Configurable carrier rocket multi-satellite launch control system

Abstract

The invention discloses a configurable carrier rocket multi-satellite launching control system, and relates to the technical field of spaceflight, and the system comprises a satellite-rocket separation control combination, at least one flight control combination, a resistor box used for protecting a satellite-rocket separation time sequence path, and a plurality of satellite separation mechanisms used for satellite installation and separation. Wherein the satellite-rocket separation control combination, each flight control combination and each satellite separation mechanism are all connected with the resistance box; and the satellite-rocket separation control combination communicates with the flight control combination. Under the condition that an original carrier rocket satellite separation control scheme is not changed, more time sequence control is provided by newly adding a satellite-rocket separation control combination, the carrier rocket satellite separation time sequence is greatly increased, and the number of multiple satellites in one rocket is greatly increased.

Description

Technical Field

[0001] The present application relates to the field of aerospace technology, and in particular to a configurable multi-satellite launch control system for a carrier rocket. Background Art

[0002] With the development of aerospace technology, the design and manufacturing technology of rockets have been continuously improved, making it possible to launch multiple satellites with one rocket. Modern rocket design takes into account the deployment requirements of multiple satellites and can accurately send multiple satellites into the predetermined orbit in one launch. With the continuous development of my country's satellite technology, launching multiple satellites with one rocket has become the mainstream launch mode, especially in the field of civil satellites. The mode of launching small satellites in batches and forming constellations in space has gradually become the mainstream, and "combining rockets" to go to the sky has also become the norm for satellite launches.

[0003] At present, my country's multi-satellite launch technology is in a period of rapid development, and the technology is also constantly breaking through. On June 7, 2023, the Lijian-1 Yao-2 carrier rocket set a record of launching 26 satellites in one rocket, but was restricted by the initial design of the rocket and could not provide more satellite separation sequences. With the continuous development of satellite technology, the existing satellite separation sequence can no longer meet the rapidly growing demand for satellite launches. Summary of the invention

[0004] The purpose of this application is to provide a configurable launch vehicle multi-satellite launch control system. Without changing the original launch vehicle satellite separation control scheme, a satellite-rocket separation control combination is added to provide more timing control, thereby achieving a large increase in the launch vehicle satellite separation timing and significantly increasing the number of multiple satellites in one rocket.

[0005] To achieve the above-mentioned purpose, the present application provides a configurable launch vehicle multi-satellite launch control system, including: a satellite-rocket separation control combination, at least one flight control combination, a resistor box for protecting the satellite-rocket separation timing path, and multiple 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 all connected to the resistor box; the satellite-rocket separation control combination communicates with the flight control combination; the satellite-rocket separation control combination: used to receive the timing control instructions sent by the flight control combination, output the satellite-rocket separation control timing; send the timing recovery data message; the flight control combination: used to send the timing control instructions; receive the satellite-rocket separation control timing; receive the timing recovery data message.

[0006] As above, the satellite-rocket separation control combination communicates with the flight control combination via the 1553B bus.

[0007] As above, the satellite-rocket separation control combination includes: a central processing unit component, a power supply component, a first timing component, a second timing component and a bus component; the central processing unit component, the power supply component, the first timing component and the second timing component are all connected to the bus component; wherein, the central processing unit component: is used to complete the collection of timing data, as well as the collection of its own status data; provides external interface, Ethernet, 1553B bus and RS422; receives the timing control instructions sent by the flight control combination, and outputs the satellite-rocket separation control timing; the power supply component: is used to convert the input primary power supply into the secondary power supply required by the internal components of the satellite-rocket separation control combination, and to power the bus component; the first timing component: is used to provide 26-way timing control functions; the second timing component: is used to provide 26-way timing control functions; the bus component: is used to realize the interconnection of signals between boards.

[0008] As mentioned above, the power supply component includes: an input filter circuit, a DC / DC conversion module and an output filter circuit; the input primary power supply is filtered by the input filter circuit to obtain the filtered power supply; the filtered power supply is converted into the secondary power supply required by the internal components of the satellite-rocket separation control combination by the DC / DC conversion module; the secondary power supply is output by the output filter circuit to power the bus component.

[0009] As above, where the primary power supply is 28V.

