Engine posture orbit control servo mechanism

Abstract

This invention discloses an engine attitude trajectory control mechanism, relating to the field of attitude trajectory control technology, to solve the problem of difficulty in achieving continuous adjustment of nozzle thrust in existing technologies. The engine attitude trajectory control mechanism of this invention includes a gas passage, a housing, a control component, and a nozzle. The gas passage and the nozzle are connected to the housing. The control component is disposed within the housing and is used to control the area of ​​the nozzle throat. The control component includes a servo motor and a drive gear, with the servo motor connected to the drive gear. This invention enables continuous adjustment of nozzle thrust, has a simple structure, and is easy to operate. The thrust of the nozzle can be effectively controlled by controlling the servo motor.

Description

Technical Field

[0001] This invention relates to the field of attitude and trajectory control technology, and in particular to an engine attitude and trajectory control servo mechanism. Background Technology

[0002] Solid Attitude and Orbit Control (SDACS) systems are mainly divided into two types: gas-controlled valve type and array impulse type. Among them, the gas-controlled valve type solid attitude and orbit control propulsion system mainly consists of a gas generator, high-temperature gas valve, nozzle, igniter and controller, etc., and is suitable for aircraft models with high thrust, long endurance and complex attitude adjustment maneuvers.

[0003] In the existing technology, conventional solenoid valves and gas valves cannot achieve continuous proportional adjustment, making it difficult to achieve continuous adjustment of the thrust of the aircraft nozzle. At the same time, impurities in the gas can easily clog the pipeline, affecting the engine's performance. Summary of the Invention

[0004] Based on the above analysis, the present invention aims to provide an engine attitude trajectory control mechanism to solve the problem that it is difficult to achieve continuous adjustable nozzle thrust in the prior art.

[0005] The objective of this invention is mainly achieved through the following technical solutions:

[0006] The present invention provides an engine attitude control mechanism, including a gas passage, a housing, a control component, and a nozzle. The gas passage and the nozzle are connected to the housing, and the control component is disposed within the housing. The control component is used to control the area of ​​the throat of the nozzle.

[0007] Furthermore, the control component includes a servo motor and a drive gear, with the servo motor connected to the drive gear.

[0008] Furthermore, the control component also includes a rack that meshes with the drive gear.

[0009] Furthermore, the control assembly also includes a valve stem and a needle valve, the rack being connected to the valve stem, and the valve stem being connected to the needle valve.

[0010] Furthermore, a movable ring is provided on the valve stem, the movable ring is connected to the housing, and the valve stem can move within the movable ring.

[0011] Furthermore, the control assembly also includes a connecting rod, a fixing rod, and a sealing element.

[0012] Furthermore, a support rod is provided on the drive gear, and the support rod is connected to the connecting rod.

[0013] Furthermore, the connecting rod is hinged to the housing and connected to the sealing element.

[0014] Furthermore, the fixing rod is disposed inside the housing, the sealing member is connected to the fixing rod, and can move along the fixing rod under the drive of the connecting rod.

[0015] Furthermore, it also includes a filter component.

[0016] Furthermore, the connecting rod includes a swing section and a connecting groove. The connecting groove is connected to the support rod, so that the support rod moves within the connecting groove as the drive gear rotates, thereby driving the connecting rod to swing as the drive gear rotates.

[0017] Furthermore, the swing section is connected to the connecting groove, and the position where the swing section is connected to the connecting groove is hinged to the housing. The swing section is engaged with the sealing component to drive the sealing component to move.

[0018] Furthermore, the end of the swing section connected to the sealing component is set to be arc-shaped.

[0019] Furthermore, the sealing component includes a sealing plate, a sleeve, and an engaging block. The engaging block is connected to the sealing plate via the sleeve, and the sleeve is connected to the fixed rod and can move along the fixed rod. The position of the sealing plate matches the position of the nozzle throat to seal the nozzle throat. The engaging block is engaged with the swing section.

