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.

Cell-based systems may interlock in a reconfigurable configuration to support a mission. Space systems, for example, of a relatively large size may be assembled using an ensemble of individual “cells”, which are individual space vehicles. The cells may be held together via magnets, electromagnets, mechanical interlocks, etc. The topology or shape of the joined cells may be altered by cells hopping, rotating, or “rolling” along the joint ensemble. The cells may be multifunctional, mass producible units. Rotation of cell faces, or of components within cells, may change the functionality of the cell. The cell maybe collapsible for stowage or during launch.

The present invention presents an adjustable speed reusable rocket with attachable wings system which is optimized for multiple purpose, such as space travel, high-speed long-distance travel between different addresses on earth, etc. The rocket system comprises an adjustable speed rocket propulsion system (rocket booster), an attachable wings system, a payload or space shuttle and may include slider wings system, etc. Firstly, the rocket system flies at a lift force caused by the attachable wings system at a low speed (e.g., Mach 0.5˜3). While the rocket system reaches relatively high altitude (e.g., 25,000 meters), at this altitude, the air density is extremely low comparing with the surface of earth at zero sea level, and then the attachable wings system may detach from the rocket system and fly to a designated location as a glider or by its engine on a runway, and the rocket system begins to fully initiate propulsion system and exert the payload to forward at a super high speed. Comparing with rocket fully initiate propulsion system from earth surface, the aerodynamic friction and the aerodynamic heat caused by air is extremely small and low.

The present invention relates to a single-board processor card configured for use in a 1U CubeSat payload form-factor multi-purpose architecture, including: a field-programmable-gate-array (FPGA) which is reconfigurable in flight; wherein a configuration memory of the FPGA can be scrubbed in flight to correct errors or upsets; and a radiation-hardened monitor (RHM) which provides radiation mitigation and system monitoring of the single-board processor card, and which reconfigures said FPGA during flight, scrubs the configuration memory, and monitors a health of the FPGA. The 1U CubeSat payload form-factor multi-purpose architecture includes a backplane having a plurality of slots, one of the plurality of slots which accommodates the single-board processor card, wherein the backplane routes signals to a plurality of standard-sized processor cards, interchangeably disposed in any of the plurality of slots.