A rocket-boosted unmanned aerial vehicle

Abstract

The present invention discloses a rocket-boosted unmanned aerial vehicle, and a fuel flow control valve is provided on its fuel oil path. The fuel flow control valve includes a valve body, an end cover and a valve core. One end of the valve body is open, and the other end of the valve body is closed. An oil inlet part is provided at the closed end of the valve body; the end cover is detachably arranged at the open end of the valve body, and an oil outlet part is provided on the end cover; the valve core is arranged inside the valve body, a throttle hole communicating the oil inlet part and the oil outlet part is arranged inside the valve core, and an elastic part connected to the valve body is provided on the valve core. In the present invention, at the moment of the UAV launch, under the action of the inertial force generated by the forward acceleration, the valve core moves backward and closely fits with the oil inlet part, and the fuel is supplied to the engine from the throttle hole of the valve core, controlling the fuel entering the engine to an appropriate amount so that the engine operates in the margin area; once the launch is completed, under the action of the fuel pressure and the elastic restoring force, the valve core separates from the oil inlet part, the valve core is reopened, and metered fuel is supplied to the engine, and the engine then accelerates to the required value.

Description

Technical Field

[0001] The present invention relates to the technical field of small aero-engines, and particularly to a rocket-boosted unmanned aerial vehicle. Background Art

[0002] Launch platforms powered by rockets are widely used for the launch of small unmanned aerial vehicles. The booster rocket provides sufficient kinetic and potential energy in a short time, enabling the flight speed of the unmanned aerial vehicle to increase rapidly and causing it to rise to a certain height. Then the rocket detaches itself, and the on-board engine completes the flight mission.

[0003] Due to the action of acceleration impulse, the load on the engine rotor will decrease; at the same fuel flow rate, the engine speed will be higher than in the stationary state. The engine is usually in an accelerating state during launch. If not controlled during this process, it is very easy to cause problems such as engine overheating and overspeeding. In addition, the fuel tank of the unmanned aerial vehicle is usually arranged in the front of the engine. When the unmanned aerial vehicle is launched by rocket boost, a large acceleration in the opposite direction to the flight direction will be generated. During launch, the fuel will produce a "surge effect" under the action of acceleration, and the engine may be over-rich in fuel during the acceleration process, resulting in engine overheating, flameout, etc., and thus leading to the failure of the flight mission. Therefore, how to ensure the working stability of the engine during the launch of the unmanned aerial vehicle is the key to determining the success or failure of its mission.

[0004] Currently, in conventional long-life aero-engines, the fuel system actuator usually adopts a fuel regulator, which is internally provided with a fuel rapid-drop device. Its main function is to prevent the engine from stalling due to rich fuel during large maneuver flights; however, this device needs to be realized through a series of valves and pressure-sensing elements, with a complex structure and high cost, and is not suitable for short-life and low-cost micro-aero-engines. Summary of the Invention

[0005] The purpose of this application is to provide a rocket-boosted unmanned aerial vehicle to solve the problems raised in the above background art.

[0006] To achieve the above purpose, this application provides the following technical solutions:

[0007] A rocket-boosted unmanned aerial vehicle of the present invention includes a fuel tank and an engine. The fuel tank is connected to the engine through a fuel oil path, and a fuel flow control valve is provided on the fuel oil path. The fuel flow control valve includes:

[0008] A valve body, one end of the valve body is open, the other end of the valve body is closed, and an oil inlet part is provided at the closed end of the valve body;

[0009] An end cover, the end cover is detachably arranged at the open end of the valve body, and an oil outlet part is provided on the end cover;

[0010] The spool valve is arranged inside the valve body. A throttle hole communicating the oil inlet part and the oil outlet part is provided inside the spool valve. An elastic part connected to the valve body is provided on the spool valve. During launch, the spool valve is in close contact with the oil inlet part, and fuel is supplied to the engine through the throttle hole. After the launch is completed, the spool valve is separated from the oil inlet part.

