309 results about "Zero gravity" patented technology

The invention relates to a solar cell array and antenna deployment test device for spacecraft such as a satellite and the like, and provides a zero-gravity suspension type deployment test device which overcomes the shortcomings of the air-floating deployment test device in the prior art and solves the problem existing in simulation of the zero-gravity state of the environment orbit of the solar cell array and antenna of the satellite in the ground gravity environment. The zero-gravity suspension type deployment test device is characterized by comprising a support system [1], a guide rail system [2] and a hanging system [3]. The support system [1] comprises four upright frames and a horizontal frame. The guide rail system [2] comprises two longitudinal guide rails, multiple transverse guide rails and a guide rail hanger. The guide rail system [2] is mounted below the horizontal frame. The hanging system [3] comprises a rolling bearing frame, a tubular dynamometer and a connecting piece. Through the invention, the problems existing in simulation of the zero-gravity state of the environment orbit of the solar cell array and antenna of the satellite in the ground gravity environment and the like are solved, and beneficial effects of simple structure, convenience in use, strong adaptability and the like are obtained.

System and methods are disclosed for fluid measurements which may be utilized to determine mass flow rates such as instantaneous mass flow of a fluid stream. In a preferred embodiment, the present invention may be utilized to compare an input mass flow to an output mass flow of a drilling fluid circulation stream. In one embodiment, a fluid flow rate is determined by utilizing a microwave detector in combination with an acoustic sensor. The acoustic signal is utilized to eliminate 2 pi phase ambiguities in a reflected microwave signal. In another embodiment, a fluid flow rate may be determined by detecting a phase shift of an acoustic signal across two different predetermined transmission paths. A fluid density may be determined by detecting a calibrated phase shift of an acoustic signal through the fluid. In another embodiment, a second acoustic signal may be transmitted through the fluid to define a particular 2pi phase range which defines the phase shift. The present invention may comprise multiple transmitters / receivers operating at different frequencies to measure instantaneous fuel levels of cryogenic fuels within containers positioned in zero or near zero gravity environments. In one embodiment, a moveable flexible collar of transmitter / receivers may be utilized to determine inhomogenuities within solid rocket fuel tubes.

The present invention comprises an apparatus and method for gravity-balanced apparatuses for training humans for space exploration and other applications. The embodiment of the simulation apparatus is less expensive to build and safe to operate and adaptable to numerous applications, including but not limited to theme parks, museums, training facilities, educational / research labs, and others, for people to experience walking and other perambulations in lower or zero gravity environments. The present invention is statically-balanced and comprises a spring apparatus that is easily adjusted. An embodiment of the present invention provides an apparatus and method for simulating walking in a zero-gravity or reduced-gravity environment.

The invention relates to a powder-based electrode forming method, which comprises the following steps of: uniformly mixing a powder active substance, a powder conductive agent and a powder adhesive through a three-dimensional powder mixer or a zero-gravity powder mixer; crushing through a low-temperature crusher; performing fibrous extrusion forming through a double-screw extruder or an internal mixer / open mill and then achieving target thickness through hot pressing of a calender; and finally performing three-layer compounding with a current collector of a printing conductive adhesive to form an electrode and performing cold rolling to improve the compaction density. According to the powder-based electrode forming method, a method of assisting machining by using a solvent is abandoned, so that the purity of an electrode material is guaranteed to the greatest extent, no energy waste of a drying process or restriction to the time of the drying process exists in a production process, the cost is reduced, the energy loss is reduced, and the working speed is increased.

Assemblies and methods for modifying an intraocular pressure of a patient's one or both eyes are disclosed. The assemblies and methods can be used to treat, inhibit, or prevent ocular conditions such as glaucoma, high intraocular pressure, optic disc edema, idiopathic intracranial hypertension, zero-gravity induced papilledema, and other optic pressure related conditions. An assembly can include a goggle including at least one cavity, a pump in fluid communication with the at least one cavity, and a control mechanism. The control mechanism can be operatively coupled to the pump and can maintain a target pressure or target pressure range in the at least one cavity, which, when the assembly is worn by a patient, is the area between a patient's eye(s) and wall surfaces of the goggle. Controlling the pressure over the outer surfaces of the patient's eye(s) can drive a desired change in the intraocular pressure of the eye(s).

