Inclined nozzle angle engine shell suitable for high-altitude aircraft

Abstract

The utility model discloses an inclined nozzle angle engine shell suitable for a high-altitude aircraft, which comprises a shell assembly, a top cover assembly is matched with the top of the shell assembly, a bottom sealing cover is matched with the bottom of the shell assembly, four inclined nozzles are arranged on one side of the bottom sealing cover, and the four inclined nozzles are uniformly distributed. According to the engine shell with the inclined spray pipe angle suitable for the high-altitude aircraft, the spray pipe is obliquely arranged, the direction of hot airflow sprayed by the spray head is changed, the hot airflow sprayed downwards originally is sprayed towards the side face, and therefore the hot airflow sprayed towards the side face is changed into the hot airflow sprayed towards the side face. Damage of sprayed hot air flow to the launching pad and surrounding objects can be greatly reduced, launching cost is reduced, meanwhile, the reflecting plate is arranged below the spraying pipe, most of heat emitted by the spraying pipe can be reflected to the outer side perpendicular to the spraying pipe, and the influence of the heat of the spraying pipe on the surrounding objects is further reduced.

Description

Technical Field

[0001] This utility model relates to the technical field of aircraft design, specifically to an engine housing with a tilt nozzle angle suitable for high-altitude aircraft. Background Technology

[0002] An angled nozzle engine is an aerospace propulsion device that achieves thrust vector control by adjusting the nozzle exit direction. Its core technology lies in converting the fixed axial thrust of a traditional engine into a vector thrust with an adjustable direction, thereby directly controlling the attitude, maneuverability, and trajectory of an aircraft. The nozzle is located on the outer casing of the angled nozzle engine. Existing angled nozzle engines house the engine inside the casing, and the engine generates a strong airflow through fuel combustion, which is then expelled from the nozzle on the casing to achieve takeoff. However, the aforementioned common angled nozzle engine casings still have shortcomings:

[0003] Traditional tilt-nozzle angled engines have nozzles in the middle of the casing, with the nozzle facing downwards from the launch pad. During launch, the heat emitted from the nozzle can easily damage the launch pad and surrounding objects, resulting in property damage and high launch costs. Utility Model Content

[0004] The purpose of this invention is to provide a tilting nozzle angle engine housing suitable for high-altitude aircraft, in order to solve the problems mentioned in the background art. In traditional tilting nozzle angle engine housings, the nozzle is located in the middle, with the nozzle facing downwards from the launch pad. During launch, the heat emitted from the nozzle can easily damage the launch pad and surrounding objects, resulting in property damage and high launch costs.

[0005] To achieve the above objectives, this utility model provides the following technical solution: a tilting nozzle angle engine housing suitable for high-altitude aircraft, comprising a housing assembly, a top cover assembly matched to the top of the housing assembly, a bottom cover matched to the bottom of the housing assembly, four tilting nozzles arranged evenly on one side of the bottom cover, a heat reflection mechanism for reflecting heat arranged in the middle of the bottom cover, and multiple bottom bolts arranged between the bottom cover and the housing assembly.

[0006] Preferably, the top cover assembly includes a top cover plate, the outer side of which has a sealing groove, and a metal sealing ring is disposed inside the sealing groove.

[0007] Preferably, the housing assembly includes a central housing, the inner wall of which is provided with a central inner housing, and a plurality of top bolts are provided between the top cover plate and the central housing, which helps to protect the stable operation of the engine.

[0008] Preferably, the reflective mechanism includes a heat insulation frame, which is fixedly installed on the bottom cover. One end of the bottom cover is fixedly connected to a sealing base plate by bolts. Multiple high-temperature hydraulic actuators are fixedly installed on the inner wall of the heat insulation frame extending to the outer side of the heat insulation frame. Multiple shaft hole plates are fixedly connected to the outer side of the heat insulation frame, and the multiple shaft hole plates are evenly arranged. A reflector is rotatably connected between two adjacent shaft hole plates. A slider assembly is slidably connected to one side of the reflector. This can greatly reduce the damage of the ejected hot gas flow to the launch pad and surrounding objects, and reduce launch costs.

[0009] Preferably, the reflector includes a rotating shaft, a reflective center plate is fixedly connected to the surface of the rotating shaft, weight-reducing reflective plates are fixedly connected to both sides of the reflective center plate, and an adjustment groove is formed on the surface of the reflective center plate.

[0010] Preferably, the slider assembly includes an adjusting slider disposed inside an adjusting groove, and two connecting hole plates are fixedly connected to the surface of the adjusting slider.

[0011] Preferably, a T-shaped connecting rod is rotatably connected between the two connecting plates, and one end of the T-shaped connecting rod is fixedly connected to the output end of the high-temperature hydraulic device.

[0012] Compared with the prior art, the beneficial effects of this utility model are: by tilting the nozzle and changing the direction of the hot air jet from the nozzle, the hot air jet that was originally jetted downwards is changed to jetted to the side, which can greatly reduce the damage of the jetted hot air jet to the launch pad and surrounding objects, and reduce the launch cost.

