310 results about "Micro gravity" patented technology

The invention discloses a space manipulator ground microgravity hybrid simulation method, and particularly relates to a realization method for ground-based simulation of a space microgravity environment by a 7-DOF space manipulator. Gravity compensation is realized at the middle part of the 7-DOF space manipulator by adopting the gas flotation method; the middle part of the 7-DOF space manipulator is supported on two gas flotation feet; shoulder parts and wrist parts at two ends as well as an end effector adopt static balance mechanisms to realize gravity compensation; two static balance mechanisms are designed, respectively named as a shoulder part static balance mechanism and a wrist part static balance mechanism, and used for realizing gravity compensation for a 2-DOF manipulator formed by a shoulder joints 1 and 2 and the end effector as well as gravity compensation for a 3-DOF manipulator formed by wrist joints 5, 6 and 7 and the end effector, as a result, gravity compensation for the whole space manipulator system is realized.

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.

A method for on-orbit calibration of the temperature sensors of a simulated blackbody is disclosed. The method may include selecting a simulated blackbody traveling in a micro-gravity environment and comprising a sensor, a container positioned proximate the senor and containing a material, and a heat transfer device positioned proximate the at least one container. The heat transfer device may transition the material through a phase change. The temperature sensor may monitor the temperature of the material during the phase change. A correction may be calculated to correct any disparity between the temperature reported by the temperature sensor during the phase change and the known plateau temperature corresponding to that phase change. The correction may be applied to subsequent temperature readings obtained using the temperature sensor.

A variable gravity field simulator can be utilized to provide three dimensional simulations for simulated gravity fields selectively ranging from Moon, Mars, and micro-gravity environments and/or other selectable gravity fields. The gravity field simulator utilizes a horizontally moveable carriage with a cable extending from a hoist. The cable can be attached to a load which experiences the effects of the simulated gravity environment. The load can be a human being or robot that makes movements that induce swinging of the cable whereby a horizontal control system reduces swinging energy. A vertical control system uses a non-linear feedback filter to remove noise from a load sensor that is in the same frequency range as signals from the load sensor.

The invention provides an astronaut training device. It includes the frame, a set of rope driving device installed on the four corners of the frame which the rope is connected to a cestus and the run machine is set under the frame; the rope driving device is made up of the servo electric machine with the coder fixed on the frame middle, the reducer, the trolley, the pull sensor installed under the frame, the crown block and its angle sensor, the over wheel and its angle sensor, the rope with one end fixed around the trolley and the other end connected to the cestus around the crown block; the pull sensor is connected to the rope between the trolley and the crown block. The invention can simulate the gravity field in the micro gravity condition to train the astronaut to avoid get the space flight sport illness, also the invention cab be used for recovering device.

The invention discloses a microfluidic bubble removal device and a preparation method thereof as well as a microfluidic device adopting the microfluidic bubble removal device. The microfluidic bubble removal device comprises a channel bottom layer and a porous drainage layer located above the channel bottom layer, wherein a microfluidic channel is formed between the channel bottom layer and the porous drainage layer, and at least one boss strip is arranged on the side, located on the microfluidic channel, of the channel bottom layer. According to the invention, dependence of the traditional microfluidic air removal method on gravity is eliminated, the air removal efficiency can be increased, and the air removal requirement of the microfluidic device in a micro-gravity environment can be met. The microfluidic bubble removal device is integrated with other microfluidic chips easily and can remove bubbles of liquids with different viscosities.

The invention relates to a multichannel temperature collecting system applied to micro-gravity fluid test, comprising interface filter circuit, multichannel switching module, thermoelectric couple temperature collecting module, two-stage signal amplifying module, A/D collecting module, couple failure detecting alarming module, central control unit and voltage stabilizing power supply module, where the temperature sensor is a thermoelectric couple to collect small temperature signal and completes multichannel temperature data collection by analog switch; after passing through a thermoelectric couple amplifier, completing linearization and cold end compensation, and amplifying the signal of the thermoelectric couple, where the linear output absolute value is 10 mv/ deg.C, and after amplifying by the second-stage operational amplifier, making the signal output range is 0-5 V/10V, corresponding to the whole temperature range of the fluid testing device, such as (0-120 deg.C); converting the temperature analogue quantity into digital quantity through the A/D collecting module and inputting the digital quantity into the central control unit. The system is simple in structure, and has high temperature measuring stability and good consistency.

