CN111959759A

CN111959759A - Combined type tilting power longitudinal rotation dual-rotor aircraft

Info

Publication number: CN111959759A
Application number: CN201910416125.5A
Authority: CN
Inventors: 范磊
Original assignee: Individual
Current assignee: Individual
Priority date: 2019-05-19
Filing date: 2019-05-19
Publication date: 2020-11-20

Abstract

The invention relates to a method for a combined type vertical take-off and landing (VTOL) high-efficiency and high-speed aircraft. Through tilting power aircraft, tandem double rotor helicopter, fixed wing aircraft, tandem rotation double rotor aircraft composite flight, power distribution, synthesize and promote aircraft flight quality, realize that the aircraft VTOL, hover, fly ahead at a high speed.

Description

Combined type tilting power longitudinal rotation dual-rotor aircraft

Technical Field

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

Background

The existing fixed wing flying aircraft can fly forward at high speed but depends on a runway to take off. Has the loss of speed, and cannot Vertically Take Off and Land (VTOL) 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 an 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.

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.

Seen from a pure compound type, the propeller increases the waste weight of the aircraft on one hand in the vertical take-off and landing process, and does not generate lift force and a corresponding control mechanism for the aircraft. Rotors, wings, and propellers can also create aerodynamic interference, affecting flight efficiency and quality.

Taking a mass-produced V-22 tilt rotor aircraft as an example, because the design of the rotor wing gives consideration to the lift requirement and the forward flying efficiency, the design is not based on the design of the rotor wing of a helicopter or the design of a propeller of a fixed wing aircraft, the load of a propeller disc is large during vertical take-off and landing, the induction speed and the induction power are large, the overload capacity is low, the overload capacity of a rotor wing system is 1.4, the overload capacity of the rotor wing of a typical helicopter is 3.5, the gap is doubled, the low-speed maneuvering capacity is greatly reduced, and the problem of insufficient control authority exists. Gusts of wind not only affect the dual rotors of the row of tiltrotors, but also affect the longer two-sided wings of the tiltrotors. Tiltrotor pilots often need to counteract the effects of gusts through complex maneuvers. In this respect, tiltrotor aircraft also has inferior hover stability to helicopters.

Because of the compromise in aerodynamic design of the rotor (propeller), the rotor cannot operate under optimal aerodynamic conditions as a conventional proprotor, and thus its forward flight speed and efficiency are lower than those of a fixed wing aircraft. The load-to-air-weight ratio of tiltrotor aircraft is only 40%.

The design is convenient for the compromise of the rotor wing, but the propeller of the aircraft is still much larger than that of the conventional fixed wing aircraft, and the aircraft cannot be taken off and landed in a fixed wing mode to leave enough clearance and is inconvenient for running and taking off.

In the compound type of the X2 and the X3, the propeller is not disturbed with the rotor, and the propeller is wasted in taking off, landing and hovering, so that the load efficiency of the aircraft is sacrificed.

In addition to the situation that the propeller waste is heavy and the load efficiency is sacrificed, due to the adoption of the propeller pneumatic design, the combined type of the black leopard type multi-rotor wings has the advantages of large propeller disc load, low lift efficiency and low overload coefficient when the combined type of the black leopard type multi-rotor wings cruises at low speed in vertical take-off and landing, hovering and vertical lifting modes. Once the external disturbance is greater than its overload capability, its control margin is severely insufficient. Because of being compound with fixed wing, the external disturbance is similar to the gyroplane that verts, and the disturbance coefficient is far greater than many pure gyroplanes, controllability greatly reduced.

Disclosure of Invention

The utility model provides a combined type power of verting tandem rotation double rotor aircraft, aircraft organism 1 upper portion is listed as in the column and is arranged two pairs of main lift rotor group 5, and fixed wing 2 has been arranged at organism 1 middle part, and two vertical-vertical tilting force 4 of turning have been arranged at fixed wing 2 both ends, have arranged aileron 8 on the fixed wing 2, have arranged parallel fin 3, perpendicular fin 6, undercarriage 7 on the organism 1.

