Pressing belt pressing force loading device of spacecraft unfolding mechanism

Abstract

The invention relates to a pressing force loading device for a pressing belt of a spacecraft unfolding mechanism, which is characterized in that the pressing belt is ingeniously fixed on the side edge of the spacecraft unfolding mechanism, and the highly accurate control of the pressing belt is realized by combining the fixation of a plate spring and the adjustment of a pull wire. Specifically, one end of the plate spring is connected with the pressing belt, the other end of the plate spring is fixed to the mechanism, and the correct position of the pressing belt can be effectively kept through the device. According to the invention, through the combination of the stay wire and the plate spring and the simple and convenient stay wire tensioning mechanism, the rapid and accurate pressing of the pressing belt is realized. And meanwhile, the pull wire is released by adopting the breaking device during releasing, and the mechanism is released under the action of the plate spring, so that the safety and the controllability of the releasing process are ensured.

Description

Technical Field

[0001] The invention relates to the field of aerospace technology, and in particular to a compression force loading device for a compression belt of a spacecraft deployment mechanism. Background Art

[0002] With the continuous development of aerospace technology, the deployment mechanism of spacecraft plays a vital role in mission execution. The deployment mechanism usually contains multiple key components, among which the compression belt is a key component, which is used to compress the structural parts during the deployment of the spacecraft to ensure the correct position and reliability of each component. In order to effectively realize the function of the deployment mechanism, the compression force of the compression belt must be accurately controlled and adjusted.

[0003] At present, the existing compression belt loading devices have some technical bottlenecks to a certain extent. For example, in the prior art, the compression belt loading device of the deployment mechanism has the problems of complex operation and difficult adjustment, which makes the precise control of the clamping force a challenge. At the same time, the controllability of the release mechanism is also an important issue. It is difficult for traditional loading devices to achieve precise adjustment of the clamping force of the compression belt, which may lead to problems such as inaccurate structural displacement and component position deviation during the deployment of the spacecraft, thereby affecting the normal operation of the spacecraft. Some devices are prone to wear and failure during long-term use, reducing the reliability and life of the entire deployment mechanism. The loading device may be affected by external environmental factors, resulting in changes in the clamping force, thereby affecting the stability of the spacecraft. In addition, some loading devices may not be able to flexibly adapt to different deployment mechanisms, which limits their adaptability in different application scenarios. Summary of the invention

[0004] The technical problem solved by the present invention is: to overcome the deficiencies of the prior art, the present invention provides a compression belt pressing force loading device for a spacecraft deployment mechanism, which realizes high-precision control of the compression belt pressing force and ensures the reliability and stability of the deployment mechanism.

[0005] The technical solution of the present invention is: a compression belt pressing force loading device of a spacecraft deployment mechanism, the device comprising a mounting base, a compression lever, a compression belt, a compression belt cover plate, a guide rope ring, a pull rope tensioning seat, a release leaf spring, and a loading device;

[0006] A mounting base, used for fixed installation on the surface of the spacecraft, providing support for the pressing force loading device, and serving as a bottom limit support for the deployment mechanism;

[0007] The clamping lever is a two-section structure. One section is the clamping end, which is used to connect with the lower end of the clamping belt to clamp the clamping belt. The other section is the loading end, which is tensioned by a pull rope to achieve precise adjustment of the clamping belt. The middle part connecting the two sections is connected to the legs of the mounting base through a rotating shaft.

[0008] The pull rope tensioning seat is fixedly installed on the surface of the space vehicle;

[0009] A rope guide ring is fixed on the rope tensioning seat, and the rope guide ring is located above the loading end of the clamping lever;

[0010] There are two compression belt cover plates, which are clamped on both sides of one end of the compression belt. The compression belt and the compression belt cover plates clamped on both sides are installed on the unfolding mechanism through screws; the other end of the compression belt is connected with the compression end of the compression lever; one end of the pull rope is fixed on the loading end of the compression lever, and the other end passes through the guide rope ring and is turned to connect to the loading device;

[0011] One end of the release leaf spring is fixedly mounted on the base, and the other end is connected to the loading end of the clamping lever. In the initial state, the release leaf spring is in a stretched state, generating a downward preload force.

[0012] Preferably, the pressing end of the pressing lever and the pressing belt are connected by a hook-type structure, the hook of the pressing end of the pressing lever is downward, and the hook of the pressing belt is upward.

