| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 244172600 | With deployable appendage | 35 |
| 20080283670 | K-truss deployable boom system - An outer space deployable boom system is formed of a plurality of interconnected longeron members that are linked by diagonal members and batten frames. The diagonal members are arranged in a unique K-type configuration that provides a predictable and orderly folding dynamic as the boom system transitions from a stowed state to a deployed state. | 11-20-2008 |
| 20080290221 | Support Device For Elements on a Piece of Space Equipment With Flexible Deploying Arms - A device (D) is devoted to supporting a first (M1) and a second (M2) element of a piece of space equipment, such as a telescope for example. This device (D) comprises at least two deployable flexible arms (O | 11-27-2008 |
| 20090184207 | Synchronously self deploying boom - A deployable boom with adjacent panels hinged together typically in an end to end configuration. A first longeron is attached to at least two panels and a second longeron is also attached to at least two panels. Each longeron includes a self locking hinge between adjacent panels. | 07-23-2009 |
| 20100163684 | SELF OPENING HINGES - A self opening hinge comprises a tubular member with a set of circumferentially spaced blades extending longitudinally between opposite end portions. It can be folded by bending the blades to bring the end portions together and when released will naturally return to the straight condition under the spring action of the blades. The blade which will be located on the inside of the fold when the member is in its folded condition is configured with a convex circumferential curvature as viewed from the axis of the member when in its unfolded condition, namely reversed in curvature as compared with the other blades. In this way the stress on the inside blade when the member is folded is reduced as compared with a conventional hinge where all the blades follow a circular tube profile and are concave as viewed from the central axis. | 07-01-2010 |
| 20100282915 | Unique Device for Extending and Retracting Space Appendices - Device for deploying and retracting appendages of space systems comprising at least one support ( | 11-11-2010 |
| 20110147532 | Device for Deploying and Aiming Structural Elements in a Space Environment - A device for deploying and aiming structural elements designed to be placed in Earth includes at least one locking/unlocking device making it possible to deactivate the first coupling mode and to activate a second coupling mode allowing a portion of the device to be aimed at a target. The device uses: a plurality of structural elements linked together by articulations, the assembly forming an articulated arm linked to a payload via a root section; the articulations having at least one pivoting connection making it possible to have two consecutive structural elements pivot relative to one another; a motor making it possible to activate at least one pivoting connection of an articulation; and a system for coupling the articulations making it possible to link the pivoting of all of the structural elements comprising a first coupling mode. | 06-23-2011 |
| 20110204186 | DEPLOYABLE STRUCTURES HAVING COLLAPSIBLE STRUCTURAL MEMBERS - Deployable structures are disclosed having collapsible structural members that include a stowed configuration with a volume smaller than the expanded configuration. Such structures can include and/or be used for litters, bridges, support structures, solar arrays, and more. These structures can be easily transported to a new location and deployed from the stowed configuration into a larger functional structure. In some embodiments these structures can use one or more slit-tube longerons that can have two resting states: deployed and rolled. | 08-25-2011 |
| 20110210209 | SELF DEPLOYING SOLAR ARRAY - A deployable structure that may include a slit-tube longeron and a flat panel coupled with the slit-tube longeron. The slit-tube longeron may include a tubular member having a slit that runs along the longitudinal length of the slit-tube longeron. The deployable structure may be configured to couple with a satellite. And the deployable structure may be configured to transform between a stowed state and a deployed state where the tubular member is substantially straight when the deployable structure is in the deployed state, and the tubular member is wrapped around the satellite when the deployable structure is in the stowed state. | 09-01-2011 |
| 20120068019 | High Capacity Broadband Satellite - A high capacity broadband service is provided from an Earth orbiting satellite having a payload that includes multiple large antennas, the satellite having an inverted configuration when deployed on orbit. The satellite has an aft surface proximate to a launch vehicle structural interface, a forward surface opposite to said aft surface, and a structure disposed therebetween. In a launch configuration, two or more deployable antennas are disposed, undeployed, on or proximate to and forward of the forward surface; on-orbit, the payload is operable when the satellite is disposed with the aft surface substantially Earth facing while the forward surface is substantially facing in an anti-Earth direction. Each deployable antenna is disposed, so as to be Earth facing, when deployed, in a position substantially forward and outboard of the forward surface. | 03-22-2012 |