System and methods are disclosed for fluid measurements which may be utilized to determine mass flow rates such as instantaneous mass flow of a fluid stream. In a preferred embodiment, the present invention may be utilized to compare an input mass flow to an output mass flow of a drilling fluid circulation stream. In one embodiment, a fluid flow rate is determined by utilizing a microwave detector in combination with an acoustic sensor. The acoustic signal is utilized to eliminate 2pi phase ambiguities in a reflected microwave signal. In another embodiment, a fluid flow rate may be determined by detecting a phase shift of an acoustic signal across two different predetermined transmission paths. A fluid density may be determined by detecting a calibrated phase shift of an acoustic signal through the fluid. In another embodiment, a second acoustic signal may be transmitted through the fluid to define a particular 2pi phase range which defines the phase shift. The present invention may comprise multiple transmitters / receivers operating at different frequencies to measure instantaneous fuel levels of cryogenic fuels within containers positioned in zero or near zero gravity environments. In one embodiment, a moveable flexible collar of transmitter / receivers may be utilized to determine inhomogenuities within solid rocket fuel tubes.

The invention provides a cable drive robot device for simulating the zero-gravity or low-gravity environment. The cable drive robot device comprises a basic frame, cables, cable drive units, cable guide devices, a simulation loading platform, sensors and a control system. The eight cables are arranged in a spatially-symmetric mode, wherein four cables are arranged at the upper portion and the other four cables are arranged at the lower portion. The cables are lengthened or shortened through the drive units driven by motors according to instructions of the control system. The control system conducts closed-loop or semi-closed-loop control over the length and the force of the cables according to force and displacement data given by the sensors, so that movement of the simulation loading platform in the zero-gravity or low-gravity environment is simulated. Meanwhile, one or more cables can be selected and used for being overlapped to apply external interference force. According to the experiment device, the defect that work space is limited or dynamism is insufficient in a traditional simulation method is overcome and six-freedom-degree movement control and stress simulation of the simulation loading platform in the zero-gravity or low-gravity environment can be achieved.

The invention relates to the research field of a microgravity simulating platform of a space robot, in particular to a microgravity air floatation target satellite simulator system with five degrees of freedom. The system consists of three parts, namely a movement simulator, a satellite simulator and a ground control panel. The movement simulator simulates the states of zero gravity, low friction and micro interference of a base satellite; the satellite simulator has a basic single-shaft attitude adjustment and track control function under a condition that a satellite provided by the movement simulator is in a track movement simulating environment, comprises a sensor, a controller and an actuating mechanism (a counteractive flywheel and a cold gas injecting system), and is provided with auxiliary systems such as a power system, a wireless communication assembly, a structural component and the like; and the ground control panel provides a basic function of the wireless data communication between a target satellite and the ground, and realizes the control on the target satellite and the receiving, storage and display of the data.

The invention relates to a ground zero-gravity test device for a small-space one-dimension extension mechanism for a spacecraft to overcome the defects of various test devices in the prior art and to solve the problem that the small-space one-dimension extension mechanism simulates the zero-gravity state of in-orbit operation in the ground gravity environment and to further solve the problem about compatibility of the small-space one-dimension extension mechanism with the comprehensive operation of the vacuum test and the thermal test. The ground zero-gravity test device adopts the principle of square teeth meshing and combines the real-time synchronism of a synchronous belt to vertically hang a tested mechanism. The ground zero-gravity test device is simple and feasible in design, small in size and light in weight, convenient to move, and strong in adaptability to the environment, can effectively operate in a vacuum or thermal environment condition, and can be used for testing the expanding characteristic of one-dimension extension mechanisms like a coiled extension arm and a thin-wall tubular extension arm.

A zero gravity chair generally holds an occupant in a position where the angle between the legs and the torso may be greater than 90 degrees. Typically, the legs may also be elevated such that the legs are even with or above a user's heart. The disclosed zero gravity chair, in some embodiments, enables the backrest portion to pivot relative to the seat portion allowing the user to adjust an angle between the seat portion and the backrest portion. The disclosed zero gravity chair further enables both the backrest and the seat portions to pivot as a unit independent of the angle adjustment. In certain embodiments, the chair also rotates 360 degrees about a vertical axis.