[0011] The direction from the oil inlet part to the oil outlet part of the fuel flow control valve is the same as the acceleration direction of the rocket-boosted unmanned aerial vehicle during launch.

[0012] Further, the spool valve includes a first cylinder body, a second cylinder body, and a third cylinder body connected in sequence from the oil outlet part to the oil inlet part. The cross-section of the first cylinder body is a rounded rectangle, the second cylinder body is cylindrical, the third cylinder body is conical, and the large end of the third cylinder body is connected to the second cylinder body.

[0013] Further, the elastic part is a spring. The spring is sleeved outside the second cylinder body and the third cylinder body. One end of the spring is connected to the outer wall of the second cylinder body, and the other end of the spring is connected to the inner wall of the valve body.

[0014] Further, the throttle hole axially penetrates the first cylinder body, the second cylinder body, and the third cylinder body.

[0015] Further, the oil inlet part includes a first oil inlet channel and a second oil inlet channel. One end of the first oil inlet channel penetrates the outer side wall of the valve body, the other end of the first oil inlet channel is connected to one end of the second oil inlet channel, the other end of the second oil inlet channel penetrates the inner wall of the valve body inward, and the axis of the second oil inlet channel is collinear with the axis of the spool valve.

[0016] Further, the cross-section of the second oil inlet channel is circular. The aperture of the second oil inlet channel is larger than the outer diameter of the small end of the third cylinder body and smaller than the outer diameter of the large end of the third cylinder body.

[0017] Further, one end of the end cover is provided with a first connection disk, and the open end of the valve body is provided with a second connection disk. The first connection disk and the second connection disk are connected by screws.

[0018] Further, an extension part is provided on the side of the first connection disk close to the valve body. The extension part extends into the valve body, and a sealing ring is provided between the extension part and the valve body.

[0019] Further, a boss is provided at the end of the extension part, and the outer peripheral wall of the boss is in contact with the inner wall of the valve body.

[0020] In summary, the technical effects and advantages of the present invention:

[0021] 1. In the present invention, at the moment of the UAV launch, under the action of the inertial force generated by the forward acceleration, the valve core moves backward and closely fits with the oil inlet part. Fuel is supplied to the engine from the throttle hole of the valve core, and the fuel entering the engine is controlled to an appropriate amount, enabling the engine to operate in the margin area. Once the launch is completed, under the action of the fuel pressure and the elastic restoring force, the valve core separates from the oil inlet part, the valve core reopens, and metered fuel is supplied to the engine, and the engine then accelerates to the required value.

[0022] 2. In the present invention, the fuel flow control valve has a small number of parts, consisting of only 4 parts: the valve body, the end cover, the valve core, and the spring; it is light in weight; and it has a low cost. All are ordinary machined parts, without special valves or pressure-sensing elements; it is convenient for disassembly, assembly, and maintenance. The internal situation of the valve body can be inspected by removing the end cover.

[0023] 3. The present invention has a pure mechanical structure and has a passive self-adaptive adjustment function. The flow control can be achieved by relying on the spring to sense the change in acceleration, with high reliability and not easily failing. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the following will briefly introduce the drawings required for use in the description of the embodiments or the prior art. Obviously, the following-described drawings are only some embodiments of the present application. For those skilled in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0025] Figure 1 It is a schematic structural diagram of the fuel flow control valve during launch in an embodiment of the present invention;

[0026] Figure 2 It is a schematic structural diagram of the fuel flow control valve after the launch is completed in an embodiment of the present invention;

[0027] Figure 3 It is Figure 1 the A-A sectional view of

[0028] In the figure: 1. Valve body; 2. End cover; 3. Valve core; 4. Spring; 11. Oil inlet part; 12. Second connection disc; 111. First oil inlet channel; 112. Second oil inlet channel; 21. Oil outlet part; 22. First connection disc; 23. Screw; 24. Extension part; 25. Sealing ring; 26. Boss; 27. External thread; 28. Compression nut; 31. Throttle hole; 32. First cylinder; 33. Second cylinder; 34. Third cylinder. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0029] The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. 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.

