CN211442754U

CN211442754U - Five-engine tilt rotor unmanned aerial vehicle

Info

Publication number: CN211442754U
Application number: CN201921622993.0U
Authority: CN
Inventors: 舒婧; 舒良国; 赵耀斌; 赵�智; 丁泽木
Original assignee: Qianheng Trading Hangzhou Co ltd
Current assignee: Qianheng Trading Hangzhou Co ltd
Priority date: 2019-09-27
Filing date: 2019-09-27
Publication date: 2020-09-08
Anticipated expiration: 2029-09-27

Abstract

The utility model discloses a five engines rotor unmanned aerial vehicle that verts, the reciprocating impact tunnel drilling machine comprises a machine body, be provided with host computer wing, horizontal tail wing and perpendicular fin on the fuselage respectively, the host computer wing sets up in the fuselage middle part, horizontal tail wing and perpendicular fin set up in the fuselage tail end, the fuselage is being provided with the engine near perpendicular fin one side lower extreme, fuselage lower extreme front side is provided with the undercarriage, fuselage lower extreme rear side is provided with the rear landing gear, the fuselage is provided with a plurality ofly respectively in host computer wing both sides to the same rotor that turns that leans forward of structure, hypsokinesis, the rotor that turns forward includes steering wheel, rotor back shaft, connecting rod, pull ring, support, the rotor motor that verts. The utility model discloses when steering wheel output power, drive the rocking arm motion through the connecting rod to make the support relative pivot that verts rotate, thereby make the rotor blade can accomplish down tilting under the drive of steering wheel, overall structure is simple, and control is convenient, easily carries out and verts, and it is less, stable, reliable to occupy the volume.

Description

Five-engine tilt rotor unmanned aerial vehicle

Technical Field

The utility model relates to an unmanned air vehicle technique field specifically is a five engines rotor unmanned aerial vehicle that verts.

Background

The unmanned aerial vehicle is an unmanned aerial vehicle operated by utilizing a radio remote control device and a program control device, and in the prior art, a fixed-wing aircraft has field requirements, needs a longer runway, has long takeoff time and is greatly limited in application field. Conventional VTOL machines do not have high site requirements, but lack endurance due to the absence of wings. At present, an innovative small unmanned aerial vehicle product which is miniaturized, high in integration level, low in cost and meets the task requirements of complex take-off and landing conditions is not developed at home and abroad.

In the prior art, a fixed wing aircraft has field requirements, needs a longer runway, has long take-off time, and is greatly limited in application field, and a conventional vertical take-off and landing aircraft does not have higher field requirements, but lacks cruising ability due to the absence of wings. The existing tilt rotor aircraft, such as American V-22 osprey, Chinese rainbow-10 and the like, adopts double rotors, has poor stability, and the rotor wash-down has serious aerodynamic interference influence on the wings under the helicopter flight mode of hovering and flying before a small speed, and when the flight state of vertical flight and flying before the flying is converted, the accident is easy to occur under the unstable condition.

Therefore, develop a section miniaturization, the integrated level that accords with market demand high, low cost, be applicable to complicated take off and land condition task requirement, satisfy emergent quick response, the rotor unmanned aerial vehicle product that verts of novel quick response of market demands such as road vehicle control is very necessary.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a five engines rotor unmanned aerial vehicle that verts to solve the problem poor and the operating performance is weak to the comprehensive aerodynamic efficiency among the prior art, provided a rotor unmanned aerial vehicle aerodynamic configuration that verts, overcome prior art's mobility weak, the defect that airspeed is low.

