A cubic satellite separation gap compensation mechanism

Abstract

The invention discloses a cubic satellite separation gap compensation mechanism, comprising a guide slide rail, a single-head stud, a retaining frame, a double-pass hexagonal copper column, a screw, a nut, a gasket, a spring compression spring, a connecting rod, a spring support block, a clamping block, a stepped shaft, a fixed seat, a bearing retaining ring, a gasket, a nut, and a bearing; the invention has the advantages of simple structure, high reliability, convenient control, and can realize the gap compensation effect between the cubic satellite and the separation mechanism slide rail to eliminate the gap.

Description

Technical Field

[0001] The invention relates to a cubic satellite separation structure, in particular to a cubic satellite separation gap compensation mechanism, and belongs to the field of cubic satellite separation structures. Background Art

[0002] In recent years, due to my country's policy support for private aerospace, more and more private capital other than universities has gradually entered the aerospace field, especially in the research and development of cubic satellites, which have advantages such as short development cycle and low manufacturing cost. The research and development capabilities and number of cubic satellites are constantly improving and increasing. With the growth of the demand for cubic satellite launches, various cubic satellite separation mechanisms have emerged, but they generally have large internal gaps and high vibration amplitudes, and poor adaptability to the harsh mechanical environment such as acceleration and impact during rocket launch. Summary of the invention

[0003] The purpose of the present invention is to design a cubic satellite separation gap compensation mechanism, which has a simple structure, high reliability, and convenient control, and can realize the gap compensation function between the cubic satellite and the separation mechanism slide rail to eliminate the gap.

[0004] The technical solution of the present invention is:

[0005] A cubic satellite separation gap compensation mechanism includes a guide rail, a single-head stud, a retaining frame, a double-pass hexagonal copper column, a screw, a nut, a gasket, a spring compression spring, a connecting rod, a spring support block, a clamping block, a stepped shaft, a fixing seat, a bearing retaining ring, a gasket, a nut, a bearing and other accessories.

[0006] The guide slide rail is provided with a slotted hole, through which the clamping block can pass and be pressed against the satellite load-bearing frame.

[0007] The stud assembly includes a double-pass hexagonal copper column, a screw, a nut, a gasket, and a compression spring, which pass through corresponding circular holes in the top frame and the bottom frame. The double-pass hexagonal copper column is installed at the upper end of the screw and contacts the hatch cover through the corresponding circular hole of the top frame. The double-pass hexagonal copper column is compressed when the hatch cover is closed and released when the hatch cover is opened. The double-pass hexagonal copper column, single nut, spring support block, double nut, gasket, spring compression spring, and spring support block are installed on the screw in sequence, wherein the double nut, gasket, spring compression spring, and spring support block can be repeated in multiple groups as needed.

[0008] The connecting rod is provided with a spring support block, the connecting rod and the spring support block are fastened by countersunk screws, and the connecting rod and the star clamping assembly are fastened by screws.

[0009] Furthermore, the connecting rod is an L-shaped structure and can be arranged symmetrically to the central symmetry plane of the separation mechanism.

[0010] Furthermore, the spring support block is provided with a through hole, and the screw can move in the through hole during the opening and closing of the hatch cover. At the same time, the spring support block, the nut and the gasket jointly limit the stroke of the spring compression spring. The distance between the nut and the spring support block is adjusted according to the mass of the satellite and the working conditions it is subjected to, thereby adjusting the clamping force of the cube satellite.

[0011] Furthermore, the spring support block is a triangular structure, which not only plays a stabilizing role but also saves internal space.

[0012] The star body clamping assembly includes a clamping block, a stepped shaft, a fixed seat, a bearing retaining ring, a gasket, a nut, and a bearing. The clamping block passes through the slot of the guide slide rail to clamp and loosen the star body. The stepped shaft passes through one side of the fixed seat, the bearing, the bearing retaining ring, the other side of the fixed seat and the gasket in sequence, and is finally fastened by the nut.

[0013] Furthermore, an inclined groove is provided inside the clamping block, and the bearing rotates in the inclined groove.

[0014] Furthermore, the clamping block is provided with a protruding structure outwardly, and the protruding structure passes through the slot hole of the guide slide rail to clamp the cubic star.

[0015] Furthermore, a countersunk hole is provided on the fixing seat to limit the axial position of the stepped shaft, and the other end of the fixing seat is axially limited by a nut.

