Aircraft

Abstract

The invention discloses an aircraft, comprising: an aircraft body having a head and a tail; the engine is arranged in the aircraft main body; one end of the spray pipe is connected with the engine, and the other end of the spray pipe extends towards the tail; a through opening is formed in the tail of the exhaust pipe, the exhaust pipe is movably arranged in the through opening, and the exhaust pipe is arranged on the periphery of the spray pipe in a sleeving mode; the adjusting mechanism is connected with the exhaust pipe and used for driving the exhaust pipe to move in the axial direction of the other end of the spray pipe. Through the application of the invention, the invention provides the aircraft capable of adjusting the extension length of the exhaust pipe according to the flight state; through the arrangement of the adjusting mechanism, the exhaust pipe shrinks inwards to reduce the influence of air resistance in the stable level flight, vertical take-off or landing state, and the exhaust pipe automatically extends outwards during climbing or accelerated flight to ensure that high-temperature tail gas is far away from the tail skin, so that the risk that the skin is damaged due to high temperature is effectively avoided.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and particularly to an aircraft. Background Art

[0002] At present, as a new type of aircraft, electric vertical takeoff and landing vehicles (eVTOLs) have shown great potential in the fields of urban air transportation, emergency rescue, etc. In the prior art, the power devices of such eVTOLs are mainly divided into two types: pure electric and hybrid. Among them, the hybrid power device has become the preferred power solution for eVTOLs because it can meet the requirements of large payload and long endurance. Specifically, during the operation of an eVTOL equipped with a hybrid device, the aviation engine keeps running in the cruise state, and high-temperature gas needs to be discharged outward through the exhaust pipe; while during takeoff and landing, the power source switches to the battery, and at this time the exhaust pipe does not participate in the work.

[0003] However, the traditional fixed exhaust pipe has obvious drawbacks in different flight stages of eVTOLs. Specifically, in the cruise state of eVTOLs, especially when climbing or accelerating, the exhaust gas will diffuse towards the tail of the eVTOL. If the exhaust pipe is too short, the high-temperature exhaust gas may directly bake the tail skin, resulting in overheating of the skin and even potentially causing safety accidents. In addition, during takeoff, landing or other non-cruise states, the power source of the eVTOL is electric energy, and the exhaust pipe does not participate in the work. At this time, the too-long exhaust pipe is not only useless, but also affects the overall aerodynamic performance of the eVTOL, increases air resistance, and thus affects flight efficiency and energy consumption. Summary of the Invention

[0004] In view of this, to solve the above problems, the purpose of the present invention is to provide an aircraft, including:

[0005] An aircraft body having a head and a tail opposite to the head;

[0006] An engine disposed within the aircraft body;

[0007] A nozzle, one end of the nozzle is connected to the engine, and the other end of the nozzle extends towards the tail;

[0008] An exhaust pipe, a through hole is opened in the tail, the exhaust pipe is movably disposed within the through hole, and the exhaust pipe is sleeved on the outer periphery of the nozzle;

[0009] An adjustment mechanism connected to the exhaust pipe, and the adjustment mechanism is used to drive the exhaust pipe to move axially along the other end of the nozzle.

[0010] In another preferred embodiment, one end of the exhaust pipe extends into the aircraft body, the other end of the exhaust pipe extends outward through the through opening, and the other end of the exhaust pipe is movably arranged close to or away from the surface of the tail.

[0011] In another preferred embodiment, an installation space is formed in the tail, and the adjustment mechanism is installed in the installation space.

[0012] In another preferred embodiment, the adjustment mechanism includes:

[0013] A mounting frame, the mounting frame is arranged at the bottom of the installation space;

[0014] A first spring, one end of the first spring is connected to the mounting frame;

[0015] A counterweight, the other end of the first spring is connected to the counterweight;

[0016] An extension plate, one end of the extension plate is connected to the exhaust pipe, and the counterweight abuts against the other end of the extension plate;

[0017] A second spring, the second spring is connected between the bottom of the installation space and the extension plate.

[0018] In another preferred embodiment, the counterweight is arranged in a spherical structure.

[0019] In another preferred embodiment, the extension plate includes a first plate body and a second plate body which are connected to each other. The first plate body is arranged parallel to the bottom surface of the installation space, the second plate body is arranged obliquely relative to the bottom surface of the installation space, the second plate body is closer to the first spring relative to the first plate body, and the end of the second plate body away from the first plate body is relatively close to the bottom surface of the installation space.

[0020] In another preferred embodiment, the mounting frame includes a first connecting piece and a second connecting piece which are connected to each other. One end of the first connecting piece and one end of the second connecting piece are respectively fixedly arranged at the bottom of the installation space. The other end of the first connecting piece is connected to the second connecting piece, the second connecting piece is connected to the first spring, and the second connecting piece is arranged obliquely relative to the bottom surface of the installation space.

