| Entries |
| Document | Title | Date |
|---|
| 20080265098 | Configuration and method of use of optimized cooperative space vehicles - A spacecraft system that includes a primary space vehicle and a secondary space vehicle, both of which are designed to optimize payload capacity and launch weight of the primary space vehicle. The primary and secondary space vehicles combine to form an on-orbit space vehicle capable of performing functions and maneuvers that exceed the physical capabilities of the primary space vehicle at the time of its launch. The spacecraft system is designed to minimize propellant containment-related disturbances while maintaining a standard level of functionality. The primary space vehicle is designed to be incapable of independently performing a propellant-intensive orbit change maneuver. Instead the primary space vehicle is designed to couple to a secondary space vehicle having propellant and thrust capability sufficient to perform an orbit change maneuver when the primary and secondary space vehicles are coupled. The secondary space vehicle may also be designed to deliver additional payload to the primary space vehicle. | 10-30-2008 |
| 20090008503 | SINGLE-WIRE TELEMETRY AND COMMAND - Communication between a payload services unit (PSU) and a payload unit utilizes a single-wire interface used to power the PSU as well as to communicate telemetry and command signals. A telemetry and command (T&C) system includes a payload unit configured to respond to a plurality of commands and generate a plurality of telemetry data, an embedded service module (ESM) within the payload unit, and a payload service unit (PSU) configured to generate the plurality of commands and receive the plurality of telemetry data. A single-wire interface is coupled between the ESM and the PSU and configured to provide power to the ESM, wherein the payload unit and PSU are configured to communicate the plurality of commands and the plurality of the telemetry data over the single-wire interface. | 01-08-2009 |
| 20090127398 | Modular spacecraft - A modular spacecraft incorporating a launch vehicle interface design that also functions as a berthing or docking interface for the spacecraft. The vehicle interface utilizes existing launch vehicle components to minimize cost and time to flight. In addition, the spacecraft is constructed from off-the-shelf launch vehicle components that enable a low cost construction as well as a secondary payload carrying functionality. | 05-21-2009 |
| 20090184206 | PARTICLE-FILLED WING-TO-BODY FAIRING - A wing-to-body fairing for reducing noise due to wing-to-body fairing vibrations in an aircraft, spacecraft, or vehicle may include a honeycomb center having a cavity which is at least partially filled with particle material. | 07-23-2009 |
| 20100001141 | Device for Controlling the Heat Flows in a Spacecraft and Spacecraft Equipped with Such a Device - A device for controlling heat flow in a spacecraft which always has the same face facing towards the earth, a pair of mutually parallel opposed North and South faces perpendicular to the North-South axis of the earth and two pairs of mutually parallel opposed East/West and Earth/Anti-earth faces, heat-dissipating or -transmitting equipment being provided on the internal walls of the North and South faces, this device comprising a plurality of heat pipes connecting the North and South faces of said craft to another pair of opposed faces of said craft and forming a heat-pipe loop in thermal-conduction contact with one another. | 01-07-2010 |
| 20100012787 | STRONG BONDED JOINTS FOR CRYOGENIC APPLICATION - A method and apparatus for strong bonded wide joints for cryogenic applications. In one advantageous embodiment, an apparatus may comprise a three-dimensional preform and a plastic matrix. The plastic matrix may be impregnated in the three-dimensional preform to form a softening strip that may be capable of remaining flexible at a temperature at which a gas may have a liquid form. | 01-21-2010 |
| 20100038490 | METHOD, SATELLITE, AND A SYSTEM OR AN ARRANGEMENT WITH AT LEAST ONE SATELLITE FOR DETECTING NATURAL OR ARTIFICIAL OBJECTS, AND THE USE THEREOF IN THE EXECUTION OF SAID METHOD - The invention relates to a method, a satellite, and a system or an arrangement with at least one satellite for detecting flying objects that are located in the vicinity of a planet, planetoid or similar celestial bodies. The invention further relates to the use thereof for carrying out said method and particularly to a constellation of LEO satellites (LEO=Low Earth Orbit) as an early warning of ballistic missiles, wherein said constellation comprises only satellites on equatorial orbits or orbits with low inclination. Satellite constellations in the low earth orbit (LEO) for missile detection are used for early warning of ballistic missiles, either by detecting the combustion phase of the flying object or by detection during the free-flight phase. The viewing direction of the sensors can be directed directly toward the earth or at an angle past the atmosphere. | 02-18-2010 |