The invention discloses a zero-gravity experiment system for a spatial multi-dimensional unfolding mechanism. The zero-gravity experiment system comprises an analog wall (1), an unfolding rack (2), a rocker arm hanging device and an air floatation vehicle device, wherein the spatial multi-dimensional unfolding mechanism consists of a big arm (13), a small arm (14) and a load (15); the analog wall (1) is used for fixing the spatial multi-dimensional unfolding mechanism; one end of the big arm (13) is movably connected to the analog wall (1), and the other end of the big arm (13) is hinged to the small arm (14); the small arm (14) is fixedly connected with the load (15); the rocker arm hanging device is arranged on the unfolding rack (2) and can rotate opposite to the unfolding rack; the rocker arm hanging device can hang the big arm (13); the load (15) is positioned on the air flotation vehicle device. According to the experiment system, the unloading resistance is small, and the unloading efficiency reaches 95 percent.

In accordance with the present invention, a system for separating gas and liquid phases from a mixed phase system is provided. Furthermore, the present invention provides for the reliable separation of liquid and gas phases, regardless of the orientation of the system with respect to a gravitational field, and in low or zero gravity environments. The system of the present invention generally provides a reservoir having a variable volume that is formed from a gas permeable, hydrophobic, microporous, polymer material. Material confined within the reservoir is maintained under pressure, to expel any gases introduced to the interior of the reservoir as part of a mixed phase inlet stream. The liquid phase component of the mixed phase inlet stream may be removed from the reservoir through an outlet located within the reservoir volume.

A zero gravity chair generally holds an occupant in a position where the angle between the legs and the torso may be greater than 90 degrees. Typically, the legs may also be elevated such that the legs are even with or above a user's heart. The disclosed zero gravity chair, in some embodiments, enables the backrest portion to pivot relative to the seat portion allowing the user to adjust an angle between the seat portion and the backrest portion. The disclosed zero gravity chair further enables both the backrest and the seat portions to pivot as a unit independent of the angle adjustment. In certain embodiments, the chair also rotates 360 degrees about a vertical axis.

A shock protection apparatus includes a zero-gravity sensor 5 for detecting whether a hard disk drive 1 is in a zero-gravity state and accordingly generating a zero-gravity detection signal Sul; and ahead-slap sign detector 4 for outputting to the hard disk drive a signal Sul for retracting a head, if the hard disk drive 1 is determined to be in a zero-gravity state as detected by the zero-gravity detection signal Sul. In the shock protection apparatus, the influence of change over time of a shock-cushioning material is reduced, the difference in shock-resistant performance between operating and non-operating states is reduced, and signs of a head slap are detected promptly and properly to urgently retract the head.

The invention relates to a gravity unloading mechanism for solar array ground experiment, which comprises a thrust ball bearing, a bearing inner base, a bearing outer base, a cross beam, steel cables, pressure sensors and a display. The inner circle and the outer circle of the thrust ball bearing are respectively matched with the bearing inner base and the bearing outer base to form a moving component of an unloading mechanism; the bearing inner base is connected with the force bearing part of a solar array, and the bearing outer base is connected with the cross beam; the two ends of the cross beam are connected with the steel cables which are provided with the pressure sensors, and the two steel cables are hung on a mounting surface outside the system. The gravity of the solar array is transmitted to the external mounting surface through the bearing inner base, the thrust ball bearing, the cross beam and the steel cables, and is not born through a cavity driving motor any more, and simultaneously the free rotation can be guaranteed, therefore the mechanical environment that the driving motor provides torque for the solar array only and does not provide holding power for the solar array under zero gravity conditions can be simulated.

A gravity compensation device for solar wing low temperature unfolding experiment is capable of realizing one sixth gravity compensation and zero gravity compensation of solar wing at a temperature of -120 DEG C. The device also can carry out solar wing multi-angle repeated unfolding and folding experiments in a limit position by simulating a landing situation when the included angle between the moon surface and the horizontal plane is 15 degrees. A balance rod is adopted in the device to carry out gravity compensation, and is completely made of metals so as to adapt to the low temperature environment. The three-dimensional trace movement of the mass center of a solar wing is completed by the swinging of a guide rail and a suspension rod; the conventional bidirectional guide rail structure composed of a solar wing vertical guide rail and a solar wing horizontal guide rail is broken through, thus the system complexity is reduced, and the movement reliability is improved. A horizontal rotation assembly is adopted to enable the main beam to freely rotate in a horizontal plane, and the gravity compensation technology is broken through when the included angle between a solar wing and the horizontal plane is 15 degrees namely the extreme working condition. A pulley and a pulley structure are adopted to reduce the movement resistance. A main beam having an I-shaped aluminum structure is adopted, the weight of movable parts is reduced, and thus the inertia force during the folding and unfolding process of a solar wing is effectively reduced.

