A high altitude vehicle is brought to a desired altitude above sea-level prior to the transfer of fuel and/or oxidant from an airplane to the high altitude vehicle. The high altitude vehicle may be towed to the desired altitude by a tow airplane or may reach the desired altitude under its own power. At the desired altitude, the high altitude vehicle is connected to the tow airplane via a tow cable. Alternatively, the high altitude vehicle may be mechanically carried by the tow airplane. Fuel and/or oxidant is transferred to the high altitude vehicle from the tow airplane via respective fuel and/or oxidant lines. The high altitude vehicle then separates from the tow airplane and proceeds to high altitude under its own power.

The present disclosure relates to a robotically controlled satellite refueling tool and associated robotically controlled support and site preparation tools which facilitates on-orbit refueling by teleoperation of fill/drain valves of various designs and dimensions on satellites not originally prepared for on-orbit servicing, through the installation of quick connect safety valves, using vision-based feedback as well as feedback from sensors embedded in the refueling tool to operate a suite of adaptable and adjustable mechanisms. The refueling tool has an open architecture to allow a refueling tool vision system to see the fill/drain valve and the section of the refueling tool that is engaged with the fill/drain valve. The support tools include a blanket cutter tool, a blanket handler tool, a wire cutter tool, a gripper tool, and the site preparation tools include a B-nut removal tool and a crush seal removal tool. Each of these tools includes a common base structure which is interfaced to the end effector of the robotic arm for transmitting rotation and torque to the various tools.

A high altitude vehicle is brought to a desired altitude above sea-level prior to the transfer of fuel and/or oxidant from an airplane to the high altitude vehicle. The high altitude vehicle may be towed to the desired altitude by a tow airplane or may reach the desired altitude under its own power. At the desired altitude, the high altitude vehicle is connected to the tow airplane via a tow cable. Alternatively, the high altitude vehicle may be mechanically carried by the tow airplane. Fuel and/or oxidant is transferred to the high altitude vehicle from the tow airplane via respective fuel and/or oxidant lines. The high altitude vehicle then separates from the tow airplane and proceeds to high altitude under its own power.

A high pressure separator/accumulator that uses dual bellows is provided. The dual bellows are not mechanically linked but rather operationally coupled through a fluid medium. The high pressure separators includes a housing defining a first internal space. The housing is in fluid communication with a first fluid system and a second fluid system. A first bellows is coupled to the interior of the separator and defines a space with a variable volume. The space is in fluid communication with the first fluid system. A second bellows is coupled to the interior of the separator, generally opposed to the first bellows, and defines a space with a variable volume. The space is in fluid communication with the second fluid system. The two fluid systems, however, are isolated from each other by the separator. The housing is charged with a fluid medium that transmits force between the first and second bellows.

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.

Methods of accelerating a target vehicle to a higher orbit via a Kinetic Energy Storage and Transfer (KEST) vehicle are provided. The KEST vehicle is configured to transfer kinetic energy to the target vehicle by way of a catching mechanism using one or more brakes on one or more associated tethers along which the braking mechanism traverses, accelerating the target vehicle into a higher orbit, potentially even beyond the Earth.

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 Cooperative Service Valve includes a fitting connected to a valve body via a tube, a stem configured to fit within the valve body. The stem includes a stem first end having a first seal and configured to movably fit within a tube first end, a sealing portion connected to the stem first end and configured, in a first position, to provide a second seal between the sealing portion and an inner surface of the stem body, a fluid flow portion comprising openings for allowing liquid or gaseous media to pass through the Cooperative Service Valve when the stem is in a second position and a stem second end configured to secure a poppet guide, a poppet and a spring associated with the poppet that biases the poppet against a seal to yield a third seal. The first, second and third seals open and close in a particular order to allow or prevent fluid from flowing through the stem.

An optical mining apparatus comprising: a light weight solar reflector; optics for controlling the delivery of concentrated sun light onto the surface of a target; and a temperature controlled gas enclosure that contains the target; wherein said solar reflector is oriented to reflect sun light onto said optics.

Material transfer interfaces for space vehicles, and associated systems and methods are disclosed. A representative system includes a first coupler configured to be carried by a first space vehicle, and a first valve device carried by the first coupler. The system further includes a second coupler configured to be carried by a second space vehicle and a second valve device carried by the second coupler. The first coupler includes rotatable and translatable latch arms positioned to engage with and connect to the second coupler. The first valve device incudes a moveable probe that is insertable into the second valve device when the latch arms of the first coupler are connected to the second coupler to transfer fluid between the first and second valve devices.