| 20100224730 | PRESSURE-BASED SEPARATION APPARATUSES - Embodiments of separation apparatuses are generally described herein. Other embodiments may be described and claimed. In an embodiment, a separation apparatus is provided that is configured to be disposed between a first component and a second component associated with an aerospace vehicle. The separation apparatus comprises a sealed cavity filled with gas, and the separation apparatus is configured to expand based on a decrease in atmospheric pressure. This expansion is configured to separate the first component from the second component. | 09-09-2010 |
| 20110114792 | Sky station - Sky station structure comprises circle center core structure and circle outer Ring structure which comprises multi floor section levels. | 05-19-2011 |
| 20110114793 | ZERO-SHOCK SEPARATION SYSTEM - A system and corresponding method for a launch vehicle or spacecraft for releasably connecting a first body ( | 05-19-2011 |
| 20110127382 | Sky/space elevators - Sky/Space elevators structure comprises circle cylindrical structure provide multi floor Section levels. major center structure of center elevator provide transportations from Bottom cockpit levels to top cockpit floor levels. | 06-02-2011 |
| 20110210208 | TECHNIQUE FOR DE-ORBITING SMALL DEBRIS FROM THE NEAR-EARTH SPACE ENVIRONMENT - System and method for inducing rapid reentry of orbital debris including determining a spatial extent of the orbital debris, and deploying dust to the orbital debris to enhance the drag on the orbital debris. | 09-01-2011 |
| 20110278399 | PANEL TYPE ARTIFICIAL SATELLITE AND ARTIFICIAL SATELLITE SYSTEM THEREWITH - An artificial satellite system | 11-17-2011 |
| 20110315825 | ROTARY CASING OF SATELLITE ANTENA HAVING AN ANGLE ADJUSTABLE DISPLAY SCREEN - A rotary casing of a satellite antenna having an angle adjustable display screen includes a supporting arm, a hollow casing, a rotating means and an adjusting and controlling assembly. The casing has a panel provided with two keys and a top surface provided with a window. The rotating means is provided in the casing and controlled by the keys to drive the rotation of the supporting arm. The adjusting and controlling assembly is provided in the casing and includes a control unit and a display unit. The two keys are electrically connected to the control unit to drive the supporting arm. By this arrangement, the control unit receives an adjustment instruction inputted by the keys and transmits the instruction to the rotating means to generate a corresponding amount of rotation, while the control unit converts the instruction into a numerical value to be displayed on the display unit. | 12-29-2011 |
| 20120104175 | Space-based anti-missile defensive system (SAMS) - This invention presents a missile defensive system based on existing technology in which numerous non-explosive, meteor-like projectiles are launched in a shotgun manner from an orbiting space station at an enemy's missiles while on earth or in flight. Collateral damage is minimized with this system. This Spaced-based Anti-Missile System (SAMS) requires international cooperation. An International Orbital Treaty Organization (IOTO) is proposed. | 05-03-2012 |
| 20120234979 | METHOD AND SYSTEM FOR INSULATING FRAME MEMBER - The disclosure provides in one embodiment a method of insulating a structural frame member of a transport vehicle. The method comprises providing at least one flexible insulation member. The method further comprises providing at least two self-retaining foam insulation members. The method further comprises wrapping the flexible insulation member over a first end of a structural frame member of a transport vehicle and over at least portions of two sides of the structural frame member. The method further comprises positioning one self-retaining foam insulation member on each side of the wrapped structural frame member and in compression fit between each side of the wrapped structural frame member and adjacent structural frame members, such that the self-retaining foam insulation members impart one or more compression forces on the flexible insulation member to secure the flexible insulation member in place without use of any fastener device. | 09-20-2012 |
| 20120234980 | POLYGONAL SUPPORT STRUCTURE - A polygonal support structure is disclosed herein. The polygonal support structure has a plurality of rigid segments configured to be joined at longitudinal ends by a joint affixed to at least one end of each rigid segment. Each joint is configured to rigidly, rotatingly or hingedly join each rigid segment to an adjacent rigid segment to form the polygonal support structure. A plurality of flexible members are configured and disposed to provide tension between each joint and joints spaced two segments therefrom, in each direction, about the polygonal support structure. One or more joints may be configured to join and un-join two adjacent rigid segments and each rigid segment and each joint may be configured to enable stacking of rigid segment into a compact configuration for transport. In at least one aspect, a polygonal support structure may be configured to support assemblies in a substantially weightless environment. | 09-20-2012 |
