Star-rocket separation signal system and star-rocket separation system

Abstract

This invention provides a satellite-launch separation signal system and a satellite-launch separation system, comprising: a first user unit that outputs two satellite-launch separation signal sources, each leading to two different contacts of a first analog separation relay; these signals then return to the first user unit via a first separation connector and a second separation connector; the input and output terminals of the first analog separation relay are each connected to a satellite display socket via cables; and a second user unit that outputs two satellite-launch separation signal sources, each leading to two different contacts of a second analog separation relay; these signals then return to the second user unit via a first separation connector and a second separation connector; the input and output terminals of the second analog separation relay are each connected to a satellite display socket via cables. This invention ensures that the signal is provided by the analog satellite-launch separation relay during ground testing, and avoids fatal malfunctions such as accidental separation commands issued before launch or mis-separation due to severe vibrations during the active phase, thus improving the reliability of the satellite-launch separation signal link.

Description

Technical Field

[0001] This invention relates to the field of electronic information technology for spacecraft, specifically to a satellite-launcher separation signal system and a satellite-launcher separation system. More particularly, it relates to a method for generating a satellite-launcher separation indication signal for a spacecraft. Background Technology

[0002] The separation signal is a landmark signal indicating that the spacecraft has begun to operate independently after separating from the spacecraft-launcher combination. Only after the spacecraft receives the correct separation signal can its onboard software begin to function normally, and various software-based programmed actions such as solar panel deployment and attitude control can be performed according to the time base requirements. In addition, the separation signal is generally used to lock the transmission of pyrotechnic commands from the spacecraft. Only when the separation is normal can subsequent pyrotechnic detonation commands be correctly transmitted. Therefore, the reliability of the separation signal is related to the success or failure of the spacecraft mission. It is necessary to ensure that no false separation signals are generated before separation and that a separation signal can be given after separation.

[0003] Due to the importance of the satellite-rocket separation signal, electromagnetic separation and mechanical separation are usually used as redundancies. In this case, there are four failure mechanisms of the satellite-rocket separation signal: electrical unlocking failure, electrical unlocking mis-separation, mechanical unlocking failure, and mechanical unlocking mis-separation. Among them, mechanical unlocking failure and mechanical unlocking mis-separation have corresponding guarantee measures and the probability of occurrence is extremely low. Electrical unlocking failure can also be ensured by mechanical separation. Therefore, the failure mechanism that needs to be considered in the design of the satellite-rocket separation signal should mainly focus on the design to prevent electrical unlocking mis-separation.

[0004] Currently, in the design of spacecraft star-rocket separation signals in China, series and parallel connection of separation connectors and simulated star-rocket separation control are used in both ground-based and space-based schemes. However, most of these schemes focus on the design and optimization of separation devices or mechanisms. There is no unified system-level star-rocket separation signal design method for separation methods using conventional separation connectors, and there is a lack of design schemes to prevent accidental separation.

[0005] The patent document with publication number CN108945530A discloses a design and simulation method for a satellite-rocket separation signal. It uses two 28V bus voltage dividers to provide separation signal sources for two separation connectors. The two satellite-rocket separation signals are ANDed and then provided to the user end. The satellite-rocket separation signal is led from the separation connector to the ground and the simulated satellite-rocket separation function is realized through ground relay control.

[0006] A method for separating a redundant backup satellite-rocket separation electrical connector is disclosed in patent document CN10995193A. It uses electric disconnection and aramid rope forced disconnection as the separation method for redundancy backup. The separation electrical connector is installed on the satellite base plate, and the aramid rope is tied to the separation electrical connector and the docking bracket base. During separation, the separation electrical connector is first electrically disconnected. If the separation fails, the separation electrical connector is separated by stretching the aramid rope.

[0007] In the paper "A Novel Microsatellite Autonomous Satellite-Rocket Separation Power Control Technology" Communication Power Technology 2018.35(5)p.47-49, an autonomous satellite-rocket separation power control technology was designed. After the satellite separates, the separation signal without electrical contacts provided by the launch vehicle is received and the power is provided to the separation unlocking pyrotechnics after being delayed by the control circuit.

[0008] The doctoral dissertation "Design Analysis Method and Key Technology Research of Pi-Satellite Separation Mechanism" published by Zhejiang University in 2014 (p. 28) introduces a design scheme for unlocking telemetry signals of the pico-satellite separation mechanism. It adopts a series connection of two normally closed limit switches to monitor whether the opening of the separation mechanism hatch and the separation of the satellite and rocket are normal.

