CN111044365A - Test cabin for testing space suit - Google Patents
Test cabin for testing space suit Download PDFInfo
- Publication number
- CN111044365A CN111044365A CN201911385307.7A CN201911385307A CN111044365A CN 111044365 A CN111044365 A CN 111044365A CN 201911385307 A CN201911385307 A CN 201911385307A CN 111044365 A CN111044365 A CN 111044365A
- Authority
- CN
- China
- Prior art keywords
- test
- cabin
- pressure
- test chamber
- suit
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/08—Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
Abstract
The invention relates to a test chamber for testing an aerospace suit, and belongs to the field of aerospace suit testing. According to the invention, the installation interface matched with the wearing and taking-off port of the space suit is arranged on the bulkhead of the test chamber, so that the space suit is assembled with the test chamber through the installation interface, and a closed space is formed between the outside of the suit and the inside of the test chamber. The test chamber replaces a traditional positive pressure test mode of the space suit, semi-open type garment pressure simulation is realized by using test chamber equipment, the interior of the space suit is communicated with the atmosphere, a subject installs a sensor on the skin and wears the suit to perform related operations, the safety of people is guaranteed, errors caused by an auxiliary test device in the traditional test mode are avoided, experimental data can be accurately tested and can be transmitted back in real time, and the test performance and the operability of the test are improved.
Description
Technical Field
The invention relates to a test chamber, in particular to a test chamber for testing an aerospace suit, and belongs to the field of aerospace suit testing.
Background
The space suit is used as individual protective equipment for the astronaut to perform flight missions in orbit, provides an anthropomorphic closed space isolated from the outside for the astronaut, integrates an environmental control and life support system product inside, and provides support for the life safety of the astronaut in space.
Before the space suit is put into use, a series of test evaluations are carried out to verify the performance and reliability of the space suit. The test and evaluation of the space suit covers the aspects of motion characteristics, service life and strength, interface matching, operation efficiency and the like. The astronaut needs to wear the space suit to carry out a series of activities such as taking out of the cabin and on-orbit maintenance during the on-orbit task execution period, and higher requirements are provided for the motion characteristics of the space suit. For the motion characteristics of the space suit, the reachable areas of the upper and lower limbs, the operation force, the joint moment and other indexes are mainly considered, and the factors of the suit coupling and the hysteresis in the working state of the suit must be considered.
When the space suit is tested, in order to simulate a real use state, the pressure inside the suit needs to be higher than the pressure of the external environment. When testing the athletic characteristics of the space suit, the traditional method adopts the whole suit positive pressure test, namely, a subject wears the space suit, various athletic operations are carried out by pressurizing the inside of the suit to a state of relative positive pressure, and the test and the evaluation are mainly carried out by a simple outside-suit auxiliary test device and the subjective feeling of people. The external auxiliary device is generally large in size and mass and large in motion constraint on people, and in addition, human-clothing coupling factors also have great influence on the motion characteristics of clothing personnel, so that the additional external auxiliary device brings larger errors to the test, and the motion characteristics of the space clothing cannot be objectively and accurately evaluated. On the other hand, in the traditional test mode, the testee is isolated from the outside in the closed space in the clothes and is in a high-pressure environment, so that the human body can be damaged when an accident happens, and certain safety risk exists. In addition, the testee is in a narrow and closed space in the clothes, related parameters cannot be accurately collected in real time in a wired mode, great difficulty is brought to the test of the motion characteristics of the space suit, and the test testability and the operability are poor.
Disclosure of Invention
The invention aims to provide a test chamber for testing an aerospace suit. The installation interface matched with the wearing and taking-off port of the space suit is arranged on the bulkhead of the test chamber, so that the space suit is assembled with the test chamber through the installation interface, and a closed space is formed between the outside of the suit and the inside of the test chamber. The test chamber replaces a traditional positive pressure test mode of the space suit, semi-open type garment pressure simulation is realized by using test chamber equipment, the space suit is communicated with the atmosphere, a subject installs a sensor on the skin and wears the sensor to perform related operation, the safety of people is ensured, errors caused by an auxiliary test device in the traditional test mode are avoided, experimental data can be accurately tested and can be transmitted back in real time, and the test performance and the operability of the test are improved.
