A clamping force loading device for a spacecraft deployment mechanism.

Abstract

This invention relates to a clamping force loading device for a spacecraft deployment mechanism's clamping band. This device achieves precise height control of the clamping band by cleverly fixing the clamping band to the side of the deployment mechanism, combined with the fixation of a leaf spring and the adjustment of a pull cable. Specifically, one end of the leaf spring is connected to the clamping band, while the other end is fixed to the mechanism. This device effectively maintains the correct position of the clamping band. In this invention, the combination of the pull cable and the leaf spring, along with a simple pull cable tensioning mechanism, achieves rapid and accurate clamping of the clamping band. Simultaneously, during release, a pull cable release mechanism is used, and the mechanism is released under the action of the leaf spring, ensuring the safety and controllability of the release process.

Description

Technical Field

[0001] This invention relates to the field of aerospace technology, and more specifically to a clamping force loading device for a spacecraft deployment mechanism. Background Technology

[0002] With the continuous development of aerospace technology, the deployment mechanism of spacecraft plays a crucial role in mission execution. The deployment mechanism typically comprises several key components, among which the clamping straps are a critical element. Their function is to clamp the structural components during spacecraft deployment, ensuring the correct position and reliability of each component. To effectively realize the function of the deployment mechanism, the clamping force of the clamping straps must be precisely controlled and adjusted.

[0003] Currently, existing clamping band loading devices suffer from several technical bottlenecks. For example, existing clamping band loading devices for deployment mechanisms are complex to operate and difficult to adjust, making precise control of the clamping force a challenge. Simultaneously, the controllability of the release mechanism is also a significant issue. Traditional loading devices struggle to achieve precise adjustment of the clamping force, potentially leading to inaccurate structural displacement and component position deviations during spacecraft deployment, thus affecting the normal operation of the spacecraft. Some devices are prone to wear and failure during long-term use, reducing the reliability and lifespan of the entire deployment mechanism. The loading device may be affected by external environmental factors, causing changes in the clamping force and thus impacting the stability of the spacecraft. Furthermore, some loading devices may not be flexible enough to adapt to different deployment mechanisms, limiting their adaptability in various application scenarios. Summary of the Invention

[0004] The technical problem solved by this invention is to overcome the shortcomings of the prior art. This invention provides a clamping force loading device for the clamping band of a spacecraft deployment mechanism, which realizes high-precision control of the clamping force of the clamping band and ensures the reliability and stability of the deployment mechanism.

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

[0006] Mounting base for fixed installation on the surface of spacecraft, providing support for the clamping force loading device, and serving as a bottom limiting support for the deployment mechanism;

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

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

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

[0010] There are two clamping band cover plates, which are clamped on both sides of one end of the clamping band. The clamping band and the clamping band cover plates clamped on both sides are installed on the unfolding mechanism by screws. The other end of the clamping band is connected to the clamping end of the clamping lever. One end of the pull rope is fixed to the loading end of the clamping lever, and the other end passes through the guide rope loop and turns 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.

[0012] Preferably, the pressing end of the pressing lever and the pressing band are connected by a hook-shaped structure, with the hook of the pressing end of the pressing lever pointing downwards and the hook of the pressing band pointing upwards.

[0013] Preferably, under load, the loading end of the clamping lever is pulled upward by the rope, and the clamping end of the clamping lever moves downward to clamp the clamping band.

[0014] In the released state, the tension of the pull rope on the loading end of the clamping lever contacts the tension, the release leaf spring generates a downward pulling force, and the clamping end of the clamping lever releases its pressure on the clamping band.

[0015] Preferably, the uncompressed state of the compression band is curled.

[0016] Preferably, the hole for the screw to pass through on the clamping band cover is an oblong hole.

[0017] Preferably, the tensioning seat for the rope has an elongated hole for pre-tensioning the rope.

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

[0019] Preferably, the clamping lever is made of titanium alloy.

[0020] The advantages of this invention compared to the prior art are:

[0021] (1) Precise control and adjustable release: By introducing new design elements such as the tensioning seat and release leaf spring, this invention achieves precise control and adjustable release of the clamping band. Compared with some existing loading devices that are complex to operate and difficult to adjust, the design of this invention makes the control of the unfolding mechanism more intuitive and flexible.

[0022] (2) Improved Qualitative and Adaptability: Through a cleverly designed loading device, this invention can effectively cope with the influence of external environmental factors and improve the stability of the deployment mechanism. At the same time, the adjustable loading device improves its adaptability to different deployment mechanisms and working conditions, making it more versatile.

[0023] (3) Ease of operation: The loading device of this invention is designed with user convenience in mind. By combining the pull rope and the release leaf spring, the operation process is made simpler, the threshold of use is lowered, and different operators can more easily perform loading and releasing operations.

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

[0025] (5) Flexible adaptation to different scenarios: Due to the more flexible design of the loading device, the present invention can be adjusted by pulling the tension seat to adapt to different working scenarios and the deployment mechanism of spacecraft, thus improving the versatility and adaptability of the device. Attached Figure Description

[0026] Figure 1 This is a schematic diagram of the clamping force loading device of the clamping belt according to an embodiment of the present invention. Detailed Implementation

[0027] The present invention will be further described below with reference to the embodiments.

[0028] To improve the practicality of the entire loading device, this invention aims to design a simple-to-operate clamping force loading device for the clamping band of a spacecraft deployment mechanism, making the loading of the clamping band and the release of the deployment mechanism more intuitive and controllable. By introducing advanced control technology and materials engineering, this loading device can achieve high-precision control of the clamping force, ensuring the reliability and stability of the deployment mechanism. Simultaneously, the loading device of this invention is designed to be more durable, effectively extending the service life of the spacecraft and improving the overall system performance.

