CN217864733U - Compact rhombic composite wing aircraft - Google Patents

Abstract

The utility model relates to a compact diamond-shaped composite wing aircraft, which comprises an aircraft body, wherein the aircraft body is provided with a front wing, a thrust duct and a tail wing in sequence from the front part to the rear part; the two thrust ducts are symmetrically arranged on two sides of the fuselage, the empennage is convexly arranged on the rear part of the fuselage, and the top of the empennage is provided with a rear wing; wingtips at the left end and the right end of the front wing are connected with wingtips at the left end and the right end of the rear wing through a connecting wing, and a plurality of lift fans capable of providing lift in the vertical direction are respectively arranged on the front wing and the rear wing; the front wing, the rear wing and the two connecting wings form a diamond-shaped composite wing together; the thrust duct is capable of tilting movement relative to the fuselage to switch between a vtol mode and a cruise mode. The utility model discloses the scheme of taking is safer when promoting VTOL performance, and a plurality of lift fans carry out redundantly, and the aircraft security is high.

Description

Compact rhombic composite wing aircraft

Technical Field

The utility model relates to an aviation aircraft design field, especially a compound wing aircraft of compact rhombus.

Background

The rhombic wing layout aircraft has light weight, high strength rigidity, small induced resistance, large lift coefficient and good maneuverability direct aerodynamic force control capability, can provide independent attitude or track control for the aircraft, and improves the response quality of flight. The disadvantages of the prior art are that the flight resistance is large and the flight speed is low; complex structure, high requirement on materials and the like. The Xianglong unmanned aircraft in China is the only unmanned aircraft adopting the pneumatic layout of the connecting wings in the world at present.

In order to further apply the advantages of the layout of the diamond-shaped wings to the novel vertical take-off and landing aircraft

The invention discloses a Chinese invention with the application number of 201910260979.9, and provides a novel vertical take-off and landing unmanned aerial vehicle with a coupled wing structure, which realizes vertical take-off and landing flight by mounting propellers on the lower wing surface of a diamond wing. But this design directly increases the flight resistance of the aircraft.

The invention provides a Chinese invention with the application number of 201610227947.5, and provides a high-speed aircraft capable of taking off and landing vertically and a control method thereof, and the scheme is that a rotatable propeller of a osprey aircraft is simply combined with a diamond-shaped wing, so that the aircraft is weak in vertical taking off and landing capability and high in flight control difficulty.

How to design utility model a multipurpose aircraft, possess low-altitude low-speed, high altitude long voyage, the high motor-driven characteristic of anti stall simultaneously, have the aerodynamic configuration advantage of rhombus wing, overcome its defect simultaneously, seem especially important.

SUMMERY OF THE UTILITY MODEL

To solve the above problems, it is an object of the present invention to provide a compact rhombic composite wing aircraft having excellent vertical take-off and landing capability.

The embodiment of the utility model provides an in adopt following scheme to realize: a compact rhombic composite wing aircraft comprises an aircraft body, wherein a front wing, a thrust duct and an empennage are sequentially arranged on the aircraft body from the front part to the rear part; the two thrust ducts are symmetrically arranged on two sides of the fuselage, the empennages are arranged on the rear portion of the fuselage in a protruding mode, and a rear wing is arranged on the top of each empennage;

wingtips at the left end and the right end of the front wing are connected with wingtips at the left end and the right end of the rear wing through a connecting wing, and a plurality of lift fans capable of providing lift in the vertical direction are respectively arranged on the front wing and the rear wing; the front wing, the rear wing and the two connecting wings form a diamond-shaped composite wing together;

the thrust duct can tilt relative to the fuselage so as to switch between a vertical take-off and landing mode and a level flight cruise mode, wherein in the vertical take-off and landing mode, the thrust duct tilts until the ejected airflow is vertically downward; in the level flight cruise mode, the thrust duct is tilted to the level of the ejected airflow and towards the rear of the fuselage.

Preferably, the empennage comprises a left empennage and a right empennage, the left empennage and the right empennage are respectively and partially embedded in the left side and the right side of the rear part of the fuselage, the tops of the left empennage and the right empennage are both connected with the rear wing, and the wing surface between the left empennage and the right empennage forms a V-shaped included angle.

Preferably, the front wing is mounted on the fuselage by adopting a lower single-wing structure, and the rear wing is mounted on the fuselage by adopting an upper single-wing structure.

