CN109840234A - A kind of carrier rocket electrical system and data processing method - Google Patents
A kind of carrier rocket electrical system and data processing method Download PDFInfo
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Abstract
This application discloses a kind of carrier rocket electrical system and data processing methods, comprising: rocket Upper Stage, rocket second level and rocket level-one；The electrical system of rocket Upper Stage includes: the first power supply board, the first concentration interface, the first FPGA board, one piece of radio-frequency channel board, CPU calculating and memory module and information sensing module；First power supply board is used to provide unified power supply in rocket Upper Stage；First concentration interface is for providing unified interface in rocket Upper Stage；First FPGA board is for handling data；Radio-frequency channel board is for handling radio-frequency channel information in rocket Upper Stage.The beneficial effect of the application is to each section rocket body of carrier rocket electrical system using centralized systems such as centrally connected power supply, concentration interface, intensive data processing, so that the integrated level of electrical system, reliability are significantly improved on rocket arrow, the component for making system dress arrow integrated simultaneously and weight of equipment substantially reduce, and rocket transport power is significantly improved.
Description
Technical field
The present disclosure relates generally to the technical fields of Rocket Electrical System, and in particular to a kind of carrier rocket electrical system and number
According to processing method.
Background technique
Carrier rocket electrical system is the important component of rocket, completes the sequential exports such as rocket engine ignitions at different levels
Control obtains the information such as rocket position, speed, angular speed and controls according to the flights at different levels that predetermined control strategy completes rocket, complete
At functions such as rocket real-time telemetry, exterior measuring, wireless peace controls.
It mostly uses 1553B, CAN bus to communicate between each component devices of carrier rocket electrical system at present, respectively sets
Standby function is relatively simple, and integrated level is not high, and existing bus higher cost, is unfavorable for commercial applications.
Summary of the invention
In view of drawbacks described above in the prior art or deficiency, be intended to provide a kind of carrier rocket electrical system integrated approach and
Device.
First aspect the application provides a kind of carrier rocket electrical system, rocket Upper Stage, rocket second level and rocket level-one；
The equipment of the rocket Upper Stage includes: that arrow carries computer, inertial measurement cluster, satellite navigation receiver and telemetry terminal system；Institute
The equipment for stating rocket second level includes: second level integrated controller, second level servo-system；The equipment of the rocket level-one includes: level-one
Integrated controller, level-one servo-system；
The electrical system of the rocket Upper Stage includes: that the first power supply board for sharing of each equipment, each equipment share
The radio-frequency channel plate that one the first FPGA board, satellite navigation receiver and the telemetry terminal system for concentrating interface, each equipment shared shares
The CPU that card, arrow carry computer is calculated and the information sensing module of memory module and inertial measurement cluster；
The first power supply board, has redundant power supply ability, is configured to: providing collection for each equipment of rocket Upper Stage
Middle unified power supply；
Described first concentrates interface, is configured to: providing centralized and unified interface for each equipment of rocket Upper Stage, and lead to
Redundancy RS422 bus is crossed to be connected with the interface of the rocket second level and rocket level-one；
The first FPGA board, is configured to: in rocket Upper Stage, rocket second level described in integrated treatment and rocket level-one
The data of each equipment；
The radio-frequency channel board, is configured to: the radio-frequency channel of integrated treatment satellite navigation receiver and telemetry terminal system
Information.
According to technical solution provided by the embodiments of the present application, the electrical system of the rocket second level includes: that each equipment shares
The second power supply board, each equipment share second concentrate interface, each equipment shared the 2nd FPGA board, second level comprehensively control
The sequential export module of device and the drive module of second level servo-system；The second power supply board, has redundant power supply ability, matches
It sets and is used for: providing centralized and unified power supply for each equipment of rocket second level；Described second concentrates interface, is configured to: for rocket two
Each equipment of grade provides centralized and unified interface, and passes through redundancy RS422 bus and the rocket Upper Stage and rocket level-one
Interface is connected；The 2nd FPGA board handles the FPGA board of CPU in real time for one piece of embedded multicore ARM, is configured to:
Handle the data of each equipment in rocket second level.
