CN218751364U

CN218751364U - High-speed aircraft of tandem double rotor tilting configuration

Info

Publication number: CN218751364U
Application number: CN202223149765.0U
Authority: CN
Inventors: 孙梓萌; 刘明琦; 王鹏
Original assignee: China Helicopter Research and Development Institute
Current assignee: China Helicopter Research and Development Institute
Priority date: 2022-11-27
Filing date: 2022-11-27
Publication date: 2023-03-28
Anticipated expiration: 2032-11-27

Abstract

The utility model belongs to the technical field of aircraft design, in particular to a vertical double-rotor-wing tilting-configuration high-speed aircraft; the aircraft comprises a fuselage, a tiltable rotor wing and a foldable wing; foldable wings symmetrical arrangement is in fuselage middle part both sides, and the tilting rotor arranges in aircraft nose upper portion and tail upper portion. Double rotor power overall arrangement around adopting, rotor control structure is similar with helicopter owner rotor control structure, in addition 90 degrees tilting mechanism. The center of gravity of the fuselage is located below the rotor to improve hovering stability. The folded wings provide smaller occupied space in the processes of transportation, storage and the like. Meanwhile, the aircraft can be unfolded in a fixed wing flight mode and folded in a hovering flight mode. To improve the maneuverability of the aircraft. The retractable landing gear is beneficial to reducing the resistance in the flight process. The power is a turboshaft engine.

Description

High-speed aircraft of tandem double rotor tilting configuration

Technical Field

The utility model belongs to the technical field of the aircraft design, concretely relates to vertical double rotor configuration high-speed aircraft that verts.

Background

Most of the existing tilt rotor aircrafts are in a transverse double-rotor tilt layout. Follow the current rotor craft accident analysis that verts and draw, the rotor craft that verts of the overall arrangement of tandem pair rotor has very big degree of difficulty and risk at the rotor transition stage that verts. The tilt rotor aircraft with the transverse double-rotor tilt layout is particularly difficult to control in the pitch direction in the tilt transition stage, and the phenomena of excessive head lowering, head raising, pitch oscillation and the like easily occur to the aircraft in the process.

Disclosure of Invention

The utility model aims at: the utility model discloses a based on current safe problem, the new rotor configuration aircraft that verts that provides makes the rotor aircraft that verts obtain the improvement and the performance optimization of security in the transition phase that verts.

The technical scheme of the utility model: the double-rotor-wing tilting-configuration high-speed aircraft is simple to control, high in efficiency and safe in tilting transition.

A high-speed aircraft with a longitudinal double-rotor wing tilting configuration comprises an aircraft body, tilting rotors and foldable wings; foldable wings symmetrical arrangement is in fuselage middle part both sides, and the tilting rotor arranges in aircraft nose upper portion and tail upper portion.

Furthermore, a tiltable rotor wing positioned above the machine head adopts a pulling paddle; the tiltable rotor wing above the tail adopts a thrust paddle.

Further, the aircraft comprises a take-off and landing mode, a hovering mode and a forward flight mode in the flight process.

Further, in a take-off and landing or hovering mode of the aircraft, the tiltable rotor wing above the aircraft nose tilts upwards in a mode; a tilt-down tilt mode of a tiltable rotor above the tail; the combined mode can effectively improve the hovering efficiency.

Furthermore, in the front flying mode of the aircraft, the front and rear tiltable rotors of the aircraft body are all in a horizontal state in a transition mode from a vertical state, and the arrangement can improve the control stability of the pitching attitude of the aircraft body in the transition state, so that the transition flying safety is improved.

Further, when the aircraft is in a take-off and landing mode, the foldable wings are in a folded state; in the forward flight mode, the foldable wings are in an unfolded state.

Furthermore, an engine is arranged on the airplane body and is positioned below the foldable wings.

Further, in the above-mentioned case, an avionic system and a flight control system are further arranged in the aircraft body.

Furthermore, the lower part of the machine body is also provided with an undercarriage retraction chamber, and a three-point undercarriage is adopted corresponding to the undercarriage.

The utility model has the advantages that: double rotor power overall arrangement around adopting, rotor control structure is similar with helicopter owner rotor control structure, in addition 90 degrees tilting mechanism. The center of gravity of the fuselage is located below the rotor to improve hovering stability. The folded wings provide smaller occupied space in the processes of transportation, storage and the like. Meanwhile, the aircraft can be unfolded in a fixed wing flight mode and folded in a hovering flight mode. To improve the maneuverability of the aircraft. The retractable landing gear is beneficial to reducing the resistance in the flight process. The power is a turboshaft engine.