[0009] However, the aforementioned technical documents only improved the safety of the power supply for the separation signal, the convenience of the simulated separation operation, and the reliability of the separation. They did not conduct an in-depth analysis of the failure mechanism of the star-rocket separation signal, and there were no corresponding guarantee measures for preventing accidental separation, which is a key consideration in the design.

[0010] Therefore, there is a market need for a satellite-rocket separation signal system and a satellite-rocket separation system that can prevent accidental separation. Summary of the Invention

[0011] To address the shortcomings of existing technologies, the purpose of this invention is to provide a method and system for analyzing satellite-rocket separation signals.

[0012] According to the present invention, a satellite-rocket separation signal system includes: a first user unit, a second user unit, a main power distributor, a first separation connector, a second separation connector, a satellite display plug, and a satellite display socket. The main power distributor includes a first analog separation relay and a second analog separation relay. The satellite display plug is connected to the satellite display socket.

[0013] The first single-use unit outputs two star-rocket separation signal sources, which are respectively led to two different contacts of the first analog separation relay. After passing through the first separation connector and the second separation connector, they return to the first single-use unit. The input and output terminals of the first analog separation relay are respectively led to the star meter socket via cables.

[0014] The second single-use unit outputs two star-rocket separation signal sources, which are respectively led to two different contacts of the second analog separation relay. After passing through the first separation connector and the second separation connector, they return to the second single-use unit. The input and output terminals of the second analog separation relay are respectively led to the star meter socket via cables.

[0015] Preferably, when the shielding separation function is required, the satellite connector is short-circuited.

[0016] Preferably, the first single-unit application includes a first satellite-rocket separation signal source and a second satellite-rocket separation signal source. The first satellite-rocket separation signal source is connected to the first stationary contact of the first analog separation relay via a cable, and the second satellite-rocket separation signal source is connected to the second stationary contact of the first analog separation relay via a cable.

[0017] The first stationary contact of the first analog disconnect relay is connected to the satellite meter socket via a wire. The satellite meter socket is connected to the first moving contact of the first analog disconnect relay via a wire. The first moving contact of the first analog disconnect relay is connected to the first disconnect connector via a wire. The first disconnect connector is connected to the first user unit via a wire. The second moving contact of the first analog disconnect relay is connected to the second disconnect connector via a wire. The second disconnect connector is connected to the first user unit via a wire.

[0018] Preferably, the first analog separation relay includes an e-contact, an a-contact, and a d-contact that are mutually connected. The a-contact is connected to the first satellite-rocket separation signal source, and the e-contact is connected to the satellite display socket.

[0019] It also includes a c-contact connected to the first stationary contact of the first analog relay, a b-contact connected to the second stationary contact of the first analog relay, the c-contact and the b-contact connected by a wire, the d-contact connected to the c-contact, and the b-contact connected to the second star-rocket separation signal source;

[0020] It also includes a j-connector, an f-connector, and an i-connector that are interconnected. The j-connector is connected to the star socket, and the f-connector is connected to the first disconnector connector.

[0021] It also includes an h-contact connected to the first moving contact of the first analog relay, a g-contact connected to the second moving contact of the first analog relay, the h-contact being connected to the g-contact, the h-contact being connected to the i-contact, and the g-contact being connected to the second disconnect connector.

[0022] Preferably, both the first and second satellite-rocket separation signal sources include a 30V signal source.

[0023] Preferably, the second single-unit application includes a third satellite-rocket separation signal source and a fourth satellite-rocket separation signal source. The third satellite-rocket separation signal source is connected to the first stationary contact of the second analog separation relay via a cable, and the fourth satellite-rocket separation signal source is connected to the second stationary contact of the second analog separation relay via a cable.

[0024] The first stationary contact of the second analog disconnect relay is connected to the satellite meter socket via a wire. The satellite meter socket is connected to the first moving contact of the second analog disconnect relay via a wire. The first moving contact of the second analog disconnect relay is connected to the first disconnect connector via a wire. The first disconnect connector is connected to the second user unit via a wire. The second moving contact of the second analog disconnect relay is connected to the second disconnect connector via a wire. The second disconnect connector is connected to the second user unit via a wire.

