Light low-impact satellite-rocket separation device for pico-satellite and nano-satellite

Abstract

The invention discloses a light low-impact satellite-rocket separation device for a pico-satellite and a nano-satellite. The light low-impact satellite-rocket separation device 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, a measurement socket base and the like; the unlocking function module comprises an explosive bolt, an explosive bolt protection cover and the like; the separation power module comprises a separation push rod, a separation push rod sleeve, a separation spring and the like. 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 explosive bolts or process bolts, the process bolts are only started during transportation, and launching is conducted only through the explosive bolts; at the beginning of separation, the explosive bolt is started by a circuit, and the explosive bolt protection cover is used for relieving explosion impact and collecting the cut-off part of the explosive bolt; the separation spring is mounted between the separation push rod and the separation push rod sleeve; and after the explosive bolt is detonated, the separation spring drives the separation push rod to realize satellite-rocket separation.

Description

Technical Field

[0001] The invention belongs to the field of aerospace technology, and specifically relates to a light and low-impact satellite-rocket separation device for a Pina satellite. Background Art

[0002] With the country's emphasis on and investment in the aerospace field in recent years, the frequency of space launch missions has continued to increase. The satellite-rocket separation process is an important stage to ensure the smooth separation of the satellite into the predetermined orbit, and the satellite-rocket separation device plays a key role in it. With the continuous refinement of the semiconductor industry process, artificial satellites are also constantly improving the integration and precision of internal electronic devices. The size and mass of satellites have been greatly reduced, but the requirements for the separation accuracy and reliability of the satellite-rocket separation device have also been increased.

[0003] The main functions of the satellite-rocket separation device are: providing connection strength between the satellite and the launch vehicle, transmitting signals between the satellite and the launch vehicle, detonating pyrotechnics to start separation, unlocking the power mechanism to achieve kinetic energy transfer, etc. The design of the satellite-rocket separation device usually needs to consider requirements such as simple structure, light weight, high structural strength, high reliability, strong robustness, and low pollution.

[0004] Currently, commonly used satellite-rocket separation devices can be mainly divided into two categories: pyrotechnics and non-pyrotechnics. The scheme of separating satellites and rockets by detonating pyrotechnics is prone to produce a large impact, which is likely to have a large impact on microsatellites and their internal precision instruments. Existing pyrotechnic separation schemes usually consider reducing impact loads in structural design and material stacking, but they tend 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 pyrotechnic separation schemes do not have a design for recovering 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 is not designed to recover explosive bolt fragments.

[0005] Non-pyrotechnic separation solutions include belt-wrapped locking, electromagnetic, hot knife, etc. Although they avoid the impact of explosion, the cost is a large and complex structural design. For example, the connecting rod belt-wrapped separation mechanism designed in the Chinese patent application with publication number CN111619831A has a cross-sectional size equivalent to the bottom surface of the satellite, and its own mass is also increased accordingly; another example is the rotating electromagnet separation mechanism designed in the Chinese patent applications with publication numbers CN216734828U and CN114132535A. In addition to the power device in the separation direction, its structure also adds an electromagnetic unlocking device perpendicular to the separation direction. The structure is relatively complex, which increases the difficulty of maintenance and reduces the reliability during the launch process.

[0006] Therefore, how to reduce the impact of the detonation of pyrotechnics on the satellite-rocket separation process and improve the reliability of satellite-rocket separation through structural design is a difficult problem that needs to be urgently solved in the pyrotechnic separation solution. Summary of the invention

[0007] In view of the above, the present invention provides a light and low-impact satellite-rocket separation device for Pina satellites, which reduces the volume and weight of the satellite-rocket separation device while ensuring the strength of the satellite-rocket connection. By designing the layout and installation of pyrotechnics, the impact load when the pyrotechnics are detonated is reduced, further improving the separation accuracy and reliability.

[0008] A light and low-impact satellite-rocket separation device for a Pina satellite comprises 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 launch vehicle, and provides an installation position for the unlocking function module and the separation power module;

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

[0011] The unlocking function module is deployed in two sets, which are respectively installed on two sets of locking seat modules at diagonal positions;

[0012] Before the separation of the satellite and the rocket, the locking seat module ensures the strength and reliability of the satellite-rocket connection; after the satellite enters orbit, the unlocking function module unlocks the limit, and the separation power module pushes the satellite base plate to achieve the separation of the satellite and the rocket.

