Connecting rod configuration separation mechanism for pressing and releasing stacked satellite assembly

Abstract

The invention relates to a connecting rod configuration separation mechanism for pressing and releasing a stacked satellite assembly, and belongs to the technical field of spaceflight separation mechanisms, the connecting rod configuration separation mechanism comprises a stacking device and pressing separation devices, the stacking device is installed on the corner of each satellite of the stacked satellite assembly, each pressing separation device comprises a pressing mechanism and a rotating mechanism, and the rotating mechanism is installed on the stacking device. The pressing mechanisms are installed on the stacking device of the top satellite, the rotating mechanism is installed on the stacking device of the bottom satellite, the satellites are sequentially stacked through the stacking devices on the corners to form a stacked satellite combination, each pressing mechanism comprises two pressing rods, the pressing mechanisms are connected with the rotating mechanism through the two pressing rods, and the rotating mechanism is connected with the rotating mechanism through the two pressing rods. According to the mechanism, reliable compression connection of a plurality of stacked satellites can be achieved, the action of the mechanism is released from constraint during separation, separation of the stacked satellites is achieved, and the mechanism has the advantages of being simple in structure, large in bearing capacity, small in separation impact, large in separation margin and the like.

Description

TECHNICAL FIELD

[0001] The present application relates to a kind of connecting rod configuration separation mechanism for the compression and release of stacked satellite combination, belong to aerospace separation mechanism technical field. BACKGROUND

[0002] In recent years, the launch demand of stacked satellite is increasing, and through the launch of multi-satellite stacked combination, the space utilization rate of rocket fairing can be improved, the launch cost can be reduced, and the launch efficiency can be improved.

[0003] Domestic and foreign researches on the compression and separation technology of stacked satellite combination have been carried out. The compression of stacked satellite generally adopts the form of threaded pre-tightening. When unlocking and separating, the unlocking is generally realized by pyrotechnic separation device or complex transmission mechanism. When unlocking, the compression force is released instantaneously, and the unlocking impact is large. After unlocking, the lateral impulse is generally provided by spring or pusher to drive the mechanism to expand outward. In order to ensure the outward expansion speed, a large spring or push device is needed to provide sufficient impulse, and the composition is relatively complex, the energy utilization rate is low, and the separation margin is small. Therefore, it is urgent to develop a separation mechanism with micro-impact, high reliability and high efficiency. SUMMARY

[0004] The technical problem solved by the present application is to meet the launch demand of stacked satellite, realize reliable compression and unlocking and separation after entering orbit in the launch process of stacked satellite, and provide a connecting rod configuration separation mechanism for the compression and release of stacked satellite combination. The mechanism can realize reliable compression connection of multiple stacked satellites, and when separating, the mechanism is released from constraint to realize the separation of stacked satellite, which has the advantages of simple structure, large carrying capacity, small separation impact and large separation margin.

[0005] The technical solution adopted by the present application is as follows:

[0006] The connecting rod configuration separation mechanism for the compression and release of stacked satellite combination includes n×m stacking devices and m compression and separation devices. The stacked satellite combination includes n satellites, each satellite includes m corners, the n×m stacking devices are respectively installed on the corners of each satellite, each compression and separation device includes a compression mechanism and a rotating mechanism, the compression mechanism is installed on the stacking device of the top satellite of the stacked satellite combination, the rotating mechanism is installed on the stacking device of the bottom satellite of the stacked satellite combination, the n satellites are stacked in turn to form the stacked satellite combination through the stacking devices on each corner, each compression mechanism includes two compression rods, the compression mechanism is connected with the rotating mechanism through the two compression rods to limit the stacked satellite combination, the compression and separation device is used for compressing and unlocking and separating the stacked satellite combination, and the rotating mechanism is used for realizing one-way rotation of the compression rod when unlocking and separating, wherein n and m are positive integers greater than or equal to 2.

