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 electromagnetic phased array (100) is disclosed comprising a plurality of antenna elements (102), each antenna element (102) comprising at least three constituent antennae (104). A drive circuit (106) generates about an axis of each element (102) a radiation pattern that has a defined minima at or close to a null in at least one direction. The drive circuit (106) effects electronic steering of this minima through a range of angles around the axis of each antenna element (102) of the array (100) by appropriate setting of the vector currents associated with its constituent antennae (104). The axes of each of the antenna elements (102) are aligned in parallel with a central axis of the array (100) and at least a sub-set of the elements (102) lie substantially on a common helical surface. The elements (102) are spaced on this surface such that the array (100) has a substantially constant aperture.

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.

A satellite rescue system (SRS) (1) for rescue and recertification of dormant satellites, said SRS having a thruster end (13) with a primary propulsion nozzle (11) and maneuvering thrusters (12) and a satellite connection end (8) with a body (15) between both ends. The satellite connection end of the SRS has an interface ring (14) with clinch clamps (4) that securely attach to a ring (3) on the rescued satellite. An umbilical connector (7) on the satellite connecting end of the SRS provides power and data to the rescued satellite.

A self-deployable array of panels includes a plurality of panels, each panel having a first compressed panel thickness state and a second expanded panel thickness state, and including a spring bias element biased to the second expanded panel thickness state. A plurality of locking hinges hingedly couple each of the panels to an adjoining panel. Each locking hinge is biased to an open position. A release of stored potential energy of both of the spring bias element biased to the second expanded panel thickness state, and the locking hinges biased to the open position causes the self-deployable array of panels to self-deploy from a folded stowed state. A single part offset locking hinge is also described.

A self-deployable array of panels includes a plurality of panels, each panel having a first compressed panel thickness state and a second expanded panel thickness state, and including a spring bias element biased to the second expanded panel thickness state. A plurality of locking hinges hingedly couple each of the panels to an adjoining panel. Each locking hinge is biased to an open position. A release of stored potential energy of both of the spring bias element biased to the second expanded panel thickness state, and the locking hinges biased to the open position causes the self-deployable array of panels to self-deploy from a folded stowed state. A single part offset locking hinge is also described.

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.

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.

A trussed collapsible tubular mast includes a deformable beam having an extended state, a flattened state, and a rolled state, where a stiffness and strength of the deformable beam in the extended state is greater than a different stiffness and a different strength of the deformable beam in the flattened state. At least one collapsible tubular mast wall has a plurality of truss members of a first material having a first material thickness. At least one truss member is disposed substantially perpendicular to a longitudinal axis of the trussed collapsible tubular mast. Disposed between the truss members is a wall area of a second material thickness less thick than the first material thickness.

A trussed collapsible tubular mast includes a deformable beam having an extended state, a flattened state, and a rolled state, where a stiffness and strength of the deformable beam in the extended state is greater than a different stiffness and a different strength of the deformable beam in the flattened state. At least one collapsible tubular mast wall has a plurality of truss members of a first material having a first material thickness. At least one truss member is disposed substantially perpendicular to a longitudinal axis of the trussed collapsible tubular mast. Disposed between the truss members is a wall area of a second material thickness less thick than the first material thickness.