Imaging simulation becomes an effective and necessary way to see how the wide-field sensor performs because design and analysis of a wide-field sensor requires a lot of rigid conditions. Here, a long-wave infrared panoramic scanning sensor is designed for small target detection. Space-based imaging simulation based on the characteristics of the panoramic scanning sensor is realized. Serial images covering 360°×10° field of view is generated. Stars, long-distance satellites, and space debris appear as point sources in the images. It is demonstrated that the panoramic scanning sensor has the capability of observing a long-distance small target and can be used for space target detection.
Vortex beams have special applications in many areas, such as quantum information processing, quantum entanglement, particles trapping and manipulation etc. A great deal of attention has been given to the research of the generating vortex beam and measuring the topological charge. This paper presents a method to measure the topological charge of vortex beams by using a cylinder Lens. Simulation and experiment results show that dark stripes appear when topological charge is non-zero, and the number of dark stripes is equal to the topological charge. Therefore our research results may be applied as a new method to analyze the topological charge of vortex beams.
One of the strategic goals for the development of space technology is to achieve the mass, volume and lifetime cost of spacecraft lower than at present, which requires lightweight, miniaturization, low power consumption, rapid design and rapid integration, rapid testing and other aspects to achieve a deep level of technical breakthroughs.[1] The traditional electronic system of satellite cabin is connected by cable, which has many disadvantages, such as large volume weight, narrow band, poor anti-electromagnetic interference ability, complex network connection and low integration. If the effective No-cable technology can be adopted, the dry weight of the space vehicle can be reduced, the utilization efficiency of the payload can be improved, and the layout of the internal conductor of the space vehicle can be reduced, which not only saves the space, but also shortens the development period. Therefore, the high-speed interconnection technology of electronic equipment in satellite cabin is studied in this paper. By analyzing the characteristics of information flow and sensor distribution in the satellite, laser communication technology is adopted for high speed interconnection. Aiming at the future application, the laser communication device in satellite cabin is designed and verified in orbit, which provides an effective support for the application of No-cable satellite.
Thermal effect severely limits the output power and beam quality in high-power solid-state lasers systems. In solid-state lasers, most optical elements are cylindrical, such as laser medium, mirrors, and so on. Normally, thermal analysis is deduced based on the hypothesis that just one surface is cooled while the others are adiabatic. This paper presents semi-analytical formula of steady-state temperature field distribution, based on the hypothesis that both side surface and one end surface are cooled with different coefficients of heat transfer. Simulation results with Ansys confirmed the correctness of the above formula. The results are helpful to the study of thermal effect in disc laser, rod laser and reflective mirrors in high-power laser system.
Distributed reconfigurable satellite is a new kind of spacecraft system, which is based on a flexible platform of modularization and standardization. Based on the module data flow analysis of the spacecraft, this paper proposes a network component of ad hoc Laser networks architecture. Low speed control network with high speed load network of Microwave-Laser communication mode, no mesh network mode, to improve the flexibility of the network. Ad hoc Laser networks component technology was developed, and carried out the related performance testing and experiment. The results showed that ad hoc Laser networks components can meet the demand of future networking between the module of spacecraft.
At present, Spacecraft manufacturing face with high adventure for its complicate structure, serious space environment and not maintained on orbit. When something wrong with spacecraft, monitoring its health state, supply health data in real time would assure quickly locate error and save more time to rescue it. For FBG sensor can distributed test several parameters such as temperature, strain, vibration and easily construct net. At same time, it has more advantages such as ant-radiate, anti-jamming, rodent-resistant and with long lifetime, which more fit for applying in space. In this paper, a spacecraft health monitor system based on FBG sensors is present, Firstly, spacecraft health monitor system and its development are introduced. Then a four channels FBG demodulator is design. At last, Temperature and strain detecting experiment is done. The result shows that the demodulator fully satisfied the need of spacecraft health monitor system.
Distributed reconfigurable satellite is a new kind of spacecraft system, which is based on a flexible platform of modularization and standardization. Based on the module data flow analysis of the spacecraft, this paper proposes a network component of ad hoc Laser networks architecture. Low speed control network with high speed load network of Microwave-Laser communication mode, no mesh network mode, to improve the flexibility of the network. Ad hoc Laser networks component technology was developed, and carried out the related performance testing and experiment. The results showed that ad hoc Laser networks components can meet the demand of future networking between the module of spacecraft.
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