[0016] Furthermore, the stepped shaft is provided with a shaft shoulder, which fits with the inner ring of the bearing after passing through the countersunk hole of the fixing seat, so that the bearing can rotate normally.

[0017] Furthermore, the double-pass hexagonal copper column is connected to the screw rod by threads, and a nut is installed at the bottom to position the double-pass hexagonal copper column. The hatch cover is a flip cover, which is located at the top of the entire mechanism, is provided with a countersunk hole, and a gap is left, so that the double-pass hexagonal copper column can be tightened when the flip cover is closed;

[0018] The spring support block is connected to the connecting rod by screws, and the screw rod passes through the through hole of the spring support block to position the screw rod; the clamping block is in contact with the bearing, and the stepped shaft clamps and positions the bearing through a nut and a bearing retaining ring to limit the movement of the bearing in the directions of both sides of the inclined surface of the clamping block; the clamping retaining frame is fixedly connected to the clamping block fixing seat by screws, so that the two are fixed and can move together.

[0019] Furthermore, the guide rail is provided with a slotted hole, through which the clamping block can pass and be pressed against the satellite load-bearing frame.

[0020] The guide assembly includes a top frame, a middle frame, a bottom frame, and a guide block. The top frame, the middle frame, and the bottom frame are fastened to the guide rails by screws. The guide block is installed on the middle frame to provide guidance and limiting functions when the connecting rod moves.

[0021] The single-end stud is connected to the side skin by screws, and the other end is connected to the slide rail to fix the slide rail; the baffle frame is fixed to the front skin and the side skin by screws, and the other side is connected to the guide slide rail by screws to fix the slide rail. The skin assembly includes the side skin and the front skin, which can be fastened with screws through the single-end stud and the threaded holes on the baffle frame. It protects and supports the components inside the satellite.

[0022] The cubic star is locked inside the separation mechanism, and the clamping block is in a static state under the joint action of the bearing, connecting rod, spring compression spring, stepped shaft, etc. The clamping block contacts the bearing, and the stepped shaft clamps and positions the bearing through the nut and the bearing retaining ring, limiting the movement of the bearing in the direction of the inclined surface of the clamping block. The connecting rod passes through the through hole of the clamping spring support block and the spring compression spring, and is fixed by the nut and the gasket. At this time, the connecting rod can transmit the downward force of the hatch cover to the spring compression spring, and the spring compression spring transmits the force to the clamping spring support block. The clamping spring support block and the clamping connecting rod clamping block fixing seat together transmit the force to the clamping block stepped shaft, and the stepped shaft transmits the force to the bearing, and the bearing compresses the clamping block to clamp the cubic star.

[0023] Compensation process of the cubic satellite separation gap compensation mechanism: The hatch is equipped with an electrical connector interface and an electromagnetic switch. When the electrical connector receives the separation electrical signal from the external power supply, it will generate magnetism opposite to that of the permanent magnet, the permanent magnet disappears, the switch opens, and the hatch is lifted up by the double-pass hexagonal copper column and popped open. The separation mechanism opens, the spring compression spring relaxes, the bearing moves upward along the groove slope of the clamping block, the clamping block is retracted, and a gap is generated with the cubic satellite. The double-pass hexagonal copper column is lifted up, and the cubic satellite can be ejected safely. The spring compression spring has a moderate stiffness coefficient and a margin is left, which will not exceed the linear elastic range.

[0024] The spring support block is fixedly connected to the connecting rod, and is provided with threaded hole one and threaded hole two, which are threaded holes matching with the connecting rod. The spring support block is provided with a through hole, which is a through hole matching with the screw rod, and there is a gap between the spring support block and the screw rod, thereby reducing friction.

[0025] Furthermore, the clamping block is designed with a groove slope, and the contact with the bearing is point contact, which also reduces friction.

[0026] The connecting rod is L-shaped and is provided with a first threaded hole, a third threaded hole, a fifth threaded hole, and a sixth threaded hole, which are used to connect the threaded holes of the spring support block so that the two can be firmly combined to reduce stress concentration.

[0027] The bearing is clamped by the stepped shaft and the bearing retaining ring and is fixed by only one nut, so it is convenient to disassemble and replace.

