CN108647027A - Digital satellite attitude and orbit control subsystem source code artificial intelligence Writing method - Google Patents
Digital satellite attitude and orbit control subsystem source code artificial intelligence Writing method Download PDFInfo
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F8/00—Arrangements for software engineering
- G06F8/40—Transformation of program code
- G06F8/41—Compilation
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C21/00—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00
- G01C21/02—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00 by astronomical means
- G01C21/025—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00 by astronomical means with the use of startrackers
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C21/00—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00
- G01C21/24—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00 specially adapted for cosmonautical navigation
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
- G01S19/38—Determining a navigation solution using signals transmitted by a satellite radio beacon positioning system
- G01S19/39—Determining a navigation solution using signals transmitted by a satellite radio beacon positioning system the satellite radio beacon positioning system transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
- G01S19/53—Determining attitude
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Abstract
The invention discloses digital satellite attitude and orbit control subsystem source code artificial intelligence Writing methods, include the following steps：(1) result is chosen according to the offline mode of satellite, the combination of Satellite attitude and orbit control subsystem component and Satellite attitude and orbit control subsystem component mount message writes offline mode and defines header file, component selection header file and component mount message header file respectively；(2) sensor and track profile used according to satellite determines algorithm, writes track profile and determines algorithm file；(3) according to the executing agency of satellite use and track profile control algolithm, track profile control algolithm file is write；(4) according to satellite flight pattern switching logic, offline mode switching control file is write；(5) it is exported according to the input of the sensitive information of satellite controller and control instruction, writes controller information and transmit file.The development amount that Attitude and orbit control system emulation source code can be reduced through the invention improves the Universal and scalability of Attitude and orbit control system emulation source code.
Description
Technical field
The present invention relates to a kind of artificial intelligence Writing methods of source code, in particular to a kind of digital satellite appearance rail
Control subsystem source code artificial intelligence Writing method.
Background technology
Attitude and orbit control subsystem is the important component of satellite system, is responsible for Satellite Orbital Attitude and determines and control, to defend
Star executes task and provides safeguard.It is limited to the period manufactured and designed and cost, the attitude and orbit control subsystem of each corresponding satellite is set
It is unpractical that meter scheme and posture are determining, attitude control method all manufactures a real satellite to carry out flight validation；Therefore, lead to
High-precision analog verification is carried out to design of satellites scheme or control method frequently with digital simulation technique.
In the prior art, a large amount of personnel of tissue are needed to carry out prolonged attitude and orbit control subsystem source code for each satellite
It writes, compile and debugs, can just develop the digital satellite attitude and orbit control subsystem of complete set.Attitude and orbit control subsystem is more multiple
Miscellaneous, the period needed for a set of digital satellite attitude and orbit control subsystem of exploitation of completely independent starting from scratch is longer；In addition, identical type is not
Satellite with model may use similar design scheme or use identical parts, and exploitation has a large amount of repeat again completely
Sex work, wastes time and manpower；Therefore, it generally selects and directly existing digital satellite attitude and orbit control subsystem is transformed.
However, different, use sensors are different with executing agency with model, developer is different for the type of satellite, just
So that the composition of digital satellite attitude and orbit control subsystem, structure and source code writing style are different.To digital Satellite attitude and orbit control
The transformation of subsystem source code needs to establish in composition, the structure for fully understanding existing digit Satellite attitude and orbit control subsystem source code
On the basis of writing style, the replacement of developer needs to repeat to understand and learn again so that development cost compared with
It is high.
It would therefore be highly desirable to provide a kind of digital satellite attitude and orbit control subsystem source code artificial intelligence Writing method, number is reduced
The repeated labor that Satellite attitude and orbit control subsystem source code is write, and improve the general of digital satellite attitude and orbit control subsystem source code
Property.
Invention content
Place based on the deficiencies of the prior art, the present invention provide a kind of artificial intelligence of digital satellite attitude and orbit control subsystem source code
Energy Writing method shortens the development cycle to reduce the development amount of digital satellite attitude and orbit control subsystem, improves digital satellite appearance
The versatility of rail control subsystem source code.
