A compression release device and satellite equipment

Abstract

The present invention belongs to the field of aerospace technology, and discloses a compression release device and satellite equipment. The compression release device includes a fuse module, a support module and a rope ring, the fuse module includes a first connector and a fuse, the first connector includes two first rope winding parts and two rope threading holes; the support module includes a bracket and two second connectors connected to the bracket, the two second connectors correspond to the two rope threading holes one by one; the rope ring is arranged in abutment with the fuse, along the direction close to the bracket, one end of the rope ring passes through a rope threading hole along the direction close to the bracket, is wound around the corresponding second connector and is hung and fixed to a first rope winding part, and the other end of the rope ring passes through another rope threading hole along the direction close to the bracket, is wound around the corresponding second connector and is hung and fixed to another first rope winding part. The device solves the problem that the existing compression function is prone to failure under complex working conditions due to insufficient compression force of the rope ring, which affects the reliability of compression and deployment of spacecraft loads such as satellite equipment.

Description

Technical Field

[0001] The present invention relates to the field of aerospace technology, and in particular to a compression release device and satellite equipment. Background Art

[0002] In the aerospace field, the normal operation of satellite equipment is inseparable from the deployment of satellite solar panels and payloads. The clamping and releasing device is a crucial electromechanical device for performing this task. It requires high reliability and mechanical and electrical redundancy to cope with the complex environment of space. Before entering orbit, the clamping and releasing device must overcome vibration to keep the load compacted and meet the envelope requirements. After entering orbit, the clamping and releasing device can smoothly deploy to ensure working conditions. In recent years, non-pyrotechnic devices have received much attention. The hot knife locking and releasing device is one of them. It uses electric heating to melt the connecting wire to achieve unlocking.

[0003] In the prior art, the compression and release device usually uses two PE ropes to connect the support rod and the satellite body. However, when encountering a large-scale mechanical environment, the compression function of the compression and release device may fail due to insufficient compression force of the PE rope, which cannot meet the strict requirements of satellite equipment on the reliability and stability of the compression and release device in a complex space environment, thereby affecting the smooth execution of the satellite equipment mission. Summary of the invention

[0004] The purpose of the present invention is to provide a clamping and releasing device and satellite equipment, which solves the problem that the clamping function is easily failed under complex working conditions due to insufficient clamping force of the rope ring, affecting the reliability of clamping and deployment of spacecraft payloads such as satellite equipment.

[0005] To achieve this object, the present invention adopts the following technical solutions:

[0006] A compression release device, comprising:

[0007] The fuse module comprises a first connecting member and a fuse, wherein the first connecting member comprises two first rope winding parts and two rope threading holes;

[0008] A supporting module comprises a bracket and two second connecting members connected to the bracket, wherein the two second connecting members correspond to the two rope threading holes one by one;

[0009] A rope ring is arranged in contact with the fuse, one end of the rope ring passes through one rope threading hole along the direction close to the bracket, is wrapped around the corresponding second connecting piece and is hung and fixed with one of the first rope winding parts, and the other end of the rope ring passes through another rope threading hole along the direction close to the bracket, is wrapped around the corresponding second connecting piece and is hung and fixed with the other first rope winding part.

[0010] Preferably, the second connecting member is symmetrically provided with two second rope winding parts, and the rope ring includes a first winding section, a first hanging section, a second winding section and a second hanging section which are connected end to end and form a ring, one end of the first winding section is wound around one of the second rope winding parts of the second connecting member, the other end of the first winding section is wound around one of the second rope winding parts of another second connecting member, and the first hanging section is used to be hung and fixed with one of the first rope winding parts, one end of the second winding section is wound around another second rope winding part of the second connecting member, the other end of the second winding section is wound around another second rope winding part of another second connecting member, and the second hanging section is used to be hung and fixed with another first rope winding part.

[0011] Preferably, the second connecting member is movably connected to the bracket to adjust the distance between the second connecting member and the first connecting member to pre-tighten the rope ring.

