Raumschiff Raumfahrt die Technik auf über 10773 Seiten - Dr. Thorsten Schwerte Computer Verlag

Raumschiff Raumfahrt die Technik auf über 10773 Seiten
Raumschiffe, Satelliten, Bahnberechnungen und Artverwandtes in allen Ausführungen. Mit genauen Angaben über die mechanische Anordung, Explosionszeichnungen und alle Berechnungen. Hier finden Sie hochmodernes, aber auch klassisches. Verblüffend einfache ..
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Eine Kollektion von 895 original Patentschriften (ca. 10773 (!) DIN A4 Seiten druckbar). Nominalwert (auf Basis von 3,5 Euro pro Patent): über 3132 Euro*
Zu Ihrem Komfort, sind alle Patentschriften in einer Datenbank mit echtem Patentindex (c). Sie können in allen Titeln suchen, ohne einzelne PDF-Dateien öffnen zu müssen, wie das bei anderen Sammlungen gerne der Fall ist. Sie erhalten hier mehr als nur eine Pateninfo. Sie können aber auch durch ALLE Seiten schnell durchblättern, wenn Sie etwas suchen. Mit weniger sollten Sie sich nicht zufrieden geben. Wir geben Ihnen eine Updategarantie. Sollte eine Sammlung innerhalb von 6 Monaten nach Ihrem Kauf aktualisiert werden, erhalten Sie diese auf Anfrage kostenlos! Patentportfolios werden auf original Verlagsdatenträgern (CD oder DVD) ausgeliefert.
Ein Qualitätprodukt des Verlages Dr. Schwerte.
Raumschiffe, Satelliten, Bahnberechnungen und Artverwandtes in allen Ausführungen. Mit genauen Angaben über die mechanische Anordung, Explosionszeichnungen und alle Berechnungen. Hier finden Sie hochmodernes, aber auch klassisches. Verblüffend einfache und bizarr komplexe Konstruktionen. Ein Muss für jeden Raumschiffinteressierten. Eine Fundgrube für jeden Modellbauer und Techniker. Finden Sie hier alle Patente in Ihre unzensierten Vollständigkeit.
Wußten Sie, dass es aufblasbare Satelliten gibt. Finden Sie hier Strahlungsmessgeräte, die Sie leicht selbst nachbauen können. Sie lernen alles über Flugbahnberechnungen und Innovationen rund um die Raumfahrt.
Viele Ideen lassen sich auch leicht selbst verwirklichen, lassen Sie sich inspirieren. Damit Ihnen das gelingt, gibt es hier noch folgendes:
Ein Bonusbuch mit professionellen Techniken der großen Erfinder der Vergangenheit und Gegenwart erhalten Sie gratis zu Ihrem Patentportfolio (siehe unten).
In den Abbildungen unten sind nur einige Beispiele der sehr detailliert bebilderten und beschriebenen Systeme und Verfahren. Eine Patentschrift muss so ausführlich beschrieben sein, dass ein technisch Versierter diese nachvollziehen und auch nachbauen kann. Patentschriften sind immer die ersten Veröffentlichungen von Innovationen, oft lang bevor solche Artikel im Handel erhältlich sind. Ausserdem ist diese Patentsammlung ein unergründlicher Pool von innovativen Ideen für die eigene Anwendung (selbstverständlich dürfen diese Produkte in unveränderter Form ;-) nur für private, nicht kommerzielle Zwecke nachgebaut werden. Die ausführlich beschriebenen Gedankengänge der Erfinder schulen den eigenen Geist für Ihre vielleicht nächste eigene "Erfindung". Profitieren Sie von diesem Wissensvorsprung.
Normalerweise können es sich nur Firmen leisten umfangreiche Patentrecherchen, wie die hier angebotene, erstellen zu lassen. Die Zusammenstellung solcher Sammlungen in gut archivierbarem Format ist aufwendig und setzt kostenpflichtige Datenbankprogramme voraus. Manche amerikanische Firmen berechnen für die Recherche bis zu 3,50 Euro pro Patent! Unser Verlag bietet Ihnen hier diese Leistungen zu einem unschlagbar niedrigen Preis an. Sollte Ihnen ein Sie interessierendes Thema fehlen, so fordern Sie uns und wir erstellen Ihnen ein Angebot, zu dem Sie nicht "Nein" sagen können (allerdings nur für private und nicht kommerzielle Zwecke, für Firmenanfragen existieren andere Bedingungen (Anfragen erwünscht)).
Die meisten Patente weltweit sind in englischer Sprache verfasst. Das ist auch gut so, oder wollen Sie die Ausführungen eines japanischen Erfinders geniessen? Schulkenntnisse in English sind vollkommen ausreichend und die zahlreichen Abbildungen erleichtern den Nachbau und Ihre eigene "Forschung".
Als Bonus erhalten Sie ein eBook aus unserem Verlag "Kreativitätstechniken". Hier finden Sie die Techniken der Profis und können Ihre Produktivität zusätzlich steigern.
*(auf Basis von durschschnittlich 3,50 pro Patent, der Preis der Agenturen)
Die Quellen zu oben dargestellen Abbildungen befinden sich unter bzw. über den Bildern.