[0020] Furthermore, the filter assembly includes a filter frame, a filter screen, a rotating wheel, and a driven wheel. One end of the filter frame is connected to the gas passage, and the other end is connected to the housing. A rotating wheel is installed inside the filter frame, and the two sides of the rotating wheel are connected to the driven wheel through connecting rods. The driven wheel can rotate with the rotating wheel. The driven wheel is connected to the filter frame through a bearing seat. The driven wheel is connected to the filter screen, and the position of the filter screen is matched with the gas passage to filter the gas entering the filter frame.

[0021] The present invention also provides a nozzle thrust control method, which uses the above-mentioned engine attitude and trajectory control mechanism to control nozzle thrust.

[0022] Furthermore, it includes the following steps:

[0023] S1: Identify the flight target and plan the flight route;

[0024] S2: Determine the ignition time and required thrust of the attitude control engine;

[0025] S3: Adjust the throat area of ​​the nozzle;

[0026] S4: Start the attitude control engine;

[0027] S5: Corrects flight attitude.

[0028] Furthermore, step S2 specifically includes:

[0029] Step S21: Determine the attitude control engine that needs to be activated;

[0030] Step S22: Determine the thrust of the nozzle.

[0031] Furthermore, step S3 specifically includes:

[0032] S31: Determine the nozzle throat area based on the required thrust;

[0033] S32: Start the servo motor.

[0034] Furthermore, in step S32, the servo motor is controlled to rotate the drive gear, thereby changing the sealing area of ​​the nozzle throat so that the throat area of ​​the nozzle is adapted to the thrust required by the nozzle.

[0035] Furthermore, in step S32, the needle valve is moved toward or away from the nozzle by the drive gear driven by the servo motor.

[0036] Furthermore, in step S32, the drive gear is rotated by the servo motor, causing the connecting rod to swing, which in turn drives the sealing plate to move along the fixed rod, thereby changing the sealing area of ​​the nozzle throat.

[0037] Compared with the prior art, the present invention can achieve at least one of the following beneficial effects:

[0038] (1) The engine attitude trajectory control mechanism provided by the present invention can control the area of ​​the nozzle throat by setting a control component, so that the area of ​​the nozzle throat changes linearly, thereby realizing the continuous adjustment of the nozzle thrust. The control component includes a servo motor and a drive gear. The clock valve can move closer to or further away from the nozzle as the drive gear rotates, thereby linearly changing the contact area between the gas and the nozzle throat, realizing the continuous adjustment of the nozzle thrust. The structure is simple, and the nozzle thrust can be controlled by controlling the servo motor. The operation is simple and the magnitude of the nozzle thrust can be effectively controlled.

[0039] (2) The engine attitude trajectory control mechanism provided by this invention can control the area of ​​the nozzle throat by setting a control component, so that the area of ​​the nozzle throat changes linearly, thereby realizing continuous adjustment of the nozzle thrust. The control component includes a servo motor, a drive gear, a connecting rod, and a sealing component. By controlling the servo motor, the drive gear can be rotated, thereby causing the connecting rod to swing. Through the meshing connection between the swing section and the sealing component, the sealing plate is driven to move along the fixed rod, thereby linearly changing the nozzle throat area and making the nozzle thrust change continuously. This invention has a simple structure. By controlling the movement of the sealing plate by controlling the servo motor, the nozzle throat area is linearly changed. It is easy to operate and can effectively control the magnitude of the nozzle thrust.

[0040] (3) The engine attitude control mechanism provided by the present invention can filter the gas entering the housing through the gas passage by setting a filter component, preventing solid impurities in the gas from clogging the nozzle, thereby ensuring the working performance of the nozzle. By setting a rotating wheel and a driven wheel, the filter screen can be continuously rolled, preventing solid impurities from accumulating on the filter screen and affecting the gas flow and filtration effect; by setting a cleaning component, the solid impurities deposited on the filter screen can be cleaned during the rolling process of the filter screen, thereby keeping the filter screen clean, improving the working performance and service life of the filter screen, and preventing the accumulation of solid impurities from affecting the working performance of the filter component and the flow of gas.