[0007] In the above-mentioned connecting rod configuration separation mechanism for compressing and releasing the stacked satellite assembly, the compressing mechanism includes a screw, a pre-tightening nut, a cross beam, a limiting nut, a compression flap, a connecting beam, a satellite compression seat and a separator, wherein the screw passes through the through holes at both ends of the cross beam and is tightened and fixed by the pre-tightening nut and the limiting nut located on the upper and lower surfaces of the cross beam through hole; the screw is axially connected to the compression rod, the compression flap is connected to the cross beam and can rotate around the cross beam, and the bottom of the compression flap is stuck in the groove corresponding to the satellite compression seat; the connecting beam is connected to the compression flap, and is connected to the satellite compression seat through a separator; the satellite compression seat is axially fixed on the stacking device of the top satellite.

[0008] In the above-mentioned connecting rod configuration separation mechanism for compressing and releasing the stacked satellite assembly, the connecting beam includes a horizontal beam and a vertical beam connecting the two ends of the horizontal beam, wherein the end of the vertical beam is connected to the compression flap, and the horizontal beam is connected to the satellite compression seat through a separator.

[0009] In the above-mentioned connecting rod configuration separation mechanism for compressing and releasing the stacked satellite assembly, the angle a between the horizontal beam and the vertical beam satisfies: 90°<a<180°.

[0010] In the above-mentioned connecting rod configuration separation mechanism for compressing and releasing the stacked satellite assembly, the compression flap includes a columnar structure at the top and a variable thickness flat plate structure connected to the columnar structure. The crossbeam passes through the through hole inside the columnar structure, so that the compression flap can rotate around the crossbeam. The thickness of the variable thickness flat plate structure gradually decreases from top to bottom, and the bottom is stuck in the long strip groove corresponding to the satellite compression seat; two support ears are provided on the variable thickness flat plate structure of the compression flap, which are hinged to the vertical beam of the connecting beam through the support ears.

[0011] In the above-mentioned connecting rod configuration separation mechanism for compressing and releasing the stacked satellite assembly, the separator is a point-type separator, specifically a cylindrical structure, which passes through the crossbeam of the connecting beam and the side wall of the satellite compression seat to connect the connecting beam and the satellite compression seat respectively; when unlocking and separating, the point-type separator is energized and unlocked, releasing the connection constraint between the connecting beam and the satellite compression seat.

[0012] In the above-mentioned connecting rod configuration separation mechanism for compressing and releasing the stacked satellite assembly, the compressing mechanism further includes reinforcing beams, and a plurality of reinforcing beams are provided between the two compressing rods to connect the two compressing rods into a whole.

[0013] In the above-mentioned connecting rod configuration separation mechanism for compressing and releasing the stacked satellite assembly, the rotation mechanism includes a root hinge, a base and a rotating shaft, wherein the root hinge and the base are hinged through the rotating shaft and can rotate around the rotating shaft in the expansion direction, the root hinge and the clamping rod are axially connected, and the base is connected to the stacking device of the bottom satellite.

[0014] In the above-mentioned connecting rod configuration separation mechanism for compressing and releasing the stacked satellite assembly, the rotation mechanism also includes a ratchet and a spring. A ratchet is provided on the root hinge, and the ratchet is connected to the base through a sliding pair. The spring provides pre-pressure to make the ratchet close to the root hinge. When unlocking and separating, one-way rotation is achieved through the cooperation between the root hinge and the ratchet, ensuring that the compression and separation device only rotates along the expansion direction during the expansion process.

[0015] In the above-mentioned connecting rod configuration separation mechanism for compressing and releasing the stacked satellite assembly, the stacking device is a stacking column, and the two end surfaces of the stacking column are provided with positioning cone surfaces to realize the positioning and shear resistance functions of the satellite stacking surface.

[0016] In the above-mentioned connecting rod configuration separation mechanism for compressing and releasing the stacked satellite assembly, the satellite is a flat plate structure comprising four corners, with a stacking column mounted on each corner.

