A satellite constellation forming system (100) forms a satellite constellation which is composed of a satellite group and in which the satellite group cooperatively provides a service. The satellite constellation has a plurality of orbital planes in each of which a plurality of satellites fly at the same nominal orbital altitude. A satellite constellation forming unit (110) continues providing the service while avoiding a collision between satellites by both or one of control of an orbital altitude and control of a passage timing of a satellite group flying in a region where the plurality of orbital planes intersect.

A method of communication with a non-GEO constellation of satellites, includes providing an Earth-based terminal configured for communication with a satellite constellation, and establishing communication between the Earth-based terminal and a non-GEO constellation of satellites, the non-GEO constellation of satellites including a first plurality of satellites orbiting at a first inclination, wherein each of the satellites in the first plurality of satellites is in a discrete planar orbit to form a first snake of satellites, the first snake of satellites including adjacent satellites in adjacent orbits having adjacent RAAN (Right Ascension of the Ascending Node), wherein the Earth-based terminal is positioned and configured for continuous communication with at least one satellite from the non-GEO constellation of satellites.

Systems, apparatuses, and methods provide for technology that locates one or more masses of a thunderstorm system, as the thunderstorm system starts to organize and before the thunderstorm system spawns a tornado, and controls a transmission of electromagnetic radiation from the space platform to the one or more masses, wherein the transmitted electromagnetic radiation tracks the one or more masses as the thunderstorm system is starting to organize and rotate, and wherein the transmitted electromagnetic radiation prevents the thunderstorm system from rotating and spawning the tornado.

An orbit transition apparatus that transitions an orbit of a payload in outer space includes a rotating body, an adapter disposed on a center part of the rotating body for docking a payload, a launch module disposed outside of the rotating body for launching the payload, and a thruster for rotating the rotating body. The launch module may launch the payload to a target orbit.

An orbit transition apparatus that transitions an orbit of a payload in outer space includes a rotating body, an adapter disposed on a center part of the rotating body for docking a payload, a launch module disposed outside of the rotating body for launching the payload, and a thruster for rotating the rotating body. The launch module may launch the payload to a target orbit.

Aspects of the subject disclosure may include, for example, a device that has a processing system including a processor; and a memory that stores executable instructions that, when executed by the processing system, facilitate performance of operations, including receiving a request for an observation of an overhead viewing area from an observer location; discovering an interference of a satellite with the observation of the overhead viewing area; determining possible solutions to the interference; selecting a solution of the possible solutions; receiving the observation from one or more satellites responding to the solution selected; and providing a response to the request including the observation received. Other embodiments are disclosed.

A servicing system for on-orbit spacecrafts is disclosed. The system comprises a servicing or host spacecraft configured to perform on-orbit servicing of client spacecrafts. The servicing spacecraft comprises a dedicated, deployable, boom having capture and docking mechanisms. The capture mechanism comprises one or more electromagnets spaced apart and suspended on a frame that may include means for compensating for any out of plane misalignments during capture. The client spacecraft includes a striker plate that covers an area, nominally larger than the footprint of the capture mechanism, that is sized to accommodate a capture envelope determined by the rendezvous and proximity sensing systems. The electromagnets attract the striker plate to capture the client spacecraft in order to provide on-orbit servicing. The docking system has multiple degrees of freedom that are independent of the capture system; docking is accomplished by mechanically coupling the two spacecrafts together, post capture. During docking, electrical and fluid transfer connections may also be accomplished. The servicing spacecraft further comprises a manipulator arm that may be configured to position/align the captured client spacecraft for docking, thereby permitting a very flexible, larger, capture envelope, and reducing operational complexity.

The present invention relates to a resident space object orbit determination system comprising a high efficiency module for determining a resident space object's orbit and a highly efficient method for determining same. Applicants developed a method and system to determine the orbits of residence space objects including resident space objects that do not reflect energy that is directed at them and/or may be coated to minimize the ability to accurately see such resident space objects. Thus, a method, a module and a system for making such determinations that can easily and inexpensively be added to an early warning reentry system is provided.

System and method for direct solar energy to device transmission includes collecting and converting solar radiation energy to electrical energy by at least one satellite, generating a transmissive energy from the electrical energy, forming a transmissive energy beam, transmitting the energy beam from space directly to an electronic device located on Earth, receiving the energy beam by the electronic device's rectenna, converting the energy beam to alternating current, matching rectenna's antenna impedance with the rectenna's rectifying circuit impedance, rectifying the alternating current to direct current, and powering a load of the electronic device.

Multi-functional coilable thin-walled structures that can be implemented within space-based satellite modules, and methods for their manufacture are provided. Multi-functional coilable thin-walled structures are comprised of at least one longeron that is capable of rolling and collapsing upon itself. In some embodiments, the coilable thin-walled longeron is a flange longeron. The flange longeron contains at least two major regions: a web and a plurality of flanges. The web region comprises portions of flanges that are bonded to one another. The plurality of flanges separate from one another on the same end of the web region. The plurality of flanges are similar in thickness and shape.