[0025] Preferably, the second analog separation relay includes an O contact, a K contact, and an N contact that are mutually connected, the K contact being connected to the third satellite-rocket separation signal source, and the O contact being connected to the satellite display socket;

[0026] It also includes an m-contact connected to the first stationary contact of the second analog relay, and an l-contact connected to the second stationary contact of the second analog relay. The m-contact is connected to the l-contact, and the l-contact is connected to the fourth star-rocket separation signal source.

[0027] It also includes a q-contact connected to the first moving contact of the second analog relay, a P-contact connected to the second moving contact of the second analog relay, the q-contact being connected to the P-contact, the P-contact being connected to the second disconnect connector, and the q-contact being connected to the star meter socket.

[0028] Preferably, both the third and fourth satellite-rocket separation signal sources include a 30V signal source.

[0029] Preferably, the first detachable connector includes a first socket and a first plug that are mated together;

[0030] The second disconnect connector includes a second socket and a second plug that engage in a mating process.

[0031] According to the present invention, a star-rocket separation system is provided, wherein the star-rocket separation signal system is installed on the star-rocket.

[0032] Compared with the prior art, the present invention has the following beneficial effects:

[0033] 1. This invention adopts a passive contact-based star-rocket separation signal implementation method. To address the failure mechanism of preventing accidental separation of the star-rocket separation signal, the reliability is improved by using a parallel design of two separation connectors. This invention can be applied to all star-rocket separation signal designs that use two or more separation connectors.

[0034] 2. This invention uses a dual-contact magnetic latching relay in the main power distribution unit to realize the simulated satellite-rocket separation function required for ground testing. To address the possibility of malfunction of the simulated separation relay, a satellite meter socket is designed to be connected in parallel with the simulated separation relay. The satellite meter function plug can be used to meet different needs in ground testing, such as providing satellite-rocket separation signals from the simulated separation relay and pre-launch and on-orbit shielded simulated separation control. This reduces the possibility of erroneous separation signals caused by the simulated separation relay disconnecting and improves the reliability of the satellite-rocket separation signal link. Attached Figure Description

[0035] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0036] Figure 1 This is a schematic diagram illustrating the design principle of generating, simulating, and preventing accidental separation of the star-rocket separation signal in this invention. Detailed Implementation

[0037] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0038] Example 1

[0039] A satellite-rocket separation signal system according to the present invention includes: a first user unit, a second user unit, a main power distributor, a first separation connector, a second separation connector, a satellite display plug, and a satellite display socket. The main power distributor includes a first analog separation relay and a second analog separation relay. The satellite display plug is inserted into the satellite display socket. When the separation function needs to be shielded, the satellite display plug is short-circuited.

[0040] The first single-use unit outputs two star-rocket separation signal sources, which are respectively led to two different contacts of the first analog separation relay. After passing through the first separation connector and the second separation connector, they return to the first single-use unit. The input and output terminals of the first analog separation relay are respectively led to the star meter socket via cables.

[0041] Specifically, the first user unit includes a first satellite-rocket separation signal source and a second satellite-rocket separation signal source. The first satellite-rocket separation signal source is connected to the first stationary contact of the first analog separation relay via a cable, and the second satellite-rocket separation signal source is connected to the second stationary contact of the first analog separation relay via a cable. The first stationary contact of the first analog separation relay is connected to a satellite display socket via a wire, and the satellite display socket is connected to the first moving contact of the first analog separation relay via a wire. The first moving contact of the first analog separation relay is connected to a first separation connector via a wire, and the first separation connector is connected to the first user unit via a wire. The second moving contact of the first analog separation relay is connected to the second separation connector via a wire, and the second separation connector is connected to the first user unit via a wire. The first analog separation relay includes three mutually conductive contacts: e, a, and d. Contact a is connected to the first satellite-rocket separation signal source, and contact e is connected to the satellite display socket. It also includes a c contact connected to the first stationary contact of the first analog relay, a b contact connected to the second stationary contact of the first analog relay, contacts c and b connected via a wire, contact d connected to contact c, and contact b connected to the second satellite-rocket separation signal source. It also includes interconnected J-contact, F-contact, and I-contact. The J-contact connects to the satellite display socket, and the F-contact connects to the first disconnect connector. It also includes an H-contact connected to the first moving contact of the first analog relay, a G-contact connected to the second moving contact of the first analog relay, an H-contact connected to the G-contact, an H-contact connected to the I-contact, and a G-contact connected to the second disconnect connector. Both the first and second satellite-rocket separation signal sources include a 30V signal source.

