CN111532426A - Aircraft with V-shaped empennage and multiple rotors in vertical take-off and landing layout - Google Patents
Aircraft with V-shaped empennage and multiple rotors in vertical take-off and landing layout Download PDFInfo
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- CN111532426A CN111532426A CN202010320399.7A CN202010320399A CN111532426A CN 111532426 A CN111532426 A CN 111532426A CN 202010320399 A CN202010320399 A CN 202010320399A CN 111532426 A CN111532426 A CN 111532426A
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- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000011217 control strategy Methods 0.000 description 2
- 239000002131 composite material Substances 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/16—Aircraft characterised by the type or position of power plants of jet type
- B64D27/20—Aircraft characterised by the type or position of power plants of jet type within, or attached to, fuselages
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- Aviation & Aerospace Engineering (AREA)
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Abstract
The invention relates to the technical field of aircrafts, and discloses an aircraft with a V-shaped empennage and a multi-rotor vertical take-off and landing layout, which comprises an aircraft body, fixed side wings, a V-shaped empennage and a power mechanism for providing forward pulling force of the aircraft, wherein the fixed side wings on two sides are symmetrically provided with wingtip rotors close to the tip end, and the rotating planes of the wingtip rotors and the side wings are positioned in the same plane; the V-tail rotor wings are symmetrically arranged in the two wing sections of the V-shaped empennage, and the rotating planes of the two V-tail rotor wings and the wing sections of the V-shaped empennage are positioned in the same plane. The invention adopts the layout mode that four rotors are respectively embedded in wing tips of wings at two sides and a V-shaped empennage, and the appearance layout of the aircraft can improve the wind resistance of the multi-rotor aircraft, reduce the resistance and improve the flight speed on the premise of ensuring higher structural strength and sufficient power of the aircraft body.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to an aircraft with a V-shaped empennage and a plurality of rotors in vertical take-off and landing layout.
Background
The vertical take-off and landing fixed wing aircraft is an aviation fixed wing aircraft with vertical take-off and landing in a simple and small environment, has the characteristics of simplicity in take-off and landing, long endurance, long voyage distance and the like, and is one of aviation equipment which is mainly developed in various countries. A more common vtol unmanned aerial vehicle mainly includes a multi-rotor composite vtol aircraft, a tail-seated vtol aircraft, and a tilt-type vtol aircraft.
The multi-wingtip rotor wing of the existing multi-rotor wing combined type vertical take-off and landing aircraft is exposed like a multi-wingtip rotor wing and depends on multi-rotor wing reverse twist to carry out course control, and the existing multi-rotor wing combined type vertical take-off and landing aircraft has the defects of larger flight resistance, weaker wind resistance, poorer direction stability and the like; the fuselage of the tail-seated vertical take-off and landing aircraft is in a vertical state in a take-off and landing mode, and a horizontal flying mode is changed into a horizontal state, so that the problems of high gravity center, difficult take-off and landing, complex control and the like exist; and the tilting mechanism and the control system of the tilting type vertical take-off and landing aircraft are relatively complex and have high technical difficulty.
Disclosure of Invention
Based on the problems, the invention provides the aircraft with the V-shaped empennage and the multi-rotor vertical take-off and landing layout, the four rotors are respectively embedded in wing tips of the two sides of the aircraft and the V-shaped empennage, and the appearance layout of the aircraft can improve the wind resistance of the multi-rotor aircraft, reduce the resistance and improve the flight speed on the premise of ensuring higher structural strength and sufficient power of the aircraft body.
In order to solve the technical problems, the invention provides an aircraft with a V-shaped empennage and a multi-rotor-wing vertical take-off and landing layout, which comprises an aircraft body, fixed side wings, a V-shaped empennage and a power mechanism for providing forward pulling force of the aircraft, wherein the fixed side wings on two sides are symmetrically provided with wingtip rotors close to the tip end, and the rotating planes of the wingtip rotors and the fixed side wings are positioned in the same plane; the V-tail rotor wings are symmetrically arranged in the two wing sections of the V-shaped empennage, and the rotating planes of the two V-tail rotor wings and the wing sections of the V-shaped empennage are positioned in the same plane.
Furthermore, two wingtip rotors are respectively embedded in the positions of the fixed side wings close to the wingtips.
Furthermore, the power mechanism is a propeller and is positioned at the front end of the machine body.
Furthermore, the power mechanism is a propeller and is positioned at the tail part of the machine body.
