CN213832107U

CN213832107U - Combined forward-pulling longitudinal wing-changing counter-speed rotor aircraft

Info

Publication number: CN213832107U
Application number: CN201920826650.XU
Authority: CN
Inventors: 范磊
Original assignee: Individual
Current assignee: Individual
Priority date: 2019-06-03
Filing date: 2019-06-03
Publication date: 2021-07-30
Anticipated expiration: 2029-06-03

Abstract

The invention relates to a vertical take-off and landing (VTOL) high-efficiency and high-speed aircraft. A combined forward-pulling longitudinal variable wing counter-speed rotor aircraft is characterized in that a main lift rotor set 5 is arranged on the upper portion of an engine body 1 in a longitudinal mode, two pairs of convertible blades 9 are arranged on the main lift rotor set 5, a fixed wing 2 is arranged in the middle of the engine body 1, a forward-flying power system 4 is arranged on the head portion of the engine body 1, an aileron 8 is arranged on the fixed wing 2, and a horizontal tail wing 3, a vertical tail wing 6 and an undercarriage 7 are arranged on the engine body 1. The rotor wing-wing conversion enables the composite forward-pulling longitudinal variable wing counter-speed rotor aircraft to really become a high-speed helicopter capable of vertically taking off, landing and hovering, and has great significance in national economy and national defense construction.

Description

Combined forward-pulling longitudinal wing-changing counter-speed rotor aircraft

Technical Field

The invention relates to a vertical take-off and landing (VTOL) high-efficiency and high-speed aircraft.

Background

The existing fixed wing aircraft can fly forwards at a high speed, but takes off by depending on a runway. Has the loss of speed and can not vertically take off, land and hover. The helicopter has vertical take-off and landing capability, can hover in the air, does not depend on an airport, but cannot fly forwards at high speed and high efficiency. The research and development of a composite aircraft which has vertical take-off and landing capability, can hover in the air and can fly forwards at high speed and high efficiency is always the direction of the effort of the aviation industry.

The development types can be generally classified as: composite, tilting and stalling. The composite rotors can be classified into two types, one type is a conventional rotor, and the other type is an ABC rotor; the tilting type can be classified into two types, one type is wing tilting type, and the other type is rotor wing tilting type; the stall category can also be divided into two categories, one category is rotor fixing category and the other category is rotor collecting category.

Typical machine types include: x2, S-97, SB-1 from Western Spanish, Inc., of hybrid, X3 from European helicopter, Inc. Examples of the tilting type include V-22 and V-280 by Bell and X-18 by Hiller. The stop-rotation type comprises the following steps: m85 by NASA, a disk-plane by modafinil, CR/W by Boeing. The multi-rotor composite type blackdog developed in Israel is provided.

In view of the existing research and mass-produced models, the technical implementation path is compromised. At the same time of pursuing high speed, the flight efficiency is sacrificed.

The CR/W of Boeing company introduces the concept of composite variable wing (blade variable wing), but in the forward flying flight of CR/W from low speed to high speed, the realization is more complex because the single rotor wing group changes the wing and is driven by high-pressure jet. Because the single rotor wing group is adopted, the variable wing is adopted, and the operation authority is insufficient, the design concept can not be realized.

Disclosure of Invention

The combined forward-pulling longitudinal variable wing counter-speed rotor aircraft is characterized in that a main lift rotor set 5 is arranged on the upper portion of an engine body 1 in a longitudinal mode, two pairs of convertible blades 9 are arranged on the main lift rotor set 5, fixed wings 2 are arranged in the middle of the engine body 1, a forward-flying power system 4 is arranged on the engine body 1, ailerons 8 are arranged on the fixed wings 2, and a horizontal tail wing 3, a vertical tail wing 6 and an undercarriage 7 are arranged on the engine body 1.

The helicopter is characterized in that the main lift rotor wing groups 5 are longitudinally arranged on the body 1 and bear the main lift of the aircraft in vertical take-off and landing, hovering and longitudinal helicopter mode cruising, and the aircraft is controlled in a longitudinal dual-rotor helicopter mode during vertical take-off and landing, hovering and longitudinal helicopter mode cruising.

The helicopter is characterized in that two pairs of main lift rotor wing groups 5 arranged in a longitudinal row at the upper part of the body 1 are driven to rotate by power during vertical take-off and landing, hovering and helicopter mode flight in the longitudinal row.

The variable-pitch propeller is characterized in that a counter-speed rotor technology is introduced into each pair of main lift rotor sets 5, two variable blades 9 with small aspect ratio are installed, the variable blades 9 are symmetrically designed at the front edge and the rear edge, and the variable total pitch and the variable periodic pitch of the variable blades 9 are achieved.