According to technical solution provided by the embodiments of the present application, the first FPGA board and the 2nd FPGA board pass through redundancy
RS422 bus is connected.
According to technical solution provided by the embodiments of the present application, the electrical system of the rocket level-one includes: that each equipment shares
Third power supply board, the shared third of each equipment concentrate interface, each equipment shared the 3rd FPGA integrated treatment board, level-one
The sequential export module of integrated controller and the drive module of level-one servo-system；The third power supply board, has redundancy confession
Electric energy power, is configured to: providing centralized and unified power supply for each equipment of rocket level-one；Described first concentrates interface, is configured to:
Centralized and unified interface is provided for each equipment of rocket level-one, and passes through redundancy RS422 bus and the rocket Upper Stage and fire
The interface of arrow second level is connected；The 3rd FPGA board is the FPGA board that one piece of embedded multicore ARM handles CPU in real time, matches
It sets and is used for: the data of each equipment in processing rocket level-one.
According to technical solution provided by the embodiments of the present application, the 3rd FPGA board and the first FPGA board and second
It is connected on FPGA board by redundancy RS422 bus.
Second aspect the application provides a kind of data processing method of carrier rocket electrical system, comprising the following steps:
Input data and output data that arrow carries computer are obtained in real time；
Rocket level one data and rocket secondary data are obtained with the fixed cycle；
Judge whether rocket level-one starts work according to rocket level one data；
When rocket level-one starts work, rocket level one data is obtained with the first predetermined period, fire is obtained with the fixed cycle
Arrow secondary data；First predetermined period is less than the fixed cycle；
Judge whether rocket second level starts work according to rocket secondary data；
When rocket second level starts work, rocket secondary data is obtained with the first predetermined period, stops obtaining rocket level-one
Data；
Inertial measurement cluster data are obtained with the second predetermined period；
Satellite navigation receiver data are obtained with third predetermined period；The third predetermined period is the second predetermined period
Integral multiple；
Telemetry terminal system data are obtained with the 4th predetermined period；4th predetermined period is greater than the third predetermined period.
According to technical solution provided by the embodiments of the present application, setting alarm marker in the rocket secondary data, when obtaining
It is further comprising the steps of when the alarm marker data taken are abnormal:
First predetermined period is equal to the minimum acquisition data period；
Judge in the frame structure of telemetry terminal system data comprising shock measurement radio frequency channel or image radio frequency channel；
When in frame structure including shock measurement radio frequency channel, deposit arrow is carried in unappropriated shock measurement radio frequency channel in the frame structure
Computer data rocket secondary data corresponding with alarm marker；
When in frame structure including image radio frequency channel, it will be stored in arrow in unessential image radio frequency channel in the frame structure and carry computer
Data, the corresponding rocket secondary data of alarm marker and inertial measurement cluster data.
According to technical solution provided by the embodiments of the present application, setting alarm marker in the rocket level one data, when obtaining
It is further comprising the steps of when the alarm marker data taken are abnormal:
First predetermined period is equal to the minimum acquisition data period；
Judge in the frame structure of telemetry terminal system data comprising shock measurement radio frequency channel or image radio frequency channel；
When in frame structure including shock measurement radio frequency channel, deposit arrow is carried in unappropriated shock measurement radio frequency channel in the frame structure
Computer data rocket level one data corresponding with alarm marker；
When in frame structure including image radio frequency channel, it will be stored in arrow in unessential image radio frequency channel in the frame structure and carry computer
Data, the corresponding rocket level one data of alarm marker and inertial measurement cluster data.
The beneficial effect of technical scheme is: is supplied using concentration each section rocket body of carrier rocket electrical system
Electricity concentrates the centralized systems such as interface, intensive data processing, so that the integrated level of electrical system, reliability are shown on rocket arrow
It writes and improves, simultaneously because component, board and the weight of equipment of system dress arrow are substantially reduced, therefore rocket transport power is shown
It writes and is promoted, cost is effectively controlled.In addition in data processing, when the rocket level-one that the FPGA of rocket Upper Stage is obtained
Or the data of rocket second level are deposited when abnormal, the data response frequency on the one hand increasing rocket level-one or second level (reduces response
Period), acquire the data of the rocket level-one or second level that are abnormal more；On the other hand, pass through the data frame of change telemetry terminal system
Structure is stored in arrow into the data space of part telemetry terminal system and carries computer and have the data of abnormal rocket level-one or second level,
So that the data more acquired can be sent out abnormal data by telemetry terminal system in the case where not needing ground control centre cooperation
Go back to ground.