[0021] In another preferred embodiment, it further includes a limiting plate. The limiting plate is arranged above the extension plate, and the counterweight is movably arranged between the limiting plate and the extension plate.

[0022] In another preferred embodiment, it further includes: a limit groove body, which is arranged on the upper side of the extension plate, and the counterweight can movably extend into the limit groove body.

[0023] In another preferred embodiment, at least part of the tail is arranged in a skin structure.

[0024] Due to the adoption of the above technical solution, the positive effects of the present invention compared with the prior art are as follows:

[0025] By applying the present invention, an aircraft capable of adjusting the outer extension length of the exhaust pipe according to the flight state is provided; through the setting of the adjustment mechanism, when in a stable level flight, vertical takeoff or landing state, the exhaust pipe contracts inward to reduce the influence of air resistance, and when in a climbing or accelerating flight, the exhaust pipe automatically extends outward to ensure that the high-temperature exhaust gas is far away from the tail skin, effectively avoiding the risk of damage to the skin due to high temperature. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 It is an overall schematic diagram of an aircraft of the present invention;

[0027] Figure 2 It is a partial schematic diagram of an aircraft of the present invention.

[0028] In the drawings:

[0029] 1. Aircraft body; 2. Head; 3. Tail; 4. Engine; 5. Nozzle; 6. Exhaust pipe; 7. Adjustment mechanism; 8. Installation space; 9. Mounting bracket; 10. First spring; 11. Counterweight; 12. Extension plate; 13. Second spring; 14. First plate body; 15. Second plate body; 16. First connecting piece; 17. Second connecting piece; 18. Limit plate. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0030] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are part of the embodiments of the present invention, rather than all of them. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0031] In the description of the present invention, it should be understood that the orientation or positional relationship indicated by terms such as "upper", "lower", "left", "right", "inner", "outer", "front", "rear", "horizontal", "vertical", etc. is based on the orientation or positional relationship shown in the accompanying drawings, and is only for the convenience of describing the present invention, rather than indicating or implying that the device or component referred to must have a specific orientation, so it should not be construed as a limitation to the present invention.

[0032] It should be specifically noted that the "horizontal" and "vertical" in the present invention are used to illustrate the approximate positional relationship, rather than the strict "horizontal plane" or "vertical plane".

[0033] As Figure 1 and Figure 2 shown, a flying vehicle of a preferred embodiment is shown, including: a flying vehicle body 1, the flying vehicle body 1 having a head 2 and a tail 3 opposite to the head 2; an engine 4, the engine 4 being disposed within the flying vehicle body 1; a nozzle 5, one end of the nozzle 5 being connected to the engine 4, the other end of the nozzle 5 extending towards the tail 3; an exhaust pipe 6, the tail 3 having an opening, the exhaust pipe 6 being movably disposed within the opening, the exhaust pipe 6 being sleeved around the outer periphery of the nozzle 5; an adjustment mechanism 7, the adjustment mechanism 7 being connected to the exhaust pipe 6, the adjustment mechanism 7 being configured to drive the exhaust pipe 6 to move axially along the other end of the nozzle 5. Further, the flying vehicle body 1 of the present flying vehicle employs a hybrid engine 4 that can be switchably in a hybrid mode or an all-electric mode according to the instructions of a control system; under the drive of the adjustment mechanism 7, the exhaust pipe 6 moves relative to the opening towards the outside or towards the inside of the flying vehicle body 1 so as to cooperate with the operation of the nozzle 5; that is, in the hybrid mode, the exhaust pipe 6 is moved outwards, thereby guiding the exhaust gas generated by the nozzle 5 and keeping it away from the surface of the tail 3 of the flying vehicle body 1; in the all-electric mode, since the nozzle 5 no longer generates exhaust gas, the exhaust pipe 6 is moved inwards, preferably no longer protruding from the surface of the tail 3 of the flying vehicle body 1.

[0034] Further, as a preferred embodiment, the adjustment mechanism 7 at least has the ability to sense the flight state of the flying vehicle body 1 and drive the exhaust pipe 6 to perform different actions according to the flight state.

[0035] Further, as a preferred embodiment, one end of the exhaust pipe 6 extends into the flying vehicle body 1, the other end of the exhaust pipe 6 extends outwards through the opening, and the other end of the exhaust pipe 6 is movably disposed closer to or farther from the surface of the tail 3.

[0036] Further, as a preferred embodiment, an installation space 8 is formed within the tail 3, and the adjustment mechanism 7 is installed within the installation space 8.