[0013] Meanwhile, a reflector is installed below the nozzle, which can reflect most of the heat emitted by the nozzle to the outside perpendicular to the nozzle, further reducing the impact of the nozzle heat on the surrounding objects. After the launch is completed, the reflector can be retracted to prevent the reflector from increasing the drag of the reflected lift-off. Attached Figure Description

[0014] Figure 1 This is a structural diagram of the engine housing with the tilted nozzle angle of this utility model;

[0015] Figure 2 This is a bottom structural diagram of the engine housing with the tilted nozzle angle of this utility model;

[0016] Figure 3 This is a cross-sectional view of the structure of the engine casing with the tilted nozzle angle of this utility model;

[0017] Figure 4 This is a structural diagram of the tilt nozzle angle engine housing reflector mechanism of this utility model;

[0018] Figure 5This is a diagram showing the internal structure of the engine housing with the encapsulation base plate hidden, representing the tilted nozzle angle of this utility model.

[0019] In the diagram: 1. Middle outer shell; 2. Top cover plate; 3. Top bolt; 4. Bottom cover; 5. Metal sealing ring; 6. Middle inner shell; 7. Bottom bolt; 8. Angled nozzle; 9. Heat insulation frame; 10. Encapsulation base plate; 11. High-temperature resistant hydraulic unit; 12. Shaft hole plate; 13. Rotating shaft; 14. Reflector center plate; 15. Weight-reducing side reflector plate; 16. Adjusting slide; 17. Adjusting slider; 18. Connecting hole plate; 19. T-shaped connecting rod. Detailed Implementation

[0020] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention.

[0021] Please see Figure 1-5 This utility model provides an inclined nozzle angle engine housing suitable for high-altitude aircraft, including a housing assembly, a top cover assembly matched with the top of the housing assembly, a bottom cover 4 matched with the bottom of the housing assembly, four inclined nozzles 8 are arranged on one side of the bottom cover 4 and the four inclined nozzles 8 are evenly arranged, a heat reflection mechanism is provided in the middle of the bottom cover 4, and multiple bottom bolts 7 are provided between the bottom cover 4 and the housing assembly.

[0022] See Figure 2 , Figure 3 , Figure 4 and Figure 5Furthermore, the top cover assembly includes a top cover plate 2, with a sealing groove on the outer side of the top cover plate 2 and a metal sealing ring 5 inside the sealing groove. The outer shell assembly includes a middle outer shell 1, with a middle inner shell 6 on the inner wall of the middle outer shell 1. Multiple top bolts 3 are provided between the top cover plate 2 and the middle outer shell 1. The reflective mechanism includes a heat insulation frame 9, which is fixedly installed on the bottom cover 4. One end of the bottom cover 4 is fixedly connected to a sealing base plate 10 by bolts. Multiple high-temperature hydraulic actuators 11 are fixedly installed on the inner wall of the heat insulation frame 9 and the outer side of the heat insulation frame 9. Multiple shaft hole plates 12 are fixedly connected to the outer side of the heat insulation frame 9, and the multiple shaft hole plates 12 are evenly arranged. A reflector is rotatably connected between two adjacent shaft hole plates 12. A slider assembly is slidably connected to one side of the reflector. The reflector includes a rotating shaft 13. A reflective center plate 14 is fixedly connected to the surface of the rotating shaft 13. Weight-reducing side reflectors 15 are fixedly connected to both sides of the reflective center plate 14. An adjustment groove 16 is opened on the surface of the reflective center plate 14. The slider assembly includes an adjustment slider 17. The adjustment slider 17 is disposed inside the adjustment groove 16. Two connecting hole plates 18 are fixedly connected to the surface of the adjustment slider 17. A T-shaped connecting rod 19 is rotatably connected between the two connecting hole plates 18. One end of the T-shaped connecting rod 19 is fixedly connected to the output end of the high-temperature hydraulic device 11.

[0023] During operation, the hot air generated by the engine is ejected through four angled nozzles 8, which avoids directly expelling the hot air towards the launch pad, reducing damage to the launch pad during aircraft launch. Before launch, four high-temperature hydraulic actuators 11 are activated, and their output ends extend, driving the T-shaped connecting rods 19 to extend. At this time, the T-shaped connecting rods 19 rotate relative to the two connecting orifice plates 18, causing the connecting orifice plates 18 and the adjusting slider 17 to move inside the adjusting groove 16. At this time, the reflector center plate 14 rotates from the initial vertical bottom cover 4 position to the position of the angled nozzles 8. In a parallel position, the core function of the reflector center plate 14 is to reflect the airflow from the engine. The weight-reducing side reflector plate 15 is relatively thin. The position where the weight-reducing side reflector plate 15 is installed is not the closest position to the oblique nozzle 8, so a thinner material can be used. While reducing weight, it can also achieve a better heat reflection effect. After the launcher is launched and lifted into the air, the high-temperature hydraulic device 11 resets and simultaneously resets multiple reflector center plates 14 and weight-reducing side reflector plates 15 to prevent the deployed reflector center plates 14 and weight-reducing side reflector plates 15 from causing drag on the aircraft's ascent.

