Pinasat light low-impact satellite-rocket separation device

Abstract

The application discloses a Picosatellite light low-impact satellite-rocket separation device, which comprises a locking seat module, an unlocking function module and a separation power module; the locking seat module comprises a carrying end separation base, a satellite end separation base and a measurement socket base; the unlocking function module comprises an explosive bolt and an explosive bolt protection cover; and the separation power module comprises a separation push rod, a separation push rod sleeve and a separation spring. The carrying end separation base is connected with a rocket, the satellite end separation base is connected with a satellite, the carrying end separation base and the satellite end separation base are connected through an explosive bolt or a process bolt, the process bolt is only used during transportation, and the explosive bolt is used for connecting during launching; the explosive bolt is started by a circuit when separation starts, the explosive bolt protection cover is used for slowing down the explosion impact and collecting the cut-off part of the explosive bolt; and the separation spring is installed between the separation push rod and the separation push rod sleeve, and the separation push rod is driven by the separation spring to realize satellite-rocket separation after the explosive bolt is detonated.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of aerospace, and particularly relates to a Picosatellite light low-impact satellite-rocket separation device. BACKGROUND

[0002] With the attention and investment of the state in the field of aerospace in recent years, the frequency of space launch missions is continuously improving, and the satellite-rocket separation process is an important stage to ensure the stable separation of satellites into the predetermined orbit, and the satellite-rocket separation device plays a key role. With the continuous refinement of semiconductor industry processes, man-made satellites are also continuously improving the integration and precision of internal electronic devices, greatly reducing the volume and mass of the satellite, but also increasing the requirements for separation precision and reliability of the satellite-rocket separation device.

[0003] The main functions of the satellite-rocket separation device include providing the connection strength of the satellite and the launch vehicle, transmitting signals between the satellite and the launch vehicle, igniting the explosive to start separation, unlocking the power mechanism to realize kinetic energy transmission, etc. The design of the satellite-rocket separation device usually needs to consider the requirements of simple structure, light weight, high structural strength, high reliability, strong robustness, low pollution, etc.

[0004] The commonly used satellite-rocket separation device can be mainly divided into two categories: explosive and non-explosive. The explosive separation scheme is easy to produce a large impact, which has a great influence on the microsatellite and its internal precision instruments. The existing explosive separation scheme usually considers reducing the impact load in the structure design and material stacking, but it is easy to make the size of the separation mechanism larger, such as the four-point separation mechanism designed in the Chinese patent application with publication number CN108583940A, but its overall structure is larger. In addition, some explosive separation schemes do not have the design of recycling explosive bolt fragments, which will produce a small amount of space debris, such as the separation mechanism provided in the Chinese patent application with publication number CN104859870A, which does not design to recycle explosive bolt fragments.

[0005] The non-explosive separation scheme includes band-type locking, electromagnetic, hot knife, etc. Although it avoids the explosion impact, the cost is a large and complex structure design, such as the connecting rod band-type separation mechanism designed in the Chinese patent application with publication number CN111619831A, whose cross-sectional size is comparable to the satellite bottom surface, and the mass size is also correspondingly increased. For example, the rotating electromagnetic iron separation mechanism designed in the Chinese patent applications with publication numbers CN216734828U and CN114132535A, in addition to the power device in the separation direction, an electromagnetic unlocking device perpendicular to the separation direction is also added, the structure is relatively complex, which increases the maintenance difficulty and reduces the reliability during the launch process.

[0006] Therefore, how to reduce the impact of the shock of the initiation of the initiating explosive on the process of the separation of the satellite and the rocket by structural design and improve the reliability of the separation of the satellite and the rocket is a difficult problem to be solved in the separation scheme of the initiating explosive. SUMMARY

[0007] In view of the above, the present application provides a Picosatellite light low-impact satellite-rocket separation device, which reduces the volume and weight of the satellite-rocket separation device while ensuring the strength of the connection between the satellite and the rocket, reduces the impact load when the initiating explosive is initiated by designing the layout and installation of the initiating explosive, and further improves the separation accuracy and the reliability of the separation.

