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CN-119872919-B - Configurable carrier rocket multi-star launching control system

CN119872919BCN 119872919 BCN119872919 BCN 119872919BCN-119872919-B

Abstract

The application discloses a configurable carrier rocket multi-satellite launching control system, which relates to the technical field of spaceflight and comprises a satellite-rocket separation control combination, at least one flight control combination, a resistor box for protecting a satellite-rocket separation time sequence passage and a plurality of satellite separation mechanisms for satellite installation and separation, wherein the satellite-rocket separation control combination, each flight control combination and each satellite separation mechanism are connected with the resistor box, and the satellite-rocket separation control combination is communicated with the flight control combination. Under the condition of not changing the original carrier rocket satellite separation control scheme, the application provides more time sequence control by adding a satellite-rocket separation control combination, realizes the great increase of the carrier rocket satellite separation time sequence, and greatly improves the number of satellites of one rocket.

Inventors

  • WEI DE

Assignees

  • 北京中科宇航技术有限公司

Dates

Publication Date
20260512
Application Date
20250224

Claims (9)

  1. 1.A configurable carrier rocket multi-satellite launching control system is characterized by comprising a satellite-rocket separation control combination, at least one flight control combination, a resistor box for protecting a satellite-rocket separation time sequence passage and a plurality of satellite separation mechanisms for satellite installation and separation; The satellite-rocket separation control combination, each flight control combination and each satellite separation mechanism are connected with the resistor box; The satellite-rocket separation control combination is used for receiving a time sequence control instruction sent by the flight control combination, outputting a satellite-rocket separation control time sequence, and sending a time sequence stoping data message; the flight control combination is used for sending a time sequence control instruction, receiving a satellite and arrow separation control time sequence, and receiving a time sequence stoping data message; the satellite and rocket separation control combination comprises a central processing unit component, a power supply component, a first time sequence component, a second time sequence component and a bus component, wherein the central processing unit component, the power supply component, the first time sequence component and the second time sequence component are all connected with the bus component; The central processing unit component is used for completing acquisition of time sequence stoping data and acquisition of state data of the central processing unit component, providing an external interface, an Ethernet, a 1553B bus and an RS422, receiving a time sequence control instruction sent by a flight control combination and outputting a satellite and rocket separation control time sequence; The power supply component is used for converting the input primary power supply into a secondary power supply required by the internal component of the satellite and rocket separation control combination and supplying power for the bus component; the first time sequence component is used for providing 26 paths of time sequence control functions; the second time sequence component is used for providing 26 paths of time sequence control functions; the bus assembly is used for realizing interconnection of signals between boards; And each time sequence control signal is subjected to double redundancy, and meanwhile, a time sequence stoping function is realized through stoping circuits in the first time sequence component and the second time sequence component, and the time sequence switching value sent by the stoping circuits is collected.
  2. 2. A configurable launch vehicle control system according to claim 1 wherein the satellite-rocket separation control assembly communicates with the flight control assembly via a 1553B bus.
  3. 3. The configurable launch vehicle multi-satellite control system of claim 1, wherein the power assembly comprises an input filter circuit, a dc/dc conversion module, and an output filter circuit; Filtering the input primary power supply through an input filter circuit to obtain a filtered power supply; converting the filtered power supply into a secondary power supply required by an internal component of the satellite-rocket separation control combination through a direct current/direct current conversion module; And outputting a secondary power supply through an output filter circuit to supply power for the bus assembly.
  4. 4. A configurable launch control system according to claim 3 wherein the primary power source is 28V.
  5. 5. A configurable launch control system of a launch vehicle according to claim 3 wherein the secondary power source is ± 5V.
  6. 6. A configurable launch vehicle control system according to claim 1 wherein the central processor unit is connected to a first connector through which the external interface, ethernet, 1553B bus and RS422 are provided.
  7. 7. A configurable launch vehicle control system according to claim 1 wherein the power supply assembly is connected to the second connector, external signal interconnection is achieved through the second connector, and primary power is input.
  8. 8. A configurable launch vehicle control system according to claim 1 wherein the first timing assembly is connected to a third connector through which external signal interconnection is achieved, and wherein the connection is made to the initiating explosive device, the timing control signal output is made, and the analog input is made.
  9. 9. A configurable launch vehicle control system according to claim 1 wherein the second timing assembly is connected to a fourth connector through which external signal interconnection is achieved, and wherein the connection is made to the initiating explosive device, the timing control signal output is made, and the analog input is made.

