107 results about "Space suit" patented technology

The invention discloses a fiber-optic sensing intelligent garment and heart sound and blood pressure parameter processing methods thereof. The fiber-optic sensing intelligent garment comprises a garment body, a fiber Bragg grating pulse sensor, a fiber Bragg grating heart sound / breath sensor, an optical signal processing unit and an information processing terminal; the optical signal processing unit is used for wavelength demodulation and signal transmission; the information processing terminal is used for parameter information displaying, storage and remote communication. The heart sound parameter processing method of the fiber-optic sensing intelligent garment is a method of judging mathematical morphological peaks of heart sounds and mathematical morphological start-stop points through linear structure elements and cosine structure elements. The blood pressure parameter processing method of the fiber-optic sensing intelligent garment includes blood pressure model establishing and blood pressure estimating. The fiber-optic sensing intelligent garment has high electromagnetic interference resistance and high detection sensitivity, is applicable to places with strong magnetic field, high electromagnetic noise, strong radiation or the like and is applicable to body sign monitoring in magnetic resonance imaging, safety monitoring for physical conditions of mine workers, clothing of astronauts, safety clothing of fire fighters and the like.

A protective cover for a space suit, suitable for use in lunar or Mars visits which provides protection to the space suit against dust and organic contaminants while withstanding the rigors of contact with lunar or Martian rocks and equipment and not degrade or tear. The cover can be easily donned and doffed without contaminating the space suit. High strength coated fabrics which are functional in the thermal extremes of the lunar and Mars environments are suitable materials for the protective covers.

The invention provides a device for training and detecting extravehicular operation capability. The device comprises an air compressor, a supporting platform, at least two air flotation systems, a space station system, an extravehicular spacesuit system and a data detector; the air flotation systems are arranged on the supporting platform and are connected with the air compressor; the space station system and the extravehicular spacesuit system are respectively arranged on the air flotation systems; and the air compressor provides air pressure for the air flotation systems after the air compressor is started, and the air flotation systems discharge airflow to generate air film between the air flotation system and the supporting platform so that the air flotation systems freely move and rotate on a plane of the supporting platform to simulate micro-gravity motion states of three degrees of freedom. The invention can provide a micro-gravity environment simulator for training and detecting extravehicular operation capability of astronauts so as to improve an extravehicular operation training effect of the astronauts and obtain technical data of the extravehicular operation of the astronauts.

The invention relates to composite sol and a method for preparing a material for an anti-radiation space suit by use of the same. The silicon oxide-aluminum oxide composite sol comprises silicon oxide sol and aluminum oxide sol; the silicon oxide sol comprises tetraethoxysilane, gamma-(methacryloxy)propyltrimethoxylsilane, absolute ethyl alcohol, hydrochloric acid and N,N-dimethylformamide; and the aluminum oxide sol comprises aluminum isopropoxide, distilled water and nitric acid. Meanwhile, the invention also relates to a material for a space suit prepared by use of the silicon oxide-aluminum oxide composite sol and a preparation method. Through the composite sol provided by the invention, a space composite structure is formed between silicon oxide and aluminum oxide to guarantee the stability, density and flexibility of a membrane layer; after irradiation in a space radiation environment, the generation of cracks and micropores is avoided on the surface of the aluminum oxide-silicon oxide composite membrane; and the material for an anti-radiation space suit can bear long-time radiation in the space radiation environment.

The invention discloses novel intelligent clothes with a warning function. A physiological characteristic monitoring system comprises a monitoring system front end and a monitoring system back end, wherein the monitoring system back end comprises an illuminant and demodulation module (3) and a warning system (13); a spacesuit underwear (1) as the monitoring system front end comprises a first fiber grating (6), a second fiber grating (7), a third fiber grating (8), a fourth fiber grating (9), a fifth fiber grating (10), and curved optical fiber (12); one end of the curved optical fiber (12) is connected with any fiber grating in series, and the other end of the curved optical fiber (12) is connected with the illuminant and demodulation module (3) through optical fiber (2); the five fiber gratings (6)-(10) pass through a coupler (5) to be connected with the illuminant and demodulation module (3) through optical fiber (4). The novel intelligent clothes provided by the invention are simple in structure, high in detection precision, good in reliability, diversified in functions, lower in manufacturing cost and comfortable to wear. The intelligent clothes can be used in the field of spaceflight and aviation, and can be used for detecting the body temperature and the respiratory rate of an astronaut at the same time, so as to monitor the two physiological characteristics of the astronaut in a real-time manner.