[0041] (4) The nozzle thrust control method provided by this invention employs an engine attitude trajectory control mechanism. By planning the flight path of the aircraft, the thrust of the attitude trajectory control engine and nozzle to be activated is determined. The throat area of ​​the nozzle is linearly adjusted by a servo motor, which improves the control of the nozzle thrust. The operation is simple and improves the accuracy and stability of attitude trajectory control adjustment. The servo motor drives the drive gear to rotate, which can move the needle valve or sealing plate, thereby linearly changing the throat area of ​​the nozzle and thus changing the thrust of the nozzle. This allows for precise control of the nozzle thrust, ensuring the flight path and attitude of the aircraft and improving the flight accuracy of the aircraft.

[0042] In this invention, the above-described technical solutions can be combined with each other to achieve more preferred combinations. Other features and advantages of this invention will be set forth in the following description, and some advantages may become apparent from the description or be learned by practicing the invention. The objects and other advantages of this invention can be realized and obtained through the embodiments described and the accompanying drawings, which are particularly pointed out. Attached Figure Description

[0043] The accompanying drawings are for illustrative purposes only and are not intended to limit the invention. Throughout the drawings, the same reference numerals denote the same parts.

[0044] Figure 1This is a schematic diagram of the overall structure of the engine attitude trajectory control mechanism according to Embodiment 1 of the present invention;

[0045] Figure 2 This is a schematic diagram of the control component of Embodiment 1 of the present invention;

[0046] Figure 3 This is a schematic diagram of the structure of the control component in Embodiment 2 of the present invention;

[0047] Figure 4 A schematic diagram of the overall structure of the engine attitude control mechanism in Embodiment 3 of the present invention;

[0048] Figure 5 This is a schematic cross-sectional view of the filter assembly according to Embodiment 3 of the present invention;

[0049] Figure 6 This is a schematic flowchart of the nozzle thrust control method according to Embodiment 4 of the present invention.

[0050] Figure label:

[0051] 1-Gas passage; 2-Housing; 3-Control component; 31-Servo motor; 32-Drive gear; 321-Support rod; 33-Rack; 34-Valve stem; 341-Moving ring; 35-Needle valve; 36-Connecting rod; 361-Swing section; 362-Connecting groove; 37-Fixing rod; 38-Sealing component; 381-Sealing plate; 382-Sleeve; 383-Meshing block; 4-Nozzle; 5-Filter assembly; 51-Filter outer frame; 511-Cleaning component; 52-Filter screen; 53-Rotator; 54-Driven wheel. Detailed Implementation

[0052] The preferred embodiments of the present invention will now be described in detail with reference to the accompanying drawings, which form part of the present invention and are used together with the invention to illustrate the principles of the invention.

[0053] Example 1

[0054] This embodiment provides an engine attitude trajectory control mechanism, such as Figures 1-2 As shown, it includes a housing 2, a control component 3, and a nozzle 4. The nozzle 4 is connected to the housing 2, and the housing 2 is connected to the gas passage 1. The control component 3 is located inside the housing 2 and is used to control the area of ​​the throat of the nozzle 4, thereby achieving continuous adjustment of the thrust of the aircraft through the linear change of the throat area of ​​the nozzle 4.

