Patent application number | Description | Published |
20080290222 | SPACECRAFT LOW TUMBLE LINEAR RELEASE SYSTEM - Systems and methods for releasing a spacecraft payload at a substantially constant velocity are disclosed. A linear actuator is used that includes a spring loaded and fluid filled chamber. The spring drives against a piston within the chamber that includes a control orifice that restricts the fluid flowing from one side of the piston to the other and results in a substantially constant damped motion of the piston. The piston drives a rod from the chamber that is attached to a capture device that holds a flange of the spacecraft payload. The capture device moves along a linear guide toward an open end. Spring loaded latches are held in a closed position by the side walls of the guide as the capture device moves. The latches release the flange as exit the open end of the guide. | 11-27-2008 |
20130299641 | Multiple Space Vehicle Launch System - A multiple space vehicle launch system that may be adapted to be disposed within a payload region of a launch vehicle fairing. The launch system may include a first space vehicle, a second space vehicle releasably attached to the first space vehicle and oriented relative to the first space vehicle such that, when placed within the fairing, a launch load of the first space vehicle is transmitted to and borne by the second space vehicle. In certain embodiments, the first and second space vehicles each may include one of an electrical propulsion unit and a hybrid chemical and electrical propulsion unit. Use of electrical or hybrid chemical and electrical propulsion units enables the second space vehicle to bear all or a significant portion of the launch load of the first space vehicle, thereby eliminating the need for additional support structure. | 11-14-2013 |
20140061386 | METHODS AND APPARATUS FOR PERFORMING PROPULSION OPERATIONS USING ELECTRIC PROPULSION SYSTEMS - Methods and apparatus to methods and apparatus for performing propulsion operations using electric propulsion system are disclosed. An example apparatus includes a frame, a power source coupled to the frame and a payload coupled to the frame, the payload to receive or transmit data. The apparatus also includes an electric propulsion system coupled to the frame. The electric propulsion system is to enable attitude control, momentum control, and orbit control of the apparatus. | 03-06-2014 |
20140103164 | SPACECRAFT PROPELLANT TANK MOUNT - A spacecraft having a primary structural frame and a propellant tank, in which the spacecraft may include a tank mount adopted to engage a portion of the propellant tank, the tank mount being configured to transfer launch loads directly from the propellant tank to a lunch vehicle interface ring. | 04-17-2014 |
20140110158 | CARBON FIBER SPACECRAFT PANEL WITH INTEGRAL METALLIC FOIL POWER RETURN - An aerospace structure that includes a composite member and a conductive element attached to the composite member wherein the conductive element is configured to conduct electricity across at least a portion of the composite member is provided. The aerospace structure may also include a power distribution system and the conductive element is a part of the power distribution system for the aerospace structure. | 04-24-2014 |
20140110531 | Spacecraft with Anti Nadir Battery Radiator - According to an embodiment, a satellite is disclosed comprising an anti-nadir panel having a first side and a second side. In one or more embodiments, the first side of the anti-nadir panel is mounted to an anti-nadir side of the main body of the satellite. The satellite further comprises at least one battery pack mounted to the second side of the anti-nadir panel, where at least one battery pack comprises at least one battery cell. | 04-24-2014 |
20140210416 | LIGHT-WEIGHT BATTERY APPARATUS - An apparatus comprises a first plurality of walls, a second plurality of walls, and a plurality of channels formed by the first plurality of walls and the second plurality of walls. The second plurality of walls meets the first plurality of walls at substantially right angles and forms a housing with a first side and a second side. The plurality of channels extends through the housing from the first side to the second side. The plurality of channels has a first plurality of openings on the first side. The plurality of channels has a second plurality of openings on the second side. The plurality of channels has substantially a same shape and is configured to receive a plurality of battery cells. | 07-31-2014 |
20140234566 | SPIRAL LAMINATED STRUCTURAL CONE AND MANUFACTURING METHOD - A cone-shaped composite article may include an inner sublaminate containing at least four unidirectional plies having an inner stacking sequence with fiber angles of 0, 90, −45, and +45 degrees such that the inner laminate has a quasi-isotropic layup pattern at any location on the inner laminate. The cone-shaped composite article may also include an outer sublaminate containing at least four unidirectional plies having an outer stacking sequence that is a mirror image of the inner stacking sequence. Each one of the unidirectional plies may be continuous along a ply arclength wrapping 360 degrees around the cone-shaped composite article and may have opposing ply ends terminating at a ply seam. | 08-21-2014 |
20140239124 | SPACECRAFT WITH OPEN SIDES - A spacecraft may include a module structure having a plurality of module sides. The spacecraft may include a central cylinder extending through a center of the spacecraft. The central cylinder may be the only closed cross-section extending along a longitudinal axis of the spacecraft. | 08-28-2014 |
20140239125 | MODULAR CORE STRUCTURE FOR DUAL-MANIFEST SPACECRAFT LAUNCH - A spacecraft may include an upper core structure or a lower core structure. The upper core structure may include an upper cylinder for supporting an upper spacecraft of a dual-manifest launch configuration. The lower core structure may include a lower cylinder for supporting a lower spacecraft with the upper cylinder mounted on top of the lower cylinder. The upper cylinder may have an upper cylinder inner diameter that may be substantially similar to the lower cylinder inner diameter. | 08-28-2014 |