Solar radiation is collected and converted to microwave energy by means maintained in outer space on one or more platforms in space. The microwave energy is then transmitted to earth and directed to and constantly focused on one or more segments of a generally circular and slowly rotating tropical depression, which is a precursor to a tropical storm and then a hurricane (alternatively called a cyclone or typhoon). The focused microwave energy interrupts the cycle of vertical upward and downward movement of air, water, & water vapor, and destabilizes the developing rotational motion of the tropical depression, causing it to break up and dissipate, and preventing it from ultimately developing into a hurricane. When not focusing microwave energy on a tropical depression, the microwave energy can alternatively be used to create earth based solar energy, which would help alleviate costs of operating the system solely for hurricane prevention.

The present disclosure relates to a robotically controlled satellite refueling tool and associated robotically controlled support and site preparation tools which facilitates on-orbit refueling by teleoperation of fill/drain valves of various designs and dimensions on satellites not originally prepared for on-orbit servicing, through the installation of quick connect safety valves, using vision-based feedback as well as feedback from sensors embedded in the refueling tool to operate a suite of adaptable and adjustable mechanisms. The refueling tool has an open architecture to allow a refueling tool vision system to see the fill/drain valve and the section of the refueling tool that is engaged with the fill/drain valve. The support tools include a blanket cutter tool, a blanket handler tool, a wire cutter tool, a gripper tool, and the site preparation tools include a B-nut removal tool and a crush seal removal tool. Each of these tools includes a common base structure which is interfaced to the end effector of the robotic arm for transmitting rotation and torque to the various tools.

The embodiments herein provide a system and method for integrated optimization of design and performance of satellite constellations. The present disclosure provides a method for optimization of design and performance of satellite constellation to provide internet connectivity at preset geographic regions. In current methods, the optimizations of subsystems are performed independently and the results are combined, resulting in a loss of overall optimality. The present disclosure defines the relationships between subsystems such that integrity of complete design is tested with fewer complexities and provides an integrated optimization framework, in which every subsystem is optimized individually and collectively. The present disclosure provides a method for optimization of power subsystem of satellites by determining the pattern of payload operation and need for peak power. The present disclosure also provides a method to minimize the number of satellites required in constellations by carefully regulating spot beams formed by individual satellites in constellations.

The embodiments herein provide a system and method for integrated optimization of design and performance of satellite constellations. The present disclosure provides a method for optimization of design and performance of satellite constellation to provide internet connectivity at preset geographic regions. In current methods, the optimizations of subsystems are performed independently and the results are combined, resulting in a loss of overall optimality. The present disclosure defines the relationships between subsystems such that integrity of complete design is tested with fewer complexities and provides an integrated optimization framework, in which every subsystem is optimized individually and collectively. The present disclosure provides a method for optimization of power subsystem of satellites by determining the pattern of payload operation and need for peak power. The present disclosure also provides a method to minimize the number of satellites required in constellations by carefully regulating spot beams formed by individual satellites in constellations.

An aerospace mirror having a reaction bonded (RB) silicon carbide (SiC) mirror substrate, and a SiC cladding on the RB SiC mirror substrate forming an optical surface on a front side of the aerospace mirror. A method for manufacturing an aerospace mirror comprising obtaining a green mirror preform comprising porous carbon, silicon carbide (SiC), or both, the green mirror preform defining a front side of the aerospace mirror and a back side of the aerospace mirror opposite the front side; removing material from the green mirror preform to form support ribs on the back side; infiltrating the green mirror preform with silicon to create a reaction bonded (RB) SiC mirror substrate from the green mirror preform; forming a mounting interface surface on the back side of the aerospace mirror from the RB SiC mirror substrate, and forming a reflector surface of the RB SiC mirror substrate on the front side of the aerospace mirror. Additionally, the method can comprise cladding the reflector surface of the RB SiC mirror substrate with SiC to form an optical surface of the aerospace mirror.

A heat storage device including a metal layer containing a protrusion-and-recess-shaped object, in which the protrusion-and-recess-shaped object has an average height of 100 nm or more and 1,000 nm or less.

The present disclosure relates to a maritime communication system based on low earth orbit satellites and an unmanned aerial vehicle. The maritime communication system according to one embodiment may include one or more maritime users, one or more satellites connected to a network operator, and an unmanned aerial vehicle (UAV) for relaying communication between the maritime users and the satellites.

Cell-based systems may interlock in a reconfigurable configuration to support a mission. Space systems, for example, of a relatively large size may be assembled using an ensemble of individual “cells”, which are individual space vehicles. The cells may be held together via magnets, electromagnets, mechanical interlocks, etc. The topology or shape of the joined cells may be altered by cells hopping, rotating, or “rolling” along the joint ensemble. The cells may be multifunctional, mass producible units. Rotation of cell faces, or of components within cells, may change the functionality of the cell. The cell maybe collapsible for stowage or during launch.

Cell-based systems may interlock in a reconfigurable configuration to support a mission. Space systems, for example, of a relatively large size may be assembled using an ensemble of individual “cells”, which are individual space vehicles. The cells may be held together via magnets, electromagnets, mechanical interlocks, etc. The topology or shape of the joined cells may be altered by cells hopping, rotating, or “rolling” along the joint ensemble. The cells may be multifunctional, mass producible units. Rotation of cell faces, or of components within cells, may change the functionality of the cell. The cell maybe collapsible for stowage or during launch.

The disclosed technology includes systems, methods, and mechanism configurations related to satellite solar panels, including stowing arrangements, deployment sequences, special purpose hinges, hold down and release mechanisms, and associated components for controlled deployment of the satellite solar panels.