The flying control system is characterized in that when the aircraft vertically takes off and lands, hovers and navigates at low speed in a tandem dual-rotor helicopter mode, the aircraft flies and controls in a tandem dual-rotor helicopter flight mode.

The aircraft is characterized in that the middle part of the aircraft body 1 can be provided with a fixed wing 2 which bears the main lift force of the forward flight transition.

The aircraft is characterized in that a front-flying power system 4 is arranged at the head of the aircraft body 1 and bears the front-flying power of the aircraft.

The aircraft is driven to fly forwards along with a forward-flying power system 4, a main lift rotor wing group 5 is driven to rotate by self-driving force and incoming flow driving force, the aircraft is in a composite flight stage of a tandem double-rotor helicopter and a self-rotating rotor wing aircraft, and flight control is cooperatively controlled by two flight control modes of the tandem double-rotor helicopter and the tandem self-rotating double-rotor wing aircraft; the incoming flow driving force gradually takes over the self-driving force of the main lift rotor set 5, the self-driving is disconnected, the main lift rotor set 5 is in an incoming flow driving state and is changed into a longitudinal autorotation dual-rotor flight mode, the main lift rotor set 5 and the fixed wings 2 keep the flight lift of the aircraft, and the aircraft enters a fixed wing aircraft and longitudinal autorotation dual-rotor flight composite flight control mode.

The main lift rotor set 5 is characterized in that a rotating shaft can be stopped and positioned and locked through a damper, a convertible blade 9 can be locked at a position 90 degrees vertical to the machine body 1, the total torque variable distance of the convertible blade 9 is zero, and the convertible blade 9 is changed into a rotor wing; the two pairs of longitudinal main lift rotor groups 5 are converted into two pairs of fixed wings, so that the rotor-wing conversion is realized.

The aircraft is characterized in that the main lift rotor wing group 5 is changed into a fixed wing, and the aircraft is completely changed into a fixed wing aircraft to fly in a fixed wing aircraft mode.

The aircraft is characterized in that the aircraft has the autorotation characteristic under the action of incoming flow, and can autorotate, glide and land under the action of incoming flow after losing power; the rollable landing gear 7 is driven by the forward flight power system 4 to be rollable when the rollable landing gear has a rollable landing condition.

The combined forward-pulling longitudinal variable wing counter-speed rotor aircraft is characterized in that a distributed power design is adopted, and a main lift rotor set 5 and a front flying power system 4 are driven independently; the device can be driven by full electric power or hybrid power; the full-power drive is powered by the energy storage system, or the power generation system and the energy storage system are powered in a mixed mode; the hybrid power drive is that the main lift rotor wing set 5 is driven by electric power, the front-flying power system 4 is driven by the power of traditional fuel and drives the power generation system to supplement the electric energy to the energy storage system, so as to supplement the electric energy consumption of the main lift rotor wing set 5 during vertical take-off and landing, hovering and multi-rotor-wing cruise; the energy storage system can also adopt a driving system of the main lift rotor set 5 to be designed into a driving and power generation integrated system, and when the aircraft flies in a rotation rotor mode, power is generated to supplement electric energy to the energy storage system.

The beneficial effects are that.

1. Introduction of counter-speed rotor rvr (reverse vector rotor): the RVR (reverse vector rotor) rotor wing adopts a symmetrical wing section design, introduces the autorotation of the rotor wing, adopts a mechanism of reducing the rotating speed of the rotor wing and adds forward thrust to reduce the load of a paddle disk and expand a performance envelope, and can overcome the problems of the traditional helicopter 1. the influence of reducing the air compressibility by reducing the rotating speed of the rotor wing 2. the delay of the backstroke blade stall is controlled by the symmetrical wing section and high-order harmonic wave; 3. sharp/accident interference noise is avoided; 4. the tip vortex and the interference generated by the tip vortex and the fuselage are avoided. "(quoted from the development overview of the conversion type high-speed helicopter-royal peel and high plus).

2. Introduction of tandem dual rotors: the tandem double-rotor layout solves the problem of reaction torque, and compared with the jet driving of M85 of CR/W, NASA of Boeing company, the ring volume control technology simplifies the driving and control modes; due to the longitudinal arrangement, the disturbance is symmetrical when the rotor is stopped and the wings are changed, and the problem of insufficient control authority of the existing stalling design is solved.