The purpose of the invention is realized by the following technical scheme.
A test chamber for aerospace garment testing, comprising: skeleton texture, lateral wall panel, top cap, big hatch door and little hatch door.
The skeleton structure is the main part frame construction of burden ballast room, and lateral wall panel, top cap, hatch door are all fixed on skeleton structure. The skeleton texture includes: the device comprises an upright post assembly, a cross beam, a top beam, a middle beam, a bottom plate, a center ring, a top plate and an upright post interface assembly; the lower part of the stand column assembly is inserted into the bottom plate assembly and fixed with the bottom plate, the upper part of the stand column assembly is fixedly connected with the top plate, the two sides of the stand column assembly are fixedly connected with the top beam, the middle beam and the bottom beam, the lower part of the bottom beam is fixedly connected with the bottom plate, the lower part of the stand column interface assembly is inserted into the stand column assembly, the lower part of the stand column interface assembly is fixedly connected with the upper surface of the top plate, and the two ends of the cross beam are fixedly connected with the center. The framework structure mainly ensures the structural stability of the test chamber when bearing relative negative pressure.
The upright post component comprises an upright post, a middle rib reinforcing plate, an upright post reinforcing rib and a transition surface. The stand is main bearing piece, for preventing the stand unstability under the pressurized condition, at stand outside fixed connection stand stiffening rib, transition face and stand stiffening rib fixed connection, pass power when the test chamber is pressurized and give stand stiffening rib and stand, has strengthened the bearing capacity in test chamber. The middle rib reinforcing plate is fixedly connected with the two end faces of the middle beam, and is mainly used for bearing the force transmitted by the middle beam under pressure, so that the stress concentration of the upright post reinforcing rib is reduced. As the main bearing structure of the test chamber, the connection between the beam and the upright post component is realized through the upright post interface component, and the beam and the bottom plate provide radial support for the test chamber structure, so that the structural damage caused by the inclination of the upright post component is avoided. Meanwhile, the upright post assembly, the top beam, the middle beam and the bottom beam provide mounting support surfaces for the side wall panel, the top cover, the large cabin door and the small cabin door, and the structural integrity is guaranteed.
The bottom plate comprises bottom plate face, section bar, base, and base and bottom plate face fixed connection provide the installation interface for the stand subassembly, and section bar and bottom plate face and base fixed connection play the additional strengthening, can effectively improve the bottom plate pressurized indent deformation condition.
The side wall panel is made of plates, the acrylic plates can be selected for processing in consideration of strength, quality and visualization requirements, and the side wall panel is fixed on a mounting surface through screws. Through holes are formed in part of the side wall panels, small cabin doors are installed at the through holes, transportation test equipment and personnel can conveniently enter and exit the test cabin, and the side wall panels are mainly used as compression surfaces of the test cabin.
The top cover is of a special-shaped curved surface structure, the glass fiber reinforced plastic material can be selected in consideration of the pressure bearing performance, the strength and the quality requirement of the top cover, the top cover is fixed on the top plate through bolts, and the structural sealing performance is kept by pressing the sealing gasket between the top cover and the top plate.
The large cabin door is mainly used as an installation interface of the space suit. The trunk structure of the space suit and the structure are arranged to achieve the effect of communicating the inside of the space suit with the outside atmosphere, and meanwhile, a sealing gasket is arranged at the mounting interface to keep the sealing performance of the structure. The cabin door is also provided with a cabin penetrating flange which is used as a circuit and gas circuit interface, and the circuit interface is mainly used for monitoring cabin pressure in real time and supplying and distributing power for test equipment in the cabin; the air path interface is connected with a pressure pumping and compensating device, and a pressure environment of relative negative pressure in the chamber is constructed by reducing the internal pressure of the test chamber, so that the positive pressure difference inside and outside the garment is ensured, and the simulation of the use state of the garment is realized. In the test process, the body of the subject is attached with a sensor to carry out the clothes test, the specified test operation is completed, the test result is transmitted and fed back in real time, and the motion characteristic of the space suit can be objectively and accurately evaluated.
