Abstract: A space vehicle competition management system includes an orbital transfer vehicle (OTV) and a control unit. The OTV is configured to retain space vehicles (SVs) while the OTV transfers the SVs from an initial altitude of a launch vehicle to a desired altitude, and deploy the plurality of SVs at a series of offset locations and respective times representing starting points of the competition. Furthermore, the control unit is configured to receive signals indicative of waypoint arrival times for one or more of the SVs at one or more waypoints along a course of the competition, and compute one or more metrics indicative of relative performance of the plurality of SVs in the competition.

Abstract: A thruster system for use in a spacecraft combines chemical and electric or electrothermal propulsion. To that end a thruster may comprise a cavity including at least one inlet to receive a first fluid and a second fluid configured to chemically react with the first fluid within the cavity to generate a reaction product. Alternatively, the cavity may be configured to receive a monopropellant configured to chemically decompose within the cavity. The thruster system further comprises an energy source coupled to the cavity and configured to heat or ionize material within the cavity by emitting electromagnetic radiation. Still further, the thruster system comprises a nozzle provided at one end of the cavity and configured to direct heated material out of the cavity to generate thrust.

Abstract: A universal external port is proposed to add new functionality to or replace existing functionality of an already deployed spacecraft (e.g., a satellite in orbit). The universal external port is mounted on an external surface of the spacecraft and configured to connect to different types of external modules that have different functions, without removing components from the spacecraft other than one or more components of the universal external port. A communication interface onboard the spacecraft is configured to wirelessly receive a software patch from an entity remote from the spacecraft (e.g., from a ground terminal or other spacecraft) to program the spacecraft to change operation of the spacecraft to utilize the external module when the external module is connected to the universal external port.

Abstract: An integrated communication and ranging system for use on a spacecraft includes: a laser module configured to emit at least one beam, a pointing module configured to direct the at least one beam toward a ground station and toward an object in space, and a detector module configured to detect a scattered portion of the at least one beam. The system further includes a control module configured to operate the pointing module to (i) transmit data to the ground station using the at least one beam and (ii) determine, using the detector module, a distance between the spacecraft and the object using the at least one beam.

Abstract: An integrated communication and ranging system for use on a spacecraft includes: a laser module configured to emit at least one beam, a pointing module configured to direct the at least one beam toward a ground station and toward an object in space, and a detector module configured to detect a scattered portion of the at least one beam. The system further includes a control module configured to operate the pointing module to (i) transmit data to the ground station using the at least one beam and (ii) determine, using the detector module, a distance between the spacecraft and the object using the at least one beam.

Abstract: A universal external port is proposed to add new functionality to or replace existing functionality of an already deployed spacecraft (e.g., a satellite in orbit). The universal external port is mounted on an external surface of the spacecraft and configured to connect to different types of external modules that have different functions, without removing components from the spacecraft other than one or more components of the universal external port. A communication interface onboard the spacecraft is configured to wirelessly receive a software patch from an entity remote from the spacecraft (e.g., from a ground terminal or other spacecraft) to program the spacecraft to change operation of the spacecraft to utilize the external module when the external module is connected to the universal external port.

Abstract: Techniques for performing spacecraft rendezvous and/or docking include operating a first orbiting spacecraft, the first spacecraft including a sensor arrangement, a first processor and a first inter-satellite link (ISL) arrangement and performing one or both of a rendezvous operation and a docking operation with the first spacecraft and a second orbiting spacecraft, the second spacecraft including one or more actuators. The performing one or both of the rendezvous operation and the docking operation includes determining a pose and pose rate of the second spacecraft relative to the first spacecraft using observations made by the sensor arrangement and determining a desired approach trajectory for the second spacecraft.

Abstract: A spacecraft includes a plurality of deployable module elements, at least one of the deployable module elements including a robotic manipulator, the spacecraft being reconfigurable from a launch configuration to an on-orbit configuration. In the launch configuration, the deployable module elements are disposed in a launch vehicle in a first arrangement. In the on-orbit configuration, the deployable module elements are disposed in a second configuration. The spacecraft is self-assembled by the robotic manipulator reconfiguring the spacecraft from the launch configuration, through a transition configuration, to the on-orbit configuration. The deployable module elements may be in a stacked arrangement in the launch configuration and may be in a side-by-side arrangement in the on-orbit configuration.

Abstract: A spacecraft includes a plurality of deployable module elements, at least one of the deployable module elements including a robotic manipulator, the spacecraft being reconfigurable from a launch configuration to an on-orbit configuration. In the launch configuration, the deployable module elements are disposed in a launch vehicle in a first arrangement. In the on-orbit configuration, the deployable module elements are disposed in a second configuration. The spacecraft is self-assembled by the robotic manipulator reconfiguring the spacecraft from the launch configuration, through a transition configuration, to the on-orbit configuration. The deployable module elements may be in a stacked arrangement in the launch configuration and may be in a side-by-side arrangement in the on-orbit configuration.

Abstract: A spacecraft includes at least a first thruster support mechanism (TSM) and a second TSM, each TSM including a pointing arrangement, an elongated structural member and thruster for performing orbit raising north-south stationkeeping, east-west stationkeeping, and momentum management. A first pointing arrangement is articulable only by way of first and second revolute joints, the first revolute joint being rotatable about a first axis fixed with respect to the spacecraft. The second pointing arrangement is articulable only by way of third and fourth revolute joints, the third revolute joint being rotatable about a third axis fixed with respect to the spacecraft. The first axis and the third axis are asymmetrically arranged with respect to a spacecraft coordinate system origin such that the first and third axis are at acute angles to a spacecraft pitch axis and the acute angle of the first axis is less than that of the third axis.

Abstract: A spacecraft includes at least one deployable propulsion module, the propulsion module including at least one thruster fixedly disposed with respect to the propulsion module, a first arrangement for coupling the propulsion module to a first portion of the spacecraft in a first configuration and a second arrangement for coupling the propulsion module to a second portion of the spacecraft in a second configuration. The spacecraft is reconfigurable, on-orbit, from the first configuration to the second configuration. In the first configuration, the deployable propulsion module is detached from the second arrangement and the at least one thruster is oriented to produce thrust in a first direction. In the second configuration, the deployable propulsion module is detached from the first arrangement and the at least one thruster is oriented to produce thrust in a second direction, the second direction being substantially different from the first direction.

Abstract: A spacecraft includes a plurality of deployable module elements, at least one of the deployable module elements including a robotic manipulator, the spacecraft being reconfigurable from a launch configuration to an on-orbit configuration. In the launch configuration, the deployable module elements are disposed in a launch vehicle in a first arrangement. In the on-orbit configuration, the deployable module elements are disposed in a second configuration. The spacecraft is self-assembled by the robotic manipulator reconfiguring the spacecraft from the launch configuration, through a transition configuration, to the on-orbit configuration. The deployable module elements may be in a stacked arrangement in the launch configuration and may be in a side-by-side arrangement in the on-orbit configuration.