Drawings

FIG. 1 is a schematic view of the layout of the aircraft of the present invention;

FIG. 2 is a view of a helicopter in a flight state prior to tip-in;

fig. 3 shows the flying state of the fixed wing after tilting.

The aircraft comprises an aircraft body 1, a tiltable rotor wing above an aircraft tail 2, a tiltable rotor wing above an aircraft head 3, a foldable wing 4, a vertical tail 5, an undercarriage retraction chamber 6 and an engine air inlet 7.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the 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 the attached figure 1, the specifically designed aircraft with the tandem double-rotor tilting configuration comprises a fuselage 1, two tilting rotors (2 and 3) and a pair of foldable wings 4; the foldable wings 4 are symmetrically arranged on two sides of the middle of the fuselage 1, and the

tiltable rotors

2 and 3 are respectively arranged on the upper part of the nose and the upper part of the tail; two turboshaft engines are arranged on two sides of the middle of the aircraft body 1 and used for driving the rotor wing to rotate, and engine air inlet channels 7 are arranged on the left side and the right side of the aircraft body and used for engine air inlet; the lower part of the aircraft body is also provided with an undercarriage retraction chamber 6 for retracting the undercarriage after taking off; the fuselage 1 is arranged with double vertical and horizontal tails at the rear, but as a finished aircraft, the person skilled in the art will know that the aircraft also comprises flight control systems, avionics systems and other necessary components.

The utility model discloses an aircraft key design point concentrates on following several aspects:

1. the system can vertically take off and land and can switch the flight mode of the fixed wing;

2. push-pull type front and rear propellers are arranged;

3. the adoption of a longitudinal tilting mechanism is a brand new scheme different from the existing tilting configurations such as V-22, V-280 and the like;

4. the wings can be folded by 90 degrees.

The flight control of the high-speed aircraft with the tandem tilt rotor configuration in the hovering state is realized by adjusting the pitch and the tilt angle of the front and rear tilt rotors as shown in fig. 2. Before the rotor wings tilt and fly, the fixed wings automatically unfold backwards. The front rotor tilts forward by 90 degrees, the rear rotor tilts backward by 90 degrees, and the aircraft accelerates and flies forward at the same time, so that the helicopter is switched to the fixed wing state, and the undercarriage is collected as shown in fig. 3. When falling, the operation is reversed. The dual-rotor tilting configuration high-speed aircraft with the configuration can reduce the research and development difficulty of the flight controller to a great extent. The safety in the tilting transition is improved.

The above description is only for the specific embodiments of the present invention, and the present invention is described in detail, and the detailed description is not the conventional technology. However, the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are also included in the scope of the present invention. The protection scope of the present invention shall be subject to the protection scope of the claims.

Claims

1. A tandem double-rotor-wing tilting configuration high-speed aircraft is characterized by comprising an aircraft body, tilting rotor wings and foldable wings; foldable wings symmetrical arrangement is in fuselage middle part both sides, and the tilting rotor arranges in aircraft nose upper portion and tail upper portion.

2. The tandem dual-rotor tilt configuration high speed aircraft of claim 1, wherein the tiltable rotor above the nose is a tension paddle; the tiltable rotor wing above the tail adopts a thrust paddle.

3. The tandem dual-rotor tip-out configuration high-speed aircraft of claim 1, wherein the aircraft comprises a takeoff and landing mode, a hover mode, and a forward flight mode during flight.

4. The tandem dual-rotor tilt configuration high speed aircraft of claim 3, wherein in the aircraft takeoff and landing or hover mode, the tiltable rotor above the nose is in an up-tilt mode; a tilt-down tilt mode of a tiltable rotor above the tail; the combined mode can effectively improve the hovering efficiency.

5. The tandem dual rotor tilt configuration high speed aircraft of claim 3 wherein in the forward flight mode of the aircraft, both the forward and aft fuselage tiltable rotors transition from a vertical position to a horizontal position.

6. The tandem dual-rotor tiltrotor configuration high-speed aircraft of claim 3, wherein the foldable wings are in a folded state when the aircraft is in the takeoff and landing mode; in the forward flight mode, the foldable wings are in an unfolded state.

7. The tandem dual rotor tiltrotor configuration high speed aircraft of claim 1, further having an engine disposed on said fuselage below said foldable wing; an avionic system and a flight control system are further arranged in the aircraft body; and the lower part of the machine body is also provided with an undercarriage retraction chamber, and a three-point undercarriage is adopted corresponding to the undercarriage.