CN110861770A

CN110861770A - Unmanned rotation gyroplane

Info

Publication number: CN110861770A
Application number: CN201911109109.8A
Authority: CN
Inventors: 吴伟伟; 马存旺; 李明新; 付义伟
Original assignee: Rainbow UAV Technology Co Ltd
Current assignee: Rainbow UAV Technology Co Ltd
Priority date: 2019-11-13
Filing date: 2019-11-13
Publication date: 2020-03-06

Abstract

The invention discloses an unmanned autorotation gyroplane, which comprises a rotor system, a prerotation mechanism, an operating mechanism, a fuselage, a measurement and control system, a navigation flight control system, an electrical system, a short wing, a power system, a tail wing and an undercarriage, wherein the navigation flight control system, the electrical system and the measurement and control system are arranged in the fuselage; the power system is arranged on a power cabin of the aircraft body, the rotor wing system is arranged on the upper part of the aircraft body, the pre-rotation mechanism is connected with the rotor wing system and used for pre-rotating the rotor wing system to a preset rotating speed by means of power provided by the power system during takeoff, the control mechanism is connected with the rotor wing system and used for controlling the rotor wing system to drive the rotor wing system to rotate by means of incoming flow so as to provide lift force and control the flying posture of the rotorcraft during flying, and the short wings are arranged on the left side and the right side of the aircraft body and used for load hanging and providing part of lift force at; the empennage is installed at the rear side of the fuselage. The unmanned autorotation gyroplane has the capabilities of autonomous take-off and landing and air route flight, and has the advantages of short take-off and landing distance, strong environmental adaptability and the like.

Description

Unmanned rotation gyroplane

Technical Field

The invention relates to the technical field of aircraft design, in particular to an unmanned autorotation rotorcraft.

Background

The autorotation rotorcraft is a rotorcraft which utilizes incoming flow to drive the rotation of a rotor wing to generate lift force and pushes (pulls) a propeller to overcome the forward flight resistance. The autogyro is different from the helicopter in that the rotor of the autogyro is driven to rotate by the incoming flow while the rotor of the helicopter is driven by the engine; the front flight of the autorotation rotorcraft is to overcome the front flight resistance by using the pushing (pulling) force of a propeller, while the front flight resistance of the helicopter is generally overcome by using the pulling force component of a rotor wing; autogyro aircraft typically use tiltrotor disks to change flight conditions, while helicopters typically use cyclic pitch to change flight conditions.

Autogyro occurs earlier than helicopters, but because of the inability to hover, the subsequent development is slowed. However, the autorotation gyroplane has the advantages of simple structure, high safety, good economical efficiency, wide speed range, capability of taking off and landing at short distance and the like, and with the development of modern aviation technology, the autorotation gyroplane meets new development opportunities, and various types of mature manned autorotation gyroplanes appear at home and abroad in succession. However, some autogiros have limitations in use, such as inability to fly in low visibility or night conditions, fatigue of the pilot, etc.

Disclosure of Invention

The technical problem solved by the invention is as follows: the provided unmanned autorotation gyroplane capable of running and taking off and landing has the advantages of short taking-off and landing distance, strong environmental adaptability and the like.

The unmanned autorotation gyroplane comprises a rotor system, a prerotation mechanism, an operating mechanism, a fuselage, a measurement and control system, a navigation flight control system, an electrical system, a short wing, a power system, an empennage and an undercarriage, wherein the navigation flight control system, the electrical system and the measurement and control system are arranged in the fuselage; the power system is arranged on a power cabin of the aircraft body, the rotor system is arranged on the upper part of the aircraft body and is a main lifting surface and a control surface, the pre-rotation mechanism is connected with the rotor system and is used for pre-rotating the rotor system to a preset rotating speed by means of power provided by the power system during takeoff, the control mechanism is connected with the rotor system and is used for controlling the rotor system to drive the rotor system to rotate by means of incoming flow so as to provide lifting force and control the flight attitude of the rotorcraft during flight, and the short wings are arranged on the left side and the right side of the aircraft body and are used for load hanging and providing partial lifting force simultaneously so as to unload the rotors; the empennage is installed on the rear side of the fuselage and used for controlling the course.

Preferably, the control mechanism comprises a rotor wing support, two pull rods and two linear steering engines, the rotor wing system is arranged on the upper portion of the fuselage by means of the rotor wing support, and the two linear steering engines are arranged on the fuselage and are respectively connected with the two ends of the rotor wing support by means of the two pull rods, so that the front and back inclination and the left and right inclination angles of the rotor wing system are controlled.

