CN-121978884-A - Rocket-borne integrated control system capable of multiplexing carrier rocket

CN121978884ACN 121978884 ACN121978884 ACN 121978884ACN-121978884-A

Abstract

The invention belongs to the technical field of carrier rocket aviation control, and particularly relates to an rocket-borne integrated control system capable of multiplexing a carrier rocket. The system comprises at least two arrow-mounted equipment units with different control functions, wherein each arrow-mounted equipment unit comprises a plurality of functional modules with different numbers, the number of each functional module is set according to the control functions and the load path number of the arrow-mounted equipment units, the communication among the functional modules of each arrow-mounted equipment unit is completed through an MLVDS backboard bus, and the arrow-mounted equipment units with different control functions are communicated with external equipment through a Powerlink external bus. The invention effectively solves the problem of insufficient control technology of the existing carrier rocket avionics system.

Inventors

YANG MEIRONG
JIANG JIANWEN
DANG RONG
DAI ZHENG
ZHANG XIAODONG
CHEN YU
YAO YAO
ZHAO PENGFEI
LIU HUAXIANG
Tong Shize

Assignees

蓝箭航天空间科技股份有限公司

Dates

Publication Date: 20260505
Application Date: 20260403

Claims (10)

1. The rocket-borne integrated control system for the reusable carrier rocket is characterized by comprising at least two rocket-borne equipment units with different control functions, wherein each rocket-borne equipment unit comprises a plurality of functional modules with different numbers, and the number of each functional module is set according to the control functions and the load path number of each rocket-borne equipment unit; The communication between each functional module of each arrow-mounted equipment unit is completed through an MLVDS backboard bus, and the arrow-mounted equipment units with different control functions are communicated with external equipment through a Powerlink external bus; The plurality of functional modules comprise a power supply module, a processor module, a time sequence module, a motor driving module, a current conversion and collection module and a data synthesis module; The power module, the processor module and the time sequence module all adopt a layout strategy of a triple redundancy architecture; the motor driving module and the converter collecting and editing module both adopt a layout strategy of a double-redundancy architecture; the data synthesis module adopts a layout strategy of a partial redundancy architecture.
2. The system of claim 1, wherein the power module builds the tri-redundancy architecture by connecting three independent and identically configured first welding circuits in parallel; the processor module constructs the triple redundant architecture through three sets of independent and consistent configuration second welding circuits in parallel; The time sequence module constructs the triple redundant framework through three sets of independent and consistent-configuration third welding circuits in parallel; The motor driving module constructs the double-redundancy framework by switching two sets of independent fourth welding circuits with consistent configuration through hot backup; the converter acquisition module constructs the dual-redundancy framework through connecting two sets of independent fifth welding circuits in parallel, wherein the configuration of the fifth welding circuits is consistent with that of the fifth welding circuits.
3. The system of claim 1, wherein the communication between the functional modules to which each of the arrow-mounted device units belongs is accomplished via an MLVDS backplane bus, comprising: Taking the processor module as a main site; The power supply module, the time sequence module, the motor driving module, the converter editing module and the data synthesis module are used as slave stations; and the communication between the master site and the slave sites is realized through three MLVDS back-plane buses, wherein each MLVDS back-plane bus independently serves each set of welding circuits in the master site, and each set of welding circuits correspondingly constructs a redundancy.
4. The system of claim 2, wherein the processor module selects output data or execution instructions by three redundancy running a two out of three voting program built from the three independent and congruent sets of second welding circuits; The timing sequence module comprises a control platform and a driving platform, wherein three redundancy constructed by the control platform corresponds to three redundancy constructed by the processor module one by one, and after an execution instruction of the processor module is analyzed, the driving platform is controlled to realize five-pipe three-out-two and output five control signals to control five MOS pipes, wherein the five-pipe three-out-two specifically comprises five control signals or instructions of the five pipes output by the control platform, the three redundancy constructed by the control platform is respectively recorded as redundancy one, redundancy two and redundancy three, wherein the redundancy one controls two MOS pipes, the redundancy two controls two MOS pipes, and the redundancy three controls one MOS pipe; And data interaction is carried out between the two redundancy of the motor driving module through an LVDS interface, each redundancy obtains data or instructions of the three redundancy of the processor module, and the obtained data or instructions are selected by running a two-out-of-three voting program.
5. The system of claim 3, wherein said communication between said master site and said slave site through three of said MLVDS backplane buses implements an instruction scheduling policy of an MLVDS bus.
6. The system of claim 5, wherein the instruction scheduling policy of the MLVDS bus comprises an initialization procedure and a self-test and identification procedure.
7. The system of claim 6, wherein the initialization procedure comprises a software reset and an MLVDS interface initialization after the MLVDS bus is powered up, wherein the MLVDS interface initialization comprises a register initialization and a memory space zero.
8. The system of claim 6, wherein the self-test and identification procedure includes a master station self-test instruction transmission, a slave station ID identification, a slave station performing self-test, a slave station receiving a master station self-test result instruction and returning a self-test result.
9. The system of claim 8, wherein the slave station performing a self-test comprises: Comparing the three power supply voltages on the site sampling backboard with a preset voltage value, and marking an error mark if the power supply voltage exceeds the preset voltage value; Reading the initialization state of each interface from the site and comparing the initialization state with a preset value to obtain a self-checking interface state; And the slave station feeds back a self-checking result comprising the error identification and the self-checking interface state to the master station through an MLVDS bus.
10. The system of claim 2, wherein the converter acquisition module comprises an analog acquisition unit and a power conversion unit, and wherein the data integration module comprises a bus unit and a digital serial interface unit.

