Gas surface connecting structure and method for unlocking and separating gas surface of aircraft

Abstract

The application provides a gas rudder connecting structure and a method for unlocking and separating a gas rudder of an aircraft. The gas rudder connecting structure comprises a gas rudder body, a support, an elastic member and a transmission shaft. The gas rudder body is provided with a clamping tooth structure and a first boss structure. The support is provided with a clamping groove structure and a central accommodating space. One end of the transmission shaft is connected with a second boss structure. The other end of the transmission shaft is used for connecting an external driving motor. The gas rudder connecting structure has an initial state and an unlocking state. The gas rudder can be separated by the cooperation of the clamping groove structure and the clamping tooth structure, the rotation of the gas rudder and the elastic force of the elastic member. The application has a simple structure and does not use any pyrotechnic or ablation technology. The complicated pyrotechnic circuit is not needed, and the rotation time and speed of the transmission shaft can be controlled to accurately control the separation time of the gas rudder body.

Description

Technical Field

[0001] This invention relates to the field of aircraft structural design, specifically to a gas turbine control surface connection structure and a method for unlocking and separating aircraft gas turbine control surfaces. More particularly, it relates to a gas turbine control surface connection structure and a method for autonomous unlocking and separating aircraft gas turbine control surfaces. Background Technology

[0002] Due to the requirements of certain special missions, aircraft need to complete large-angle rotations of the missile's attitude angle at relatively low speeds. Since aerodynamic control is less efficient at low speeds, thrust vectoring control is required to achieve this action, and gas-propelled rudder technology is one such thrust vectoring control technology.

[0003] However, the gas control surface can affect the engine thrust performance. Therefore, after the aircraft completes its maneuvering mission, the gas control surface is often separated from the aircraft through compartment separation or ablation technology to ensure the smooth flow of engine gas.

[0004] Among these, the compartment separation schemes mostly employ explosive bolts, which are pyrotechnic devices, making the overall technology complex and requiring additional ignition circuitry and installation space. Furthermore, the ablation technology for control surfaces cannot precisely control the time it takes for the control surfaces to complete ablation.

[0005] Therefore, there is currently a lack of a simple and reliable unlocking and separation method.

[0006] Patent document CN 109795720 A discloses a design method for the detonation control of a pyrotechnic device for spacecraft segment separation, including the steps of: a. designing a detonation control circuit for the pyrotechnic device for spacecraft segment separation; b. designing a redundant control circuit based on the control circuit in step a. However, this scheme still uses the pyrotechnic device detonation method to achieve segment separation, and still suffers from the drawback of complex ignition circuit design, requiring separate design of the ignition circuit. Summary of the Invention

[0007] To address the shortcomings of existing technologies, the purpose of this invention is to provide a gas-fuel control surface connection structure and a method for unlocking and separating the gas-fuel control surfaces of an aircraft.

[0008] According to the present invention, a gas-fired control surface connection structure includes a gas-fired control surface body, a support, an elastic element, and a drive shaft.

[0009] The gas-powered control surface body is provided with a toothed structure and a first boss structure; the first boss structure is located below the toothed structure.

[0010] The support is provided with a slot structure and a central receiving space, the slot structure being above the central receiving space; one end of the drive shaft is connected to a second boss structure; the other end of the drive shaft is used to connect to an external drive motor.

[0011] The gas-powered rudder surface connection structure has an initial state and an unlocked state;

[0012] In the initial state, the end of the gas turbine control surface body is fitted into the slot structure of the support and the central receiving space through a toothed structure; one end of the drive shaft is located in the central receiving space, and one end of the drive shaft abuts against the first boss structure through a second boss structure; the other end of the drive shaft extends through the gas turbine control surface body to the outside of the gas turbine control surface body; the elastic element is installed in the central receiving space, one end of the elastic element abuts against the toothed structure, the other end of the elastic element abuts against the support, and the elastic element is in a compressed state;

[0013] When the initial state is switched to the unlocked state, the drive shaft drives the gas rudder body to rotate, and the locking tooth structure disengages from the locking slot structure under the action of the elastic element.

[0014] Preferably, the drive shaft is integrally connected to the first boss structure, and the first boss structure and the second boss structure are matched with each other.