[0008] A Picosatellite light low-impact satellite-rocket separation device, comprising a locking seat module, an unlocking function module, and a separation power module, wherein:

[0009] The locking seat module is used to connect the satellite and the carrier rocket and provide installation positions for the unlocking function module and the separation power module;

[0010] The separation power module is installed on the locking seat module, and the locking seat module and the separation power module are each deployed with four sets, which are fixed on the four corners of the bottom of the satellite and then connected with the carrier rocket;

[0011] The unlocking function module is deployed with two sets, which are installed on the two sets of locking seat modules at opposite positions;

[0012] Before the separation of the satellite and the rocket, the locking seat module ensures the strength and reliability of the connection between the satellite and the rocket; after the satellite is put into orbit, the unlocking function module unlocks the limit, and the separation power module pushes the satellite bottom plate to realize the separation of the satellite and the rocket.

[0013] Further, the locking seat module comprises a carrier end separation base, a satellite end separation base, a separation device installation limiting plate, a measurement socket base, a process nut, a separation contact plate support, and a contact spring; one side of the satellite end separation base is connected with the satellite, and the other side is connected with the carrier end separation base; the separation device installation limiting plate is installed on the connecting structure of the carrier end separation base and the satellite end separation base to assist installation and positioning; the process nut is installed inside the carrier end separation base and the satellite end separation base to ensure the connection of the two during transportation, and the process nut will be removed after the docking of the satellite and the rocket is completed; the carrier end separation base is connected with the carrier rocket, the measurement socket base is connected with the carrier end separation base, a measurement socket is installed on the base to transmit control signals; the separation contact plate support is installed on the carrier end separation base, the contact spring is installed on the separation contact plate support, and the contact spring is in contact with the corresponding interface at the bottom of the satellite before the separation of the satellite and the rocket; one end of the contact spring is in communication with the internal signal path of the satellite, and the other end is connected with an aviation plug to be connected with a centralized test box of the carrier end (carrier rocket), thereby forming a power supply, telemetry, and signal transmission path from the centralized test box to the satellite.

[0014] Further, the unlocking function module includes a travel switch, a carrier end travel switch mounting box, a satellite end travel switch mounting box, an explosive bolt, an explosive bolt protective cover, a copper pad, a rubber pad, a honeycomb aluminum, a shock absorbing spring, a shock absorbing spring limiting washer, and a shock absorbing spring limiting sleeve; the travel switch is installed inside the carrier end travel switch mounting box and contacts the satellite end travel switch mounting box on the satellite end separation base, and the carrier end travel switch mounting box is installed on the carrier end separation base; the satellite end separation base has a through hole structure for installing the explosive bolt; the explosive bolt is arranged in the explosive bolt protective cover and is used for connecting the carrier end separation base and the satellite end separation base; the explosive bolt protective cover is installed on the corresponding satellite end separation base; the copper pad, the rubber pad, and the honeycomb aluminum are sequentially installed between the top of the explosive bolt protective cover and the top of the explosive bolt; and the shock absorbing spring is installed on the explosive bolt and is positioned and installed by the shock absorbing spring limiting washer and the shock absorbing spring limiting sleeve.

[0015] Further, the separation power module includes a separation push rod, a separation spring sleeve, a separation spring, a locking nut, and a push rod guide; the separation push rod and the separation spring sleeve have a limiting structure for fixing the installation position of the separation spring and ensuring that the separation spring does not fall off the separation power module during separation; the separation spring sleeve has a through hole structure for allowing the bottom of the separation push rod to pass through; the bottom of the separation push rod has a threaded mechanism with a certain length, which is screwed with the locking nut after passing through the bottom of the separation spring sleeve, thereby realizing compression and fixation of the separation spring; the separation spring is installed between the separation push rod and the separation push rod sleeve, and is driven by the separation spring to realize satellite-rocket separation after the initiation of the initiating explosive; the locking nut is mainly used during transportation and installation of the satellite-rocket separation device and needs to be unscrewed after the satellite and the carrier rocket are connected, and then the position of the separation spring is limited by the explosive bolt; the push rod guide is annular, the inner side of which is in interference fit with the separation push rod, and the outer side of which is in clearance fit with the inner side of the separation spring sleeve, thereby realizing the guiding effect of the separation push rod during separation.

