Launch vehicles with ring-shaped external elements, and associated systems and methods are disclosed. An aerospace system in accordance with a particular embodiment includes a launch vehicle having a first end and a second end generally opposite the first end, with the launch vehicle being elongated along a vehicle axis extending between the first and second ends, and having an external, outwardly facing surface. The system can further include an annular element carried by the launch vehicle, the annular element having an external, inwardly-facing surface radially spaced apart from, and extending at least partially circumferentially around, the vehicle axis. The annular element can have a first edge surface facing a first direction along the vehicle axis, and a second edge surface facing a second direction along the vehicle axis, the second direction being opposite the first direction. A propulsion system can be carried by the launch vehicle, and can have at least one nozzle positioned toward the first end of the vehicle to launch the vehicle. A controller can be in communication with the launch vehicle and programmed to direct the vehicle in the first direction during vehicle ascent, and in the second direction during vehicle descent.

An example of a satellite includes a first radiator panel with first heat-generating components attached to its surface and a second radiator panel with second heat-generating components attached to its surface. One or more actuators are configured to deploy the first and second radiator panels from a compact configuration in which the first and second radiator panels are overlapping to a deployed configuration in which the first and second radiator panels are non-overlapping.

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.

A spacecraft includes a main body, a set of panels attached to a side of the main body, and a retaining the set of panels adjacent to the main body. The single-point release device includes a heater for generating heat to expand a thermally sensitive material, a membrane-based actuator for providing a linear movement based on a phase change of the thermally sensitive material contained in the membrane-based actuator, and a release fitting and a release rod for retaining and selectively releasing a pin based on the linear movement of the membrane-based actuator. The membrane-based actuator is configured to push the pin through the release fitting.

A deployable structure comprises: a mount comprising a first point and a second point opposite and a third point, a storage reel able to rotate about an axis Z, a tape spring able to switch from a configuration in which it is wound about the axis Z in the storage reel into a configuration in which it is deployed along an axis X substantially perpendicular to the axis Z, the first and second points forming a double support with the tape spring to keep the tape spring in the deployed configuration. The third point is able to form a simple support with the tape spring, the storage reel is able to move with respect to the third point and the storage reel is pressed against the third point to guide the deployment of the tape spring.

A boom deployment mechanism is disclosed. The boom deployment mechanism may include a boom, a root plug, and a locking mechanism. In some embodiments, the boom may have a proximal end and a distal end. The boom may have a deployed configuration where the boom has a tubular shape with a slit that extends along the longitudinal length of the boom from the proximal end of the boom to the distal end of the boom. The boom may have a stowed configuration where the boom is flattened and rolled. In some embodiments, the locking mechanism may be configured to secure the proximal end of the boom to the root plug when the boom is in a deployed configuration.

The present disclosure describes a method of deploying an extensible boom from a housing. Sheets supporting respective arrays of photovoltaic devices are deployed substantially simultaneously so that a first sheet is deployed in a first direction from the housing and a second sheet is deployed in an opposite direction from the housing. Angular momentum imparted by deploying the first sheet is canceled by angular momentum imparted by deploying the second sheet. The housing can be part of a space satellite, such that the first and second sheets are deployed without causing the satellite to move out of its orbit.

A system includes a compound flexure having a frame, a flexure, and a post flexure. The frame has an axis, and the flexure is located within the frame. The flexure is movable relative to the frame, and the frame and the flexure form at least part of a monolithic structure. The post flexure extends along the axis and engages the flexure. The system also includes a device coupled to the flexure and configured to move with the flexure relative to the frame. The system further includes an actuator coupled to the flexure and configured to move the flexure and the device relative to the frame.

A radiative fin for a spacecraft is disclosed having an end fitting of heat conductive material, configured to be mounted on the spacecraft, a flexible radiative laminate, connected to the end fitting at one end and having an opposite free end, at least one pyrolytic graphite sheet, and at least one heat emission layer in contact with the pyrolythic graphite sheet on at least part of the surface of the pyrolythic graphite sheet, and a flexible rod, extending from the end fitting along at least part of a side of the flexible radiative laminate and being affixed to the latter. The flexible rod is adapted to occupy a folded position and a deployed position and to exert, while in the folded position, a deployment torque adapted to bring the flexible rod back to the deployed position.

A blocking diode board (“BDB”) for use with a rollable solar power module (“RSPM”) array is disclosed. The DBD includes a blocking diode, first flat electrical conductor, second flat electrical conductor, first tubular hook, and second tubular hook.