Detailed description of the invention
By reading a detailed description of non-restrictive embodiments in the light of the attached drawings below, the application's is other
Feature, objects and advantages will become more apparent upon:
Fig. 1 is the principle schematic diagram of the first embodiment of the application；
Fig. 2 is the flow diagram of second of embodiment of the application；
Fig. 3 is the flow diagram of the third embodiment of the application；
100, rocket Upper Stage；101, the first power supply board；102, first interface is concentrated；103, the first FPGA board；
104, radio-frequency channel board；200, rocket second level；201, the second power supply board；202, second interface is concentrated；203, the 2nd FPGA
Board；300, rocket level-one；301, third power supply board；302, third concentrates interface；303, the 3rd FPGA board.
Specific embodiment
The application is described in further detail with reference to the accompanying drawings and examples.It is understood that this place is retouched
The specific embodiment stated is only used for explaining related invention, rather than the restriction to the invention.It also should be noted that in order to just
Part relevant to invention is illustrated only in description, attached drawing.
It should be noted that in the absence of conflict, the features in the embodiments and the embodiments of the present application can phase
Mutually combination.The application is described in detail below with reference to the accompanying drawings and in conjunction with the embodiments.
The principle schematic diagram for the first embodiment that Fig. 1 is the application is please referred to,
In the present embodiment by taking second level carrier rocket as an example, in other embodiments, other models such as three-stage launcher fortune
It carries rocket and is also applied for the application.
Carrier rocket includes: rocket Upper Stage 100, rocket second level 200 and rocket level-one 300.
The equipment of rocket Upper Stage 100 includes: that arrow carries computer, inertial measurement cluster, satellite navigation receiver and telemetering
Terminal.
The electrical system of the rocket Upper Stage 100 includes: the first confession for having redundant power supply ability that each equipment shares
The first shared FPGA board 103 of the first shared concentration interface 102 of battery plate card 101, each equipment, each equipment, satellite navigation connect
The CPU calculating of one piece of radio-frequency channel board 104, arrow load computer that receipts machine and telemetry terminal system share and memory module and inertia are surveyed
Measure the information sensing module of component.
In the present embodiment, the first power supply board 101 is designed as having redundant power supply ability and refers to powers in board herein
Devise two sets it is independent, can the same voltage of output phase, electric current simultaneously power supply circuit, between two independently-powered output circuits
Output isolation is carried out by diode, it can be ensured that can guarantee this board any circuit kit is another set of when something goes wrong
It works normally.First power supply board 101, is configured to: providing centralized and unified power supply for each equipment of rocket Upper Stage 100, mention
For supply voltage needed for the same level other equipment and electric current.
First concentrates interface 102, is configured to: providing centralized and unified interface for each equipment of rocket Upper Stage 100, and
It is connected by redundancy RS422 bus with the interface of the rocket second level 200 and rocket level-one 300.Make the information that rocket is at different levels
It can be transmitted and be interacted by this interface, RS422 provides a kind of standardized general-purpose interface level, and guarantee respectively complies with standard
Interface chip and its circuit can interconnect.
In the present embodiment, by carrier rocket electrical system interface in the prior art pass through frequently with 1553B bus (or
CAN bus) connection type is optimized for being connected by redundancy RS422 bus, and the communication interface of former each equipment room is changed to using interior
Portion's bus is communicated, and while reducing component dosage, reduce cost, improves the real-time of information exchange.
First FPGA board 103, is configured to: rocket Upper Stage 100, rocket second level 200 described in integrated treatment and rocket
The data of each equipment in level-one 300.It simultaneously further include the functions such as frame is compiled in telemetry-acquisition, part satellite navigation resolves.