[0015] Preferably, the central accommodating space includes a first accommodating cavity, a second accommodating cavity, and a third accommodating cavity;

[0016] The card slot structure includes a slot structure and a limiting block;

[0017] The first receiving cavity, the second receiving cavity, the third receiving cavity, and the groove structure are connected sequentially from bottom to top. The first receiving cavity is located at one end of the support, and the groove structure is located at the other end of the support.

[0018] The radii of the first receiving cavity, the second receiving cavity, the third receiving cavity, and the groove structure increase sequentially.

[0019] The number of limiting blocks is multiple, and the multiple limiting blocks are symmetrically arranged at the top of the groove structure. The inner diameter of the limiting blocks is smaller than the inner diameter of the groove structure.

[0020] Preferably, the elastic element is a spring, which is installed in the third receiving cavity and sleeved on the outside of the first boss structure.

[0021] Preferably, the support is securely mounted on the external aircraft.

[0022] Preferably, the tooth structure includes a connecting platform and a tooth portion;

[0023] The number of the locking teeth matches the number of the limiting blocks, and the multiple locking teeth are arranged circumferentially along the connecting platform;

[0024] The outer diameters of the first boss structure, the connecting platform, and the locking tooth portion increase sequentially.

[0025] The outer diameter of the locking teeth is smaller than the inner diameter of the groove structure but larger than the inner diameter of the limiting block.

[0026] According to the present invention, a method for unlocking and separating the gas control surface of an aircraft is provided, which employs the aforementioned gas control surface connection structure.

[0027] It also includes the following steps:

[0028] S1. In the initial state, the end of the gas control surface body is embedded in the slot structure of the support and the central receiving space through the tooth structure, so as to fix the gas control surface spanwise and enable it to work normally.

[0029] S2. An external drive motor drives the transmission shaft to cause the gas rudder body to deflect by a preset angle;

[0030] S3. Under the action of the elastic element, the tooth structure disengages from the slot structure, completing the separation of the gas rudder body from the support.

[0031] Preferably, in step S1,

[0032] The retaining teeth in the gas turbine control surface are blocked by the limiting block in the support, so that the gas turbine control surface and the support are connected to each other.

[0033] Preferably, in step S2,

[0034] As the angle of the gas turbine control surface body deflects, the locking teeth deflect out of the position of the limit block. At this time, the locking teeth are no longer blocked by the limit block, and the unlocking step is completed.

[0035] Preferably, in step S3, under the elastic force of the elastic element, the elastic element drives the locking tooth part to move upward, so that the gas rudder body as a whole detaches from the support, thus completing the separation of the gas rudder body from the support.

[0036] Compared with the prior art, the present invention has the following beneficial effects:

[0037] 1. This invention achieves separation of the gas rudder by using a combination of a slot structure and a tooth structure, combined with the rotation of the gas rudder and the elastic force of the elastic element. This invention has a simple structure and does not employ any pyrotechnic or ablation techniques. It does not require the design of complex pyrotechnic circuits and can accurately control the separation time of the gas rudder body by controlling the rotation time and speed of the drive shaft.

[0038] 2. The separation method of the present invention is simple to operate and has simple steps. It only requires rotating the drive shaft to achieve the separation of the gas rudder surface. Attached Figure Description

[0039] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0040] Figure 1 This is a cross-sectional structural diagram of the present invention;

[0041] Figure 2 for Figure 1 A schematic diagram of the three-dimensional structure;

[0042] Figure 3 This is a schematic diagram of the structure of the gas turbine control surface.

[0043] Figure 4 This is a structural schematic diagram of the support;

[0044] Figure 5 This is a schematic diagram of the drive shaft structure;

[0045] Figure 6 This is a schematic diagram of the gas-fueled rudder surface connection structure during step S1.

[0046] Figure 7 This is a schematic diagram of the gas-fueled rudder surface connection structure during step S2;

[0047] Figure 8 This is a schematic diagram of the gas rudder surface connection structure during step S3.