The aircraft as claimed in claim 1, wherein the upper part of the body 1 is provided with two pairs of main lift rotor groups 5 in longitudinal rows for bearing the main lift of the aircraft during vertical take-off and landing and hovering; the two pairs of main lift rotor groups 5 in the longitudinal row have opposite rotating directions and overcome opposite torques mutually.

The aircraft according to claim 1, characterized in that the total pitch and the cyclic pitch of the two pairs of main lift rotor groups 5 arranged in the upper longitudinal row of the body 1 are variable.

The aircraft of claim 1, wherein the two pairs of main lift rotor sets 5 arranged in tandem on the upper portion of the body are powered for vertical takeoff and landing, hovering, and helicopter mode flight.

The aircraft as claimed in claim 1, wherein two pairs of vertical-longitudinal tilting rotating forces 4 are arranged at two ends of the fixed wing 2, the vertical tilting generates auxiliary lift force, and the longitudinal tilting generates forward flying power.

The aircraft as claimed in claim 1, wherein the two pairs of main lift rotor sets 5 arranged in a longitudinal row are longitudinally tilted along with the vertical-longitudinal tilting rotating force 4, the aircraft enters a forward flight mode, the fixed wing 2 generates a lift force, the lift force is finally assisted by the vertical-longitudinal tilting rotating force 4, and the vertical-longitudinal tilting rotating force 4 is changed into forward flight power; the driving power of the main lift rotor wing set 5 is changed from self-driving power to incoming flow driving power for replacement, the self-driving power is stopped, and the variable force of the main lift rotor wing set 5 is driven to rotate under the incoming flow driving.

The aircraft as claimed in claim 1, wherein the flight attitude control of the compound tilting-powered longitudinal-rotation dual-rotor aircraft is controlled by the main lift rotor set 5 in cooperation with the vertical-longitudinal tilting rotational force 4 during vertical take-off, landing and hovering.

The aircraft as claimed in claim 1, wherein the ailerons 8, the vertical tail 6 and the horizontal tail 3 arranged on the composite tilting power tandem autorotation dual-rotor aircraft perform attitude control on the aircraft during forward flight, and the main lift rotor group performs auxiliary control.

The aircraft of claim 1, wherein the combined tilt-power tandem autorotation dual rotor aircraft is provided with a slidable landing gear 7, and the aircraft can slide, take off and land in the manner of autorotation gyroplanes and fixed-wing aircrafts.

The aircraft of claim 1, wherein the aircraft is capable of spinning, gliding and landing after power loss.

Has the advantages that: the aerodynamic layout design of the combined type tilting power longitudinal rotation dual-rotor aircraft avoids the technical defects of the existing combined type and tilting aircraft, the main lift force suspension wings are arranged by adopting the longitudinal rows, the rotor wing is designed to define a rotor wing group according to the aerodynamic requirements of vertical take-off and landing, hovering and cruise in a rotating rotor wing mode, and the load efficiency of the rotor wing group is higher than that of the existing combined type helicopter, tilting rotorcraft and combined type multi-rotor aircraft.

The main lift rotor is arranged in the vertical row, the counter torque is overcome in the counter rotation of the front rotor and the rear rotor, the lift vector is not changed by the low head before flying at high speed, the rotor lift replaces the rear rotor, the resistance of a propeller disc is reduced, the forward shock wave and the backward stall problem are effectively relieved, the power consumption is reduced, the vibration level and the noise are greatly reduced, and the flying quality is greatly improved.

Because the vertical-longitudinal tilting rotating force is pneumatically designed by the power of the fixed wing aircraft, the forward flying efficiency is greatly improved, the forward flying resistance is reduced, and the flying quality of the whole aircraft is effectively improved.

Vertical-to-vertical tiltable power design is preferred by the power demand of previous flyers, and waste weight is reduced in power design. The power rise ratio is improved.

Because main lift rotor group is with the rotation rotor mode operation when flying ahead, possess and lose power rotation gliding ability, improved the safety and quality of aircraft.

Because the main lifting rotor wing set, the vertical-longitudinal tilting rotating force, the ailerons, the vertical tails and the parallel tails are controlled in multiple ways during flight, the control redundancy of the aircraft is large, and the safety is improved.