[0037] Further, as a preferred embodiment, the adjustment mechanism 7 includes: a mounting bracket 9 disposed at the bottom of the mounting space 8; a first spring 10, one end of the first spring 10 being connected to the mounting bracket 9; a counterweight 11, the other end of the first spring 10 being connected to the counterweight 11; an extension plate 12, one end of the extension plate 12 being connected to the exhaust pipe 6, and the counterweight 11 abutting against the other end of the extension plate 12; a second spring 13 connected between the bottom of the mounting space 8 and the extension plate 12. Further, as the flight state of the aircraft body 1 changes, the counterweight 11 moves accordingly, and then the extension plate 12 drives the counterweight 11 to move accordingly.

[0038] Further, as a preferred embodiment, the counterweight 11 maintains contact with the extension plate 12 by the component of its own gravity, and the exhaust pipe 6 and the extension plate 12 are connected by welding.

[0039] Further, as a preferred embodiment, the counterweight 11 is arranged in a spherical structure.

[0040] Further, as a preferred embodiment, the counterweight 11 is a steel ball.

[0041] Further, as a preferred embodiment, the extension plate 12 includes: a first plate body 14 and a second plate body 15 connected to each other. The first plate body 14 is arranged parallel to the bottom surface of the mounting space 8, the second plate body 15 is arranged obliquely relative to the bottom surface of the mounting space 8, the second plate body 15 is arranged closer to the first spring 10 relative to the first plate body 14, and the end of the second plate body 15 away from the first plate body 14 is relatively closer to the bottom surface of the mounting space 8.

[0042] Further, as a preferred embodiment, the mounting bracket 9 includes: a first connecting member 16 and a second connecting member 17 connected to each other. One end of the first connecting member 16 and one end of the second connecting member 17 are respectively fixedly arranged at the bottom of the mounting space 8, the other end of the first connecting member 16 is connected to the second connecting member 17, the second connecting member 17 is connected to the first spring 10, and the second connecting member 17 is arranged obliquely relative to the bottom surface of the mounting space 8.

[0043] Further, as a preferred embodiment, the other end of the first connecting member 16, one end of the second connecting member 17 and the bottom surface of the accommodating space together form a triangular structure.

[0044] Further, as a preferred embodiment, the axis of the first spring 10 has a gradually upwardly inclined extension trend from the head 2 to the tail 3, and the axis of the second spring 13 is arranged perpendicular to the bottom surface of the accommodating space.

[0045] Further, as a preferred embodiment, it further includes: a limiting plate 18, the limiting plate 18 is disposed above the extension plate 12, and the counterweight 11 is movably disposed between the limiting plate 18 and the extension plate 12. Further, the limiting plate 18 is preferably used to limit the upward movement position of the counterweight 11.

[0046] Further, as a preferred embodiment, the limiting plate 18 is preferably fixedly connected to the inner wall of the accommodating space.

[0047] Further, as a preferred embodiment, it further includes: a limiting groove body, the limiting groove body is disposed on the upper side of the extension plate 12, and the counterweight 11 is movably inserted into the limiting groove body. Further, the position of the counterweight 11 along the axial direction and the radial direction of the first spring 10 is restricted by the setting of the limiting groove body; preferably, the limiting groove body is movably in contact with the lower surface of the limiting plate 18 upward to achieve limiting.

[0048] Further, based on the setting of the above adjustment mechanism 7, the specific working process of the present invention is as follows:

[0049] When the aircraft body 1 is in a level flight state, the exhaust pipe 6 remains in a contracted state to reduce air resistance.

[0050] When the aircraft body 1 enters a climb, due to the flight attitude having an angle of attack, the self-gravity of the counterweight 11 will generate a force component perpendicular to the surface of the extension plate 12, and the counterweight 11 presses the extension plate 12 and moves downward along the central axis direction of the exhaust pipe 6; the axial force of the first spring 10 is reduced due to the force component generated by the counterweight 11 on it, causing the first spring 10 to elongate, thereby pushing the counterweight 11 to slide into the limiting groove body; the extension plate 12 drives the exhaust pipe 6 to extend outward relative to the lower surface of the tail 3, and the second spring 13 is compressed to generate an elastic force; when the force component of the counterweight 11 and the thrust of the first spring 10 reach equilibrium, the exhaust pipe 6 stops displacement, or when the second spring 13 is compressed to the limit, the exhaust pipe 6 is restricted to stop displacement, and at the same time the exhaust pipe 6 extends to the outermost position.

[0051] When the aircraft body 1 enters an accelerated flight, the counterweight 11 will generate a reaction force opposite to the acceleration direction due to its own inertia force, and will also generate a force component perpendicular to the extension plate 12. The elongation principle of the exhaust pipe 6 is the same as that in the climbing situation.