[0013] Preferably, in the loading state, the loading end of the pressing lever is pulled upward by the pull rope, and the pressing end of the pressing lever moves downward to press the pressing belt;

[0014] In the released state, the tension of the pull rope on the loading end of the clamping lever contacts the leaf spring, which generates downward tension, and the clamping end of the clamping lever releases the pressure on the clamping belt.

[0015] Preferably, the compression belt is in a curled state when not compressed.

[0016] Preferably, the hole on the compression belt cover plate for passing the screw is an oblong hole.

[0017] Preferably, the rope tensioning seat is provided with an oblong hole for pre-tightening the rope.

[0018] Preferably, the pull rope is made of steel wire rope.

[0019] Preferably, the material of the pressing lever is titanium alloy.

[0020] The beneficial effects of the present invention compared with the prior art are:

[0021] (1) Precise control and adjustable release: The present invention achieves precise control and adjustable release of the compression belt by introducing new design elements such as the tensioning seat and the release leaf spring. Compared with some loading devices in the prior art that are complicated to operate and difficult to adjust, the design of the present invention makes the control of the deployment mechanism more intuitive and flexible.

[0022] (2) Improved quality and adaptability: The present invention can effectively cope with the influence of external environmental factors through the cleverly designed loading device, and improve the stability of the deployment mechanism. At the same time, the adjustable loading device improves the adaptability in different deployment mechanisms and working conditions, making it more versatile.

[0023] (3) Ease of operation: The design of the loading device of the present invention takes into account the user's convenience of operation. Through the combination of the pull rope and the release leaf spring, the operation process is simpler, the usage threshold is lowered, and different operators can more easily perform loading and releasing operations.

[0024] (4) Compact and reliable structure: By adopting a design of fixing the clamping lever on the mounting base with bolts and properly installing structures such as the guide rope ring, the loading device of the present invention achieves a compact structure and reliable connection, thereby improving the stability and reliability of the entire system.

[0025] (5) Flexible adaptation to different scenarios: Since the design of the loading device of the present invention is more flexible, it can be adjusted through the pull rope tensioning seat to adapt to different working scenarios and the deployment mechanism of spacecraft, thereby improving the versatility and adaptability of the device. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 It is a schematic diagram of a compression force loading device of a compression belt according to an embodiment of the present invention. DETAILED DESCRIPTION

[0027] The present invention will be further described below in conjunction with the embodiments.

[0028] In order to improve the practicality of the entire loading device, the present invention aims to design a simple-to-operate compression belt pressure loading device for the deployment mechanism of a spacecraft, so that the loading of the compression belt and the release process of the deployment mechanism are more intuitive and controllable. By introducing advanced control technology and material engineering, the loading device can achieve high-precision control of the compression force of the compression belt, ensuring the reliability and stability of the deployment mechanism. At the same time, the loading device of the present invention is more durable, which can effectively extend the service life of the spacecraft and improve the performance level of the entire system.

[0029] like Figure 1 As shown, the device provided by the present invention includes a mounting base 1, a clamping lever 2, a clamping belt 3, a clamping belt cover plate 4, a guide rope ring 5, a pull rope tensioning seat 6, a release leaf spring 7, and a loading device; the clamping lever 2, the clamping belt 3, the clamping belt cover plate 4, the guide rope ring 5, the pull rope tensioning seat 6, the release leaf spring 7, and the loading device can be used on one side of the spacecraft deployment mechanism, and can also be used in pairs on both sides of the spacecraft deployment mechanism.

[0030] The mounting base 1 is used for fixed installation on the surface of the spacecraft, providing firm support for the clamping force loading device, and serving as a bottom limit support for the deployment mechanism, to ensure that the entire system can remain stable and firm when installed on the spacecraft.

[0031] The clamping lever 2 adopts a two-section structure, one section is the clamping end, which is used to connect with the lower end of the clamping belt to clamp the clamping belt 3, and the other section is the loading end, which is tensioned by a pull rope to achieve precise adjustment of the clamping belt; the middle part connecting the two sections is connected to the support leg of the mounting base 1 through a rotating shaft, which ensures that the appropriate clamping force can be flexibly adjusted and maintained under different working conditions.

[0032] The pull rope tensioning seat 6 is fixedly mounted on the surface of the spacecraft; the pull rope tensioning seat adjusts the compression lever by tensioning the pull rope, thereby adjusting the strength of the compression belt. The operator can adjust the entire loading device by a simple pull rope action.

[0033] The guide rope ring 5 is fixed on the rope tensioning seat 6, and the guide rope ring 5 is located above the loading end of the clamping lever 2; the clamping lever 2 is connected to the lower end of the clamping belt 3 to enhance the support for the deployment mechanism and improve the stability of the entire system.