The layout mode of the main lift rotor wing set and the vertical-longitudinal tilting rotating force is also favorable for reducing mutual disturbance and improving the flying efficiency.

The combined type tilting power longitudinal rotation dual-rotor aircraft can fly forwards in a combined mode of the fixed wing and the rotation rotorcraft, so that the combined type tilting power longitudinal rotation dual-rotor aircraft can slide and land under the condition of sliding and landing, and the range of the tasks to be executed is expanded.

The combined type tilting power longitudinal rotation dual-rotor aircraft adopts the distributed design of the main lift force and the front flying power, and a new way is created for the application of full-electrochemical and hybrid power of an aircraft power system.

Description of the drawings:

FIG. 1 is a vertical take-off, landing and hovering side view of a combined type tilting power tandem rotation dual-rotor aircraft.

Fig. 2 is a front right-view of a compound tilt-rotor tandem autorotation dual rotor aircraft.

Fig. 3 is a front right-view of the combined tilt-power tandem rotation dual-rotor aircraft.

Figure 1-body; 2-fixed wings; 3-horizontal tail wing; 4-vertical-longitudinal tiltable power; 5-a main lift rotor set; 6-vertical tail; 7-a landing gear; 8 ailerons.

The method comprises the following specific implementation steps: as shown in fig. 1-3, the technical implementation adopts the following technical solutions: the aircraft comprises a fuselage 1, a fixed wing 2, ailerons 8, vertical-longitudinal inclinable rotating force 4, a vertical tail wing 6, a horizontal tail wing 3 and an undercarriage 7, wherein the fixed wing 2 is arranged in the middle of the fuselage 1, the vertical-longitudinal inclinable rotating force 4 is arranged at two ends of the fixed wing 2, and a main lift rotor group 5 is arranged in the upper part of the fuselage 1 in a longitudinal row.

Preferably, the main lift rotor group 5 is designed pneumatically, preferably in a vertical take-off and landing, hovering, helicopter mode cruising, with the autorotation rotorcraft flying forward.

Preferably, the main lift rotor set 5 is arranged in a longitudinal row and rotates in the opposite direction. Overcoming opposite torques from each other.

Preferably, the vertical-longitudinal tilting force 4 is designed pneumatically, preferably with high forward speed.

Preferably, the main lifting rotor set 5 and the vertical-longitudinal tilting rotating force 4 are arranged in a distributed mode, and the fuel engine drive, the electric drive or the fuel oil and electric hybrid drive is adopted.

Preferably, the total pitch and the cyclic pitch of the main lift rotor set 5 are variable.

Preferably, the vertical-longitudinal tilting rotating force 4 can tilt vertically upwards to generate an upward lifting force, and can also tilt longitudinally forwards to generate a horizontal pulling force, so that the high-speed cruising and forward flying power is realized.

Preferably, the left-right vertical-longitudinal tilting rotating force 4 can be differentially tilted, and vertical auxiliary lift force and control force are generated when the aircraft vertically takes off and lands, hovers and cruises at low speed.

The specific implementation mode comprises the following steps:

vertical takeoff, hovering and low-speed cruising: the vertical-longitudinal tilting rotating force 4 tilts vertically upwards and forms a multi-rotor main lift force and an auxiliary lift force with the main lift force rotor wing set 5, so that vertical take-off and landing, hovering and low-speed cruising are realized. The main lift rotor set 5 bears the main lift, and the vertical-longitudinal tilting rotating force 4 bears the auxiliary lift. The helicopter mode can be used for carrying out course, pitching and rolling control on the aircraft through the main lift rotor wing 5, and the auxiliary control can also be generated by means of vertical-longitudinal tilting rotating force 4 power difference and differential tilting.

Front flying and high-speed cruising: when the aircraft flies forwards, the vertical-longitudinal tilting rotating force 4 tilts forwards and longitudinally, the lifting force of the fixed wing 2 is gradually increased, the fixed wing 2 bears the main lifting force of the aircraft, the power of the main lifting force rotor wing set 5 is unloaded and converted into a rotation mode under the action of incoming flow, the aircraft flies forwards in a combined mode of a rotation gyroplane and a fixed wing aircraft, at the moment, due to the rotation mode of the main lifting force rotor wing set 5, forward shock waves and backward stall of blades of the aircraft rotor wing set are delayed, the forward flying resistance is greatly reduced, the speed can be increased, the power consumption is reduced, the noise is reduced, and the high-speed forward flight can be realized.