[0012] Preferably, the support module further comprises a first fastener, the first fastener is passed through the bracket and connected to the second connecting member, and the first fastener is threadedly connected to the bracket to adjust the distance between the second connecting member and the first connecting member.

[0013] Preferably, one of the bracket and the first connecting member is provided with a positioning protrusion, and the other of the bracket and the first connecting member is provided with a positioning recess, and the positioning protrusion can be plug-fitted with the positioning recess.

[0014] Preferably, a surface of the positioning protrusion and / or the positioning concave portion is provided with an anti-sticking layer, and the anti-sticking layer is used to isolate the positioning concave portion and the positioning protrusion.

[0015] Preferably, the fuse is connected to a side of the first connecting member away from the bracket, and the fuse is provided with a heating portion, which is used to fuse the rope ring.

[0016] Preferably, a rope winding protrusion is protruded from the outer edge of one end of the rope threading hole facing the fuse, and a portion of the rope loop located between two rope winding protrusions is tensioned by the heating portion.

[0017] Preferably, the fuse module includes a booster assembly, which includes a booster body, an elastic member and a booster column. The booster body is connected to the first connecting member, and the two ends of the elastic member respectively abut the booster body and the booster column. The booster column is slidably connected to the booster body, and the booster column abuts the bracket.

[0018] The satellite equipment comprises a satellite body, a support rod, an actuator and the compression release device, wherein the fuse module is connected to the satellite body, one end of the support rod is movably connected to the satellite body, the other end of the support rod is connected to the bracket, and the actuator is installed on the bracket.

[0019] Beneficial effects:

[0020] The present invention provides a compression release device and satellite equipment, the compression release device comprises a fuse module, a support module and a rope ring. The fuse module comprises a fuse and a first connecting member, the first connecting member is provided with two first rope winding parts and two rope threading holes, the support module bracket is connected with two second connecting members, and they correspond to the rope threading holes of the first connecting member; the rope ring abuts against the fuse, one end of the rope ring passes through a rope threading hole in the direction of the bracket, is connected with the corresponding second connecting member and is hung and fixed with one first rope winding part, and the other end passes through another rope threading hole, is connected with the corresponding second connecting member and is hung and fixed with another first rope winding part.

[0021] This connection form makes the rope ring equivalent to eight single ropes tightened at the same time in terms of mechanical effect, thereby improving the tension and stability of the rope ring and solving the problem of failure of the compression function of the traditional device due to insufficient compression force of the rope ring. When the satellite equipment encounters strong vibration and impact during the launch phase, the device can firmly maintain the load in a compacted state and meet the envelope requirements. After the satellite equipment enters orbit, it can smoothly deploy the load, effectively ensuring the stable operation of satellite equipment and other spacecraft payloads, improving the reliability, stability and adaptability of the compression and release device to complex aerospace environments, and providing support for the smooth implementation of aerospace missions. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 is a schematic structural diagram of a compression and release device provided in an embodiment of the present invention;

[0023] Figure 2 is a partial structural schematic diagram of a compression and release device provided in an embodiment of the present invention;

[0024] Figure 3 is a schematic diagram of a rope ring structure provided by an embodiment of the present invention;

[0025] Figure 4 is a structural schematic diagram of a fuse module provided in an embodiment of the present invention;

[0026] Figure 5 is a structural schematic diagram of a support module provided by an embodiment of the present invention;

[0027] Figure 6 is a schematic structural diagram of a fuse provided by an embodiment of the present invention;

[0028] Figure 7 is a schematic cross-sectional view of the structure of a fuse, a first connecting member and a rope ring provided in an embodiment of the present invention;

[0029] Figure 8It is a schematic diagram of the structure of the booster assembly provided in an embodiment of the present invention.