The invention provides a device and method for simulating a space mechanical arm to capture ground three-dimensional space microgravity of a target satellite, and relates to a device and method of the ground three-dimensional space microgravity. The problem that the movement of a floating satellite base in the three-dimensional space and operation process of the space mechanical arm is not considered is solved. The device comprises two industrial mechanical arms, the space mechanical arm, a hand eye camera, a capturing paw, a capturing connector, a service satellite body simulator, a target satellite body simulator and six-dimensional force and torque sensors; the method comprises the steps that target satellite movement is simulated; the position and attitude of the target satellite and movement information of joints of the space mechanical arm are determined; movement information of a service satellite body simulator base and the industrial mechanism arms is calculated; the capturing connector captures the target satellite body simulator in a capturing paw area; a movement state of the service satellite body simulator is achieved by simulating a real target satellite movement sate. The device and method for simulating the space mechanical arm to capture the ground three-dimensional space microgravity of the target satellite is applied to the field of space mechanical arm ground three-dimensional space microgravity simulation.

The invention provides a micro-low-gravity simulation apparatus and test method. The simulation apparatus comprises a magnetic guiding panel, a rotating mechanism, an arc guide rail, a suck-back typebearing, a pulley block, a suspension mechanism and a fixed pulley; the magnetic guiding panel and the arc guide rail are respectively horizontally arranged, and the center of the arc guide rail is disposed on a rotating axis of the rotating mechanism; the suck-back bearing is stabilized on a noncontact balance point of a bottom surface of the magnetic guiding panel; the suspension mechanism is suspended on the suck-back bearing by virtue of the pulley block, one end of a rope is fixed on a sliding block of the arc guide rail, and the other end passes by the first fixed pulley to be provided with a weight block in a suspension manner. By adopting the micro-low-gravity simulation apparatus of the invention, a low-cost micro-gravity simulation experimental environment is provided, the suck-back type bearing is combined with an air floatation technology and an electromagnetic technology, the micro-low-gravity simulation apparatus can be adsorbed on the lower surface of the magnetic guiding panel and can move freely in a bottom plane of the magnetic guiding panel; and moreover, the micro-low-gravity simulation apparatus has the advantages of no friction and no contact, so that the testinterference is greatly reduced, and the accuracy of a test simulation result is further improved.

The invention relates to intelligent three dimensional microgravity air feet, which pertains to the microgravity simulation experiment device of spatial mechanism. Three air feet are arranged on the lower side of a supporting plate and a shell and three steering bars are arranged on the upper side of the supporting plate. The bottom part and the upper part of the shell are respectively provided with a servo-actuator and an antithrust bearing. A shaft joint and a speed reducer are arranged between the servo-actuator and the antithrust bearing. The lower end of a screw bolt inserted in the antithrust bearing bore is connected with the shaft joint. Transmission nuts matched with three sleeves are arranged on a connection board. A linear bearing is matched with and arranged on the lower end of the sleeve. Three flexible spring mechanisms are connected with a working plate on which a sensor and a joint for a test piece bracket are arranged. The intelligent air feet can effectively solve the technical problem of microgravity simulation during the complicated three dimensional movement of the spatial mechanism and is characterized by simple structure, high simulation precision, flexible test method, simple technique, small floor occupation and convenient debugging, thus being particularly applicable to the microgravity simulation test of complicated three-dimensional movement.

The invention provides a harmonic drive-containing space manipulator simulation device, and belongs to the technical field of aerospace engineering. The device adopts harmonic speed reducer drive and a space manipulator microgravity test mechanism, and comprises the following five parts, namely a base, a joint driving mechanism, an arm lever stiffening regulating mechanism, a suspension mechanism, and a movement precision test mechanism, wherein the base has a 90-degree installation adjustable function; the joint driving mechanism adopts a form of servo motor driving and harmonic speed reducer drive; the arm lever stiffening regulating mechanism simulates different flexibilities of an arm lever under a stress stiffening effect by adopting a tensile force pre-tightening mechanism with a replaceable arm lever sleeve; the suspension mechanism comprises an aluminum profile bracket and a two-dimensional suspension mechanism without additional constraint; the movement precision test mechanism comprises a PSD (position sensitive detector) and a laser generator, and can measure the flexible deformation amount at the tail end of a manipulator. The device can realize the dynamic performance test of the harmonic drive space manipulator in a microgravity environment, and has a wide application prospect in the field of aerospace engineering.