Hovering and landing: the flying speed is reduced, the main lift rotor wing set 5 is driven, the vertical-longitudinal tilting rotating force 4 vertically tilts upwards, the main lift rotor wing set 5 generates main lift, the tilting rotating force generates auxiliary lift, and hovering and landing are realized.

Running and taking off: the aircraft can tilt forwards and longitudinally by utilizing the vertical-longitudinal tilting rotating force 4, and the load is increased through the undercarriage 7 under the condition of taking off so as to take off by short-distance running in a composite mode of fixed wing aircraft and autorotation gyroplanes. And the takeoff load efficiency is improved.

Spin short landing: the aircraft has the flight characteristics of a fixed wing aircraft and a autorotation gyroplane combined mode, and can autorotate and glide down to land by depending on the fixed wings 2 and the main lift rotor set 5. After losing power, also can slide and land, promoted the safety device of aircraft.

Claims

1. The utility model provides a combined type power of verting tandem rotation double rotor aircraft, aircraft organism 1 upper portion is listed as in the column and is arranged two pairs of main lift rotor group 5, and fixed wing 2 has been arranged at organism 1 middle part, and two vertical-vertical tilting force 4 of turning have been arranged at fixed wing 2 both ends, have arranged aileron 8 on the fixed wing 2, have arranged parallel fin 3, perpendicular fin 6, undercarriage 7 on the organism 1.

2. The aircraft as claimed in claim 1, wherein the upper part of the body 1 is provided with two pairs of main lift rotor groups 5 in longitudinal rows for bearing the main lift of the aircraft during vertical take-off and landing and hovering; the two pairs of main lift rotor groups 5 in the longitudinal row have opposite rotating directions and overcome opposite torques mutually.

3. The aircraft according to claim 1, characterized in that the total pitch and the cyclic pitch of the two pairs of main lift rotor groups 5 arranged in the upper longitudinal row of the body 1 are variable.

4. The aircraft of claim 1, wherein the two pairs of main lift rotor sets 5 arranged in tandem on the upper portion of the body are powered for vertical takeoff and landing, hovering, and helicopter mode flight.

5. The aircraft as claimed in claim 1, wherein two pairs of vertical-longitudinal tilting rotating forces 4 are arranged at two ends of the fixed wing 2, the vertical tilting generates auxiliary lift force, and the longitudinal tilting generates forward flying power.

6. The aircraft as claimed in claim 1, wherein the two pairs of main lift rotor sets 5 arranged in a longitudinal row are longitudinally tilted along with the vertically-longitudinally tiltable propeller 4, the aircraft enters a forward flight mode, the fixed wing 2 generates lift force, the lift force is finally assisted by the vertically-longitudinally tiltable rotating force 4, and the vertically-longitudinally tiltable rotating force 4 is changed into forward flight power; the driving power of the main lift rotor wing set 5 is changed from self-driving power to incoming flow driving power for replacement, the self-driving power is stopped, and the variable force of the main lift rotor wing set 5 is driven to rotate under the incoming flow driving.

7. The aircraft as claimed in claim 1, wherein the flight attitude control of the compound tilting-powered longitudinal-rotation dual-rotor aircraft is controlled by the main lift rotor set 5 in cooperation with the vertically-longitudinally tiltable propeller 4 during vertical take-off, landing and hovering.

8. The aircraft as claimed in claim 1, wherein the ailerons 8, the vertical tail 6 and the horizontal tail 3 arranged on the composite tilting power tandem autorotation dual-rotor aircraft perform attitude control on the aircraft during forward flight, and the main lift rotor group performs auxiliary control.

9. The aircraft of claim 1, wherein the combined tilt-power tandem autorotation dual rotor aircraft is provided with a slidable landing gear 7, and the aircraft can slide, take off and land in the manner of autorotation gyroplanes and fixed-wing aircrafts.

10. The aircraft of claim 1, wherein the aircraft is capable of spinning, gliding and landing after power loss.