[0028] Furthermore, the point where the bearing contacts the clamping block is the moving point, the connection point of the bottom frame spring is the fixed system, the connecting rod is the moving system, the absolute motion direction is along the normal direction of the clamping block inclined surface groove, the relative motion is along the normal direction of the clamping block protrusion, the involved motion is in the vertical downward direction, and the acceleration direction is along the direction of each force, forming a force vector triangle. At the same time, the inclined surface angle is reasonably designed, and it is calculated from the force balance relationship that it is within the locking range at this time.

[0029] During the recovery phase after ground testing:

[0030] After completing the hatch cover test, the ground technicians closed the hatch cover. The double-pass hexagonal copper column was subjected to downward pressure from the hatch cover. The screw drove the nut and gasket downward, compressing the spring. At the same time, the connecting rod and the fixed seat moved downward together and drove the bearing to rotate. The bearing pressed down the clamping block, causing it to tilt. At this time, the internal cubic satellite had been taken out and the spring was in a compressed state.

[0031] Furthermore, after the hatch cover opening test is completed, if no more tests are performed within a certain period of time, the double-pass hexagonal copper column is removed. At this time, the flip cover is closed, the spring compression spring will not be compressed, and its service life can be extended to a certain extent.

[0032] Furthermore, the non-threaded section of the screw surface is polished to reduce the friction between the screw and the spring support block.

[0033] Working principle: When the flap is closed, the double-pass hexagonal copper column is under downward pressure from the top cover, and the screw drives the nut and gasket to move downward, compressing the spring. At the same time, the clamping link and the clamping block fixed seat move downward together and drive the bearing to rotate. The bearing presses the clamping block downward, causing it to tilt, and produces pressure on the cubic star in the X and Z directions. The structure is symmetrical, and the four parts can all produce clamping force to compensate for the gap between the cubic star and the slide rail. When the flap is opened, the spring compression spring relaxes, the bearing moves upward along the groove slope of the clamping block, the clamping block is retracted, and a gap is created between it and the cubic star. The double-pass hexagonal copper column pushes upward, and the cubic star can be ejected safely.

[0034] The beneficial effects of the present invention are:

[0035] 1. Simple structure, adjustable pressing force on the star body, easy to control;

[0036] 2. The gap compensation effect is obvious and can be applied to various occasions;

[0037] 3. There are few changes to the original separation mechanism;

[0038] 4. All components are symmetrical in structure, and the symmetrical setting can effectively reduce vibration damage during the launch of the cubic satellite.

[0039] The present invention will be further described below in conjunction with the accompanying drawings and embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0040] Figure 1 An exploded schematic diagram of a cubic satellite separation gap compensation mechanism according to an embodiment of the present invention;

[0041] Figure 2 It is a schematic diagram of the present invention during the launching process;

[0042] Figure 3 It is a schematic diagram of the present invention when the hatch cover reaches the limit position;

[0043] Figure 4-1 It is a schematic diagram of the force analysis of the structure of the present invention;

[0044] Figure 4-2 Schematic diagram of the star clamping assembly of the present invention

[0045] Figure 5 It is a schematic diagram of the spring compression spring of the present invention;

[0046] Figure 6-1 This is a front view of the clamping spring support block of the present invention;

[0047] Figure 6-2 A side view of the clamping spring support block of the present invention

[0048] Figure 7 It is a schematic diagram of the screw of the present invention;

[0049] Figure 8 It is a schematic diagram of the clamping connecting rod of the present invention;

[0050] Fig. 9 A schematic diagram of a bearing according to the present invention;

[0051] Figure 10-1 It is a side schematic diagram of the clamping block of the present invention;

[0052] Figure 10-2 This is a front view of the clamping block of the present invention;

[0053] Fig.11 This is a schematic diagram of the skin of the present invention;

[0054] Fig.12 Schematic diagram of the cubic satellite structure

[0055] Among them: 1-guide rail, 2-single-head stud, 3-stop frame, 4-double-pass hexagonal copper column, 5-screw, 6-nut, 7-gasket, 8-spring compression spring, 9-connecting rod, 10-spring support block, 11-star clamping assembly, 12-top frame, 13-middle frame, 14-bottom frame, 15-guide block, 16-side skin, 17-hatch cover, 18-front skin. DETAILED DESCRIPTION

[0056] The preferred embodiments of the present invention are described below. It should be understood that the preferred embodiments described herein are only used to illustrate and explain the present invention, and are not used to limit the present invention.