Description

Configurable carrier rocket multi-star launching control system Technical Field The application relates to the technical field of aerospace, in particular to a configurable carrier rocket multi-star launching control system. Background Along with the development of aerospace technology, the design and manufacturing technology of rockets are continuously improved, so that one-rocket multi-satellite launching is possible, the modern rocket design considers the deployment requirement of multiple satellites, and the multiple satellites can be accurately sent into a preset orbit in one launching. With the continuous development of satellite technology in China, one arrow and multiple satellites become a mainstream emission mode, especially in the field of civil satellites, small satellites emit in batches, a mode of constituteing constellations in space becomes a mainstream gradually, and the "exchange fire arrow" is increasingly becoming a satellite emission normalcy on the sky. At present, the one-arrow-multiple-star launching technology in China is in a rapid development period, and the one-arrow-multiple-star launching technology is also continuously broken through. The method is characterized in that 2023, 6 and 7 days, a rocket 26-star mode is adopted by a rocket-like remote two-rocket type carrier rocket, so that a record of one rocket for multiple satellites in China is created, but more satellite separation time sequences cannot be provided due to the initial design scheme of the rocket. With the continuous development of satellite technology, the existing satellite separation timing cannot meet the rapidly growing satellite transmission requirement. Disclosure of Invention The application aims to provide a configurable carrier rocket multi-satellite launching control system, which can provide more time sequence control by adding a satellite-rocket separation control combination under the condition of not changing the original carrier rocket satellite separation control scheme, thereby realizing the great increase of the carrier rocket satellite separation time sequence and greatly improving the number of multiple satellites of one rocket. The application provides a configurable carrier rocket multi-satellite launching control system which comprises a satellite-rocket separation control combination, at least one flight control combination, a resistor box for protecting a satellite separation time sequence passage and a plurality of satellite separation mechanisms for satellite installation and separation, wherein the satellite-rocket separation control combination, each flight control combination and each satellite separation mechanism are connected with the resistor box, the satellite-rocket separation control combination is communicated with the flight control combination, the satellite-rocket separation control combination is used for receiving time sequence control instructions sent by the flight control combination, outputting satellite separation control time sequences, sending time sequence recovery data messages, the flight control combination is used for sending time sequence control instructions, receiving the satellite separation control time sequences and receiving the time sequence recovery data messages. As above, the satellite and rocket separation control combination communicates with the flight control combination via the 1553B bus. The satellite and arrow separation control combination comprises a central processing unit component, a power supply component, a first time sequence component, a second time sequence component and a bus component, wherein the central processing unit component, the power supply component, the first time sequence component and the second time sequence component are all connected with the bus component, the central processing unit component is used for completing acquisition of time sequence stopdata and acquisition of state data of the central processing unit, an external interface, an Ethernet, a 1553B bus and an RS422 are provided, a time sequence control instruction sent by a flight control combination is received, a satellite and arrow separation control time sequence is output, the power supply component is used for converting an input primary power supply into a secondary power supply required by an internal component of the satellite and arrow separation control combination to supply power for the bus component, the first time sequence component is used for providing 26 paths of time sequence control functions, the second time sequence component is used for providing 26 paths of time sequence control functions, and the bus component is used for realizing interconnection of signals between boards. The power supply assembly comprises an input filter circuit, a direct current/direct current conversion module and an output filter circuit, wherein the input filter circuit is used for filtering an input primary power supply to obtain a filtered power supply,