[0030] In the figure:

[0031] 1- Fuse module;

[0032] 11-first connecting member; 111-first connecting portion; 112-first rope winding portion; 113-positioning protrusion;

[0033] 1111-rope threading hole; 1112-first mounting hole; 1113-rope winding protrusion; 1121-limiting part;

[0034] 12-fuse element; 121-heating part; 122-second mounting hole; 123-groove;

[0035] 13-boost assembly; 131-boost body; 132-elastic member; 133-boost column; 1311-third mounting hole; 1312-boost cavity;

[0036] 2-support module; 21-bracket; 22-first fastener; 23-second connecting member; 211-positioning recess; 231-second rope winding portion; 2311-anti-slip portion;

[0037] 3-rope ring; 31-first winding section; 32-first hanging section; 33-second winding section; 34-second hanging section. DETAILED DESCRIPTION

[0038] The present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. It is to be understood that the specific embodiments described herein are only used to explain the present invention, rather than to limit the present invention. It should also be noted that, for ease of description, only parts related to the present invention, rather than all structures, are shown in the accompanying drawings.

[0039] In the description of the present invention, unless otherwise clearly specified and limited, the terms "connected", "connected", and "fixed" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0040] In the present invention, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may include that the first and second features are in direct contact, or may include that the first and second features are not in direct contact but are in contact through another feature between them. Moreover, a first feature being "above", "above" and "above" a second feature includes that the first feature is directly above and obliquely above the second feature, or simply indicates that the first feature is higher in level than the second feature. A first feature being "below", "below" and "below" a second feature includes that the first feature is directly below and obliquely below the second feature, or simply indicates that the first feature is lower in level than the second feature.

[0041] In the description of this embodiment, the terms "upper", "lower", "right", etc., directions or positional relationships are based on the directions or positional relationships shown in the drawings, and are only for the convenience of description and simplification of operation, rather than indicating or implying that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore cannot be understood as limiting the present invention. In addition, the terms "first" and "second" are only used to distinguish in the description and have no special meaning.

[0042] This embodiment provides a compression release device, such as Figure 1-Figure 8 As shown, the compression release device includes a fuse module 1, a support module 2 and a rope ring 3. One end of the fuse module 1 is fixedly connected to the satellite body, the support module 2 is rotatably connected to the satellite body, and the other end of the fuse module 1 is connected to the support module 2 through the rope ring 3. Specifically, the fuse module 1 includes a first connecting member 11 and a fuse 12, the first connecting member 11 includes two first rope winding parts 112 and two rope threading holes 1111; the support module 2 includes a bracket 21 and two second connecting members 23 connected to the bracket 21, the two second connecting members 23 correspond to the two rope threading holes 1111 one by one; the rope ring 3 is arranged in abutment with the fuse 12, one end of the rope ring 3 passes through a rope threading hole 1111 in a direction close to the bracket 21, is wrapped around the corresponding second connecting member 23 and is hung and fixed with a first rope winding part 112, and the other end of the rope ring 3 passes through another rope threading hole 1111 in a direction close to the bracket 21, is wrapped around the corresponding second connecting member 23 and is hung and fixed with the other first rope winding part 112.

[0043] Among them, the rope ring 3 is an oblong shape, and the two ends along the length direction are used for hanging and fixing, so as to ensure the stability of the entire compression and release device structure and the effective transmission of force. This connection form makes the rope ring 3 equivalent to eight single ropes being tightened at the same time in terms of mechanical effect, thereby improving the tension and stability of the rope ring 3, and solving the problem that the compression function of the traditional device fails due to insufficient compression force of the rope ring 3. When the satellite equipment encounters strong vibration impact during the launch phase, the compression and release device can firmly maintain the load in a compacted state and meet the envelope requirements, ensuring the safety and stability of the satellite equipment during the launch process. When the satellite equipment successfully enters orbit and reaches the predetermined position, the fuse 12 in the fuse module 1 will fuse the rope ring 3, and the support module 2 can be smoothly deployed, thereby realizing the smooth release of the load, effectively ensuring the stable operation of satellite equipment and other spacecraft payloads, improving the reliability, stability and adaptability of the compression and release device to complex aerospace environments, and providing assistance for the smooth implementation of aerospace missions.

[0044] Specifically, Figure 4 As shown, the first connecting member 11 includes a first connecting portion 111, two first rope winding portions 112 are symmetrically arranged on opposite sides of the first connecting portion 111, and rope threading holes 1111 are respectively arranged at the first connecting portion 111 adjacent to the two first rope winding portions 112.