Preferably, the front wing is connected with the front end of the fuselage, the rear wing is connected with the rear end of the fuselage, and the tail wing is arranged at the top of the connection position of the rear wing and the fuselage.

Preferably, the lift fan comprises a culvert wall, a first mounting bracket and a lift unit, the culvert walls are symmetrically arranged on the front wing and the rear wing respectively, the culvert wall is communicated with the upper surface and the lower surface of the wing, the first mounting bracket is erected in the culvert wall, and the lift unit is arranged on the first mounting bracket.

Preferably, the thrust duct includes duct shell, second installing support and rotates the rotor, and the duct shell can incline tiltably and be connected with the fuselage, and the second installing support will rotate the fixed setting of rotor inside the duct shell.

Preferably, the thrust duct is connected with a duct tilting device embedded in the fuselage to realize tilting, the duct tilting device comprises a fuselage bulkhead, a bearing seat, a duct rotating shaft and a linear steering engine, the fuselage bulkhead is vertically arranged in the fuselage, the bearing seat is a protrusion arranged on the fuselage bulkhead, a hole for the duct rotating shaft to pass through is formed in the bearing seat, the duct rotating shaft consists of a rod piece and a rocker arm connected to one end of the rod piece, the other end of the rod piece is fixedly connected with the thrust duct, and two ends of the linear steering engine are respectively hinged to the rocker arms of the fuselage bulkhead and the duct rotating shaft; the straight line steering wheel is flexible at the during operation, and straight line steering wheel promotes the rocking arm and makes the duct pivot rotates in order to drive the thrust duct and vert.

Preferably, a plurality of horizontal control surfaces are symmetrically arranged on the front wing and the rear wing, and the horizontal control surfaces are used for controlling the rolling and pitching of the aircraft.

The utility model has the advantages that: the utility model provides a compact rhombus composite wing aircraft compares in prior art, the utility model discloses at least, following technological effect has:

1. the utility model discloses the scheme of taking is safer when promoting VTOL performance, and a plurality of lift fans carry out redundantly, and the aircraft security is high.

2. The design of the embedded lifting fan can reduce the weight of the body and increase the components for providing lifting force, and the designed diamond composite wing has small aerodynamic resistance.

3. The design of the thrust duct that can vert can only work under the level flies the mode of cruising, when needs quick VTOL, switches to and uses the VTOL mode to increase aircraft VTOL performance.

Drawings

Fig. 1 is a schematic structural diagram of the present invention;

FIG. 2 is a schematic view of the vertical take-off and landing mode of the present invention;

fig. 3 is a top view of the present invention;

fig. 4 is a front view of the present invention;

fig. 5 is a side view of the present invention;

fig. 6 is a first schematic structural view of the duct tilting device of the present invention;

fig. 7 is a schematic structural diagram of the duct tilting device of the present invention.

Description of reference numerals: the aircraft comprises an aircraft body-1, a front aircraft wing-2, a duct tilting device-3, a rear aircraft wing-4, a connecting wing-204, an empennage-5, a lift fan-6, a thrust duct-7, an aircraft body bulkhead-31, a bearing seat-32, a duct rotating shaft-33, a linear steering engine-34, a duct wall-61, a first mounting bracket-62, a lift unit-63, a duct shell-71, a second mounting bracket-73, a rotary rotor-74, a left empennage-51, a right empennage-52 and a horizontal rudder surface-24.

Detailed Description

The present invention will be further described with reference to the accompanying drawings and specific embodiments.

Referring to fig. 1 to 7, a compact rhombic composite wing aircraft comprises a fuselage 1, wherein the fuselage 1 is provided with a front wing 2, a thrust duct 7 and a tail 5 in sequence from the front to the rear; the empennage 5 is convexly arranged at the rear part of the fuselage 1, and the top of the empennage 5 is provided with a rear wing 4;

wingtips at the left end and the right end of the front wing 2 are connected with wingtips at the left end and the right end of the rear wing 4 through a connecting wing 204, and a plurality of lift fans 6 capable of providing lift in the vertical direction are respectively arranged on the front wing 2 and the rear wing 4; the front wing 2, the rear wing 4 and the two connecting wings 204 form a diamond-shaped composite wing together; the utility model discloses a design neotype rhombus composite wing, make the aircraft have good VTOL performance. The utility model discloses with a plurality of lift fans 6 embedding setting respectively in the front on wing 2 and rear wing 4. The embedded lift fan 6 design can reduce the weight of the body and increase the components for providing lift, and the diamond composite wing has small aerodynamic resistance. The main lift component of the utility model is a lift fan 6.