The cabin door comprises a cabin cover, hinges, a base and a quick locking mechanism. The base is fixedly arranged at the position of the opening of the side wall panel, and the opening and closing of the hatch cover and the base are realized through hinges; the quick locking mechanism is used for locking the hatch cover and the base.
The quick locking mechanism comprises a mounting seat, a rotating pin, a rotating rod, a bolt, a handle and a locking block. The mounting seat is fixed on the edge of the hatch cover and is used as a mounting support of the quick locking mechanism; the locking block passes through bolted connection with the hatch cover, and the handle can revolute the rotation pin and rotate, and dwang and handle screw-thread fit extrude the locking block through screwing up the dwang screw thread and reach the effect of locking the hatch door after closing the hatch cover.
The working process is as follows:
in order to test the motion characteristics of the space suit, the test cabin equipment is utilized to realize semi-open type clothing pressure simulation.
Before testing, the pipeline and the circuit are connected according to a test principle diagram. The vacuum pump, the air compressor and the cabin pressure monitoring equipment are communicated with the test cabin through the cabin penetrating flange of the test cabin. Meanwhile, a test subject installs a sensor at a specific position on the body and penetrates into the clothing from the back of the space suit from the opening of the big cabin door of the test cabin. The circuit of the sensor passes through an opening communicated with the outside atmosphere on the back of the space suit and is connected with the input end of the information acquisition equipment, and the signal acquired by the sensor is transmitted back to the information acquisition equipment in real time through the circuit. (ii) a The cabin pressure monitoring equipment is used for feeding back and monitoring the internal pressure in the experiment cabin and the relative pressure in the clothing in real time.
In the test process, the vacuum pump and the air compressor are simultaneously opened and are always in working states. Wherein the vacuum pump is a pressure pumping device and is used for pumping pressure to the test chamber; the air compressor is a pressure compensation device and is used for repressing the interior of the test cabin, the pressure in the test cabin is reduced by adjusting the air inlet flow of the air compressor, and finally the pressure in the test cabin is maintained at a test pressure value, so that the simulation of the real pressure environment of the clothes is completed. After the simulation of the pressure environment is completed, the subject performs a series of specific test actions in the clothing, and test data are accurately transmitted back to the information acquisition equipment in real time through the sensor.
After the test is finished, the vacuum pump is turned off, the internal pressure of the test cabin is gradually recovered by adjusting the flow of the air compressor, after the pressure in the test cabin is recovered to the atmospheric pressure, the air compressor is turned off, the personnel wear out the clothes from the back of the space suit, the test data are stored, and the sensor is detached.
Advantageous effects
1. The test chamber replaces the traditional positive pressure test mode of the space suit, and semi-open type clothing pressure simulation is realized by using test chamber equipment;
2. the interior of the space suit is communicated with the atmosphere, so that the safety of people is ensured;
3. the test subject installs the sensor on the skin, so that the influence on the operation of people is small, the error caused by an auxiliary test device in the traditional test mode is avoided, the test data is accurately returned in real time, and the test testability and the operability are improved.
Drawings
FIG. 1 is a schematic view of a negative pressure test chamber;
FIG. 2 is a schematic representation of the skeletal structure;
FIG. 3 is a schematic structural view of a column assembly;
FIG. 4 is a schematic view of a base plate;
FIG. 5 is a schematic view of a hatch;
FIG. 6 is a schematic view of a quick lock mechanism;
FIG. 7 is a schematic diagram of a test of the motion characteristics of the space suit;
FIG. 8 is a schematic view of a sensor attachment location;
FIG. 9 picks up the sample from a far right designated location;
FIG. 10 shows the sample being taken to the front of the eye;
FIG. 11 places the sample at a designated location closer to the front side;
FIG. 12 values of the shoulder joint 3 degrees of freedom motion angles;
fig. 13 values of the degrees of freedom motion of the elbow joint 2.