3. The introduction of the double-rotation rotor technology and the distributed power and the hybrid power: 1. the problem of using traditional power mode to require to many drives is solved, can conveniently realize rotor variable speed, stall, simple structure. 2. The vertical take-off and landing and hovering of the aircraft are realized. 3. The forward and backward traveling stall of the high-speed forward flight is delayed, and the flight efficiency is greatly improved. 4. Because the proportion of the landing, hovering and helicopter mode cruising time in the line-by-line tasks of the aircraft is lower, and the waste weight of the power storage system is lower than that of a full-electric drive aircraft, a new approach is created for the full-electrochemical and hybrid power application of an aircraft power system. 5. Because the aircraft has the characteristics of incoming flow driving, the aircraft can rotate, slide down and land after losing power, can slide and take off under the condition of sliding and taking off, and greatly improves the load efficiency.

The rotor wing-wing conversion enables the composite forward-pulling longitudinal variable wing counter-speed rotor aircraft to really become a high-speed helicopter capable of vertically taking off, landing and hovering, and has great significance in national economy and national defense construction.

Drawings

FIG. 1 is a vertical take-off and landing, hovering side view.

Fig. 2 is a front flying side view of the straightening vane.

In FIGS. 1-2: 1-body; 2-fixed wings; 3-horizontal tail wing; 4-front flying power system; 5-a main lift rotor set; 6-vertical tail; 7-a landing gear; 8, an aileron; 9-convertible blade

Detailed Description

As shown in fig. 1-2, two main lift rotor sets 5 are arranged in front-back longitudinal rows on the upper part of a body 1 of the compound forward-pulling longitudinal row variable wing counter-speed rotorcraft. The main lift rotor wing group 5 has the functions of changing total distance and periodic distance, the rotating directions of the front rotor wing and the rear rotor wing are opposite, and the front rotor wing and the rear rotor wing can overcome reaction torque; the main lift rotor wing group 5 has the functions of damping stall of a main driving shaft, positioning locking and power disconnection; the convertible blades 9 are converted into fixed airfoils.

Two pairs of convertible blades 9 with small aspect ratio are arranged on the main lift Rotor set 5, a counter-speed Rotor (RVR-Reverse vector Rotor) technology is introduced, and the wing profiles are symmetrical at the front edge and the rear edge.

The composite forward-pulling longitudinal counter-speed variable wing aircraft is characterized in that a fixed wing 2 is arranged in the middle of an aircraft body 1, an aileron 8 is arranged on the fixed wing 2, a forward-flying power system 4 is arranged on the aircraft body 1, and the forward-flying power system 4 is installed at the nose.

The main lift rotor set 5 is driven by independent power to provide lift force and control force when taking off and landing vertically, hovering and flying at low speed, and the aircraft flies and is controlled in a tandem double-rotor helicopter mode.

When flying forward, the front-flying power system 4 provides forward power, the flying speed is gradually increased, the lift force of the fixed wing 2 is gradually increased, the driving power of the main lift rotor wing set 5 is gradually replaced by the flow driving power, and the aircraft is changed from a tandem double-rotor helicopter mode to a fixed wing aircraft and a double-autorotation rotor aircraft composite flying and control mode. At the moment, the aircraft flies forward and is controlled in a combined mode of a fixed wing aircraft and a self-rotating rotor aircraft.

In order to further increase the flying speed, the total distance can be changed to zero through the function of changing the distance, the main driving shaft stops rotating in a damping mode, the positioning locking mode and the main driving shaft stops rotating and is locked, and the convertible paddle 9 is locked at the position 90 degrees vertical to the machine body 1. At the moment, the main lift rotor wing group 5 is changed into two fixed wings which are connected with the middle fixed wing in series, the aircraft completely flies at high speed in a fixed wing aircraft mode, and the aircraft is controlled through the ailerons 8, the vertical tail wing 6 and the parallel tail wing 3.

Because aircraft main lift rotor group 5 has the self-rotation characteristic under the incoming current, when losing power, usable its rotation gliding characteristic, the rotation gliding is safe to be descended.

When the sliding-off and landing condition is met, the front-flying power system 4 provides forward power, the main lift rotor group 5 can be in a self-rotating rotor mode or can be changed into a fixed wing, and the aircraft can slide off and land at the moment.

The composite forward-pulling longitudinal variable wing counter-speed rotor aircraft adopts a distributed power design, and a main lift rotor set 5 and a front flying power system 4 are driven independently; the device can be driven by full electric power or hybrid power; the full-power drive is powered by the energy storage system, or the power generation system and the energy storage system are powered in a mixed mode; the hybrid power drive is that the main lift rotor wing set 5 is driven by electric power, the front-flying power system 4 is driven by the power of traditional fuel and drives the power generation system to supplement the electric energy to the energy storage system, so as to supplement the electric energy consumption of the main lift rotor wing set 5 during vertical take-off and landing, hovering and multi-rotor-wing cruise; the energy storage system can also adopt a driving system of the main lift rotor set 5 to be designed into a driving and power generation integrated system, and when the aircraft flies in a rotation rotor mode, power is generated to supplement electric energy to the energy storage system.