[0013] Furthermore, the locking seat module includes a carrier-end separation base, a satellite-end separation base, a separation device installation limit plate, a measuring socket base, a process nut, a separation contact plate bracket and a contact spring; wherein the satellite-end separation base is connected to the satellite on one side and connected to the carrier-end separation base on the other side; the separation device installation limit plate is installed on the connection structure between the carrier-end separation base and the satellite-end separation base to assist in installation and positioning; the process nut is installed inside the carrier-end separation base and the satellite-end separation base to ensure the connection between the two during transportation. After the satellite-rocket docking is completed, the process nut The nuts will be removed; the carrier-end separation base is connected to the carrier rocket, the measuring socket base is connected to the carrier-end separation base, and the measuring socket is installed on the base for transmitting control signals; the separation contact plate bracket is installed on the carrier-end separation base, and the contact spring is installed on the separation contact plate bracket, and the contact spring contacts 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 connected to the internal signal path of the satellite, and the other end is connected to the aviation plug, which is connected to the 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] Furthermore, the unlocking function module includes a travel switch, a carrier-end travel switch installation box, a satellite-end travel switch installation 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 limit washer and a shock-absorbing spring limit sleeve; wherein the travel switch is installed inside the carrier-end travel switch installation box and contacts the satellite-end travel switch installation box on the satellite-end separation base, and the carrier-end travel switch installation box is installed on the carrier-end separation base; the satellite-end separation base has a through-hole structure for installing explosive bolts; the explosive bolts are arranged in the explosive bolt protective cover for connecting the carrier-end separation base with the satellite-end separation base, and the explosive bolt protective cover is installed on the corresponding satellite-end separation base, and the copper pad, rubber pad and honeycomb aluminum are sequentially installed between the top of the explosive bolt protective cover and the top of the explosive bolt; the shock-absorbing spring is installed on the explosive bolt, and the positioning installation is achieved by the shock-absorbing spring limit washer and the shock-absorbing spring limit sleeve.

[0015] Furthermore, the separation power module includes a separation push rod, a separation spring sleeve, a separation spring, a locking nut and a push rod guide; wherein 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 will not separate from the separation power module during the separation process; the separation spring sleeve has a through-hole structure for allowing the bottom of the separation push rod to pass through, and the bottom of the separation push rod has a threaded mechanism of a certain length, which is tightened 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 the separation spring drives the separation push rod to realize satellite-rocket separation after the pyrotechnics are detonated; the locking nut is mainly activated during the transportation and installation of the satellite-rocket separation device, and needs to be unscrewed after the satellite and the carrier rocket are docked, and then the limiting of the separation spring is guaranteed by the explosive bolt; the push rod guide is annular, the inner side of which is in interference fit contact with the separation push rod, and the outer side is clearance fit with the inner side of the separation spring sleeve, thereby realizing the guiding effect on the separation push rod during the separation process.

[0016] Furthermore, a travel switch is also provided in the travel switch installation box at the satellite end, so the travel switches in the entire satellite-rocket separation device are divided into two groups by diagonal installation, 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 at the satellite end are used to transmit the separation signal to the inside of the satellite, and the two travel switches at the carrier end are used to transmit the separation signal to the measuring socket, which is then connected to the controller at the carrier end through a cable to provide a separation signal to the carrier rocket.

[0017] Furthermore, the separation contact plate bracket is fixed on the separation base at the carrier end and is used to install the contact spring. The separation contact plate bracket is a hollow structure as a whole to reduce the mass.

[0018] Furthermore, the carrier-end separation base and the satellite-end separation base, when connected, present two planes and a columnar structure. The cross-section of the columnar structure is a square with four corners hollowed out into sectors with the same radius. This structure reduces a certain amount of mass while ensuring strength, and is also convenient for tightening bolts during installation operations.

[0019] Furthermore, the appearance of the explosive bolt protective cover is a hollow cylindrical boss stretched out from a circular base, and a buffer structure is provided inside the explosive bolt protective cover, which can absorb the impact generated when the explosive bolt is detonated. At the same time, the internal space is used to store the debris generated after the explosion of the explosive bolt. The explosive bolt protective cover is installed on the satellite end separation base, and the corresponding position on the satellite has a recessed structure for installing and storing the explosive bolt protective cover.