The invention provides graphene modified spandex fiber as well as a preparation method and application thereof. The preparation method comprises the following steps: uniformly mixing a first part of graphene material and a chain extender in an organic solvent to obtain a chain extension solution; mixing diisocyanate, polyether glycol and a second part of graphene material for a pre-polymerization reaction; adding an organic solvent for dilution to obtain a prepolymer solution; mixing the chain extension solution with the prepolymer solution for chain extension to obtain a polymer solution; uniformly mixing a third part of graphene material with a dispersing agent in an organic solvent, adding the mixture into the polymer solution, curing and spinning, wherein the weight ratio of the graphene materials added in the three steps is (20 to 40):(10 to 30):(30 to 70). Compared with traditional spandex fiber, the spandex fiber provided by the invention has the advantages of high elongation at break, strong breaking strength, high electrical conductivity, high antibacterial rate and the like, and can be used for making underwear, ski suits, sport suits, swimming suits, welts, conveying belts, medical fabric, space suit, and the like.

The invention relates to an amusement device, in particular to a magnetic suspension type imitative space capsule and a magnetic space suit. The magnetic suspension type imitative space capsule is provided with a horizontal cylindrical imitative space ship cabin; the bottom of the inner cylinder wall of the horizontal cylindrical cabin body is fixedly provided with a magnetic plate; and a vertically-upward strong magnetic field is formed in the cabin. The magnetic space suit is distributed with permanent magnetic flakes, and the magnetic pole direction of the permanent magnetic flakes is repellent to the magnetic pole of the imitative space capsule. The amusement device adopts the magnetic suspension principle so that a player can experience the fun of weightless flight in the outer space with lower cost. The amusement device can also be used for weightless training of astronauts.

The invention discloses an assisting method and device for movements in space. According to the assisting method and device, the moving ability of astronauts can be effectively enhanced. According to the method, an external skeleton system is coupled on a space suit. The external skeleton system comprises a profiling mechanical structure, a man-machine interface system, a control system, an actuator and an energy power system. The man-machine interface system senses and sends moving states and moving intensions of the astronauts to the control system, the control system processes information and sends instructions to the actuator, and the actuator drives the profiling mechanical structure to assist in supporting of astronaut loads or providing of boosting power for movements of the astronauts, accordingly, energy consumption of the astronauts is greatly reduced, the bearing ability, the moving ability of upper and lower limbs and the information processing ability of the astronauts are improved, the adaptability of the astronauts to severe environments is enhanced, and the astronauts are assisted in completion of various space operations. Besides, by the aid of the profiling mechanical structure, astronaut bodies can be protected, the astronauts are prevented from being injured, and the assisting method and device are suitable for popularization in the of astronaut space operation devices.

The invention provides an extravehicular spacesuit upper-limb joint service life testing device, which comprises a rack, a driving mechanism and a fixing mechanism, wherein the driving mechanism and the fixing mechanism are arranged at a bottom plate of the rack; and the driving mechanism comprises a shoulder driving mechanism and an elbow driving mechanism, the fixing mechanism is arranged at the center of the bottom plate of the rack, and the shoulder driving mechanism and the elbow driving mechanism are arranged at two sides of the fixing mechanism respectively. An extravehicular spacesuit upper limb is installed on the fixing mechanism, and the extravehicular spacesuit upper limb is internally provided with a joint arm. Through the joint arm arranged inside the spacesuit upper limb, the torque is transmitted to the spacesuit upper limb through the built-in arm for a spacesuit, thereby more conforming to using characteristics of the spacesuit, and thus enabling a service life testing result of the spacesuit to be closer to real situations.

An enclosure providing a workspace for astronauts, deep-sea divers, etc. wearing pressurized suits includes a housing providing a substantially-closed chamber, a port providing access to the chamber, and a connector circumscribing the port. The enclosure's connector is configured to mate with, and form an airtight seal with, a complementary connector of the suit to close the chamber. A pressure control system may be provided to pressurize and depressurize the chamber. After connecting the enclosure to the suit, the closed chamber may be pressurized to balance pressures internal and external to the suit to facilitate manual operations. Any mated connectors of suit portions internal to the enclosure may be decoupled to expose a human limb, etc., and yet the pressure in the chamber may be maintained. The suit may include a limb-engaging seal resisting intermixing of chamber gases with suit gases while matable connectors of the suit are decoupled.

