| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 181 | Aerospace environment simulator | US20029162 | 1962-06-05 | US3084454A | 1963-04-09 | OTTO SCHUELLER |
| 182 | Space chambers | US6052760 | 1960-10-04 | US3064364A | 1962-11-20 | OTTO SCHUELLER |
| 183 | Zero gravity sensor | US632960 | 1960-02-02 | US3010219A | 1961-11-28 | OTTO SCHUELLER |
| 184 | DEVICE AND METHOD FOR CONTROLLING TEMPERATURE OF LOW-TEMPERATURE PUMP | US15746526 | 2016-04-14 | US20180216610A1 | 2018-08-02 | Hyok Jin CHO; Hee Jun SEO; Sung Wook PARK; Guee Won MOON |
| Provided is a cryopump enabling the maintaining of a preset temperature during a preset time, even when turned off. The cryopump may comprise: a displacer which adjusts outside temperature by compressing or expanding a refrigerant existing therein; a thermal conduction part which transfers heat outside the cryopump to the refrigerant; and a thermal conduction buffer part which, if the displacer is turned off, absorbs the heat outside that is transferred to the refrigerant, and uses same as energy for changing a phase. | ||||||
| 185 | DOCKING SIMULATOR | US15822901 | 2017-11-27 | US20180162562A1 | 2018-06-14 | Jae Wook KWON; Yong Sik CHUN; IL YOUNG KIM; Dong Young REW; Gi Hyuk CHOI |
| A docking simulator according to an exemplary embodiment of the present disclosure is a docking simulator capable of mimicking docking between two flight vehicles in a zero gravity environment, the docking simulator including: a passive module which is disposed at a preset position; and an active module which performs docking with the passive module by approaching the passive module while performing a translational motion. According to the present disclosure, the docking simulator capable of performing, on the ground, a logic verification test for rendezvous docking between the two flight vehicles in the space in the zero gravity environment is implemented, and as a result, it is possible to perform more various logic verification tests for rendezvous docking by mimicking the rendezvous docking by using actual objects. | ||||||
| 186 | APPARATUS FOR DRIVING THREE-DIMENSIONAL MICROGRAVITY CABLE | US15575402 | 2015-12-09 | US20180134420A1 | 2018-05-17 | O-hung KWON; Jae-hwan PARK; Dae-hee WON; Jin-young KIM |
| The technical objective of the present disclosure is to provide an apparatus for driving a three-dimensional microgravity cable that can reproduce microgravity environments such as those experienced on the moon or Mars. To this end, the apparatus for driving a three-dimensional microgravity cable of the present disclosure comprises: a frame unit for forming a virtual space; a wire unit comprising three or more wires, provided at the frame unit; a winch unit for winding or unwinding each of the three or more wires; tension measuring units, respectively provided at the three or more wires, for measuring the tensions of the respective wires; a position sensing unit, provided at the frame unit, for sensing the position of a participant; and a support unit, positioned in the virtual space, for supporting the participant by the three or more wires. | ||||||
| 187 | SPACE FLIGHT SIMULATOR, PLANETARIUM HAVING THE SAME, AND SPACE FLIGHT SIMULATING PROGRAM | US15612351 | 2017-06-02 | US20170353657A1 | 2017-12-07 | Kazuhiro TAKEUCHI; Nobuhiro ISHIMAKI; Kenichi OOTANI |
| A space flight simulator includes: a celestial-body-position output unit configured to output three-dimensional positions of extragalactic celestial bodies in space; an observation-position designation unit configured to allow an operator to designate a three-dimensional position and a posture of an observer in extragalactic space; a celestial-body-image arrangement unit configured to determine, based on the output from the celestial-body-position output unit, arrangement of an image of each extragalactic celestial body in a star field seen from the designated three-dimensional position and posture of the observer, and generate a star field image; a cosmic-expansion selection unit configured to allow the operator to perform selection as to whether a cosmic expansion effect is taken into account; a time designation unit configured to designate an observation time; and a cosmic-expansion correction unit configured to correct the three-dimensional position of each extragalactic celestial body based on the cosmic expansion effect and the designated observation time. | ||||||
| 188 | VESTIBULAR STIMULATION SYSTEMS AND METHODS OF USE | US14935133 | 2015-11-06 | US20170154545A9 | 2017-06-01 | Kevin Maher |
| A vestibular stimulation system, computer controls, methods, and doses are provided. | ||||||
| 189 | Angularly Unbounded Three-Axis Spacecraft Simulator | US14908483 | 2014-07-28 | US20160163218A1 | 2016-06-09 | Simone CHESI; Marcello ROMANO |
| A method of simulating 3-degrees of freedom spacecraft rotational dynamics is provided that includes attaching a payload, using a spherical air bearing, to an inner gimbal of a 3-axis gimbal, where the 3-axis gimbal includes an outer gimbal, a mid-gimbal and the inner gimbal, using a motion controller to control motion of each the gimbal of the 3-axis gimbal, where the motion controller includes an appropriately programmed computer and a motion control motor, sensing limits of free travel of the spherical air bearing, using a position sensor, and changing a position of the 3-axis gimbal away from the limit of free travel of the spherical air bearing when the spherical air bearing approaches the limit of free travel, wherein the position change effects travel of the spherical bearing to be unbounded by the limit of free travel, wherein 4π steradians spacecraft dynamics of the payload are simulated. | ||||||