Damit Sie vorher wissen, auf was Sie sich einlassen listen wir zahlreiche Patente mit Titel. Folgende Patente sind in dieser Sammlung enthalten (Doppelnennungen sind verschiedene Patente! Ältere Patente vor 1975 haben im Index keinen Titel, sind aber im Volltext mit Titel enthalten):
Satellite constellations using nodally-adjusted repeating ground track orbits;De-orbit instrument package;Automated docking of space vehicle;Method for limiting interference between satellite communications systems;Hinge assembly for deploying the petals of a sectored mirror of an optical space telescope;Mitigation of angular acceleration effects on optical sensor data;Spacecraft radiator system and method using cross-coupled deployable thermal radiators;Constellation of spacecraft, and broadcasting method using said constellation;System for high efficiency spacecraft orbit transfer;System and methods for integrating a payload with a launch vehicle;Satellite charge monitor;Apparatus and methods for in-space satellite operations;Lox-compatible composite tank for aerospace applications;Balloon device for lowering space object orbits;Integrated glass ceramic spacecraft;Multi-crew modules for space flight;Artificial satellite with an orbit having a long staying time in a zenith direction, an orbit control method and a communication system therewith;System and method for return and landing of launch vehicle booster stage;Optical position measurement system employing one or more linear detector arrays;Method of providing protection against the effects of solar originating protons, so as to make it possible for a star sensor to be reconfigured, and an attitude control system implementing the method;Integral node tubular spaceframe;Spacecraft data acquisition and distribution interface;Deployable inflatable boom and methods for packaging and deploying a deployable inflatable boom;Payload deployment system with an internal cargo unit;Energy-absorbing connecting strut for use as a gearbox suspension strut for rotary wing aircraft;System for deploying the petals of a sectored mirror of an optical space telescope;High stability latch mechanism;Satellite system and method of deploying same;Attitude-acquisition methods and systems for controlled spacecraft attitude;Artificial satellite with an orbit having a long staying time in a zenith direction, an orbit control method and a communication system therewith;Method for observing and stabilizing electrodynamic tethers;System and method for controlling a space-borne propulsion system;Apparatus for observing and stabilizing electrodynamic tethers;Aircraft taxi planning system and method;Low energy method for changing the inclinations of orbiting satellites using weak stability boundaries and a computer process for implementing same;System, method and apparatus for searching geographic area using prioritized spacial order;Reusable module for the storage, transportation, and supply of multiple propellants in a space environment;Aircraft flight and voice data recorder system and method;Satellite commanding using remotely controlled modulation of satellite on-board telemetry parameters;Combined propulsion system intended for a spacecraft;Method for making a support base plate for an artificial satellite on a dispenser platform for a plurality of such satellites;Reusable space access launch vehicle system;Satellite communications system;Miniature spacecraft;Method for deploying an orbiting sparse array antenna;Satellite deployment structure;Air bag tether system comprising multiple segments cut in alignment with fabric warp of fill;Apparatus and method for altering the tension of a clampband;METHOD FOR PLACING PAYLOAD IN ORBIT BY MULTIFUNCTIONAL LAUNCH VEHICLE OF COMBINED SCHEME WITH CRUISE LIQUID ROCKET ENGINE SYSTEM (LRES), MULTIFUNCTIONAL LAUNCH VEHICLE OF COMBINED SCHEME WITH CRUISE LRES AND METHOD OF REFINING IT;Variable spacer for a separation system of a launch vehicle;Spacecraft methods and structures for enhanced service-attitude accuracy;Shock isolation system for spacecraft fairing;Virtually geostationary satellite array;Communication system, communication receiving device and communication terminal in the system;X33 aeroshell and bell nozzle rocket engine launch vehicle;Title Not Available.;Pointing device and an onboard pointing system;Title Not Available.;Spacecraft methods and structures with beacon-receiving field-of-view matched to beacon station window;Method and system for controlling the eccentricity of a near-circular orbit;Method and apparatus for supplying orbital space platforms using payload canisters via intermediate orbital rendezvous and docking;Deployable radiator for a space vehicle;Crewed on-orbit, returnable, and reusable space vehicle;Spacecraft for removal of space orbital debris;Title Not Available.;Artificial satellite with an orbit having a long staying time in a zenith direction, an orbit control method and a communication system therewith;Attitude sensor for spacecraft;Satellite constellation for measuring atmospheric wind speeds using doppler lidar;Graphical system and method for defining pilot tasks, patterns and constraints;Aircraft signal definition for flight safety system monitoring system;Heat transfer device;System and method for inhibiting corrosion of metal containers and components;Spacecraft configuration and attitude steering method for highly inclined orbit (HIO) communications;Reusable flyback rocket booster and method for recovering same;Attitude determination system and method with outer-loop gyro scale-factor non-linearity calibration;Supporting structure for a solar sail of a satellite;Dual coverage grid method;Non-geostationary orbit satellite constellation for continuous coverage of northern latitudes;Attitude control methods and systems for multiple-payload spacecraft;Passive cooler comprising dual elliptically-based cones;Device for suspending a payload in a launch vehicle;Spacecraft with integrated pulsed-plasma thrusters;METHOD FOR PLACING PAYLOAD IN ORBIT BY MULTIFUNCTIONAL LAUNCH VEHICLE OF COMBINED SCHEME WITH CRUISE LIQUID ROCKET ENGINE SYSTEM (LRES), MULTIFUNCTIONAL LAUNCH VEHICLE OF COMBINED SCHEME WITH CRUISE LRES AND METHOD FOR REFINING IT;Low energy method for changing the inclinations of orbiting satellites using weak stability boundaries and a computer process for implementing same;6-degree-of-freedom