[0048] The diagram shows:

[0049] Detailed Implementation

[0050] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0051] This invention provides a gas-fired control surface connection structure, such as Figure 1-5 As shown, it includes a gas control surface body 1, a support 2, an elastic element 3, and a drive shaft 4; in a preferred embodiment, the support 2 is fastened to an external aircraft.

[0052] The gas-powered rudder body 1 is provided with a tooth structure 11 and a first boss structure 12; the first boss structure 12 is located below the tooth structure 11.

[0053] The support 2 is provided with a slot structure and a central receiving space, the slot structure being above the central receiving space; one end of the drive shaft 4 is connected to a second boss structure 41; the other end of the drive shaft 4 is used to connect to an external drive motor.

[0054] The gas-powered rudder surface connection structure has an initial state and an unlocked state;

[0055] In the initial state, the gas-powered control surface is in normal working condition. The end of the gas-powered control surface body 1 is embedded in the slot structure and central receiving space of the support 2 through a toothed structure. One end of the drive shaft 4 is located in the central receiving space, and one end of the drive shaft 4 abuts against the first boss structure 12 through the second boss structure 41. The other end of the drive shaft 4 extends through the gas-powered control surface body 1 to the outside of the gas-powered control surface body 1 and is connected to an external drive motor. The elastic element 3 is installed in the central receiving space. One end of the elastic element 3 abuts against the toothed structure 11, and the other end of the elastic element 3 abuts against the support 2 and is sleeved on the outside of the first boss structure 12. The elastic element 3 is in a compressed state.

[0056] When the initial state is switched to the unlocked state, the drive shaft 4 drives the gas rudder body 1 to rotate, and the tooth structure 11 disengages from the slot structure under the action of the elastic member 3.

[0057] The drive shaft 4 is integrally connected to the second boss structure 41, and the first boss structure 12 and the second boss structure 41 are matched with each other. In a preferred embodiment, the first boss structure 12 includes a first boss base 121 and a first protrusion structure 122 integrally connected to each other, and the second boss structure 41 includes a second boss base 411 and a second protrusion structure 412 integrally connected to each other. The first boss base 121 and the second boss base 411 have the same radius. In the initial state, the first protrusion structure 122 and the second protrusion structure 412 are matched with each other. Specifically, the projection of the first protrusion structure 122 and the projection of the second protrusion structure are both arc-shaped, and the two arcs can be combined to form a circle with the same radius as the first boss base 121.

[0058] The central accommodating space includes a first accommodating cavity 21, a second accommodating cavity 22, and a third accommodating cavity 23;

[0059] The slot structure includes a slot structure 24 and a limiting block 25; the first receiving cavity 21, the second receiving cavity 22, the third receiving cavity 23, and the slot structure 24 are connected sequentially from bottom to top, the first receiving cavity 21 is located at one end of the support 2, and the slot structure 24 is located at the other end of the support 2; the radii of the first receiving cavity 21, the second receiving cavity 22, the third receiving cavity 23, and the slot structure 24 increase sequentially; in a preferred embodiment, the limiting block 25 is integrally connected to the support 2.

[0060] In a preferred embodiment, regarding the support 2 alone, the first receiving cavity 21 is a through hole structure at the bottom end of the support 2, and the second receiving cavity 22 communicates with the outside of the support 2 through the first receiving cavity 21; the groove structure 24 is a through hole structure at the top of the support 2, and the third receiving cavity 23 communicates with the outside of the support 2 through the groove structure 24.

[0061] The number of limiting blocks 25 is multiple, and the multiple limiting blocks 25 are symmetrically arranged at the top of the groove structure 24. The inner diameter of the limiting blocks 25 is smaller than the inner diameter of the groove structure 24. Preferably, the number of limiting blocks 25 is two.

[0062] In a preferred embodiment, the elastic element 3 is a spring, which is installed within the third receiving cavity 23.

[0063] The locking structure 11 includes a connecting platform 111 and locking teeth 112; the number of locking teeth 112 matches the number of limiting blocks 25, and multiple locking teeth 112 are arranged circumferentially along the connecting platform 111; the outer diameters of the first boss structure 12, the connecting platform 111, and the locking teeth 112 increase sequentially; the outer diameter of the locking teeth 112 is smaller than the inner diameter of the groove structure 24 and larger than the inner diameter of the limiting block 25.