[0020] Furthermore, the separation push rod integrates multiple functions such as contacting the satellite and transmitting power, providing a spring limit installation position, guiding the spring release direction, and locking the spring before separation. Its structure is a combination of a circular sheet and a cylindrical screw. The top of the circular sheet is a hemisphere, which is used to contact the bottom of the satellite and transmit separation power. There is an annular groove at the bottom of the circular sheet for installing and limiting the spring. The cylindrical screw and the inner hole of the separation spring sleeve jointly realize the guiding effect on the spring separation process. The bottom of the cylindrical screw is a threaded structure, which is used to install a locking nut to achieve locking of the separation spring during transportation and storage of the satellite-rocket separation device.

[0021] Furthermore, the separation spring sleeve has a through hole at its axis for the screw portion 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 connecting the stud to the separation base at the carrying end.

[0022] Furthermore, when the separation of the satellite and the rocket begins, the pyrotechnics are activated by the circuit, and the separation signal is transmitted by the carrier end to activate the explosive bolt. The separation base at the carrier end and the explosive bolt protective cover respectively store and recover the two parts of the explosive bolt after detonation, and the explosive bolt protective cover absorbs most of the explosion impact; then the limit of the four sets of separation springs are unlocked, and the separation springs release elastic potential energy, which is transmitted to the satellite through the separation push rod; the travel switch separates from the separation base at the satellite end, and the separation signal is detected and transmitted back to the centralized test box at the carrier end to complete the separation process.

[0023] Based on the above technical solution, the present invention has the following beneficial technical effects:

[0024] 1. The satellite-rocket separation device of the present invention has a small volume and a small mass. The total mass of the four sets of separation devices used for each satellite is within 4 kg. At the same time, it has sufficient structural strength to ensure the connection strength and reliability before the satellite-rocket separation.

[0025] 2. The design and layout of the explosive bolt protection cover of the present invention can effectively absorb the explosion impact generated by the explosive bolt, further improving the accuracy and reliability of 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 accommodate satellites of different sizes within the base's carrying range.

[0027] 4. On the basis of retaining the design appearance of the satellite-rocket separation device of the present invention, the separation of satellites with larger mass can also be achieved by increasing the separation base and the explosive bolts. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 (a) and Figure 1 (b) are schematic diagrams of the overall structure of the satellite-rocket separation device of the present invention at two different viewing angles.

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

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

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

[0032] Figure 5 A cross-sectional diagram of the unlocking function module.

[0033] In the figure: 1—locking seat module, 2—unlocking function module, 3—separation power module, 101—carrier end separation base, 102—satellite end separation base, 103—separation device installation limit plate, 104—process nut, 105—measuring socket base, 106—separation contact plate bracket, 107—contact spring, 201—travel switch, 2021—carrier end travel switch installation box, 2022—satellite end travel switch installation box, 203—explosive bolt, 204—explosive bolt protection cover, 205—copper pad, 206—rubber pad, 207—honeycomb aluminum, 208—shock-absorbing spring, 209—shock-absorbing spring limit washer, 210—shock-absorbing spring limit 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 describe the present invention more specifically, the technical solution of the present invention is described in detail below in conjunction with the accompanying drawings and specific implementation methods.

[0035] like Figure 1 (a) and Figure 1As shown in (b), the light and low-impact satellite-rocket separation device for the pina satellite of the present invention comprises a locking seat module 1, an unlocking function module 2 and a separation power module 3; the locking seat module 1 is used to connect the satellite and the launch vehicle, and provides an installation position for the unlocking function module 2 and the separation power module 3; four sets of locking seat modules 1 and separation power modules 3 are respectively deployed, installed on the four corners of the bottom of the satellite, and then installed and connected with the launch vehicle; two sets of unlocking function modules 2 are deployed on two sets of locking seat modules 1 at diagonal positions. Before the satellite is separated, the locking seat module 1 ensures the strength and reliability of the satellite-rocket connection. After the satellite enters orbit, the unlocking function module 2 unlocks the limit, and the separation power module 3 pushes the satellite bottom plate to achieve satellite-rocket separation.