[0055] like Figure 2As shown, the control component 3 includes a servo motor 31, a drive gear 32, a rack 33, a valve stem 34, and a needle valve 35. The servo motor 31 is connected to the drive gear 32, the drive gear 32 is meshed with the rack 33, the rack 33 is connected to the valve stem 34, and the valve stem 34 is connected to the needle valve 35. A moving ring 341 is provided on the valve stem 34, and the moving ring 341 is connected to the housing 2, allowing the valve stem 34 to move within the moving ring 341. The rotation of the servo motor 31 drives the drive gear 32 to rotate, thereby causing the rack 33 to drive the valve stem 34 to move. The position of the needle valve 35 is matched with the throat of the nozzle 4, and the needle valve 35 can move with the valve stem 34, thereby changing the air intake area of ​​the throat of the nozzle 4.

[0056] When it is necessary to reduce the throat area of ​​the nozzle 4, the servo motor 31 is controlled to rotate forward, so that the rack 33 drives the valve stem 34 to move closer to the nozzle 4 under the rotation of the drive gear 32, so that the needle valve 35 blocks the throat of the nozzle 4. As the needle valve 35 moves closer to the nozzle 4, the needle valve 35 linearly reduces the contact area between the throat of the nozzle 4 and the gas.

[0057] When it is necessary to increase the throat area of ​​the nozzle 4, the servo motor 31 is reversed, causing the rack 33 to drive the valve stem 34 to move away from the nozzle 4 under the rotation of the drive gear 32. As the needle valve 35 moves away from the nozzle 4, the needle valve 35 linearly increases the contact area between the throat of the nozzle 4 and the gas.

[0058] In summary, by using the servo motor 31 to drive the drive gear 32 to move the needle valve 35 closer to or further away from the nozzle 4, the sealing area of ​​the needle valve 35 at the throat of the nozzle 4 is linearly changed, thereby achieving continuous adjustment of the thrust.

[0059] Example 2

[0060] This embodiment provides an engine attitude trajectory control mechanism, such as Figure 3 As shown, the difference from Embodiment 1 is that the control component 3 does not include rack 33, valve stem 34 and needle valve 35. The control component 3 includes servo motor 31, drive gear 32, connecting rod 36, fixing rod 37 and sealing component 38. The control component 3 is used to linearly change the sealing area of ​​the throat of nozzle 4, thereby realizing continuous adjustment of the thrust of the aircraft.

[0061] The servo motor 31 is connected to the drive gear 32, and the servo motor 31 can control the rotation of the drive gear 32. A support rod 321 is provided on the drive gear 32, and the support rod 321 is connected to the connecting rod 36. The connecting rod 36 is hinged to the housing 2 and meshes with the sealing member 38.

[0062] Furthermore, the connecting rod 36 includes a swing section 361 and a connecting groove 362. The swing section 361 is connected to the connecting groove 362, and the position where the swing section 361 and the connecting groove 362 are connected is hinged to the housing 2. The swing section 361 is engaged with the sealing member 38 to drive the sealing member 38 to move, thereby changing the contact area between the sealing member 38 and the throat of the nozzle 4, so that the throat area of ​​the nozzle 4 changes linearly. The connecting groove 362 is connected to the support rod 321, so that the support rod 321 moves within the connecting groove 362 as the drive gear 32 rotates, thereby driving the connecting rod 36 to swing with the rotation of the drive gear 32, so that the swing section 361 drives the sealing member 38 to move.

[0063] Furthermore, the end of the swing section 361 connected to the sealing member 38 is set to be arc-shaped, and the swing section 361 and the sealing member 38 are engaged and connected.

[0064] The fixing rod 37 is installed inside the housing 2, and the sealing member 38 is connected to the fixing rod 37 and can move along the fixing rod 37 under the drive of the connecting rod 36.

[0065] Furthermore, the sealing component 38 includes a sealing plate 381, a sleeve 382, ​​and an engaging block 383. The engaging block 383 is connected to the sealing plate 381 through the sleeve 382. The sleeve 382 is connected to the fixed rod 37 and can move along the fixed rod 37. The position of the sealing plate 381 matches the position of the throat of the nozzle 4 to seal the throat of the nozzle 4. The engaging block 383 is engaged with the swing section 361. The swing section 361 can drive the engaging block 383 to move up and down along the fixed rod 37, thereby causing the sealing area of ​​the sealing plate 381 on the throat of the nozzle 4 to change linearly, so as to realize the continuous adjustable thrust of the nozzle 4.