control apparatus for spacecraft;Inflatable satellite design;Modular spacecraft structure;Combination solar sail and electrodynamic tether propulsion system;Efficient high latitude service area satellite mobile broadcasting systems;Title Not Available.;Orbit transfer vehicle with support services;Crewed on-orbit, returnable, and reusable space vehicle;Fixed ground track satellite constellation and user terminal;Aerodynamic fairing;Spacecraft constellation formation keeping using inter-spacecraft distance measurement;Aerobraking orbit transfer vehicle;Electric orbit raising with variable thrust;Airborne turbulence alert system;Inflatable satellite;Device for supporting a payload in a launch vehicle of said payload;Satellite communications adapter for cellular handset;Supervisory control system for aircraft flight management during pilot command errors or equipment malfunction;Satellite communications system and method with real-time power-based flow control;Logistics module system and method;Method for limiting interference between satellite communications systems;Launch lock for spacecraft payloads;Inclined non-uniform planar spaced constellation of satellites;Satellite, satellite control method and satellite communication system;Deployable flexible airlock;Rocket engine with reduced thrust and stagable venting system;Universal flange joint for attaching;Thermal protection system especially for space vehicles;Rocket fairing and method of opening the same;PEAR composites for oxygen systems;Halogenated composites for oxygen systems;Space elevator;Technique for satellite constellation growth;Transportation of unqualified spacecraft or component to space;Redundant satellite system;Apparatus and methods for in-space satellite operations;Articulated set of sequentially opened solar generator panels;Embedded terrain awareness warning system for aircraft;Apparatus for spacecraft thermal management;Spacecraft with deployable panel array;Title Not Available.;Phase change material thermal control for electric propulsion;Method, apparatus and computer program product for estimating airplane attitude with reduced sensor set;Spacecraft sleeping berth;Round-trip orbital operation of a spacecraft;Satellite system and method of deploying same;System and method for adjusting the orbit of an orbiting space object using an electrodynamic tether and micro-fabricated field emission device;Propulsion device and method of generating shock waves;Method for maintaining the position of geostationary satellites;Constellation of elliptical orbit satellites with line of apsides lying in or near the equatorial plane;Spacecraft architecture for disturbance-free payload;Device and method for connecting two parts of a craft;Spacecraft attack and distress ejectable recorder;Active steering of an appendage on a spacecraft using piezoelectric actuators;Fly back booster;Controller and control method for satellite orbit-keeping maneuvers;Procedure for generating operational ballistic capture transfer using a computer implemented process;Single gimbal multiple aperture antenna;Closed-loop spacecraft orbit control;Deployable radiators for spacecraft;Separation system for missile payload fairings;Failure resistant multiline tether;Method and apparatus for operating satellites in orbit;Method and apparatus for satellite orbit interpolation using piecewise hermite interpolating polynomials;Artificial satellite with an orbit having a long staying time in a zenith direction, an orbit control method and a communication system therewith;Electrodynamic tether control;Method and apparatus for position and attitude control of a satellite;Satellite dispenser;High-energy to low-energy orbit transfer vehicle;Title Not Available.;Payload fairing with jettisonable mass acoustic suppression;Reusable, separable, structural connector assembly;Overhead system of inclined eccentric geosynchronous orbiting satellites;Failure resistant multiline tether;System and method of a ballistic capture transfer to L4, L5;Sun seeking solar array control system and method;Employing booster trajectory in a payload inertial measurement unit;Hybrid composites for oxygen propulsion systems;Method and apparatus for reducing acoustic coupling;Method of using dwell times in intermediate orbits to optimize orbital transfers and method and apparatus for satellite repair;System for emitting electrical charge from a space object in a space plasma environment using micro-fabricated gated charge emission devices;Configurable space launch system;Expendable launch vehicle;Device for controlled release of tension;Twin lobe spacecraft dispenser apparatus and method;Spacecraft magnetic torquer feedback system;Satellite, satellite control method and satellite communication system;Method for horizontal routing of an aircraft between two waypoints;Composite structure element with built-in damping;Reusable, separable, structural connector assembly;Method of simultaneously reducing inclination and eccentricity for geostationary orbit transfer;Low energy method for changing the inclinations of orbiting satellites using weak stability boundaries and a computer process for implementing same;Autonomous unified on-board orbit and attitude control system for satellites;Satellite system and method of deploying same;Attitude angle sensor correcting apparatus for an artificial satellite;Cyanate ester composites for oxygen containment;Photoemission based spacecraft charging sensor;Apparatus and methods for in-space satellite operations;Artificial satellite with an orbit having a long staying time in a zenith direction, an orbit control method and a communication system therewith;Overhead system of inclined eccentric geosynchronous orbitting satellites;Coordinatable system of inclined geosynchronous satellite orbits;Power sphere deployment method;Structure for the thermal insulation of satellites;Argument of perigee correction with longitude control for inclined, eccentric, geosynchronous satellites;Spacecraft with a microdynamic noise-free holding mechanism;Automated orbit compensation system and method;Yaw steering momentum system;Anti-friction release device;Spacecraft and appendage stepping methods that improve spacecraft attitude pointing and cancel solar array slew disturbances;Spacecraft having a dual reflector holddown for deploying multiple reflectors in a single release event;Eccentricity