The invention discloses a gas-liquid two-phase flow measuring device and method based on phase segmentation and image processing. The device is composed of an inlet section, a rotational flow device, a measuring pipe section, an outlet section, an opposite-side parallel light source, a same-side parallel light source, a first industrial camera, a second industrial camera, an image collecting and processing terminal and a synchronous controller. The invention further provides a measuring method. The method comprises the steps of firstly using the rotational flow device to rectify gas-liquid two-phase flow into a flower pattern which is convenient to measure through an in-pipe phase segmentation technology, then combining a digital image processing technology to accurately measure cross section gas void faction of the gas-liquid two-phase flow and flow velocity of each phase, and finally calculating the mass flow rate of each phase and the total mass flow rate of two-phase fluid. Compared with existing equipment and method, the gas-liquid two-phase flow measuring device based on phase segmentation and image processing has the advantages of being small in volume, high in instantaneity and high in accuracy; meanwhile, the gas-liquid two-phase flow measuring device and method are not influenced by the flow pattern of the gas-liquid two-phase fluid, and thus can be widely applied in engineering. Since the gas-liquid two-phase flow measuring method is not influenced by gravity, the gas-liquid two-phase flow measuring method is also applied to a zero-gravity environment.

The invention discloses spacecraft vertical passive separation test equipment comprising a test rack, a test hanger, a connecting rope, pulley assemblies, a buffering and locking mechanism, a weighting mechanism and a tensile force sensor. The test rack is fixed to the ground through bolts; the pulley assemblies are fixed on transverse beams of the test rack; the connecting rope is connected to the tensile force sensor in series, one end is connected to the test hanger, the other end is connected to the weighting mechanism, and the connecting rope spans on the pulley assemblies and penetrates the buffering and locking mechanism. Compared with the prior art, the spacecraft vertical passive separation test equipment has the advantages that the large-scale spacecraft vertical passive zero-gravity separation test requirements can be met.

A system and method for supplying thrust to a structure, such as a satellite or spacecraft, for the purposes of station keeping and attitude control of the structure in low-gravity (orbital) and zero-gravity environments. The system includes devices for emitting energy beams and targets impacted by the energy beams to cause ablation of the targets. The beam-emitting devices and targets are adapted to cooperate and cause the structure to selectively undergo translational and / or rotational motion in reaction to the motion of material ablated from the targets. The position, alignment, and / or attitude of the structure can thereby be controlled in a zero or low-gravity environment by selectively emitting the energy beams at the targets.

Systems, devices, apparatus and methods of using a simulator cabin module with an interior space which replicates a space ship, where the simulator module is mounted in a real aircraft, as a real airborne simulator. The aircraft lifts off to provide airborne maneuvers such as parabolic flight paths to cause G force and zero gravity effects to passengers in the cabin module. The cabin module includes rows of seats where passengers experience realistic sounds, lights, different temperatures, and physical effects (vibrations) of space ship liftoffs and space travel by having realistic simulation effects distributed over the seated passengers. Passengers can be seated in special reclinable seats with 5 point harnesses and pilot helmets with operable wireless communications and uniforms to add to the realistic simulation effects. Simulator modules can also be mounted in other moving vehicles, such as but not limited to submersibles, ships, and the like.

A variable zero gravity simulation system is provided. A variable zero gravity condition is achieved by substantial immersion in a fluid environment by buoyancy means (101) and using robotic displacement devices such as exoskeleton (102) to help user's movement / gravity compensation and / or relief or change loads on the subject's torso and limbs that caused by the weight and shape of the buoyancy means (101), so that user can experience the effect of the variable gravity environment being simulated, such as zero gravity in which situation user could move effortlessly in a weightless environment. When combine with VR related technology, this can create vivid immersive simulations for extraterrestrial scenes and can be widely used for entertainment, game, training, healing and etc.