Claims

1. The utility model provides a combined type is drawn forward and is indulged contrary fast rotor craft of wing that becomes, main lift rotor group (5) are arranged to the column in upper portion of organism (1), two convertible paddle (9) have been arranged on main lift rotor group (5), fixed wing (2) have been arranged at organism (1) middle part, fly driving system (4) before the aircraft nose has been arranged, aileron (8) have been arranged on fixed wing (2), horizontal tail wing (3) have been arranged on organism (1), vertical tail wing (6), undercarriage (7).

2. The aircraft according to claim 1, characterized in that the main lift rotor group (5) is arranged in longitudinal rows on the body (1) and is responsible for the main lift of the aircraft in the vertical takeoff and landing, hovering and helicopter mode cruise.

3. The aircraft according to claim 1, characterized in that the two pairs of main lift rotor sets (5) arranged in tandem on the upper part of the body (1) are driven to rotate by power during vertical take-off, landing, hovering and tandem helicopter modes of flight.

4. The aircraft according to claim 1, characterized in that each pair of main lift rotor sets (5) introduces counter-speed rotor technology, two convertible blades (9) with small aspect ratio are installed, the convertible blades (9) are designed symmetrically at the front and rear edges, and the convertible blades (9) have variable total pitch and periodic pitch.

5. The aircraft according to claim 1, characterized in that the main lift rotor set (5) can be de-actuated, after de-actuation, the rotating shaft can be stopped and locked by the damper, the convertible blade (9) can be locked at 90 degrees vertical to the body (1), the total torque variation of the convertible blade (9) is zero, and the convertible blade (9) becomes a wing; the two pairs of longitudinal main lift rotor wing groups (5) are converted into two pairs of fixed wings, so that the rotor wing-wing conversion is realized.

6. The aircraft of claim 1, wherein the aircraft is configured to fly and control in a tandem twin rotor helicopter flight mode during a vertical takeoff and landing, hovering, and low speed cruise flight in the tandem twin rotor helicopter mode.

7. An aircraft according to claim 1, characterized in that the fixed wing (2) can be arranged in the middle of the body (1) and can bear the main lift force of the forward flight transition.

8. The aircraft according to claim 1, characterized in that the nose of the body (1) is provided with a front flight power system (4) for taking over the front flight power of the aircraft.

9. The aircraft of claim 1, wherein the aircraft is driven to fly forward along with a forward-flight power system (4), the main lift rotor group (5) is driven to rotate by self-driving force and inflow driving force, the aircraft is in a composite flight stage of a tandem dual-rotor helicopter and a self-rotating rotor aircraft, and flight control is cooperatively controlled by two flight control modes of the tandem dual-rotor helicopter and the tandem self-rotating dual-rotor aircraft; the incoming flow driving force gradually takes over the self-driving force of the main lift rotor set (5), the self-driving is disconnected, the main lift rotor set (5) is in an incoming flow driving and rotating state and is converted into a tandem rotation double-rotor flight mode, the main lift rotor set (5) and the fixed wing (2) keep the flight lift of the aircraft, and the aircraft enters a fixed wing aircraft and tandem rotation double-rotor flight composite flight control mode.

10. The aircraft according to claim 1, characterized in that the main lift rotor group (5) is transformed into a fixed wing, the aircraft being completely transformed into a fixed wing aircraft, flying in fixed wing aircraft mode.

11. The aircraft of claim 1, wherein the aircraft can spin, glide and land under the action of the incoming flow after losing power due to the autorotation characteristic of the aircraft under the action of the incoming flow; when the sliding landing gear (7) is in the sliding landing condition, the sliding landing gear can be driven by the front flying power system (4) to slide and land.

12. The aircraft of claim 1, wherein the composite forward-pulling longitudinal variable wing counter-speed rotor aircraft adopts a distributed power design, and the main lift rotor group (5) and the forward-flying power system (4) are driven independently; the device can be driven by full electric power or hybrid power; the full-power drive is powered by the energy storage system, or the power generation system and the energy storage system are powered in a mixed mode; the hybrid power drive is that the main lift rotor wing set (5) is driven by electric power, the forward flight power system (4) is driven by the power of traditional fuel and drives the power generation system to supplement the electric energy to the energy storage system, so as to supplement the electric energy consumption of the main lift rotor wing set (5) during vertical take-off and landing, hovering and multi-rotor wing mode cruise; the energy storage system can also adopt a driving system of the main lift rotor set (5) to be designed into a driving and power generation integrated system, and when the aircraft flies in a self-rotation rotor mode, power is generated to supplement the energy storage system with electric energy.