Codeofchina.com is in charge of this English translation. In case of any doubt about the English translation, the Chinese original shall be considered authoritative.
This specification replaces GJB 1416-1992 General specification for satellite attitude control system.
The following main technical changes have been made with respect to GJB 1416-1992:
a) the name of the specification is changed as General specification for spacecraft control system, and the application scope is expanded from "satellites" to "spacecrafts", including satellites, manned spacecrafts and space probes;
b) "System composition" and "Unit functions and performance" are added;
c) orbit control, orbit control accuracy, rendezvous and docking, landing point control accuracy, etc. are added in "System functions and performance".
This specification was proposed by the China Aerospace Science and Technology Corporation.
GJB 1416 was issued for the first time in 1992.
General specification for spacecraft control system
1 Scope
This specification specifies the technical requirements, quality assurance requirements and delivery preparations for spacecraft control system.
This specification is applicable to the design, manufacture, test and acceptance of spacecraft control system.
2 Normative references
The following normative documents contain provisions which, through reference in this text, constitute provisions of this specification. For dated reference, subsequent amendments (excluding corrections), or revisions, of any of these publications do not apply to this specification. However parties to agreements based on this specification are encouraged to investigate the possibility of applying the most recent editions of the normative documents indicated below. For undated references or references with version not indicated, the latest edition of the normative document referred to applies.
GB/T 191 Packaging - Pictorial marking for handling of goods
GJB 150.1A-2009 Laboratory environmental test methods for military materiel - Part 1: General requirements
GJB 150.9A-2009 Laboratory environmental test methods for military materiel - Part 9: Damp heat test
GJB 150.15A-2009 Laboratory environmental test methods for military materiel - Part 15: Acceleration test
GJB 150.16A-2009 Laboratory environmental test methods for military materiel - Part 16: Vibration test
GJB 150.18A-2009 Laboratory environmental test methods for military materiel - Part 18: Shock test
GJB 151 Electromagnetic emission and susceptibility requirements for military equipments and subsystems
GJB 190 Classification of characteristics
GJB 421 Satellite terminology
GJB 899 Reliability testing for qualification and production acceptance
GJB 1027 Test requirements for launch, upper-stage, and space vehicles
GJB 1030 Methods for simulation test of satellite control system
GJB 2042 General specification for satellite electrical power system
GJB 2203 Cleanliness and contamination control requirements for satellite product
GJB 2496 Terminology for manned spacecraft astronautical engineering
GJB 2998 Mark of satellite products
GJB 3590 Electromagnetic compatibility requirements for space systems
GJB/Z 35 Derating criteria for electrical, electronic and electromechanical parts
GJB/Z 1391 Guide to failure mode, effects and criticality analysis
QJ 977 Rule for re-inspection of non-metallic materials
QJ 1286 Testing regulation for attitude control system of satellite
QJ 1386 Rule for re-inspection of metallic materials
QJ 2172 Guide to satellite reliability design
QJ 2236 Safety assurance requirements for aerospace products
QJ 2437 Analysis of effect and criticality of satellite failure
QJ 2463 Test method for three-axis stabilized satellite control system
QJ 2850 Prevention and control for foreign object debris (FOD) of space products
QJ 3065.1 Management requirements for selection of components
QJ 3128 Specification for development of space project software
QJ 3130 Specification for software configuration management of space products
3 Requirements
3.1 System composition
The control system is generally composed of sensors, controllers and actuators, as shown in Figure 1:
a) sensors generally include optical sensors (infrared earth sensors, star sensors, sun sensors, ultraviolet sensors, etc.), inertial sensors (gyroscopes, accelerometers, etc.), magnetometers, navigation sensors (rendezvous and docking sensors, navigation receivers, etc.), radio frequency sensors, etc.;
b) controllers generally include control computers, emergency controllers, man-control lines, etc.
c) actuators generally include thrusters and/or engines (cold gas thrusters, single-component thrusters, double-component thrusters and/or engines, electric thrusters, etc.), momentum wheels or reaction wheels, control moment gyroscopes, magnetic torquers, solar array driving mechanisms, antenna orientation driving mechanisms, etc.