[0066] It is understandable that when it is necessary to change the thrust of the nozzle 4, the servo motor 31 controls the drive gear 32 to rotate, thereby causing the connecting rod 36 to swing, which in turn drives the sealing plate 381 to move along the fixed rod 37, thereby causing the sealing area of ​​the nozzle 4 throat to change linearly, so as to realize the continuous adjustment of the thrust of the nozzle 4.

[0067] Example 3

[0068] This embodiment provides an engine attitude trajectory control mechanism, such as Figures 4-5 As shown, the difference from Embodiment 1 and Embodiment 2 is that a filter assembly 5 is also included, which is used to filter the gas entering the housing 2 through the gas passage 1 to prevent solid impurities in the gas from clogging the nozzle 4.

[0069] like Figure 5As shown, the filter assembly 5 includes a filter frame 51, a filter screen 52, a rotating wheel 53, and a driven wheel 54. One end of the filter frame 51 is connected to the gas passage 1, and the other end is connected to the housing 2. The rotating wheel 53 is installed inside the filter frame 51. The two sides of the rotating wheel 53 are connected to the driven wheel 54 through connecting rods. The driven wheel 54 can rotate with the rotating wheel 53. The driven wheel 54 is connected to the filter frame 51 through a bearing seat. The driven wheel 54 is connected to the filter screen 52, so that the filter screen 52 rolls with the rotation of the driven wheel 54. The position of the filter screen 52 is matched with the gas passage 1 to filter the gas entering the filter frame 51 from the gas passage 1.

[0070] Preferably, the rotor 53 is a pneumatic wheel. The gas entering the filter frame 51 can blow the pneumatic wheel to rotate, which in turn drives the driven wheel 54 to rotate, causing the filter screen 52 to roll. Thus, the filter screen 52 can roll automatically without additional power supply, preventing solid impurities in the gas from clogging the filter screen 52 and affecting the filtration efficiency.

[0071] For example, the wheel 53 can also be configured to rotate under the control of a motor.

[0072] Preferably, a plurality of cleaning components 511 are provided inside the filter frame 51. The cleaning components 511 are positioned to cooperate with the filter screen 52 and are used to clean solid impurities deposited on the filter screen 52.

[0073] For example, cleaning component 511 is a scraper or brush head.

[0074] Example 4

[0075] This embodiment provides a nozzle thrust control method, which uses the engine attitude trajectory control mechanism described in any one of Embodiments 1 to 3, and includes the following steps:

[0076] S1: Determine the flight target and plan the flight route.

[0077] Specifically, the flight target of the aircraft is determined, thereby planning the flight route and determining the flight path of the aircraft.

[0078] S2: Determine the ignition time and required thrust of the attitude control engine.

[0079] Furthermore, step S2 specifically includes: step S21: determining the attitude control engine that needs to be activated;

[0080] Step S22: Determine the thrust of nozzle 4.

[0081] Specifically, in step S21, the attitude control engine that needs to be activated is determined based on the flight path of the aircraft, and the engine activation time is determined, thereby controlling the flight attitude of the aircraft.

[0082] Specifically, in step S22, the thrust required by the nozzle 4 is determined based on the flight path and attitude of the aircraft.

[0083] S3: Adjust the throat area of ​​nozzle 4.

[0084] Furthermore, step S3 specifically includes:

[0085] S31: Determine the throat area of ​​nozzle 4 according to the required thrust;

[0086] S32: Start servo motor 31.

[0087] Specifically, in step S32, the servo motor 31 is controlled to rotate the drive gear 32, thereby changing the sealing area of ​​the throat of the nozzle 4 so that the throat area of ​​the nozzle 4 is adapted to the thrust required by the nozzle 4.

