Test method for three-axis stabilized satellite control system
1 Subject content and applicable scope
This standard specifies the test methods for the functions and main property parameters of the three-axis stabilized satellite control system in ground tests.
This standard is applicable to the test of three-axis stabilized satellite control systems and the acceptance and post-installation tests of them.
2 Reference standards
GJB 421 Terminology of satellite
3 Terms
For the purposes of this standard, the following and those specified in GJB 421 apply.
3.1 satellite control system
system (abbreviation for satellite attitude and orbit control system) used to achieve the attitude control and orbit control tasks in the stages of satellite operation
3.2 earth simulator
device that can simulate the infrared radiation of the earth sensed by satellites for purpose of testing and calibration of infrared earth sensors on ground
3.3 sun simulator
device with an apparent diameter equal to that of the sun, which can simulates the visible light of the sun for purpose of testing and calibration for sun sensor on ground
3.4 solar constant
all the radiant energy that the sun projects on a unit area perpendicular to the sunlight direction at the average sun-to-earth distance in the unit time outside the earth's atmosphere
3.5 effective solar constant
current value of a standard sensitive element under the irradiation at a solar constant, which is used as a unit in which a solar simulator provides the irradiance on the illuminated test surface in the waveband of this type of sensitive element
3.6 star simulator
device that can simulate star magnitude and graph for purpose of testing and calibration of star sensors on ground
3.7 effective drift of gyro
change of the output signal of the gyro due to the interference torque or the noise and drift in the circuit, which is expressed by the equivalent input angular velocity
3.8 operation modes
to archive the different tasks in all operation stages of the satellite, the control system adopts different structures and parameters to form the corresponding control loop
3.9 inertial attitude sensor
device that can measure satellite angular velocity and angle by using the properties of a gyro. It is consisted of gyro assembly and signal processing circuit. The gyro assembly is composed of one or more gyros installed at a certain angle to each other
3.10 satellite body coordinate system
rectangular coordinate system fixed on the satellite body, in which a characteristic point in the satellite body is used as its coordinate origin, and three mutually perpendicular characteristic directions as its axes
As shown in Figure 1, OX is the heading direction of the satellite, OZ points to the center of the earth, and OY, OX and OZ axes follow the right-hand rule when the satellite is operating normally
1 Subject content and applicable scope
2 Reference standards
3 Terms
4 Test equipment and main functions
5 Power current measurement
6 Property tests for components
7 Open circuit test for control system
8 Closed circuit test for control system