[0036] like Figure 2 and Figure 4 As shown, the locking seat module 1 includes a carrier-end separation base 101, a satellite-end separation base 102, a separation device installation limit plate 103, a process nut 104, a measuring socket base 105, a separation contact plate bracket 106, a contact spring 107, etc.; the carrier-end separation base 101 is connected to the satellite-end separation base 102, the separation device installation limit plate 103 is installed near the installation plane of the carrier-end separation base 101 and the satellite-end separation base 102 to assist in installation and positioning, and the process nut 104 is installed inside the carrier-end separation base 101 and the satellite-end separation base 102 to ensure the connection during transportation. After the satellite-rocket docking is completed, the process nut 104 is installed inside the carrier-end separation base 101 and the satellite-end separation base 102 to ensure the connection during transportation. The nut 104 will be removed, the carrier-end separation base 101 is connected to the carrier-end, the measuring socket base 105 is also connected to the carrier-end separation base 101, and the measuring socket base 105 is installed with a measuring socket, which is used to transmit control signals; the separation contact plate bracket 106 is installed on the carrier-end separation base 101, and the contact spring 107 is installed on the separation contact plate bracket 106; the contact spring 107 contacts with the corresponding interface at the bottom of the satellite before separation, and is connected with the internal signal path of the satellite; the other end of the contact spring 107 is connected to the aviation plug, which is connected to the centralized test box at the carrier-end, thereby forming a power supply, telemetry, and signal transmission path from the centralized test box to the satellite.

[0037] like Figure 3 and Figure 5As shown, the unlocking function module 2 includes a travel switch 201, a carrier-end travel switch installation box 2021, a satellite-end travel switch installation box 2022, an explosive bolt 203, an explosive bolt protection cover 204, a copper pad 205, a rubber pad 206, a honeycomb aluminum 207, a shock-absorbing spring 208, a shock-absorbing spring limit washer 209, a shock-absorbing spring limit sleeve 210, etc.; the travel switch 201 is installed inside the carrier-end travel switch installation box 2021 and contacts the satellite-end travel switch installation box 2022 on the satellite-end separation base 102, and the carrier-end travel switch installation box 2021 is in contact with the satellite-end travel switch installation box 2022 on the satellite-end separation base 102. 021 is installed on the carrier-end separation base 101. The satellite-end separation base 102 in the satellite-rocket separation device in which the unlocking function module 2 is installed has a through-hole structure for installing the explosive bolt 203. The explosive bolt protection cover 204 is installed above the corresponding satellite-end separation base 102. The copper pad 205, rubber pad 206, and honeycomb aluminum 207 are installed on the top of the explosive bolt protection cover 204. The shock-absorbing spring 208 is installed inside the satellite-end separation base 102 and the explosive bolt protection cover 204. The positioning installation is achieved by the shock-absorbing spring limiting washer 209 and the shock-absorbing spring limiting sleeve 210.

[0038] like Figure 4 As shown, 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 separate from the separation power module 3 during the separation process. 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 tightened with the locking nut 304 after passing through the bottom of the separation spring sleeve 302, thereby realizing the separation of the separation spring 30 3 is compressed and fixed; the separation spring 303 is installed between the separation push rod 301 and the separation push rod sleeve 302. After the pyrotechnics are detonated, the separation spring 303 drives the separation push rod 301 to realize the separation of the satellite and the rocket; the locking nut 304 is mainly used in the transportation and installation process of the satellite and the rocket separation device. After the docking of the satellite and the carrier rocket is completed, it needs to be unscrewed. Then the separation spring 303 is limited by the explosive bolt. The push rod guide 305 is annular, and the inner side is in interference fit contact with the separation push rod 301, and the outer side is in clearance fit with the inner side of the separation spring sleeve 302, thereby realizing the guiding effect on the separation push rod 301 during the separation process.

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

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

[0041] The carrier-end separation base 101 and the satellite-end separation base 102, when connected, present two planes and a columnar structure. The cross-section of the columnar structure is a square with four corners dug out into sectors with the same radius. This structure reduces a certain amount of mass while ensuring strength, and is also convenient for tightening bolts during installation operations.

[0042] The explosive bolt protective cover 204 has an appearance of a hollow cylindrical boss stretched out from a circular base. A buffer structure is provided inside the explosive bolt protective cover 204 to absorb the impact generated when the explosive bolt 203 is detonated. At the same time, the internal space can be used to store the debris generated after the explosive bolt 203 is detonated. The explosive bolt protective cover 204 is installed on the satellite-end separation base 102, and a corresponding position on the satellite has a recessed structure for installing and storing the explosive bolt protective cover 204.