The present invention is adopted the technical scheme that achieve the goals above：
Digital satellite attitude and orbit control subsystem source code artificial intelligence Writing method, includes the following steps：
(1) result and Satellite attitude and orbit control are chosen according to the offline mode of satellite, the combination of Satellite attitude and orbit control subsystem component
Subsystem component mount message writes offline mode and defines header file, component selection header file and component mount message head text respectively
Part；The Satellite attitude and orbit control subsystem component includes sensor, executing agency and controller；
(2) sensor and track profile used according to satellite determines algorithm, writes track profile and determines algorithm file；
(3) according to the executing agency of satellite use and track profile control algolithm, track profile control algolithm file is write；
(4) according to satellite flight pattern switching logic, offline mode switching control file is write；
(5) it is exported according to the input of the sensitive information of satellite controller and control instruction, writes controller information and transmit file.
Digital satellite as described above is integrated by the function of real satellite, composition, structure, pattern, program, operation
Operate in the dynamic analog simulation system in software simulated space environment.
Result and peace are chosen according to the combination of offline mode, Satellite attitude and orbit control subsystem component in Satellite attitude and orbit control subsystem
It fills information and writes header file, algorithm is determined to track profile, track profile control algolithm, satellite flight pattern switching logic, is defended
The sensitive information input and control instruction output of star controller carry out taxonomic revision, write digital satellite attitude and orbit control subsystem source generation
Code, can shorten the development cycle of digital satellite attitude and orbit control subsystem source code, improve development efficiency, reduce development cost.
Further, sensor includes gyro, sun sensor, earth sensor, star sensor, magnetometer, acceleration
The multiple combinations of the components such as meter, GPS；Executing agency include engine, thruster, flywheel, magnetic torquer,
The multiple combinations of the components such as control-moment gyro, accurate wheel.
Further, the offline mode in the step (1) includes：Rate damping pattern, sun acquisition pattern determine day
Pattern, attitude maneuver are kept to pattern, earth acquisition pattern, absolute orientation pattern, normal mode of operation, contingency mode, position
Pattern, orbit maneuver pattern etc..
Further, each offline mode respectively includes several flying methods；Wherein, the sun acquisition pattern packet
It includes and searches for around the Y-axis sun and searched for around the X-axis sun；The Direct to the sun pattern includes Direct to the sun and cruises day；Describedly
Ball acquisition mode includes establishing inclined shaft and earth search；The earth directing mode includes that 2 axis absolute orientations and 3 axis are fixed over the ground
To；The normal mode of operation includes normal rounds control and the control of normal thrust device；The contingency mode includes emergent earth acquisition
With emergent sun acquisition；It includes that thing position keeps keeping with north-south position that the position, which keeps pattern,；The rate damping mould
Formula includes pipeline exhaust and angular speed damping；The attitude maneuver pattern includes that motor-driven and motor-driven end is kept；The track machine
Dynamic model formula includes motor-driven preparation, motor-driven and motor-driven end holding；Various flying methods can by the derivation of change of flight parameter value
New flying method is obtained, various flying methods, which reconfigure, can form new offline mode.
Further, the offline mode in the step (1) define header file include offline mode word define header file and
Flying method word defines header file.
Further, the step (2) specifically includes：
1) sensor and track profile used in satellite are counted and determines algorithm；
2) include according to header file, variable-definition, initialization function, fixed code segment, track profile determine algorithm letter
Several sequences writes track profile and determines algorithm file one by one.
Further, the step (3) specifically includes：
1) executing agency and track profile control algolithm used in satellite are counted；
2) include according to header file, variable-definition, initialization function, fixed code segment, track profile control algolithm letter
It counts, the sequence of control instruction partition function writes track profile control algolithm file one by one.
Further, the step (4) specifically includes：
1) type, model and satellite actual task demand for the sensor and executing agency installed according to satellite, really
Determine the offline mode, flying method and monitoring event of satellite；
2) it writes the monitoring event of each offline mode and function is sentenced in switching；
3) offline mode function is write.
Further, the step (5) specifically includes：
1) it according to satellite sensor Data Transport Protocol, writes sensor metrical information and receives and dispatches code；
2) according to controller time stepping method configuration result, controller management code is write；
3) according to telecommand, processing and forwarding code are write；
4) telemetry data packet is write.
Advantageous effect：Digital satellite attitude and orbit control subsystem source code artificial intelligence Writing method provided by the present invention is abundant
Considering offline mode and flying method in Satellite attitude and orbit control system, there are similitude, the description of component mount message, offline mode
Switch logic describes and the finiteness of source code ways of writing, track profile determine the logical of algorithm and track profile control algolithm
With property, uses the method for machine learning to complete to write after carrying out classifying and dividing to attitude and orbit control subsystem source code, thereby reduce
Attitude and orbit control system emulates the development amount of source code, improves the Universal and scalability of Attitude and orbit control system emulation source code.