[0030] In the description of the present invention, it should be noted that the orientation or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings. It is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as a limitation of the present invention. In addition, the terms "first", "second", and "third" are only used for descriptive purposes and cannot be construed as indicating or implying relative importance.

[0031] In the description of the present invention, it should be noted that unless otherwise clearly defined and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the communication inside two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific situations.

[0032] In addition, the technical features involved in different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0033] The fuel rapid-drop device on the fuel regulator of a long-life aeroengine has a complex structure, high cost, and heavy weight, and is not suitable for short-life and low-cost micro-aeroengines. Currently, most micro-engines use a simple fuel pump to supply fuel, which mainly relies on the engine control law and design margin to ensure the stable operation of the engine during launch. However, it has disadvantages such as poor reliability and many usage limitations. During the launch process, the engine is extremely prone to overheating and flameout, which may lead to the failure of the flight mission.

[0034] The present invention belongs to a fuel flow control valve device for a small aeroengine, which is applicable to a micro-aeroengine device launched by a rocket booster. The purpose of the present invention is to provide a fuel flow control valve with a simple structure and a passive adaptive adjustment function to solve the problem of the influence of acceleration on the working stability of the engine during launch and prevent problems such as over-rich fuel causing engine overheating and flameout during the acceleration process of the engine.

[0035] To this end, an embodiment of the present invention provides a rocket-boosted unmanned aerial vehicle. The fuel flow control valve is applied to the aero-engine device of a micro and small unmanned aerial vehicle launched by a rocket booster; as Figures 1-3 shown, the fuel flow control valve includes a valve body 1, an end cover 2 and a valve core 3. Among them, one end of the valve body 1 is open, the other end of the valve body 1 is closed, and an oil inlet part 11 is provided at the closed end of the valve body 1; the oil inlet part 11 is used to be connected to the fuel tank through an oil inlet pipeline. The end cover 2 is detachably arranged at the open end of the valve body 1, and an oil outlet part 21 is provided on the end cover 2; the valve core 3 is arranged in the valve body 1, a throttle hole 31 communicating the oil inlet part 11 and the oil outlet part 21 is arranged in the valve core 3, and an elastic member connected to the valve body 1 is arranged on the valve core 3; under the action of the rocket boost force, the valve core 3 can move axially along the valve body 1; during launch, the valve core 3 is in close fit with the oil inlet part 11, and fuel is supplied to the engine through the oil inlet part 11, the throttle hole 31 and the oil outlet part 21; after the launch is completed, the valve core 3 is separated from the oil inlet part 11.

[0036] In this embodiment, at the moment of the unmanned aerial vehicle launch, under the action of the inertial force generated by the forward acceleration, the valve core 3 moves backward and is in close fit with the oil inlet part 11, and fuel is supplied to the engine from the throttle hole 31 of the valve core 3, controlling the fuel entering the engine to an appropriate amount so that the engine operates in the margin area; once the launch is completed, under the action of the fuel pressure and the elastic restoring force, the valve core 3 is separated from the oil inlet part 11, the valve core 3 is reopened, and metered fuel is supplied to the engine, and the engine then accelerates to the required value.

[0037] Furthermore, the valve core 3 includes a first cylinder body 32, a second cylinder body 33 and a third cylinder body 34 connected in sequence from the oil outlet part 21 to the oil inlet part 11. The cross-section of the first cylinder body 32 is a rounded rectangle, the second cylinder body 33 is cylindrical, and the third cylinder body 34 is conical. The large end of the third cylinder body 34 is connected to the second cylinder body 33. The end face formed between the first cylinder body 32 and the second cylinder body 33 is conducive to the installation of the elastic member. The conical third cylinder body 34 is conducive to being in close fit with the oil inlet part 11, making the contact between the valve core 3 and the oil inlet part 11 closer.