control strategy for inclined geosynchronous orbits;Spring component and support bearing for helicopter tail rotors and support structure for use in outer space;Spacecraft attitude control systems with dynamic methods and structures for processing star tracker signals;Space vehicular fly-by guidance method;Spacecraft with an environmentally released deployable structure;Integrated spacecraft control system and method;Cantilever, bi-level platform satellite dispenser;RF inspection satellite;Integrated translation tube assembly for a space module;Modular, producible, testable and serviceable spacecraft design;Planar hoytether failure resistant multiline tether;Photocatalytic coatings on optical solar reflectors to decompose organic contaminants;System for temporarily blocking the relative displacement of two bodies, following at least a preset direction;Alternate interconnection hoytether failure resistant multiline tether;Small satellite GEO-to-LEO orbit transfer vehicle;Spacecraft kernel;Anti-slosh liquid propellant tank for launch vehicles;Automated flight data management system;Apparatus for launching and deploying multiple satellites;Medium earth orbit communications satellite system;Robust autonomous GPS time reference for space application;Geostationary earth observation satellite incorporating multiple thruster liquid propellant apogee maneuver system;Radar interferometry device;Failure resistant multiline tether;Functionally and structurally modular parallelogram-shaped spacecraft;High-G compact folding wing;Satellite system and method of deploying same;Method and apparatus for flight parameter monitoring and control;Method and apparatus for generating orbital data;Low energy method for changing the inclinations of orbiting satellites using weak stability boundaries and a computer process for implementing same;Device for suspension of a payload in a space launch;Earth observation method, and system and observation satellite, operating ground system and program for the same;Universal communications system for space applications;Methods for using satellite state vector prediction to provide three-axis satellite attitude control;Solar array regulation and spacecraft pointing using flywheel energy storage with programmable voltage control;Modular spacecraft construction requiring no tools for assembly and disassembly;Method and liquid storage tank for minimizing permeation of liquid vapors through a tank dividing membrane;Adaptively positioned solar array;Deployable spacecraft lander leg system and method;Reusable, separable, structural connector assembly;Payload fairing with improved acoustic suppression;Efficient high latitude service area satellite mobile broadcasting systems;Deployed equipment modules for satellite architecture improvement;Aircraft navigational warning system;Title Not Available.;Method and a system for putting a space vehicle into orbit, using thrusters of high specific impulse;Vehicle launch system having an acoustic insulator;Method for low-fuel, computer-assisted control of any number of thrusters arranged on a spacecraft;Centrifugal gravity habitation torus constructed of salvaged orbital debris;Modular spacecraft bus;Adaptive mass expulsion attitude control system;Passive, multi-axis, highly damped, shock isolation mounts for spacecraft;Whole-spacecraft passive isolation devices;Satellite architecture with deployable electrical equipment;Evolvable propulsion module;Payload carry and launch system;Apparatus for spacecraft angular momentum control through the use of reflective thermal blankets;Control and telemetry signal communication system for geostationary satellites;Solar array control for electric propulsion system;Method for placing an artificial satellite on a geostationary orbit;Medium earth orbit augmentation of a global positioning system for global navigation;Radiator using thermal control coating;Utilizing high altitude long endurance unmanned airborne vehicle technology for airborne space lift range support;Payload control system and payload controller for outer space vehicle payloads;Failure resistant multiline tether;Designs of and methodology for inward or outward, and partially inward or outward turning flow hypersonic air-breathing and rocket-based-combined-cycle vehicles;Interactive fixed and mobile satellite network;Recoverable booster stage and recovery method;Spacecraft yaw pointing for inclined orbits;Structural layout for spacecraft including specialized compartment configuration;Free return lunar flyby transfer method for geosynchronous satellites havint multiple perilune stages;Method of steering a vehicle and vehicle allowing implementation of the method;Title Not Available.;Wheel speed control system for spacecraft with rejection of null space wheel momentum;Spacecraft dispensing system;Retention system for a detachable spacecraft capsule mounted on a spacecraft;Whole-spacecraft hybrid isolation system for launch vehicles;Subterranean target steering strategy;System and method for generating optimal flight plans for airline operations control;Miniature spacecraft;Process for identifying an incorrectly measuring sensor in a spacecraft;Independent launch lock mechanism;In situ method and system for autonomous fault detection, isolation and recovery;Coordinatable system of inclined eccentric geosynchronous orbits;Apparatus for retaining and releasing a payload;Non-geostationary orbit satelite constellation for continuous preferential coverage of northern latitudes;Low shock anti-friction release device;Title Not Available.;Free return lunar flyby transfer method for geosynchronous satellites;Electrodynamic tether and method of use;Method and a system for putting a space vehicle into orbit, using thrusters of high specific impulse;Delivering liquid propellant in a reusable booster stage;Electromagnetic, sliding space environment protection satellite door;Passive device for stabilizing the direction in which a spacecraft points;Elliptical orbit satellite, system, and deployment with controllable coverage characteristics;Method and apparatus for determining close approaches for earth-fixed launch trajectories;Satellite with improved heat sinkage;Solid-state spacecraft with minimal moving parts;Low energy method for changing the inclinations of orbiting satellites using weak stability boundaries and a computer process for implementing