[0017] In the above-mentioned connecting rod configuration separation mechanism for compressing and releasing the stacked satellite assembly, the compression flap, the connecting beam and the satellite compression seat form a triangular structure in the compression state. The compression rod transmits the compression force to the stacking device through the triangular structure. By controlling the angle of the force line, the component force formed by the compression flap is much larger than the component force formed by the compression force in the connecting beam, and the large load-bearing capacity is achieved by relying on the axial compression deformation of the compression flap.

[0018] The method for implementing the connecting rod configuration separation mechanism for compressing and releasing the stacked satellite assembly includes:

[0019] During compression, the pre-tightening force is transmitted to the satellite through the force transmission path of pre-tightening nut-crossbeam-compression flap-satellite compression seat-stacking device to achieve compression;

[0020] When unlocking and separating, the separation mechanism is energized and unlocked, releasing the connection constraint between the connecting beam and the satellite compression seat. The compression force of the stacking device and the tension of the compression rod form a driving torque on the compression flap, driving the compression flap to accelerate outward with the bottom as the rotation axis, and driving the compression rod to evert through the kinematic relationship of the connecting rod, converting the compression strain energy into kinetic energy of the compression rod's deployment, releasing the mechanism's compression effect on the satellite, and achieving unlocking and deployment.

[0021] Compared with the prior art, the present invention has at least the following beneficial effects:

[0022] (1) An embodiment of the present invention provides a connecting rod configuration separation mechanism for compressing and releasing a stacked satellite assembly. The mechanism can realize reliable compression and connection of multiple stacked satellites. During separation, the mechanism action releases the constraints, thereby realizing separation of the stacked satellites. The mechanism has the advantages of simple structure, large load-bearing capacity, small separation impact, and large separation margin.

[0023] (2) An embodiment of the present invention provides a connecting rod configuration separation mechanism for compacting and releasing a stacked satellite assembly. It adopts a modular design and can be equipped with multiple separation mechanisms according to the actual number and layout of compaction points to achieve reliable compaction and separation of multiple layers of satellites. By changing the length of the compaction rod, it can adapt to the compaction and separation of satellites with different layers.

[0024] (3) The embodiment of the present invention provides a connecting rod configuration separation mechanism for compressing and releasing a stacked satellite assembly. Through the optimized design of the structure, a part of the deformation energy of the initial compression of the stacking device and the compression rod is preferably converted into kinetic energy for the swinging and unfolding of the mechanism through the transmission of the connecting rod, thereby improving the separation margin; the impulse of the lateral movement is provided through the transmission of the connecting rod, eliminating the lateral thrust device and simplifying the overall solution; the time for releasing the deformation energy is extended through the transmission of the connecting rod, further reducing the impact caused by the energy release, and realizing the function of reducing the impact; through the transmission design of the connecting rod, it is ensured that the movement of satellite separation is in the same direction as the unfolding movement of the separation mechanism, and the satellite separation movement is beneficial to the unfolding of the mechanism without causing scratches or interference, thereby ensuring the reliability and safety of the separation.

[0025] (4) An embodiment of the present invention provides a connecting rod configuration separation mechanism for compressing and releasing a stacked satellite assembly. Preferably, by designing the angle between the force lines of the compressing flap, the connecting beam and the compressing rod, the magnitude of the components of the compressing force on different parts can be controlled, ensuring that most of the components of the compressing force are transmitted to the axial direction of the compressing flap, and relying on the axial compression of the compressing flap to achieve load-bearing, thereby ensuring a large load-bearing margin and reducing the load on the point-type separation mechanism, thereby reducing the load-bearing requirement and unlocking impact of the point-type separation mechanism; and a one-way rotating hinge design is adopted to prevent the compressing rod from rebounding, avoid collision between the compressing rod and the satellite, and ensure the safety of satellite separation. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 Schematic diagram of the assembly of the stacked satellite assembly, the stacking device, and the pressing and separating device in an embodiment of the present invention;

[0027] Figure 2 Schematic diagram of the stacked satellite structure in an embodiment of the present invention;

[0028] Figure 3 is a schematic cross-sectional view of a stacked column according to an embodiment of the present invention;