[0064] Specifically, in the initial state, one end of the drive shaft 4 is located in the first receiving cavity 21, the second boss structure 41 and the first protrusion structure 122 are located in the second receiving cavity 22, the first boss base 121 and the elastic member 3 are located in the third receiving cavity 23, and the locking tooth structure 11 is located in the groove structure 24.

[0065] This invention also provides a method for unlocking and separating the gas control surfaces of an aircraft, such as... Figure 6-8 As shown, the gas-powered rudder surface connection structure is adopted;

[0066] The process also includes the following steps: S1. In the initial state, the end of the gas rudder body 1 is embedded in the slot structure and central receiving space of the support 2 through the tooth structure 11, thereby fixing the gas rudder spanwise and enabling it to work normally. In step S1, the tooth portion 112 in the gas rudder body 1 is blocked by the limiting block 25 in the support 2, so that the gas rudder body 1 and the support 2 are connected to each other.

[0067] S2. An external drive motor drives the transmission shaft 4 to deflect the gas-powered rudder body 1 by a preset angle. In step S2, as the gas-powered rudder body 1 deflects, the locking tooth 112 deflects out of the position of the limiting block 25. At this time, the locking tooth 112 is not blocked by the limiting block 25, completing the unlocking step. In a preferred embodiment, the preset angle is a relatively large angle, preferably 90°.

[0068] S3. Under the action of the elastic element 3, the locking tooth structure 11 disengages from the locking slot structure, completing the separation of the gas rudder body 1 from the support 2. In step S3, under the elastic force of the elastic element 3, the elastic element 3 drives the locking tooth part 112 to move upward, causing the gas rudder body 1 to detach from the support 2 as a whole, thus completing the separation of the gas rudder body 1 from the support 2.

[0069] The working principle and process of this invention are as follows:

[0070] like Figure 1 As shown, in its initial state, the gas rudder body 1 achieves spanwise constraint through the contact between the toothed structure 11 and the slotted structure on the support 2. The gas rudder body 1 and the elastic element 3 achieve transmission by constraining their relative rotational degrees of freedom through the engagement of the boss. Therefore, the gas rudder can deflect normally under command. After the gas rudder completes its task, the gas rudder body 1 deflects at a certain angle under the action of an external motor and transmission shaft 4, causing the toothed part 112 of the gas rudder body 1 to rotate out of the range of the upper limit block 25 of the support 2, thus releasing the spanwise constraint and unlocking. The gas rudder body 1 pops out under the action of the compression spring, and the rotational constraint between the gas rudder body 1 and the second boss structure 41 is automatically released as the gas rudder body 1 separates from the second boss structure 41. At this point, the gas rudder body 1 achieves rudder-spring separation.

[0071] This invention uses a toothed structure 11 and a slotted structure to constrain the spanwise degree of freedom of the gas turbine control surface. Unlocking is achieved by deflecting the gas turbine control surface to a preset angle. This invention, through a simple toothed and slotted structure, constrains the spanwise degree of freedom of the gas turbine control surface, allowing for normal angle deflection to complete the designated task. The method is simple and reliable.

[0072] The present invention can also control the rotation angle of the gas control surface body 1 by controlling an external motor. By setting the rotation angle to a larger angle, the gas control surface can be unlocked and separated from the aircraft structure. This method is simple, controllable, and reliable.

[0073] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0074] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A gas-powered rudder surface connection structure, characterized in that, It includes the gas-powered steering surface body (1), support (2), elastic element (3), and drive shaft (4); The gas-powered rudder body (1) is provided with a tooth structure (11) and a first boss structure (12); the first boss structure (12) is located below the tooth structure (11); The support (2) is provided with a slot structure and a central receiving space, the slot structure being above the central receiving space; one end of the drive shaft (4) is connected to a second boss structure (41); the other end of the drive shaft (4) is used to connect to an external drive motor; The gas-powered rudder surface connection structure has an initial state and an unlocked state; In the initial state, the end of the gas rudder body (1) is embedded in the slot structure and central receiving space of the support (2) through the tooth structure (11); one end of the drive shaft (4) is located in the central receiving space, and one end of the drive shaft (4) abuts against the first boss structure (12) through the second boss structure (41); the other end of the drive shaft (4) extends through the gas rudder body (1) to the outside of the gas rudder body (1); the elastic element (3) is installed in the central receiving space, one end of the elastic element (3) abuts against the tooth structure (11), the other end of the elastic element (3) abuts against the support (2), and the elastic element (3) is in a compressed state; When the initial state is switched to the unlocked state, the drive shaft (4) drives the gas rudder body (1) to rotate, and the tooth structure (11) disengages from the slot structure under the action of the elastic element (3).

