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.

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 method for determining, by reanalysis, a vibratory environment of a coupled vehicle/passenger system. A vehicle is subjected to external forces Fext and is coupled to a new passenger including multiple payloads (e.g., x=I, . . . N payload(s)). At the level of vehicle/passenger interfaces Ix, the method comprising a step DET1) for determining, based on reference interfacial acceleration γ.sub.x_ref of a reference passenger, the interfacial acceleration γ.sub.x′ relative to the new passenger.

A method for determining, by reanalysis, a vibratory environment of a coupled vehicle/passenger system. A vehicle is subjected to external forces Fext and is coupled to a new passenger including multiple payloads (e.g., x=I, . . . N payload(s)). At the level of vehicle/passenger interfaces Ix, the method comprising a step DET1) for determining, based on reference interfacial acceleration γ.sub.x_ref of a reference passenger, the interfacial acceleration γ.sub.x′ relative to the new passenger.

The present invention relates to an assembly apparatus for assembling components of spacecraft in space. The assembly apparatus comprises: a core platform (7); and a mobile platform (4) comprising an end effector configured to perform an assembly or manufacturing task. The mobile platform (4) is connected to the core platform (7) by a tether (6a). The core platform comprises a body and a coupling element (15a) connected to and extendable from the body (7) such that the coupling element (15a) may be spaced from the body of the core platform (7). The tether (6a) connects the mobile platform (4) to the body (7) via the coupling element (15a). The assembly apparatus further comprises an actuator configured to vary the length of the tether extending between the coupling element and the mobile platform to control the position of the mobile platform relative to the body of the core platform.

The invention relates to a separation device for a spacecraft or launcher. The separation device includes an inner housing divided into at least two portions locked to each other by a locking device in a locking position. The locking device is arranged to move between a locking position and a releasing position. The separation device includes an initiator including means for providing high pressure fluid to an expansion chamber when the separation device is switched from a locked state to a released state. The high pressure fluid in an expansion chamber moves the locking device from the locking position to the releasing position when the separation device is switched from the locked state to the released state. The separation device comprises a dampening arrangement arranged to attenuate a peak load when the separation device is switched from the locked state to the released state.

A load-decoupling attachment system is configured to secure to a primary structure. The load-decoupling attachment system includes one or more baffle tiers. One or more beams are coupled to the one or more baffle tiers. The one or more beams include a fore end and an aft end. A fore end coupling joint is configured to secure the fore end to a first portion of the primary structure. The fore end coupling joint includes a spherical bearing that allows the fore end to rotate in relation to the first portion of the primary structure. An aft end coupling joint is configured to secure the aft end to a second portion of the primary structure. The aft end coupling joint includes a slot that allows the aft end to linearly translate in relation to the second portion of the primary structure.

A load-decoupling attachment system is configured to secure to a primary structure. The load-decoupling attachment system includes one or more baffle tiers. One or more beams are coupled to the one or more baffle tiers. The one or more beams include a fore end and an aft end. A fore end coupling joint is configured to secure the fore end to a first portion of the primary structure. The fore end coupling joint includes a spherical bearing that allows the fore end to rotate in relation to the first portion of the primary structure. An aft end coupling joint is configured to secure the aft end to a second portion of the primary structure. The aft end coupling joint includes a slot that allows the aft end to linearly translate in relation to the second portion of the primary structure.

Methods and apparatus to methods and apparatus for performing propulsion operations using electric propulsion system are disclosed. An example launch vehicle includes a first space vehicle including a first core structure and a first electric propulsion system, and a second space vehicle including a second core structure and a second electric propulsion system, the second core structure releasably attached to the first space vehicle in a stacked configuration.