[0024] In this embodiment, the double-layer design of the engine casing provides excellent vibration and impact resistance, ensuring stable engine operation. The heat insulation frame 9 itself has multiple levels of heat insulation barriers, and a high-temperature reflective coating is applied to the surface of the high-temperature hydraulic unit 11 to ensure its stable operation. The encapsulation base plate 10 is bolted together, allowing for periodic maintenance of the internal high-temperature hydraulic unit 11. An aircraft battery is installed on the aircraft, and the engine is also connected to a generator. During engine operation, the generator generates electricity, which is stored in the aircraft battery and used to power the high-temperature hydraulic unit 11. The high-temperature hydraulic unit 11 can be remotely controlled via related devices. The reflective center plate 14 and the weight-reducing side reflective plate 15 are metal substrates coated with ceramic coatings, which can increase the emissivity to over 80% and maintain stability at high temperatures. The reflector surface structure remains intact without melting, oxidation, or decomposition. The heat flow emitted by the angled nozzle 8 is mainly infrared radiation, and its energy distribution matches the peak wavelength of the reflective material. At the same time, the ceramic material has a higher reflectivity in the mid-infrared band, which can effectively reflect the radiant heat of the high-temperature combustion gas. It should be noted that this utility model is an inclined nozzle angle engine shell suitable for high-altitude aircraft. All components are general standard parts or parts known to those skilled in the art. Its structure and principle can be learned by those skilled in the art through technical manuals or conventional experimental methods. In the idle part of this device, all the above-mentioned electrical components, which refer to power components, electrical components, and the matching monitoring computer and power supply, are connected by wires. The specific connection method should refer to the working principle above and complete the electrical connection between each electrical component in sequence. The detailed connection method is a well-known technology in the field.

[0025] Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent substitutions for some of the technical features. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A tilting nozzle angle engine housing suitable for high-altitude aircraft, comprising a housing assembly, characterized in that: The top of the outer casing assembly is matched with a top cover assembly, and the bottom of the outer casing assembly is matched with a bottom cover (4). Four oblique nozzles (8) are provided on one side of the bottom cover (4), and the four oblique nozzles (8) are evenly arranged. A reflective mechanism for reflecting heat is provided in the middle of the bottom cover (4). Multiple bottom bolts (7) are provided between the bottom cover (4) and the outer casing assembly.

2. The inclined nozzle angle engine casing for high-altitude aircraft according to claim 1, characterized in that: The top cover assembly includes a top cover plate (2), and a sealing groove is provided on the outer side of the top cover plate (2), and a metal sealing ring (5) is provided inside the sealing groove.

3. The inclined nozzle angle engine casing for high-altitude aircraft according to claim 2, characterized in that: The outer casing assembly includes a central outer casing (1), the inner wall of which is provided with a central inner casing (6), and a plurality of top bolts (3) are provided between the top cover plate (2) and the central outer casing (1).

4. The inclined nozzle angle engine casing for high-altitude aircraft according to claim 1, characterized in that: The reflective mechanism includes a heat insulation frame (9), which is fixedly installed on a bottom cover (4). One end of the bottom cover (4) is fixedly connected to a sealing base plate (10) by bolts. Multiple high-temperature hydraulic cylinders (11) are fixedly installed on the inner wall of the heat insulation frame (9) to the outer side of the heat insulation frame (9). Multiple shaft hole plates (12) are fixedly connected to the outer side of the heat insulation frame (9), and the multiple shaft hole plates (12) are evenly arranged. A reflector is rotatably connected between two adjacent shaft hole plates (12), and a slider assembly is slidably connected to one side of the reflector.

5. The inclined nozzle angle engine casing for high-altitude aircraft according to claim 4, characterized in that: The reflector includes a rotating shaft (13), a reflective center plate (14) is fixedly connected to the surface of the rotating shaft (13), and weight-reducing reflective plates (15) are fixedly connected to both sides of the reflective center plate (14). An adjustment groove (16) is provided on the surface of the reflective center plate (14).

6. The inclined nozzle angle engine casing for high-altitude aircraft according to claim 5, characterized in that: The slider assembly includes an adjusting slider (17), which is disposed inside the adjusting groove (16), and two connecting hole plates (18) are fixedly connected to the surface of the adjusting slider (17).

7. The inclined nozzle angle engine housing for high-altitude aircraft according to claim 6, characterized in that: A T-shaped connecting rod (19) is rotatably connected between the two connecting plates (18), and one end of the T-shaped connecting rod (19) is fixedly connected to the output end of the high-temperature hydraulic device (11).

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