The invention discloses a zero (micro) gravity suspension method and device with a zero-frequency vibration isolation characteristic and relates to the technical field of zero gravity or micro gravity environmental simulation in the outer space. The problems of space ground simulation, low-frequency and ultralow frequency vibration isolation and the like are solved. The series of suspension devices can be each substantially seen as being formed by connecting a vertical spring and a vertical spring which support gravity support through a connecting rod and a suspended object. According to the basic principle, support force which is equal to the magnitude of the gravity and opposite to the direction of the gravity is provided through geometric nonlinearity arrangement of a spring connecting rod mechanism, so that the resultant force acted on the suspended object within the device design range is zero, and thus the suspended object is in the suspension state. The zero (micro) gravity suspension device can be used for space zero and micro gravity environments including ground simulation experiments such as spacecraft docking, large space flexible structure dynamics performance tests and astronaut training. Through the suspension characteristics of the zero (micro) gravity suspension method device, the problems of low-frequency and ultralow frequency vibration isolation can be solved effectively, and the defect that through a traditional vibration isolation theory, system resonance is difficult to be avoided is overcome.

The invention discloses a spiral type gas-liquid separator under micro-gravity based on a porous material. The spiral type gas-liquid separator comprises a shell, wherein the shell is provided with a mixed fluid inlet, a gas-phase working medium outlet and a liquid-phase working medium outlet; the shell is internally provided with a hydrophobic-phase porous material column located at the axis of the shell, a lyophilic-phase porous material layer located on the inner wall of the shell, and a baffle plate is arranged between the hydrophobic-phase porous material column and the lyophilic-phase porous material layer and is in spiral arrangement along the axial direction of the shell; and the two side edges of the baffle plate are fixedly connected with the outer wall of the hydrophobic-phase porous material column and the inner wall of the lyophilic-phase porous material layer respectively. Therefore, the spiral type gas-liquid separator under the micro-gravity based on the porous material combines the advantages of a static separator and a dynamic separator; and meanwhile, the respective disadvantages are also overcome. The spiral type gas-liquid separator has the advantages of great gas-liquid separation amount, no power consumption, high reliability and the like and has a very good application prospect under a micro-gravity environment.

A method for on-orbit calibration of the temperature sensors of a blackbody is disclosed. The method may include selecting a blackbody traveling in a micro-gravity environment and comprising a sensor, a container positioned proximate the sensor and containing a material, and a heat transfer device positioned proximate the at least one container. The heat transfer device may transition the material through a phase change. The temperature sensor may monitor the temperature of the material during the phase change. Additionally, the state of the material may be measured by displacement of the container to improve the accuracy of the plateau temperature measurement. A correction may be calculated to correct any disparity between the temperature reported by the temperature sensor during the phase change and the known plateau temperature, measured at a threshold state of the material, corresponding to that phase change. The correction may be applied to subsequent temperature readings obtained using the temperature sensor.

The invention discloses a longitudinal gravity compensation device with micro-gravity simulation implementation systems and six degrees of freedom for spatial mechanisms, and relates to a gravity compensation device. By the aid of the longitudinal gravity compensation device, the problem of difficulty in implementing longitudinal gravity compensation by an existing gravity compensation mechanism in a scheme when spatial mechanisms are heavy can be solved. The longitudinal gravity compensation device is characterized in that an upper-layer platform, a middle platform and a lower-layer platform of the longitudinal gravity compensation device are sequentially arranged from top to bottom, a central upright column is vertically arranged between the lower surface of the upper-layer platform and the upper surface of the middle platform, the upper end of the central upright column is connected with the lower surface of the upper-layer platform by a ball bearing, the lower end of the central upright column is connected with the upper surface of the middle platform, four compensation systems are arranged on the upper surface of the lower-layer platform to form a square, the middle platform is connected with the lower-layer platform by the four compensation systems, and pneumatic feet are uniformly distributed on the lower surface of the lower-layer platform. The longitudinal gravity compensation device is used in the field of spaceflight.

The invention provides an air flotation supporting device for a space manipulator moving in the plane and relates to the field of air flotation supporting devices. The air flotation supporting device comprises a plane air foot assembly, a force sensor, a linear bearing spring assembly, a rolling wheel assembly, an arm rod containing ring, a first mounting plate, a second mounting plate, a third mounting plate, a fourth mounting plate and a rolling wheel mounting plate. The air flotation supporting device for the space manipulator is provided and used for a micro-gravity environment simulation test of the space manipulator. The force sensor senses the pressure applied to the upper plate and the lower plate to judge whether the center of gravity of the manipulator reliably falls on the air flotation supporting device or not. The manipulator can move slightly within the up-down reasonable position range through the linear bearing guide rail assembly, unexpected vertical movement is compensated for automatically, and it is guaranteed that the manipulator is in the horizontal state all the time. A manipulator rod of the manipulator can conduct slight friction rolling movement through the rolling wheel assembly.