Wherein, 1-skeleton structure, 2-side wall panel, 3-top cover, 4-big cabin door, 5-small cabin door;
11-upright post component, 12-cross beam, 13-top beam, 14-middle beam, 15-bottom beam, 16-bottom plate, 17-center ring, 18-top plate and 19-upright post interface component;
111-upright column, 112-middle rib reinforcing plate, 113-upright column reinforcing rib and 114-transition surface;
161-bottom plate surface, 162-section bar, 163-base;
51-hatch cover, 52-hinge, 53-base, 54-quick locking mechanism;
541-mounting seat, 542-rotating pin, 543-rotating rod, 544-bolt, 545-handle and 546-locking block.
Detailed Description
In order to make the aforementioned objects, features and advantages of the present application more comprehensible, the present application is described in further detail with reference to specific embodiments.
Example 1
A test chamber for aerospace garment testing, as shown in fig. 1, comprising: the structure comprises a framework structure 1, a side wall panel 2, a top cover 3, a big cabin door 4 and a small cabin door 5.
As shown in fig. 2, the skeleton structure 1 is a main body frame structure of a negative pressure cabin, and a side wall panel 2, a top cover 3 and a large cabin door 4 are all fixed on the skeleton structure 1. The skeleton structure 1 includes: the vertical column assembly 11, the cross beam 12, the top beam 13, the middle beam 14, the bottom beam 15, the bottom plate 16, the center ring 17, the top plate 18 and the vertical column interface assembly 19; the lower portion of the upright post component 11 is inserted into the bottom plate component 16 and fixed with the bottom plate, the upper portion of the upright post component 11 is fixedly connected with the top plate 18, two sides of the upright post component 11 are fixedly connected with the top beam 13, the middle beam 14 and the bottom beam 15, the lower portion of the bottom beam 15 is fixedly connected with the bottom plate 16, the lower interface of the upright post interface component 19 is inserted into the upright post component 11 and is fixedly connected with the upper surface of the top plate 18, and two ends of the cross beam 12 are fixedly connected with the center ring 17 and the upright post interface component 19 respectively. The framework structure 1 is mainly used for ensuring the structural stability of the test chamber when the test chamber bears relative negative pressure.
As shown in FIG. 3, the pillar assembly 11 includes a pillar 111, a center rib reinforcement plate 112, a pillar reinforcement rib 113, and a transition surface 114. The upright column 111 is a main bearing part, in order to prevent the instability of the upright column 111 under the condition of pressure, the upright column reinforcing rib 113 is fixedly connected to the outer side of the upright column 111, the transition surface 114 is fixedly connected with the upright column reinforcing rib 113, force is transmitted to the upright column reinforcing rib 113 and the upright column 111 when the test chamber is pressurized, and the bearing capacity of the test chamber is enhanced. The middle rib reinforcing plate 112 is fixedly connected with two end faces of the middle beam 14, and mainly bears the force transmitted by the compression of the middle beam 14, so that the stress concentration of the upright post reinforcing rib 113 is reduced. As the main bearing structure of the test chamber, the connection between the cross beam 12 and the upright post assembly 11 is realized through the upright post interface assembly 19, and the cross beam 12 and the bottom plate 16 provide radial support for the test chamber structure, so that the structural damage caused by the inclination of the upright post assembly 11 is avoided. Meanwhile, the upright post assemblies 11, the top beams 13, the middle beams 14 and the bottom beams 15 provide installation supporting surfaces for the side wall panels 2, the top cover 3, the large cabin door 4 and the small cabin door 5, and the structural integrity is guaranteed.
As shown in fig. 4, the bottom plate 16 is composed of a bottom plate surface 161, a profile 162 and a base 163, the base 163 is fixedly connected to the bottom plate surface 161 to provide an installation interface for the pillar assembly 11, and the profile 162 is fixedly connected to the bottom plate surface 161 and the base 163 to play a role in reinforcement, so that the deformation of the bottom plate 16 caused by pressure and concavity can be effectively improved.
The side wall panel 2 is made of plates, the acrylic plates can be selected for processing in consideration of strength, quality and visualization requirements, and the side wall panel is fixed on a mounting surface through screws. Through holes are formed in part of the side wall panels 2, small cabin doors 5 are installed at the through holes, transportation test equipment and personnel can conveniently enter and exit the test cabin, and the side wall panels 2 are mainly used as compression surfaces of the test cabin.