[0043] The separation push rod 301 has a structure that integrates multiple functions such as contacting the satellite and transmitting power, providing a spring limit installation position, guiding the spring release direction, and locking the spring before separation; its structure can be seen as a combination of a circular sheet and a cylindrical screw. The top of the circular sheet is a hemisphere, which is used to contact the bottom of the satellite and transmit the separation power. The bottom of the circular sheet has an annular groove for installing and limiting the spring. The cylindrical structure and the inner hole of the separation spring sleeve 302 jointly realize the guiding effect on the spring separation process. The bottom of the cylindrical structure is a threaded structure, which is used to install a nut to achieve locking of the spring during transportation and storage of the separation device.

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

[0045] At the beginning of the separation of the satellite and the rocket, the pyrotechnics are activated by the circuit, and the separation signal is transmitted by the carrier end to activate the explosive bolt 203. The carrier end separation base 101 and the explosive bolt protection cover 204 respectively store and recover the two parts of the explosive bolt 203 after detonation, and the explosive bolt protection cover 204 absorbs most of the explosion impact; then the limit of the four groups of separation springs 303 is unlocked, and the separation spring 303 releases elastic potential energy, which is transmitted to the satellite through the separation push rod 301; the travel switch 201 is separated from the satellite end separation base 102, and the separation signal is detected and transmitted back to the centralized test box at the carrier end to complete the separation process.

[0046] The above description of the embodiments is to facilitate the understanding and application of the present invention by those skilled in the art. It is obvious that 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 work. Therefore, the present invention is not limited to the above embodiments. Improvements and modifications made by those skilled in the art to the present invention based on the disclosure of the present invention should be within the protection scope of the present invention.

Claims

1. A light and low-impact satellite-rocket separation device for Pina satellites, 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 location for the unlocking function module and the separation power module; The separation power module is installed on the locking seat module. Four sets of the locking seat module and the separation power module are deployed, respectively fixed on the four corners of the bottom of the satellite, and then installed and connected with the carrier rocket; 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 separation of the satellite and the rocket, the locking seat module ensures the strength and reliability of the satellite-rocket connection; after the satellite enters orbit, the unlocking function module unlocks the limit, and the separation power module pushes the satellite base plate to achieve the separation of the satellite and the rocket.

2. The light and low-impact satellite-rocket separation device for PINA satellite according to claim 1 is characterized in that: The locking seat module includes a carrier end separation base, a satellite end separation base, a separation device installation limit plate, a measurement socket base, a process nut, a separation contact plate bracket and a contact spring; One side of the satellite-end separation base is connected to the satellite, and the other side is connected to the carrier-end separation base; the separation device installation limit plate is installed on the connection structure between 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 between the two during transportation. After the satellite-rocket docking is completed, the process nut will be removed; the carrier-end separation base is connected to the launch vehicle, and the measuring socket base is connected to the carrier-end separation base. The measuring socket is installed on the base for transmitting control signals; the separation contact plate bracket is installed on the carrier-end separation base, and the contact spring is installed on the separation contact plate bracket. The contact spring contacts the corresponding interface at the bottom of the satellite before the satellite-rocket separation; one end of the contact spring is connected to the internal signal path of the satellite, and the other end is connected to the aviation plug, which is connected to the centralized test box on the carrier end, thereby forming a power supply, telemetry, and signal transmission path from the centralized test box to the satellite.

3. The light and low-impact satellite-rocket separation device for Pinna satellites according to claim 2 is characterized in that: The unlocking function module includes a travel switch, a carrier end travel switch installation box, a satellite end travel switch installation box, an explosive bolt, an explosive bolt protection cover, a copper pad, a rubber pad, a honeycomb aluminum, a shock absorbing spring, a shock absorbing spring limit washer, and a shock absorbing spring limit sleeve; wherein the travel switch is installed inside the carrier end travel switch installation box and contacts the satellite end travel switch installation box on the satellite end separation base, and the carrier end travel switch installation box is installed on the carrier end separation base; The satellite separation base has a through-hole structure for installing explosive bolts; the explosive bolts are arranged in the explosive bolt protection cover for connecting the carrier separation base and the satellite separation base; the explosive bolt protection cover is installed on the corresponding satellite separation base, and the copper pad, rubber pad and honeycomb aluminum are installed in sequence between the top of the explosive bolt protection cover and the top of the explosive bolt; the shock-absorbing spring is installed on the explosive bolt, and the positioning installation is achieved by the shock-absorbing spring limit washer and the shock-absorbing spring limit sleeve.

