Techniques for deploying a plurality of smallsats from a common launch vehicle are disclosed where a structural arrangement provides a load path between an upper stage of the launch and the plurality of spacecraft. Each spacecraft is mechanically coupled with the launch vehicle upper stage only by the structural arrangement. The structural arrangement includes at least one trunk member that is approximately aligned with the longitudinal axis of the launch vehicle upper stage, a plurality of branch members, each branch member being attached to the trunk member and having at least a first end portion that is substantially outboard from the longitudinal axis; and a plurality of mechanical linkages, each linkage coupled at a first end with a first respective spacecraft and coupled at a second end with one of the plurality of branch members, the trunk member or a second respective spacecraft.

An attitude control module is described for providing propellant-free attitude control and momentum desaturation to a spacecraft. The attitude control module includes at least one solar sail comprising a reflective surface for reflecting solar photons; and at least one robotic arm coupled to the at least one solar sail, said at least one robotic arm comprising at least 4 degrees of freedom for positioning and orienting the at least one solar sail relative to the spacecraft. A corresponding method for operating the attitude control module to unload excess momentum from a spacecraft is also described.

A satellite in orbit around a planetary body includes a bus and a drag flap coupled to the bus. The drag flap is used to increase the drag torque applied to the satellite. The bus may house sensors and actuators, such as a star tracker, a gyroscope, a reaction wheel, and a global position system (GPS) receiver to monitor the attitude of the satellite in response to the applied drag torque. The measurements from the sensors and actuators may be used to determine the drag torque applied to the satellite. An estimate of the atmospheric density may be then be determined based on the drag torque. Compared to conventional approaches, the satellite and methods described herein estimates the atmospheric density at comparable, if not better, resolution and bandwidth. The atmospheric density estimates may also be acquired in real-time using a cheaper, lighter, and smaller satellite.

A fastening device for assembly and quick release between objects includes a retaining device for an attachment element with a dockable portion. There is a plurality of separable parts held close together around the attachment element by at least one disengagable preloading mechanism. The preloading mechanism includes a link wound around the separable parts in order to hold them closed on the attachment element, which has the appearance of a ribbon wound in a spiral and has spring properties. The ribbon has a non-constant thickness, i.e. the thickness decreases from the inside towards the outside of the spiral. The thickness decreases with the angle of the spiral. It is manufactured as such, in its final form, by a manufacturing process employing either the removal of material by machining, or by aggregation of material.

A debris management system for use in space and a method of controlling space debris is disclosed. In one embodiment, the system includes: (1) a frame, (2) a plurality of material sections, coupled to the frame, that cooperate to form a material structure when deployed from the frame and (3) a plurality of microvehicles, coupled to the plurality of material sections, each one of the plurality including propulsion units configured to eject the each one relative to the frame and pull the plurality of material sections to deploy the plurality of material sections to form the material structure.

A joint for unfolding and locking a solar generator or a reflector, or other aerospace components that can be unfolded, includes two half joints, a joint axis, and a drive. A drive spring of the drive has a progressive characteristic curve over the unfolding angle of the two half joints, which increases over the unfolding, to compensate for a frictional torque that varies over the unfolding angle.

A flexible solar array for extraterrestrial deployment and a method of manufacturing such a flexible solar array are disclosed. A power generating layer, a durable layer, and an ultraviolet radiation blocking layer are disposed such that durable layer is between the power generating layer and the ultraviolet radiation blocking layer.

An apparatus includes a satellite in the form of a plate having a thickness being smaller than a width of the satellite. The apparatus also includes a plurality of contact points distributed on a face of the satellite, allowing for one or more additional satellites to be stacked upon the satellite.

Provided are devices for generating a desired gas or mixture of gases by thermally decomposing a gas-generating composition (e.g. a metal hydride or polymer) using the thermal energy generated by reaction of a heat-generating composition (e.g. a thermite mixture), and methods of making and using such devices. The devices include phase-changing separators, i.e. separators that at least partially melt, vaporize, or sublimate as a result of the thermal energy generated by the heat-generating composition.

A self-deployable array of panels includes a plurality of panels, each panel having a first compressed panel thickness state and a second expanded panel thickness state, and including a spring bias element biased to the second expanded panel thickness state. A plurality of locking hinges hingedly couple each of the panels to an adjoining panel. Each locking hinge is biased to an open position. A release of stored potential energy of both of the spring bias element biased to the second expanded panel thickness state, and the locking hinges biased to the open position causes the self-deployable array of panels to self-deploy from a folded stowed state. A single part offset locking hinge is also described.