The thrust duct 7 can perform tilting movement relative to the fuselage 1 so as to switch between a vertical take-off and landing mode and a level flight cruise mode, wherein in the vertical take-off and landing mode, the thrust duct 7 tilts until the ejected airflow is vertically downward; in the cruise mode, the thrust duct 7 is tilted to the level of the ejected air flow and towards the rear of the fuselage 1. In the present case, the thrust duct 7 is used for further improving the vertical take-off and landing function of the aircraft and providing thrust for the aircraft in the level flight cruise mode. It is worth noting that the lift fan 6 and the thrust duct 7 are mutually matched in the take-off process, when the thrust duct 7 is switched to the level flight cruise mode in the vertical take-off and landing mode, the lift fan 6 needs to provide lift in real time, so that the problem that the lift is insufficient and the aircraft is out of control is avoided. In the past, a pair of propellers capable of tilting are adopted as a lifting force and a thrust device like a majun osprey helicopter, and the design causes a plurality of osprey helicopters to break down or even crash when taking off and landing. The event the utility model discloses the scheme of taking is safer when promoting the VTOL, and a plurality of lift fans 6 carry out redundantly, and the aircraft security is high. And the utility model discloses a rhombus composite wing also is fit for being used for the rollerball take-off and landing. The thrust duct 7 can only work in a level flight cruise mode, and when rapid vertical take-off and landing are needed, the vertical take-off and landing mode is switched to be used to increase the vertical take-off and landing performance of the aircraft.

The empennage 5 comprises a left empennage 51 and a right empennage 52, the left empennage 51 and the right empennage 52 are respectively and partially embedded at the left side and the right side of the rear part of the fuselage 1, the tops of the left empennage 51 and the right empennage 52 are both connected with the rear wing 4, and the wing surface between the left empennage 51 and the right empennage 52 is in a V-shaped included angle.

The thrust ducts 7 are symmetrically arranged on two sides of the machine body 1. The design is to further facilitate the control of the aircraft, and the symmetrical design of the two thrust ducts 7 can realize decoupling on the control. Power devices may be further redundant.

The front wing 2 is arranged on the fuselage 1 by adopting a lower single-wing structure, and the rear wing 4 is arranged on the fuselage 1 by adopting an upper single-wing structure. In the design of rhombus wing, the specific configuration of rhombus wing is manifold, and some are that rear wing 4 directly overlap joint is on wing 2 in the front, and some are that rear wing 4 overlap joint is in 2 middle parts of wing in the front, and wing 2 adopts lower single wing structure before the present case, and rear wing 4 adopts last single wing structure.

The front wing 2 is connected with the front end of the fuselage 1, the rear wing 4 is connected with the rear end of the fuselage 1, and the tail wing 5 is arranged at the top of the connection position of the rear wing 4 and the fuselage 1. The aircraft nose part of the aircraft adopts a rhombus composite wing and the aircraft body 1 fusion design, the flight resistance is small, the lift-drag ratio of the rhombus wing is high, the wing load is low, the wing span length can be reduced as far as possible under the condition of meeting the flight requirement, the whole aircraft is more compact, and the occupied space is smaller. The small-size aircraft is easier to save the area of the aircraft hangar, saves the maintenance cost, and is convenient to transport and popularize and use on a large scale. The thrust duct 7 can further make up for the defects that the diamond-shaped wing has large kinetic energy loss at large elevation angle and needs strong thrust, so that the diamond-shaped composite wing is more convenient to apply.

The lift fan 6 comprises a plurality of culvert walls 61, first mounting brackets 62 and lift units 63, wherein the culvert walls 61 are symmetrically arranged on the front wing 2 and the rear wing 4 respectively, the culvert walls 61 are communicated with the upper surface and the lower surface of the wings, the first mounting brackets 62 are erected in the culvert walls 61, and the lift units 63 are arranged on the first mounting brackets 62. The lift fans 6 are main devices for providing lift of the aircraft, and in the scheme, 4 lift fans 6 are symmetrically arranged on the front wing 2 and the rear wing 4 respectively, and 8 lift fans 6 are arranged in total. The number of lift fans 6 can be adjusted as required. If the technical requirements of the aircraft are to be high capacity, the number of lift fans 6 can be set to 12 or more. Besides being symmetrically arranged on the front wing 2 and the rear wing 4, the lift fans 6 can be symmetrically arranged on the front wing 2 and the rear wing 4 in a staggered manner in order to further increase the number of the lift fans 6.