The top cover 3 is of a special-shaped curved surface structure, the glass fiber reinforced plastic material can be selected in consideration of the pressure bearing performance, the strength and the quality requirement of the top cover, the top cover 3 is fixed on the top plate 18 through bolts, and the structural sealing performance is kept by pressing the sealing gasket between the top cover 3 and the top plate 18.
The large cabin door 4 is mainly used as an installation interface of the space suit. The trunk structure of the space suit and the structure are arranged to achieve the effect of communicating the inside of the space suit with the outside atmosphere, and meanwhile, a sealing gasket is arranged at the mounting interface to keep the sealing performance of the structure. The cabin door 4 is also provided with a cabin penetrating flange which is used as a circuit and gas circuit interface, and the circuit interface is mainly used for carrying out real-time monitoring on cabin pressure and power supply and distribution of test equipment in the cabin; the air path interface is connected with a pressure pumping and compensating device, and a pressure environment of relative negative pressure in the chamber is constructed by reducing the internal pressure of the test chamber, so that the positive pressure difference inside and outside the garment is ensured, and the simulation of the use state of the garment is realized. In the test process, the body of the subject is attached with a sensor to carry out the clothes test, the specified test operation is completed, the test result is transmitted and fed back in real time, and the motion characteristic of the space suit can be objectively and accurately evaluated.
As shown in fig. 5, the hatch 5 comprises a hatch 51, hinges 52, a base 53 and a quick-locking mechanism 54. The base 53 is fixedly arranged at the position of the opening of the side wall panel 2, and the opening and closing of the hatch cover and the base 53 are realized through the hinge 52; the quick-locking mechanism 54 is used to lock the hatch 51 and the base 53.
As shown in fig. 6, the quick lock mechanism 54 includes a mounting seat 541, a rotation pin 542, a rotation lever 543, a bolt 544, a handle 545, and a lock block 546. The mounting seat 541 is fixed at the edge of the hatch 51 and used as a mounting support of the quick locking mechanism 54; the locking block 546 is connected with the hatch 51 through a bolt 544, the handle 545 can rotate around the rotating pin 542, the rotating rod 543 is in threaded fit with the handle 545, and after the hatch 51 is closed, the locking block 546 is extruded by screwing the threads of the rotating rod 543 to achieve the effect of locking the hatch 5.
The working process is as follows:
based on typical actions of the out-of-cabin activities, kinematic data related to 5-degree-of-freedom complex motions of the upper limbs are obtained, input is provided for upper limb mechanics simulation of a human garment system, and a human-garment operation capability test is carried out. The test mainly simulates the action process of collecting, observing and collecting samples by astronauts in space.
The test is carried out by a subject wearing an aerospace suit in the test chamber device.
And in the test preparation stage, the space suit is arranged according to the motion characteristic test principle diagram 7 of the space suit to connect the pipeline and the circuit. The examinee is pasted with the electromyographic sensor at the position shown in the sensor pasting position schematic diagram 8, and after the sensor is pasted and the line connection is completed, the examinee penetrates into the clothes from the back of the space suit from the opening of the big cabin door of the test cabin.
In the test process, the vacuum pump and the air compressor are started, the internal pressure of the test cabin is reduced and finally maintained at a specific test pressure value, and the simulation of the real pressure environment in the space is completed.
In order to simulate the action process of collecting, observing and collecting samples, the test designs the complex movement with the degree of freedom of the upper limbs 5. The 5 degrees of freedom of the upper limb mainly comprise adduction/abduction of the shoulder joint, anteflexion/retroflexion of the shoulder joint, external rotation/internal rotation of the shoulder joint, flexion/extension of the elbow joint and external rotation/internal rotation of the forearm. The series of actions can be simplified into picking up the sample from a designated position far from the right side (fig. 9), taking the sample to the front of the eye for observation (fig. 10), and placing the sample at a designated position near the front side (fig. 11).