[0016] Further, the satellite end travel switch mounting box also has a travel switch, so that the travel switches in the entire satellite-rocket separation device are installed in two groups in a diagonal manner, one group of travel switches belongs to the carrier end, and the other group of travel switches belongs to the satellite end; the two travel switches of the satellite end are used to transmit a separation signal to the inside of the satellite, and the two travel switches of the carrier end are used to transmit a separation signal to a measurement socket, which is connected to a controller of the carrier end through a cable to provide a separation signal to the carrier rocket.

[0017] Further, the separation contact plate support is fixed on the carrier end separation base and is used to install a contact spring, and the separation contact plate support has a hollow structure as a whole to reduce the mass.

[0018] Further, the carrier end separation base and the satellite end separation base are connected to form two planes and a columnar structure with a square cross section with two semicircular sectors removed, which reduces the mass while ensuring the strength and facilitates the tightening of the bolts during installation.

[0019] Further, the explosion bolt protection cover has a hollow cylindrical boss extending from a circular base, and a buffer structure is arranged in the interior of the explosion bolt protection cover to absorb the impact generated when the explosion bolt is detonated, and the space in the interior of the explosion bolt protection cover is used to accommodate the debris generated after the explosion bolt is detonated.

[0020] Further, the separation push rod has multiple functions, such as contact with the satellite and transmission of power, provision of a spring limiting installation position, guidance of the spring release direction, locking of the spring before separation, and the like, and has a structure of a circular sheet combined with a cylindrical screw rod, the top of the circular sheet is a hemisphere for contact with the bottom of the satellite and transmission of separation power, the bottom of the circular sheet has an annular groove for installation and limiting of the spring, the cylindrical screw rod and the inner hole of the separation spring sleeve jointly realize the guiding function of the spring separation process, and the bottom of the cylindrical screw rod is threaded for installation of a locking nut to lock the separation spring during transportation and storage of the satellite-rocket separation device.

[0021] Further, the separation spring sleeve has a through hole at the axis for the screw rod part of the separation push rod to pass through and guide the separation of the separation spring, and the top surface also has an annular groove structure for installation and limiting of the separation spring, and the bottom surface has three feet for connection of the screw columns and the carrier end separation base.

[0022] Further, the explosion bolt protection cover absorbs most of the explosion impact, and the four sets of separation springs are unlocked, the separation spring releases the elastic potential energy, and the elastic potential energy is transmitted to the satellite through the separation push rod.

[0023] Based on the above technical solutions, the present application has the following beneficial technical effects:

[0024] 1. The satellite-rocket separation device has a small size and mass, and the total mass of the four sets of separation devices used for each satellite is less than 4 kg, and the structural strength is sufficient to ensure the connection strength and reliability before satellite-rocket separation.

[0025] 2. The design and layout of the explosion bolt protection cover can effectively absorb the explosion impact generated by the explosion bolt, further improving the precision and reliability of the satellite-rocket separation.

[0026] 3. The satellite-rocket separation device has strong versatility, and the distance between the four separation bases can be flexibly changed to adapt to satellites of different sizes within the bearing range of the base.

[0027] 4. On the basis of retaining the design appearance of the satellite-rocket separation device, the separation base and the explosion bolt can also be increased to realize the separation of a satellite with larger mass. BRIEF DESCRIPTION OF DRAWINGS

[0028] Figure 1 (a) and Figure 1 (b) are overall structure schematic diagrams of the satellite-rocket separation device from two different angles, respectively.

[0029] Figure 2 is a structure schematic diagram of the locking seat module.

[0030] Figure 3 is a structure schematic diagram of the unlocking function module.

[0031] Figure 4 is a cross-sectional schematic diagram of the locking seat module and the separation power module.

[0032] Figure 5 is a cross-sectional schematic diagram of the unlocking function module.