same;Flight event record system;Aircraft course correction for wind and fuzzy logic course intercept profile based upon accuracy and efficiency;Method and apparatus for propulsion;Autonomous orbit control with position and velocity feedback using modern control theory;Semiconductor antenna array and solar energy collection array assembly for spacecraft;Releasable payload shell for connecting a payload fairing, a payload and a payload propulsion unit;Satellite orbiting toward west in the equatorial plane and meteorological satellite system using the satellite;Cryogenic tanks for launch vehicles;Folding truss;System for attaching and separating satellites;High power spacecraft with full utilization of all spacecraft surfaces;Method of earth orbit space transportation and return;Satellite attitude sensor using thermal imaging;Interplanetary transfer method;Payload module;Method and a system for launching satellites on non-coplanar orbits, making the use of gravitational assistance from the moon;Method and apparatus for efficient GPS assistance in a communication system;Modular spacecraft payload support structure;Asymmetric open rosette constellations;White pigments stabilized against UV radiation by an oxidizing agent;Adjustable three dimensional focal length tracking reflector array;Aerodynamically actuated magnetic ascent vent cover;Direction detecting device for detecting direction of space vehicle;Constellation of non-geostationary satellites providing permanent coverage;Method for adding a geostationary component to a non-geostationary satellite network;Space launch vehicles configured as gliders and towed to launch altitude by conventional aircraft;Spacecraft with all-cryogenic electronics;Method for powering a spacecraft with extended-life battery operation;Coordinatable system of inclined geosynchronous satellite orbits;Apparatus and methods for in-space satellite operations;Spacecraft platforms;Passive lateral vibration isolation system for a spacecraft launch vehicle;Technique for the use of GPS for high orbiting satellites;Method and apparatus for early service using phased satellite depolyment;Actively controlled thermal panel and method therefor;Apparatus and method for combined redundant deployment and launch locking of deployable satellite appendages;Earth based spacecraft orbit and attitude control using a look-ahead thruster selection logic and magnetic torquers;Momentum unloading using gimbaled thrusters;Integrated launch and spacecraft propulsion system;Universal communications system for space applications;Modular spacecraft architecture;Dual ring array of satellites;System and method for attaching a structural component to an aerospace vehicle;Method and arrangement for keeping a geostationary satellite cluster on a dedicated position by employing an optical intersatellite link;Apparatus and method for aircraft display and control;Modular launch pad system;Multiple altitude satellite relay system and method;Object-transporting apparatus and method for transporting object;Passive axial vibration isolation system for a spacecraft launch vehicle;Method and a system for launching satellites simultaneously on non-coplanar orbits by using highly eccentric orbits and atmospheric braking;Modular spacecraft development process;Method and apparatus for pressurized feeding of liquid propellants to a rocket engine;Ellipitical satellite system which emulates the characteristics of geosychronous satellites;Satellite with east and west battery radiators;Method and system for autonomous spacecraft control;Autonomous craft controller system for landing craft air cushioned vehicle;Split shell spacecraft;Load vibration isolation apparatus;Embedded command module with matrix switch drive capability;Technique for the use of GPS for high orbiting satellites;Reducing satellite weight and cost;Functionally independent spacecraft module;Non-geostationary orbit satellite constellation for continuous coverage of northern latitudes above 25.degree. and its extension to global coverage tailored to the distribution of populated land masses on earth;Two-stage reusable earth-to-orbit aerospace vehicle and transport system;System for observation of geostationary satellites, use of a system of this kind and corresponding observation methods;Load isolator apparatus;Wave based satellite constellation;Multiple altitude satellite relay system and method;Method for adjusting stiffness and acoustic properties of an externally mountable spacecraft equipment module;Title Not Available.;Externally mountable spacecraft equipment module;Combination space station handrail clamp and pointing device;Device at the adapter of a launcher and a satellite carried by the adapter;Medium earth orbit communication satellite system;Satellite dispenser;Artificial satellite communication system;Tilting adaptor for the carriage of several payloads on the same launcher;Precision deployable boom assembly;Method of controlling a plurality of satellites;Method and system for rapidly assembling a launch vehicle;One piece spacecraft frame;Integrated cargo carrier for space applications;Launch vehicle with engine mounted on a rotor;Modular payload arrangement;Spacecraft with large east-west dimensions;Universal communications system for space applications;Device and method for equalizing heat dissipation between multiple radiators on a spacecraft;Method for replacing failing satellites in a satellite communication system;Salvage hardware apparatus and method for orbiting objects;Title Not Available.;Title Not Available.;Method and apparatus for a satellite station keeping;Method and system for formationkeeping between orbiting spacecraft by varying their ballistic coefficients;Dual function deployable radiator cover;Variable length mission-configurable module for space transportation vehicle;System and method for the construction of spacecraft structures;Temperature control for spacecraft inertial control unit;Elliptical orbit satellite, system, and deployment with controllable coverage characteristics;Satellite exclusion zone viewing and control system;Dual fault tolerant actuator control system;Satellite assembly having modular common bus components;Joint for a cantilever arm on a satellite;Self-powered horizon crossing indicator;System and method for deploying multiple probes;Slotted nut type releasing device for microsatellite