[0029] Figure 4 Schematic diagram of the compression and separation device in an embodiment of the present invention;

[0030] Figure 5 Schematic diagram of root locking of the rotating mechanism in an embodiment of the present invention;

[0031] Figure 6 Schematic diagram of the compression and expansion process of the separation mechanism in an embodiment of the present invention;

[0032] Screw 1-1, pre-tightening nut 1-2, crossbeam 1-3, limit nut 1-4, clamping flap 1-5, connecting beam 1-6, satellite clamping seat 1-7, separator 1-8, reinforcing crossbeam 1-9, clamping rod 1-10, root hinge 1-11, base 1-12, rotating shaft 1-13, ratchet 1-14, spring 1-15. DETAILED DESCRIPTION

[0033] The present invention will be described in further detail below with reference to the accompanying drawings and specific embodiments:

[0034] like Figure 1 As shown, the connecting rod configuration separation mechanism for compacting and releasing a stacked satellite assembly provided by an embodiment of the present invention includes n×m stacking devices 2-1 and m compacting and separating devices 1. The stacked satellite assembly includes n satellites 2, each satellite 2 includes m corners, and n×m stacking devices are respectively installed on the corners of each satellite 2. Each compacting and separating device 1 includes a compacting mechanism and a rotating mechanism. The compacting mechanism is installed on the stacking device of the top satellite of the stacked satellite assembly, and the rotating mechanism is installed on the stacking device of the bottom satellite of the stacked satellite assembly. The n satellites are stacked in sequence through the stacking device on each corner to form a stacked satellite assembly. Each compacting mechanism includes two compacting rods 1-10. The compacting mechanism is connected to the rotating mechanism through the two compacting rods 1-10 to limit the stacked satellite assembly. A number of reinforcing beams 1-9 are arranged between the two compacting rods 1-10 to connect the two compacting rods 1-10 into a whole to improve the overall stiffness and rotation synchronization of the compacting rod 1-10. The compression and separation device 1 is used to compress and unlock the stacked satellite assembly. A rotation mechanism is used to achieve unidirectional rotation of the compression rods 1-10 during unlocking and separation. The bottom of the unlocking and separation mechanism 1 is fixed to the satellite bracket or tooling. After the stacked satellites 2 are stacked and assembled, they are compressed and connected by multiple separation mechanisms 1 to form a whole unit for launch.

[0035] like Figure 4As shown, the compacting and separating device 1 in the embodiment of the present application comprises a compacting mechanism and a rotating mechanism. The compacting mechanism comprises a screw rod 1-1, a pre-tightening nut 1-2, a cross beam 1-3, a limiting nut 1-4, a compacting flap 1-5, a connecting beam 1-6, a satellite compacting seat 1-7, and a separator 1-8. The screw rod 1-1 passes through the through holes reserved at both ends of the cross beam 1-3, and is pre-tightened by the threaded connection with the pre-tightening nut 1-2. The limiting nut 1-4 is located below the cross beam 1-3, and the cross beam 1-3 is fixed by the limiting nut 1-4 and the pre-tightening nut 1-2 from above and below. The screw rod 1-1 and the compacting rod 1-10 are axially connected by screwing or gluing. The compacting flap 1-5 comprises a cylindrical structure at the top and a variable-thickness flat plate structure connected with the cylindrical structure. The cross beam 1-3 passes through the through hole in the cylindrical structure, so that the compacting flap 1-5 can rotate around the cross beam 1-3. The thickness of the variable-thickness flat plate structure gradually decreases from top to bottom, and the bottom is clamped in the corresponding long slot of the satellite compacting seat 1-7. Two lugs are arranged on the variable-thickness flat plate structure of the compacting flap 1-5, and the lugs are hinged to the vertical beam of the connecting beam 1-6. In this embodiment, the compacting flap 1-5 can be designed in an upper and lower split type. The upper part is part of a cylinder, the lower part is another part of a cylinder, and the variable-thickness flat plate structure part. The upper and lower parts are connected with the cross beam 1-3 by clamping the cross beam 1-3. In the clamped state, it can rotate around the cross beam 1-3, and the lower end of the variable-thickness flat plate structure is clamped in the corresponding slot of the satellite compacting seat 1-7.

