An orbital debris interception vehicle includes a satellite bus and a debris interception module releasably coupled to the satellite bus. The debris interception module includes a debris impact pad, such as a pancake-shaped Whipple shield. A plurality of such vehicles can be deployed into an equatorial orbit and maneuvered to intercept orbital debris as it passes through the equatorial plane. In particular, the satellite bus can release the debris interception module before an intercept and reconnect to it after the intercept.

A system for landing or docking a mobile platform is enabled by a flash LADAR sensor having an adaptive controller with Automatic Gain Control (AGC). Range gating in the LADAR sensor penetrates through diffuse reflectors. The LADAR sensor adapted for landing/approach comprises a system controller, pulsed laser transmitter, transmit optics, receive optics, a focal plane array of detectors, a readout integrated circuit, camera support electronics and image processor, an image analysis and bias calculation processor, and a detector array bias control circuit. The system is capable of developing a complete 3-D scene from a single point of view.

A device 100 for a service vehicle for docking with and transferring a fluid to a vehicle in motion is disclosed. The device 100 includes a first part 105 and a second part 110. The first part 105 is communicatively coupled to the service vehicle and the second part 110 to the vehicle in motion. A guide pin 106 of the first part 105 is configured for being inserted into a guide pin holder 112 of the second part 110 for actuating a servomotor 102B of the first part 105 for capturing of the second part 110. Two or more male quick couplings 102 of the first part 105 are configured for being inserted into two or more female quick couplings 110 of the second part 110 for initiating a latching mechanism using the servomotor 102A of the first part 105 for hard clamping with the first part 105.

A system for landing or docking a mobile platform is enabled by a flash LADAR sensor having an adaptive controller with Automatic Gain Control (AGC). Range gating in the LADAR sensor penetrates through diffuse reflectors. The LADAR sensor adapted for landing/approach comprises a system controller, pulsed laser transmitter, transmit optics, receive optics, a focal plane array of detectors, a readout integrated circuit, camera support electronics and image processor, an image analysis and bias calculation processor, and a detector array bias control circuit. The system is capable of developing a complete 3-D scene from a single point of view.

An orbital debris interception vehicle includes a satellite bus and a debris interception module releasably coupled to the satellite bus. The debris interception module includes a debris impact pad, such as a pancake-shaped Whipple shield. A plurality of such vehicles can be deployed into an equatorial orbit and maneuvered to intercept orbital debris as it passes through the equatorial plane. In particular, the satellite bus can release the debris interception module before an intercept and reconnect to it after the intercept.

An orbital debris interception vehicle includes a satellite bus and a debris interception module releasably coupled to the satellite bus. The debris interception module includes a debris impact pad, such as a pancake-shaped Whipple shield. A plurality of such vehicles can be deployed into an equatorial orbit and maneuvered to intercept orbital debris as it passes through the equatorial plane. In particular, the satellite bus can release the debris interception module before an intercept and reconnect to it after the intercept.

Spacecraft servicing systems include a spacecraft servicing device and at least one mission extension pod comprising at least one spacecraft servicing component. The spacecraft servicing device is configured to transfer the at least pod to a target spacecraft in order to service the target spacecraft with the at least one spacecraft servicing component of the at least one pod. Spacecraft servicing pods configured to be supplied to a spacecraft with a spacecraft servicing device include at least one spacecraft servicing component.

Movable platforms for use with a vehicle capture assembly of a capture vehicle and related devices, systems, and methods include floors with rotatable legs extending between the floors. The rotation of the legs relative to one or more of the floors enables the movable platform to move from an initial position to a displaced position as one or more of the floors move relative to each other.

A fluid transfer interface is provided. The fluid transfer interface includes one or more of first and second interface portions. The first interface portion includes a first portion of a fluid connector and one or more ferromagnetic surfaces. The second interface portion includes an extendable second portion of the fluid connector and one or more electropermanent magnets, laterally disposed around the second portion of the fluid connector, configured to be magnetized or demagnetized in unison. The one or more electropermanent magnets are further configured to provide attraction force to the one or more ferromagnetic surfaces when magnetized and couple the first interface portion to the second interface portion and provide no attraction force to the one or more ferromagnetic surfaces when demagnetized and allow the first interface portion to be decoupled from the second interface portion.

Movable platforms for use with a vehicle capture assembly of a capture vehicle and related devices, systems, and methods include floors with rotatable legs extending between the floors. The rotation of the legs relative to one or more of the floors enables the movable platform to move from an initial position to a displaced position as one or more of the floors move relative to each other.