A configurable launch vehicle multi-satellite control system
By adding a new satellite-rocket separation control assembly, utilizing a central processing unit, power supply, and timing components, more satellite separation timing control can be achieved, solving the problem of limited satellite separation timing, increasing the number of satellites launched on a single rocket, and meeting the needs of batch launches of small satellites.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- BEIJING ZHONGKE AEROSPACE TECH CO LTD
- Filing Date
- 2025-02-24
- Publication Date
- 2026-05-12
AI Technical Summary
The existing satellite separation timing cannot meet the rapidly growing demand for satellite launches, resulting in a limitation on the number of satellites that can be launched in a single launch.
By adding a new satellite-launch separation control assembly, including a central processing unit, power supply unit, first and second timing units, and bus unit, and communicating with the flight control assembly via the 1553B bus, more timing control is provided, and satellite separation timing is enhanced.
Without changing the original rocket separation control scheme, the satellite separation sequence is significantly increased, the number of satellites launched in one rocket is increased, and the batch launch mission of small satellites is met.
Smart Images
Figure CN119872919B_ABST
Abstract
Description
Technical Field
[0001] This application relates to the field of aerospace technology, and in particular to a configurable multi-satellite launch control system for a launch vehicle. Background Technology
[0002] With the development of aerospace technology and the continuous advancement of rocket design and manufacturing techniques, multiple satellite launches have become possible. Modern rocket designs take into account the deployment requirements of multiple satellites, enabling the precise delivery of multiple satellites into their designated orbits in a single launch. As my country's satellite technology continues to develop, multiple satellite launches have become the mainstream launch mode, especially in the civilian satellite field. The model of launching small satellites in batches and forming constellations in space is gradually becoming the norm, and "rocket-fueled" launches are increasingly becoming the standard for satellite launches.
[0003] Currently, my country's multi-satellite launch technology is in a period of rapid development, and breakthroughs are constantly being made. On June 7, 2023, the Lijian-1 Y2 carrier rocket set a new record for my country by launching 26 satellites in one launch. However, due to limitations in the initial design of the rocket, it could not provide more satellite separation sequences. With the continuous development of satellite technology, the existing satellite separation sequences 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 new satellite-launcher separation control combination is added to provide more timing control, thereby significantly increasing the launch vehicle satellite separation timing and greatly improving the number of satellites launched in one launch.
[0005] To achieve the above objectives, this application provides a configurable multi-satellite launch control system for a launch vehicle, comprising: a satellite-rocket separation control assembly, at least one flight control assembly, 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 assembly, each flight control assembly, and each satellite separation mechanism are all 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 timing control commands sent by the flight control assembly, output satellite-rocket separation control timing, and send timing data recovery messages; the flight control assembly is used to send timing control commands, receive satellite-rocket separation control timing, and receive timing data recovery messages.
[0006] As shown above, the star-rocket separation control unit communicates with the flight control unit via the 1553B bus.
[0007] As described above, the satellite-launch separation control assembly includes: a central processing unit (CPU), a power supply unit, a first timing component, a second timing component, and a bus component. The CPU, power supply, first timing component, and second timing component are all connected to the bus component. Specifically, the CPU is used to acquire timing data and its own status data; it provides external interfaces, Ethernet, 1553B bus, and RS422; it receives timing control commands from the flight control assembly and outputs the satellite-launch separation control timing. The power supply unit converts the input primary power into the secondary power required by the internal components of the satellite-launch separation control assembly, powering the bus component. The first timing component provides 26-channel timing control functions. The second timing component provides 26-channel timing control functions. The bus component enables interconnection of signals between boards.
[0008] As described above, the power supply components include: an input filter circuit, a DC / DC converter module, and an output filter circuit; the input filter circuit filters the primary power supply to obtain the filtered power supply; the DC / DC converter module converts the filtered power supply into the secondary power supply required by the internal components of the star-rocket separation control assembly; and the output filter circuit outputs the secondary power supply to power the bus components.
[0009] As shown above, the primary power supply is 28V.
[0010] As shown above, the secondary power supply is ±5V.
[0011] As shown above, the central processing unit is connected to the first connector, which provides external interfaces, Ethernet, 1553B bus and RS422.
[0012] As shown above, the power supply component is connected to the second connector, through which external signal interconnection and primary power input are achieved.
[0013] As shown above, the first timing component is connected to the third connector, which enables external signal interconnection, connection to thermal power, timing control signal output, and analog input.
[0014] As shown above, the second timing component is connected to the fourth connector, which enables external signal interconnection, connection to thermal power, 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 this application, without changing the original launch vehicle satellite separation control scheme, adds a satellite-rocket separation control combination to provide more timing control, thereby greatly increasing the launch vehicle satellite separation timing and significantly increasing the number of satellites launched in one rocket.
[0017] (2) The configurable launch vehicle multi-satellite launch control system of this 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 number of satellites launched in one rocket can be increased by flexibly configuring the separation timing to meet the batch launch mission of small satellites. Attached Figure Description
[0018] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in this application. For those skilled in the art, other drawings can be obtained based on these drawings.
