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Rotated quadrotor

A technology for tilting quadrotors and aircraft, applied in aircraft, rotorcraft, aircraft parts, etc., can solve problems such as performance changes and increased resistance of quadrotors, and achieve the effects of simple structure, reduced resistance, and increased flight speed.

Active Publication Date: 2015-11-11
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Although this solution can enable the fuselage to generate a certain lift and improve the performance of the aircraft, but during the flight, when the flight speed changes, the windward angle of the fuselage will also change, and the faster the speed, the greater the forward tilt angle of the fuselage. , so that the flight resistance will be greatly increased, and the changes to the performance of the quadrotor aircraft will be very limited.

Method used

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Embodiment Construction

[0028] The present invention will be further described in detail below with reference to the drawings and embodiments.

[0029] The invention provides a tilting quad-rotor aircraft, such as Figure 1 ~ Figure 3 As shown, it includes the flying rotor 1, the brushless DC motor 2, the fixed pipe 3, the fuselage 4, the tilting rocker arm 5, the connecting rod 6, the tilting steering gear 7, the landing gear 8, the rotor arm 9, and the power supply unit 10. Flight control system 11, ball head 12, cockpit cover 13. The tilting rocker arm 5, the connecting rod 6, and the tilting steering gear 7 constitute a tilting servo unit, and the flying rotor 1 and the brushless DC motor 2 constitute a power unit.

[0030] The fuselage 4, landing gear 8, and rotor arm 9 are all made of carbon fiber materials. The fuselage 4 is provided with fixed pipes 3 at the left front, right front, right rear, and left rear positions for installing and fixing the rotor arm 9; The tube 3 is glued to the fuselage...

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Abstract

The invention provides a rotated quadrotor, and belongs to the technical field of aircraft design. The rotated quadrotor comprises flying rotor wings, brushless direct current motors, a fuselage, a canopy, undercarriages, a power supply unit, a flight control system, fixing tubes, a rotated rocker arm, a connecting rod, a rotated steering engine, rotor wing arms, and round heads. According to the rotated quadrotor, rotating angles of the four flying rotor wings in the front-back direction are controlled to as to realize forward flying or backward flying; installation angles of the flying rotor wings are changed so as to realize forward flying of the four flying rotor wings, maintain level condition of the fuselage, ensure that the best aerodynamic performance of the quadrotor is maintained all the time, and the maximum lifting force of the fuselage is induced, increase flying speed of the quadrotor, prolong flight duration, and improve wind resistance, operation capability, and efficiency.

Description

Technical field [0001] The invention belongs to the technical field of aircraft design, and in particular relates to a tilting quad-rotor aircraft. Background technique [0002] Quadrotor is an aircraft with four rotor shafts that can take off and land vertically. The motor on each shaft rotates to drive the rotor to generate lift and thrust. The four rotors are evenly distributed around the body, and are configured in pairs. Various flight actions are realized by changing the rotation speed between different rotors. [0003] Due to its simple structure, stable flight, easy operation, and convenient portability, multi-rotor aircraft, especially quadrotor aircraft, have been widely used in various fields at home and abroad in recent years. Compared with traditional helicopters, it has many advantages: its total rotor pitch is fixed and its structure is simple. The blades of each rotor are relatively short, and the linear speed at the end of the blades is slow, the impact force i...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C27/08B64C27/52B64C1/00B64C27/12
Inventor 王松陈万里顿文强
Owner BEIHANG UNIV
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