[0038] Furthermore, the elastic member adopts a spring 4. The spring 4 is sleeved outside the second cylinder body 33 and the third cylinder body 34. One end of the spring 4 is in contact with the outer wall of the second cylinder body 33, and the other end of the spring 4 is in contact with the inner wall of the valve body 1. In this embodiment, the spring 4 is a compression spring. At the moment of the unmanned aerial vehicle launch (1 s to 3 s), under the action of the forward acceleration, the spring 4 is compressed. Once the launch is completed, under the action of the fuel pressure and the restoring force of the spring 4, the valve core 3 is reopened. Optionally, the throttle hole 31 axially penetrates through the first cylinder body 32, the second cylinder body 33 and the third cylinder body 34.

[0039] Further, the oil inlet part 11 includes a first oil inlet passage 111 and a second oil inlet passage 112. One end of the first oil inlet passage 111 penetrates through the outer wall of the valve body 1, the other end of the first oil inlet passage 111 is connected to one end of the second oil inlet passage 112, the other end of the second oil inlet passage 112 penetrates through the inner wall of the valve body 1 inward, and the axis of the second oil inlet passage 112 is collinear with the axis of the valve core 3. The first oil inlet passage 111 is connected to the oil inlet pipeline, and the axis of the second oil inlet passage 112 is collinear with the axis of the valve core 3, which is beneficial to the third cylinder body 34 fitting with the second oil inlet passage 112.

[0040] Further, the cross-section of the second oil inlet passage 112 is circular, the aperture of the second oil inlet passage 112 is larger than the outer diameter of the small end of the third cylinder body 34, and the aperture of the second oil inlet passage 112 is smaller than the outer diameter of the large end of the third cylinder body 34.

[0041] Further, one end of the end cover 2 is provided with a first connection disk 22, the open end of the valve body 1 is provided with a second connection disk 12, and the first connection disk 22 and the second connection disk 12 are connected by screws 23. The number of the screws 23 is multiple, and they are evenly distributed along the circumferential direction of the first connection disk 22 and the second connection disk 12.

[0042] Further, an extension part 24 is provided on the side of the first connection disk 22 close to the valve body 1, the extension part 24 extends into the valve body 1, and a sealing ring 25 is provided between the extension part 24 and the valve body 1. The sealing ring 25 can ensure the sealing performance of the connection between the end cover 2 and the valve body 1.

[0043] Further, a boss 26 is provided at the end of the extension part 24, and the outer peripheral wall of the boss 26 fits with the inner wall of the valve body 1. The provision of the boss 26 can further improve the tightness of the connection between the end cover 2 and the valve body 1.

[0044] This embodiment also provides a rocket-boosted unmanned aerial vehicle, which is launched by a rocket booster. The unmanned aerial vehicle includes a fuel tank and an engine. The fuel tank is connected to the engine through a fuel oil pipeline, and a fuel flow control valve as described above is provided on the fuel oil pipeline. The direction of the oil inlet part 11 of the fuel flow control valve pointing to the oil outlet part 21 is the same as the acceleration direction of the rocket-boosted unmanned aerial vehicle during launch. Specifically, the oil inlet part 11 of the valve body 1 is connected to one end of the oil inlet pipeline, the other end of the oil inlet pipeline is connected to the fuel tank; the end cover 2 is connected to the fuselage, the oil outlet part 21 of the end cover 2 is communicated with the internal oil circuit of the fuselage, and the internal oil circuit of the fuselage is communicated with the fuel nozzle of the engine. An external thread 27 is provided on the outer surface of the end of the end cover 2 away from the valve body 1. After connecting with the fuselage through the external thread 27, it is further fastened by a compression nut 28.