Preferably, the pre-rotation mechanism adopts a linear steering engine to control whether to switch on the pre-rotation mechanism or not, and comprises a large gear, a small gear, an upper transmission rod, a gear box, a lower transmission rod, a belt pulley, a belt, a pre-rotation pressure rod and a linear steering engine, wherein the linear steering engine and the belt pulley are arranged at the rear part of the machine body, the belt pulley is connected with a power system through the belt, the linear steering engine can enable the belt pulley to move up and down through the pre-rotation pressure rod, so that the power transmission of the power system can be switched on or off, the belt pulley is coaxially and fixedly connected with the lower transmission rod, the lower transmission rod is in steering connection with the upper transmission rod through the gear box, the large gear is meshed with the small gear, the large gear and the small gear are both arranged on the rotor wing support, the, therefore, when the airplane starts to take off, the linear steering engine controls the pre-rotation pressure rod to enable the belt pulley to descend, loosen the belt, disconnect power transmission, slowly switch on when the pre-rotation is switched on, and quickly switch off when the pre-rotation is switched off.

Preferably, the aircraft body adopts a streamline aerodynamic shape, and meanwhile, the aircraft body and a rotor system connecting structure adopts a fairing so as to reduce flight resistance.

Preferably, the undercarriage adopts a front three-point undercarriage, the main undercarriage support arm adopts a fairing for rectification, and the front undercarriage adopts a steering engine to control the steering of the front wheel.

Preferably, the short wing is detachable, and whether the short wing is installed or not can be selected according to task requirements.

Preferably, the rotor system adopts a seesaw type rotor, and the pitching and rolling of the rotor system are controlled by the control mechanism, so that the flight attitude of the unmanned aerial vehicle is controlled.

Preferably, the navigation flight control system is provided with a module for realizing autonomous take-off and landing, attitude, height and speed control, can fly by an autonomous air route, and can receive manual remote control instructions.

Preferably, the empennage comprises a horizontal tail, a large vertical tail, a rudder and two small vertical tails, wherein the small vertical tails are positioned at two ends of the horizontal tail, and the steering engine is adopted to control the deflection angle of the rudder so as to control the course of the unmanned aerial vehicle.

Compared with the prior art, the invention has the beneficial effects that:

(1) the invention provides an unmanned autorotation gyroplane which has the capabilities of autonomous take-off and landing and air route flight, and has the advantages of short take-off and landing distance, strong environmental adaptability and the like.

(2) The invention adopts a streamline fuselage and combines a rectification measure, thereby reducing the flight resistance of the whole aircraft.

(3) The control mechanism, the pre-rotation mechanism, the undercarriage nose wheel steering and the like all adopt full electric control, so that the system complexity is reduced.

(4) The invention adopts the linear steering engine to directly operate the rotor wing, thereby reducing the complexity of the operating mechanism and lightening the structural mass.

Drawings

FIG. 1 is an isometric view of the present invention;

fig. 2 is a partial isometric view of the present invention.

Detailed Description

As shown in fig. 1, the present invention provides an unmanned autorotation rotorcraft, which comprises a rotor system 1, a prerotation mechanism 2, an operating mechanism 3, a fuselage 4, a measurement and control system 5, a navigation flight control system 6, an electrical system 7, a short wing 8, a power system 9, an empennage 10 and an undercarriage 11, and can realize autonomous short take-off and landing and air line flight.

The navigation flight control system 6, the electric system 7 and the measurement and control system 5 are arranged in the machine body 4; the power system 9 is arranged in a power cabin of the machine body 4 and provides forward flying power and comprises an engine, a propeller and a fuel device; the rotor system 1 is arranged on the upper part of the fuselage 4, comprises blades, a hub and the like, is a main lifting surface and a control surface, and is pre-rotated to a preset rotating speed by a power system engine through a pre-rotation mechanism 2 during takeoff, then is disconnected, and the unmanned aerial vehicle runs in an accelerated manner to take off, wherein the takeoff distance is within 60 meters; when flying, the rotor wing tilts backwards, the rotor wing system 1 is driven to rotate by means of incoming flow to provide lift force, and the front-back tilt angle and the left-right tilt angle of the rotor wing system 1 are controlled by the control mechanism 3, so that the flying posture of the gyroplane is controlled; the short wings 8 are arranged on the left side and the right side of the fuselage 4, can be used for load hanging, and provide partial lift force for unloading the rotor wing; the tail 10 is used to control heading.

The navigation flight control system 6 has the functions of autonomous take-off and landing, attitude, height and speed control, autonomous air route flight, capability of receiving manual remote control instructions and the like;

the aircraft body 4 adopts a streamline aerodynamic shape, and meanwhile, a connecting structure of the aircraft body 4 and the rotor system 1 adopts a fairing for rectification, so that the flight resistance is reduced;

the undercarriage 11 adopts the three point type undercarriage in front, and main undercarriage support arm adopts the radome fairing rectification, and the nose landing gear adopts steering wheel control front wheel to turn to.

The short wing 8 can be detached, and whether the short wing is installed or not can be selected according to task requirements.

Rotor system 1 adopts seesaw formula rotor to by the every single move and the roll of operating mechanism 3 control rotor system 1, and then control unmanned aerial vehicle's flight gesture.