Specific implementation mode
The present invention is described in further detail with reference to embodiment：
Embodiment 1
Digital Satellite attitude and orbit control subsystem source code is write using C language or C Plus Plus, the specific method is as follows：
(1) writing of header file：
1) offline mode is write according to the offline mode of satellite and defines header file；
It includes that offline mode word defines header file and flying method word defines header file that offline mode, which defines header file,；Specifically
Ground defines each offline mode word and flying method word by the way of macrodefinition：
Wherein, the name of offline mode word macrodefinition uses the English word of offline mode；
Flying method word macrodefinition is named as pattern-word, connector and mode combinatorics on words.Wherein, mode word indicates to fly
The either code name of writing a Chinese character in simplified form of line mode is generally indicated using number or English alphabet in Practical Project, in the present embodiment will
It is defined as the phrase of several English word compositions, such as " angular speed damping " mode under " rate damping " pattern, mode word
For " DampingVelocity ", corresponding code name is " 01 ".
2) it is combined according to Satellite attitude and orbit control subsystem component and chooses result writing nib selection header file；
Satellite attitude and orbit control subsystem component includes sensor, executing agency and controller；Satellite attitude and orbit control subsystem passes through
Sensor acquires measurement data, and determine appearance calculating according to satellitosis or aerial mission, passes through actuating mechanism controls satellite
Posture.
Wherein, sensor include gyro, it is sun sensor, earth sensor, star sensor, magnetometer, accelerometer, complete
The multiple combinations of the components such as ball global position system；Executing agency includes engine, thruster, flywheel, magnetic torquer, control force
The multiple combinations of the components such as square gyro, accurate wheel.
Further, it is as follows to choose header file Writing method for component：
1. counting the number of satellite sensor and executing agency's combination；
2. for each sensor or executing agency, number mark is chosen using the form writing nib of macrodefinition；
3. the naming method that component chooses number identification macro includes number of element types, unit type, the English list convenient for identification
Word or abbreviation.
3) according to Satellite attitude and orbit control subsystem component mount message writing nib mount message header file；
The specific method is as follows：
1. counting satellite sensor and executing agency's mount message；
2. using the form writing nib installation site information and Installation posture information of array；
3. for installation site information, the first dimension of array is components number, and the second dimension is the installation position of corresponding component
Set vector；
Gyro installation position array is such as defined as GyroInstallPosition [2] [3], indicates that one shares 2 tops
The installation site of spiral shell, each gyro includes 3 coordinate components；Further, [0] [0]=1.25 GyroInstallPosition
Indicate that the x-component of the installation site of first gyro is 1.25, y-component and z-component and so on be
GyroInstallPosition [0] [1] and GyroInstallPosition [0] [2].
4. for Installation posture information, then it is components number, the second dimension and third to have 3 dimensions, the first dimension of array
Dimension is described with installing vector, installation Eulerian angles, installation quaternary number, and is converted to the installation laggard running hand of matrix and is write, jointly
A 3*3 matrix is formed, such as gyro installation matrix GyroInstallMatrix [2] [3] [3].
(2) track profile determines the writing of algorithm file：
1) sensor and its corresponding track profile used in satellite are counted respectively determine algorithm；
Wherein, the posture of gyro determines that algorithm includes gyro angular velocity, gyro integral survey attitude angle；Sun sensor
Posture determines that algorithm includes sun sensor shoot the sun azimuth, sun sensor surveys rolling pitch angle, sun sensor is surveyed partially
Boat angle；The posture of earth sensor determines that algorithm includes earth sensor geodesic sphere azimuth, earth sensor survey rolling pitching
Angle；The posture of accelerometer determines that algorithm includes accelerometer measures acceleration；The posture of star sensor determines that algorithm includes surveying
Attitude angle；The posture of magnetometer determine algorithm include survey attitude angle, GPS track determine algorithm include survey
Absolute position.