Notes:
1 Sometimes the control system also includes special power supply units or DC/DC power converters.
2 The configuration of control system is determined according to the mission requirements.
Figure 1 Schematic diagram for control system composition
3.2 System functions and performance
3.2.1 System functions
The system functions are selected according to the specific requirements of spacecraft control system. The control system has the following main functions:
a) program control and mode control.
b) navigation and escape survival control of the launching phase.
c) eliminate the initial attitude deviation of the spacecraft after it is separated from the launch vehicle and the attitude disturbance when the solar array and antenna are deployed.
d) capture and directional control of celestial bodies such as sun and earth.
e) establishment and stability of normal attitude.
f) attitude stability during attitude maneuver, attitude offset and orbit control.
g) orbit capture, maneuver and maintenance.
h) autonomous navigation.
i) control of celestial bodies such as solar array and antenna.
j) combination control (used for space station combination after rendezvous and docking, space station laboratory combination, etc.).
k) rendezvous and docking and evacuation control.
l) for manned spacecraft, the control ability of attitude, orbit, rendezvous and docking, evacuation and return, etc. with astronaut participation shall be provided.
m) brake control.
n) return reentry control.
o) celestial surface landing control.
p) celestial surface rising control.
q) spin-up and spin-down control of spin-stabilized satellites.
r) autonomous nutation damping control.
s) send telemetry data.
t) receive remote control commands and have the functions of remote control data injection and/or in-orbit programming.
u) receive man-control commands.
v) failure-safe function. In case of failure of the control system unit, which makes the spacecraft lose its attitude reference and fail to maintain normal business, the control system has the ability of autonomous diagnosis and reconstruction, and cooperates with other spacecraft systems to make the spacecraft in a safe state with ensured power supply, communication link and propellant supply, waiting for ground treatment, and realizing the restoration of normal attitude autonomously if necessary.
3.2.2 System performance
The system performance is selected according to the specific requirements of spacecraft control system.
The dynamic characteristics and disturbance moments of spacecraft in different operation phases shall be considered in the design of control system, so that the following main performance parameters meet the requirements of special technical documents:
a) the maximum allowable initial attitude angular velocity;
b) allowable initial attitude angle;
c) attitude offset range and accuracy;
d) time required for attitude maneuver;
e) attitude measurement accuracy;
f) attitude determination accuracy;
g) attitude control accuracy;
h) attitude stability;
i) orbit determination accuracy;
j) orbit control accuracy;
k) navigation accuracy;
l) guidance accuracy;
m) pointing accuracy for solar array;
n) orientation accuracy for antenna;
o) anti-disturbance ability;
p) initial docking conditions and control accuracy of rendezvous and docking;
q) control accuracy of landing point and the maximum overload (manned or unmanned);
r) number of air injection and propellant consumption;
s) robustness of control system and stability margin under the worst parameter combination;
t) secondary control accuracy (inter-satellite link, optical observation platform);
u) dynamic quality of control system;
v) reliability of control system;
w) design lifetime, etc.
3.3 Unit functions and performance
3.3.1 Sensors
3.3.1.1 Sensor functions
The sensor functions shall meet the requirements of special technical documents, which generally include:
a) acquire the attitude or position information of the spacecraft relative to the reference target or inertial space by using the reference target sensitive to optical system;
b) acquire the spacecraft attitude or navigation information by using inertial instruments;
c) acquire spacecraft attitude or position information through sensitive celestial magnetic fields;
d) acquire the relative position and/or relative attitude information between two or more spacecrafts by optical and electromagnetic means;
e) acquire the attitude or position information of the spacecraft relative to the radio frequency emission source with known sensitive position through the radio waves emitted by such source.
3.3.1.2 Sensor performance
The sensor performance shall meet the requirements of special technical documents, which generally include:
a) measurement range;
b) field of view;
c) absolute/relative accuracy;
d) resolution;
e) linearity;
f) measurement bandwidth;
g) time requirements (including sampling rate, maximum delay time, stability of sampling rate and delay time, etc.);
h) allowable maximum noise;
i) error model and related parameters obtained after calibration;
j) allowable remnant magnetic torque, etc.