[0042] The second single-use unit outputs two star-rocket separation signal sources, which are respectively led to two different contacts of the second analog separation relay. After passing through the first separation connector and the second separation connector, they return to the second single-use unit. The input and output terminals of the second analog separation relay are respectively led to the star meter socket via cables.

[0043] Specifically, the second user unit includes a third and a fourth satellite-rocket separation signal source. The third satellite-rocket separation signal source is connected to the first stationary contact of the second analog separation relay via a cable, and the fourth satellite-rocket separation signal source is connected to the second stationary contact of the second analog separation relay via a cable. The first stationary contact of the second analog separation relay is connected to a satellite display socket via a wire. The satellite display socket is connected to the first moving contact of the second analog separation relay via a wire. The first moving contact of the second analog separation relay is connected to a first separation connector via a wire. The first separation connector is connected to the second user unit via a wire. The second moving contact of the second analog separation relay is connected to the second separation connector via a wire. The second separation connector is connected to the second user unit via a wire. The second analog separation relay includes mutually conductive O, K, and N contacts. The K contact is connected to the third satellite-rocket separation signal source, and the O contact is connected to the satellite display socket. It also includes an M contact connected to the first stationary contact of the second analog relay, an L contact connected to the second stationary contact of the second analog relay, an M contact connected to an L contact, and an L contact connected to the fourth satellite-rocket separation signal source. It also includes a q-contact connected to the first moving contact of the second analog relay, a P-contact connected to the second moving contact of the second analog relay, a q-contact connected to the p-contact, a p-contact connected to the second disconnect connector, and a q-contact connected to the satellite display socket. Both the third and fourth satellite-rocket separation signal sources include a 30V signal source.

[0044] The first detachable connector described above includes a first socket and a first plug that are mated together. The second detachable connector includes a second socket and a second plug that are mated together.

[0045] The star meter socket includes contacts A, B, C, and D. Contacts A and B are connected, as are contacts C and D. Contact A and contact e are connected via wires. Contact D is connected to contact q and the first tap connector via wires. Contact B is connected to contact j via wires, and contact C is connected to contact o via wires. The contacts of the star meter socket and the star meter plug correspond one-to-one.

[0046] Example 2

[0047] Based on Embodiment 1, according to the present invention, a method for analyzing satellite-rocket separation signals is provided, such as... Figure 1 As shown, it includes:

[0048] The first 30V star-rocket separation signal source, output by a microcontroller, is connected via a cable to contact a in the first group of three interconnected contacts of the main power distribution unit. The second 30V star-rocket separation signal source, output by a microcontroller, is connected via a cable to contact b, corresponding to contact 1B of the second auxiliary contact of the first analog star-rocket separation relay of the main power distribution unit. The third 30V star-rocket separation signal source, output by a microcontroller, is connected via a cable to contact k, one of the three interconnected contacts in the second group of the main power distribution unit. The fourth 30V star-rocket separation signal source, output by a microcontroller, is connected via a cable to contact l, corresponding to contact 2B of the second auxiliary contact of the second analog star-rocket separation relay of the main power distribution unit.

[0049] Connect the d contact of the first group of three interconnected contacts of the main power distribution unit to the c contact corresponding to the first auxiliary contact 1A of the first simulated star-rocket separation relay using a wire. Then connect the n contact of the second group of three interconnected contacts of the main power distribution unit to the m contact corresponding to the first auxiliary contact 2A of the second simulated star-rocket separation relay using a wire.

[0050] Connect the C contact of the first group of three interconnected contacts of the main power distributor to the A contact of the star meter socket via a wire. Connect the O contact of the second group of three interconnected contacts of the main power distributor to the C contact of the star meter socket via a wire. The contacts of the star meter socket and the star meter plug correspond one-to-one.