[0057] Example 1

[0058] like Figure 1-12 As shown, a cubic satellite separation gap compensation mechanism includes a guide rail 1, a single-head stud 2, a stop frame 3, a double-pass hexagonal copper column 4, a screw 5, a nut 6, a gasket 7, a spring compression spring 8, a connecting rod 9, a spring support block 10, a clamping block 11-1, a stepped shaft 11-2, a fixing seat 11-3, a bearing retaining ring 11-4, a gasket 11-5, a nut 11-6, a bearing 11-7 and other accessories.

[0059] The guide rail 1 is provided with a slotted hole, through which the clamping block can pass and be pressed against the satellite load-bearing frame.

[0060] The stud assembly passes through the corresponding circular holes of the top frame and the bottom frame, and includes a double-pass hexagonal copper column 4, a screw 5, a nut 6, a gasket 7, and a compression spring 8. The double-pass hexagonal copper column 4 is installed on the upper end of the screw 5, and contacts the hatch cover 17 through the corresponding circular hole of the top frame 12. After the hatch cover 17 is closed, the double-pass hexagonal copper column 4 is compressed, and after the hatch cover 17 is opened, the double-pass hexagonal copper column 4 is released; the double-pass hexagonal copper column 4, the single nut 6, the spring support block 10, the double nut 6, the gasket 7, the spring compression spring 8, and the spring support block 10 are installed on the screw 5 in sequence, wherein the double nut 6, the gasket 7, the spring compression spring 8, and the spring support block 10 can be repeated in multiple groups as required.

[0061] The connecting rod 9 is provided with a spring support block 10, the connecting rod 9 and the spring support block 10 are fastened by countersunk screws, and the connecting rod and the star clamping assembly are fastened by screws.

[0062] The connecting rod is an L-shaped structure, which can be symmetrical to the central symmetry plane of the separation mechanism (the separation mechanism is a device that reliably connects the satellite and the rocket and realizes reliable separation of the satellite and the rocket after entering orbit. The present invention is a part of a cubic satellite separation mechanism. In addition to all those mentioned in this article, the entire composition of the mechanism also includes a semicircular turntable, a flip-cover limit long plate, a limit tension spring, an electromagnetic switch, a nylon shaft sleeve, a detection circuit, a torsion spring, a tension spring, a compression spring, a spring support plate, a satellite pushing platform assembly, a flip-cover shaft, a top frame baffle, a side sealing plate, an internal sealing plate, an electrical interface, a docking block and matching screws, studs, nuts and other structures).

[0063] The spring support block 10 is provided with a through hole, and the screw rod 5 can move in the through hole during the opening and closing of the hatch 17. At the same time, the spring support block 10, the nut 6 and the gasket 7 jointly limit the stroke of the spring compression spring 8. The distance between the nut 6 and the spring support block 10 can be adjusted according to the mass of the satellite and the working conditions to be subjected to, so as to adjust the cubic satellite (a cubic satellite is a low-cost Pina satellite adopting international universal standards, divided into "U" as the standard unit, and a "1U" cubic satellite is 10cm×10cm×10cm. On this basis, it can be expanded to "2U" of 20cm×10cm×10cm to "12U" of 30cm×20cm×20cm. For example Fig.12 (as shown) is the compression force of the satellite.

[0064] The spring support block 10 is a triangular structure, which not only plays a stabilizing role but also saves internal space.

[0065] The star body clamping assembly includes a clamping block 11-1, a stepped shaft 11-2, a fixed seat 11-3, a bearing retaining ring 11-4, a gasket 11-5, a nut 11-6, and a bearing 11-7. The clamping block 11-1 passes through the slot of the guide rail 1 to achieve clamping and loosening of the star body. The stepped shaft 11-2 passes through one side of the fixed seat 11-3, the bearing 11-7, the bearing retaining ring 11-4, the other side of the fixed seat 11-3 and the gasket 11-5 in sequence, and is finally fastened by the nut 11-6.

[0066] An inclined groove is provided inside the clamping block 11 - 1 , and the bearing 11 - 7 rotates in the inclined groove.

[0067] The clamping block 11 - 1 is provided with a protruding structure outwardly, and the protruding structure passes through the slot hole of the guide rail 1 to clamp the cube star.

[0068] The fixing seat 11-3 is provided with a countersunk hole to limit the axial position of the stepped shaft 11-2, and the other end of the fixing seat is axially limited by a nut 11-6.