[0033] In the figure: 1 - locking seat module, 2 - unlocking function module, 3 - separation power module, 101 - launch end separation base, 102 - satellite end separation base, 103 - separation device installation limiting plate, 104 - process nut, 105 - measurement socket base, 106 - separation contact plate support, 107 - contact spring, 201 - travel switch, 2021 - launch end travel switch installation box, 2022 - satellite end travel switch installation box, 203 - explosion bolt, 204 - explosion bolt protection cover, 205 - copper pad, 206 - rubber pad, 207 - honeycomb aluminum, 208 - shock absorbing spring, 209 - shock absorbing spring limiting washer, 210 - shock absorbing spring limiting sleeve, 301 - separation push rod, 302 - separation spring sleeve, 303 - separation spring, 304 - locking nut, 305 - push rod guide. DETAILED DESCRIPTION

[0034] In order to more specifically describe the present application, the technical solutions of the present application will be described in detail below in combination with the drawings and specific embodiments.

[0035] As Figure 1 (a) and Figure 1(b)As shown, the pinasatellite light low-impact satellite-rocket separation device of the present application includes locking seat module 1, unlocking function module 2 and separation power module 3; locking seat module 1 is used to connect the satellite and the carrier rocket, and provides installation position for unlocking function module 2 and separation power module 3; locking seat module 1 and separation power module 3 are respectively deployed in four sets, installed on the four corners of the bottom of the satellite, and then connected with the carrier rocket; unlocking function module 2 is deployed in two sets on the two sets of locking seat module 1 in opposite positions. Before the satellite separates, locking seat module 1 ensures the strength and reliability of the connection between the satellite and the rocket, and after the satellite enters the orbit, unlocking function module 2 unlocks the limit, separation power module 3 pushes the satellite bottom plate, and the satellite-rocket separation is realized.

[0036] As shown in Figure 2 and Figure 4 locking seat module 1 includes carrier end separation base 101, satellite end separation base 102, separation device installation limiting plate 103, process nut 104, measurement socket base 105, separation contact plate support 106, contact spring 107, etc.; carrier end separation base 101 is connected with satellite end separation base 102, separation device installation limiting plate 103 is installed near the installation plane of carrier end separation base 101 and satellite end separation base 102, used for auxiliary installation and positioning, process nut 104 is installed inside carrier end separation base 101 and satellite end separation base 102, used to ensure the connection during transportation, after the completion of the docking of the satellite and the rocket, process nut 104 will be removed, carrier end separation base 101 is connected with the carrier end, measurement socket base 105 is also connected with carrier end separation base 101, measurement socket is installed on measurement socket base 105, which is used for transmitting control signals; separation contact plate support 106 is installed on carrier end separation base 101, and contact spring 107 is installed on separation contact plate support 106; contact spring 107 contacts the corresponding interface on the bottom of the satellite before separation, and communicates with the internal signal path of the satellite; the other end of contact spring 107 is connected with an aviation plug, which is connected with the centralized test box of the carrier end, thereby forming the power supply, telemetry and signal transmission path from the centralized test box to the satellite.

[0037] As shown in Figure 3 and Figure 5As shown, the unlocking function module 2 includes a travel switch 201, a carrier end travel switch mounting box 2021, a satellite end travel switch mounting box 2022, an explosive bolt 203, an explosive bolt protective cover 204, a copper pad 205, a rubber pad 206, a honeycomb aluminum 207, a shock absorbing spring 208, a shock absorbing spring limiting washer 209, a shock absorbing spring limiting sleeve 210, etc.; the travel switch 201 is installed inside the carrier end travel switch mounting box 2021 and in contact with the satellite end travel switch mounting box 2022 on the satellite end separation base 102, the carrier end travel switch mounting box 2021 is installed on the carrier end separation base 101, the satellite end separation base 102 in the satellite-rocket separation device where the unlocking function module 2 is installed has a through-hole structure for installing the explosive bolt 203, the explosive bolt protective cover 204 is installed above the corresponding satellite end separation base 102, the copper pad 205, the rubber pad 206, and the honeycomb aluminum 207 are installed on the top of the explosive bolt protective cover 204, and the shock absorbing spring 208 is installed inside the satellite end separation base 102 and the explosive bolt protective cover 204, which are positioned and installed by the shock absorbing spring limiting washer 209 and the shock absorbing spring limiting sleeve 210.