The invention provides a joint movement life testing device for an extravehicular space suit. The device comprises a stand, a driving unit and a rotary part, wherein the driving unit is arranged on the stand; the stand is connected with upper limbs of the space suit; the upper limbs of the space suit are connected with the rotary part by a flange unit; and the rotary part is connected with the driving unit. According to the joint movement life testing device, the upper limb movement of a person is simulated by a physical method, so that the life cycle of the upper limbs of the extravehicular space suit can be rapidly tested.

Provided is a manned spacecraft extravehicular maintenance ground simulating system. The system comprises a servo mechanism, a control platform, a vacuum tank, an observation window, spacesuit gloves and a support guide rail. The servo mechanism comprises a base, a stand column, a slide plate and a rotary platform. The base of the servo mechanism is fixed to the support guide rail, and the stand column is installed on the base and can move in the axial direction of the vacuum tank; the slide plate is installed on the stand column and can move in the perpendicular direction; the rotary platform is installed on the slide plate, and can move in the direction vertical to the axial direction of the vacuum tank within a horizontal plane; the rotary platform is internally provided with a motor connected to a rotary disc, the rotary disc is provided with a cross notch which can fix a maintenance equipment imitation part, and the motor rotates to drive the maintenance equipment imitation part to roll; the observation window and the spacesuit gloves are arranged on the vacuum tank. Through the manned spacecraft extravehicular maintenance ground simulating system, the maintenance equipment imitation part can be placed in the vacuum tank, and when the internal and external pressure difference of the spacesuit gloves is simulated, it is simulated that in-orbit extravehicular maintenance experiments are supported for a manned spacecraft when the relative position of the experiment personnel and the maintenance equipment imitation part are arbitrary.

The invention relates to a portable universal transportation tool for an aerospace extra-vehicular product, and belongs to the field of design of extra-vehicular maintenance equipment of a space station power subsystem cabin. The portable universal transportation tool comprises a handle, a handle grip, a guide base, a locking head, two locking hooks, a torsion spring and equipment to be transported; the equipment to be transported is horizontally placed, the guide base is installed in the middle of the top end of the equipment to be transported, and a grip of the handle is vertically placed upwards; the axial direction of the handle grip is vertically and fixedly installed at the bottom of the handle, the locking head is installed at the bottom end of the handle grip, the torsion spring isarranged inside the locking head, the two locking hooks are symmetrically arranged on the two sides of the locking head, the two locking hooks are matched with the two leading-out angles of the torsion spring, the two locking hooks extend into the guide base through the locking head and are fixedly connected, so that a lifting handle drives the the equipment to be transported to move, so that thetransportation is achieved. The portable universal transportation tool adapts to the operation work efficiency generated after an astronaut wears the extra-vehicular space suit, the working efficiency is improved, and the unnecessary accidents are avoided.

The invention provides a manufacturing method for a space Rubik cube air inflation living house. The space Rubik cube air inflation living house is composed of a multi-step air inflation cabin group or a high-step air inflation cabin group. A shell of the whole air inflation house is composed of one or more high-strength airtight films similar to materials of space suits. Compared with a thick and heavy single-shell barrel air inflation space house which is only protected by a shell, the space Rubik cube air inflation living house mainly depends on peripheral cabins which provide multi-step shielding and protection to an interior cabin. Best shielding and protection can be obtained by a central zone cabin where spacemen work and live. Purposes of other peripheral cabins can be arranged according to different requirements for protection. The higher the step of a group is, the safer shielding and protection which are obtained by the group are. The space living house which is light, chip and high in safety is achieved through the step-type protection design, and manufacturing, launching and operating costs are greatly reduced. Therefore, the step-shaped protection design can be used for space transportation, can be used for catching asteroids where foundations can be found and space mining and manufacturing industries can be developed, and can be used for developing space house property and tourist industries and building space stations and temporary planet immigrant living houses.