[0019] Figure 1 A schematic diagram of one embodiment of a configurable multi-satellite launch control system for a launch vehicle;
[0020] Figure 2 Functional block diagram of one embodiment of the star-rocket separation control combination;
[0021] Figure 3 This is a schematic diagram of the timing output for the star-rocket separation control. Detailed Implementation
[0022] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.
[0023] like Figure 1-2 As shown, this application provides a configurable multi-satellite launch control system for a launch vehicle, comprising: a satellite-rocket separation control assembly, at least one flight control assembly, 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 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 timing control commands sent by the flight control assembly (i.e.: Figure 1The system includes timing control command messages, outputting satellite-rocket separation control timing, sending timing data recovery messages, and flight control assembly: used to send timing control commands, receive satellite-rocket separation control timing, and receive timing data recovery messages.
[0024] Specifically, the satellite payload consists of multiple satellite separation mechanisms used for satellite installation and separation.
[0025] Furthermore, the star-rocket separation control assembly communicates with the flight control assembly via a 1553B bus, but is not limited to a 1533B bus. In this application, the 1533B bus is preferred, as the control signal of the 1533B bus is stable and reliable.
[0026] Specifically, the star-rocket separation control unit communicates with the CPU module of the flight control unit via the 1553B bus.
[0027] Furthermore, the star-rocket separation control assembly 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, power supply component, first timing component, and second timing component are all connected to the BUS component.
[0028] The CPU component is used to acquire timing data and its own status data; it provides external interfaces, Ethernet, 1553B bus and RS422; it receives timing control commands sent by the flight control unit and outputs 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 unit: Used to convert the input primary power supply into the secondary power supply required by the internal components of the star-rocket separation control assembly, and to power the BUS component.
[0031] Furthermore, the power supply components include: an input filter circuit, a DC / DC converter module, and an output filter circuit; the input filter circuit filters the primary power supply to obtain filtered power; the DC / DC converter module converts the filtered power supply into the secondary power supply required by the internal components of the star-rocket separation control assembly; and the output filter circuit outputs the secondary power supply to power the BUS components.
[0032] Specifically, the power supply is designed using a highly integrated and reliable DC / DC converter module and external filter circuits.
[0033] Furthermore, the specific value of the primary power supply is set according to the actual situation, and in this application, it is preferably 28V.
[0034] Furthermore, the specific value of the secondary power supply is set according to the actual situation, and in this application, it is preferably ±5V.
[0035] First timing component: used to provide 26-channel timing control functions.
[0036] Second timing component: used to provide 26-channel timing control function.
[0037] Specifically, the first and second timing components work together to achieve 52-channel timing control signal output. Specifically, the first timing component outputs 26 timing control signals, and the second timing component outputs 26 timing control signals. These signals are used to control the opening and closing of solid-state relays in the first and second timing components. When a solid-state relay is open, a timing control signal is output; when a solid-state relay is closed, no timing control signal is output. Each timing control signal is doubly redundant. Simultaneously, timing retrieval is achieved through the retrieval circuits in both the first and second timing components, which collect the emitted timing switching signals.
[0038] BUS component: Used to enable interconnection of signals between boards.
[0039] Specifically, the CPU component and the BUS component are interconnected by signals. The BUS component supplies power to the CPU component. The specific power supply value is set according to the actual situation. In this application, it is preferred to be 5V. The BUS component and the CPU component communicate via RS422, but it is not limited to RS422. In this application, it is preferred to transmit analog signals via RS422 communication.
[0040] The power supply component and the BUS component are interconnected by signal. The power supply component supplies power to the BUS component (i.e., secondary power supply). The specific value of the power supply is set according to the actual situation. In this application, it is preferred to be 5V.
[0041] The first timing component and the BUS component are interconnected by signals. The BUS component supplies power to the first timing component. The specific value of the power supply is set according to the actual situation. In this application, it is preferred to be 5V. The BUS component and the first timing component communicate via RS422, but it is not limited to RS422. In this application, it is preferred to transmit analog quantities via RS422 communication.
[0042] The second timing component and the BUS component are interconnected by signals. The BUS component supplies power to the second timing component. The specific value of the power supply is set according to the actual situation. In this application, it is preferred to be 5V. The BUS component and the second timing component communicate via RS422, but it is not limited to RS422. In this application, it is preferred to transmit analog quantities via RS422 communication.
[0043] Furthermore, the CPU component is connected to the first connector, which provides external interfaces, Ethernet, 1553B bus and RS422.
[0044] Furthermore, the power supply assembly is connected to the second connector, through which external signal interconnection and input instrument power (i.e., primary power) are achieved.
[0045] Specifically, the specific value of the instrument voltage is set according to the actual situation, and in this application, it is preferably 28V.
[0046] Furthermore, the first timing component is connected to the third connector to achieve external signal interconnection, connect to thermal power, output timing control signals, and input analog signals.
[0047] Furthermore, the second timing component is connected to the fourth connector to achieve external signal interconnection, connect to thermal power, output timing control signals, and input analog signals.