[0036] The connecting beam 1-6 comprises a cross beam and vertical beams connecting both ends of the cross beam. The end of the vertical beam is connected to the compacting flap 1-5 through the lug, and the cross beam is connected to the satellite compacting seat 1-7 through the separator 1-8. In this embodiment, the included angle between the cross beam and the vertical beam is greater than 90° and less than 180°. In this embodiment, the separator 1-8 is a point-type separator, which is a cylindrical structure and connects the connecting beam 1-6 and the satellite compacting seat 1-7 by passing through the cross beam of the connecting beam 1-6 and the side wall of the satellite compacting seat 1-7, respectively. When unlocking and separating, the point-type separator 1-8 is energized to unlock and release the connection constraint between the connecting beam 1-6 and the satellite compacting seat 1-7.

[0037] The satellite compacting seat 1-7 is axially fixed on the stacking column 2-1 of the top satellite and is connected by screwing or riveting. A plurality of reinforcing cross beams 1-9 are arranged between the two compacting rods 1-10, which connect the two compacting rods 1-10 into a whole to improve the overall stiffness and rotating synchronicity of the compacting rod 1-10.

[0038] As Figure 4As shown, the rotating mechanism includes a root hinge 1-11, a base 1-12, a rotating shaft 1-13, a ratchet 1-14 and a spring 1-15, wherein the root hinge 1-11 and the base 1-12 are hinged through the rotating shaft 1-13, can rotate in the unfolding direction around the rotating shaft 1-13, the root hinge 1-11 is axially connected with the pressing rod 1-10 through screwing or gluing, and the base 1-12 is connected with the stacking device of the bottom satellite.

[0039] As shown in the figure, Figure 5 The root hinge 1-11 is provided with the ratchet 1-14, the ratchet 1-14 is connected with the base 1-12 through a sliding pair, and the spring 1-15 provides a pre-pressure to ensure that the ratchet 1-14 can be tightly attached to the root hinge 1-11. During the unfolding process of the separation mechanism, the root hinge 1-11 and the ratchet 1-14 are matched to realize one-way rotation, so as to ensure that the mechanism can only rotate in the unfolding direction during the unfolding process, and prevent the mechanism from rebounding and colliding with the satellite.

[0040] As shown in the figure, Figure 2 In this embodiment, the stacked satellite 2 is a flat plate structure, and four stacking columns are installed at four corners of the satellite. Figure 3 As shown in the figure, the stacking column is designed with a positioning cone surface at both ends, which is used to realize the positioning and shearing resistance of the satellite stacking surface.

[0041] As shown in the figure, Figure 6 In this embodiment, the pressing process of the connecting rod configuration separation mechanism for pressing and releasing the stacked satellite assembly is as follows:

[0042] The unlocking separation mechanism 1 is connected with the satellite support or tool, the bottom satellite stacking column 2-1 is tightly attached to the base 1-12 through the taper surface, the stacked satellite 2 is stacked layer by layer, the satellite pressing seat 1-7 is axially fixed on the stacking column 2-1 of the top satellite and connected through a screw. The top ends of the two screw rods 1-1 pass through the two connecting holes pre-provided in the cross beam 1-3, and are connected and pre-tightened with the pre-tightening nut 1-2 through the external threads of the screw rod 1-1. The pre-tightening force is transmitted to the satellite 2 through the force transmission path of the pre-tightening nut 1-2-cross beam 1-3-pressing flap 1-5-satellite pressing seat 1-7-stacking column 2-1, so as to realize the pressing. As shown in the figure, Figure 6As shown, in the clamping state, the clamping flap 1-5, the connecting beam 1-6 and the satellite clamping seat 1-7 form a triangular structure, and the clamping rod 1-10 transmits the clamping force to the satellite stacking column 2-1 through the triangular structure. The force line angle between the clamping flap 1-5 and the clamping rod 1-10 is designed to be a smaller value, ensuring that the component force formed by the clamping force on the clamping flap 1-5 is much larger than the component force formed by the clamping force on the connecting beam 1-6. The large load-bearing capacity is achieved by relying on the axial compression deformation of the clamping flap 1-5. The connecting beam 1-6 and the satellite clamping seat 1-7 are connected by a point-type separation mechanism 1-8. The component force formed by the clamping force on the connecting beam 1-6 is borne by the point-type separation mechanism 1-8. Since the component force formed by the clamping force on the connecting beam 1-6 is relatively small, a small-load point-type separation mechanism 1-8 can be selected for connection to reduce the separation impact.