[0051] Connect the A and B contacts, and the C and D contacts of the star meter plug end with wires, naming this star meter plug the "natural short-circuit star meter plug". Connect the B contact of the star meter socket to the j contact of the three interconnected contacts in the third group of the main distributor via a cable. Connect the i contact of the three interconnected contacts in the third group of the main distributor via a wire to the h contact corresponding to the output terminal of the first auxiliary contact 1A of the first analog star-rocket separation relay. Connect the D contact of the star meter socket to the q contact corresponding to the output terminal of the first auxiliary contact 2A of the second analog star-rocket separation relay of the main distributor via a cable.

[0052] Connect the f contact of the three interconnected contacts in the third group of the main power distribution unit to the socket of plug 1 via a cable, and then send the first star-rocket separation signal 1 back to the first microcontroller from another point of the plug 1 socket via a cable; connect the g contact corresponding to the output terminal of the second auxiliary contact 1B of the first analog star-rocket separation relay of the main power distribution unit to the socket of plug 2 via a cable, and then send the other star-rocket separation signal 1 back to the first microcontroller from another point of the plug 2 socket via a cable. The contacts of the plug socket and the plug correspond one-to-one.

[0053] Another wire is led out from the D contact of the star meter socket and connected to the socket of plug 1 via a cable. Then, the first star-rocket separation signal 2 is sent back to the second microcontroller via a cable from another point of the plug 1 socket. The p contact corresponding to the output terminal of the second auxiliary contact 2B of the second analog star-rocket separation relay of the main power distributor is connected to the socket of plug 2 via a cable. Then, the other star-rocket separation signal 2 is sent back to the second microcontroller via a cable from another point of the plug 2 socket.

[0054] When it is necessary to avoid the possibility of malfunction of the analog disconnect relay, plugging in the natural color short-circuit star meter plug will bypass the analog disconnect relay in the main distributor. At this time, only when both plug 1 and plug 2 are correctly disconnected can the star-rocket disconnect signal be generated normally. In this embodiment, plug 1 and plug 2 are described as the first disconnect connector and the second disconnect connector, respectively.

[0055] This invention aims to prevent accidental triggering of satellite-launch separation. Each user unit outputs two satellite-launch separation signal sources, which are respectively led to two different contacts of the same set of analog separation relays. After passing through two separation connectors, the signals return to the user unit to provide the required satellite-launch separation signals. At the same time, the input and output terminals of the main power distribution unit for each satellite-launch separation signal are led to the satellite display socket via cables. When it is necessary to shield the analog separation function before launch, the analog satellite-launch separation relays can be shorted through the satellite display function plug, causing them to fail. At this time, the satellite-launch separation signal can only be correctly generated when both separation connectors are correctly separated, thereby preventing accidental triggering of satellite-launch separation.

[0056] This invention designs the two separation connectors to output the satellite-launch separation signal in parallel, and adds the function of bypassing the satellite table to simulate the satellite-launch separation relay. This ensures that the satellite-launch separation signal is provided by the simulated satellite-launch separation relay during ground testing, and avoids fatal failures such as accidental issuance of simulated satellite-launch separation commands before launch or malfunction of the simulated separation relay due to severe vibration environment during the active phase, thereby improving the reliability of the link that generates the satellite-launch separation signal.

[0057] Example 3

[0058] According to the present invention, a star-rocket separation system is provided, wherein the star-rocket separation signal system is installed on the star-rocket.

[0059] Those skilled in the art will understand that, besides implementing the system and its various devices, modules, and units provided by this invention in the form of purely computer-readable program code, the same functions can be achieved entirely through logical programming of the method steps, making the system and its various devices, modules, and units of this invention function in the form of logic gates, switches, application-specific integrated circuits, programmable logic controllers, and embedded microcontrollers. Therefore, the system and its various devices, modules, and units provided by this invention can be considered as a hardware component, and the devices, modules, and units included therein for implementing various functions can also be considered as structures within the hardware component; alternatively, the devices, modules, and units for implementing various functions can be considered as both software modules implementing the method and structures within the hardware component.