2. The gas-powered rudder surface connection structure according to claim 1, characterized in that, The drive shaft (4) is integrally connected to the second boss structure (41), and the first boss structure (12) and the second boss structure (41) are matched with each other.

3. The gas-powered rudder surface connection structure according to claim 1, characterized in that, The central accommodating space includes a first accommodating cavity (21), a second accommodating cavity (22), and a third accommodating cavity (23). The card slot structure includes a slot structure (24) and a limiting block (25); The first receiving cavity (21), the second receiving cavity (22), the third receiving cavity (23), and the groove structure (24) are connected sequentially from bottom to top. The first receiving cavity (21) is located at one end of the support (2), and the groove structure (24) is located at the other end of the support (2). The radii of the first receiving cavity (21), the second receiving cavity (22), the third receiving cavity (23), and the groove structure (24) increase sequentially; The number of the limiting blocks (25) is multiple, and the multiple limiting blocks (25) are symmetrically arranged at the top of the groove structure (24). The inner diameter of the limiting blocks (25) is smaller than the inner diameter of the groove structure (24).

4. The gas-powered rudder surface connection structure according to claim 3, characterized in that, The elastic element (3) is a spring, which is installed in the third receiving cavity (23) and sleeved on the outside of the first boss structure (12).

5. The gas-powered rudder surface connection structure according to claim 1, characterized in that, The support (2) is securely installed on the external aircraft.

6. The gas-powered rudder surface connection structure according to claim 3, characterized in that, The locking tooth structure (11) includes a connecting platform (111) and a locking tooth part (112). The number of the locking teeth (112) matches the number of the limiting blocks (25), and the multiple locking teeth (112) are arranged circumferentially along the connecting platform (111); The outer diameters of the first boss structure (12), the connecting platform (111), and the locking tooth part (112) increase sequentially; The outer diameter of the toothed part (112) is smaller than the inner diameter of the groove structure (24) and larger than the inner diameter of the limiting block (25).

7. A method for unlocking and separating the gas control surfaces of an aircraft, characterized in that, The gas-fired control surface connection structure as described in any one of claims 1 to 6 is adopted; It also includes the following steps: S1. In the initial state, the end of the gas rudder body (1) is embedded in the slot structure and central accommodating space of the support (2) through the tooth structure (11) to achieve the spanwise fixation of the gas rudder so that it can work normally. S2, The external drive motor drives the transmission shaft (4) to drive the gas rudder body (1) to deflect by a preset angle; S3. Under the action of the elastic element (3), the tooth structure (11) disengages from the slot structure, completing the separation of the gas rudder body (1) from the support (2).

8. The method for unlocking and separating the gas control surfaces of an aircraft according to claim 7, characterized in that, In step S1, The locking teeth (112) in the gas rudder body (1) are blocked by the limiting block (25) in the support (2), so that the gas rudder body (1) and the support (2) are connected to each other.

9. The method for unlocking and separating the gas control surfaces of an aircraft according to claim 7, characterized in that, In step S2, As the angle of the gas rudder body (1) deflects, the locking tooth (112) deflects out of the position of the limiting block (25). At this time, the locking tooth (112) is not blocked by the limiting block (25), and the unlocking step is completed.

10. The method for unlocking and separating the gas control surfaces of an aircraft according to claim 8, characterized in that, In step S3, under the elastic force of the elastic element (3), the elastic element (3) drives the toothed part (112) to move upward, so that the gas rudder body (1) is separated from the support (2) as a whole, thus completing the separation of the gas rudder body (1) from the support (2).

Images