The starlight navigation is considered to be one of the most important methods for spacecraft navigation. Starlight simulator system is a high-precision system with large fields of view, designed to test the starlight navigation sensor performance on the ground. A complete simulation of the system has been built. The starlight sensor testing system consists of star simulator, star scene generation computer, sensor control computer. The starlight simulator is made up of power module, light source, LCD, display circuitry, optical collimator and computer interface. LCD and optical collimator are the key display component of starlight simulator.
Starlight navigation technology is widely used in spacecraft. Celestial navigation is designed for star identification and confirmation of satellite attitudes in the space. Sensors of celestial navigation require hardware-in-the-loop simulation system for ground-testing. A new celestial navigation technology is based on dual-star-sensor for the sake of high accuracy and reliability. Hardware-in-the-loop simulation system for ground-testing generates two celestial scenes and projects them into the dual-star-sensors during navigation process by real-time graphics and simulation technologies according to the satellite’s orientation.
With the increase in application of celestial navigation as well as the advances in computer graphics technology, modeling and simulation of celestial background is widely used in ground-testing of celestial navigation.
Celestial navigation is designed for star identification and confirmation of satellite attitudes in the space. A new celestial navigation technology is based on dual-star-sensor for the sake of high accuracy and reliability. Two star-sensors are set on the satellite, and there is an angle between the light axis of these two star-sensors. So these two star-sensors are designed pointed to the different direction in the space.
Modeling and simulation of celestial background which is used in the ground-testing for dual-star-sensor displays two different celestial scenes during navigation process by real-time graphics technology according to the two sensors’ orientation.
The starlight navigation is considered to be one of the most important methods for spacecraft navigation. Starlight simulation system is a high-precision system with large fields of view, designed to test the starlight navigation sensor performance on the ground. A complete hardware-in-the-loop simulation of the system has been built. The starlight simulator is made up of light source, light source controller, light filter, LCD, collimator and control computer. LCD is the key display component of the system, and is installed at the focal point of the collimator. For the LCD cannot emit light itself, so light source and light source power controller is specially designed for the brightness demanded by the LCD. Light filter is designed for the dark background which is also needed in the simulation.
In order to test 2-color infrared sensors, a coupled infrared simulation system can generate radiometric outputs with wavelengths that range from less than 3 microns to more than 12 microns. There are two channels in the coupled simulation system, optically combined by a diachronic beam combiner. Each channel has an infrared blackbody, a filter, a diaphragm, and diaphragm-motors. The system is projected to the sensor under testing by a collimator. This makes it difficult to calibrate the system with only one-band thermal imager. Errors will be caused in the radiance levels measured by the narrow band thermal imager. This paper describes colorimetric temperature measurement techniques that have been developed to perform radiometric calibrations of these infrared simulation systems above. The calibration system consists of two infrared thermal imagers; one is operated at the wavelength range of MW-IR, and the other at the range of LW-IR.
KEYWORDS: Stars, Star sensors, Computer simulations, Visualization, OpenGL, Image sensors, Space operations, Scene simulation, Computing systems, Navigation systems
The star sensor simulation system is uesed to test the star sensor performance on the ground,which is designed for star identification and spacecraft attitude determnation of the spacecraft. The computer star scene based on the astronomical star chat is generated for hardware-in-the-loop simulation of the star sensor simulation system using by openGL.
The star sensor simulation system is used to test the star sensor performance on the ground, which is designed for star
identification and spacecraft attitude determination of the spacecraft. The computer star scene based on the astronomical
star chat is generated for hardware-in-the-loop simulation of the star sensor simulation system using by OpenGL.
The radiant characteristic is one of the most important characteristics of the infrared simulation system. This paper
evaluates the radiant energy from the target of the infrared imaging hardware-in-the-loop simulation system and
background of laboratory environment. The previous studies focuses only on the radiation of the whole target, the
radiation of background is usually discussed from the angle of noise voltage. This study analyzes the radiant energy
difference between the target and the background of the laboratory environment on a pixel of sensor focal plane array
under test.
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