| 20120234982 | Retractable Plane Structure, and Satellite Comprising Such a Structure - A retractable plane structure includes an unfoldable membrane linked to N main assemblies of n main rods connected end-to-end by n−1 articulations respectively equipped with a deployment means, and further includes at least one intermediate assembly of n intermediate rods, less bulky than said main rods, connected end-to-end by n−1 articulations. | 09-20-2012 |
| 20120286100 | Device for Trapping Space Debris - A device for trapping space debris with at least one rope-like trap for space debris is provided. The trap includes an end piece configured for being wound around space debris or parts thereof. The rope-like trap is further configured in such a manner that upon contact with the space debris, it can generate a friction that is sufficient for towing the space debris. | 11-15-2012 |
| 20120325973 | Large Rigid Deployable Structures and Method of Deploying and Locking Such Structures - The invention is situated in the field of telecommunication satellites. A deployable structure with which such a satellite may be equipped and a method of deploying the deployable structure is provided. The deployable structure includes: a set of primary panels, a set of secondary panels, primary articulation systems, each primary articulation system enabling a primary panel to be caused to pivot relative to another primary panel about a primary axis, the primary axes being substantially parallel to the primary panels, and secondary articulation systems, each secondary articulation system being associated with a secondary panel and enabling said panel to be caused to pivot relative to another panel about a secondary axis parallel to said panels, the deployable structure being configured in such a manner that, in a deployed configuration, the front surfaces of the panels form a substantially continuous overall surface. | 12-27-2012 |
| 20120325974 | Deployable Structure Forming an Antenna Equipped with a Solar Generator for a Satellite - A deployable structure with panels forming an antenna equipped with a solar generator includes: a set of antenna panels each having a substantially rectangular useful surface, the antenna panels abutting each other on first sides parallel to each other, at least one photovoltaic solar panel, each photovoltaic solar panel abutting an antenna panel on a second side of said antenna panel perpendicular to the first sides, first articulation systems, each of said articulation systems enabling an antenna panel to be caused to pivot relative to an adjacent antenna panel about an axis substantially parallel to the first sides of said antenna panels, a second articulation system for each photovoltaic solar panel, each of said articulation systems enabling a photovoltaic solar panel to be caused to pivot relative to the antenna panel that it abuts about an axis substantially parallel to the second side of said antenna panel. | 12-27-2012 |
| 20140042275 | GOSSAMER APPARATUS AND SYSTEMS FOR USE WITH SPACECRAFT - Gossamer apparatus and systems for use with spacecraft may include a deployable gossamer apparatus. The deployable gossamer apparatus may include a plurality rib members and gossamer material extending therebetween and may be configured in a stowed configuration and a deployed configuration. The rib members of the deployable gossamer apparatus store potential energy used for deployment of the deployable gossamer apparatus. | 02-13-2014 |
| 20140117164 | MOTORIZATION SYSTEM WITH TORQUE SUITABLE FOR HINGE WITH CROSSED WINDING MEANS - A motorization device comprises two substantially parallel winding cylinders, at least one longitudinal link element to maintain a predetermined distance between the cylinders, and wound around said winding tracks, the link element consequently having a crossover point between the winding cylinders, two flexible tracks fixed to the winding cylinders and arranged facing and in contact with one another at the point of contact, a winding cylinder and flexible track assembly forming a fitting, a prestressing force being applied at the point of contact under the effect of the link element. The flexible tracks have a spiral form configured that the point of contact between the two flexible tracks in spiral form, situated between said winding cylinders, is offset relative to the crossover point, such that a torque dependent on the distance between the point of contact and the crossover point is applied, to provoke the mutual rotation of the fittings. | 05-01-2014 |
