A satellite comprises a body and a generally planar structure extending from the body. One or more radio frequency “RF” antennas, an amplification system for RF signals, and a power distribution system for the amplification system are mounted on the generally planar structure. Two or all of the power distribution system, the one or more RF antennas and the amplification system are arranged on respective parallel boards (310, 312, 314) forming part of the generally planar structure (300). One or more of the parallel boards (310, 312, 314) and the components mounted thereon may be connected to another similar board to form, respectively, a larger power distribution system, antenna array or amplification system, for example arranged in a plurality of modules, each comprising at least one antenna, at least one power distribution system and at least one amplifier supported on at least two respective boards. A satellite may be manufactured by assembling the modules to form a generally planar structure, and attaching the planar structure to

A system for securing spacecraft to a rocket and deploying the spacecraft into orbit includes a stack having a plurality of spacecraft arranged in layers, with each spacecraft being releasably mated with at least one spacecraft in an adjacent layer, and at least one hold down and deploy assembly configured to, in a first configuration, secure the layers of the stack together and secure the entire stack to the rocket, and, in a second configuration, release the entire stack from the rocket into orbit such that the layers passively separate.

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.

The invention relates to a device for unfolding a rolled-up elongate hollow member having: at least one elongate hollow member which has two elongate shell member halves, and an unfolding mechanism which has a fixed base structure and a winding core which is rotatably supported on the base structure and on which the at least one elongate hollow member in a first state is rolled up and compressed and which by rotating moves and unfolds the elongate hollow member from the first state into an unrolled and unfolded second state so that an elongate hollow space is formed between the two shell member halves of the at least one elongate hollow member, wherein the at least one elongate hollow member has as a first end a hollow member root, via which the elongate hollow member is secured to the rotatably supported winding core, wherein the first shell member half of the at least one elongate hollow member is secured in the region of the hollow member root to the rotatably supported winding core, and the unfolding mechanism has an expansion mechanism which in the region of the hollow member root is in engagement with the second shell member half and which moves the second shell member half in the region of the hollow member root away from the rotatably supported winding core in order to expand the cross-section of the at least one elongate hollow member in the region of the hollow member root when the elongate hollow member is unrolled from the rotatably supported winding core.

NASA, ESA, and Japanese Space Agency (JAXA) have undertaken studies (e.g., “Lunar Ice-Trap ISRU Mining, Processing and Storage Infrastructure: An infrastructure that mines and breaks down lunar ice into oxygen and hydrogen fuel”) to determine likely sources of water and oxygen for human colonies on Mars or Moon. Some of these studies are university-level research through fund allocations for departmental research, or through student interest in space exploration. Other studies are conducted at national levels through space agencies and through privately funded space probes. One of these studies was executed by the JAXA determined the source of the lunar-ice on the Moon (from the Kaguya/ZELENE lunar probe). JAXA estimated that 90 metric tons of Earth's atmosphere escapes per day with oxygen ions reaching energies of between 1 keV and 10 keV.

Retrofittable satellite systems for an in-orbit host satellite comprising an enhancement module for adding a capability to the in-orbit host satellite, modifying the function of the in-orbit host satellite, and/or extending the function of the in-orbit host satellite. The in-orbit, retrofittable satellite system comprises a transfer vehicle for transferring the enhancement module from a first to a second location and a service vehicle for receiving the enhancement module from the transfer vehicle and installing the enhancement module on the in-orbit host satellite. In-orbit space situational awareness systems, comprising one or more in-orbit host satellites having one or more enhancement modules attached thereto, the enhancement modules comprising sensors such as satellite spatial location/position sensors, range sensors, navigation sensors, and/or proximity sensors for detecting other objects in-orbit, their location, speed, acceleration, orbital trajectory or the like, wherein the enhancement modules communicate to create a mesh network between the satellites.

A harmless low-consumption on-orbit continuous launch system includes a satellite platform, a launch apparatus and a plurality of CubeSats. The satellite platform carries the launch apparatus and dozens or hundreds of CubeSats, and is launched from a ground into an orbit for on-orbit operation. The launch apparatus is configured to store the plurality of CubeSats and provide power for on-orbit launching of each of the CubeSats. A solid working medium in the launch apparatus is activated by heating to undergo a phase change, and the activated solid working medium expands instantly and is converted into a high-pressure gaseous working medium. The high-pressure gaseous working medium does work to eject the CubeSats, such that the CubeSats obtain a speed increment. The CubeSats enter a transfer orbit towards different target spacecraft through the speed increment applied by the launch apparatus to perform a plurality of different on-orbit serving missions.

A space vehicle comprising an optical system having a field of view, the optical system comprising at least two optical elements spaced from one another along an optical axis, thereby defining an interior cavity; at least one control system comprising at least one physical element configured for performing function(s) for enabling operation of the vehicle; and at least one holding assembly for holding the at least one control system and comprising a folding mechanism configured to move between a folded position corresponding to an inoperative mode of the optical system, and a deployed position corresponding to an operative mode of the optical system, such that in the folded position, the control system is at least partially located in the interior cavity for stowage, and in the deployed position, the control system is located outside the interior cavity and outside the field of view of the optical system, allowing operation of the optical system.

In a method of facilitating flight operations, a payload is coupled to a spacecraft via a payload interface. The relative alignment of the payload and the spacecraft is dynamically adjusted (e.g., for thrust alignment) while the payload remains coupled to the spacecraft.

A method is provided for realigning or relieving mechanical stress in a spacecraft frame. The process includes providing a spacecraft which includes at least two frame subsections connected by a mechanical connector. The mechanical connector provides both a soft dock connection which mechanically connects the two frame subsections but allows relative movement between the two frame sections and a hard dock connection which mechanically connects the two frame subsections but does not allow relative movement between the two frame sections. Once in space, a controller causes the mechanical connector to transition from a hard dock connection to a soft dock connection, which is maintained for a predetermined time period to realign or relieve stress within the spacecraft frame. Thereafter, the controller causes the mechanical connector to transition from the soft dock connection back to the hard dock connection.