Thrust duct 7 includes duct shell 71, second installing support 73 and rotates rotor 74, and duct shell 71 can be connected with fuselage 1 tiltably, and second installing support 73 will rotate the fixed setting of rotor 74 inside duct shell 71.

The thrust duct 7 realizes tilting by connecting a duct tilting device 3 embedded in the fuselage 1, the duct tilting device 3 comprises a fuselage bulkhead 31, a bearing seat 32, a duct rotating shaft 33 and a linear steering engine 34, the fuselage bulkhead 31 is vertically arranged in the fuselage 1, the bearing seat 32 is a protrusion arranged on the fuselage bulkhead 31, a hole for the duct rotating shaft 33 to pass through is formed in the bearing seat 32, the duct rotating shaft 33 consists of a rod piece and a rocker arm connected to one end of the rod piece, the other end of the rod piece is fixedly connected with the thrust duct 7, and two ends of the linear steering engine 34 are respectively hinged on the rocker arms of the fuselage bulkhead 31 and the duct rotating shaft 33; the linear steering engine 34 stretches out and draws back during operation, and the linear steering engine 34 pushes the rocker arm to enable the duct rotating shaft 33 to rotate so as to drive the thrust duct 7 to tilt. The bypass rotating shaft 33 is connected with the bypass casing 71. The structure of the duct tilting device 3 can be various, and the tilting of the thrust duct 7 can be realized by using modes such as gear meshing and the like.

The front wing 2 and the rear wing 4 are symmetrically provided with a plurality of horizontal control surfaces 24, and the horizontal control surfaces 24 are used for controlling the rolling and pitching of the aircraft. Furthermore, the horizontal control surface 24 is also used for deceleration of the aircraft.

The power system capable of providing energy is arranged in the fuselage 1, and the battery system provides electric energy for power systems and avionic equipment such as the duct tilting device 3, the lift fan 6 and the thrust duct 7.

The working process is as follows:

preparation before takeoff: checking each component of the aircraft, and starting the aircraft after preparing before taking off.

Vertical takeoff: lift fan 6 on wing 2 and the rear wing 4 before starting, start the duct and vert device 3, the duct verts device 3 and drives thrust duct 7 and verts to the vertical downwards of 7 spun air currents of thrust duct, thrust duct 7 in the mode of VTOL. And the power of the lift fan 6 and the power of the thrust duct 7 are increased, and the lift fan 6 and the thrust duct 7 generate vertical lift force to lift the aircraft.

Entering a level flight cruise: the control duct tilting device 3 drives the thrust duct 7 to tilt to the air flow level sprayed out by the thrust duct 7 and face the rear part of the aircraft body 1, and the thrust duct 7 is in a flat flying cruise mode. At this time, the lift fan 6 can be reduced in power to rotate at a low speed, and flow fields on the surfaces of the front wing 2 and the rear wing 4 are stabilized. The lift fan 6 also maintains high power at takeoff, providing further lift to the aircraft.

And (3) a landing process: the control duct verts the work of device 3 and drives thrust duct 7 and verts to the vertical downwards of thrust duct 7 spun air current, and thrust duct 7 is in the mode of VTOL. And the power of the lift fan 6 and the power of the thrust duct 7 are increased, and after the aircraft keeps stable, the power of the lift fan 6 and the power of the thrust duct 7 are gradually reduced until the aircraft lands stably.

The points to be explained are: first, in the description of the present application, it should be noted that, unless otherwise specified and limited, the terms "mounted," "connected," and "connected" should be understood broadly, and may be a mechanical connection or an electrical connection, or a communication between two elements, and may be a direct connection, "upper," "lower," "left," and "right," and the like are only used to indicate a relative positional relationship, and when the absolute position of the object to be described is changed, the relative positional relationship may be changed.

Secondly, the method comprises the following steps: the utility model discloses in the embodiment drawing, only involve the structure that involves with this disclosed embodiment, other structures can refer to common design, under the conflict-free condition, the utility model discloses same embodiment and different embodiments can the intercombination.

Finally, it is only above the preferred embodiment of the present invention, the protection scope of the present invention is not limited to the above embodiments, all belong to the technical scheme of the present invention under the thought all belong to the protection scope of the present invention.

