118 results about "Solar angle" patented technology

The present invention provides a method for the attitude control of satellites in elliptic orbits or satellites initially placed in circular orbits perturbed to elliptic orbits due to environmental disturbances. The method relies on the application of solar radiation pressure to provide the desired torque for the satellite attitude control. The satellite is equipped with two-oppositely placed light-weight solar panels extending away from the satellite along a predetermined direction (satellite body fixed Y-axis). By rotating one of these solar panels or both of them through desired angles about their axis using the respective driver motors as per the simple open-loop control law, the torque about the satellite axis is developed to achieve the desired attitude performance. The open-loop control law is derived using an analytical approach to neutralize the excitation caused by eccentricity and it is implemented via analog logic based on the information of sun angle and satellite position provided by the sensors. The present invention significantly improves the performance of the satellite by a factor of more than 20 times approximately in general and it only requires the rotation of the solar panels by fraction of a degree for particular system parameters. Thus, the semi-passive nature of the present invention makes it attractive for future space applications.

The invention relates to the field of satellite development, in particular to a satellite configuration design method adapting to one-rocket multi-satellite launching. According to the method, for the illumination characteristic that the solar angle of a low-dip-angle orbit changes in a large range, an outer surface corresponding to the lower bottom of a satellite trapezoidal cross section is improved to be an arch formed by three panels in an enclosing mode to serve as an installing surface for fixing a solar cell array, and iterative optimization is conducted on included angles of the three cell panels. A satellite configuration designed through the method can be equivalent to the satellite configuration formed by a prismoid with a trapezoidal cross section and two slant prismoids with trapezoidal cross sections. The satellite configuration design method adapting to one-rocket multi-satellite launching has the main advantages that a solar wing spreading and driving mechanism is not arranged for each satellite, the weights of the satellites are reduced, and the reliability of the satellites is improved; a flight mission of long-time over-the-ground three-axis stable operation of a low-oblique-angle orbit can be met.

The present invention relates to a tracking-type blinds device using solar modules, and more specifically, the device comprises: a plurality of shade slats spaced apart at preset intervals so as to regulate the amount of light passing therethrough; solar modules attached to the plurality of shade slats and generating electricity by using the sunlight; a driving unit connected to the plurality of shade slats so as to respectively adjust the inclination angles of the shade slats and a distance between the shade slats; and a control unit for setting any one operation mode of a power generation mode, a privacy protection mode, and a lighting mode according to a user command, and respectively controlling the inclination angles of the shade slats and the distance between the shade slats according to the set operation mode, the current solar term, and a visual angle and solar angles.