2) include according to header file, variable-definition, initialization function, fixed code segment, track profile determine algorithm letter
Several sequences writes track profile and determines algorithm file one by one；
The specific method is as follows：
1. the source code that header file includes is fixed code, direct copying is stored in the source code file content of specific position
After write；
2. traversing the sensor that satellite uses, reads each sensor respective carter posture and determine that the variable-definition of algorithm is fixed
Code snippet is simultaneously write；
3. writing the function class that track profile determines algorithm file initialization function according to the specific ways of writing that standardizes
Type, function name, parameter void；The sensor that satellite uses is traversed, writes the reference of sensor mount message header file one by one
Sentence；Each sensor respective carter posture is last read to determine the initialization fixed code segment of algorithm and write.
4. writing track profile determines other fixed code segments in algorithm file；
5. the track profile that traversal satellite uses determines algorithm, algorithm fixed code segment is read one by one and is write.
The above method determines algorithm by traversing sensor and its corresponding track profile, to the track appearance with versatility
State determines that algorithm file carries out orderly writing and arranges, to ensure write digital satellite attitude and orbit control subsystem source code in appearance
Versatility in state determination.
(3) writing of track profile control algolithm file：
1) executing agency and its corresponding track profile control algolithm used in satellite are counted respectively；
Such as：The track profile control algolithm of thruster includes relay-type cortrol, phase plane control, pulse width modulation controlled；Fly
The gesture stability algorithm of wheel includes proportional integral derivative control；The orbits controlling algorithm of engine includes change rail point fire control system；Magnetic
The gesture stability algorithm of torquer includes desaturation control and the thick oriented control of three axis；The gesture stability algorithm of control-moment gyro
It is controlled including proportional integral derivative；The gesture stability algorithm of precision wheel includes step motion control.
2) include according to header file, variable-definition, initialization function, fixed code segment, track profile control algolithm letter
It counts, the sequence of control instruction partition function writes track profile control algolithm file one by one；
The specific method is as follows：
1. the source code that header file includes is fixed code, direct copying is stored in the source code file content of specific position
After write；
2. traversing the executing agency that satellite uses, the variable-definition of each executing agency's respective carter gesture stability algorithm is read
Fixed code segment is simultaneously write；
3. writing the function class of track profile control algolithm file initialization function according to the specific ways of writing that standardizes
Type, function name, parameter void；The executing agency that satellite uses is traversed, writes executing agency's mount message header file one by one
Reference statement；It last reads the initialization fixed code segment of each executing agency's respective carter gesture stability algorithm and writes；
4. writing other fixed code segments in track profile control algolithm file；
5. traversing the track profile control algolithm that satellite uses, reading algorithm fixed code segment one by one and writing.
The above method is by traversing executing agency and its corresponding track profile control algolithm, to the track with versatility
Gesture stability algorithm file carries out orderly writing and arranges, and is existed with the digital satellite attitude and orbit control subsystem source code for ensureing write
Versatility in gesture stability.
(4) writing of offline mode switching control file：
1) it is defended according to the sensor of satellite installation and executing agency's type and model and satellite actual task demand, determination
Offline mode, flying method and the monitoring event of star；
Offline mode includes rate damping pattern, sun acquisition pattern, Direct to the sun pattern, earth acquisition pattern, over the ground
Directional pattern, normal mode of operation, contingency mode, position keep pattern, attitude maneuver pattern, orbit maneuver pattern etc..
Each offline mode respectively includes several flying methods.Wherein, sun acquisition pattern include around the Y-axis sun search and
It is searched for around the X-axis sun；Direct to the sun pattern includes Direct to the sun and cruises day；Earth acquisition pattern includes establishing inclined shaft and ground
Ball is searched for；Earth directing mode includes 2 axis absolute orientations and 3 axis absolute orientations；Normal mode of operation includes normal rounds control and just
Normal thruster control；Contingency mode includes emergent earth acquisition and emergent sun acquisition；It includes thing position that position, which keeps pattern,
It keeps and north-south position is kept；Rate damping pattern includes pipeline exhaust and angular speed damping；Attitude maneuver pattern includes motor-driven
It is kept with motor-driven end；Orbit maneuver pattern includes motor-driven preparation, motor-driven and motor-driven end holding；Various flying methods are by changing
Become the derivation of flight parameter value and new flying method can be obtained, various flying methods, which reconfigure, can form new offline mode.
Monitoring event includes that the time, whether time-out, attitude angle control accuracy, attitude angular velocity control accuracy, the sun were visible
Property, earth visibility, solar vector angle control accuracy, earth azimuth control accuracy etc..