[0045] like Figure 2 and Figure 4 As shown, the first rope winding portion 112 includes a limiting portion 1121, which extends in a direction away from the bracket 21 to limit the rope ring 3 to prevent the rope ring 3 from being displaced or falling off, providing additional protection for the stability of the rope ring 3, thereby enhancing the reliability and stability of the entire device.

[0046] like Figure 2 and Figure 3As shown, the second connecting member 23 is symmetrically provided with two second rope winding portions 231, and the rope ring 3 includes a first winding section 31, a first hanging section 32, a second winding section 33 and a second hanging section 34 which are connected end to end and form a ring. One end of the first winding section 31 is wound around one of the second rope winding portions 231 of a second connecting member 23, and the other end of the first winding section 31 is wound around one of the second rope winding portions 231 of another second connecting member 23. The first hanging section 32 is used to be hung and fixed with one of the first rope winding portions 112, one end of the second winding section 33 is wound around another second rope winding portion 231 of a second connecting member 23, and the other end of the second winding section 33 is wound around another second rope winding portion 231 of another second connecting member 23. The second hanging section 34 is used to be hung and fixed with another first rope winding portion 112. The double winding design of the first winding section 31 and the second winding section 33 of the rope ring 3 and the second rope winding part 231 in the present device avoids the poor contact problem caused by the mutual squeezing of the first winding section 31 and the second winding section 33, makes the contact more sufficient and effective, optimizes the transmission and distribution of force, enhances the resistance to tension, vibration and impact, and ensures the reliability and stability of the clamping and releasing device. At the same time, the force is evenly dispersed to the two second rope winding parts 231 to prevent problems such as excessive wear and deformation caused by excessive local force, maintain the integrity and stability of the structure, ensure that the connection efficiency can be stably exerted under long-term force and complex vibration and impact conditions, and enhance the reliability and adaptability of the device in aerospace applications.

[0047] Specifically, Figure 2 and Figure 3 As shown, the two ends of the first winding section 31 are respectively wound around the second rope winding parts 231 on the same side of the two second connecting members 23, and the two ends of the second winding section 33 are respectively wound around the second rope winding parts 231 on the other side of the two second connecting members 23. This winding method effectively avoids the crossover of the rope ring 3, ensuring the reliable operation of the clamping release device in aerospace applications.

[0048] Specifically, Figure 1-Figure 2As shown, the two second rope winding parts 231 disposed on the same second connecting member 23 are both cylindrical at the ends close to each other, and this shape helps the winding section 31 to fit together and realize uniform force transmission; and at the ends of the two second rope winding parts 231 that are away from each other, a non-slip part 2311 is provided through an arc transition, and the non-slip part 2311 can prevent the winding section 31 from sliding or displacing under complex force environments, thereby enhancing the stability and reliability of the connection structure and providing a guarantee for the precise and stable operation of the device in space missions. In other embodiments, the second connecting member 23 is provided with a second rope winding part 231, the first winding section 31 and the second winding section 33 are wound around a second rope winding part 231, and the first hanging section 32 and the second hanging section 34 are respectively used to hang and fix with the corresponding first rope winding part 112. This structure provides the device with a variety of design options. In some scenarios that require space or cost, although the force dispersion effect is inferior to the design of the double second rope winding part 231, the reliability and stability of the device can still be ensured through reasonable material selection and optimized process, so that it can operate normally and meet mission requirements.

[0049] like Figure 1 and Figure 2 As shown, the second connecting member 23 is movably connected to the bracket 21 to adjust the distance between the second connecting member 23 and the first connecting member 11 to pre-tighten the rope ring 3. By adjusting the distance to pre-tighten the rope ring 3, it is prevented from being in a loose state, ensuring that the rope ring 3 fits tightly with each component, improving the overall structural stability of the clamping and releasing device, and reducing the displacement and shaking of the components during the force process. In this way, even under the strong vibration and impact conditions faced by satellite equipment during launch, the device can stably and reliably realize the clamping function of the load, providing guarantee for the smooth implementation of the space mission.