| 20140117165 | MOTORIZATION SYSTEM FOR HINGE WITH FLEXIBLE ROLLING TRACKS - A motorization device comprises two substantially parallel winding cylinders, at least longitudinal link element-forming winding means, the winding means being suitable for maintaining a predetermined distance between the winding cylinders and being wound around the winding cylinders, and at least two flexible tracks, a flexible track being fixed to each winding cylinder, the flexible tracks being arranged facing one another and having a point of contact, a prestressing force being applied at said point of contact of the flexible tracks under the effect of the winding means. The motorization device comprises elastic means arranged between each winding cylinder and the corresponding flexible track, the elastic means being configured so as to exert a radial compression force on each flexible track, normal to the surface of the flexible track at least at said point of contact. | 05-01-2014 |
| 20140263847 | SOLAR ARRAYS, DEPLOYMENT MECHANISMS THEREFOR, AND RELATED METHODS - Mechanisms for deploying a solar array include an elongated deployment member routed along a first panel, along an extension, and at least partially along a second panel. The elongated deployment member is configured to, upon retraction of the elongated deployment member by the deployment motor, move the extension into an extended position and rotate the second panel about a hub located at a distal end of the extension. Solar array assemblies include such a mechanism. Methods of deploying a solar array include retracting an elongated deployment member to rotate an extension into an extended position and further retracting the elongated deployment member to rotate a panel coupled to the extension approximately 360° about a hub of the extension. | 09-18-2014 |
| 20140291451 | AUTONOMOUS SPONTANEOUS DEPLOYMENT DEPLOYABLE MAST AND SATELLITE INCLUDING AT LEAST ONE SUCH MAST - An autonomous spontaneous deployment deployable mast includes at least one elementary structural unit having a longitudinal deployment axis X and two platforms parallel to a plane YZ orthogonal to the axis X. The elementary structural unit includes N stages stacked above one another parallel to the longitudinal deployment axis X, where N is greater than 1. Each stage includes at least three longitudinal flexible tape-springs, the N stages being fixed to one another two by two by means of connecting platforms parallel to the plane YZ and two contiguous lower and upper stages being offset angularly relative to each other by rotation about the deployment axis X, the tape-springs of the lower stage being interleaved between the tape-springs of the upper stage. | 10-02-2014 |
| 20150021440 | DEBRIS MANAGEMENT SYSTEM AND METHOD OF OPERATION THEREOF - A debris management system for use in space and a method of controlling space debris is disclosed. In one embodiment, the system includes: (1) a frame, (2) a plurality of material sections, coupled to the frame, that cooperate to form a material structure when deployed from the frame and (3) a plurality of microvehicles, coupled to the plurality of material sections, each one of the plurality including propulsion units configured to eject the each one relative to the frame and pull the plurality of material sections to deploy the plurality of material sections to form the material structure. | 01-22-2015 |
| 20150060605 | MECHANICAL SUPPORT RING STRUCTURE - A mechanical support ring structure for supporting a deployable space reflector antenna. The mechanical support ring structure is convertible from a folded state into a deployed state and includes a ring-shaped pantograph having a plurality of circumferentially arranged pantograph sections which are deployable for converting the mechanical support ring structure from the folded state into the deployed state, and a plurality of circumferentially arranged support rods, each pantograph section being arranged between a respective pair of support rods, wherein each pantograph section includes one or more pairs of pantograph rods which intersect crosswise with each other at a respective crossing position. | 03-05-2015 |
| 20150144740 | EXTENDIBLE BOOM - An asymmetric mast is disclosed that can be used for solar arrays. The asymmetric mast can have an asymmetry out of the plane of the solar blanket. The mast may include two or more booms that comprise slit tube longerons. In some embodiments, a single mast can be used with one or two solar blankets. | 05-28-2015 |
| 20150372374 | SPACE VEHICLE ELECTROMECHANICAL SYSTEM AND HELICAL ANTENNA WINDING FIXTURE - A space vehicle electromechanical system may employ an architecture that enables convenient and practical testing, reset, and retesting of solar panel and antenna deployment on the ground. A helical antenna winding fixture may facilitate winding and binding of the helical antenna. | 12-24-2015 |
| 20160001896 | SATELLITE WITH VARIABLE MASTER CROSS SECTION - A satellite comprises at least one first communication module, a repeater module, one or more antennas, at least one propulsion module and an avionics module, the repeater module comprising: a north first panel when the satellite is in an orbital position, an east second panel, a south third panel and a west fourth panel arranged respectively opposite the north first panel and the east second panel, the north panel and the south panel having widths Xmc | 01-07-2016 |