ejector;Modular, independent subsystem design satellite bus and variable communication payload configurations and missions;Spacecraft with integrated array of solar cells and electronically scannable antenna;Launch mount pedestal and umbilical mast;Payload housing and assembly joint for a launch vehicle;Heat transport system for spacecraft integration;Method and apparatus for coupling space vehicles;Multicontact spacing control device;Precision alignment and movement restriction safeguard mechanism for loading multiple satellites into a launch vehicle;Artificial satellite equipped with aerodynamic orientation rudders;Aperture door and calibration source for spacecraft remote sensing devices;Constant sun angle transfer orbit sequence and method using electric propulsion;Unlockable connection device;Wave energy beaming and holograph tracking for power generating spacecraft platforms;Space vehicle and method;Title Not Available.;Satellite system using equatorial and polar orbit relays;Deployment hinge apparatus;Elliptical orbit satellite, system, and deployment with controllable coverage characteristics;Space vehicle apparatus including a cellular sandwich with phase change material;Methods and apparatus for reusable launch platform and reusable spacecraft;Electrically conductive black silicone paint having spacecraft applications;Actively controlled damper;Method for re-orbiting a dual-mode propulsion geostationary spacecraft;Containment assembly for spin table;Inflatable torus and collapsible hinged disc spacecraft designs for satellite communication system;Satellite cellular telephone and data communication system at an inclined orbit;Encapsulating service module for emergency descent vehicles;Space launch vehicles configured as gliders and towed to launch altitude by conventional aircraft;Spacecraft structure and method;Multisatellite distributor for launcher;Thermal blanket joining tape;Space vehicle dispenser;Spacecraft shield;Optimal transfer orbit trajectory using electric propulsion;Elliptical orbit satellite, system, and deployment with controllable coverage characteristics;Satellite fueling system and method therefor;Steered perigee velocity augmentation;Descent, travel, and protection apparatus, method of making and using same;Two stage launch vehicle and launch trajectory method;System and method for deploying multiple probes;High performance anti-weather protection system for space shuttles and launching vehicles;Satellite telecommunications and remote sensing system based on the use of short-period sun-synchronous elliptical orbits;Medium-earth-altitude satellite-based cellular telecommunications;Space game floater apparatus;Launch vehicle system;Satellite orbit maintenance system;Modular communication satellite;Worldwide satellite telephone system and a network coordinating gateway for allocating satellite and terrestrial gateway resources;Satellite having a stackable configuration;Spacecraft with gradual acceleration of solar panels;Multi-mission spacecraft bus having space frame structural design;Method for extending the useful life of a space satellite;Satellite and method to place this satellite in orbit by gravitational assistance;Apparatus for orbit control of at least two co-located geostationary satellites;Electronic avoidance configurations;Spacecraft structure and method;Disturbance compensation system for a camera on board a spacecraft;Tuneable rotating unbalanced mass device;Method for attaching metallic tubing to nonmetallic pressure vessel, and pressure vessel made by the method;Medium-earth-altitude satellite-based cellular telecommunications;Medium-earth-altitude satellite-based cellular telecommunications system;Method for producing extreme microgravity in extended volumes;Method for making nonmetallic pressure vessel with integral propellant management vane, and pressure vessel made by the method;Device for coupling at least two spacecraft and use of the device for repairing tether damage;Spacecraft adapter and dispenser;Space debris clearing device;Inflatable rescue device;Optical solar reflector and mounting method;Spacecraft berthing mechanism;Space transport architecture and method for robotic planetary operations;Suspension system for gimbal supported scanning payloads;Device for holding an object onto a support and subsequently separating it therefrom in a controlled sequence;Technique for dispensing earth satellites into multi-planar orbits;Spacecraft designs for satellite communication system;Spacecraft system;Thermal control arrangements for a geosynchronous spacecraft;Space-based tethered phased-array antenna;Device for filtering vibration, and a fixing system comprising a plurality of such devices for fixing a load on a support;Low-cost shuttle-derived space station;Multiple application paraboloid spacecraft structure;Active control of vibration;Low cost, selectable configuration spacecraft;Spacecraft-to-launch-vehicle transition;Attachment device;Engine protection system for recoverable rocket booster;Apogee at constant time-of-day equatorial (ACE) orbit;Spacecraft assembly with misalignment tolerant fasteners;Methods and arrangements tailoring aerodynamic forces afforded by a payload to reduce flight loads and to assist flight control for the coupled system;Electron gun device for controlling the potential of a body in space;Stage separation mechanism for space vehicles;Multi-mission spacecraft bus having space frame structural design;Atomic oxygen protective coating with resistance to undercutting at defect sites;Battery thermal control arrangement;Multiaxis vibration isolation system;Spaceship propulsion by momentum transfer;Atmospheric ultra-violet laser ozonogenesis;High altitude launch platform payload launching apparatus and method;Integrated system and method for assembling, and then transporting and supporting a launch vehicle;Solar array output regulator using variable light transmission;Modular mother satellite bus for subsidiary payloads;Protective enclosure apparatus for magnetic propulsion space vehicle;Precision alignment and mounting apparatus;Chain driven, rail guided payload deployment system;No-shock separation mechanism;Passive nonlinear interface strut (PNIS);Space transfer vehicle and integrated guidance launch system;Space station trash removal system;Patch for radiative coolers;Outer space solar energy collection