Further, the power mechanism is a turbojet engine or a turbofan engine arranged at the tail of the engine body.
Furthermore, the power mechanism comprises two propellers which are respectively and symmetrically arranged at the front positions of the windward sides of the fixed side wings at the two sides.
Further, two wingtip rotors are two tilting rotors, and the two tilting rotors are respectively and symmetrically arranged at the outer side positions of the tips of the two fixed side wings.
Compared with the prior art, the invention has the beneficial effects that:
1) the flight resistance during cruise is reduced: the vertical take-off and landing aircraft composed of two fixed side wing wingtip rotary wings and a V-shaped tail rotary wing of a V-shaped tail wing has the advantages that the hovering power or posture auxiliary arrangement mode can obviously reduce the resistance of the aircraft, and under the condition of ensuring the same propelling efficiency, because the multiple rotary wings are embedded, the fixed wings have small resistance and longer flight time;
2) enhancing the wind resistance of the aircraft: compared with a combined vertical takeoff device which is operated by means of multi-rotor wing reverse-twisting course, the wing tip rotor wings of the fixed side wings on the two sides and the V-shaped tail rotor wing of the V-shaped tail wing are embedded, and the course operation is still directly driven by the tension of the V-shaped tail rotor wing of the V-shaped tail wing, so that the wind resistance of the aircraft can be obviously improved;
3) the control of the vertical lifting is simple: the hovering control mode of the layout is similar to a combined type vertical take-off and landing mode, and the difficulty in designing a flight control strategy and a control law is low;
4) compatible with various power arrangements: the aircraft adopts a vertical layout form of wingtip rotors of wingtips of two fixed side wings and V-shaped tail rotors of a V-shaped tail wing, the aircraft has a simple structure, the problem of blade interference of forward pulling and backward pushing power does not exist, and the aircraft can be compatible with various power layouts;
5) applicable high-speed configuration: the aircraft adopts the embedded mode rotor layout, does not have other parts that expose, and the area of facing the wind is little, can be applicable to high-speed overall arrangement configuration.
Drawings
FIG. 1 is a schematic structural view of an aircraft in a V-tail multi-rotor VTOL layout in embodiment 1;
FIG. 2 is a front view of the arrangement of the V-shaped flight of FIG. 1;
FIG. 3 is a schematic view showing a multi-rotor VTOL layout of the V-type empennage in which propellers are installed at the front ends of wings on both sides in embodiment 2;
FIG. 4 is a schematic view showing a multi-rotor VTOL layout with a V-shaped tail and propellers mounted on the tail of a fuselage in accordance with embodiment 2;
FIG. 5 is a schematic view showing a V-type empennage multi-rotor VTOL layout with a turbofan engine added to the tail of the fuselage in embodiment 2;
fig. 6 is a schematic view of a V-type empennage multi-rotor vertical take-off and landing layout of a tip-tilt rotor according to embodiment 3;
wherein: 1. a body; 2. fixing the side wings; 3. a propeller; 4. a wingtip rotor; 5. a V-shaped tail; 6. a tail rotor wing V; 7. turbofan engine.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail below with reference to examples and accompanying drawings, and the exemplary embodiments and descriptions thereof are only used for explaining the present invention and are not meant to limit the present invention.
Example 1:
referring to fig. 1 and 2, an aircraft with a V-shaped empennage and multiple rotor wings in vertical take-off and landing layout comprises an aircraft body 1, fixed side wings 2, a V-shaped empennage 5 and a power mechanism for providing forward tension of the aircraft, wherein wing tip rotors 4 are symmetrically arranged at positions of the fixed side wings 2 on two sides close to a tip end, and rotating planes of the wing tip rotors 4 and the fixed side wings 2 are located in the same plane; v-tail rotor wings 6 are symmetrically arranged in two wing sections of the V-shaped tail wing 5, and the rotating planes of the two V-tail rotor wings 6 and the wing sections of the V-shaped tail wing 5 are positioned in the same plane.
