A method for rendezvous with an orbiting object comprising: launching a tug and a servicer into a client orbit; separating the servicer from the tug; and docking the servicer with a client. A system for rendezvous with an orbiting object comprising: a first spacecraft comprising a tug capable of towing a second spacecraft, wherein the second spacecraft is a servicer configured to dock with a tumbling client orbiting object.

A method for rendezvous with an orbiting object comprising: launching a tug and a servicer into a client orbit; separating the servicer from the tug; and docking the servicer with a client. A system for rendezvous with an orbiting object comprising: a first spacecraft comprising a tug capable of towing a second spacecraft, wherein the second spacecraft is a servicer configured to dock with a tumbling client orbiting object.

A spacecraft capable of re-entry into atmosphere includes an airframe, including a body and one or more wings, and one or more propulsion devices, for example, rocket engines, reaction control thrusters, and jet engines. One or more louver systems are incorporated into the airframe to assist in controlling the aerodynamic profile of the spacecraft. The louver system includes a number of fins rotatable about and axis. An actuator system may rotate the fins in unison or independently of the other fins. A controller may receive information from sensors incorporated into the airframe and send instructions to the actuator system to rotate the fins in response to the sensor information in order to achieve a calculated aerodynamic profile. The spacecraft may also include retractable landing legs. One or more of the wings may be actuated wings.

A spacecraft capable of re-entry into atmosphere includes an airframe, including a body and one or more wings, and one or more propulsion devices, for example, rocket engines, reaction control thrusters, and jet engines. One or more louver systems are incorporated into the airframe to assist in controlling the aerodynamic profile of the spacecraft. The louver system includes a number of fins rotatable about and axis. An actuator system may rotate the fins in unison or independently of the other fins. A controller may receive information from sensors incorporated into the airframe and send instructions to the actuator system to rotate the fins in response to the sensor information in order to achieve a calculated aerodynamic profile. The spacecraft may also include retractable landing legs. One or more of the wings may be actuated wings.

A space launch system includes a launch track and an elevating platform for horizontally launching aerospace vehicles at a takeoff velocity. The launch track includes a first portion horizontally oriented with respect to the horizon, a second portion positioned after the first portion and horizontally oriented with respect to the horizon, and a third curved transition portion disposed between the first portion and the second portion. The elevating platform is coupled to the launch track and is configured to receive and position an aerospace vehicle upon the launch track. A magnetic accelerator is disposed along the launch track for propelling the aerospace vehicle down the launch track to reach the takeoff velocity. The magnetic accelerator includes magnetic levitation trains, each comprising a respective plurality of carriers that couple to the aerospace vehicle.

A spacecraft reaction control system comprising: a spacecraft having a center of mass; a length of tether extending from said spacecraft and offset from said spacecraft's center of mass and means for controllably changing said extension of said offset such that a variable force is exerted upon said spacecraft by said tether, said force being offset from said center of mass.

Embodiments provide a spacecraft airlock system. Embodiments provide a method and apparatus for attaching space exposed payloads to a space station. The spacecraft airlock system provides a defined volume of space payload to the international space station. The airlock further includes a means of attaching to a space station, a closed structure attached to said means, said means of attaching is capable of robotic manipulation, and a cooling system for cooling payload components within said closed structure.

A magnetic position sensor for determining the angular position of a magnet on a rotatable component, comprising: at least one magnetic sensor for determining different vector components of a magnetic field of the magnet; a memory having a look-up table stored therein that is populated with data representative of different angular positions of the magnet, the data representative of each angular position being correlated with data in the look-up table that is representative of the vector components that would be detected by the at least one magnetic sensor at that angular position; wherein the magnetic position sensor is configured to use the vector components determined by the magnetic sensor and logic to determine the angular position of the magnet from the look-up table.

Rocket propulsion systems and associated methods are disclosed. A representative system includes a combustion chamber having an inwardly-facing chamber wall enclosing a combustion zone. The chamber has a generally spherical shape and is exposed to the combustion zone. A propellant injector is coupled to the combustion chamber and has at least one fuel injector nozzle positioned to direct a flow of cooling fuel radially outwardly along the inwardly-facing chamber wall. In addition to or in lieu of the foregoing features, the injector can include an oxidizer piston and a fuel piston that deliver oxidizer and fuel, respectively, to the combustion chamber, in a sequenced manner so that the oxidizer is introduced prior to the fuel.

Rocket propulsion systems and associated methods are disclosed. A representative system includes a combustion chamber having an inwardly-facing chamber wall enclosing a combustion zone. The chamber has a generally spherical shape and is exposed to the combustion zone. A propellant injector is coupled to the combustion chamber and has at least one fuel injector nozzle positioned to direct a flow of cooling fuel radially outwardly along the inwardly-facing chamber wall. In addition to or in lieu of the foregoing features, the injector can include an oxidizer piston and a fuel piston that deliver oxidizer and fuel, respectively, to the combustion chamber, in a sequenced manner so that the oxidizer is introduced prior to the fuel.