4. The light and low-impact satellite-rocket separation device for PINA satellite according to claim 3 is characterized by: 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 will not separate from the separation power module during the separation process; the separation spring sleeve has a through-hole structure for allowing the bottom of the separation push rod to pass through, and the bottom of the separation push rod has a threaded mechanism of a certain length, which is tightened 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 the separation spring drives the separation push rod to realize satellite-rocket separation after the pyrotechnics are detonated; the locking nut is mainly activated during the transportation and installation of the satellite-rocket separation device, and needs to be unscrewed after the satellite and the launch vehicle are docked, and then the limiting of the separation spring is guaranteed by the explosive bolt; the push rod guide is annular, the inner side of which is in interference fit contact with the separation push rod, and the outer side is clearance fit with the inner side of the separation spring sleeve, thereby realizing the guiding effect on the separation push rod during the separation process.

5. The light and low-impact satellite-rocket separation device for Pinna satellites according to claim 3 is characterized in that: A travel switch is also provided in the travel switch installation box at the satellite end. Therefore, the travel switches in the entire satellite-rocket separation device are divided into two groups by diagonal installation, 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 at the satellite end are used to transmit the separation signal to the inside of the satellite, and the two travel switches at the carrier end are used to transmit the separation signal to the measuring socket, which is then connected to the controller at the carrier end through a cable to provide a separation signal to the carrier rocket.

6. The light and low-impact satellite-rocket separation device for Pinna satellites according to claim 2 is characterized in that: The separation contact plate bracket is fixed on the separation base at the carrier end and is used to install the contact spring. The separation contact plate bracket is a hollow structure as a whole to reduce the mass. The separation base at the carrier end and the separation base at the satellite end are two planes and a columnar structure when connected. The cross-section of the columnar structure is a square with the four corners dug out into sectors with the same radius. This structure reduces a certain amount of mass while ensuring strength, and is also convenient for tightening bolts during installation operations.

7. The light and low-impact satellite-rocket separation device for Pina satellite according to claim 3 is characterized by: The explosive bolt protective cover has an appearance of a hollow cylindrical boss stretched out from a circular base, and a buffer structure is provided inside the explosive bolt protective cover to absorb the impact generated when the explosive bolt is detonated. At the same time, the internal space is used to store the debris generated after the explosion of the explosive bolt. The explosive bolt protective cover is installed on the satellite end separation base, and the corresponding position on the satellite has a recessed structure for installing and storing the explosive bolt protective cover.

8. The light and low-impact satellite-rocket separation device for Pinna satellites according to claim 4 is characterized by: The separation push rod integrates multiple functions such as contacting the satellite and transmitting power, providing a spring limit installation position, guiding the spring release direction, and locking the spring before separation. Its structure is a combination of a circular sheet and a cylindrical screw. The top of the circular sheet is a hemisphere, which is used to contact the bottom of the satellite and transmit separation power. There is an annular groove at the bottom of the circular sheet for installing and limiting the spring. The cylindrical screw and the inner hole of the separation spring sleeve jointly realize the guiding effect on the spring separation process. The bottom of the cylindrical screw is a threaded structure, which is used to install a locking nut to achieve locking of the separation spring during transportation and storage of the satellite-rocket separation device.

9. The light and low-impact satellite-rocket separation device for Pinna satellites according to claim 4 is characterized in that: The separation spring sleeve has a through hole at its axis for the screw portion 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 stud to connect with the separation base at the carrier end.

10. The light and low-impact satellite-rocket separation device for Pinna satellites according to claim 4 is characterized in that: When the rocket-satellite separation begins, the circuit activates the pyrotechnics, and the carrier transmits the separation signal to activate the explosive bolt. The carrier separation base and the explosive bolt protection cover respectively store and recover the two parts of the explosive bolt after detonation, and the explosive bolt protection cover absorbs most of the explosion impact. Then the limit switches of the four sets of separation springs are unlocked, and the separation springs release their elastic potential energy, which is transmitted to the satellite through the separation push rod; the travel switch separates from the separation base at the satellite end, and the separation signal is detected and transmitted back to the centralized test box at the carrier end, completing the separation process.

Images