In the present embodiment, 103 integrated treatment rocket Upper Stage of the first FPGA board, rocket second level, each in rocket level-one
The data of equipment are the centers of data processing in entire carrier rocket electrical system.
Radio-frequency channel board 104, is configured to: the radio-frequency channel letter of integrated treatment satellite navigation receiver and telemetry terminal system
Breath.Complete the enhanced processing of satellite navigation radio-frequency signal, the coding of down coversion and telemetry data stream, modulation and prime radiofrequency signal
The work such as enhanced processing.
Centrally connected power supply is used to the electrical system of rocket Upper Stage, concentrates the centralized systems such as interface, intensive data processing, is subtracted
Lifting system reliability while light weight.
As shown in Figure 1, in a preferred embodiment, the equipment of rocket second level 200 includes: second level integrated controller, second level
Servo-system.The electrical system of the rocket second level 200 includes: the second power supply for having redundant power supply ability that each equipment shares
Second one piece of embedded multicore ARM for concentrating interface 202, each equipment shared that board 201, each equipment share handles CPU's in real time
The drive module of 2nd FPGA board 203, the sequential export module of second level integrated controller and second level servo-system.
Second power supply board 201, is configured to: providing centralized and unified power supply for each equipment of rocket second level 200.
Second concentrates interface 202, is configured to: providing centralized and unified interface for each equipment of rocket second level 200, and lead to
Redundancy RS422 bus is crossed to be connected with the interface of the rocket Upper Stage 100 and rocket level-one 300.
2nd FPGA board 203, is configured to: the data of each equipment in processing rocket second level 200.
2nd FPGA board 203 is connected with the first FPGA board 103 by redundancy RS422 bus.
The purpose that one piece of embedded multicore ARM handles the FPGA board of CPU in real time: this CPU is set in the preferred embodiment
Computing capability needed for servo-system carries out Controlling model resolving, the first FPGA board of opposite rocket Upper Stage can be provided
103, this embedded CPU volume is smaller, integrated level is higher but computing capability is on the weak side；The superfluous of software is promoted while mitigating weight
Remaining computing capability improves system reliability of operation.
In the preferred embodiment, each device data of the rocket second level 200 is the first concentration of rocket Upper Stage 100
Interface 102 is obtained by the data on the 2nd FPGA board 203 of access.
As shown in Figure 1, in a preferred embodiment, the equipment of rocket level-one 300 includes: level-one integrated controller, level-one
Servo-system.The electrical system of rocket level-one 300 includes: the third power supply board for having redundant power supply ability that each equipment shares
301, one piece of embedded multicore ARM that the shared third of each equipment concentrates interface 302, each equipment shared handles the third of CPU in real time
The drive module of FPGA board 303, the sequential export module of level-one integrated controller and level-one servo-system.
Third power supply board 301, is configured to: providing centralized and unified power supply for each equipment of rocket level-one 300.
Third concentrates interface 302, is configured to: providing centralized and unified interface for each equipment of rocket level-one 300, and lead to
Redundancy RS422 bus is crossed to be connected with the interface of the rocket Upper Stage 100 and rocket second level 200.
3rd FPGA board 303, is configured to: the data of each equipment in processing rocket level-one 300.In this preferred embodiment
In, the 3rd FPGA board 303 is connected by redundancy RS422 bus with the first FPGA board 103 and the 2nd FPGA board 203.
As shown in Fig. 2, being the flow diagram of second of embodiment of the application, comprising the following steps:
S10, input data and output data that arrow carries computer are obtained in real time.
S20, rocket level one data and rocket secondary data are obtained with the fixed cycle.In the present embodiment, the fixed cycle is
5ms。
S30, judge whether rocket level-one starts work according to rocket level one data.First FPGA board in the present embodiment
It can judge whether rocket level-one starts ignition operation to apparent acceleration data by the way that the rocket level-one flight of acquisition is each.Work as fire
When arrow level-one starts work, step S40 is executed；When the inactive work of rocket level-one, step S20 is executed.