| 20120241562 | Space Debris Removal - A method comprises removing space debris having a relatively low ballistic coefficient by hastening orbital decay of the debris. A transient gaseous cloud is created at an altitude of at least 100 km above Earth. The cloud has a density sufficient to slow the debris so the debris falls into Earth's atmosphere. | 09-27-2012 |
| 20120286097 | METHOD FOR CLEARING SPACE DEBRIS - Disclosed is a method for clearing space debris in geocentric orbit, wherein, in geocentric orbit, a spatial region having a greater resistive force than atmosphere in the geocentric orbit is provided, space debris passing through the spatial region is decelerated by the resistive force, and the decelerated space debris is dropped from the geocentric orbit. | 11-15-2012 |
| 20120286098 | STABILIZATION OF UNSTABLE SPACE DEBRIS - Disclosed herein, in certain embodiments, is a method of altering the stability of unstable space debris. In some embodiments, the method further comprises changing the orbit of the unstable space debris. | 11-15-2012 |
| 20120292448 | METHOD FOR FORMING A STRUCTURAL COMPONENT OF AN AIRCRAFT OR SPACECRAFT, AND FORMING DEVICE - In a method for forming a structural component of an aircraft or spacecraft a preform comprising at least one band is formed by means of braiding around a core. A severing cut is introduced at least in portions into the at least one band of the preform to form two band portions of the at least one band. The two formed band portions of the at least one band are then deformed into a predetermined shape by means of a deformation tool which can be guided along the severing cut. A deformation device is used to carry out the method. A structural component is produced by means of the method and/or the deformation device. | 11-22-2012 |
| 20130099059 | SATELLITE HAVING A SIMPLIFIED, STREAMLINED, AND ECONOMICAL STRUCTURE, AND METHOD FOR IMPLEMENTING SAME - The invention relates to a satellite having a structure that includes a circular launching interface ring and at least two main planar apparatus-holding walls that are substantially parallel to the axis of the ring and rigidly connected to one another and to the ring. Each wall directly bears on the ring by a base of the wall, and each wall is rigidly and directly attached to the ring by at least one somewhat point-by-point connection on at least one point or area of tangency or intersection with the base of the wall and the ring. | 04-25-2013 |
| 20130153709 | PROCESS AND APPARATUS FOR A VEHICLE THAT LEVITATES - A levitation system of a vehicle is provided. This system allows a vehicle to levitate and move in all directions. The vehicle can travel in Earth atmosphere. Also this system could be used in space for space travel allowing accelerations never reached before and cover large distances with great autonomy. If a miniaturization of the system is successful, then the system could be applied in a multitude of already existing transport systems, as a complement or as a principal source of movement. Although the purpose of this invention is to levitate and move a vehicle in a three dimensional space, the same system is perfectly applicable to move a vehicle in a two dimension space. The centrifugal force is applied in this system and an internal or external source of energy is necessary to allow the system to operate. | 06-20-2013 |
| 20130175400 | Extending the Schwarzschild Derivation to a Pseudo-Spherical Space-time - This invention explains what anti-matter and black holes really are and how they can be used in a space ship to achieve space travel. | 07-11-2013 |
| 20150048212 | UNSTEADY AERODYNAMICS MITIGATION FOR MULTI-BODY AEROSPACE APPARATUS - A multi-body aerospace apparatus includes a first aerospace body, a second aerospace body, and a flow separation member. The second aerospace body is attached adjacent to the first aerospace body with a gap disposed between the first aerospace body and the second aerospace body. The flow separation member is attached to the first aerospace body or to the second aerospace body. | 02-19-2015 |
| 20150367964 | SPACE VEHICLE CHASSIS - A modular space vehicle chassis may facilitate convenient access to internal components of the space vehicle. Each module may be removable from the others such that each module may be worked on individually. Multiple panels of at least one of the modules may swing open or otherwise be removable, exposing large portions of the internal components of the space vehicle. Such chassis architectures may reduce the time required for and difficulty of performing maintenance or modifications, may allow multiple space vehicles to take advantage of a common chassis design, and may further allow for highly customizable space vehicles. | 12-24-2015 |
| 20160129984 | STRUCTURAL COMPONENT AND METHOD FOR PRODUCING A STRUCTURAL COMPONENT - A structural component for reinforcing the fuselage of an aircraft or spacecraft is integrally formed and segmented into surface-like stiffening sections, whereby at least one stiffening section is formed as a rigid mesh section, and at least one stiffening section is formed as a solid section. | 05-12-2016 |
