A method for assembling devices on a satellite structure is disclosed including attaching the devices to a first face of a plate drilled with a through-hole provided with a fluid connector, on a second face of the plate, depositing a continuous peripheral bead of polymerisable adhesive composition and depositing a plurality of discontinuous and disjointed inner beads of polymerisable adhesive composition, pressing the second face of the plate against a continuous face of the structure, performing suction so as to create a pressure differential between the plate and the structure, at least partially polymerising the polymerisable adhesive compositions so as to form adhesive joints between the plate and the structure, and interrupting the suction.

A method for assembling devices on a satellite structure is disclosed including attaching the devices to a first face of a plate drilled with a through-hole provided with a fluid connector, on a second face of the plate, depositing a continuous peripheral bead of polymerisable adhesive composition and depositing a plurality of discontinuous and disjointed inner beads of polymerisable adhesive composition, pressing the second face of the plate against a continuous face of the structure, performing suction so as to create a pressure differential between the plate and the structure, at least partially polymerising the polymerisable adhesive compositions so as to form adhesive joints between the plate and the structure, and interrupting the suction.

[Problem] When configuring a device for storing and supplying fluid, each components such as vessels, valves/pipes and the like, are placed independently outside a vessel that stores the fluid, and even if these components are small, the volume of the area between the components cannot be effectively used because each of them occupies the surrounding area, and when the total size of the device is limited, it is difficult to ensure a sufficient volume of the vessel that stores the fluid. The present invention provides a design for a configuration of a mechanism consisting of components such as valves/pipes and the like, that functions for storing and exhausting the fluid inside the storage vessel to innovatively improve the volume usage efficiency of the device.

A jamming satellite avoidance method changes an orbital altitude for each of orbital planes with different normal vectors in a mega-constellation satellite group composed of 100 or more satellites, so as to avoid a jamming satellite controlled by a ground device that is different from a device that controls the mega-constellation satellite group. The jamming satellite is an artificial satellite that includes a propulsion device and adopts a nominal orbital altitude and a nominal orbital inclination at which the mega-constellation satellite group flies, and maintains an average orbital altitude and an average orbital inclination while operating the propulsion device irregularly, and is controlled by the ground device that is different from the device that controls the mega-constellation satellite group.

A jamming satellite avoidance method changes an orbital altitude for each of orbital planes with different normal vectors in a mega-constellation satellite group composed of 100 or more satellites, so as to avoid a jamming satellite controlled by a ground device that is different from a device that controls the mega-constellation satellite group. The jamming satellite is an artificial satellite that includes a propulsion device and adopts a nominal orbital altitude and a nominal orbital inclination at which the mega-constellation satellite group flies, and maintains an average orbital altitude and an average orbital inclination while operating the propulsion device irregularly, and is controlled by the ground device that is different from the device that controls the mega-constellation satellite group.

Technology is disclosed for a spacecraft launch restraint and dispensing structure. Stacks of spacecrafts may be arranged around a central post. The dispensing structure has primary tie-down mechanisms that axially clamp the stacks of spacecrafts when in a stowed position. Each primary tie-down mechanism may have a rod located between two adjacent stacks, such that the rod tensions two stacks. In a deployment position, the primary tie-down rods extend away from the stack such that an ejection path is cleared. The dispensing structure also includes secondary tie-down mechanisms that radially connect the spacecrafts to the central post. After the primary tie-down rods are moved to the deployment position, the secondary tie-down mechanisms still hold the spacecrafts. The spacecrafts may be deployed by issuing control signals to the secondary tie-down mechanisms when the primary tie-down rods are in the deployment position.

Technology is disclosed for a spacecraft launch restraint and dispensing structure. Stacks of spacecrafts may be arranged around a central post. The dispensing structure has primary tie-down mechanisms that axially clamp the stacks of spacecrafts when in a stowed position. Each primary tie-down mechanism may have a rod located between two adjacent stacks, such that the rod tensions two stacks. In a deployment position, the primary tie-down rods extend away from the stack such that an ejection path is cleared. The dispensing structure also includes secondary tie-down mechanisms that radially connect the spacecrafts to the central post. After the primary tie-down rods are moved to the deployment position, the secondary tie-down mechanisms still hold the spacecrafts. The spacecrafts may be deployed by issuing control signals to the secondary tie-down mechanisms when the primary tie-down rods are in the deployment position.

A support structure for a spacecraft is disclosed having a first side wall, a second side wall which is parallel to and opposite the first side wall, a third side wall attached to at least the first side wall, and a fourth side wall which is parallel to and opposite the third side wall; at least one interior panel attached between and perpendicular to the first side wall and to the second side wall, at least one first thermal coupling device bearing against the second side wall and attached to the interior panel, electronic devices arranged on and in direct thermal contact with at least a portion of the first thermal coupling device.

A disclosed spacecraft is provided with: an attitude control actuator configured to control an attitude of the spacecraft; an imaging device configured to receive an optical communication signal from another spacecraft; and an attitude controller configured to control the attitude control actuator, based on a position of the optical communication signal in an image obtained by the imaging device.

A thruster assembly, including a switch connected to a power source, a thruster, a propellant tank for storing and pressurising a propellant, and a propellant channel for guiding the propellant to the thruster. The thruster includes a space for receiving the propellant from the propellant channel, an electrically controlled heating element, a thruster body having a first thermal expansion coefficient, a valve component having a second thermal expansion coefficient, which is different than the first thermal expansion coefficient, inside the thruster body, and a nozzle, wherein the valve component includes a sealing surface closing the nozzle in a first temperature, and the electrically controlled heating element in response to actuation of the switch heats said thruster to a second temperature where the thermal expansion of the thruster opens the nozzle.