S40, when rocket level-one start work when, with the first predetermined period obtain rocket level one data, obtained with the fixed cycle
It gets fire arrow secondary data；First predetermined period is less than the fixed cycle.In this step, rocket level-one is started to work, fire
The inactive work of arrow second level accesses rocket to preferably monitor rocket level-one with the first predetermined period for being less than the fixed cycle
Level-one, in the present embodiment, the first predetermined period are 3ms.
S50, judge whether rocket second level starts work according to rocket secondary data.First FPGA board in the present embodiment
It can judge whether rocket second level starts ignition operation by the rocket secondary data of acquisition.When rocket second level starts work
When, execute step S60；When the inactive work of rocket second level, step S40 is executed.
S60, when rocket second level start work when, with the first predetermined period obtain rocket secondary data, stop obtain rocket
Level one data.In this step, rocket second level is started to work, the power cut-off of rocket level-one, in order to preferably monitor rocket second level,
Rocket second level is accessed with the first predetermined period for being less than the fixed cycle.
S70, inertial measurement cluster data are obtained with the second predetermined period.The second predetermined period is in the present embodiment
2.5ms。
S80, satellite navigation receiver data are obtained with third predetermined period；The third predetermined period was the second default week
The integral multiple of phase.In the present embodiment, satellite navigation is for supplementary inertial measurement, so setting second for third predetermined period
The integral multiple of predetermined period is conducive to navigation data amendment.In the present embodiment, third predetermined period is set as the second predetermined period
2 times.
S90, telemetry terminal system data are obtained with the 4th predetermined period；4th predetermined period is greater than the third default week
Phase.The 4th predetermined period is 6ms in the present embodiment.
It is illustrated in figure 3 the third embodiment of the application, the setting alarm marker in rocket secondary data, when first
It is further comprising the steps of when the alarm marker data that FPGA board obtains are abnormal:
S100, the first predetermined period is equal to the minimum acquisition data period.In the present embodiment, the first FPGA plate
The minimum of card obtains the data period as 1ms.
S200, judge in the frame structure of telemetry terminal system data comprising shock measurement radio frequency channel or image radio frequency channel.When telemetering end
When in the frame structure of end data including shock measurement radio frequency channel, step 300 is executed；When in the frame structure of telemetry terminal system data comprising figure
When as radio frequency channel, step 400 is executed.
S300, when in frame structure including shock measurement radio frequency channel, unappropriated shock measurement radio frequency channel memory in the frame structure
Enter arrow and carries computer data rocket secondary data corresponding with alarm marker.
S400, when in frame structure include image radio frequency channel when, in the frame structure will in unessential image radio frequency channel be stored in arrow carry
Computer data, the corresponding rocket secondary data of alarm marker and inertial measurement cluster data.Since image radio frequency channel accounts for frame lattice
Radio frequency channel quantity in formula is more than the number of channels of shock measurement radio frequency channel, and in the present embodiment, it is total that image radio frequency channel accounts for radio frequency channel in frame format
Quantity is more than or equal to 30%, can have more data space storing datas compared to shock measurement radio frequency channel, so in this reality
It applies in example, not only can store arrow in image radio frequency channel and carry computer data rocket secondary data corresponding with alarm marker, also
It can store inertial measurement cluster data.
In a preferred embodiment, the setting alarm marker in rocket level one data, obtains when the first FPGA board
It is further comprising the steps of when the alarm marker data are abnormal:
First predetermined period is equal to the minimum acquisition data period；
Judge in the frame structure of telemetry terminal system data comprising shock measurement radio frequency channel or image radio frequency channel；
When in frame structure including shock measurement radio frequency channel, filling arrow is carried in unappropriated shock measurement radio frequency channel in the frame structure
Computer data rocket level one data corresponding with alarm marker；
When in frame structure including image radio frequency channel, arrow will be filled in unessential image radio frequency channel in the frame structure and carry computer
Data, the corresponding rocket level one data of alarm marker and inertial measurement cluster data.