The control mechanism 3 adopts a linear steering engine to directly control and comprises a rotor wing support 14, a pull rod 16 and a linear steering engine 19;

the empennage 10 comprises a horizontal tail, a large vertical tail, a rudder and two small vertical tails, wherein the small vertical tails are positioned at two ends of the horizontal tail, and the steering engine is adopted to control the deflection angle of the rudder so as to control the course of the unmanned aerial vehicle.

As shown in fig. 2, the pre-rotation mechanism 2 adopts a linear steering engine to control whether to turn on or not to pre-rotate, and comprises a large gear 12, a small gear 13, an upper transmission rod 15, a gear box 17, a lower transmission rod 18, a belt pulley 20, a belt 21, a pre-rotation pressure lever 22 and a linear steering engine 23, wherein the pre-rotation mechanism is slowly turned on when being turned on for about 10 seconds, and is quickly turned off when being turned off for within 0.5 seconds.

The invention is described as an example of a specific application in this field, but any person skilled in the art should understand that the invention includes but is not limited to this example, and any modification made on the basis of this example is within the scope of protection of intellectual and technical property rights of the invention.

Claims

1. An unmanned rotation gyroplane which is characterized in that: the aircraft comprises a rotor wing system, a pre-rotation mechanism, an operating mechanism, an aircraft body, a measurement and control system, a navigation flight control system, an electrical system, a short wing, a power system, an empennage and an undercarriage, wherein the navigation flight control system, the electrical system and the measurement and control system are arranged in the aircraft body; the power system is arranged on a power cabin of the aircraft body, the rotor system is arranged on the upper part of the aircraft body and is a main lifting surface and a control surface, the pre-rotation mechanism is connected with the rotor system and is used for pre-rotating the rotor system to a preset rotating speed by means of power provided by the power system during takeoff, the control mechanism is connected with the rotor system and is used for controlling the rotor system to drive the rotor system to rotate by means of incoming flow so as to provide lifting force and control the flight attitude of the rotorcraft during flight, and the short wings are arranged on the left side and the right side of the aircraft body and are used for load hanging and providing partial lifting force simultaneously so as to unload the rotors; the empennage is installed on the rear side of the fuselage and used for controlling the course.

2. An unmanned rotary wing aircraft according to claim 1, wherein: the control mechanism comprises a rotor wing support, two pull rods and two linear steering engines, the rotor wing system is arranged on the upper portion of the machine body through the rotor wing support, the two linear steering engines are arranged on the machine body and are connected with the two ends of the rotor wing support through the two pull rods respectively, and therefore the front and back inclination and the left and right inclination angles of the rotor wing system are controlled.

3. The unmanned rotorcraft of claim 2, wherein: the pre-rotation mechanism adopts a linear steering engine to control whether to switch on pre-rotation or not, and comprises a large gear, a small gear, an upper transmission rod, a gear box, a lower transmission rod, a belt pulley, a belt, a pre-rotation pressure rod and a linear steering engine, wherein the linear steering engine and the belt pulley are arranged at the rear part of a machine body, the belt pulley is connected with a power system through the belt, the linear steering engine can enable the belt pulley to move up and down through the pre-rotation pressure rod, so that the power transmission of the power system can be switched on or off, the belt pulley is coaxially and fixedly connected with the lower transmission rod, the lower transmission rod is in steering connection with the upper transmission rod through the gear box, the large gear is meshed with the small gear, the large gear and the small gear are both arranged on a rotor wing support, the large gear is, therefore, when the airplane starts to take off, the linear steering engine controls the pre-rotation pressure rod to enable the belt pulley to descend, loosen the belt, disconnect power transmission, slowly switch on when the pre-rotation is switched on, and quickly switch off when the pre-rotation is switched off.

4. The unmanned rotorcraft of claim 1, wherein: the fuselage adopts streamlined aerodynamic configuration, and fuselage and rotor system connection structure adopt the radome fairing simultaneously, reduce flight resistance.

5. The unmanned rotorcraft of claim 1, wherein: the undercarriage adopts the three point type undercarriage in front, and main undercarriage support arm adopts the radome fairing rectification, and the nose landing gear adopts steering wheel control front wheel to turn to.

6. The unmanned rotorcraft of claim 1, wherein: the short wings can be detached, and whether installation is required or not can be selected according to task requirements.

7. The unmanned rotorcraft of claim 1, wherein: the rotor system adopts seesaw formula rotor, by the every single move and the roll of operating mechanism control rotor system, and then control unmanned aerial vehicle's flight gesture.

8. The unmanned rotorcraft of claim 1, wherein: the navigation flight control system is provided with a module for realizing autonomous take-off and landing, attitude, height and speed control, can fly by an autonomous air route, and can receive manual remote control instructions.

9. The unmanned rotorcraft of claim 1, wherein: the fin includes the horizontal tail, big vertical fin, the rudder, two little vertical fins, and little vertical fin is located the horizontal tail both ends, adopts the deflection angle of steering wheel control rudder, and then control unmanned aerial vehicle's course.