[0050] Furthermore, if Figure 1 and Figure 5 As shown, the support module 2 also includes a first fastener 22, which is inserted into the bracket 21 and connected to the second connector 23, and the first fastener 22 is threadedly connected to the bracket 21 to adjust the spacing between the second connector 23 and the first connector 11. Due to the connection pre-tightening force of the rope ring 3 and the limitation of the side wall of the bracket 21 on the second connector 23, when adjusting the spacing, the rotation of the second connector 23 is small and can be ignored. Through this precise spacing adjustment, the overall structural stability of the clamping release device is improved, the displacement and shaking of the components when they are stressed are reduced, and the device is ensured to operate stably under complex working conditions, providing guarantee for the smooth implementation of space missions.

[0051] In this embodiment, if Figure 4 and Figure 5As shown, the bracket 21 is provided with a positioning recess 211, and the first connecting member 11 is provided with a positioning protrusion 113, and the positioning protrusion 113 can be plugged and matched with the positioning recess 211 to achieve positioning, which not only ensures the overall structural stability of the clamping and releasing device, and avoids the rope ring 3 from being subjected to additional unreasonable stress due to loose components or position deviation, but also accurately determines the force transmission path of the rope ring 3 to prevent it from twisting and bending, thereby ensuring that the rope ring 3 is evenly stressed, strengthening the anti-external force performance of the clamping and releasing device, and stabilizing the stability and safety of satellite equipment in space missions. In other embodiments, the bracket 21 is provided with a positioning protrusion 113, and the first connecting member 11 is provided with a positioning recess 211, and the positioning protrusion 113 can be plugged and matched with the positioning recess 211 to achieve positioning.

[0052] Specifically, Figure 4 and Figure 5 As shown, the positioning protrusion 113 is in the shape of a truncated cone. When it is inserted into the positioning recess 211, the small end of the truncated cone enters the positioning recess 211 as the starting end, guiding the positioning protrusion 113 to be initially aligned with the positioning recess 211, ensuring a smooth insertion process. As the insertion progresses, the side surface of the truncated cone gradually fits with the inner wall of the positioning recess 211 until the large end of the truncated cone contacts the edge of the outer port of the positioning recess 211, completing a tight and stable plug-in fit between the two.

[0053] In other embodiments, the positioning protrusion 113 and the positioning recess 211 can also be other compatible shapes. When the cylindrical positioning protrusion 113 is plugged into the positioning recess 211, a stable positioning effect is achieved by means of the close fit between the circumferential surface and the inner wall; the hemispherical positioning protrusion 113 is combined with the matching hemispherical groove-shaped positioning recess 211, and accurate positioning can be achieved during the assembly process by relying on the hemispherical surface characteristics; the prismatic positioning protrusion 113 is tightly fitted with the precisely corresponding prism groove in the positioning recess 211 through its edges, giving the component connection reliable and accurate positioning accuracy, thereby meeting the diverse needs for component connection and positioning under different working conditions, and ensuring the stable operation and accurate assembly of the overall device.

[0054] In this embodiment, the surface of the positioning protrusion 113 is provided with an anti-sticking layer (not shown in the figure), and the anti-sticking layer is used to isolate the positioning recess 211 and the positioning protrusion 113, so as to avoid the cold welding of the positioning protrusion 113 and the positioning recess 211 due to direct surface contact in the complex environment of aerospace, thereby preventing the connection part of the two from being difficult to separate. When subjected to external force, the anti-sticking layer can ensure that the components maintain a relatively smooth relative movement, reduce the possibility of adhesion between the positioning protrusion 113 and the positioning recess 211, and effectively ensure the reliability of the compression release device. Specifically, the material of the anti-sticking layer can be selected from molybdenum disulfide or tungsten carbide, etc., and the material selected for the anti-sticking layer is not specifically limited. In an optional embodiment, the surface of the positioning recess 211 is provided with an anti-sticking layer coated with an anti-sticking layer, and the anti-sticking layer is used to isolate the positioning recess 211 and the positioning protrusion 113. In another optional embodiment, the surfaces of the positioning concave portion 211 and the positioning convex portion 113 are both provided with an anti-sticking layer, and the anti-sticking layer is used to isolate the positioning concave portion 211 and the positioning convex portion 113 .