The invention relates to a two-dimensional plane air-floatation zero-gravity cradle which comprises two long-distance air-floatation linear guide rails, a Y-axis air-floatation axle, a Y-axis air-floatation sleeve and a hanging rope, wherein at least two X-axis air-floatation sleeves are sleeved on an X-axis air-floatation axle, the X-axis air-floatation sleeves are all connected with an air storage sleeve in a sealing way, an installing slide block is slidably arranged on the long-distance air-floatation linear guide rails and is connected with a drive mechanism in a drive way, the slide block is fixedly connected with the X-axis air-floatation axle, an air storage cavity is arranged between the air storage sleeve and the X-axis air-floatation axle, the axle center of the X-axis air-floatation axle is provided with an air inlet channel which is communicated with the air storage cavity, the air storage cavity is provided with an air outlet which is communicated with an air inlet of each X-axis air-floatation sleeve through a connecting air pipe; the air storage sleeve is fixedly connected with supports, the two supports are respectively sleeved at two ends of the Y-axis air-floatation axle, the Y-axis air-floatation sleeve is sleeved on the Y-axis air-floatation axle, and the Y-axis air-floatation sleeve is connected with the hanging rope. The invention can effectively avoid additional influences on friction force and inertia force, and is suitable for high-precision occasions.

The invention relates to the field of an erosion corrosion device and particularly provides a rotary test device for simulating the erosion corrosion on an inner wall of a pipeline, and overcomes the defects that the conventional rotary erosion corrosion test device cannot simulate the erosion corrosion on the inner wall of the pipeline well and a pipe flow type erosion corrosion test device is high in manufacturing cost. The rotary test device disclosed by the invention is provided with a rotating shaft, a slurry tank, a sample clamp and an annular sample. A carbon brush is arranged at the upper part of the rotating shaft and is connected with electrochemical test equipment; the rotating shaft is connected with an output end of a motor which is provided with a frequency converter; the lower part of the rotating shaft extends to a place above slurry in the slurry tank; the rotating shaft is connected with the sample clamp through a rotary joint; and the annular test is mounted on the test clamp. The rotary test device disclosed by the invention combines the advantages of the conventional rotary erosion corrosion test device with the conventional pipe flow type erosion corrosion test device, so that axial erosion corrosion behaviors on the inner wall of the pipe are researched in a rotated condition. According to the rotary test device disclosed by the invention, the flow speed, the medium component and the temperature can be controlled, and real-time electrochemical parameter measurement and zero gravity measurement can be realized simultaneously.

The invention belongs to the technical field of aviation and astronavigation of a ground microgravity simulation experimental platform, and discloses a six-freedom-degree zero-gravity simulation system based on combination of hoisting and air-suspending. A shaft at the other end of a large-diameter coiling block and a shaft at the other end of a small-diameter coiling block are rotationally installed on a base through a second set of air-suspending bearings. The other end of a torque sensor and the other end of a large torque sensor are in transmission connection with a rotary shaft of the small-diameter coiling block through a clutch and a brake. An air-suspending guide rail is vertically installed on a base. After going out of the large-diameter coiling block in a tangent mode, a first sling rope is swerved through a pulley and connected with a platform for a workpiece to be tested perpendicularly in a suspended mode. The workpiece to be tested is horizontally arranged on the upper end surface of a spherical air-suspending bearing, the lower end surface of the spherical air-suspending bearing is arranged on the platform for the workpiece to be tested, and an air tank supplies air to the spherical air-suspending bearing so that the air-suspending bearing can float. The six-freedom-degree zero-gravity simulation system based on combination of hoisting and air-suspending is compact in structure, overcomes the defect that common air-suspending microgravity equipment can not carry out freedom-degree simulation in the vertical direction, and additionally has the function of simulation of hoisting type microgravity equipment on three rotation freedom degrees.

An improved singlet delta oxygen generator (SOG) and method of its use are disclosed. The improved SOG is compact and scalable, capable of operating in a zero-gravity or low gravity environment, requires no gaseous diluent or buffer gas, and is capable of operating at pressures as high as one atmosphere. The improved SOG also efficiently utilizes the reactants and produces a O2(1Δ) stream that is largely free of chlorine and water vapor contamination and therefore does not require a BHP regeneration system or a water vapor trap. When used as part of a COIL system, the SOG may be part of a plenum that directly feeds the laser's nozzle. The close proximity of the SOG to the laser cavity allows operation of the SOG at higher pressures without significant depletion of available O2(1Δ) through collisional deactivation.