In the embodiment, the vertical take-off and landing aircraft composed of the wingtip rotor 4 of the wingtips of the two fixed side wings 2 and the V-tail rotor 6 of the V-shaped empennage 5 can obviously reduce the resistance of the aircraft due to the arrangement form of hovering power or attitude assistance; under the condition of ensuring the same propelling efficiency, the rotating planes of the wingtip rotor wing 4 and the V-shaped tail rotor wing 6 are respectively positioned in the same plane with the wing sections where the rotating planes are positioned, and the fixed wing has small resistance and longer flight time during cruising; the hovering control mode of the layout is similar to a combined vertical take-off and landing mode, the difficulty in designing a flight control strategy and a control law is low, but compared with a combined vertical take-off device which depends on multi-rotor anti-twist course control, the wingtip rotors 4 of the fixed side wings 2 on two sides and the V-shaped tail rotors 6 of the V-shaped tail wing 5 adopt an embedded mode, the course control still adopts a mode of directly driving the V-shaped tail rotors 6 of the V-shaped tail wing 5 through pulling force, and the wind resistance of the aircraft can be obviously improved.
In this embodiment, two wingtip rotors 4 are embedded respectively in the position that fixed flank 2 is close to the wingtip, realize the embedded of many rotors. The power mechanism is a propeller 3 and is positioned at the front end of the aircraft body 1 to provide forward pulling force for the course flight of the aircraft.
Example 2:
referring to fig. 3, 4 or 5, the aircraft with the V-shaped empennage and the multi-rotor vertical take-off and landing layout comprises an aircraft body 1, fixed side wings 2, a V-shaped empennage 5 and a power mechanism for providing forward pulling force of the aircraft, wherein the fixed side wings 2 on two sides are symmetrically provided with wingtip rotors 4 at positions close to the tips, and the rotating planes of the wingtip rotors 4 and the fixed side wings 2 are positioned in the same plane; v-tail rotor wings 6 are symmetrically arranged in two wing sections of the V-shaped tail wing 5, and the rotating planes of the two V-tail rotor wings 6 and the wing sections of the V-shaped tail wing 5 are positioned in the same plane.
The aircraft adopts a vertical layout form of wingtip rotors 4 of two fixed side wings 2 and V-shaped tail rotors 6 of a V-shaped tail wing 5, the aircraft is simple in structure, the problem of blade interference of forward pulling and backward pushing power does not exist, and various power layouts can be compatible; therefore, the present invention is not limited to the layout scheme of the V-type tail 5 with multiple rotors in the embodiment 1, but also includes the layout scheme of the propeller 3 propulsion or the tail-band turbojet/turbofan. For example:
the power mechanism comprises two propellers 3, and the two propellers 3 are respectively and symmetrically arranged at the front positions of the windward sides of the fixed side wings 2 at the two sides, as shown in fig. 3; the propeller 3 may also be mounted aft of the fuselage 1, as shown in fig. 4; in addition, the power mechanism may also provide forward thrust for the turbojet engine or turbofan engine 7 disposed at the tail of the fuselage 1, so as to form a multi-rotor vertical take-off and landing layout of the V-shaped empennage 5 of the turbojet engine or turbofan engine 7 at the tail of the fuselage 1, as shown in fig. 5, which is a schematic view of an aerodynamic layout of the turbofan engine 7 at the tail of the fuselage 1.
Other parts in this embodiment are the same as embodiment 1, and are not described herein again.
Example 3:
referring to fig. 6, the aircraft with the V-shaped empennage and the multi-rotor vertical take-off and landing layout comprises an aircraft body 1, fixed side wings 2, a V-shaped empennage 5 and a power mechanism for providing forward pulling force of the aircraft, wherein the fixed side wings 2 on two sides are symmetrically provided with wingtip rotors 4 at positions close to the tip ends, and the rotating planes of the wingtip rotors 4 and the fixed side wings 2 are positioned in the same plane; v-tail rotor wings 6 are symmetrically arranged in two wing sections of the V-shaped tail wing 5, and the rotating planes of the two V-tail rotor wings 6 and the wing sections of the V-shaped tail wing 5 are positioned in the same plane.
In this embodiment, two wingtip rotors 4 are two tilting rotors, two tilting rotors are respectively symmetrical to be set up in the most advanced outside position of two fixed flanks 2, form tilting rotor aircraft, tilting rotor aircraft is in the two wing point departments of similar fixed wing aircraft wing, respectively adorn one set can be at the rotor system of tilting between horizontal position and vertical position subassembly that can rotate, when aircraft vertical takeoff and landing, rotor shaft perpendicular to ground, be the tandem helicopter flight state, and can hover in the air, fly around and the side flies. After the tilt rotor aircraft takes off and reaches the uniform velocity, the rotor shaft can tilt 90 degrees forward, is the horizontality, and the tilt rotor directly provides the pulling force that advances for the aircraft as power unit, and the tilt rotor aircraft can do long-range flight like the fixed wing aircraft with higher speed this moment. The helicopter has the capabilities of vertical take-off and landing and hovering in the air of a common helicopter, also has the capability of high-speed cruising flight of a turbine engine aircraft, can also save other power mechanisms at the front end, the tail part or the side end of the helicopter body 1, reduces the weight of the aircraft, and is beneficial to further increasing the cruising ability.