[0069] The stepped shaft 11-2 is provided with a shaft shoulder, which fits with the inner ring of the bearing after passing through the countersunk hole of the fixing seat 11-3, so that the bearing can rotate normally.

[0070] The double-pass hexagonal copper column 4 is connected to the screw rod 5 by threads, and a nut is installed at the bottom to position the double-pass hexagonal copper column 4. The hatch 17 is a flip cover, which is located at the top of the entire mechanism, is provided with a countersunk hole, and a gap is left, so that the double-pass hexagonal copper column 4 can be tightened when the flip cover is closed;

[0071] The spring support block 10 is connected to the connecting rod 9 by screws, and the screw 5 passes through the through hole of the spring support block 10 to position the screw; the clamping block 11-1 is in contact with the bearing 11-7, and the stepped shaft 11-2 clamps and positions the bearing 11-7 through the nut 11-6 and the bearing retaining ring, limiting the movement of the bearing in the directions of both sides of the clamping block inclined surface; the clamping retaining frame 3 is fixedly connected to the clamping block fixing seat 11-3 by screws, so that the two are fixed and can move together.

[0072] The guide rail 1 is provided with a slotted hole, through which the clamping block 11 can pass and be pressed against the satellite load-bearing frame.

[0073] The guide assembly includes a top frame 12, a middle frame 13, a bottom frame 14, and a guide block 15. The top frame 12, the middle frame 13, and the bottom frame 14 are fastened to the guide rail 1 by screws. The guide block is installed on the middle frame 13 to provide guidance and limiting functions when the connecting rod moves.

[0074] The single-end stud 2 is connected to the side skin 16 by screws, and the other end is connected to the slide rail 1, which plays a role in fixing the slide rail; the baffle 3 is fixed to the front skin 18 and the side skin 16 by screws, and the other side is connected to the guide slide rail 1 by screws, which plays a role in fixing the slide rail 1. The skin assembly includes the side skin 16 and the front skin 18, which can be fastened with screws through the single-end stud and the threaded holes on the baffle. It plays a role in protecting and supporting the components inside the satellite.

[0075] like Figure 2 , which is a schematic diagram of the launch phase of the cubic satellite separation gap compensation mechanism. The cubic satellite is locked inside the separation mechanism, and the clamping block 11-1 is in a stationary state under the joint action of the bearing 11-7, the connecting rod 9, the spring compression spring 8, the stepped shaft 11-2, etc. The clamping block 11-1 is in contact with the bearing 11-7, and the stepped shaft 11-2 clamps and positions the bearing 11-7 through the nut 11-6 and the bearing retaining ring 11-4, limiting the movement of the bearing in the directions of both sides of the clamping block inclined surface. The connecting rod 9 passes through the through hole of the clamping spring support block 10, and passes through the spring compression spring 8, and is fixed by the nut and the gasket. At this time, the connecting rod 9 can transmit the downward force of the hatch cover 17 to the spring compression spring 8, and the spring compression spring 8 transmits the force to the clamping spring support block 10. The clamping spring support block 10 and the clamping connecting rod 9 clamping block fixing seat 11 transmit the force to the clamping block stepped shaft 11-2 together, and the stepped shaft 11-2 transmits the force to the bearing 11-7. The bearing 11-7 presses the clamping block 11-1 to clamp the cubic star.

[0076] Compensation process of cubic satellite separation gap compensation mechanism: Figure 2-4, the hatch 17 is equipped with an electrical connector interface and an electromagnetic switch. When the electrical connector receives a separation electrical signal from an external power source, it will generate magnetism opposite to that of the permanent magnet, the permanent magnet disappears, the switch opens, and the hatch 17 is lifted up and popped open by the double-pass hexagonal copper column 4. The separation mechanism opens, the spring compression spring 8 relaxes, the bearing 11-7 moves upward along the groove slope of the clamping block 11-1, the clamping block 11-1 is retracted, and a gap is generated with the cubic satellite. The double-pass hexagonal copper column 4 is lifted up, and the cubic satellite can be safely ejected. Figure 5 The spring compression spring 8 has a moderate stiffness coefficient and leaves a margin that will not exceed the linear elastic range.