[0088] For example, the needle valve 35 is moved closer to or further away from the nozzle 4 by the servo motor 31 driving the drive gear 32, thereby changing the sealing area of ​​the needle valve 35 on the throat of the nozzle 4.

[0089] For example, the servo motor 31 controls the drive gear 32 to rotate, causing the connecting rod 36 to swing, which in turn drives the sealing plate 381 to move along the fixed rod 37, thereby changing the sealing area of ​​the throat of the nozzle 4.

[0090] The servo motor 31 drives the drive gear 32 to rotate, which can move the needle valve 35 or the sealing plate 381, thereby linearly changing the area of ​​the throat of the nozzle 4, and thus changing the thrust of the nozzle 4. This allows for precise control of the thrust of the nozzle 4, ensuring the flight path and attitude of the aircraft and improving the flight accuracy of the aircraft.

[0091] S4: Start the attitude control engine.

[0092] Specifically, the attitude control engine is activated at the time determined in step S21 to adjust the attitude of the aircraft, so that the aircraft travels along the predetermined path.

[0093] By adjusting the throat area of ​​nozzle 4, the nozzle 4 can reach the preset thrust after the attitude control engine is started, thereby adjusting the flight attitude of the aircraft and improving the accuracy of the aircraft's flight.

[0094] S5: Corrects flight attitude.

[0095] Specifically, the aircraft is equipped with sensors and a control system. The sensors monitor changes in the aircraft's attitude and trajectory in real time and feed the new status data back to the control system. When there is a deviation between the actual state and the planned route, the throat area of ​​the nozzle 4 is adjusted by the servo motor 31 to correct the flight attitude.

[0096] The above description is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any changes or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in the present invention should be included within the scope of protection of the present invention.

Claims

1. An engine attitude control mechanism, characterized in that, It includes a gas passage (1), a housing (2), a control component (3) and a nozzle (4). The gas passage (1) and the nozzle (4) are connected to the housing (2). The control component (3) is disposed inside the housing (2) and is used to control the area of ​​the throat of the nozzle (4).

2. The engine attitude trajectory control mechanism according to claim 1, characterized in that, The control component (3) includes a servo motor (31) and a drive gear (32), wherein the servo motor (31) is connected to the drive gear (32).

3. The engine attitude trajectory control mechanism according to claim 2, characterized in that, The control component (3) further includes a rack (33) that meshes with the drive gear (32).

4. The engine attitude trajectory control mechanism according to claim 3, characterized in that, The control component (3) further includes a valve stem (34) and a needle valve (35), wherein the rack (33) is connected to the valve stem (34) and the valve stem (34) is connected to the needle valve (35).

5. The engine attitude trajectory control mechanism according to claim 4, characterized in that, A movable ring (341) is provided on the valve stem (34), the movable ring (341) is connected to the housing (2), and the valve stem (34) can move within the movable ring (341).

6. The engine attitude trajectory control mechanism according to claim 2, characterized in that, The control component (3) also includes a connecting rod (36), a fixing rod (37), and a sealing element (38).

7. The engine attitude trajectory control mechanism according to claim 6, characterized in that, A support rod (321) is provided on the drive gear (32), and the support rod (321) is connected to the connecting rod (36).

8. The engine attitude trajectory control mechanism according to claim 7, characterized in that, The connecting rod (36) is hinged to the housing (2) and the connecting rod (36) is connected to the sealing member (38).

9. The engine attitude trajectory control mechanism according to claim 8, characterized in that, The fixing rod (37) is disposed inside the housing (2), and the sealing member (38) is connected to the fixing rod (37) and can move along the fixing rod (37) under the drive of the connecting rod (36).

10. A nozzle thrust control method, characterized in that, The thrust control of the nozzle (4) is performed using the engine attitude trajectory control mechanism described in any one of claims 1-9.

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