The present disclosure concerns a device for deploying a nanosatellite including a main structure mounted on a launching vehicle, a support frame carrying the nanosatellite, and a locking/unlocking structure. The locking/unlocking structure includes a first clamping element complementary to a second clamping element of the support frame, and an elastically deformable actuating element to allow, in a locking position, constrain the first clamping element to the second clamping element to retain the support frame to the main structure, and in an unlocking position, release the first clamping element from the second clamping element to release the support frame from the main structure causing it to be ejected.

A Hold Down Release Mechanism, HDRM, interface for attachment of a spacecraft to an adjacent structure of a launch vehicle or another spacecraft, wherein the HDRM interface is configured for forming part of a single or multi-point releasable attachment of the spacecraft to said adjacent structure. The HDRM interface includes first and second connector parts, wherein one of the first and second connector parts is fastened to said adjacent structure, and other is fastened to the spacecraft; wherein the first connector part has a tapered projection with a non-circular external surface; wherein the second connector part has a tapered recess with a non-circular interior surface configured for form-lockingly receiving the tapered projection, for enabling transfer of torsion and shear load between the first and second connector parts, when the tapered projection is inserted in the tapered recess and the first and second connector parts are pressed together.

Technology is disclosed herein for a spacecraft launch restraint and dispensing structure. The dispensing structure has a number of trusses and a central structure. When the trusses are in a support position, each spacecraft may be supported at one point by the central structure and at two points by one or more of the trusses. Therefore, each spacecraft may be supported at three points, thereby providing a stable support for each spacecraft. The spacecrafts do not touch each other and do not bear the weight of other spacecrafts. In a deployment position, the trusses extend away from the satellites and do not support the satellites; however, the satellites initially remain connected to the central structure. In the deployment position, the trusses are out of an ejection path such that the satellites can be ejected in a desired sequence from the central structure.

Stacked satellite dispensing systems are described herein. The disclosed systems have diagonal struts that stabilize satellite stacks horizontally and vertically without adding performance-reducing mass. The diagonal struts increase the number of bracing points and improve stability. The improved stability can allow for the satellite stack to be made heavier and taller, such as by having more satellites than a dispensing system with vertical struts. The diagonal struts, which provide the improved stability, can also allow for sub-stacks to be used. The sub-stacks include batches of satellites retained by the stacked satellite dispensing system. Therefore, the stacked satellite dispending system can release single satellites batches at once, rather than all the satellites at once.

A representative spacecraft system includes a launch vehicle elongated along a launch vehicle axis and having at least one stage carrying a corresponding rocket engine. The representative system further includes an annular support structure carried by the at least one stage and positioned to support a cargo spacecraft having a service module and a cargo module. The cargo module of the cargo spacecraft is positioned along the launch vehicle axis in a direction distal from the support structure, and at least a portion of the service module of the cargo spacecraft positioned within an annulus of the support structure

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.

Technology is disclosed for a dispenserless multi-satellite launch configuration in which multiple satellites are interconnected to form a composite beam structure that provides stability independently of the launch vehicle. When in the launch configuration, the satellites are formed into a bundle, where each satellite connects by one or more simple connector along the edges of its inner facing vertical side to the satellite adjacent on each side. This composite beam structure provides a stable launch configuration independently of the launch vehicle. Each of the satellites also has one or more connectors along the bottom edge of the inner facing vertical side allowing the bundle to be attached to a ring type launch vehicle interface. Once launched, the satellites can be dispensed by releasing the connector.

A satellite system may have a constellation of communications satellites in orbits such as highly inclined eccentric geosynchronous orbits and low earth orbits. To place satellites in inclined eccentric geosynchronous orbits, a series of launch vehicles may be launched. Each launch vehicle may be used to place a set of satellites, such as a set of three satellites, into a common orbital plane with distinct longitude of ascending node values. To place satellites in low earth orbits, a series of launch vehicles may be launched, each of which releases satellites in sequence from a stack of satellites into a common orbital plane. After desired separations have been produced between the released satellites, circularization procedures may be performed using the propulsion systems of the satellites to place the satellites into final orbit.

A method of releasing artificial satellites into Earth's orbit includes providing an orbital transport spacecraft able to move at orbital height and comprising a cargo area, hooking a plurality of satellites in said cargo area, housing said orbital transport spacecraft in a space launcher configured to reach an orbital height, releasing said orbital transport spacecraft at orbital height, when said space launcher reaches orbital height, by imparting a separation thrust to said orbital transport spacecraft, releasing satellites in sequence from the cargo area. The release of each satellite from the cargo area occurs in a respective predetermined direction and upon the orbital transport spacecraft has reached a respective predetermined position.

Provided herein are various improvements to launch vehicle payload systems, such as employed to launch and deploy secondary payloads into orbit. In one example, a system includes a fairing configured to encase a payload within an envelope of a primary fairing of a launch vehicle, and a mount system configured to adapt a mounting port for the payload to a mounting port associated with the launch vehicle. The system also includes a fairing door configured to be commanded open for deployment of the payload after the primary fairing has open.