system;Arrangement for attach, quick disconnect and jettison of rocket booster from space vehicle core;Protective barriers;Plasma plume MHD power generator and method;Solar powered system for a space vehicle;Device for jettisoning a payload from a spacecraft;Multi-position support structure connecting a payload to a booster rocket;Modular solid-propellant launch vehicle and related launch facility;Multi-use launch system;Ablative shielding for hypervelocity projectiles;Mobile rocket service tower;Title Not Available.;Integrated aerospike engine and aerobrake for a spacecraft;Method and apparatus for deploying a satellite network;Extraterrestrial transportation apparatus and methods;Locking device for a band or the like, subject to a tensile force;Title Not Available.;Space transfer vehicle and integrated guidance launch system;Antenna pointing equipment;Statite: spacecraft that utilizes sight pressure and method of use;Process of launching a capsule into space and corresponding launching means;Space launcher and method for launching objects into space;Geostationary earth observation satellite incorporating liquid propellant apogee maneuver system and hollow antennas;Pyrotechnic removal of a radome cover;Rapid re-targeting, space-based, boresight alignment system and method for neutral particle beams;Thermally isolated variable diameter deployable shield for spacecraft;Orbital systems for cislunar travel;Modular space station;Modular mother satellite bus for subsidiary payloads;Barrier for scattering electromagnetic radiation;Recharge device, particularly for drive mechanisms for extending and withdrawing operative members of a space vehicle;Advanced survivable radiator;Launch vehicle with reconfigurable interstage propellant manifolding and solid rocket boosters;Integrated launch and emergency vehicle system;Launch vehicle with interstage propellant manifolding;Access door pallet;Method and apparatus for reactionless rotation;Front end structure of a booster rocket mounted on the main body of a launcher;Multistage launch vehicle employing interstage propellant transfer and redundant staging;Jack screw payload deployment system;Title Not Available.;Orbital debris processor and method therefor;Geostationary satellite system;Multiple access communication system;Device for overcoming the problem of crew safety during a spacecraft launch and improve the joints connecting the segments of the solid rocket booster;Micro-g neutral platform for space travel missions;Method of providing a lunar habitat from an external tank;Method of delivering lunar generated fluid to earth orbit using an external tank;Measurement of mass of fluid in a container;Projectile delivery system;Modular space structure;Lunar radiator shade;Method and apparatus for mitigating space debris;Liquid propellant supply device for spacecraft adapted to predict the end of its service life;Load limiting energy absorbing lightweight debris catcher;Method of placing a geostationary telecommunicaiton satellite in orbit;Hypervelocity impact shield;Turbulent droplet generator with boom mounted pitot pump collector;Temporary linking device, especially for an artificial satellite lengthening piece, and method to free such a link;Spaceship to harness radiations in interstellar flights;Over-the-horizon targeting system and method;Spacecraft design enabling the flat packing of multiple spacecraft in the launch vehicle;Modular payload transport and operating device for space vehicle;ORU latch;Inflatable foldable structure and method of manufacturing foldable structures;Mechanical stabilization system having counter-rotating rotors which are separate;Payload adapter ring;High efficiency heat exchanger;Petal deployable radiator system for spacecraft;Satellite system having variable configuration;Stratospheric Welsbach seeding for reduction of global warming;SRB and external tank stabilizing system;Electronic sun incidence avoidance device;Orbital debris sweeper and method;Apparatus for filling cryogenic engines of a launcher with automatic separation on lift-off;Process for data transmission by means of a geo-stationary satellite and at least one sub-satellite;Method for improving atomic oxygen resistance;Fuel tank for aggressive liquid fuels;LDR centrifugal collector apparatus;Protection for spacecraft;Spacecraft structure for orbital assembly and servicing;Vehicle shield;Fixing system enabling a structure to be rapidly docked for securing thereon an element in a detachable way;Soft ride method for changing the altitude or position of a spacecraft in orbit;Method and apparatus for orbital debris mitigation;Tether power generator for earth orbiting satellites;Heat resistive wall assembly for a space vehicle;Raked circular-cone aerobraking orbital transfer vehicle;Method for cleaning spacecraft critical surfaces;Propellant remaining gaging system;Sample levitation and melt in microgravity;Satelite transfer vehicle;Aerodynamic braking system for recovering a space vehicle;Active damping of spacecraft structural appendage vibrations;Earth-to-orbit vehicle providing a reusable orbital stage;Multipurpose modular spacecraft;Prefabricated space station;Flat end cap module for space transportation systems;Manipulator system with small arm removably attachable at points along large arm;Passive zero-gravity leg restraint;Payload deployment method and system;Tetrahedral multi-satellite continuous-coverage constellation;Spacecraft design enabling the compact nesting of multiple spacecraft in the launch vehicle;Redundant seal for pressure vessels;Modular space vehicle for deep space applications;Dual mode vibration isolator;Method and apparatus for atomic beam irradiation;Hatch cover;Rate controllable damping mechanism;Expandable radiator;Modular spacecraft system;Survivable pulse power space radiator;Fluid lock;Orbital system including a tethered satellite;Aerobraking orbital transfer vehicle;Hermetic feedthrough change-out module device and method for use in a pressurized spacecraft hull;Satellite continuous coverage constellations;Combined space vehicle fuel cell and space station structural building component;Horizontal-takeoff transatmospheric launch system;Space launch vehicle;Electromagnetic transportation system for manned space travel;Space station;Pad apparatus for supporting a payload in a cradle apparatus of a space vehicle;Large solar arrays