2) the monitoring event and switching judging function of each offline mode are write；
1. time whether overtime monitoring event includes time time-out, time having not timed out 2 kinds of monitoring results, monitoring parameters include
Current time and time-out time；
2. attitude angle/angular speed control accuracy monitoring event, which includes attitude angle/angular speed control, meets required precision, posture
Angle/attitude angular velocity control accuracy is unsatisfactory for requiring 2 kinds of monitoring results, monitoring parameters including current pose angle/angular speed, expectation
Attitude angle/angular speed, attitude angle/angular speed precision threshold and attitude angle/angular speed meet precision and count mark；
3. the sun/earth visibility monitoring event includes, the sun/earth is visible, the invisible 2 kinds of monitorings knot of the sun/earth
Fruit, monitoring parameters include that the sun/earth visibility identifies counting mark visible with the sun/earth；
4. the sun/earth azimuth control accuracy monitoring event, which includes the sun/earth azimuth control accuracy, to be met the requirements,
The sun/earth azimuth control accuracy is unsatisfactory for requiring 2 kinds of monitoring results, monitoring parameters including the sun/earth vector angular accuracy
Threshold value and the sun/earth azimuth meet precision and count mark；
5. for the monitoring result of each monitoring event, it is arranged one and counts mark and be initialized as 0, monitoring event satisfaction
Mark is then counted from adding 1, otherwise returns 0；
6. the logical expression of switching condition is write according to switch logic, by be switched flight in condition judgment sentence
Mode word is assigned to the current flight regime word of satellite, then write mode switching function call statement.
3) offline mode function is write；
1. offline mode function is divided into offline mode switching control function and flight parameter assignment function, it is all made of more
Branching selection sentence is as function body structure；
2. multiple-limb case statement is write, using current flight regime word as branching selection Rule of judgment；
3. using all flying method words of satellite as branching selection；
4. for each flying method word, algorithm calling language is write in the branching selection of offline mode switching control function
Sentence writes flying method parameter, the assignment statement of monitoring event argument, algorithm parameter in flight parameter assignment function；
5. writing control system pattern switching to show and printf call statement；
6. function return value is current flight regime word.
The above method carries out standardization definition to the monitoring event in offline mode, switch logic, improves digital satellite appearance
The writing efficiency of rail control subsystem source code, and ensure that expanding for write digital satellite attitude and orbit control subsystem source code
Property.
(5) writing of controller information transmission file：
1) it according to satellite sensor Data Transport Protocol, writes sensor metrical information and receives and dispatches code；
Transport protocol includes but is not limited to question-response, one asks the form more answered.
Controller sends to each sensor and instructs, and the transmission times of sensor measurement data is arranged and sends interval time；
Transmission times determines the number that sensor measurement data is sent to controller, sends interval time decision sensor and measures number twice
According to the time interval sent to controller.
2) according to controller time stepping method configuration result, controller management code is write；
Controller management event includes flight control operation, instruction transmission, simulation time delay, Orbit simulation etc..
Control management code is write using multiple-limb case statement；Instruction is sent, simulation time delay event is in each emulation week
It is interim to be performed both by, it is write outside multiple-limb case statement；Flight control operation, instruction send the multiple emulation cycles of interval of events and hold
Row is primary, is write as a branching options in multiple-limb case statement.
3) according to telecommand, processing and forwarding code are write；
For the telecommand of controller, after being sent to controller data transmitting-receiving file by information transmission, to corresponding
Quantity of state assignment；Wherein, include pattern switching instruction, the instruction of attitude maneuver angle initialization, portion for the telecommand of controller
Part chooses setting instruction, engine ignition instructs, establishes inclined shaft instruction etc..
4) telemetry data packet is write；
The telemetry of controller includes offline mode, currently used sensor, currently used executing agency, sensor survey
Magnitude, thruster on off state, Speed of Reaction Wheels etc..
According to the practical telemetry protocol of satellite, Star Service data management module will be sent to after data group packet.Practical telemetry protocol
Including the radio frequency channel method of salary distribution, CCSDS protocol modes etc..
It the above is only the preferred embodiment of the present invention, protection scope of the present invention is not limited to reality shown in this article
Example is applied, all technical solutions belonged under thinking of the present invention all belong to the scope of protection of the present invention.It should be pointed out that being led for this technology
For the those of ordinary skill in domain, several modifications and retouching without departing from the principles of the present invention also should be regarded as the present invention's
Protection domain.