| 190 | Gravity acceleration station | US13894386 | 2013-05-14 | US08931741B1 | 2015-01-13 | Pavel Kilchichakov |
| A gravity acceleration station for producing gravity acceleration and creating conditions for living under a permanent effect of gravity acceleration more than 1 g for prolonged periods of time. The station comprises a base and a hollow torus, rotating around a central vertical axis. A support of the station and motors for rotation of the station are located peripherally, along with the perimeter of the torus. That feature allows variable size of the station with diameter more than 100 meters, larger area for location of objects, and gradual increase of gravity acceleration from the center of the station along the radius. Due to a mechanism for altering the angle of deviation of the premises of the station, the value of the net acceleration can be changed according to the needs while keeping direction perpendicular to the floor of the premises. The station can be located on the ground or underground. | ||||||
| 191 | Vestibular stimulation systems and methods | US12744896 | 2008-11-26 | US08702631B2 | 2014-04-22 | Kevin Maher |
| A method of and system for administering a dose of vestibular stimulation to a subject comprising a rotational device comprising at least a first axis of rotation and configured to allow continuous rotation through more than 360 degrees around each axis of rotation are provided. | ||||||
| 192 | Plug and play reconfigurable processor boards for use with mission spacecraft design tools in rapidly developable spacecraft | US12848060 | 2010-07-30 | US08478571B1 | 2013-07-02 | Gerald B. Murphy; James L. Wolf; Ramon Krosley |
| Systems and methods reduce development, integration and testing time of a spacecraft implemented with one or more reconfigurable processor boards. Mission spacecraft design tools design, configure, simulate and analyze the spacecraft based upon constraints of the mission requirements. The mission spacecraft design tools utilize a database of defined module specifications and firmware components. One or more RPBs are programmed based upon the configuration and interfaced to other end item components defined by the configuration to form the spacecraft. | ||||||
| 193 | RADIO FREQUENCY TRANSPARENT THERMAL WINDOW | US13299095 | 2011-11-17 | US20130125676A1 | 2013-05-23 | MICHAEL A. TOCKSTEIN; JAMES P. NOKES; JON V. OSBORN; DHRUV N. PATEL; ALAN R. HOPKINS; JOHN S. WILLIAMS |
| A radio-frequency transparent window having internal conduits for the passage of cooling fluid is configured for simulating a highly uniform thermal environment for testing a device intended for use in space. The device to be tested is placed within a chamber in which a vacuum condition is maintained by a radio-frequency transparent pressure window under a pressure seal. Within the chamber, the thermal window is positioned adjacent, but not in contact with, the pressure window. A radio frequency signal is capable of passing directly through both the thermal window and the pressure window to permit communication with the device being tested within the housing. The thermal window is not in contact with the device so there in no conduction of heat from the device. Radiant heat transfer may occur from the device to the thermal window. | ||||||
| 194 | Hybrid type satellite simulation system and method thereof | US11182133 | 2005-07-14 | US20060100846A1 | 2006-05-11 | Sang-Uk Lee; Jae-Hoon Kim; Ho-Jin Lee; Seong-Pal Lee |
| A hybrid-type satellite simulation system and a method thereof are disclosed. The system includes: a satellite modeling unit including a satellite model and a software model having flight dynamics and space environment data; a satellite operation unit for generating a telecommand, transmitting the telecommand to the satellite simulation system, receiving simulation result as a telemetry, analyzing the simulation result and displaying the analyzed result; a simulator kernel for managing and controlling the satellite simulation system; a TCP/IP interface processing unit for performing an interface function of TCP/IP level between the simulator kernel and a satellite onboard computer; an onboard computer interface processing unit for performing an interface function between the satellite onboard computer and the TCP/IP interface processing unit; and a satellite onboard computer including flight software for controlling a satellite. | ||||||
| 195 | Educational Satellite system and a method of use thereof | US10940899 | 2004-09-14 | US20060058023A1 | 2006-03-16 | James White; Timothy White; David Barnhart; John Clark; Jerry Sellers; Carl Enloe |
| In one embodiment, an educational non-flight capable satellite is described comprising a plurality of modular subsystems that are adapted to be coupled together via standardized bus connectors and standard mechanical connectors. The educational satellite is fully functional and can be utilized for teaching satellite engineering and operation at high school through college level courses. | ||||||