[0038] As shown in Figure 4 The separation power module 3 includes a separation push rod 301, a separation spring sleeve 302, a separation spring 303, a locking nut 304, a push rod guide 305, etc.; the separation push rod 301 and the separation spring sleeve 302 have a limiting structure for fixing the installation position of the spring and ensuring that the spring does not come off the separation power module 3 during separation; the separation spring sleeve 302 has a through-hole structure for allowing the bottom of the separation push rod 301 to pass through; the bottom of the separation push rod 301 has a threaded mechanism of a certain length, which is screwed with the locking nut 304 after passing through the bottom of the separation spring sleeve 302, thereby realizing the compression and fixation of the separation spring 303; the separation spring 303 is installed between the separation push rod 301 and the separation push rod sleeve 302, and is driven by the separation spring 303 to drive the separation push rod 301 to realize satellite-rocket separation after the initiation of the initiating explosive; the locking nut 304 is mainly used during the transportation and installation of the satellite-rocket separation device and needs to be unscrewed after the satellite is docked with the carrier rocket, and then the limiting of the separation spring 303 is guaranteed by the explosive bolt; the push rod guide 305 is annular, with an inner side in interference fit contact with the separation push rod 301 and an outer side in clearance fit with the inner side of the separation spring sleeve 302, thereby realizing the guiding effect of the separation push rod 301 during separation.

[0039] Each separation device is equipped with a travel switch 201 and a travel switch mounting box 202; in addition, among the four separation devices used by each satellite, the diagonal installation is divided into two groups, and the travel switches of one group belong to the carrier end, and the travel switches of the other group belong to the satellite end; the two travel switches 201 of the satellite end transmit the separation signal to the inside of the satellite, and the two travel switches 201 of the carrier end transmit the separation signal to the measurement socket 206, which is connected to the controller of the carrier end through a cable to provide the separation signal to the rocket.

[0040] The separation contact plate bracket 106 is fixed on the carrier end of the separation device, and is used for mounting the contact spring 107. The separation contact plate bracket 106 has a hollow structure as a whole to reduce the mass.

[0041] The carrier end separation base 101 and the satellite end separation base 102 are connected to form a two-plane and one-column structure. The cross section of the column structure is a square with two semicircular sectors removed. This structure not only ensures the strength, but also reduces the mass and facilitates the tightening of the bolts during installation.

[0042] The explosive bolt protection cover 204 has a hollow cylindrical boss extending from a circular base. The explosive bolt protection cover 204 has a buffer structure inside to absorb the impact generated when the explosive bolt 203 is detonated. The space inside the explosive bolt protection cover 204 can be used to store the debris generated after the explosive bolt 203 is detonated. The explosive bolt protection cover 204 is installed on the satellite end separation base 102, and the corresponding position on the satellite has a recess structure for installing and storing the explosive bolt protection cover 204.

[0043] The separation push rod 301 has multiple functions such as contacting the satellite and transmitting power, providing spring limiting installation position, guiding spring release direction, and locking the spring before separation. The structure of the separation push rod 301 can be considered as the combination of a circular sheet and a cylindrical screw rod. The top of the circular sheet is a hemisphere for contacting the satellite bottom and transmitting separation power. The bottom of the circular sheet has an annular groove for spring installation and limiting. The cylindrical structure and the inner hole of the separation spring sleeve 302 together realize the guiding function of the spring separation process. The bottom of the cylindrical structure has a threaded structure for installing a nut to lock the spring during transportation and storage of the separation device.

[0044] The separation spring sleeve 302 has a through hole at its axis to allow the screw part of the push rod to pass through and guide the spring separation. The top surface of the separation spring sleeve 302 also has an annular groove structure for spring installation and limiting. The bottom surface of the separation spring sleeve 302 has three feet that can be connected to the carrier end separation base 102 by studs.

[0045] The circuit starts the explosive device at the beginning of the satellite-rocket separation, and the carrier end transmits a separation signal to start the explosive bolt 203. The carrier end separation base 101 and the explosive bolt protection cover 204 respectively accommodate and recycle the two parts after the explosive bolt 203 is initiated, and most of the explosion impact is absorbed by the explosive bolt protection cover 204. Then the limit of the four sets of separation springs 303 is unlocked, the separation spring 303 releases the elastic potential energy, and transmits it to the satellite through the separation push rod 301. The travel switch 201 and the satellite end separation base 102 are separated, the separation signal is detected, and the centralized test box in the carrier end is transmitted to complete the separation process.