The invention relates to the technical field of aerospace equipment, in particular to a molten metal space suit which comprises a basic garment and further comprises a molten metal pipeline, a control device, a temperature monitoring device and a temperature adjusting device for heating or cooling molten metal. The molten metal pipeline contains molten metal and is fixed to the surface of the basic garment and spread all over the body. One end of the temperature monitoring device is connected with the molten metal pipeline, and the other end of the temperature monitoring device is connected with a fourth port of the control device so that temperature information detected by the molten metal pipeline is transmitted to the control device. A pipeline outlet of the molten metal pipeline is connected with a first port of the control device so as to distribute molten metal flowing out of the molten metal pipeline again according to the received temperature information. A second port and a third port of the control device are connected with a pipeline inlet of the molten metal pipeline and one end of the temperature adjusting device so that molten metal flowing out of the control device can form two accesses under different temperatures to be supplied back to the molten metal pipeline.

The invention relates to a low-stress manufacturing process for eliminating anisotropism of a 2A12 aluminum alloy forging, and belongs to the field of metal material engineering. In the aerospace field, according to the use and stress environment of an aluminum alloy product, the requirement for lowering the anisotropism of a material is high, and especially the requirements of an airtight knuckle bearing type forging for the chordwise and radial strength and toughness of the product are higher. Especially the requirement of an airtight knuckle bearing for a space suit for the machining precision of the product is quite high. For an aluminum alloy capable of being subjected to heat treatment and strengthening, after the material is quenched, large internal quenching stress exists in the material, and for the product with the high requirement for machining precision, waste can be possibly caused by size tolerance after finish machining. According to the method, the anisotropism, in the chordwise direction and the radial direction, of the product can be effectively eliminated, especially the internal stress of the product is effectively eliminated, and the machining yield of the product is remarkably increased.

The invention relates to space suit upper limb performance test equipment. An elbow joint assembly is mounted on an equipment support. A space suit elbow clamping hoop is locked onto the elbow joint assembly. A shoulder flange fast clamping device and a wrist connection assembly are located at the two sides of the elbow joint assembly correspondingly. Joint driving assemblies are arranged at the positions, below the shoulder flange fast clamping device and the wrist connection assembly, inside the equipment support correspondingly. Each joint driving assembly is mounted on the equipment support in a relatively-movable manner. The output ends of the Joint driving assemblies at the two sides are connected with the shoulder flange fast clamping device and the wrist connection assembly correspondingly to drive the shoulder flange fast clamping device and the wrist connection assembly to swing. A space suit shoulder flange is clamped to the shoulder flange fast clamping device. The wrist connection assembly is provided with a wrist tool for fixing a space suit wrist interface. The space suit upper limb performance test equipment is novel in structure, flexible to control, easy and convenient to operate and applicable to the upper limb performance test for space suits of different sizes.

The invention provides a glove fingertip vacuum absorption fixing device of an extravehicular space suit, which relates to a vacuum absorption fixing device. The invention can solve the problems between the fingertip of an EVA glove which adopts rigid fixing device for connection and the fingertip of an exoskeleton mechanism that the fingertip is easy to break off, the clamping force is difficult to control and the expensive EVA glove is easy to be damaged. An adsorption cap (2) is connected with a fingertip sensor (6) of an exoskeleton manipulator (1) by a connection shaft (3), one end of a first air duct (7) is communicated with the absorption cap (2) by an air duct joint (5), the other end of the first air duct (7) is communicated with an air inlet of an air valve (10), an air outlet of the air valve (10) is communicated with the input end of a micro vacuum pump (8) with an electric motor by a second air duct (11). The invention realizes the flexible connection between the fingertip of the glove of the EVA space suit and the fingertip of the exoskeleton mechanism; the device never breaks off and has no damage to the glove of the expensive EVA space suit.

A motor stand of a primary motor-driven pump unit of a pressurized water nuclear reactor comprises an upper flange and fixing means suited to ensure the fixing of transverse holding means of the said primary motor-driven pump unit, the said primary motor-driven pump unit comprising an electric motor having a lower flange suited to be integrated with the said upper flange of the said motor stand. The motor stand is characterized in that the said fixing means comprise an annular element resting on the said upper flange of the said motor stand suited to be flanged between the said upper flange of the said motor stand and the said lower flange of the said motor, the said fixing means comprising at least one radial excrescence in which there is arranged a space suited to receive the said holding means.

The invention discloses an active heating device for extravehicular space suit gloves, comprising a box body, a controller, a power supply, a heating sheet, a negative temperature heat-sensitive sensor, a winding displacement sheet and a magnet; the controller comprises an automatic control module and a manual control module, thus realizing automatic heating and manual heating on the extravehicular space suit gloves. Ambient temperature is detected by the negative temperature heat-sensitive sensor to send a temperature signal to the controller, and the controller drives the heating sheet to work so as to finish the automatic heating of the extravehicular space suit gloves. The manual control module is communicated by the magnet, thereby ensuring the heating sheet to heat so as to finish manual heating of the extravehicular space suit gloves. The heating device can ensure the continuity of extravehicular work, improve extravehicular work efficiency and reduce the risk of extravehicular work for astronauts; and in addition, the heating device has small volume, compact structure and convenient operation.