[0045] In this embodiment, the fuel flow control valve has few parts, consisting of only four parts: the valve body 1, the end cover 2, the valve core 3, and the spring 4; it is light in weight; and it has a low cost as all are common machined parts without special valves or pressure-sensing elements. It is convenient for disassembly, assembly, and maintenance. By removing the end cover 2, the internal condition of the valve body 1 can be inspected. This embodiment has a pure mechanical structure and has a passive self-adaptive adjustment function. By relying on the spring 4 to sense the change in acceleration, flow control can be achieved, with high reliability and not easily failing.

[0046] Finally, it should be noted that the above are only the preferred embodiments of the present invention and are not used to limit the present invention. Although the present invention has been described in detail with reference to the foregoing embodiments, for those skilled in the art, they can still modify the technical solutions described in the foregoing embodiments, or perform equivalent replacements for some of the technical features. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention shall be included within the protection scope of the present invention.

Claims

1. A rocket-boosted unmanned aerial vehicle, comprising a fuel tank and an engine, wherein the fuel tank is connected to the engine through a fuel oil circuit, and is characterized in that A fuel flow control valve is provided on the fuel pipeline, and the fuel flow control valve includes: A valve body, one end of the valve body is open, the other end of the valve body is closed, and an oil inlet part is provided at the closed end of the valve body; An end cover, which is detachably arranged at the open end of the valve body, and an oil outlet part is provided on the end cover; A valve core, which is arranged in the valve body. A throttle hole communicating the oil inlet part and the oil outlet part is provided in the valve core, and an elastic part connected to the valve body is provided on the valve core; During launch, the valve core is in close contact with the oil inlet part, and fuel is supplied to the engine through the throttle hole; After the launch is completed, the valve core is separated from the oil inlet part; The direction in which the oil inlet part of the fuel flow control valve points to the oil outlet part is the same as the acceleration direction of the rocket-boosted unmanned aerial vehicle during launch.

2. The rocket-boosted unmanned aerial vehicle according to claim 1, wherein The valve core includes a first cylinder, a second cylinder, and a third cylinder connected in sequence from the oil outlet part to the oil inlet part. The cross-section of the first cylinder is a rounded rectangle, the second cylinder is cylindrical, the third cylinder is conical, and the large end of the third cylinder is connected to the second cylinder.

3. The rocket-boosted unmanned aerial vehicle according to claim 2, wherein The elastic part uses a spring, and the spring is sleeved outside the second cylinder and the third cylinder. One end of the spring is in contact with the outer wall of the second cylinder, and the other end of the spring is in contact with the inner wall of the valve body.

4. The rocket-boosted unmanned aerial vehicle according to claim 2, wherein The throttle hole axially penetrates the first cylinder, the second cylinder, and the third cylinder.

5. The rocket-boosted unmanned aerial vehicle according to claim 2, wherein The oil inlet part includes a first oil inlet channel and a second oil inlet channel. One end of the first oil inlet channel penetrates the outer side wall of the valve body, the other end of the first oil inlet channel is connected to one end of the second oil inlet channel, the other end of the second oil inlet channel penetrates the inner wall of the valve body inward, and the axis of the second oil inlet channel is collinear with the axis of the valve core.

6. The rocket-boosted unmanned aerial vehicle according to claim 5, wherein, The cross-section of the second oil inlet channel is circular, the diameter of the second oil inlet channel is larger than the outer diameter of the small end of the third cylinder, and the diameter of the second oil inlet channel is smaller than the outer diameter of the large end of the third cylinder.

7. The rocket-boosted unmanned aerial vehicle according to claim 1, characterized in that, One end of the end cover is provided with a first connection plate, the open end of the valve body is provided with a second connection plate, and the first connection plate and the second connection plate are connected by screws.

8. The rocket-boosted unmanned aerial vehicle according to claim 7, characterized in that An extension part is provided on the side of the first connection plate close to the valve body, the extension part extends into the valve body, and a sealing ring is provided between the extension part and the valve body.

9. The rocket-boosted unmanned aerial vehicle according to claim 8, wherein, A boss is provided at the end of the extension part, and the outer peripheral wall of the boss is in contact with the inner wall of the valve body.

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