[0046] The above description of the embodiments is to facilitate those of ordinary skill in the art to understand and apply the present application. Those skilled in the art can easily make various modifications to the above embodiments, and apply the general principles described herein to other embodiments without creative labor. Therefore, the present application is not limited to the above embodiments, and any improvements and modifications made by those skilled in the art based on the disclosure of the present application should be within the scope of protection of the present application.

Claims

1. A lightweight, low-impact satellite-launch separation device for a Pinasatellar satellite, characterized in that, It includes a locking seat module, an unlocking function module, and a separation power module, wherein: The locking seat module is used to connect the satellite and the launch vehicle, and provides an installation position for the unlocking function module and the separation power module; The separation power module is installed on the locking seat module. There are four sets of both the locking seat module and the separation power module, which are fixed at the four corners of the bottom of the satellite and then connected to the launch vehicle. The unlocking function module is deployed in two sets, which are respectively installed on two sets of locking seat modules at diagonal positions; Before the satellite separates from the launch vehicle, the locking seat module ensures the strength and reliability of the connection between the satellite and the launch vehicle; after the satellite enters orbit, the unlocking function module unlocks the limit switch, and the separation power module pushes the satellite base plate to achieve the separation of the satellite and the launch vehicle. The locking seat module includes a launch vehicle separation base, a satellite separation base, a separation device mounting limit plate, a measurement socket base, a process nut, a separation contact plate bracket, and contact springs. The satellite separation base is connected to the satellite on one side and to the launch vehicle separation base on the other. The separation device mounting limit plate is installed on the connection structure between the launch vehicle separation base and the satellite separation base to assist in installation and positioning. The process nut is installed inside the launch vehicle separation base and the satellite separation base to ensure connection during transportation; it will be removed after satellite-rocket docking. The launch vehicle separation base is connected to the launch vehicle, and the measurement socket base is connected to the launch vehicle separation base. A measurement socket is installed on this base for transmitting control signals. The separation contact plate bracket is installed on the launch vehicle separation base, and the contact springs are installed on the separation contact plate bracket. Before satellite-rocket separation, the contact springs contact the corresponding interface on the bottom of the satellite. One end of the contact spring is connected to the internal signal path of the satellite, and the other end is connected to an aviation plug, which connects to the centralized test box on the launch vehicle, thus forming a power supply, telemetry, and signal transmission path from the centralized test box to the satellite.

2. The lightweight, low-impact satellite-rocket separation device for Pinasatellar satellites according to claim 1, characterized in that: The unlocking function module includes a limit switch, a carrier-side limit switch mounting box, a satellite-side limit switch mounting box, an explosion bolt, an explosion bolt protective cover, a copper pad, a rubber pad, honeycomb aluminum, a shock-absorbing spring, a shock-absorbing spring limit washer, and a shock-absorbing spring limit sleeve; wherein the limit switch is installed inside the carrier-side limit switch mounting box and contacts the satellite-side limit switch mounting box on the satellite-side separation base, and the carrier-side limit switch mounting box is installed on the carrier-side separation base; The satellite-end separation base has a through-hole structure for installing explosive bolts; the explosive bolts are located inside the explosive bolt protective cover and are used to connect the carrier-end separation base and the satellite-end separation base. The explosive bolt protective cover is installed on the corresponding satellite-end separation base. Copper pads, rubber pads, and honeycomb aluminum are installed sequentially between the top of the explosive bolt protective cover and the top of the explosive bolt; shock-absorbing springs are installed on the explosive bolts, and the positioning installation is achieved by shock-absorbing spring limiting washers and shock-absorbing spring limiting sleeves.