[0055] like Figure 6 As shown, the fuse 12 is connected to the side of the first connector 11 away from the bracket 21, and the fuse 12 is provided with a heating part 121, and the heating part 121 is used to fuse the rope ring 3. In this way, on the one hand, the risk of mechanical unlocking failure is reduced, and the force transmission is stable during fusing, thereby protecting the device structure; on the other hand, this position is close to the rope ring 3, which can reduce energy loss, improve fusing efficiency, and avoid damage to key structures, thereby ensuring safe and stable operation of satellite equipment. Specifically, the heating part 121 is selected as a heating resistor, which uses the thermal effect of current to efficiently generate heat and can quickly reach a high temperature for fusing the rope ring 3.

[0056] In this embodiment, the connection between the rope ring 3 and the first rope winding part 112 is fixed by glue. In a space mission, if the rope ring 3 falls off after melting, it will float around in the microgravity and vacuum environment of space, making it difficult to recover, polluting the space environment and affecting other spacecraft and space missions. By fixing the connection between the rope ring 3 and the first rope winding part 112 with glue, when the rope ring 3 melts, it can still be attached to the first rope winding part 112, avoiding it from falling off and becoming space junk, thus ensuring a clean and safe space environment.

[0057] In this embodiment, if Figure 7 As shown, a rope-winding protrusion 1113 is protruded from the outer edge of the rope-threading hole 1111 toward one end of the fuse 12, and the portion of the rope ring 3 between the two rope-winding protrusions 1113 is tensioned by the heating portion 121. After the rope ring 3 is wound and fixed, the portion between the two rope-winding protrusions 1113 is straightened. At this time, the heating portion 121 presses against the rope ring 3 and applies a force toward the bracket 21, so that the portion of the rope ring 3 in contact with the heating portion 121 is tensioned, thereby closely fitting the heating portion 121 to ensure the effective effect of the heating portion 121 on the rope ring 3.

[0058] like Figure 6 and Figure 7 As shown, grooves 123 are symmetrically provided on both sides of the fuse 12, and the rope ring 3 passes through the rope threading hole 1111 through the gap between the groove 123 and the rope winding protrusion 1113, so that the rope ring 3 can pass through the rope threading hole 1111 smoothly, and the groove 123 provides a suitable passing space for the rope ring 3, optimizes the winding path of the rope ring 3, avoids the rope ring 3 from getting stuck or twisted at the connection part, and makes the connection of the rope ring 3 more stable and reliable, thereby enhancing the stability and reliability of the entire clamping and releasing device in a complex aerospace environment.

[0059] In this embodiment, if Figure 1 , Figure 4 and Figure 8 As shown, the fuse module 1 includes a booster assembly 13, which includes a booster body 131, an elastic member 132 and a booster column 133. The booster body 131 is connected to the first connecting member 11, and the two ends of the elastic member 132 abut against the booster body 131 and the booster column 133 respectively. The booster column 133 is slidably connected to the booster body 131, and the booster column 133 abuts against the bracket 21. When the rope ring 3 is not fused, with the help of the elastic member 132 acting on the booster column 133, the booster assembly 13 applies tension to the rope ring 3 through the bracket 21, so that the rope ring 3 remains moderately tight and prevents relaxation, thereby improving the stability and reliability of the device. Therefore, when the rocket launch faces strong vibration and impact, the compression and release device can stably maintain the load retracted and compressed state and meet the envelope requirements, thereby ensuring the safe launch of satellite equipment and other spacecraft. When the predetermined working condition is reached and the load needs to be released, the elastic force stored in the elastic member 132 is quickly released at the moment the rope ring 3 melts, pushing the booster column 133 to move quickly, so that the support module 2 and the fuse module 1 are quickly separated, avoiding jamming due to friction between components, ensuring the smooth deployment of the support module 2, creating conditions for the smooth release of the load, and enhancing the reliability and stability of the clamping release device in space missions, so that it can better adapt to complex space environments and ensure the stable operation of spacecraft.