Claims (8)
1. digital satellite attitude and orbit control subsystem source code artificial intelligence Writing method, which is characterized in that include the following steps：
(1) result and Satellite attitude and orbit control subsystem are chosen according to the offline mode of satellite, the combination of Satellite attitude and orbit control subsystem component
System component mount message writes offline mode and defines header file, component selection header file and component mount message header file respectively；
The Satellite attitude and orbit control subsystem component includes sensor, executing agency and controller；
(2) sensor and track profile used according to satellite determines algorithm, writes track profile and determines algorithm file；
(3) according to the executing agency of satellite use and track profile control algolithm, track profile control algolithm file is write；
(4) according to satellite flight pattern switching logic, offline mode switching control file is write；
(5) it is exported according to the input of the sensitive information of satellite controller and control instruction, writes controller information and transmit file.
2. digital satellite attitude and orbit control subsystem source code artificial intelligence Writing method according to claim 1, feature exist
In the offline mode in the step (1) includes：Rate damping pattern, sun acquisition pattern, Direct to the sun pattern, the earth are caught
Obtain pattern, absolute orientation pattern, normal mode of operation, contingency mode, position holding pattern, attitude maneuver pattern and orbit maneuver
Pattern.
3. digital satellite attitude and orbit control subsystem source code artificial intelligence Writing method according to claim 2, feature exist
In each offline mode respectively includes several flying methods；Wherein, the sun acquisition pattern includes being searched around the Y-axis sun
Rope and around the X-axis sun search for；The Direct to the sun pattern includes Direct to the sun and cruises day；The earth acquisition pattern includes
Establish inclined shaft and earth search；The earth directing mode includes 2 axis absolute orientations and 3 axis absolute orientations；The normal work
Pattern includes normal rounds control and the control of normal thrust device；The contingency mode includes emergent earth acquisition and emergent sun acquisition；
It includes that thing position keeps keeping with north-south position that the position, which keeps pattern,；The rate damping pattern include pipeline exhaust and
Angular speed damps；The attitude maneuver pattern includes that motor-driven and motor-driven end is kept；The orbit maneuver pattern includes motor-driven standard
Standby, motor-driven and motor-driven end is kept；Various flying methods derive to obtain new flying method by change of flight parameter value, respectively
Kind flying method reconfigures to form new offline mode.
4. digital satellite attitude and orbit control subsystem source code artificial intelligence Writing method according to claim 1, feature exist
In it includes that offline mode word defines header file and the definition of flying method word that the offline mode in the step (1), which defines header file,
Header file.
5. digital satellite attitude and orbit control subsystem source code artificial intelligence Writing method according to claim 1, feature exist
In the step (2) specifically includes：
1) sensor and track profile used in satellite are counted and determines algorithm；
2) include according to header file, variable-definition, initialization function, fixed code segment, track profile determine algorithmic function
Sequence writes track profile and determines algorithm file one by one.
6. digital satellite attitude and orbit control subsystem source code artificial intelligence Writing method according to claim 1, feature exist
In the step (3) specifically includes：
1) executing agency and track profile control algolithm used in satellite are counted；
2) include according to header file, variable-definition, initialization function, fixed code segment, track profile control algolithm function, control
The sequence of system instruction partition function writes track profile control algolithm file one by one.
7. digital satellite attitude and orbit control subsystem source code artificial intelligence Writing method according to claim 1, feature exist
In the step (4) specifically includes：
1) type, model and satellite actual task demand for the sensor and executing agency installed according to satellite, determination are defended
Offline mode, flying method and the monitoring event of star；
2) it writes the monitoring event of each offline mode and function is sentenced in switching；
3) offline mode function is write.
8. digital satellite attitude and orbit control subsystem source code artificial intelligence Writing method according to claim 1, feature exist
In the step (5) specifically includes：
1) it according to satellite sensor Data Transport Protocol, writes sensor metrical information and receives and dispatches code；
2) according to controller time stepping method configuration result, controller management code is write；
3) according to telecommand, processing and forwarding code are write；
4) telemetry data packet is write.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110687825A (en) * | 2019-09-25 | 2020-01-14 | 中国科学院微小卫星创新研究院 | Satellite single-machine simulation system and method |
| CN111190356A (en) * | 2019-12-12 | 2020-05-22 | 上海卫星工程研究所 | Simulation decision support system, method and realization method of simulation decision support system |
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