3. The lightweight, low-impact satellite-launch separation device for Pinasatellar satellites according to claim 2, characterized in that: The separation power module includes a separation push rod, a separation spring sleeve, a separation spring, a locking nut, and a push rod guide. The separation push rod and separation spring sleeve have a limiting structure to fix the installation position of the separation spring and ensure that the separation spring does not detach from the separation power module during separation. The separation spring sleeve has a through hole structure to allow the bottom of the separation push rod to pass through. The bottom of the separation push rod has a threaded mechanism of a certain length. After passing through the bottom of the separation spring sleeve, it is tightened with a locking nut to compress and fix the separation spring. The separation spring is installed between the separation push rod and the separation push rod sleeve. After the pyrotechnic device is detonated, the separation spring drives the separation push rod to achieve satellite-rocket separation. The locking nut is mainly used during the transportation and installation of the satellite-rocket separation device. It needs to be unscrewed after the satellite and launch vehicle are docked. Subsequently, the limiting of the separation spring is ensured by the explosive bolt. The push rod guide is annular. Its inner side is in interference fit with the separation push rod, and its outer side is in clearance fit with the inner side of the separation spring sleeve, thereby guiding the separation push rod during separation.

4. The lightweight, low-impact satellite-rocket separation device for Pinasatellar satellites according to claim 2, characterized in that: The satellite-side limit switch mounting box also contains limit switches. Therefore, the limit switches in the entire satellite-rocket separation device are installed diagonally in two groups. One group of limit switches belongs to the launch vehicle end, and the other group belongs to the satellite end. The two limit switches on the satellite end are used to transmit the separation signal to the satellite's interior, and the two limit switches on the launch vehicle end are used to transmit the separation signal to the measurement socket. The measurement socket is then connected to the controller on the launch vehicle end via a cable to provide the separation signal to the launch vehicle.

5. The lightweight, low-impact satellite-rocket separation device for Pinasatellar satellites according to claim 1, characterized in that: The separation contact plate bracket is fixed on the carrier-side separation base and is used to install the contact springs. The separation contact plate bracket has a hollow structure to reduce weight. The carrier-side separation base and the satellite-side separation base are connected in the form of two planes and a columnar structure. The cross-section of the columnar structure is a square with the four corners cut out to form sectors of the same radius. This structure reduces weight while ensuring strength and also facilitates tightening bolts during installation.

6. The lightweight, low-impact satellite-rocket separation device for Pinasatellar satellites according to claim 2, characterized in that: The explosive bolt protective cover is shaped like a hollow cylindrical boss stretched from a circular base. It has a buffer structure inside that can absorb the impact generated when the explosive bolt is detonated. At the same time, its internal space is used to collect the debris generated after the explosive bolt is detonated. The explosive bolt protective cover is installed on the satellite-end separation base, and there is a recessed structure at the corresponding position on the satellite for installing and storing the explosive bolt protective cover.

7. The lightweight, low-impact satellite-launch separation device for Pinasatellar satellites according to claim 3, characterized in that: The separation push rod integrates multiple functions, including contacting the satellite and transmitting power, providing the spring's limiting installation position, guiding the spring's release direction, and locking the spring before separation. Its structure consists of a combination of a circular thin plate and a cylindrical screw. The top of the circular thin plate is a hemisphere for contacting the bottom of the satellite and transmitting separation power. The bottom of the circular thin plate has an annular groove for spring installation and limiting. The cylindrical screw and the inner hole of the separation spring sleeve work together to guide the spring separation process. The bottom of the cylindrical screw has a threaded structure for installing a locking nut to lock the separation spring during the transportation and storage of the satellite-rocket separation device.

8. The lightweight, low-impact satellite-launch separation device for Pinasatellar satellites according to claim 3, characterized in that: The separation spring sleeve has a through hole at its axis to allow the screw part of the separation push rod to pass through and guide the separation spring to separate; its top surface also has an annular groove structure for the installation and limiting of the separation spring; its bottom surface has three feet for the studs to connect with the carrier end separation base.

9. The lightweight, low-impact satellite-launch separation device for Pinasatellar satellites according to claim 3, characterized in that: When the star-rocket separation begins, the pyrotechnics are activated by the circuit. The separation signal is transmitted from the carrier end to activate the explosive bolts. The carrier end separation base and the explosive bolt protective cover respectively collect and recover the two parts after the explosive bolts are detonated, and the explosive bolt protective cover absorbs most of the blast impact. Subsequently, the limits of the four sets of separation springs are unlocked, the separation springs release elastic potential energy, which is transmitted to the satellite through the separation push rod; the limit switch separates from the separation base at the satellite end, a separation signal is detected, and transmitted back to the centralized test box at the carrier end, completing the separation process.

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