The invention discloses a carbon dioxide absorbent with low flow resistance, belonging to the technical field of air purification in enclosed spaces. The carbon dioxide absorbent is a honeycomb-like CO2 absorbent medicament tray prepared by pressing the following raw materials by mass: 85% to 99% of lithium hydroxide, 0% to 5% of sodium hydroxide, 0% to 5% of calcium hydroxide and 1% to 5% of a binder. The carbon dioxide absorbent provided by the invention has two molding manners, is mainly applied to removal of carbon dioxide exhaled by an occupant in a space suit, and can also be used for removal of carbon dioxide in the enclosed spaces of firefighting, submarines, underground tunnels, etc. The carbon dioxide absorbent provided by the invention can greatly reduce resistance of air flow in an air circulation loop; and compared with flow resistance of a granular carbon dioxide absorbent, the flow resistance of the carbon dioxide absorbent in the invention significantly reduces from about 600 Pa to about 250 Pa. According to the invention, axial compressive strength of the carbon dioxide absorbent is more than or equal to 1.5MPa, and radial compressive strength of the carbon dioxide absorbent is more than or equal to 0.5MPa. A plurality of pieces of the absorbent can be stacked together for use, thereby greatly prolonging working time.

The invention discloses a joint stiffening device of repeatable flexible space suit based on a cylindrical air bag and a joint stiffening device of repeatable flexible space suit application thereof. The joint stiffening device of repeatable flexible space suit is made on the basis of a cylindrical air bag and the initial shape of the space suit is a straight cylinder shape. The cylindrical air bag is composed of a base, a cylindrical air bag and a film, wherein a plurality of cylindrical air bags are arranged between the base and the film. The joint stiffening device of repeatable flexible space suit provided is characterized in that according to the change of the limb strength and bending tendency of the astronaut, the positive or reverse bending state of a plurality of cylindrical air bags in the space joint stiffening device can be changed continuously; adaptability and repeatability of joint stiffening device of space suits is achieved; the problem that the limbs and joints of astronauts in space suits are not easy to bend in the space environment is solved. The plurality of cylindrical air bags in the space joint stiffening device have good elasticity, and can adjust the tightness, and avoid problems such as stiffness of joints and swelling of the limbs due to lack of flexibility in space suits.

The invention discloses a two-round energy recovery system of an extra vehicular activity space suit life support system. The energy recovery system of the extra vehicular activity space suit life support system comprises an oxygen supply loop, a turbine power device and a ventilation and circulation loop, wherein the oxygen supply loop is used for supplementing oxygen consumed by metabolic exhaustion of an astronaut and keeping the absolute work pressure necessarily required inside an extra vehicular activity space suit and takes high-pressure oxygen as power for driving the turbine power device to work and driving a fan in ventilation and circulation to work, and the turbine plays roles of parts of pressure reducers due to acting caused by expansion at the same time; and the ventilation and circulation loop realizes gas circulation and regeneration inside the extra vehicular activity space suit by means of a purification can and the fan driven by the turbine power device, so that carbon dioxide and other harmful gases produced by the metabolic activities of the astronaut are removed, and at the same time, the ventilation and circulation loop absorbs partial produced heat inside the extra vehicular activity space suit. The extra vehicular activity space suit can effectively reduce the total electrical power consumption of the extra vehicular activity space suit, reduce the weight of a storage battery carried with the extra vehicular activity space suit, and improve the energy utilization rate inside the extra vehicular activity space suit.

The invention discloses an underwater training space suit dryer based on the heat pump technology. The underwater training space suit dryer based on the heat pump technology comprises a heat pump system and a working air processing system, wherein the heat pump system is used for circulating of refrigerating fluid. According to the underwater training space suit dryer based on the heat pump technology, the heat pump technology and the heat recovering technology are combined, and working air which has the most reasonable temperature and humidity and can be used for drying can be obtained. The underwater training space suit dryer based on the heat pump technology has the advantages that due to the fact that the drying method which is achieved by combining of the heat pump drying technology and the waste heat recovering technology is adopted, the requirements of drying of training space suits are met; due to the fact that the waste heat recovering and reusing technology is utilized, the dehumidifying efficiency and the utilization rate of a drying machine are improved, unit dehumidification energy consumption is reduced, operating cost is reduced, and the quantity of heat discharged to the environment is reduced to the maximum degree.