[0060] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A satellite-rocket separation signal system, characterized by, include: The system includes a first stand-alone unit, a second stand-alone unit, a main power distributor, a first disconnect connector, a second disconnect connector, a satellite meter plug, and a satellite meter socket. The main power distributor includes a first analog disconnect relay and a second analog disconnect relay. The satellite meter plug is connected to the satellite meter socket. The first single-use unit outputs two star-rocket separation signal sources, which are respectively led to two different contacts of the first analog separation relay. After passing through the first separation connector and the second separation connector, they return to the first single-use unit. The input and output terminals of the first analog separation relay are respectively led to the star meter socket via cables. The second single-use unit outputs two star-rocket separation signal sources, which are respectively led to two different contacts of the second analog separation relay. After passing through the first separation connector and the second separation connector, they return to the second single-use unit. The input and output terminals of the second analog separation relay are respectively led to the star meter socket via cables. When the shielding separation function is required, short-circuit the star meter connector; The first single-unit application includes a first satellite-rocket separation signal source and a second satellite-rocket separation signal source. The first satellite-rocket separation signal source is connected to the first stationary contact of the first analog separation relay via a cable, and the second satellite-rocket separation signal source is connected to the second stationary contact of the first analog separation relay via a cable. The first stationary contact of the first analog disconnect relay is connected to the satellite meter socket via a wire. The satellite meter socket is connected to the first moving contact of the first analog disconnect relay via a wire. The first moving contact of the first analog disconnect relay is connected to the first disconnect connector via a wire. The first disconnect connector is connected to the first user unit via a wire. The second moving contact of the first analog disconnect relay is connected to the second disconnect connector via a wire. The second disconnect connector is connected to the first user unit via a wire.

2. The star-rocket separation signal system according to claim 1, characterized in that, The first analog separation relay includes an e contact, an a contact, and a d contact that are mutually connected. The a contact is connected to the first satellite-rocket separation signal source, and the e contact is connected to the satellite display socket. It also includes a c-contact connected to the first stationary contact of the first analog relay, a b-contact connected to the second stationary contact of the first analog relay, the c-contact and the b-contact connected by a wire, the d-contact connected to the c-contact, and the b-contact connected to the second star-rocket separation signal source; It also includes a j-connector, an f-connector, and an i-connector that are interconnected. The j-connector is connected to the star socket, and the f-connector is connected to the first disconnector connector. It also includes an h-contact connected to the first moving contact of the first analog relay, a g-contact connected to the second moving contact of the first analog relay, the h-contact being connected to the g-contact, the h-contact being connected to the i-contact, and the g-contact being connected to the second disconnect connector.

3. The star-rocket separation signal system according to claim 1, characterized in that, Both the first satellite-rocket separation signal source and the second satellite-rocket separation signal source include a 30V signal source.

4. The star-rocket separation signal system according to claim 1, characterized in that, The second single-unit application includes a third satellite-rocket separation signal source and a fourth satellite-rocket separation signal source. The third satellite-rocket separation signal source is connected to the first stationary contact of the second analog separation relay via a cable, and the fourth satellite-rocket separation signal source is connected to the second stationary contact of the second analog separation relay via a cable. The first stationary contact of the second analog disconnect relay is connected to the satellite meter socket via a wire. The satellite meter socket is connected to the first moving contact of the second analog disconnect relay via a wire. The first moving contact of the second analog disconnect relay is connected to the first disconnect connector via a wire. The first disconnect connector is connected to the second user unit via a wire. The second moving contact of the second analog disconnect relay is connected to the second disconnect connector via a wire. The second disconnect connector is connected to the second user unit via a wire.

5. The star-rocket separation signal system according to claim 4, characterized in that, The second analog separation relay includes an o-contact, a k-contact, and an n-contact that are mutually connected. The k-contact is connected to the third satellite-rocket separation signal source, and the o-contact is connected to the satellite display socket. It also includes an m-contact connected to the first stationary contact of the second analog relay, an l-contact connected to the second stationary contact of the second analog relay, the m-contact being connected to the l-contact, and the l-contact being connected to the fourth star-rocket separation signal source; It also includes a q-contact connected to the first moving contact of the second analog relay, a P-contact connected to the second moving contact of the second analog relay, the q-contact being connected to the P-contact, the P-contact being connected to the second disconnect connector, and the q-contact being connected to the star meter socket.

6. The star-rocket separation signal system according to claim 4, characterized in that, Both the third and fourth satellite-rocket separation signal sources include a 30V signal source.

7. The star-rocket separation signal system according to claim 1, characterized in that, The first separate connector includes a first socket and a first plug that are mated together; The second disconnect connector includes a second socket and a second plug that engage in a mating process.

8. A star-rocket separation system, characterized in that, The satellite-rocket separation signal system according to any one of claims 1-7 is used, and the satellite-rocket separation signal system is installed on the satellite-rocket.

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