[0043] like Figure 6 As shown, the unlocking and separation process of the connecting rod configuration separation mechanism for compressing and releasing the stacked satellite assembly in the embodiment of the present invention is as follows:

[0044] The point-type separation mechanism 1-8 is powered on and unlocked, releasing the connection constraint between the connecting beam 1-6 and the satellite clamping seat 1-7. The clamping force of the satellite stacking column 2-1 and the tension of the clamping rod 1-10 form a driving torque on the clamping flap 1-5, driving the clamping flap 1-5 to rotate outward with the bottom as the axis of rotation. The clamping rod 1-10 is driven outward through the kinematic relationship of the connecting rod, converting the strain energy of the clamping into the kinetic energy of the clamping rod's deployment. At the same time, the stacked satellite 2 begins to separate, and the satellite stacking column 2-1 moves axially under the action of the separation spring, which can continue to push the clamping flap 1-5 and the clamping rod 1-10 outward, which helps to separate and deploy the clamping separation mechanism. During the deployment process, the clamping rod 1-10 can be rotated in one direction through the cooperation of the root hinge 1-11 and the ratchet 1-14, ensuring that the mechanism can only rotate in the deployment direction during deployment, preventing the mechanism from rebounding and hitting the satellite, affecting the satellite separation posture.

[0045] The embodiment of the present invention adopts a modular design and can be equipped with multiple separation mechanisms according to the actual number and layout of compression points to achieve reliable compression and separation of multiple layers of satellites. By changing the length of the compression rod, it can adapt to the compression and separation of satellites with different numbers of layers.

[0046] In the embodiment of the present invention, a portion of the deformation energy of the initial compression of the stacking columns and the compression rod is converted into kinetic energy for the swinging and unfolding of the mechanism through the transmission of the connecting rod, thereby improving the separation margin.

[0047] The embodiment of the present invention provides the impulse of lateral movement through the transmission of the connecting rod, eliminating the need for a lateral pushing device and simplifying the overall solution.

[0048] The embodiment of the present application prolongs the time of deformation energy release through the transmission of the connecting rod, reduces the impact generated by energy release, and realizes the function of impact reduction.

[0049] The embodiment of the present application guarantees that the movement of satellite separation is the same as the direction of the unfolding movement of the separation mechanism through the transmission design of the connecting rod, and the satellite separation movement is beneficial to the unfolding of the mechanism, and will not produce scratching or interference, thereby guaranteeing the reliability and safety of the separation.

[0050] The embodiment of the present application can control the force size of the compression force on different parts through the design of the included angle of the force line between the compression turning plate, the connecting beam and the compression rod, guarantees that most of the force of the compression force is transmitted to the axial direction of the compression turning plate, relies on the axial compression of the compression turning plate to realize the bearing, guarantees a large bearing margin, simultaneously reduces the load received by the point type separation mechanism, and reduces the bearing demand and unlocking impact of the point type separation mechanism.

[0051] The embodiment of the present application adopts the design of one-way rotation hinge, prevents the rebound of the compression rod, avoids the collision between the compression rod and the satellite, and guarantees the safety of the satellite separation.

[0052] The above is only the best specific embodiment of the present application, but the protection scope of the present application is not limited to this, any person skilled in the art can easily think of the changes or replacements within the technical range disclosed by the present application, which should be covered in the protection scope of the present application.