3.3.2 Controller
3.3.2.1 Controller functions
With the support of related system software and hardware, the controller has the following main functions:
a) complete the program control for the processes of pending, launching, injection, separation of satellite (airship, spacecraft) and launch vehicle, in-orbit (including the main in-orbit working modes such as rendezvous and docking), deorbit and return;
b) complete the automatic (or manual) setting and switching of working modes in the control process; complete the structural reorganization of the control system in various working modes, including the selection of thrusters in various working modes; complete the parameter modification and channel offset setting of the corresponding working mode;
c) in various working modes, complete the acquisition and processing of attitude sensor measurement data (or manual control command), and calculate the attitude angle and angular velocity of each axis of spacecraft, navigation and relative position/attitude; calculate the control amount of each channel according to the set control rules based on the offset or compensation quantities of each channel and sent it to the actuator;
d) provide remote control interface with TT&C or data management system, receive ground remote control command, and realize switching of major units and backup units; complete the setting and switching of various control modes and states of the control system; complete the setting of control parameters of the control system;
e) provide telemetry interface with TT&C or data management system, and send the measured output values and working parameters of each sensor as well as the main control quantities of each control channel of the control system to TT&C or data management system; intensively transform and transmit the working state parameters of each unit and various working modes of system;
f) provide input interfaces for various sensor signals and other control commands;
g) provide the output interface with the control actuator;
h) complete the automatic unloading of momentum exchange unit;
i) pointing control of solar array and orientation control of antenna;
j) orbit calculation;
k) ephemeris table computation;
l) memory downloading and modification of memory data and programs by remote control;
m) failure detection, isolation and recovery.
3.3.2.2 Controller performance
The control computer (digital controller) has the following performance:
a) computer word length;
b) memory capacity;
c) computing speed;
d) type of CPU;
e) sampling time;
f) interruption;
g) control cycle;
h) redundancy (multi-computer, single-computer operation, cold backup of memory and structure switching/reorganization, etc.);
i) fault tolerance against single event upset (SEU), single event latchup (SEL) and other accidental errors;
j) input/output interface;
k) memory downloading and modification of the capacity of memory data;
Codeofchina.com is in charge of this English translation. In case of any doubt about the English translation, the Chinese original shall be considered authoritative.
This specification replaces GJB 1416-1992 General specification for satellite attitude control system.
The following main technical changes have been made with respect to GJB 1416-1992:
a) the name of the specification is changed as General specification for spacecraft control system, and the application scope is expanded from "satellites" to "spacecrafts", including satellites, manned spacecrafts and space probes;
b) "System composition" and "Unit functions and performance" are added;
c) orbit control, orbit control accuracy, rendezvous and docking, landing point control accuracy, etc. are added in "System functions and performance".
This specification was proposed by the China Aerospace Science and Technology Corporation.
GJB 1416 was issued for the first time in 1992.
General specification for spacecraft control system
1 Scope
This specification specifies the technical requirements, quality assurance requirements and delivery preparations for spacecraft control system.
This specification is applicable to the design, manufacture, test and acceptance of spacecraft control system.
2 Normative references
The following normative documents contain provisions which, through reference in this text, constitute provisions of this specification. For dated reference, subsequent amendments (excluding corrections), or revisions, of any of these publications do not apply to this specification. However parties to agreements based on this specification are encouraged to investigate the possibility of applying the most recent editions of the normative documents indicated below. For undated references or references with version not indicated, the latest edition of the normative document referred to applies.