[0060] Specifically, Figure 8 As shown, the boosting body 131 is provided with a boosting cavity 1312 , the elastic member 132 is a compression spring and is placed in the boosting cavity 1312 , one end of the boosting column 133 is connected to the elastic member 132 , and the other end passes through the boosting cavity 1312 and abuts against the bracket 21 .

[0061] like Figure 1 , Figure 2 and Figure 6As shown, the fuse module 1 also includes a second fastener (not shown in the figure), the first connecting portion 111 is provided with four first mounting holes 1112 at intervals, the fuse 12 is provided with four second mounting holes 122 at positions corresponding to the first mounting holes 1112, and the booster body 131 is provided with four third mounting holes 1311 at positions corresponding to the first mounting holes 1112. The second fastener penetrates the first mounting hole 1112, the second mounting hole 122 and the third mounting hole 1311 in sequence, thereby achieving a tight connection between the first connecting member 11, the fuse 12 and the booster assembly 13. This connection method is stable and reliable, ensuring that the various components work together under complex working conditions, and providing a strong guarantee for the stable operation of the entire device.

[0062] The second fastener may be a bolt, a rivet or a pin, which is not specifically limited here, and only needs to ensure the requirement of a firm connection between the first connecting member 11, the fuse 12 and the booster assembly 13.

[0063] The present embodiment provides a satellite device, which includes a satellite body (not shown in the figure), a support rod (not shown in the figure), an actuator (not shown in the figure) and the above-mentioned compression and release device, wherein the fuse module 1 is connected to the satellite body, one end of the support rod is movably connected to the satellite body, the other end of the support rod is connected to the bracket 21, and the actuator is installed on the bracket 21. When the satellite equipment is launched, the compression and release device can firmly maintain the load in a collapsed and compressed state under vibration and shock and meet the envelope requirements to ensure the safety of the launch. After entering orbit, the fuse 12 fuses the rope ring 3, and the support module 2 unfolds to realize load release, thereby improving the reliability and environmental adaptability of the satellite equipment.

[0064] Specifically, the execution device can be a satellite solar wing, a payload device (space camera, communication antenna, etc.) or other auxiliary structures, which are not specifically limited here.

[0065] The working process of the compression and release device provided in this embodiment is roughly as follows:

[0066] Before the satellite equipment is launched, the rope ring 3 passes through the gap between the first connecting piece 11 and the fuse 12, and then the two ends of the rope ring 3 pass through the rope threading holes 1111 respectively, and are wrapped around the second connecting piece 23 and then hung and fixed with the first rope winding part 112, and then the rope ring 3 is pre-tightened by adjusting the distance between the second connecting piece 23 and the first connecting piece 11.

[0067] During the launch of the satellite equipment, under vibration and impact, the load is kept in a compacted state by means of the stable cooperation of the rope ring 3 and various components. At the same time, the booster assembly 13 provides tension for the rope ring 3 to prevent relaxation.

[0068] After the satellite device enters orbit, the heating part 121 of the fuse 12 melts the rope ring 3, and the rope ring 3 will not fall off due to the glue. At the moment of melting, the elastic force of the booster component 13 is released, pushing the support module 2 to separate from the fuse module 1, and the support module 2 is smoothly deployed to achieve load release.

[0069] Obviously, the above embodiments of the present invention are merely examples for clearly illustrating the present invention, and are not intended to limit the embodiments of the present invention. For those skilled in the art, various obvious changes, readjustments and substitutions can be made without departing from the protection scope of the present invention. It is not necessary and impossible to list all the embodiments here. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included in the protection scope of the claims of the present invention.