[0010] As above, where the secondary power supply is ±5V.

[0011] As above, the central processing unit component is connected to the first connector, and the first connector provides external interfaces, Ethernet, 1553B bus and RS422.

[0012] As above, the power supply component is connected to the second connector, and external signal interconnection and primary power input are achieved through the second connector.

[0013] As above, the first timing component is connected to the third connector, and external signal interconnection is realized through the third connector to connect the pyrotechnics, perform timing control signal output, and analog input.

[0014] As above, the second timing component is connected to the fourth connector, and the external signal interconnection is realized through the fourth connector, connecting the pyrotechnics, performing timing control signal output, and analog input.

[0015] The beneficial effects achieved by this application are as follows:

[0016] (1) The configurable launch vehicle multi-satellite launch control system of the present application, without changing the original launch vehicle satellite separation control scheme, provides more timing control by adding a satellite-rocket separation control combination, thereby achieving a large increase in the launch vehicle satellite separation timing and significantly increasing the number of multiple satellites launched with one rocket.

[0017] (2) The configurable launch vehicle multi-satellite launch control system of the present application adds 52 satellite separation timing controls through the first timing component and the second timing component. According to the specific satellite mission requirements, the separation timing can be flexibly configured to increase the number of multiple satellites launched with one rocket to meet the batch launch mission of small satellites. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in the present application. For ordinary technicians in this field, other drawings can also be obtained based on these drawings.

[0019] Figure 1 A schematic diagram of the structure of an embodiment of a configurable launch vehicle multi-satellite launch control system;

[0020] Figure 2 A functional block diagram of an embodiment of a satellite-rocket separation control combination;

[0021] Figure 3 This is a schematic diagram of the timing output of the satellite-rocket separation control. DETAILED DESCRIPTION

[0022] The following is a clear and complete description of the technical solutions in the embodiments of the present invention in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative work are within the scope of protection of the present invention.

[0023] like Figure 1-2 As shown, the present application provides a configurable launch vehicle multi-satellite launch control system, including: a satellite-rocket separation control assembly, at least one flight control assembly, a resistor box for protecting a satellite-rocket separation timing path, and a plurality of satellite separation mechanisms for satellite installation and separation; wherein the satellite-rocket separation control assembly, each flight control assembly, and each satellite separation mechanism are connected to the resistor box; the satellite-rocket separation control assembly communicates with the flight control assembly; the satellite-rocket separation control assembly: is used to receive a timing control instruction sent by the flight control assembly (i.e.: Figure 1The flight control combination is used to send timing control instructions, receive the timing control instruction of the separation of the satellite and the rocket, and receive the timing recovery data message.

[0024] Specifically, the satellite payload is composed of a plurality of satellite separation mechanisms for installing and separating satellites.

[0025] Furthermore, the satellite-rocket separation control combination communicates with the flight control combination through the 1553B bus, but is not limited to the 1533B bus. The present application prefers the 1533B bus, and the control signal of the 1533B bus is stable and reliable.

[0026] Specifically, the satellite-rocket separation control combination communicates with the CPU module of the flight control combination through the 1553B bus.

[0027] Furthermore, the satellite-rocket separation control combination includes: a CPU (central processing unit) component, a power supply component, a first timing component, a second timing component and a BUS (bus) component; the CPU component, the power supply component, the first timing component, and the second timing component are all connected to the BUS component.

[0028] Among them, the CPU component is used to complete the collection of timing data and its own status data; provide external interfaces, Ethernet, 1553B bus and RS422; receive timing control instructions sent by the flight control combination, and output the satellite-rocket separation control timing.

[0029] Specifically, the CPU component is used to complete functions such as data acquisition, external interface implementation and logic control.

[0030] Power supply assembly: used to convert the input primary power into the secondary power required by the internal components of the satellite-rocket separation control combination and to power the BUS components.

[0031] Furthermore, the power supply component includes: an input filter circuit, a DC / DC (direct current / direct current) conversion module and an output filter circuit; the input primary power supply is filtered by the input filter circuit to obtain a filtered power supply; the filtered power supply is converted into a secondary power supply required by the internal components of the satellite-rocket separation control combination by the DC / DC module; the secondary power supply is output by the output filter circuit to power the BUS component.