Other parts in this embodiment are the same as embodiment 1, and are not described herein again.
The above is an embodiment of the present invention. The embodiments and specific parameters in the embodiments are only for the purpose of clearly illustrating the verification process of the invention and are not intended to limit the scope of the invention, which is defined by the claims, and all equivalent structural changes made by using the contents of the specification and the drawings of the present invention should be covered by the scope of the present invention.
Claims (7)
1. The utility model provides an aircraft of many rotors VTOL overall arrangement of V type fin, includes fuselage (1), fixed flank (2), V type fin (5) and provides the aircraft power unit that pulling force advances, its characterized in that: wing tip rotors (4) are symmetrically arranged at the positions, close to the tip, of the fixed side wings (2) on the two sides, and the rotating planes of the wing tip rotors (4) and the fixed side wings (2) are located in the same plane; v tail rotor wings (6) are symmetrically arranged in two wing sections of the V-shaped empennage (5), and the rotating plane of the V tail rotor wings (6) and the wing sections of the V-shaped empennage (5) are located on the same plane.
2. The aircraft of claim 1, wherein the V-tail multi-rotor vtol configuration comprises: the two wingtip rotors (4) are embedded in the positions, close to the wingtips, of the fixed side wings (2) respectively.
3. The aircraft of claim 2, wherein the V-tail multi-rotor vtol configuration comprises: the power mechanism is a propeller (3) and is positioned at the front end of the machine body (1).
4. The aircraft of claim 2, wherein the V-tail multi-rotor vtol configuration comprises: the power mechanism is a propeller (3) and is positioned at the tail part of the machine body (1).
5. The aircraft of claim 2, wherein the V-tail multi-rotor vtol configuration comprises: the power mechanism is a turbojet engine or a turbofan engine (7) arranged at the tail of the engine body (1).
6. The aircraft of claim 2, wherein the V-tail multi-rotor vtol configuration comprises: the power mechanism comprises two propellers (3), and the two propellers (3) are symmetrically arranged at the front positions of the windward sides of the fixed side wings (2) respectively.
7. The aircraft of claim 1, wherein the V-tail multi-rotor vtol configuration comprises: two wingtip rotor (4) are two tilting rotor, two tilting rotor symmetry respectively sets up in the most advanced outside position of two fixed flank (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010320399.7A CN111532426A (en) | 2020-04-22 | 2020-04-22 | Aircraft with V-shaped empennage and multiple rotors in vertical take-off and landing layout |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010320399.7A CN111532426A (en) | 2020-04-22 | 2020-04-22 | Aircraft with V-shaped empennage and multiple rotors in vertical take-off and landing layout |
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| CN111532426A true CN111532426A (en) | 2020-08-14 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113697097A (en) * | 2021-09-01 | 2021-11-26 | 中国航空研究院 | Overall pneumatic layout of fixed-wing aircraft with tiltable outer wings and rotary wings |
| CN116215852A (en) * | 2023-05-08 | 2023-06-06 | 成都沃飞天驭科技有限公司 | A kind of control method of vertical take-off and landing aircraft and vertical take-off and landing aircraft |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113697097A (en) * | 2021-09-01 | 2021-11-26 | 中国航空研究院 | Overall pneumatic layout of fixed-wing aircraft with tiltable outer wings and rotary wings |
| CN113697097B (en) * | 2021-09-01 | 2024-01-02 | 中国航空研究院 | Fixed wing aircraft overall aerodynamic layout with tiltable outer wings and rotor wings |
| CN116215852A (en) * | 2023-05-08 | 2023-06-06 | 成都沃飞天驭科技有限公司 | A kind of control method of vertical take-off and landing aircraft and vertical take-off and landing aircraft |
| CN116215852B (en) * | 2023-05-08 | 2023-07-18 | 成都沃飞天驭科技有限公司 | A kind of control method of vertical take-off and landing aircraft and vertical take-off and landing aircraft |
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Application publication date: 20200814 |