with high natural frequencies;High temperature-resistant fibrous silicon dioxide material;Cradle apparatus for supporting payloads in a space vehicle;Extraterrestrial transportation apparatus and method;Payload container and fastening structure for use in space vehicles;Method and equipment for deploying an envelope around an object, in particular a satellite;Deployment system for space radiators;Off axis optical communication system;Remotely operable locking mechanism;Auxiliary grapple fixture;Satellite retrieval apparatus;Method and apparatus for launching a spacecraft by use of a recoverable upper rocket stage;Direct condensation radiator for spacecraft;Inflatable core orbital construction method and space station;Space station architecture, module, berthing hub, shell assembly, berthing mechanism and utility connection channel;Deployment system;Rocket staging system;Space ultra-vacuum facility and method of operation;Clamping connection assembly for spacecraft;Method and apparatus for creating an artificial electron cyclotron heating region of plasma;Apparatus for ejection of a spacecraft;Retroflective attitude determining system;Satellite station;Apparatus and method for transporting a spacecraft and a fluid propellant from the earth to a substantially low gravity environment above the earth;Spacecraft subsystem support structure;Co-operative satellites;Geostationary communications satellite;Satellite despin device;Two-stage spacecraft with collapsible wings;Title Not Available.;Spacecraft structure with symmetrical mass center and asymmetrical deployable appendages;Spacecraft structure;Payload depolyment from shuttle employing an ejection restraint device;Passive thermal radiator for earth orbiting satellite;Transfer chamber and method of operating same;Multiple body handling operations on the space shuttle;Space based orbit transfer vehicle;Deployable space panel structure;Satelite transfer vehicle;Spacecraft to shuttle docking method and apparatus;Spacecraft stabilization system and method;Spacecraft support and separation system;Sun shield;Apparatus and method for constructing and disassembling a truss structure;Spacecraft payload ejection mechanism;Transportable solar power station;Device for separation and launch of a body with linear and rotational velocity;Acetylene (ethynyl) terminated polyimide siloxane and process for preparation thereof;Spacecraft angular momentum stabilization system and method;Spacecraft structure for supporting an optical bench;Solar sail;Integrated spacecraft cradle and shuttle structure;Propulsion apparatus and method using boil-off gas from a cryogenic liquid;Earth orbiting satellite with improved passive thermal radiator;Method and apparatus for orbital plane changing;Method and apparatus for establishing a reference potential on satellites in planetary ionospheres;Spacecraft for use in conjunction with a reusable space shuttle;Expandable spacecraft;Aerospace vehicle;Title Not Available.;Variable length strut with longitudinal compliance and locking capability;Mounting device for supporting a component, especially a mirror or an antenna reflector in a spacecraft;Device for derivation of temporary force for maintaining a displayable appendix in its stored position on a space vehicle;Exoatmospheric calibration sphere;Braided preform for refractory articles and method of making;Hemispherical latching apparatus;Payload deployment from launch vehicle using canted springs for imparting angular and linear velocities;Multiple locking device insensitive to thermal variations especially applicable to space vehicles;Magnetic bearing arrangement for an artificial satellite;Transfer vehicle for use in conjunction with a reusable space shuttle;Vortex inhibiting closed spherical outlet structure;Backup bearing and power transfer assembly for communication satellite;Space shuttle with rail system and aft thrust structure securing solid rocket boosters to external tank;Low density resin systems for improved filament-wound composites useful as rocket motor cases;System for releasably securing movable support elements on space vehicles;Apparatus for acceleration-free mounting of a body in a spacecraft;Atmosphere modification satellite;Survivable satellite bus structural frame;Modular spacecraft structures;Process and apparatus for exploring the atmosphere of a planet;Elastomer toughened polyimide adhesives;Satellite system configuration;Space satellite with agile payload orientation system;Satellite arrangement providing effective use of the geostationary orbit;Spacecraft configuration permitting a continuous three-axes attitude control;Deployable support structure for spacecrafts;Converting solar power to electric power;Payload deployment from shuttle with linear and angular velocity;Spacecraft separation apparatus;Decoy missile;Spacecraft with internal propulsion stages;Integrated spacecraft and cradle structure;Closed space structures;Deployable shield;Solar energy system with relay satellite;Apparatus for gyroscopic ejection of shuttle launched spacecraft;Satellite deployment system with remotely controlled relocking capability;Roving geosynchronous orbit satellite maintenance system;Three point attachment for an ejectable spacecraft;Toy spaceship;Satellite servicing;Method of placing a spacecraft into final earth orbit or earth escape trajectory;Lightweight structural columns;Spin activated safety circuit for spacecraft;Vehicle enshrouding apparatus;Stowable and inflatable vehicle;Advanced cryogenic multi-staged radiator system;Thermal insulation attaching means;Mounting structure;Cook-off coating;Anti-missile missile;Traffic switching in communications satellites;Satellite connected by means of a long tether to a powered spacecraft;Magnetic suspension and pointing system;Continuous integrated clamping hoop space vehicle support system;Module exchanger systems;Composite dome;Spin ejector;Support and load alleviation system for space vehicles;Method and apparatus for triggering a substantial change in earth characteristics and measuring earth changes;Method and apparatus for controlling earth orbiting satellites and vehicles inter alia;Ejection system;Vehicle operation control system;Spacecraft structure;Method of storing spare satellites in orbit;Launch lock device;Deployable flexible tunnel;Solid state solar to microwave energy converter system and apparatus;