[0077] The nut 11-6 and the gasket 11-5 are optional and can be increased or decreased according to actual needs. Figure 2 At the position of the star clamping assembly 11, the detailed disassembly diagram is Figure 4-2 , connected to the clamping block stepped shaft 11-2, and together with the bearing retaining ring 11-4 and the clamping block fixing seat 11-3, the outer ring of the bearing 11-7 is pressed to limit its movement in the directions on both sides of the clamping block 11.

[0078] As shown in Figure 6, the spring support block 10 is fixedly connected to the connecting rod 9. The spring support block 10 is provided with a threaded hole 10-1 and a threaded hole 10-2, which are threaded holes matched with the connecting rod 9. The spring support block 10 is provided with a through hole 10-3, which is a through hole matched with the screw rod 5. There is a gap between the spring support block 10 and the screw rod 5, which reduces friction.

[0079] The clamping block 11 - 1 is designed with a groove slope, and the contact with the bearing 11 - 7 is point contact, which also reduces friction.

[0080] like Figure 7 The connecting rod 9 is L-shaped and is provided with a first threaded hole 9-1, a third threaded hole 9-3, a fifth threaded hole 9-5, and a sixth threaded hole 9-6, which are used to connect the threaded holes of the spring support block 10 so that the two can be firmly combined to reduce stress concentration.

[0081] like Fig. 9 The bearing 11-7 is a standard part, which is clamped by the stepped shaft 11-2 and the bearing retaining ring 11-4 and is fixed with only one nut, which is convenient for disassembly and replacement.

[0082] As shown in Fig. 4, the point where the bearing 11-7 contacts the clamping block 11-1 is the moving point, the connection point of the bottom frame spring is the fixed system, the connecting rod 9 is the moving system, the absolute motion direction is along the normal direction of the clamping block 11-1 inclined surface groove, the relative motion is along the normal direction of the clamping block 11-1 protrusion, the involved motion is in the vertical downward direction, and the acceleration direction is along the direction of each force, forming a force vector triangle. At the same time, the inclined surface angle is reasonably designed, and it is calculated from the force balance relationship that it is within the locking range at this time.

[0083] During the recovery phase after ground testing:

[0084] After the ground technicians complete the hatch cover test, they close the hatch cover 17. The double-pass hexagonal copper column 4 is subjected to the downward pressure of the hatch cover 17, and the screw 5 drives the nut 6 and the gasket 7 to move downward, so that the spring compression spring 8 is compressed. At the same time, the connecting rod 9 and the fixing seat 11-3 move downward together and drive the bearing to rotate. The bearing 11-7 presses down the clamping block 11-1 to make it tilt. At this time, the internal cubic satellite has been taken out and the spring compression spring 8 is in a compressed state.

[0085] After the hatch cover test is completed, if no more tests are performed within a certain period of time, the double-pass hexagonal copper column 4 can be removed. At this time, the flip cover is closed, and the spring compression spring 8 will not be compressed, so its life can be extended to a certain extent.

[0086] like Figure 7 The non-threaded section of the screw 5 surface is polished to reduce the friction between the screw 5 and the spring support block 10.

[0087] The working principle of the present invention is:

[0088] When the flap is closed, the double-pass hexagonal copper column is subjected to downward pressure from the top cover, and the screw drives the nut and gasket downward, compressing the spring. At the same time, the clamping link and the clamping block fixed seat move downward together and drive the bearing to rotate. The bearing presses the clamping block downward, causing it to tilt, and produces pressure on the cubic star in the X and Z directions. The structure is symmetrical, and all four parts can produce clamping force to compensate for the gap between the cubic star and the slide rail. When the flap is opened, the spring compression spring relaxes, the bearing moves upward along the groove slope of the clamping block, the clamping block is retracted, and a gap is created between it and the cubic star. The double-pass hexagonal copper column pushes upward, and the cubic star can be ejected safely.

