Multiple subsidiary small payloads are connected to standard mechanical and electrical interfaces provided by an expendable or recoverable modular mother satellite bus (MMSB) and launched into space as an assembly acting as a common carrier providing low unit launch costs for the attached subsidiary payloads and also providing a variety of electrical, pointing, and thermal control services for these payloads after reaching orbit. These services include but are not necessarily limited to controlled separation of free-flying satellites or re-entry vehicles, regulated electric power at a variety of voltages, telemetry, computer control, payload control via time delayed pre-programmed instructions, optional real-time payload control via direct radio communication or transmission through geostationary or other communication satellite links, time-driven or event-driven control logic, mass data memory, encryption and decryption of data and commands, payload pointing, augmented heat rejection, and interconnection between subsidiary attached payloads through the data bus.

Modular mother satellite bus for subsidiary payloads

An object mounted on a carrier constitute a rotationally free system such as a telescope on a space vehicle. A separation vector is directed from the center-of-mass of the carrier to the center-of-mass of the object. The object is rotated through a selected angle thereby defining a rotation vector. Simultaneously the object is translated so as to displace the object center-of-mass through a translation distance in a direction such that mathematically crossing the translation vector into the separation vector results in a further vector having the same direction as the rotation vector. A formula is provided for the translation distance in order that the object may be rotated without counter-rotation of the carrier.

Method and apparatus for reactionless rotation

A spacecraft is mounted in a cradle secured in the space shuttle by means of a suspension system including four cradle attachment members secured to the upper longeron bridge of the shuttle, in which provision is made for movably mounting one attachment member on the cradle to provide a component of movement substantially normal to the adjacent longeron bridge to accommodate misalignment between the longeron bridges and the attachment members without the need for removing the spacecraft and cradle from the shuttle.

Integrated spacecraft cradle and shuttle structure

Apparatus for use in gyroscopically ejecting a spacecraft supported in the open end of a spacecraft supporting cradle. The invention comprises a separable ejection restraint mechanism attached between the cradle and the spacecraft. The mechanism restrains the thrust force applied to the spacecraft for a predetermined time period in order to dissipate undetermined forces acting upon the spacecraft prior to the ejection thereof. The mechanism comprises a separable resilient portion and a releasable clamp portion coupled thereto. The resilient portion comprises a spring loaded anchor rod arrangement while the releasable clamp portion comprises a spring loaded split ball clamp arrangement. The invention also contemplates the use of a flexible carrier coupled between the spacecraft and the cradle. The invention acts as a tether connected between the cradle and spacecraft which acts to establish a determinant state of force on the cargo and eliminate unwanted ejection-related problems prior to cargo deployment. In addition, the release of a single tether employed as the sole cargo release initiator minimizes the possible imparting of uncontrolled momentum to the cargo due to structural deformation energy.

Payload depolyment from shuttle employing an ejection restraint device

A system for providing an interface between a launch vehicle and a payload of the launch vehicle includes payload integration points of the launch vehicle that remain unchanged relative to different payload configurations, such that a payload is configurable apart from the launch vehicle. The system makes it possible to de-couple payload installation and launch vehicle turnaround operations. Payloads can be configured off-line from launch vehicle processing, thus making it possible to accommodate unique payloads while reducing wear and tear on the launch vehicle.

System and methods for integrating a payload with a launch vehicle

A payload such as a spacecraft is deployed from launch vehicle with linear and angular velocity, using a structural arrangement for applying a tangential, single point ejection force to the spacecraft, in which, the single point ejection force and the spacecraft/launch vehicle reaction points enclose the spacecraft center of mass and center of percussion.

Alois Wittmann

Papers

Payload deployment from shuttle with linear and angular velocity