GB/T 191 Packaging - Pictorial marking for handling of goods
GJB 150.1A-2009 Laboratory environmental test methods for military materiel - Part 1: General requirements
GJB 150.9A-2009 Laboratory environmental test methods for military materiel - Part 9: Damp heat test
GJB 150.15A-2009 Laboratory environmental test methods for military materiel - Part 15: Acceleration test
GJB 150.16A-2009 Laboratory environmental test methods for military materiel - Part 16: Vibration test
GJB 150.18A-2009 Laboratory environmental test methods for military materiel - Part 18: Shock test
GJB 151 Electromagnetic emission and susceptibility requirements for military equipments and subsystems
GJB 190 Classification of characteristics
GJB 421 Satellite terminology
GJB 899 Reliability testing for qualification and production acceptance
GJB 1027 Test requirements for launch, upper-stage, and space vehicles
GJB 1030 Methods for simulation test of satellite control system
GJB 2042 General specification for satellite electrical power system
GJB 2203 Cleanliness and contamination control requirements for satellite product
GJB 2496 Terminology for manned spacecraft astronautical engineering
GJB 2998 Mark of satellite products
GJB 3590 Electromagnetic compatibility requirements for space systems
GJB/Z 35 Derating criteria for electrical, electronic and electromechanical parts
GJB/Z 1391 Guide to failure mode, effects and criticality analysis
QJ 977 Rule for re-inspection of non-metallic materials
QJ 1286 Testing regulation for attitude control system of satellite
QJ 1386 Rule for re-inspection of metallic materials
QJ 2172 Guide to satellite reliability design
QJ 2236 Safety assurance requirements for aerospace products
QJ 2437 Analysis of effect and criticality of satellite failure
QJ 2463 Test method for three-axis stabilized satellite control system
QJ 2850 Prevention and control for foreign object debris (FOD) of space products
QJ 3065.1 Management requirements for selection of components
QJ 3128 Specification for development of space project software
QJ 3130 Specification for software configuration management of space products
3 Requirements
3.1 System composition
The control system is generally composed of sensors, controllers and actuators, as shown in Figure 1:
a) sensors generally include optical sensors (infrared earth sensors, star sensors, sun sensors, ultraviolet sensors, etc.), inertial sensors (gyroscopes, accelerometers, etc.), magnetometers, navigation sensors (rendezvous and docking sensors, navigation receivers, etc.), radio frequency sensors, etc.;
b) controllers generally include control computers, emergency controllers, man-control lines, etc.
c) actuators generally include thrusters and/or engines (cold gas thrusters, single-component thrusters, double-component thrusters and/or engines, electric thrusters, etc.), momentum wheels or reaction wheels, control moment gyroscopes, magnetic torquers, solar array driving mechanisms, antenna orientation driving mechanisms, etc.
Notes:
1 Sometimes the control system also includes special power supply units or DC/DC power converters.
2 The configuration of control system is determined according to the mission requirements.
Figure 1 Schematic diagram for control system composition
3.2 System functions and performance
3.2.1 System functions
The system functions are selected according to the specific requirements of spacecraft control system. The control system has the following main functions:
a) program control and mode control.
b) navigation and escape survival control of the launching phase.
c) eliminate the initial attitude deviation of the spacecraft after it is separated from the launch vehicle and the attitude disturbance when the solar array and antenna are deployed.
d) capture and directional control of celestial bodies such as sun and earth.
e) establishment and stability of normal attitude.
f) attitude stability during attitude maneuver, attitude offset and orbit control.
g) orbit capture, maneuver and maintenance.
h) autonomous navigation.
i) control of celestial bodies such as solar array and antenna.
j) combination control (used for space station combination after rendezvous and docking, space station laboratory combination, etc.).
k) rendezvous and docking and evacuation control.
l) for manned spacecraft, the control ability of attitude, orbit, rendezvous and docking, evacuation and return, etc. with astronaut participation shall be provided.
m) brake control.
n) return reentry control.
o) celestial surface landing control.
p) celestial surface rising control.
q) spin-up and spin-down control of spin-stabilized satellites.
r) autonomous nutation damping control.
s) send telemetry data.
t) receive remote control commands and have the functions of remote control data injection and/or in-orbit programming.
u) receive man-control commands.
v) failure-safe function. In case of failure of the control system unit, which makes the spacecraft lose its attitude reference and fail to maintain normal business, the control system has the ability of autonomous diagnosis and reconstruction, and cooperates with other spacecraft systems to make the spacecraft in a safe state with ensured power supply, communication link and propellant supply, waiting for ground treatment, and realizing the restoration of normal attitude autonomously if necessary.
3.2.2 System performance
The system performance is selected according to the specific requirements of spacecraft control system.
