Embodiments of the present disclosure are directed to techniques for transitioning a spacecraft from a power-saving state to a power-consuming state at a time after launch of the spacecraft on a launch vehicle. Because the spacecraft can detect conditions for transitioning to the power-consuming state, commands received via an umbilical connection to the launch vehicle, or detecting the presence or absence of such a connection, is unnecessary, thereby removing several technical barriers to eliminating such umbilical connections altogether.

A satellite system may have a constellation of communications satellites in orbits such as highly inclined eccentric geosynchronous orbits and low earth orbits. To place satellites in inclined eccentric geosynchronous orbits, a series of launch vehicles may be launched. Each launch vehicle may be used to place a set of satellites, such as a set of three satellites, into a common orbital plane with distinct longitude of ascending node values. To place satellites in low earth orbits, a series of launch vehicles may be launched, each of which releases satellites in sequence from a stack of satellites into a common orbital plane. After desired separations have been produced between the released satellites, circularization procedures may be performed using the propulsion systems of the satellites to place the satellites into final orbit.

The disclosure provides a locking and separating mechanism capable of achieving sequential release of multiple satellites and a working method thereof. The locking and separating mechanism includes a satellite group, two sets of locking assemblies and two sets of separating assemblies, wherein the satellite group includes a plurality of satellite bodies, the locking assemblies are located above the satellite group, the locking assemblies are connected with a base, the two sets of locking assemblies are arranged symmetrically at the diagonal line of the satellite group, the two sets of separating assemblies are arranged symmetrically on the two opposite sides of the satellite group, the bottom parts of the separating assemblies are fixedly connected with the base, and the inner sides of the separating assemblies are connected with the satellite group; the separating assemblies include sliding rails, a plurality of sliding blocks, redundant steel wire ropes, fixed pulleys A, pulley support seats A, fixed pulleys B, separating motors and pulley support seats B; the plurality of sliding blocks are matched with the sliding rails, the sliding blocks are arranged in one-to-one correspondence with spherical structures on the satellite bodies, the locking assemblies compress the satellite group, and the separating assemblies separate the satellite bodies one by one. The mechanism is simple in structure, low in energy consumption, and convenient to install and store, and can achieve separation of multiple satellites one by one.

A spacecraft is disclosed having at least three flat side walls, at least one main communication antenna, including a radiating element having a central axis of radiation (AC-AC), a movable arm configured to move between a deployed position and a folded position, a reflector suitable for reflecting or receiving radiofrequency waves in a direction of emission (DE). The radiating element is fixed to a side wall so that the central axis of radiation (AC-AC) is arranged perpendicularly to the side wall, and the movable arm is shaped so that an offset angle (β) of between 25° and 65° is formed between the side wall and the direction of emission (DE), when the movable arm is in a deployed position.

A space vehicle system, a method of manufacturing a multiple space vehicle system, and a method of disposing space vehicles into Earth orbit are disclosed. The space vehicle system may include a first space vehicle including a first core structure with a first wall thickness. The space vehicle system may include a second space vehicle including a second core structure with a second wall thickness, the second wall thickness different from the first wall thickness, and the second core structure releasably attached to the first space vehicle in a stacked configuration.

The subject of the present invention relates to a floating platform (10) for launching a space rocket (100) from high altitude comprising a support structure (20) for suspending the space rocket (100) and which support structure (20) can be releasably connected to the space rocket (100), one or more hydrogen or helium filled balloons (30) fixed to the support structure (20), one or more rigid-walled tanks (12) and a compressor module (40) connected to the one or more balloons (30) and rigid-walled tanks (12) for delivering at least a portion of the hydrogen or helium stored in the balloons (30) into the one or more rigid-walled tanks (12), said one or more balloons (30) are dimensioned to lift the floating platform (10) and the space rocket (100) connected thereto, characterized in that the floating platform (10) comprises a hydrogen or helium-filled, preferably cigar-shaped rigid-walled balloon (35) which is releasably connected to the support structure (20) and secured to the top of the space rocket (100) and which is suitable for connecting the space rocket (100) to the support structure (20). The invention further relates to a method for launching a rigid-walled balloon (35) into space.

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.

An image-capturing plan creating device comprises an image-capturing plan creating unit and a condition establishing unit. The image-capturing plan creating unit is configured to create an image-capturing plan based on image-capturing target information related to image-capturing targets and of image-capturing device information related to image-capturing devices. The condition establishing unit is configured to establish conditions for recreating parts of the created image-capturing plan based on the contents of changes to the created image-capturing plan. The image-capturing plan creating unit is further configured to recreate the parts of the created image-capturing plan based on the established conditions.

Systems and methods are described for computing a trajectory of an object in space to a secondary body (M2) in orbit around a primary body to land on, or capture into orbit, or flyby M2 in a Three-Or-More Body Problem. A special plotting of sampled vectors from M2 are integrated backward using a Poincaré Map to form a “Swiss Cheese plot” to find a nominal trajectory. A funnel-like set of trajectories can be constructed along the nominal trajectory for navigation purposes. A global resonant encounter map over a sphere around M2 can be constructed to provide trajectories to, for example, flyby any point near M2, capture into orbit over any point about M2, land on any point on M2. Besides space exploration, there are many applications to the development of Cislunar space commercialization and colonization including asteroid capture and mining.

An earth to space transport method, system and apparatus. The earth to space transport system can include a main body; a plurality of storage tanks disposed in an inside of the main body, the storage tanks configured to store helium; one or more electric jet propulsion turbines coupled to the main body; a first inflatable cushion disposed at a top of the main body and a second inflatable cushion disposed at a bottom of the main body; a space capsule disposed above the first inflatable cushion; a power generator; and a rotor propeller. Such an earth to space transport system may be utilized to efficiently move humans, satellites and cargo from earth to space.