In order to achieve the above object, the utility model provides a following technical scheme: a five-engine tilting rotor unmanned aerial vehicle comprises a fuselage, wherein a main wing, a horizontal tail wing and a vertical tail wing are respectively arranged on the fuselage, the main wing is arranged in the middle of the fuselage, the horizontal tail wing and the vertical tail wing are arranged at the tail end of the fuselage, an engine is arranged at the lower end of one side of the fuselage close to the vertical tail wing, a front undercarriage is arranged at the front side of the lower end of the fuselage, a rear undercarriage is arranged at the rear side of the lower end of the fuselage, a plurality of pairs of forward-tilting rotor wings and backward-tilting rotor wings with the same structure are respectively arranged on two sides of the main wing of the fuselage, the forward-tilting rotor wings comprise a steering engine, a rotor support shaft, a connecting rod, a pull ring, a tilting bracket, a rotor motor and rotor blades, the steering engine is fixedly arranged on one side of the fuselage, the output end of the steering engine is, rotor back shaft one end is connected with the steering wheel, the rotor back shaft other end and the support lower extreme swing joint that verts, the rotor motor is fixed to be set up in the support upper end that verts, the rotor blade sets up on the output shaft of rotor motor.

Preferably, the engine is a turbojet engine, and the turbojet engine is of the type P1000-PRO.

Preferably, the number of the forward-tilting rotor and the backward-tilting rotor is at least two pairs.

Preferably, the steering engine and the rotor wing supporting shaft are fixedly arranged on one side of the aircraft body, and the rotor wing supporting shaft is movably connected with the tilting support through a pin shaft.

Preferably, the tilting bracket is arranged inside the pull ring by screw fastening.

Compared with the prior art, the beneficial effects of the utility model are that:

1. by using the structural layout of the tilt rotor wing, the field limitation of vertical take-off and landing widening can be realized, and meanwhile, the horizontal flight in a fixed wing mode can be realized, so that the flight speed is high and the flight time is long;

2. the turbojet engine is used as a main power source for the flat flight, the speed is high, the flight time can be prolonged, and in addition, the body has small mass during the flight and is easy to balance;

3. the rotary wing support shafts which can rotate are respectively arranged at the front and the rear of the fuselage, the interference with the main wing is small, and the influence of the rotor wing downwash on the aerodynamic interference of the wings is small in the helicopter flight mode;

4. the rotor of gyroplane can vert, when steering wheel output power, drives the rocking arm motion through the connecting rod to the relative pivot of support that makes verting rotates, thereby makes rotor blade can accomplish under the drive of steering wheel and verts, and overall structure is simple, and control is convenient, easily carries out and verts, and it is less, stable, reliable to occupy the volume.

Drawings

Fig. 1 is a top view of a five-engine tiltrotor unmanned aerial vehicle according to the present invention;

fig. 2 is a side view of a five-engine tiltrotor unmanned aerial vehicle of the present invention;

fig. 3 is a schematic diagram of a forward tilting rotor structure of a five-engine tilting rotor unmanned aerial vehicle according to the present invention;

fig. 4 is the utility model relates to a five engines rotor unmanned aerial vehicle's that verts plane state schematic diagram that flies.

In the figure: 1. a body; 2. a main wing; 3. a horizontal rear wing; 4. a vertical tail; 5. an engine; 6. a nose landing gear; 7. a rear landing gear; 8. a forward tilting rotor; 81. a steering engine; 82. a rotor support shaft; 83. a connecting rod; 84. a pull ring; 85. a tilt bracket; 86. a rotor motor; 87. a rotor blade; 9. the rotor is tilted backwards.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

Referring to fig. 1-4, the present invention provides a technical solution: a five-engine 5 tilting rotor unmanned aerial vehicle comprises a fuselage 1, wherein a main wing 2, a horizontal tail wing 3 and a vertical tail wing 4 are respectively arranged on the fuselage 1, the main wing 2 is arranged in the middle of the fuselage 1, the horizontal tail wing 3 and the vertical tail wing 4 are arranged at the tail end of the fuselage 1, the lower end of one side of the fuselage 1 close to the vertical tail wing 4 is provided with an engine 5, the front side of the lower end of the fuselage 1 is provided with a front undercarriage 6, the rear undercarriage 7 is arranged at the rear side of the lower end of the fuselage 1, the fuselage 1 is respectively provided with a plurality of pairs of forward tilting rotors 8 and backward tilting rotors 9 with the same structure at the two sides of the main wing 2, the forward tilting rotors 8 comprise a steering engine 81, a rotor support shaft 82, a connecting rod 83, a pull ring 84, a tilting bracket 85, a rotor motor 86 and rotor blades 87, the steering engine 81 is fixedly arranged at one, support 85 that verts fixed mounting is in pull ring 84 upper end, and rotor support shaft 82 one end is connected with steering wheel 81, and rotor support shaft 82 other end and support 85 lower extreme swing joint verts, and rotor motor 86 fixed mounting is in support 85 upper end that verts, and rotor blade 87 is installed on rotor motor 86's output shaft.