Claims

1. A compression release device, characterized in that: include: A fuse module (1) comprising a first connecting member (11) and a fuse member (12), wherein the first connecting member (11) comprises two first rope winding portions (112) and two rope threading holes (1111), and the first connecting member (11) further comprises a first connecting portion (111), wherein the two first rope winding portions (112) are symmetrically arranged on opposite sides of the first connecting portion (111), and the rope threading holes (1111) are respectively arranged at locations of the first connecting portion (111) adjacent to the two first rope winding portions (112); A support module (2) comprising a bracket (21) and two second connecting members (23) connected to the bracket (21), wherein the two second connecting members (23) correspond one-to-one to the two rope threading holes (1111); A rope ring (3), the rope ring (3) being arranged in contact with the fuse (12), one end of the rope ring (3) passing through one of the rope threading holes (1111) in a direction close to the bracket (21), being wound around the corresponding second connecting piece (23) and being hung and fixed to one of the first rope winding parts (112), and the other end of the rope ring (3) passing through another of the rope threading holes (1111) in a direction close to the bracket (21), being wound around the corresponding second connecting piece (23) and being hung and fixed to another of the first rope winding parts (112).

2. The compression release device according to claim 1, characterized in that: The second connecting member (23) is symmetrically provided with two second rope winding parts (231), and the rope ring (3) comprises a first winding section (31), a first hanging section (32), a second winding section (33) and a second hanging section (34) which are connected end to end and form a ring shape, one end of the first winding section (31) is wound around one of the second rope winding parts (231) of one of the second connecting members (23), the other end of the first winding section (31) is wound around one of the second rope winding parts (231) of another of the second connecting members (23), the first hanging section (32) is used for hanging and fixing with one of the first rope winding parts (112), one end of the second winding section (33) is wound around another of the second rope winding parts (231) of one of the second connecting members (23), the other end of the second winding section (33) is wound around another of the second rope winding parts (231) of another of the second connecting members (23), and the second hanging section (34) is used for hanging and fixing with another of the first rope winding parts (112).

3. The compression release device according to claim 1, characterized in that: The second connecting member (23) is movably connected to the bracket (21) to adjust the distance between the second connecting member (23) and the first connecting member (11) so as to pre-tighten the rope ring (3).

4. The compression release device according to claim 3, characterized in that: The support module (2) further comprises a first fastener (22), the first fastener (22) being inserted through the bracket (21) and connected to the second connecting member (23), and the first fastener (22) being threadedly connected to the bracket (21) to adjust the distance between the second connecting member (23) and the first connecting member (11).

5. The compression release device according to claim 1, characterized in that: One of the bracket (21) and the first connecting member (11) is provided with a positioning protrusion (113), and the other of the bracket (21) and the first connecting member (11) is provided with a positioning recess (211), and the positioning protrusion (113) can be plugged into and matched with the positioning recess (211).

6. The compression release device according to claim 5, characterized in that: An anti-sticking layer is provided on the surface of the positioning convex portion (113) and / or the positioning concave portion (211), and the anti-sticking layer is used to isolate the positioning concave portion (211) from the positioning convex portion (113).

7. The compression release device according to claim 1, characterized in that: The fuse (12) is connected to a side of the first connecting member (11) away from the bracket (21), and the fuse (12) is provided with a heating portion (121), and the heating portion (121) is used to fuse the rope ring (3).

8. The hold-down release device according to claim 7, characterized in that: A rope winding protrusion (1113) is protruded from the outer edge of one end of the rope threading hole (1111) facing the fuse (12), and a portion of the rope ring (3) located between the two rope winding protrusions (1113) is tensioned by the heating portion (121).

9. The compression release device according to claim 1, characterized in that: The fuse module (1) comprises a booster assembly (13), the booster assembly (13) comprising a booster body (131), an elastic member (132) and a booster column (133), the booster body (131) being connected to the first connecting member (11), two ends of the elastic member (132) respectively abutting against the booster body (131) and the booster column (133), the booster column (133) being slidably connected to the booster body (131), and the booster column (133) abutting against the bracket (21).

10. Satellite equipment, comprising a satellite body, a support rod and an actuator, characterized in that: It also includes a compression release device as described in any one of claims 1 to 9, the fuse module (1) is connected to the satellite body, one end of the support rod is movably connected to the satellite body, the other end of the support rod is connected to the bracket (21), and the actuator is installed on the bracket (21).

Images