System for Emergency Crew Return and Down-Mass from Orbit

摘要

A system for emergency crew return and down-mass orbit comprising a stowable, self-contained, deployable maneuvering reentry vehicle for automated, on-demand reentry to ground for cargo of 1-10 kilograms or up to single or multiple human use for evacuation of orbital facilities. The system includes a deployable “aeroshell” that is contiguous (a single geometric object—surface or hollow shape—that can morph in 3D shape), modular (a collection of modular components externally acting as a contiguous shape, but morphed in 3D via actuators contained in each modular member to create a general asymmetric geometry), or discontiguous (a collection of independently controlled surfaces or bodies that morph to form desirable asymmetric drag configurations). The system contains traditional spacecraft guidance, navigation and control, propulsion, and attitude control elements, in addition to communications, power, and actuator energetics systems for controlling the vehicle aeroshell shape during reentry, thus, minimizing the landing footprint of the vehicle.

主权项

1. A system for emergency crew return and down-mass orbit comprising:
a reentry vehicle having an axisymmetrical aeroshell and a stowable configuration and a deployed configuration; a high temperature resistant refractory fabric covering said aeroshell; a plurality of circumferential inflatable stiffeners connected to said aeroshell; a plurality of radial inflatable stiffeners connected to said aeroshell and said plurality of circumferential inflatable stiffeners; a multiple layer debris shield partially enclosing said aeroshell when said aeroshell is in said stowable configuration; a plurality of radially axisymmetric panels in an annular configuration, said plurality of radially axisymmetric panels defining the outer perimeter of said aeroshell when said aeroshell is in a deployed configuration; deployment mechanisms capable of morphing the shape of said aeroshell when said aeroshell is in said deployed configuration; a payload connected to said plurality of circumferential inflatable stiffeners, plurality of radially axisymmetric panels, and said deployment mechanisms; a plurality of actuating trailing edge control surfaces connected to one end of said plurality of radially axisymmetric panels; a plurality of control systems surrounding said payload; and wherein said system has a low ballistic coefficient and is stowed within a launch vehicle.