The invention provides a cable driven space suspension assembly state simulation device with the adjustable attitude. The device is a cabled driven mechanism with the adjustable attitude, wherein thecable driven mechanism is connected with a to-be-assembled part and driving sensing units through flexible cables and can be used for simulating product assembly under the working condition environments such as space zero gravity or low gravity. The device is characterized by being composed of a supporting frame, a servo unit, the flexible cables, the driving sensing units, a constant tension unit, wire rulers and the like. Driving units are formed by connecting servo motors, speed reducers and couplers in series. The servo unit is composed of the constant tension unit, the driving unit and the like. The constant tension unit provides constant tension and is used for completely or partially offsetting the gravity of the assembled part and simulating the space zero gravity or low gravity environments. The driving units are used for driving and controlling motion of the servo unit. The driving sensing units are composed of the driving units, tension and pressure sensors and the like andis used for enabling the assembled part to achieve external force sensing and attitude adjusting.

A nine-rope driving robot device for simulating zero gravity and low gravity comprises a foundation framework, ropes, a rope driving unit, a rope guiding device, a simulation load platform, a sensor and a control system. According to the nine-rope driving robot device for simulating the zero gravity and the low gravity, a nine-rope redundant driving scheme is adopted, the nine ropes are distributed in a mode with six ropes being arranged at the top and three ropes being arranged at the bottom; extension and shortening of the ropes are achieved through a driving unit which is driven by a motor according to a command of the control system; the control system achieve closed-loop or semi-closed-loop control on the length and force of every rope according to the force and pose position data from the sensor; meanwhile the upper six ropes can be adopted to control and simulate the pose position and movement of a load platform, the lower three ropes perform force tensioning or compensation control, and accordingly the nine-rope driving robot device for simulating the zero gravity and the low gravity has the capability of stimulating six degrees of freedom under the zero gravity or low gravity environment in large working space and meanwhile can apply the distributing force in a superposition mode through the lower three ropes or mote ropes. The nine-rope driving robot device for simulating the zero gravity and the low gravity is good in isotropy performance and has an application potential in other fields such as rehabilitation equipment.

In order to solve a problem that the existing mechanical state simulation of a space target cannot realize tasks of effective spin counteraction of the target and multiple repeated trapping of the target, the invention provides a ground physical simulation experiment system for space spinning target trapping and spin counteraction and belongs to the field of ground zero-gravity simulations of space operation systems and space targets. According to the ground physical simulation experiment system for space spinning target trapping and spin counteraction, the space target spinning state is simulated by using a six-degree-of-freedom simulator; the six-degree-of-freedom motion and zero-gravity state of a service aircraft are simulated by using air flotation and air injection; a six-degree-of-freedom mechanical arm carries a spinning tracking claw device to track and trap the spin angle velocity and spin axis of the spinning space target; angular momentum in the trapping process is transmitted to the service aircraft; and reverse air jet is adopted to perform spin counteraction. The structure of the ground physical simulation experiment system for space spinning target trapping and spincounteraction has the advantages that effective spin counteraction can be realized, trapping and spin counteraction can be integrated and the target can be repeatedly trapped for multiple times.

A comprehensive experiment testing system for a small satellite antenna comprises the antenna, a satellite rotating mechanism, accuracy testing mechanisms, a shock response collecting mechanism, a satellite, an antenna unfolding mechanism and an experiment control mechanism, wherein the antenna is a double-shaft rotating antenna; the satellite rotating mechanism is used for arranging a satellite state required by the antenna during performing multi-dimensional unfolding; the accuracy testing mechanisms is used for testing the mounting accuracy and the pointing accuracy of the antenna at every stage of an experiment; the shock response collecting mechanism is used for collecting shock response data generated during a detonating process of initiating explosive devices; the satellite is used for mounting the antenna; the antenna unfolding mechanism is used for providing a zero gravity simulation environment required by the antenna for unfolding; the experiment control mechanism is used for controlling detonation of the initiating explosive devices to unlock the antenna, and drives the antenna to unfold and fold. The system can perform the unlocking shock experiment and the unfolding experiment that the double-shaft rotating antenna is on the small satellite, the testing items are multiple, and the use range is wide.

The present invention relates to variable low / zero gravity simulation systems. variable low / zero gravity condition is achieved by substantial immersion in a fluid environment (“buoyancy means”) and using power assist means / robotic displacement devices such as exoskeleton to help user's movement / gravity compensation and / or relief or change loads on the subject's torso and limbs that caused by the weight and shape of the “Buoyancy means”, so that user can experience the effect of the (variable) gravity environment being simulated, such as Zero gravity in which situation user could move effortlessly in a weightless environment. When combine with VR related technology, this can create vivid immersive simulations for extraterrestrial scenes and can be widely used for entertainment, game, training, healing and etc.