Description

Rocket-borne integrated control system capable of multiplexing carrier rocket Technical Field The invention belongs to the technical field of carrier rocket aviation control, and particularly relates to an rocket-borne integrated control system capable of multiplexing a carrier rocket. Background The existing carrier rocket avionics system mainly adopts two architectures, namely a traditional distributed architecture and a hybrid architecture. Under the powerful drive of huge constellation plans such as 'star net', the high-density emission of rockets becomes a necessary trend of industry development, and the high-reliability, rapid turnover and low-cost three-cooperation optimization stringent requirements are provided for the avionic system. The conventional distributed architecture suffers from the following drawbacks: The number of products is numerous, namely, each functional module is independently designed, so that the number of system components is increased; The cable layout is complex, namely a discrete signal connection mode causes a cable network to be huge and chaotic; the system has overlarge weight, and redundant connectors and cables obviously increase the load of an arrow body; The fault troubleshooting is difficult, namely the distributed fault points are difficult to quickly locate and isolate; the resource utilization rate is low, and the computing power is dispersed in each independent module. The hybrid architecture suffers from the following drawbacks: the upgrade and maintenance are difficult, any function improvement needs to introduce new hardware equipment; development period is prolonged, namely development time is obviously prolonged due to hardware redesign; Bus bandwidth bottleneck, namely the traditional 1553B bus 1MHz bandwidth is difficult to meet the requirement of large data volume transmission; The cost control is difficult, and the manufacturing cost is high due to hardware redundancy and special design; And the expandability is limited, and a fixed architecture is difficult to adapt to future technical evolution and task change. In the traditional distributed architecture, each functional module such as navigation, guidance and control, driving control, data management, telemetry, safe self-destruction, power supply and distribution, time sequence and initiating explosive device management and the like are independent of each other, and are interconnected and communicated through discrete signals and an analog bus (such as 1553B). Although the architecture realizes function separation, a series of engineering problems such as numerous products, complex cable layout, excessive system weight, difficult fault detection and the like are caused. Through continuous optimization, part of the advanced avionics systems turn to a hybrid architecture, the functions of guidance, data management and part of information acquisition are integrated by taking a core processor as a center, and meanwhile, remote interface units are distributed and deployed around an arrow body. However, the hybrid architecture still has the problems of distributed computing power, low utilization of system resources, difficulty in meeting the severe requirements of high-density transmission on data processing efficiency, and the like. The difficulty in upgrading the system is a common pain point of the existing avionics system, and any functional improvement may require the introduction of new hardware devices, resulting in prolonged development cycles and increased costs. Particularly, the lack of a high-bandwidth system bus is difficult to cope with the challenge of the rapid increase of the data volume of a novel rocket, further improvement of system performance is limited, and advanced functions such as real-time image transmission, health status big data return and the like are difficult to support. Disclosure of Invention The invention aims to provide an rocket-borne integrated control system capable of multiplexing a carrier rocket, so as to solve the technical problems of various defects existing in the architecture of the existing carrier rocket avionics system. The embodiment of the invention provides an arrow-mounted integrated control system of a reusable carrier rocket, which comprises at least two arrow-mounted equipment units with different control functions, wherein each arrow-mounted equipment unit comprises a plurality of functional modules with different numbers, and the number of each functional module is set according to the control function and the load path number of the arrow-mounted equipment unit; The communication between each functional module of each arrow-mounted equipment unit is completed through an MLVDS backboard bus, and the arrow-mounted equipment units with different control functions are communicated with external equipment through a Powerlink external bus; The plurality of functional modules comprise a power supply module, a processor module, a time sequence module,