A system for separating composites of a space launch vehicle, comprising non-pyrotechnic separating modules distributed between the composites to be separated and a device for activating the separation modules, which can generate the simultaneous activation of all of the separating modules. The activation device consists of a source of compressed gas, the outlet of which is connected to each separation module.

An electro-permanent magnet (EPM) for an electromagnetic mooring system (EMS) includes a low coercivity magnet surrounded by a reversible coil, and one or more high coercivity magnets surrounding the low coercivity magnet and the reversible coil. The reversible coil switches polarity of the low coercivity magnet to null the stronger, one or more high coercivity magnets. The nulling of the stronger, one or more high coercivity magnets allows for the EMS to connect and disconnect to an adjacent apparatus.

An electrical interface can include one or more connector devices that facilitate communication between components while they are connected. The connector devices can provide a secure communication and/or power link that resists infiltration by foreign object debris (“FOD”) as well as redundant electrical pathways. The connector devices can further provide mechanisms that are lightweight, are operable in a broad range of temperatures (e.g., low temperatures), accommodate displacement without loss of electrical continuity, and are of low resistance and induction. The connector devices can further provide a kickoff force upon separation of the components.

The invention discloses a modular satellite deployer system and method utilizing a novel geometric door configuration employing a novel geometry that permits any number or combination of satellites to deploy from a common sized satellite deployer. The satellite deployer system includes an enclosure. The satellite deployer system includes two or more satellites shaped to conform with the inside of the enclosure. The satellite deployer system includes multi segmented doors, door release mechanisms, and multi segmented ejector mechanisms. Each of multi segmented ejector mechanisms is capable of pushing a satellite of the two or more satellites out of the enclosure. Two or more satellites deploy from the enclosure in any desired sequence by selectively opening the multi segmented doors using the multi segmented door release mechanisms and the multi segmented ejector mechanisms.

A space vehicle system, a method of manufacturing a multiple space vehicle launch system, and a method to transmit a launch load between space vehicles during a launch are disclosed. The space vehicle system may include a first space vehicle including a first core structure, a second space vehicle including a second core structure releasably attached to the first space vehicle in a stacked configuration, a first solar array supported by the first core structure, the first core structure extending beyond a lower edge of the first solar array, and a second solar array supported by the second core structure, the second core structure extending beyond an upper edge of the second solar array.

In order to provide a temporary connection between two structure elements, such as two parts of a space launcher or of another type of spacecraft or aircraft, a connection device with controlled separation comprises a thermally breakable layer, two thermal containment layers, between which the thermally breakable layer is arranged, and an electrically conductive element arranged between the two thermal containment layers in such a way as to heat the thermally breakable layer using the Joule effect when an electric current passes through the electrically conductive element.

The disclosure relates to an improved satellite deployer system and method utilizing a novel geometric configuration employing a draft geometry between a satellite and a deployer that prevents jamming of a satellite during deployment while simultaneously reducing satellite deployment tipoff rates. The satellite deployer system includes a receptacle having the general shape of an extruded cylinder or polygon with draft. The satellite deployer system includes a satellite shaped to conform with the inside of the receptacle. The satellite deployer system includes a releasable mechanism to hold the satellite in the receptacle. The satellite deployer system includes an ejector mechanism that pushes or pulls the satellite out of the receptacle. The satellite is deployed from the launch vehicle by the ejector mechanism after the releasable mechanism is released.

A launch vehicle dispenser attach structure is disclosed. The launch vehicle dispenser attach structure includes a launch vehicle adapter, and a polygonal extruded cylinder comprising tapered side and an essentially closed end. The polygonal extruded cylinder connects to the launch vehicle adapter. The tapered sides and the closed end of the polygonal extruded cylinder provide mounting interfaces for connecting satellite dispensers. A mounting interface of the mounting interfaces includes a separation ring for transforming the launch vehicle dispenser attach structure into a free flying satellite. The launch vehicle dispenser attach structure is particularly useful for attaching multiple payload separation systems to launch vehicle.

A nose fairing (10) is a nose fairing coupled to a main body (12) of a rocket (11) so as to be separable from the main body. The nose fairing includes: a pair of fairing pieces (40, 50) that are separated after a predetermined time has elapsed since the rocket is launched, the pair of fairing pieces being engaged with each other and maintained in a coupled state before the pair of fairing pieces separate; a biasing structure (60) that biases the fairing pieces in a proceeding direction of the rocket to separate the fairing pieces from the main body; and a separating mechanism (13) that releases the engagement between the pair of fairing pieces and separates the pair of fairing pieces in such a manner that a distance of separation of one of the pair of fairing pieces from the main body is made longer than a distance of separation of the other of the pair of fairing pieces from the main body.

A Marman band clamp has multiple parts, such as two halves, that together make up a ring. The halves are joined by diametrically opposed mechanical connections, one of which is a mechanical release separably mechanically coupled ends of the parts (halves). The mechanical release may include an explosive bolt that is used to release the ends of the halves. The mechanical release may capture portions of the release at the ends of the ring halves after severing of the explosive bolt. A nut may be retained by an end of one of the halves by use of a retainer fastener, such as a pin, to prevent the nut from separating from the ring half end when the bolt is severed. This helps retain the pressurized gases between the severed part of the bolt longer, better using the energy from the pressurized gases to reliably separate the ends of the halves.