In a culture method of the present invention, by culturing bone marrow stromal cells or mesenchymal stem cells under a pseudo micro-gravity environment generated by multi-axis rotation, bone marrow stromal cells or mesenchymal stem cells having an average cell size smaller than that before the culture are obtained. The bone marrow stromal cells or mesenchymal stem cells thus cultured are suitable as graft cells for a central nerve diseases therapy.

The invention provides an active anchoring mechanism with the two-time drive function and relates to the active anchoring mechanism. The active anchoring mechanism aims at solving the problem that anchoring force is small after media are thrown into an existing anchoring mechanism due to the fact that an anchor tip in the existing anchoring mechanism can not be deformed. The large end of a step pushing rod is fixedly connected with a piston. A back taper is arranged inside the anchor tip and is arranged adjacent to the small end of the step pushing rod. An anchoring claw is fixed at the small end of the step pushing rod. Each stretching wing is installed on the large end of the anchor tip through each stretching wing pin, and a plurality of the stretching wings are arranged in a star-shaped mode. A thrust end cover is connected with the lower end of an expansion cylinder in a threaded mode. An anti-vibration pad is arranged on the upper end face of the thrust end cover. A piston body is arranged inside the expansion cylinder and connected with the expansion cylinder in a sliding mode. A plurality of blind holes are evenly distributed in the piston body along the radial direction of the piston body. A fire device is arranged on a fire connector. The outer wall of the upper end of the expansion cylinder is connected with a limiting ring in a threaded mode. The outer wall of a combustion room of an anchoring unit is in sliding connection with the inner wall of an end cover of the expansion cylinder. The active anchoring mechanism is applied to anchoring of landing devices and instruments and equipment under a micro gravity environment.

The invention discloses a microgravity vacuum environment oriented lunar surface in-situ resource 3D printing device, and belongs to the manufacturing field of spatial additive manufacturing. The device is characterized in that the obtaining and screening of surface particular materials of lunar soil, lunar dust and the like are achieved by a lunar surface in-situ resource grabbing and screening unit; a 3D printing shaping unit is formed through ink jetting, 3D printing is conducted by using screened particular materials, and the device is suitable for lunar surface microgravity vacuum environment and the 3D printing manufacturing of large components of future lunar base. The device has the advantages that the lunar surface in-situ resources are taken as printing consuming materials, the materials do not need to be carried to the moon through spatial transportation, so that transportation energy consumption is greatly reduced, the manufacturing cost is reduced, and the device is particularly suitable for the production of components of lunar base building facilities, mechanical parts and the like.

The invention relates to an artificial climate box capable of simulating multiple complex environment conditions, in order to mainly solve the problem of simulating complex environment conditions in space and the air on the ground. The artificial climate box mainly comprises an artificial climate box body, a fluorescent lamp region, an X-ray radiation region, a high-frequency electromagnetic wave emitting probe, a low-frequency electromagnetic wave emitter, a temperature conservation layer, a box body inner container, a rotatable sample support, a temperature/humidity sensor, an observing window, a control panel, a working indicating lamp, a power supply switch, a power line interface, an artificial climate regulating and controlling region, a CO2 and O2 sensor, an electromagnetic wave sensor, an X-ray sensor, a fixer, a gear drive speed reduction device, a main body support, a rotary shaft, a rotary barrel and the like. The temperature, humidity, electromagnetic radiation and ionizing radiation conditions can be regulated and controlled flexibly by the artificial climate box, and micro gravity and supergravity effects are simulated by the rotary sample support of which the speed can be regulated, and thus the simulation of multiple complex conditions is realized and experiment equipment for environment condition simulation experiment in space and in the air is provided on the ground.

The invention provides a microwave cavity for a cold atomic clock in micro-gravity environment, which consists of coupling waveguide, a microwave cavity and a cover plate. The microwave cavity and the cover plate are combined to form a rectangular microwave cavity, wherein central cutoff waveguide is arranged on the central axis in the length direction of the microwave cavity; end cutoff waveguide extends from two ends of the microwave cavity along the central axis respectively; the central cutoff waveguide symmetrically separates the rectangular microwave cavity into four communicated areas, namely two guided wave areas on two sides of the central cutoff waveguide and two microwave action areas at two ends of the central cutoff waveguide; the coupling waveguide is vertically fixed at the symmetric central position of the cover plate; a microwave feeder mounting hole is reserved on the side wall of the coupling waveguide; and a microwave coupling slot on the symmetric central position of the cover plate forms a microwave coupling channel of the coupling waveguide and the rectangular microwave cavity. The invention provides the key technology of interaction between the microwave and atoms of the cold atomic clock in the micro-gravity environment.