| 196 | Zero-G emulating testbed for spacecraft control system | US11019569 | 2004-12-23 | US20050230557A1 | 2005-10-20 | Farhad Aghili |
| The present invention provides an emulation system having a control system that allows the testing of a satellite control system with all of its hardware in place, i.e. fully integrated. The emulation methodology is applicable to the case of either a rigid spacecraft or a flexible spacecraft, provided that the spacecraft's sensors and actuators are stowed to the rigid part of spacecraft in the case of a flexible spacecraft. Practically, the latter condition is not restrictive, as the actuators and sensors are usually placed rigidly in the satellite bus, while the satellite solar panels constitute the flexible elements. The control system is used to tune the mass properties and dynamic behaviour of a rigid ground-spacecraft in a 1-G environment to those of a flight-spacecraft in 0-G. A six-axis force/moment sensor is placed at an interface of the ground-spacecraft and a manipulator. Signals received from the force/moment sensor, and in some cases signals relating to the position and velocity of manipulator joints, are received into the control system. | ||||||
| 197 | Phenomenological orbital debris impact risk assessment model and software | US10189381 | 2002-07-08 | US06757612B1 | 2004-06-29 | David L. Talent; Ken C. K. Cheung; Daron L. Nishimoto |
| An orbital debris impact risk assessment and management model is provided for low-Earth orbit (LEO). The model is phenomenologically based, meaning real, theoretical and historical data of the LEO environment is used in conjunction with thermodynamic based code architecture to perform impact risk assessments. The format of the model is developed such that user friendliness and user adaptability are maximized. The model can be used as a stand-alone program (software) or run over the World-Wide Web as an application service provider (ASP). The model may be used to examine trends in the evolution of the LEO environment or to calculate likelihood of impacts for specific on-orbit assets or groups of assets. | ||||||
| 198 | Space ride simulator | US10289036 | 2002-11-06 | US06641485B1 | 2003-11-04 | Sanjay Chauhan |
| A space ride simulator allows a user to experience space travel l, the weightlessness of being in space, and the reduced gravitational effects experienced while walking on a celestial body that is smaller than the earth. A 3-D simulator is used to create the various sights and sounds and movements of space travel, while a weightlessness room allows the user to experience weightlessness, and a weight reduced room allows a user to experience reduced gravitational effects while walking on a celestial body. The weightlessness room and the weight reduced room each have magnets embedded within the floor and a user dons a vest having a magnet thereattached, of the same polarity as the magnets within the floors. The magnets within the floors are of sufficient strength so as to completely or partially repel the user from the floor. | ||||||
| 199 | System and method for inhibiting corrosion of metal containers and components | US10314793 | 2002-12-09 | US20030089427A1 | 2003-05-15 | Paresh R. Modi |
| A method and system for inhibiting corrosion of aluminum and other metal-containing components and structures exposed to water is disclosed. In one embodiment, the silicate solution is used as a test fluid medium for structural testing of aluminum-alloy or other metal container structures including propellant tanks, in which a structure filled with the medium is then subjected to various structural load testing. In another embodiment, the silicate solution is used as a test medium for proof pressure hydrostatic or load testing of launch vehicle booster tanks. The silicate film protects the underlying base metal surface against corrosion during these tests. The film also protects the base metal surface in normal atmospheric conditions from exposure to humidity and other atmospheric moisture after removal of the test medium from the propellant tank following completion of testing. | ||||||
| 200 | Method and apparatus for aircraft-based simulation of variable accelerations and reduced gravity conditions | US10076043 | 2002-02-13 | US20020164559A1 | 2002-11-07 | Stephen Ransom; Manfred Zier |
| A test chamber is pivotably suspended in an aircraft, so that the center of gravity of the test chamber always self-actingly orients itself in the direction of the effective residual acceleration. To simulate a selected acceleration greater than 0 g and less than 1 g, the aircraft is flown along a parabolic flight path with a downward vertical acceleration such that the difference between Earth's gravitational acceleration and the aircraft's acceleration corresponds to the selected acceleration to be simulated. To simulate gravitational conditions on Mars, the aircraft is flown with a downward vertical acceleration of about null g, so that the residual acceleration acting on the test chamber is about nullg. The atmospheric conditions, such as the gas composition, pressure and temperature, of Mars can also be established in the test chamber. | ||||||
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