[0032] Specifically, the power supply is designed with a highly integrated and highly reliable DC / DC (direct current / direct current) conversion module and a peripheral filter circuit.

[0033] Furthermore, the specific value of the primary power supply is set according to actual conditions, and the preferred value in this application is 28V.

[0034] Furthermore, the specific value of the secondary power supply is set according to actual conditions, and the preferred value in this application is ±5V.

[0035] The first timing component: used to provide 26-way timing control function.

[0036] The second timing component: used to provide 26-way timing control function.

[0037] Specifically, the first timing component and the second timing component jointly realize the output of 52 timing control signals, that is, the first timing component outputs 26 timing control signals, and the second timing component outputs 26 timing control signals, which are used to control the solid-state relays in the first timing component and the second timing component to turn on and off. When the solid-state relay is turned on, the timing control signal is output, and when the solid-state relay is turned off, the timing control signal is not output. Each timing control signal is dual redundant, and the timing recovery function is realized by the recovery circuit in the first timing component and the second timing component, and the timing switch quantity emitted is collected by the recovery circuit.

[0038] BUS component: used to interconnect signals between boards.

[0039] Specifically, the signals between the CPU component and the BUS component are interconnected, and the BUS component supplies power to the CPU component. The specific value of the power supply is set according to the actual situation. The preferred value in this application is: 5V; the communication between the BUS component and the CPU component is RS422, but is not limited to RS422. The preferred application is to transmit analog quantities through RS422 communication.

[0040] The power supply component and the BUS component are interconnected by signals, and the power supply component supplies power to the BUS component (ie, secondary power supply). The specific value of the power supply is set according to the actual situation, and the preferred value in this application is: 5V.

[0041] The first timing component and the BUS component are signal interconnected, and the BUS component supplies power to the first timing component. The specific value of the power supply is set according to the actual situation. The preferred value in this application is: 5V; the communication between the BUS component and the first timing component is RS422, but is not limited to RS422. The preferred application is to transmit analog quantities through RS422 communication.

[0042] The second timing component and the BUS component are signal interconnected, and the BUS component supplies power to the second timing component. The specific value of the power supply is set according to the actual situation. The preferred value in this application is: 5V; the communication between the BUS component and the second timing component is RS422, but is not limited to RS422. The preferred application is to transmit analog quantities through RS422 communication.

[0043] Furthermore, the CPU component is connected to the first connector, and the first connector provides an external interface, Ethernet, 1553B bus and RS422.

[0044] Furthermore, the power supply assembly is connected to the second connector, and external signal interconnection and instrument power input (ie, primary power supply) are realized through the second connector.

[0045] Specifically, the specific value of the instrument voltage is set according to the actual situation, and the preferred value in this application is 28V.

[0046] Furthermore, the first timing component is connected to the third connector, and external signal interconnection is achieved through the third connector, connecting the pyrotechnics, and performing timing control signal output and analog input.

[0047] Furthermore, the second timing component is connected to the fourth connector, and external signal interconnection is realized through the fourth connector, connecting the pyrotechnics, performing timing control signal output, and analog input.

[0048] Furthermore, the specific value of the pyrotechnic voltage is set according to actual conditions, and 28V is preferred in this application.

[0049] like Figure 3 As shown, as an embodiment, the SOC (system on chip) is connected to the output module of the FPGA (field programmable gate array) through the EMIF (external memory interface), the FPGA is connected to the driver of the first timing component or the second timing component, the driver is also connected to the 5V power supply, the driver is connected to the LSSR-0404, the LSSR-0404 is connected to the bus, and the LSSR-0404 (i.e., solid state relay) outputs the satellite-rocket separation control timing (i.e., Figure 3 Timing output in ).

[0050] Specifically, the first timing component and the second timing component implement 52 control signal outputs for controlling the solid-state relay to open and close. Each control signal is dual redundant, and controls the conduction and shutdown of the solid-state relay by controlling the positive terminal of the solid-state relay.

[0051] The beneficial effects achieved by this application are as follows:

[0052] (1) The configurable launch vehicle multi-satellite launch control system of the present application, without changing the original launch vehicle satellite separation control scheme, provides more timing control by adding a satellite-rocket separation control combination, thereby achieving a large increase in the launch vehicle satellite separation timing and significantly increasing the number of multiple satellites launched with one rocket.