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

[0030] Mounting base 1 is used to fix the system to the surface of the spacecraft, providing a firm support for the clamping force loading device and serving as a bottom limiting support for the deployment mechanism, ensuring that the entire system remains stable and secure when installed on the spacecraft.

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

[0032] The tensioning seat 6 is fixedly installed on the surface of the spacecraft; the tensioning seat adjusts the clamping lever by adjusting the tension of the tensioning rope, thereby adjusting the force of the clamping band. The operator can adjust the entire loading device by simply pulling the rope.

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

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

[0035] One end of the clamping band is fixed to the spacecraft deployment mechanism with screws along with the clamping band cover plate 4 clamped on both sides, ensuring that the connection meets the design requirements of the mechanism; the other end of the clamping band is connected to the clamping end of the clamping lever 2, and is tightly fixed by the action of the clamping lever; the design of the clamping band enables it to provide reliable support 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 clamping lever 2, and the other end passes through the guide rope ring 5 and is turned to connect to the loading device;

[0037] The release leaf spring 7 is fixedly mounted on the base 1 at one end and connected to the loading end of the clamping lever 2 at the other end. In the initial state, the release leaf spring 7 is in a stretched state, generating a downward preload. As part of the release mechanism, when the pull rope is disconnected, the release leaf spring releases the clamping lever, loosening its pressure on the clamping band and achieving safe release of the unfolding mechanism.

[0038] Preferably, the pressing end of the pressing lever 2 and the pressing band 3 are connected by a hook-shaped structure, with the hook of the pressing end of the pressing lever 2 pointing downwards and the hook of the pressing band 3 pointing upwards.

[0039] Preferably, under 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 band 3.

[0040] In the released state, the tension of the pull rope on the loading end of the clamping lever 2 contacts, the release spring 7 generates a downward pulling force, and the clamping end of the clamping lever releases its pressure on the clamping band.

[0041] Preferably, the uncompressed state of the compression band 3 is curled.

[0042] Preferably, the hole on the clamping band cover plate 4 for the screw to pass through is an oblong hole.

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

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

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

[0046] Preferably, the clamping lever is made of titanium alloy.

[0047] This design allows the loading device to adapt to different working conditions, ensuring that the clamping 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 clamping force loading device of the clamping belt in this invention, including the following steps:

[0049] Step 1: Correctly install the fixed base, clamping belt, clamping belt cover plate, clamping lever and other parts onto the star.

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

[0051] Step 3: Tension the rope. Tension one section of the clamping lever using the rope tensioning seat. This step allows you to adjust the clamping force by pulling the rope, ensuring it provides appropriate clamping force under different conditions.

[0052] Step four, maintaining operational status: In this stage, the loading device will maintain the pressure on the deployment mechanism, preserving its support force. This helps ensure that the spacecraft deployment mechanism can maintain the predetermined structural stiffness and stability.

[0053] Step 5: Release: When it is necessary to release the unfolding mechanism, operate the release spring to disconnect the pull rope. Under the action of the release spring, the clamping lever loosens its pressure on the clamping band, thus releasing the unfolding mechanism. The unfolding mechanism can then be freely unfolded or folded. Alternatively, under the action of the release spring, the clamping lever loosens its pressure on the clamping band, achieving a safe release of the unfolding mechanism.

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

[0055] In summary, this invention relates to a clamping force loading device for a spacecraft deployment mechanism's clamping strap. Its innovation lies in achieving precise height control of the clamping strap by cleverly fixing the clamping strap to the side of the deployment mechanism, combined with the fixing of a leaf spring and the adjustment of a pull cable. Specifically, one end of the leaf spring is connected to the clamping strap, while the other end is fixed to the mechanism. This device effectively maintains the correct position of the clamping strap.

[0056] In this invention, the combination of a pull cable and a leaf spring enables rapid and accurate tightening of the compression band through a simple pull cable tensioning mechanism. Simultaneously, a pull cable release mechanism is used to release the pull cable during release, and the mechanism is released under the action of the leaf spring, ensuring the safety and controllability of the release process.

[0057] Furthermore, the design of this 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 simple and efficient to operate, and can be applied to various spacecraft deployment mechanisms, providing reliable structural support for spacecraft during deployment. Through the above innovations, this invention not only improves the performance level of the system, but also demonstrates significant advantages in practical applications.

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

[0059] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solutions of the present invention by utilizing the methods and techniques disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the protection scope of the technical solutions of the present invention.

Claims

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

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

3. The clamping force loading device for the clamping band of a spacecraft deployment mechanism according to claim 1, characterized in that: Under 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 band (3); In the released state, the tension of the pull rope on the loading end of the clamping lever (2) comes into contact, the release spring (7) generates a downward pull, and the clamping end of the clamping lever loosens the clamping band.

4. The clamping force loading device for the clamping band of a spacecraft deployment mechanism according to claim 1, characterized in that, The compression band (3) is curled up when it is not compressed.

5. The clamping force loading device for the clamping band of a spacecraft deployment mechanism according to claim 1, characterized in that, The hole on the clamping band cover plate (4) for the screw to pass through is an oblong hole.

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

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

8. The clamping force loading device for the clamping band of a spacecraft deployment mechanism according to claim 1, characterized in that, The clamping lever is made of titanium alloy.

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