[0034] There are two compression belt cover plates 4, which are located above the compression belt and clamped on both sides of one end of the compression belt to protect the compression belt from external interference and help fix the compression belt to ensure that it is not damaged during loading.

[0035] One end of the compression band and the compression band cover plate 4 clamped on both sides are fixed to the spacecraft deployment mechanism by screws to ensure that the connection meets the design requirements of the mechanism; the other end of the compression band is connected with the compression end of the compression lever 2 and is tightly fixed by the action of the compression lever; the design of the compression band enables it to provide reliable supporting force in the deployment mechanism and maintain the structural rigidity of the mechanism.

[0036] One end of the pull rope is fixed to the loading end of the pressing lever 2, and the other end passes through the guide rope ring 5 and is connected to the loading device;

[0037] The release leaf spring 7 has one end fixedly mounted on the base 1 and the other end connected to the loading end of the clamping lever 2. In the initial state, the release leaf spring 7 is in a stretched state to generate a downward preload. As part of the release mechanism, when the pull rope is disconnected, the release leaf spring releases the clamping lever, causing it to release the clamping belt and achieve safe release of the deployment mechanism.

[0038] Preferably, the clamping end of the clamping lever 2 and the clamping belt 3 are connected by a hook-type structure, with the hook of the clamping end of the clamping lever 2 facing downward and the hook of the clamping belt 3 facing upward.

[0039] Preferably, in the loading state, the loading end of the clamping lever 2 is pulled upward by the pull rope, and the clamping end of the clamping lever 2 moves downward to clamp the clamping belt 3;

[0040] In the released state, the tension of the pull rope on the loading end of the clamping lever 2 contacts, releasing the leaf spring 7 to generate a downward pulling force, and the clamping end of the clamping lever releases the pressure on the clamping belt.

[0041] Preferably, the compression belt 3 is in a curled state when not compressed.

[0042] Preferably, the holes on the compression belt cover plate 4 for passing the screws are oblong holes.

[0043] The rope tensioning seat 6 and the rope guide ring 5 are used to guide the direction of the rope;

[0044] Preferably, the rope tensioning seat 6 is provided with an oblong hole for pre-tightening the rope, and the rope tensioning degree can be adjusted by moving the installation position.

[0045] Preferably, the pull rope is made of steel wire rope.

[0046] Preferably, the material of the pressing lever is titanium alloy.

[0047] This design enables the loading device to adapt to different working conditions and ensures that the pressing force applied to the deployment mechanism is just right. Through this technical solution, the present invention can achieve stable and precise control of the deployment mechanism, while improving adaptability and ease of operation, solving a series of technical problems existing in traditional loading devices and providing an efficient and reliable solution for the deployment mechanism of spacecraft.

[0048] The following is the working process of the compression belt compression force loading device in the present invention, including the following steps:

[0049] Step 1: Fix the base, compression belt, compression belt cover, compression lever and other parts on the star body correctly.

[0050] Step 2: Connect the clamping lever: Connect the clamping lever to the lower end of the clamping belt to increase support for the deployment mechanism and enhance the stability of the entire system.

[0051] Step 3, tensioning the pull rope, through the pull rope tensioning seat, tensioning a section of the clamping lever. This step can adjust the strength of the clamping belt by operating the pull rope, so that it can provide appropriate clamping force in different situations.

[0052] Step 4: Maintaining the working state: In this stage, the loading device will maintain the compression state of the deployment mechanism and maintain the support force of the deployment mechanism. This helps to ensure that the deployment mechanism of the spacecraft can maintain the predetermined structural rigidity and stability.

[0053] Step 5: Release: When the deployment mechanism needs to be released, the pull cord is disconnected by operating the release leaf spring. Under the action of the release leaf spring, the compression lever releases the compression belt, thereby releasing the deployment mechanism. The deployment mechanism can thus be freely deployed or folded. Under the action of the release leaf spring, the compression lever releases the compression belt, thereby safely releasing the deployment mechanism.

[0054] The specific implementation of the present invention realizes precise control and adjustable release of the deployment mechanism of the spacecraft by reasonably configuring key components such as the compression belt 3, the compression lever 2, the pull rope tensioning seat 6, the guide rope ring 5, etc., and has high operability, stability and adaptability.

[0055] In summary, the present invention relates to a compression force loading device for a compression belt of a spacecraft deployment mechanism, the innovation of which is to achieve highly accurate control of the compression belt by cleverly fixing the compression belt to the side of the aircraft deployment mechanism, combined with the fixation of the leaf spring and the adjustment of the tension wire. Specifically, one end of the leaf spring is connected to the compression belt, and the other end is fixed to the mechanism, and this device can effectively maintain the correct position of the compression belt.