Claims (8)

1. A compact diamond-shaped compound wing aircraft characterized by: the airplane comprises an airplane body (1), wherein a front wing (2), a thrust duct (7) and an empennage (5) are sequentially arranged on the airplane body (1) from the front part to the rear part; the two thrust ducts (7) are symmetrically arranged on two sides of the fuselage (1), the empennage (5) is convexly arranged on the rear part of the fuselage (1), and the top of the empennage (5) is provided with a rear wing (4);

wingtips at the left end and the right end of the front wing (2) are connected with wingtips at the left end and the right end of the rear wing (4) through a connecting wing (204), and a plurality of lift fans (6) capable of providing lift in the vertical direction are respectively arranged on the front wing (2) and the rear wing (4); the front wing (2), the rear wing (4) and the two connecting wings (204) jointly form a rhombic composite wing;

the thrust duct (7) can tilt relative to the fuselage (1) so as to switch between a VTOL mode and a cruise by level, wherein, in the VTOL mode, the thrust duct (7) tilts until the ejected airflow is vertically downward; in the cruise mode, the thrust duct (7) is tilted to the level of the ejected airflow and towards the rear of the fuselage (1).

2. The compact diamond-shaped compound wing aircraft according to claim 1, wherein: the tail wing (5) comprises a left tail wing (51) and a right tail wing (52), the left tail wing (51) and the right tail wing (52) are respectively partially embedded in the left side and the right side of the rear part of the fuselage (1), the tops of the left tail wing (51) and the right tail wing (52) are connected with the rear wing (4), and the wing surface between the left tail wing (51) and the right tail wing (52) is in a V-shaped included angle.

3. The compact diamond-shaped compound wing aircraft according to claim 1, wherein: the front wing (2) is arranged on the fuselage (1) by adopting a lower single-wing structure, and the rear wing (4) is arranged on the fuselage (1) by adopting an upper single-wing structure.

4. The compact diamond-shaped compound wing aircraft according to claim 1, wherein: the front wing (2) is connected with the front end of the fuselage (1), the rear wing (4) is connected with the rear end of the fuselage (1), and the tail wing (5) is arranged at the top of the connection position of the rear wing (4) and the fuselage (1).

5. The compact diamond-shaped compound wing aircraft according to claim 1, wherein: lift fan (6) are including duct wall (61), first installing support (62) and lift unit (63), and a plurality of duct walls (61) are seted up respectively symmetrically in the front on wing (2) and rear wing (4), and duct wall (61) intercommunication wing is from top to bottom, first installing support (62) are erect in duct wall (61), lift unit (63) set up on first installing support (62).

6. The compact diamond-shaped compound wing aircraft according to claim 1, wherein: thrust duct (7) include duct shell (71), second installing support (73) and rotate rotor (74), but duct shell (71) tiltably is connected with fuselage (1), and second installing support (73) will rotate rotor (74) and fix and set up inside duct shell (71).

7. The compact diamond-shaped compound wing aircraft according to claim 1, wherein: the ducted power generation device is characterized in that a thrust duct (7) is connected with a ducted tilting device (3) buried in a machine body (1) in an embedded mode to realize tilting, the ducted tilting device (3) comprises a machine body partition frame (31), a bearing seat (32), a duct rotating shaft (33) and a linear steering engine (34), the machine body partition frame (31) is vertically arranged in the machine body (1), the bearing seat (32) is a protrusion arranged on the machine body partition frame (31), a hole for the duct rotating shaft (33) to pass through is formed in the bearing seat (32), the duct rotating shaft (33) consists of a rod piece and a rocker arm connected to one end of the rod piece, the other end of the rod piece is fixedly connected with the thrust duct (7), and two ends of the linear steering engine (34) are hinged to the rocker arms of the machine body partition frame (31) and the duct rotating shaft (33) respectively; the straight line steering wheel (34) stretches out and draws back when in work, and the straight line steering wheel (34) pushes the rocker arm to enable the duct rotating shaft (33) to rotate so as to drive the thrust duct (7) to tilt.

8. The compact diamond-shaped composite wing aircraft according to claim 1, wherein: the front wing (2) and the rear wing (4) are symmetrically provided with a plurality of horizontal control surfaces (24), and the horizontal control surfaces (24) are used for controlling the rolling and pitching of the aircraft.

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