. The rotor of vertical take-off and landing aircraft based on stalled rotor technology is the main load-bearing component in the level flight mode,...
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IPC IPC(8): B64C27/28B64C27/22B64C29/00B64F5/00
CPCB64C27/22B64C27/28B64C29/00B64F5/00
Inventor 蒋崇文鲍蕊张啸迟葛昕怡严德王耀坤李道春万志强
Owner BEIHANG UNIV