Above description is only the preferred embodiment of the application and the explanation to institute's application technology principle.Those skilled in the art
Member is it should be appreciated that invention scope involved in the application, however it is not limited to technology made of the specific combination of above-mentioned technical characteristic
Scheme, while should also cover in the case where not departing from the inventive concept, it is carried out by above-mentioned technical characteristic or its equivalent feature
Any combination and the other technical solutions formed.Such as features described above has similar function with (but being not limited to) disclosed herein
Can technical characteristic replaced mutually and the technical solution that is formed.
Claims (8)
1. a kind of carrier rocket electrical system, the carrier rocket includes: rocket Upper Stage, rocket second level and rocket level-one；Institute
The equipment for stating rocket Upper Stage includes: that arrow carries computer, inertial measurement cluster, satellite navigation receiver and telemetry terminal system；It is described
The equipment of rocket second level includes: second level integrated controller, second level servo-system；The equipment of the rocket level-one includes: that level-one is comprehensive
Hop controller, level-one servo-system；It is characterized in that,
The electrical system of the rocket Upper Stage include: each equipment share first power supply board, each equipment share first collection
One block of radio-frequency channel plate that the first shared FPGA board of middle interface, each equipment, satellite navigation receiver and telemetry terminal system share
The CPU that card, arrow carry computer is calculated and the information sensing module of memory module and inertial measurement cluster；
The first power supply board, has redundant power supply ability, is configured to: providing concentration system for each equipment of rocket Upper Stage
One power supply；
Described first concentrates interface, is configured to: providing centralized and unified interface for each equipment of rocket Upper Stage, and by superfluous
Remaining RS422 bus is connected with the interface of the rocket second level and rocket level-one；
The first FPGA board, is configured to: respectively setting in rocket Upper Stage, rocket second level described in integrated treatment and rocket level-one
Standby data；
The radio-frequency channel board, is configured to: the radio-frequency channel information of integrated treatment satellite navigation receiver and telemetry terminal system.
2. carrier rocket electrical system according to claim 1, which is characterized in that the electrical system packet of the rocket second level
It includes: the second the 2nd FPGA plate for concentrating interface, each equipment shared that the second shared power supply board of each equipment, each equipment share
The drive module of card, the sequential export module of second level integrated controller and second level servo-system；
It is described second power supply board, have redundant power supply ability, be configured to: for rocket second level each equipment provide it is centralized and unified
Power supply；
Described second concentrates interface, is configured to: providing centralized and unified interface for each equipment of rocket second level, and pass through redundancy
RS422 bus is connected with the interface of the rocket Upper Stage and rocket level-one；
The 2nd FPGA board handles the FPGA board of CPU in real time for one piece of embedded multicore ARM, is configured to: processing rocket
The data of each equipment in second level.
3. carrier rocket electrical system according to claim 2, which is characterized in that the first FPGA board and second
FPGA board is connected by redundancy RS422 bus.
4. carrier rocket electrical system according to claim 1, which is characterized in that the electrical system packet of the rocket level-one
Include: the 3rd FPGA that the shared third of the shared third power supply board of each equipment, each equipment concentrates interface, each equipment shared is comprehensive
Handle board, the sequential export module of level-one integrated controller and the drive module of level-one servo-system；
The third is powered board, is had redundant power supply ability, is configured to: for rocket level-one each equipment provide it is centralized and unified
Power supply；
Described first concentrates interface, is configured to: providing centralized and unified interface for each equipment of rocket level-one, and pass through redundancy
RS422 bus is connected with the interface of the rocket Upper Stage and rocket second level；
The 3rd FPGA board is the FPGA board that one piece of embedded multicore ARM handles CPU in real time, is configured to: processing rocket
The data of each equipment in level-one.
5. carrier rocket electrical system according to claim 4, which is characterized in that the 3rd FPGA board and first
It is connected on FPGA board and the 2nd FPGA board by redundancy RS422 bus.