Claims

1. A cubic satellite separation gap compensation mechanism, characterized in that: It includes a guide rail, a single-head stud, a stop frame, a double-pass hexagonal copper column, a screw, a nut, a gasket, a spring compression spring, a connecting rod, a spring support block, a clamping block, a stepped shaft, a fixed seat, a bearing retaining ring, a gasket, a nut, and a bearing; the stud assembly includes a double-pass hexagonal copper column, a screw, a nut, a gasket, and a compression spring, which passes through the corresponding circular holes of the top frame and the bottom frame, and the double-pass hexagonal copper column is installed on the upper end of the screw and contacts the hatch cover through the corresponding circular hole of the top frame. The double-pass hexagonal copper column is compressed when the hatch cover is closed, and is released when the hatch cover is opened; the double-pass hexagonal copper column, a single nut, a spring support block, a double nut, a gasket, a spring compression spring, and a spring support block are installed on the screw in sequence; The connecting rod is provided with a spring support block, the connecting rod and the spring support block are fastened by countersunk screws, and the connecting rod and the star clamping assembly are fastened by screws; The spring support block is provided with a through hole, and the screw moves in the through hole during the opening and closing of the hatch cover. At the same time, the spring support block, the nut and the gasket jointly limit the stroke of the spring compression spring. The distance between the nut and the spring support block is adjusted according to the mass of the satellite and the working conditions to which it is subjected, and the size of the clamping force on the cube satellite is adjusted; the spring support block is a triangular structure; The star clamping assembly comprises a clamping block, a stepped shaft, a fixed seat, a bearing retaining ring, a gasket, a nut and a bearing. The clamping block passes through the slot of the guide rail, and the stepped shaft passes through one side of the fixed seat, the bearing, the bearing retaining ring, the other side of the fixed seat and the gasket in sequence, and is finally fastened by the nut; an inclined groove is provided inside the clamping block, and the bearing rotates in the inclined groove; a protruding structure is provided outwardly of the clamping block, and the protruding structure passes through the slot of the guide rail to clamp the cubic star; a countersunk hole is provided on the fixed seat to limit the axial position of the stepped shaft, and the other end of the fixed seat is axially limited by the nut; the stepped shaft is provided with a shaft shoulder, which fits with the inner ring of the bearing after passing through the countersunk hole of the fixed seat, so that the bearing rotates normally; The double-pass hexagonal copper column is connected to the screw rod by threads, and a nut is installed at the bottom to position the double-pass hexagonal copper column. The hatch cover is a flip cover, which is located at the top of the entire mechanism and is provided with a countersunk hole and a gap, so that the double-pass hexagonal copper column can be tightened when the flip cover is closed; the spring support block is connected to the connecting rod by screws, and the screw rod passes through the through hole of the spring support block to position the screw rod; the clamping block is in contact with the bearing, and the stepped shaft clamps and positions the bearing by a nut and a bearing retaining ring to limit the movement of the bearing in the directions of both sides of the inclined surface of the clamping block; the clamping retaining frame is fixedly connected to the clamping block fixing seat by screws.

2. The cubic satellite separation gap compensation mechanism according to claim 1, characterized in that: The guide rail is provided with a slot hole, so that the clamping block passes through and is pressed against the satellite load-bearing frame; the guide assembly includes a top frame, a middle frame, a bottom frame, and a guide block. The top frame, the middle frame, and the bottom frame are fastened to the guide rail by screws. The guide block is installed on the middle frame to provide guiding and limiting functions when the connecting rod moves.

3. The cubic satellite separation gap compensation mechanism according to claim 2, characterized in that: The single-head stud is connected to the side skin by screws, and the other end is connected to the slide rail; the baffle frame is fixed to the front skin and the side skin by screws, and the other side is connected to the guide slide rail by screws.

4. The cubic satellite separation gap compensation mechanism according to claim 3, characterized in that: The spring support block is fixedly connected to the connecting rod, and is provided with threaded hole 1 and threaded hole 2, which are threaded holes matching with the connecting rod. The spring support block is provided with a through hole, which is a through hole matching with the screw rod, and there is a gap between the spring support block and the screw rod.

5. The cubic satellite separation gap compensation mechanism according to claim 4, characterized in that: The clamping block is designed with a groove slope and has point contact with the bearing; the connecting rod is L-shaped and is provided with a first threaded hole, a third threaded hole, a fifth threaded hole, and a sixth threaded hole for connecting to the threaded hole of the spring support block.

6. The cubic satellite separation gap compensation mechanism according to claim 5, characterized in that: The bearing is clamped by a stepped shaft and a bearing retaining ring and is fixed with only one nut; the point where the bearing contacts the clamping block is the moving point, the connection point of the bottom frame spring is the fixed system, the connecting rod is the moving system, the absolute motion direction is along the normal direction of the inclined groove of the clamping block, the relative motion is along the normal direction of the protrusion of the clamping block, the involved motion is in the vertical downward direction, and the acceleration direction is along the direction of each force, forming a force vector triangle.

Images