The engine 5 is a turbojet engine, and the model of the engine 5 is P1000-PRO; the number of the front tilt rotor 8 and the rear tilt rotor 9 is at least two pairs; the steering engine 81 and the rotor wing support shaft 82 are both fixedly arranged on one side of the fuselage 1, and the rotor wing support shaft 82 is movably connected with the tilting bracket 85 through a pin shaft; the tilt bracket 85 is mounted inside the pull ring 84 by screw fastening.

The working principle is as follows: the utility model discloses a through install rotatable axle that verts respectively in fuselage 1 front and back position, driving system is including setting up rotor and the power device around main wing 2, set up in the whirlpool power device of 3 departments of horizontal fin, take off perpendicularly and arrive after the take-off a take the altitude, fuselage 1 adjusts the gesture to the level gradually, in order to accelerate the process of level acceleration, rotor blade 87 can further vert certain angle, this process is mainly accomplished through the mechanism of verting, the whirlpool of fin department is spouted and is opened simultaneously, increase horizontal direction's component, carry out horizontal direction with higher speed, simultaneously along with horizontal direction's speed increase, the lift of the main wing 2 of aircraft can increase gradually, aircraft wing unmanned aerial vehicle verts for traditional overall arrangement, can show aerodynamic efficiency and flight performance that promote this model under the fixed wing mode, very have using value.

It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.

Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.

Claims

1. The utility model provides a five engine (5) rotor unmanned aerial vehicle that verts, includes fuselage (1), its characterized in that: be provided with main wing (2), tailplane (3) and perpendicular fin (4) on fuselage (1) respectively, main wing (2) set up in fuselage (1) middle part, tailplane (3) set up in fuselage (1) tail end with perpendicular fin (4), fuselage (1) is being provided with engine (5) being close to perpendicular fin (4) one side lower extreme, fuselage (1) lower extreme front side is provided with nose landing gear (6), fuselage (1) lower extreme rear side is provided with rear landing gear (7), fuselage (1) is provided with a plurality of rotor (8), hypsokinesis rotor (9) that change that incline forward that the structure is the same respectively in main wing (2) both sides, it changes rotor (8) including steering wheel (81), rotor back shaft (82), connecting rod (83), pull ring (84), support of verting (85), rotor motor (86) to incline forward, Rotor blade (87), steering wheel (81) are fixed to be set up in fuselage (1) one side, the output of steering wheel (81) passes through rocking arm and connecting rod (83) one end fixed connection, the connecting rod (83) other end and pull ring (84) one side swing joint, support (85) of verting fixedly set up in pull ring (84) upper end, rotor back shaft (82) one end is connected with steering wheel (81), rotor back shaft (82) other end and support (85) lower extreme swing joint verts, rotor motor (86) are fixed to be set up in support (85) upper end of verting, rotor blade (87) set up on the output shaft of rotor motor (86).

2. A five-engine (5) tiltrotor unmanned aerial vehicle according to claim 1, wherein: the engine (5) is a turbojet engine, and the model of the engine (5) is P1000-PRO.

3. A five-engine (5) tiltrotor unmanned aerial vehicle according to claim 1, wherein: the number of the forward-tilting rotor (8) and the backward-tilting rotor (9) is at least two pairs.

4. A five-engine (5) tiltrotor unmanned aerial vehicle according to claim 1, wherein: steering wheel (81) and rotor back shaft (82) all fix and set up in fuselage (1) one side, rotor back shaft (82) and support (85) vert through round pin axle swing joint.

5. A five-engine (5) tiltrotor unmanned aerial vehicle according to claim 1, wherein: the tilting bracket (85) is arranged on the inner side of the pull ring (84) through screw fastening.