[0053] (2) The configurable launch vehicle multi-satellite launch control system of the present application adds 52 satellite separation timing controls through the first timing component and the second timing component. According to the specific satellite mission requirements, the separation timing can be flexibly configured to increase the number of multiple satellites launched with one rocket to meet the batch launch mission of small satellites.

[0054] Although the preferred embodiments of the present application have been described, those skilled in the art may make additional changes and modifications to these embodiments once they are aware of the basic creative concepts. Therefore, the scope of protection of the present application is intended to be interpreted as including the preferred embodiments and all changes and modifications that fall within the scope of the present application. Obviously, those skilled in the art may make various changes and modifications to the present application without departing from the spirit and scope of the present application. Thus, if these modifications and variations of the present application fall within the scope of the protection scope of the present application and its equivalent technology, the present application is also intended to include these modifications and variations.

Claims

1. A configurable launch vehicle multi-satellite launch control system, characterized in that: include: A satellite-rocket separation control assembly, at least one flight control assembly, a resistor box for protecting the satellite-rocket separation timing path, and a plurality of satellite separation mechanisms for satellite installation and separation; Among them, the satellite-rocket separation control assembly, each flight control assembly and each satellite separation mechanism are connected to the resistor box; the satellite-rocket separation control assembly communicates with the flight control assembly; Satellite-rocket separation control combination: used to receive the timing control instructions sent by the flight control combination, output the satellite-rocket separation control timing; send timing recovery data messages; Flight control combination: used to send timing control instructions; receive satellite-rocket separation control timing; receive timing retrieval data messages.

2. The configurable launch vehicle multi-satellite launch control system according to claim 1, characterized in that: The satellite-rocket separation control combination communicates with the flight control combination via the 1553B bus.

3. The configurable launch vehicle multi-satellite launch control system according to claim 1, characterized in that: The satellite-rocket separation control assembly includes: a central processing unit component, a power supply component, a first timing component, a second timing component and a bus component; the central processing unit component, the power supply component, the first timing component and the second timing component are all connected to the bus component; Among them, the central processing unit component is used to complete the collection of timing data and its own status data; provide external interfaces, Ethernet, 1553B bus and RS422; receive the timing control instructions sent by the flight control combination, and output the satellite-rocket separation control timing; Power supply assembly: used to convert the input primary power into the secondary power required by the internal components of the satellite-rocket separation control combination and to power the bus components; The first timing component: used to provide 26-way timing control function; The second timing component: used to provide 26-way timing control function; Bus component: used to interconnect signals between boards.

4. The configurable launch vehicle multi-satellite launch control system according to claim 3, characterized in that: The power supply assembly includes: an input filter circuit, a DC / DC conversion module and an output filter circuit; The input primary power is filtered through an input filter circuit to obtain a filtered power supply; The filtered power is converted into the secondary power required by the internal components of the satellite-rocket separation control combination through the DC / DC conversion module; The secondary power is output through the output filter circuit to power the bus components.

5. The configurable launch vehicle multi-satellite launch control system according to claim 4, characterized in that: The primary power supply is 28V.

6. The configurable launch vehicle multi-satellite launch control system according to claim 4, characterized in that: The secondary power supply is ±5V.

7. The configurable launch vehicle multi-satellite launch control system according to claim 3, characterized in that: The central processing unit component is connected to the first connector, and provides external interfaces, Ethernet, 1553B bus and RS422 through the first connector.

8. The configurable launch vehicle multi-satellite launch control system according to claim 3, characterized in that: The power supply component is connected to the second connector, and external signal interconnection and primary power input are realized through the second connector.

9. The configurable launch vehicle multi-satellite launch control system according to claim 3, characterized in that: The first timing component is connected to the third connector, and external signal interconnection is realized through the third connector, connecting the pyrotechnics, and performing timing control signal output and analog input.

10. The configurable launch vehicle multi-satellite launch control system according to claim 3, characterized in that: The second timing component is connected to the fourth connector, and external signal interconnection is realized through the fourth connector, connecting the pyrotechnics, and performing timing control signal output and analog input.

Images