| 20160068281 | DEPLOYABLE MAST WITH SPONTANEOUS AUTONOMOUS DEPLOYMENT, AND SATELLITE COMPRISING AT LEAST ONE MAST OF THIS TYPE - A deployable mast with spontaneous autonomous deployment comprises at least one elementary structural block with a longitudinal axis of deployment X, the elementary structural block comprising two, respectively lower and upper platforms parallel to a plane YZ orthogonal to axis X, and N stages stacked on one another parallel to axis X, where N is more than 1, and where i is between 1 and N−1. Each stage comprises at least six flexible longitudinal connection arms which are articulated by tape springs, which arms are, in the deployed position, on planes parallel to axis X and are inclined relative to axis X, the N stages being secured to one another in pairs by means of connection platforms parallel to the plane YZ; two adjacent lower and upper stages are offset angularly relative to one another by rotation around the axis of deployment X. | 03-10-2016 |
| 20160114912 | MANIPULATION OF A SATELLITE IN SPACE - A system for manipulating a space object in space comprises an articulated structure, wherein the articulated structure comprises a single actuator configured to control, equally, the deployment of the structure in space, the gripping of the space object and the folding down of the articulated structure. Developments describe the use of a fixed supporting structure, a threaded rod, a tapped whorl guided by the threaded rod and a set of articulated bars held by pivot links at their interfaces on the tapped whorl and on the fixed supporting structure. Various mechanical configurations are described, notably gripping devices comprising rollers for locking and/or unlocking the space object by separation of the articulated bars. A method of regulation, of control and of adjustment of the manipulation is provided. | 04-28-2016 |
| 20160122041 | EXTENDABLE SOLAR ARRAY - A spacecraft system may include a storage portion (e.g., a first portion and a second portion) and a solar array apparatus that may be configurable in at least a stowed configuration and a deployed configuration. The solar array apparatus may include at least one solar array to collect incident radiation when the solar array apparatus is in the deployed configuration. In one or more embodiments, the at least one solar array may extend away from the storage portion. In one or more embodiments, the at least one solar array may extend between the first portion and the second portion. The solar array apparatus may also include an extendable boom operable to extend the at least one solar array apparatus from the stowed configuration to the deployed configuration. | 05-05-2016 |
| 20160144984 | RETRACTABLE DEPLOYABLE STRUCTURE USING A TAPE SPRING - A deployable structure comprises: a mount comprising a first point and a second point opposite and a third point, a storage reel able to rotate about an axis Z, a tape spring able to switch from a configuration in which it is wound about the axis Z in the storage reel into a configuration in which it is deployed along an axis X substantially perpendicular to the axis Z, the first and second points forming a double support with the tape spring to keep the tape spring in the deployed configuration. The third point is able to form a simple support with the tape spring, the storage reel is able to move with respect to the third point and the storage reel is pressed against the third point to guide the deployment of the tape spring. | 05-26-2016 |
| 20160159500 | DEPLOYABLE SOLAR PANEL ARRAY FOR SPACECRAFT - A solar panel assembly for a spacecraft includes a bracket and first and second booms each having a first end secured to the bracket and a second end extending away from the bracket. Each boom is formed from a plurality of tubes that telescope between a stowed condition nested within one another and a deployed condition aligned end-to-end with one another. A solar panel is secured to the first and second booms for receiving solar energy and converting the solar energy to electrical power. The solar panel has a stowed condition collapsed between the first and second booms and a deployed condition extending in a plane between the first and second booms. | 06-09-2016 |
| 20160201372 | HINGE WITH SPRING PRE-LOAD TRANSFER MECHANISM | 07-14-2016 |
| 20170233110 | Component Deployment System | 08-17-2017 |
| 20190144137 | SYSTEMS AND METHODS FOR SATELLITE SOLAR PANEL DEPLOYMENT | 05-16-2019 |
| 20190144138 | HOLD DOWN AND RELEASE MECHANISM FOR A DEPLOYABLE SATELLITE SOLAR PANEL | 05-16-2019 |
| 20190144139 | LARGE APERTURE UNFURLABLE REFLECTOR DEPLOYED BY A TELESCOPIC BOOM | 05-16-2019 |
| 20190144142 | SYSTEMS AND METHODS FOR SATELLITE SOLAR PANEL STOWAGE AND DEPLOYMENT | 05-16-2019 |
| 20190144143 | DEPLOYABLE SATELLITE SOLAR PANEL HINGE MECHANISM | 05-16-2019 |
