7 results about "Orbital operations" patented technology

Described herein is a method for wireless transmission of energy in space, wherein a constellation of transmitting satellites orbiting around a celestial body, such as the planet (P) Earth or the Moon (L), are equipped with a laser apparatus for sending a beam of coherent electromagnetic waves to an orbiting satellite or another receiving target, such as a mobile vehicle or a fixed base on said generic celestial body, in order to transmit energy thereto. The total power transmitted is divided among the orbiting satellites in the constellation, resulting in less contraindications than in the case of a single transmitting system with equivalent total power. The advantage of such division among a constellation of satellites mainly consists of shorter periods of solar eclipse, since sunlight is necessary for the operation of the transmission system. The receiving target or satellite converts the beam of electromagnetic waves into electric energy.

A satellite (140) for operation in an orbit around the Earth includes an ADCS (131, Fig. 1) configured to mechanically steer the satellite in an azimuth direction to extend a dwell time (1105) during which a target is visible from the satellite when the satellite is orbiting above the target of choice. A processor at a ground station can be configured to process raw SAR data from any of the satellites described herein. The raw SAR data can be processed in a variety of ways to provide image information, including but not limited to forming multi-view images, compiling video sequences, and color coding images.

The invention presents a method for managing spatial data in a space and Earth surveillance or orbital operations security environment, the method being characterized by the following steps: Structuring the spatial data in the form of a directed acyclic graph (DAG); Associating each node with a creation date and traceability metadata allowing each node to be linked to the parent nodes from which it is derived; Including for each node numerical quality indicators and a confidentiality level specific to the data it contains; Transferring said metadata containing said indicators and levels from each node to the derived nodes; Managing and monitoring data transformations based on said quality and confidentiality metadata. Figure 2

The invention discloses a transfer orbit design method in on-orbit service of a synchronous orbit satellite. The problem of how to effectively image a high-orbit target satellite with low fuel consumption is solved. Belongs to the technical field of space. Comprising the following steps: determining total transfer time according to different initial states of a service satellite and a target satellite; constructing a transfer orbit mathematical model based on the total transfer time to obtain the running time of the service satellite on the initial orbit, the transfer orbit and the approaching orbit in the transfer process and the speed increment for completing the Horman transfer; taking a relative position vector included angle and an illumination angle of two stars at the end of intersection as an objective function, taking total transfer time as a constraint condition, taking the operation time of a service star in an initial orbit and an approaching orbit as an optimization variable, optimizing the objective function by using a genetic algorithm based on an HPOP model, and correcting parameters of a transfer orbit mathematical model to obtain a transfer orbit mathematical model; obtaining a transfer orbit mathematical optimization model; according to the method, effective imaging of the high-orbit target with low burnup is realized through the mathematical optimization model of the transfer orbit.

According to the device for simulating the potential state of the spacecraft structure, the potential state of the spacecraft structure running in different orbits and in a complex space environment is simulated through an electron injection mode and an electron extraction mode, and the device is an efficient and controllable space environment simulation tool; the device has the characteristics of adjustable electron flow, simple equipment, high integration level, compact structure and wide application range, is an important bridge for connecting space environment theory, material science and aerospace engineering practice, and can be applied to potential simulation experiments of different spacecrafts; the platform is an indispensable key ground verification platform for ensuring high-reliability and long-life operation of a spacecraft in orbit.

Described are techniques for determining an impact threat of an orbiting object by a crowdsource satellite network. The techniques include capturing, by a satellite included in a crowdsource satellite network, information associated with an orbiting object detected by the satellite. The techniques further include providing, by the satellite, the information associated with the orbiting object to the crowdsource satellite network. The techniques further include collaborating by the satellite with other satellites in the crowdsource satellite network to track the orbiting object, generate an orbital model of the orbiting object, and to analyze a predicted path of the orbiting object represented by the orbital model to determine an impact threat associated with the predicted path of the orbiting object.

The invention provides a thermal analysis and temperature prediction method and system for a multi-orbit cycle aerospace satellite, and the method comprises the steps: building a satellite three-dimensional physical model through finite element simulation software, setting the thermophysical parameters of all part materials, configuring a heat source and a contact thermal resistor in a solid heat transfer module, and carrying out the thermal analysis and temperature prediction. A space thermal environment and a satellite orbit attitude are defined in an orbit thermal load module, dynamic periodic control of heat source power is realized by utilizing an event module, and a step-by-step solving strategy is adopted: firstly, single-orbit periodic thermal load distribution is calculated, and then the single-orbit periodic thermal load distribution is periodically and repeatedly loaded in a plurality of orbit periods, so that the dynamic periodic thermal load control is realized. And finally, the temperature field change of the satellite in multi-orbit operation is obtained. The method effectively solves the problem that a traditional analysis method is difficult to give consideration to the multi-orbit periodic temperature accumulation effect and the dynamic thermal load change, significantly improves the prediction precision and calculation efficiency of the satellite thermal analysis, and provides a reliable basis for the thermal design of a spacecraft.