The invention discloses a detection system for acting force on a human body imposed by a wearable device. The detection system comprises a detection device and a processing device. The detection device comprises a pressure detection module and a signal sending module. The processing device comprises a signal receiving module, a signal processing module and a central control module. In this way, requirements on convenience, flexibility and low power consumption for a wearable detection tool can be met; by using a thin sheet type pressure sensor and a low power consumption small element, the whole set of the system is integrated into a PCB, so the system is small in size and practical in functions; and the detection system can be used for detecting pressure on a person imposed by exoskeletons or artificial limbs during rehabilitation and for detecting pressure on the body of a spaceman imposed by a space suit when the spaceman carries out extravehicular activities. The detection system is capable of precisely and quickly calculating pressure values in real time, thereby improving safety of the wearable device, so the detection system has important significance for development promotion of some advanced mechanical devices.

The invention discloses a multifunctional lifesaving one-piece suit, which is made by connecting surface wear-resistant layer cloth, a middle layer high-polymer water-proof tensile pressure-proof tough material and inner layer lining cloth in sequence, wherein the surface wear-resistant layer cloth, the inner layer lining cloth and the middle layer high-polymer water-proof tensile pressure-proof tough material are compounded integrally; and the surface wear-resistant layer cloth is high-temperature-resistant fire-proof and wear-resistant cloth or wear-resistant cloth of which the surface is coated with a high-temperature-resistant fire-proof material. The multifunctional lifesaving one-piece suit can be used for withstanding strong water pressure, supplying oxygen and energy to people who are in trouble and accurately positioning and performing video communication in case of severe accidents such as collapse or water permeation; and the one-piece suit can be used for preventing toxicity, resisting fire, insisting life, waiting for rescue and self-rescue and realizing underwater operation and self-rescue in case of gas explosion.

A chitosan-g-aliphatic acid phase-change material, a preparing method thereof and applications of the material are disclosed. The method includes dissolving chitosan into an aqueous acetic acid solution; precipitating the chitosan in a high-speed shearing coagulating bath to obtain chitosan subjected to ultra-micro pretreatment; dispersing anatase type nanometer titanium dioxide into a melt liquid of aliphatic acid under ultrasonic wave functions; adding the chitosan subjected to ultra-micro pretreatment into the liquid; reacting the mixture under vacuumizing conditions for 1 h; and washing a product with absolute ethanol to obtain the phase-change material. By adding the anatase type nanometer titanium dioxide in a preparing process of the phase-change material, crystallization heat release of chitosan-g-aliphatic acid in a cooling process can be promoted. The method is green, clean, and free of environment pollution. The graft polymer of this series is safe and nontoxic to human bodies and environment, is biodegradable and has good application prospects in the fields of heat-storage temperature-adjusting textiles, space suits, diving suits, high-grade sportswear, and the like.

A motor stand of a primary motor-driven pump unit of a pressurized water nuclear reactor comprises an upper flange and fixing means suited to ensure the fixing of transverse holding means of the said primary motor-driven pump unit, the said primary motor-driven pump unit comprising an electric motor having a lower flange suited to be integrated with the said upper flange of the said motor stand. The motor stand is characterized in that the said fixing means comprise an annular element resting on the said upper flange of the said motor stand suited to be flanged between the said upper flange of the said motor stand and the said lower flange of the said motor, the said fixing means comprising at least one radial excrescence in which there is arranged a space suited to receive the said holding means.

The invention provides an outboard on-orbit operated ground test method of spacecrafts. The ground test method comprises the following steps of installing a test article to a servo mechanism, installing gloves of an outboard space suit, and closing the door of a vacuum tank; adjusting the test article to fit the operating position of the gloves of the outboard space suit, regulating the air pressure in the vacuum tank to a preset pressure value, and completing an outboard test operation by a user wearing the gloves of the outboard space suit; returning to the original state after the test operation. The ground test method achieves verification of the outboard on-orbit operated ground test of spacecrafts, and solves the problem that outboard on-orbit operated tests need verifying during long-term on-orbit flights of the spacecrafts.