[0053] The contents not described in detail in the specification of the present application belong to the known technology of the person skilled in the art.

Claims

1. A connecting rod configuration separation mechanism for compacting and releasing a stacked satellite assembly, characterized in that: The invention comprises n×m stacking devices (2-1) and m pressing and separating devices (1), wherein the stacked satellite assembly comprises n satellites (2), each satellite (2) comprises m corners, and the n×m stacking devices are respectively installed on the corners of each satellite (2). Each pressing and separating device (1) comprises a pressing mechanism and a rotating mechanism, wherein the pressing mechanism is installed on the stacking device of the satellite at the top of the stacked satellite assembly, and the rotating mechanism is installed on the stacking device of the satellite at the bottom of the stacked satellite assembly. The n satellites are stacked in sequence through the stacking devices at each corner to form a stacked satellite assembly. Each pressing mechanism comprises two pressing rods (1-10), and the pressing mechanism is connected to the rotating mechanism through the two pressing rods (1-10) to limit the stacked satellite assembly. The pressing and separating device (1) is used to press and unlock and separate the stacked satellite assembly, and the rotating mechanism is used to realize unidirectional rotation of the pressing rod (1-10) during unlocking and separation, wherein n and m are both positive integers greater than or equal to 2.

2. The connecting rod configuration separation mechanism for compressing and releasing a stacked satellite assembly according to claim 1, characterized in that: The pressing mechanism comprises a screw (1-1), a pre-tightening nut (1-2), a crossbeam (1-3), a limiting nut (1-4), a pressing flap (1-5), a connecting beam (1-6), a satellite pressing seat (1-7) and a separator (1-8), wherein the screw (1-1) passes through the through holes at both ends of the crossbeam (1-3) and is tightened and fixed by the pre-tightening nut (1-2) and the limiting nut (1-4) located on the upper and lower surfaces of the through hole of the crossbeam (1-3); the screw ( The satellite pressing seat (1-7) is axially connected to the satellite pressing seat (1-7); the pressing flap (1-5) is connected to the crossbeam (1-3) and can rotate around the crossbeam (1-3); the bottom of the pressing flap (1-5) is stuck in the groove corresponding to the satellite pressing seat (1-7); the connecting beam (1-6) is connected to the pressing flap (1-5) and is connected to the satellite pressing seat (1-7) through a separator (1-8); the satellite pressing seat (1-7) is axially fixed on the stacking device of the top satellite.

3. The connecting rod configuration separation mechanism for compressing and releasing a stacked satellite assembly according to claim 2, characterized in that: The connecting beam (1-6) comprises a horizontal beam and vertical beams connecting the two ends of the horizontal beam, wherein the ends of the vertical beams are connected to the compression flaps (1-5), and the horizontal beams are connected to the satellite compression seats (1-7) via separators (1-8).

4. The connecting rod configuration separation mechanism for compressing and releasing a stacked satellite assembly according to claim 3, characterized in that: The included angle a between the horizontal beam and the vertical beam satisfies: 90°<a<180°.

5. The connecting rod configuration separation mechanism for compressing and releasing a stacked satellite assembly according to claim 3, characterized in that: The compression flap (1-5) comprises a columnar structure at the top and a variable thickness flat plate structure connected to the columnar structure. The crossbeam (1-3) passes through the through hole inside the columnar structure, so that the compression flap (1-5) can rotate around the crossbeam (1-3). The thickness of the variable thickness flat plate structure gradually decreases from top to bottom, and the bottom is stuck in the long strip groove corresponding to the satellite compression seat (1-7); two lugs are provided on the variable thickness flat plate structure of the compression flap (1-5), which are hinged to the vertical beam of the connecting beam (1-6) through the lugs.

