Networked initiation systems for hold-down and release mechanisms (HDRMs) are described. The systems include a control unit, a plurality of firing control units operably connected to and in communication with the control unit, wherein each firing control unit has at least one HDRM operably connected thereto, and wherein each firing control unit is individually addressable by the control unit over an interface bus to enable selective operation of the HDRMs operably connected to the firing control units.

A cube satellite deployer system having a body plate, a communication unit, a power unit, and a control unit. The body plate is adapted to be connected to a space arm assembly. The communication unit and the power unit are attached to the body plate. Each of the communication unit, power unit, and the control unit are in communication with one another. The body plate is also adapted to receive one or more cube satellite housings. The cube satellite housings are adapted to house and selectively launch one or more of the cube satellites that are housed by the cube satellite housings.

An assembly comprising a multiple payload set for a launch vehicle and a stiff and rigid ground support equipment. The multiple payload set comprising a plurality of payloads, wherein the plurality of payloads are interconnected via a non-self-supported connection structure before assembly of the multiple payload set to a dispenser body. Each payload comprises first attachment means attached to the non-self-supported connection structure, wherein the non-self-supported connection structure comprises second attachment means attached to the ground support equipment, for attachment of the multiple payload set to the dispenser body. The ground support equipment is attached to the multiple payload set via the second attachment means to reinforce and secure the multiple payload set to enable transport and maneuverability of the multiple payload set without jeopardizing the non-self-supported connection structure.

An example of an apparatus includes a spacecraft body and a solar array that is attached to the spacecraft body. In addition, a solar array spring element is configured to provide a force between the solar array and one or more components of a neighboring spacecraft in a stack of spacecraft.

Embodiments of the present invention include systems for launching primary or secondary payloads or actuating other launch vehicle or payload or instrumentation devices. The system includes an adapter assembly and at least one sequencer mounted to the adapter assembly. The sequencer includes: controller boards, each of the controller boards having a controller for controlling deployment of the payloads and data files; output ports coupled to the controller boards and configured to transmit signals from the controller boards to dispensers therethrough, deployment mechanisms containing the payloads, the adapter assembly having channels for accommodating the dispensers; and a detector coupled to the controller boards and adapted to detect an external signal and, in response to the external signal, to send an initiation signal to the controller boards. The system also includes at least one power supply coupled to the sequencer and adapted to provide an electrical power to the sequencer.

The disclosure concerns a satellite for inclusion in a satellite assembly comprising a plurality of satellites for deployment in space. The satellite comprising a satellite disengagement mechanism configured to separate the satellite from one or more adjacent satellites of the satellite assembly. The satellite disengagement mechanism comprises one or more disengagement coils configured to generate a repulsive electromagnetic force to separate the satellite from the one or more adjacent satellites.

A configurable spacecraft attachment and deployment system and a method of constructing a configurable spacecraft attachment and deployment system are provided herein. In one embodiment, the configurable spacecraft attachment and deployment system includes: (1) a connecting structure configured to secure at least one spacecraft to a launch interface, (2) an actuating assembly configured to constrain the spacecraft to the connecting structure before deployment thereof and release the spacecraft from the connecting structure when deployed, and (3) a deploying mechanism coupled to the connecting structure and configured to eject the spacecraft from the attaching structure, wherein the connecting structure, the actuating assembly, and the deploying mechanism are modular components and the connecting structure and deploying mechanism are selected to form the system based on parameters of the spacecraft.

A rideshare adapter for a launch vehicle (LV), a configurable-mass rideshare dispenser for a rideshare adapter employable with a LV, and a method of operating a configurable-mass rideshare dispenser for an LV are disclosed herein. In one embodiment, the rideshare adapter includes: (1) an annular peripheral wall that defines an interior of the rideshare adapter and (2) inner support walls, mechanically coupled to the peripheral wall, that are located within the interior and divide the interior into multiple rideshare dispenser compartments.

A configurable-mass rideshare dispenser for a launch vehicle (LV). In one embodiment, the rideshare dispenser includes: (1) a modular chassis having an LV mount configured to mount the modular chassis to the LV and an LV interface configured to receive a separation signal from the LV and (2) multiple internal mounts associated with the chassis and operable to mount at multiple candidate locations therein a rideshare payload, signal processing circuitry operable to provide deployment sequencing and commodities for the rideshare payload, and at least one additional mass object.

A cube satellite deployer system having a body plate, a communication unit, a power unit, and a control unit. The body plate is adapted to be connected to a space arm assembly. The communication unit and the power unit are attached to the body plate. Each of the communication unit, power unit, and the control unit are in communication with one another. The body plate is also adapted to receive one or more cube satellite housings. The cube satellite housings are adapted to house and selectively launch one or more of the cube satellites that are housed by the cube satellite housings.