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.

A secondary payload bridge for a payload adapter is disclosed and includes a body portion, plurality of payload ports, and a secondary payload port. The plurality of attachment points are connected to the body portion of the secondary payload bridge. The plurality of attachment points are configured to removably attach the secondary payload bridge to the payload adapter to allow for clockable positioning of the secondary payload bridge around a circumference of the payload adapter. The secondary payload port is connected to the body portion. The secondary payload port is configured to releasably attach to a corresponding secondary payload.

A spacecraft is disclosed, comprising a deployable spacecraft body (110) comprising a plurality of sub-systems (321-324) for controlling operations of the spacecraft, and a plurality of panels (101, 102) and a plurality of hinges (112-115) each connecting adjacent ones of the plurality of panels, the hinges being arranged to permit the plurality of panels to be folded into a stowed configuration and unfolded into a deployed configuration, wherein the plurality of sub-systems are fixed to and supported by one or more of the plurality of panels. By forming the body of the spacecraft from a deployable structure, the overall size of the spacecraft can be significantly reduced in the stowed configuration. In some embodiments, a plurality of the spacecraft in the stowed configuration can be combined into a modular spacecraft assembly prior to launch, with data and power connections between the plurality of stowed spacecraft being used to transfer power from, and data to, a payload monitoring unit on the launch vehicle.

A system for positioning at least one satellite in working orbit, characterized in that the system for positioning satellites in working orbit comprises: a first attachment device configured to attach a first satellite to the system for positioning satellites in working orbit; a main propulsion device with solid propulsion comprising a plurality of parallel solid-propellant cartridges; a secondary propulsion device which is re-ignitable; at least one position sensor configured to measure the position of said system; a monitoring unit connected to said at least one position sensor and which is configured to control a firing of the cartridges of the main propulsion device to move said system from a transfer orbit to a working orbit of the first satellite, said monitoring unit being further configured to control an opening of the first attachment device to separate said system from the first satellite.

A satellite dispenser includes a central tubular structure. The satellite dispenser also includes a plurality of satellites arranged around the central tubular structure. The satellite dispenser further includes a plurality of shear connectors coupling the central tubular structure and the plurality of satellites arranged together in shear continuity.

A reusable modular spacecraft has a spacecraft bus structure configured to support spacecraft subsystems, at least one interchangeable housing component configured to be interchangeably received and supported by the bus structure, and a wireless system configured to permit wireless communication between the at least one interchangeable housing component and spacecraft subsystems supported by the bus structure. In embodiments of the spacecraft, the wireless system includes a wireless hub and a wireless coordinator for wireless transmission of data between the at least one interchangeable housing component and the spacecraft subsystems. An electrical/power transfer interface unit is provided to the at least one interchangeable housing component for transferring electricity, power, data and/or providing thermal management and control.

A payload carrier assembly comprises a payload fairing (1) for protecting at least one payload (3) mounted on at least one payload carrier (20) of a launcher (2), comprising at least one separable fairing part (10, 11) that can be arranged on top of the launcher (2) around the payload (3) to be launched, wherein the payload carrier assembly further comprises at least one first transfer element (4), which is in contact with the at least one fairing part (10, 11) and which, in the assembled state, can be in contact with at least the at least one payload (3) and can transfer forces, applied to the at least one payload (3), to the at least one fairing part (10, 11) and vice versa.

A low Earth orbit neutral impulse defense and salvage (LEONIDAS) launch system includes a base having multiple flexible limbs including cross-bow limbs and recoil limbs. The LEONIDAS launch system also includes a solar powered mechanical drive system on the base configured to position the flexible limbs in desired positions and a rotary magazine on the base configured to hold multiple sub-vessels that are configured to perform different activities in space such as defense and salvage. The LEONIDAS launch system also includes one or more launch cables attached to the cross-bow limbs configured to impart the launch power to the sub-vessels during launch into low earth orbits.

Systems for satellite dispensing from a second stage of a launch vehicle are described. In an example, a satellite dispenser ring includes a circular ring, a vertical stanchion, and a truss. The vertical stanchion has an interface to couple with an adjacent satellite dispenser ring. The vertical ring is also coupled to a perimeter of the circular ring perpendicular to a place of the circular ring. A satellite attachment interface at an edge of the vertical stanchions couples and releases a satellite.

A stackable pancake satellite that is configured so that a plurality of the satellites can be stacked within a payload fairing of a launch vehicle. Each satellite includes sections that are folded or rotated together prior to launch, and unfolded or rotated away from each other when deployed. A first section is a satellite body having a first side that acts as a thermal radiator and a second side opposite the first side that includes an antenna. A second section includes one or more solar panels attached adjacent to the first side of the satellite body. A third section includes a splash plate reflector attached adjacent to the second side of the satellite body that reflects signals between Earth and the antenna. When deployed, the solar panels are pointed towards the Sun and the splash plate reflector directs the signals between the Earth and the antenna.