[0052] When the aircraft body 1 enters a stable level flight, vertical takeoff or landing state, the force component of the counterweight 11 on the surface of the extension plate 12 decreases, and the second spring 13 pushes the extension plate 12, the exhaust pipe 6, the limiting plate 18 and the counterweight 11 upward until reaching the limiting plate 18, the counterweight 11 exits the limiting groove body, and the exhaust pipe 6 retracts to the shortest relative to the lower surface of the tail 3.

[0053] The above are only the preferred embodiments of the present invention, and do not limit the implementation manners and protection scope of the present invention accordingly.

[0054] The present invention further has the following implementation manners on the above basis:

[0055] In a further embodiment of the present invention, at least a part of the tail 3 is arranged in a skin structure.

[0056] In a further embodiment of the present invention, the outer surface of the tail 3 has a streamlined structure that gradually slopes upward from the head 2 to the tail 3.

[0057] In a further embodiment of the present invention, a passenger cabin, a luggage compartment, and an engine 4 compartment are sequentially arranged inside the aircraft body 1 from the head 2 to the tail 3. Further, the passenger cabin is for the passengers to take seats, the luggage compartment is for the passengers to place their items, and the engine 4 is arranged in the engine 4 compartment.

[0058] In a further embodiment of the present invention, an installation space 8 is formed on the side of the engine 4 compartment away from the luggage compartment.

[0059] In a further embodiment of the present invention, the adjustment mechanism 7 may also include: a sensing device and a linear driving device. The sensing device preferably obtains the current flight state information of the aircraft body 1 through aviation sensing elements such as gyroscopes and / or accelerometers. The sensing device sends the flight state information to a control system, and the control system controls the linear driving device to drive the movement of the exhaust pipe 6.

[0060] In a further embodiment of the present invention, the sensing device is electrically connected to the control system, the control system is connected to the linear driving device, and the output end of the linear driving device is fixedly connected to the exhaust pipe 6.

[0061] The above are only the preferred embodiments of the present invention, and do not limit the implementation manners and protection scope of the present invention accordingly. For those skilled in the art, it should be realized that all the equivalent replacements and obvious changes made by using the description and illustrations of the present invention should be included in the protection scope of the present invention.

Claims

1. An aircraft, characterized in that: include: an aircraft body, the aircraft body having a head portion and a tail portion opposite to the head portion; an engine, the engine being disposed in the aircraft body; a nozzle, one end of which is connected to the engine, and the other end of which is extended toward the tail; An exhaust pipe, wherein the tail portion is provided with a through opening, the exhaust pipe is movably arranged in the through opening, and the exhaust pipe is sleeved on the outer periphery of the nozzle; An adjustment mechanism is connected to the exhaust pipe and is used to drive the exhaust pipe to move axially along the other end of the nozzle.

2. The aircraft according to claim 1, characterized in that One end of the exhaust pipe is inserted into the aircraft body, and the other end of the exhaust pipe is extended outward through the through opening. The other end of the exhaust pipe can be movably arranged close to or away from the surface of the tail.

3. The aircraft according to claim 1, characterized in that: An installation space is formed in the tail portion, and the adjustment mechanism is installed in the installation space.

4. The aircraft according to claim 3, characterized in that The adjustment mechanism comprises: A mounting frame, the mounting frame being arranged at the bottom of the mounting space; a first spring, one end of which is connected to the mounting bracket; a counterweight, the other end of the first spring being connected to the counterweight; An extension plate, one end of which is connected to the exhaust pipe, and the counterweight is against the other end of the extension plate; A second spring is connected between the bottom of the installation space and the extension plate.

5. The aircraft according to claim 4, characterized in that The counterweight is arranged in a spherical structure.

6. The aircraft according to claim 4, characterized in that The extension plate includes: a first plate body and a second plate body connected to each other, the first plate body is arranged parallel to the bottom surface of the installation space, the second plate body is arranged at an angle relative to the bottom surface of the installation space, the second plate body is arranged close to the first spring relative to the first plate body, and an end of the second plate body away from the first plate body is arranged relatively close to the bottom surface of the installation space.

7. The aircraft according to claim 4, characterized in that: The mounting frame includes: a first connecting member and a second connecting member connected to each other, one end of the first connecting member and one end of the second connecting member are respectively fixedly arranged at the bottom of the mounting space, the other end of the first connecting member is connected to the second connecting member, the second connecting member is connected to the first spring, and the second connecting member is inclined relative to the bottom surface of the mounting space.

8. The aircraft according to claim 4, characterized in that Also includes: A limiting plate is arranged above the extending plate, and the counterweight is movably arranged between the limiting plate and the extending plate.

9. The aircraft according to claim 4, characterized in that: Also includes: A limiting groove body is arranged on the upper side of the extension plate, and the counterweight piece can be movably extended into the limiting groove body.

10. The aircraft according to claim 1, characterized in that: The tail portion is at least partially arranged in a skin structure.

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