[0048] Furthermore, the specific value of the pyroelectric current is set according to the actual situation, and in this application, it is preferably 28V.
[0049] like Figure 3 As shown in the example, the SOC (System-on-a-Chip) is connected to the output module of the FPGA (Field-Programmable Gate Array) via the EMIF (External Memory Interface). The FPGA is connected to the driver of the first or second timing component. The driver is also connected to a 5V power supply and an LSSR-0404. The LSSR-0404 is connected to the bus. The LSSR-0404 (i.e., a solid-state relay) outputs the star-rocket separation control timing (i.e.,...). Figure 3 (Timing output in the middle).
[0050] Specifically, the first timing component and the second timing component implement 52 control signal outputs to control the opening and closing of the solid-state relay. Each control signal is dual-redundant, and controls the solid-state relay's conduction and cutoff 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 this application, without changing the original launch vehicle satellite separation control scheme, adds a satellite-rocket separation control combination to provide more timing control, thereby greatly increasing the launch vehicle satellite separation timing and significantly increasing the number of satellites launched in one rocket.
[0053] (2) The configurable launch vehicle multi-satellite launch control system of this 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 number of satellites launched in one rocket can be increased by flexibly configuring the separation timing to meet the batch launch mission of small satellites.
[0054] Although preferred embodiments of this application have been described, those skilled in the art, upon learning the basic inventive concept, can make other changes and modifications to these embodiments. Therefore, the scope of protection of this application is intended to be interpreted as including the preferred embodiments as well as all changes and modifications falling within the scope of this application. Obviously, those skilled in the art can make various alterations and variations to this application without departing from the spirit and scope of this application. Thus, if these modifications and variations of this application fall within the scope of protection of this application and its equivalents, this application also intends to include these modifications and variations.
Claims
1. A configurable multi-satellite launch control system for a launch vehicle, characterized in that, include: The satellite-rocket separation control assembly, at least one flight control assembly, a resistor box for protecting the satellite-rocket separation timing path, and multiple satellite separation mechanisms for satellite installation and separation; The satellite-rocket separation control assembly, each flight control assembly, and each satellite separation mechanism are all connected to the resistor box; the satellite-rocket separation control assembly communicates with the flight control assembly. Satellite-rocket separation control assembly: Used to receive timing control commands sent by the flight control assembly, output satellite-rocket separation control timing, and send timing data recovery messages; Flight control assembly: used to send timing control commands; receive satellite-launch separation control timing; and receive timing data recovery messages; The star-rocket separation control assembly includes: a central processing unit (CPU) component, a power supply component, a first timing component, a second timing component, and a 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; The central processing unit (CPU) is used to acquire timing data and its own status data; it provides external interfaces, Ethernet, 1553B bus and RS422; it receives timing control commands sent by the flight control assembly and outputs the satellite-rocket separation control timing. Power supply components: Used to convert the input primary power supply into the secondary power supply required by the internal components of the star-rocket separation control combination, and to power the bus components; First timing component: used to provide 26-channel timing control functions; Second timing component: used to provide 26-channel timing control functions; Bus components: used to interconnect signals between boards; The first and second timing components work together to output 52 timing control signals. Each timing control signal is double redundant. At the same time, the timing retrieval function is realized through the retrieval circuit in the first and second timing components. The timing switching quantity is collected by the retrieval circuit.
2. The configurable multi-satellite launch control system for launch vehicles according to claim 1, characterized in that, The star-rocket separation control unit communicates with the flight control unit via the 1553B bus.
3. The configurable multi-satellite launch control system for launch vehicles according to claim 1, characterized in that, The power supply components include: an input filter circuit, a DC / DC converter module, and an output filter circuit; The primary power supply is filtered by an input filter circuit to obtain a filtered power supply. The filtered power supply is converted into the secondary power supply required by the internal components of the star-rocket separation control assembly through a DC / DC converter module. A secondary power supply is output through the output filter circuit to power the bus components.
4. The configurable multi-satellite launch control system for a launch vehicle according to claim 3, characterized in that, The primary power supply is 28V.
5. The configurable multi-satellite launch control system for a launch vehicle according to claim 3, characterized in that, The secondary power supply is ±5V.
6. The configurable multi-satellite launch control system for a launch vehicle according to claim 1, characterized in that, The central processing unit is connected to the first connector, which provides external interfaces, Ethernet, 1553B bus and RS422.
7. The configurable multi-satellite launch control system for a launch vehicle according to claim 1, characterized in that, The power supply unit is connected to the second connector, which enables external signal interconnection and primary power input.
8. The configurable multi-satellite launch control system for a launch vehicle according to claim 1, characterized in that, The first timing component is connected to the third connector, which enables external signal interconnection, connection to thermal power, timing control signal output, and analog input.
9. The configurable multi-satellite launch control system for a launch vehicle according to claim 1, characterized in that, The second timing component is connected to the fourth connector, which enables external signal interconnection, connection to thermal power, timing control signal output, and analog input.