6. a kind of data processing method based on carrier rocket electrical system described in any one of claim 1-5, special
Sign is, comprising the following steps:
Input data and output data that arrow carries computer are obtained in real time；
Rocket level one data and rocket secondary data are obtained with the fixed cycle；
Judge whether rocket level-one starts work according to rocket level one data；
When rocket level-one starts work, rocket level one data is obtained with the first predetermined period, rocket two is obtained with the fixed cycle
Grade data；First predetermined period is less than the fixed cycle；
Judge whether rocket second level starts work according to rocket secondary data；
When rocket second level starts work, rocket secondary data is obtained with the first predetermined period, stops obtaining rocket level one data；
Inertial measurement cluster data are obtained with the second predetermined period；
Satellite navigation receiver data are obtained with third predetermined period；The third predetermined period is the integer of the second predetermined period
Times；
Telemetry terminal system data are obtained with the 4th predetermined period；4th predetermined period is greater than the third predetermined period.
7. the data processing method of carrier rocket electrical system according to claim 6, which is characterized in that the rocket two
Setting alarm marker in grade data, further comprising the steps of when the alarm marker data of acquisition are abnormal:
First predetermined period is equal to the minimum acquisition data period；
Judge in the frame structure of telemetry terminal system data comprising shock measurement radio frequency channel or image radio frequency channel；
When in frame structure including shock measurement radio frequency channel, filling arrow carries calculating in unappropriated shock measurement radio frequency channel in the frame structure
Machine data rocket secondary data corresponding with alarm marker；
When in frame structure including image radio frequency channel, arrow will be filled in unessential image radio frequency channel in the frame structure and carry computer number
According to, the corresponding rocket secondary data of alarm marker and inertial measurement cluster data.
8. the data processing method of carrier rocket electrical system according to claim 6, which is characterized in that the rocket one
Setting alarm marker in grade data, further comprising the steps of when the alarm marker data of acquisition are abnormal:
First predetermined period is equal to the minimum acquisition data period；
Judge in the frame structure of telemetry terminal system data comprising shock measurement radio frequency channel or image radio frequency channel；
When in frame structure including shock measurement radio frequency channel, filling arrow carries calculating in unappropriated shock measurement radio frequency channel in the frame structure
Machine data rocket level one data corresponding with alarm marker；
When in frame structure including image radio frequency channel, arrow will be filled in unessential image radio frequency channel in the frame structure and carry computer number
According to, the corresponding rocket level one data of alarm marker and inertial measurement cluster data.
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| CN110515296A (en) * | 2019-08-14 | 2019-11-29 | 北京深蓝航天科技有限公司 | A kind of inexpensive electrical system suitable for reurnable booster |
| CN110988564A (en) * | 2019-12-24 | 2020-04-10 | 北京中科宇航探索技术有限公司 | Subsection rocket electrical system and test method thereof |
| CN114815901A (en) * | 2022-06-24 | 2022-07-29 | 东方空间技术(北京)有限公司 | Rocket-mounted electrical system of carrier rocket |
| CN114935887A (en) * | 2022-07-25 | 2022-08-23 | 星河动力(北京)空间科技有限公司 | Distributed signal acquisition device and carrier rocket |
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| CN110515296A (en) * | 2019-08-14 | 2019-11-29 | 北京深蓝航天科技有限公司 | A kind of inexpensive electrical system suitable for reurnable booster |
| CN110988564A (en) * | 2019-12-24 | 2020-04-10 | 北京中科宇航探索技术有限公司 | Subsection rocket electrical system and test method thereof |
| CN110988564B (en) * | 2019-12-24 | 2022-04-15 | 北京中科宇航探索技术有限公司 | Subsection rocket electrical system and test method thereof |
| CN114815901A (en) * | 2022-06-24 | 2022-07-29 | 东方空间技术(北京)有限公司 | Rocket-mounted electrical system of carrier rocket |
| CN114815901B (en) * | 2022-06-24 | 2022-09-20 | 东方空间技术(北京)有限公司 | Rocket-mounted electrical system of carrier rocket |
| CN114935887A (en) * | 2022-07-25 | 2022-08-23 | 星河动力(北京)空间科技有限公司 | Distributed signal acquisition device and carrier rocket |
| CN114935887B (en) * | 2022-07-25 | 2022-11-18 | 星河动力(北京)空间科技有限公司 | Distributed signal acquisition device and carrier rocket |
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