6. The connecting rod configuration separation mechanism for compressing and releasing a stacked satellite assembly according to claim 3, characterized in that: The separator (1-8) is a point-type separator, specifically a cylindrical structure, which passes through the crossbeam of the connecting beam (1-6) and the side wall of the satellite pressing seat (1-7) to connect the connecting beam (1-6) and the satellite pressing seat (1-7); when unlocking and separating, the point-type separator (1-8) is powered on and unlocked, releasing the connection constraint between the connecting beam (1-6) and the satellite pressing seat (1-7).

7. The connecting rod configuration separation mechanism for compressing and releasing a stacked satellite assembly according to claim 2, characterized in that: The pressing mechanism further comprises a reinforcing crossbeam (1-9). A plurality of reinforcing crossbeams (1-9) are arranged between the two pressing rods (1-10) to connect the two pressing rods (1-10) into a whole.

8. The connecting rod configuration separation mechanism for compressing and releasing a stacked satellite assembly according to claim 1, characterized in that: The rotating mechanism comprises a root hinge (1-11), a base (1-12) and a rotating shaft (1-13), wherein the root hinge (1-11) and the base (1-12) are hingedly connected via the rotating shaft (1-13) and can rotate in an unfolding direction around the rotating shaft (1-13); the root hinge (1-11) and the pressing rod (1-10) are axially connected; and the base (1-12) is connected to the stacking device (2-1) of the bottom satellite.

9. The connecting rod configuration separation mechanism for compressing and releasing a stacked satellite assembly according to claim 8, characterized in that: The rotation mechanism further comprises a ratchet (1-14) and a spring (1-15); the ratchet (1-14) is provided on the root hinge (1-11); the ratchet (1-14) is connected to the base (1-12) via a sliding pair; the spring (1-15) provides pre-pressure to make the ratchet (1-14) close to the root hinge (1-11); when unlocking and separating, the root hinge (1-11) cooperates with the ratchet (1-14) to achieve unidirectional rotation, thereby ensuring that the compression and separation device (1) rotates only in the expansion direction during the expansion process.

10. The connecting rod configuration separation mechanism for compressing and releasing a stacked satellite assembly according to claim 1, characterized in that: The stacking device (2-1) is a stacking column, and positioning cone surfaces are provided on both end surfaces of the stacking column to achieve positioning and shear resistance functions of the satellite stacking surface.

11. The connecting rod configuration separation mechanism for compressing and releasing a stacked satellite assembly according to claim 10, characterized in that: The satellite (2) is a flat plate structure comprising four corners, with a stacking column mounted on each corner.

12. The connecting rod configuration separation mechanism for compressing and releasing a stacked satellite assembly according to claim 2, characterized in that: In the compressed state, the compression flap (1-5), the connecting beam (1-6) and the satellite compression seat (1-7) form a triangular structure. The compression rod (1-10) transmits the compression force to the stacking device (2-1) through the triangular structure. By controlling the angle of the force lines, the component force formed by the compression force on the compression flap (1-5) is much greater than the component force formed by the compression force on the connecting beam (1-6). The large load-bearing capacity is achieved by relying on the axial compression deformation of the compression flap (1-5).

13. The method for implementing the connecting rod configuration separation mechanism for compressing and releasing a stacked satellite assembly according to claim 2, characterized in that: include: During compression, the pre-tightening force is transmitted to the satellite (2) through the force transmission path of the pre-tightening nut (1-2)-crossbeam (1-3)-compression flap (1-5)-satellite compression seat (1-7)-stack device (2-1), thereby achieving compression; When unlocking and separating, the separation mechanism (1-8) is energized and unlocked, releasing the connection constraint between the connecting beam (1-6) and the satellite pressing seat (1-7), and the pressing force of the stacking device (2-1) and the pulling force of the pressing rod (1-10) form a driving torque on the pressing flap (1-5), driving the pressing flap (1-5) to rotate outward with the bottom as the rotation axis, and driving the pressing rod (1-10) to turn outward through the kinematic relationship of the connecting rod, converting the strain energy of the pressing into the kinetic energy of the pressing rod to expand, releasing the pressing effect of the mechanism on the satellite, and realizing unlocking and expansion.

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