The dynamic characteristics and disturbance moments of spacecraft in different operation phases shall be considered in the design of control system, so that the following main performance parameters meet the requirements of special technical documents:
a) the maximum allowable initial attitude angular velocity;
b) allowable initial attitude angle;
c) attitude offset range and accuracy;
d) time required for attitude maneuver;
e) attitude measurement accuracy;
f) attitude determination accuracy;
g) attitude control accuracy;
h) attitude stability;
i) orbit determination accuracy;
j) orbit control accuracy;
k) navigation accuracy;
l) guidance accuracy;
m) pointing accuracy for solar array;
n) orientation accuracy for antenna;
o) anti-disturbance ability;
p) initial docking conditions and control accuracy of rendezvous and docking;
q) control accuracy of landing point and the maximum overload (manned or unmanned);
r) number of air injection and propellant consumption;
s) robustness of control system and stability margin under the worst parameter combination;
t) secondary control accuracy (inter-satellite link, optical observation platform);
u) dynamic quality of control system;
v) reliability of control system;
w) design lifetime, etc.
3.3 Unit functions and performance
3.3.1 Sensors
3.3.1.1 Sensor functions
The sensor functions shall meet the requirements of special technical documents, which generally include:
a) acquire the attitude or position information of the spacecraft relative to the reference target or inertial space by using the reference target sensitive to optical system;
b) acquire the spacecraft attitude or navigation information by using inertial instruments;
c) acquire spacecraft attitude or position information through sensitive celestial magnetic fields;
d) acquire the relative position and/or relative attitude information between two or more spacecrafts by optical and electromagnetic means;
e) acquire the attitude or position information of the spacecraft relative to the radio frequency emission source with known sensitive position through the radio waves emitted by such source.
3.3.1.2 Sensor performance
The sensor performance shall meet the requirements of special technical documents, which generally include:
a) measurement range;
b) field of view;
c) absolute/relative accuracy;
d) resolution;
e) linearity;
f) measurement bandwidth;
g) time requirements (including sampling rate, maximum delay time, stability of sampling rate and delay time, etc.);
h) allowable maximum noise;
i) error model and related parameters obtained after calibration;
j) allowable remnant magnetic torque, etc.
3.3.2 Controller
3.3.2.1 Controller functions
With the support of related system software and hardware, the controller has the following main functions:
a) complete the program control for the processes of pending, launching, injection, separation of satellite (airship, spacecraft) and launch vehicle, in-orbit (including the main in-orbit working modes such as rendezvous and docking), deorbit and return;
b) complete the automatic (or manual) setting and switching of working modes in the control process; complete the structural reorganization of the control system in various working modes, including the selection of thrusters in various working modes; complete the parameter modification and channel offset setting of the corresponding working mode;
c) in various working modes, complete the acquisition and processing of attitude sensor measurement data (or manual control command), and calculate the attitude angle and angular velocity of each axis of spacecraft, navigation and relative position/attitude; calculate the control amount of each channel according to the set control rules based on the offset or compensation quantities of each channel and sent it to the actuator;
d) provide remote control interface with TT&C or data management system, receive ground remote control command, and realize switching of major units and backup units; complete the setting and switching of various control modes and states of the control system; complete the setting of control parameters of the control system;
e) provide telemetry interface with TT&C or data management system, and send the measured output values and working parameters of each sensor as well as the main control quantities of each control channel of the control system to TT&C or data management system; intensively transform and transmit the working state parameters of each unit and various working modes of system;
f) provide input interfaces for various sensor signals and other control commands;
g) provide the output interface with the control actuator;
h) complete the automatic unloading of momentum exchange unit;
i) pointing control of solar array and orientation control of antenna;
j) orbit calculation;
k) ephemeris table computation;
l) memory downloading and modification of memory data and programs by remote control;
m) failure detection, isolation and recovery.
3.3.2.2 Controller performance
The control computer (digital controller) has the following performance:
a) computer word length;
b) memory capacity;
c) computing speed;
d) type of CPU;
e) sampling time;
f) interruption;
g) control cycle;
h) redundancy (multi-computer, single-computer operation, cold backup of memory and structure switching/reorganization, etc.);
i) fault tolerance against single event upset (SEU), single event latchup (SEL) and other accidental errors;
j) input/output interface;
k) memory downloading and modification of the capacity of memory data;
l) allowable remnant magnetic torque, etc.