[0056] In the present invention, the tensioning belt is compressed quickly and accurately by combining the tensioning wire with the leaf spring and a simple tensioning wire tensioning mechanism. At the same time, the tensioning wire is released by the breaker during release, and the mechanism is released under the action of the leaf spring, thereby ensuring the safety and controllability of the release process.

[0057] In addition, the design of the present invention takes into account the stability and durability of the system, ensuring that it is not prone to wear and failure during long-term use. The entire loading device is easy to operate and efficient, and can be applied to various spacecraft deployment mechanisms, providing reliable structural support for spacecraft during deployment. Through the above innovations, the present invention not only improves the performance level of the system, but also demonstrates significant superiority in practical applications.

[0058] Combining the above advantages, the loading device of the present invention has significant innovative advantages in improving the performance and reliability of the deployment mechanism of spacecraft, and is expected to have a positive impact in the field of aerospace technology.

[0059] Although the present invention has been disclosed as above in the form of a preferred embodiment, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solution of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention.

Claims

1. A compression belt pressing force loading device for a spacecraft deployment mechanism, characterized in that It comprises a mounting base (1), a clamping lever (2), a clamping belt (3), a clamping belt cover plate (4), a guide rope ring (5), a pull rope tensioning seat (6), a release leaf spring (7), and a loading device; A mounting base (1) is used for fixedly mounting on the surface of a spacecraft, providing support for a pressing force loading device, and serving as a bottom limit support for a deployment mechanism; The clamping lever (2) is a two-section structure, one section is a clamping end, used to connect with the lower end of the clamping belt to clamp the clamping belt (3), and the other section is a loading end, which is tensioned by a pull rope to achieve precise adjustment of the clamping belt; the middle part connecting the two sections is connected to the support leg of the mounting base (1) through a rotating shaft; The pull rope tensioning seat (6) is fixedly installed on the surface of the spacecraft; A guide rope ring (5) is fixed on the rope tensioning seat (6), and the guide rope ring (5) is located above the loading end of the pressing lever (2); There are two compression belt cover plates (4) clamped on both sides of one end of the compression belt, and the compression belt and the compression belt cover plates (4) clamped on both sides are installed on the unfolding mechanism through screws; the other end of the compression belt is matched and connected with the compression end of the compression lever (2); one end of the pull rope is fixed on the loading end of the compression lever (2), and the other end passes through the guide rope ring (5) and is turned to connect to the loading device; One end of the release leaf spring (7) is fixedly mounted on the base (1), and the other end is connected to the loading end of the pressing lever (2). In the initial state, the release leaf spring (7) is in a stretched state, generating a downward preload force.

2. The device for loading the pressing force of the pressing belt of the deployment mechanism of a spacecraft according to claim 1, characterized in that: The clamping end of the clamping lever (2) and the clamping belt (3) are connected by means of a hook-shaped structure, the hook of the clamping end of the clamping lever (2) is downward, and the hook of the clamping belt (3) is upward.

3. The device for loading a pressing force of a pressing belt of a spacecraft deployment mechanism according to claim 1, characterized in that: In the loaded state, the loading end of the clamping lever (2) is pulled upward by the pull rope, and the clamping end of the clamping lever (2) moves downward to clamp the clamping belt (3); In the released state, the tension of the pull rope on the loading end of the clamping lever (2) contacts, the release leaf spring (7) generates a downward tension, and the clamping end of the clamping lever releases the clamping of the clamping belt.

4. The device for loading the pressing force of a pressing belt of a spacecraft deployment mechanism according to claim 1, characterized in that: The compression belt (3) is in a curled state when not compressed.

5. The device for loading the pressing force of a pressing belt of a spacecraft deployment mechanism according to claim 1, characterized in that: The hole on the compression belt cover plate (4) for passing the screw is an oblong hole.

6. The device for loading the pressing force of a pressing belt of a spacecraft deployment mechanism according to claim 1, characterized in that: The draw rope tensioning seat (6) is provided with an oblong hole for pre-tightening the draw rope.

7. The device for loading the pressing force of a pressing belt of a spacecraft deployment mechanism according to claim 1, characterized in that: The material of the pull rope is a steel wire rope.

8. The device for loading the pressing force of a pressing belt of a spacecraft deployment mechanism according to claim 1, characterized in that: The material of the pressing lever is titanium alloy.

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