After the test subject finishes the action process, the vacuum pump is turned off, the pressure in the test chamber is gradually recovered by adjusting the flow of the air compressor, after the pressure in the test chamber is recovered to the atmospheric pressure, the air compressor is turned off, the test subject penetrates out of the clothes from the back of the space suit, the data returned by the sensor test are stored, the sensor is detached, the test site is arranged, and the test is finished.
Experimental test data show the values of the angles of motion in 5 degrees of freedom for the upper limb during one entire motion cycle of the subject simulating acquisition-observation-collection of samples, fig. 12 shows the values of the angles of motion in the motion cycle for 3 degrees of freedom for adduction/abduction, flexion/retroflexion, and supination/pronation of the shoulder joint, and fig. 13 shows the values of the angles of motion in the motion cycle for flexion/extension of the elbow joint and 2 degrees of freedom for supination/pronation of the forearm.
The test data of the human-clothing operational capability test performed in this test chamber show that:
1. the semi-open mode pressure simulation of the test chamber equipment is effective 2, the interior of the space suit is communicated with the atmosphere in the test process, a subject feels good in the test process, and the safety of people is guaranteed;
3. the sensor adhered to the skin of the subject is small in size, the influence on the operation of the person is small, the subjective operability of the person in the test process is good, and the operability is improved;
4. the data curve in the test process is smooth and has no mutation, the acquisition and return are accurate and real-time, and the test testability is improved.
The above detailed description is intended to illustrate the objects, aspects and advantages of the present invention, and it should be understood that the above detailed description is only exemplary of the present invention and is not intended to limit the scope of the present invention, and any modifications, equivalents, improvements and the like made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (7)
1. A test chamber for testing of space suits, characterized in that: the method comprises the following steps: the device comprises a framework structure (1), a side wall panel (2), a top cover (3), a large cabin door (4) and a small cabin door (5);
the framework structure (1) is a main body framework structure of the negative pressure cabin, and the side wall panel (2), the top cover (3) and the large cabin door (4) are all fixed on the framework structure (1); the skeleton structure (1) comprises: the device comprises a column assembly (11), a cross beam (12), a top beam (13), a middle beam (14), a bottom beam (15), a bottom plate (16), a center ring (17), a top plate (18) and a column interface assembly (19); the lower part of an upright post assembly (11) is inserted into a bottom plate assembly (16) and fixed with a bottom plate, the upper part of the upright post assembly (11) is fixedly connected with a top plate (18), the two sides of the upright post assembly (11) are fixedly connected with a top beam (13), a middle beam (14) and a bottom beam (15), the lower part of the bottom beam (15) is fixedly connected with the bottom plate (16), a lower interface of an upright post interface assembly (19) is inserted into the upright post assembly (11), the lower part of the upright post interface assembly is fixedly connected with the upper surface of the top plate (18), and the two ends of a cross beam (12) are respectively fixedly connected with a central ring (17) and an upright; the framework structure (1) is mainly used for ensuring the structural stability of the test chamber when the test chamber bears relative negative pressure;
the upright post assembly (11) comprises upright posts (111), a middle rib reinforcing plate (112), upright post reinforcing ribs (113) and transition surfaces (114); the upright (111) is a main bearing part, in order to prevent the instability of the upright (111) under the condition of pressure, the outer side of the upright (111) is fixedly connected with an upright reinforcing rib (113), the transition surface (114) is fixedly connected with the upright reinforcing rib (113), and force is transferred to the upright reinforcing rib (113) and the upright (111) when the test chamber is pressurized, so that the bearing capacity of the test chamber is enhanced; the middle rib reinforcing plate (112) is fixedly connected with two end faces of the middle beam (14), and is mainly used for bearing the force transmitted by the middle beam (14) under pressure, so that the stress concentration of the upright post reinforcing rib (113) is reduced; as the main bearing structure of the test chamber, the connection between the beam (12) and the upright post component (11) is realized through the upright post interface component (19), and the beam (12) and the bottom plate (16) provide radial support for the test chamber structure, so that the structural damage caused by the inclination of the upright post component (11) is avoided; meanwhile, the upright post assembly (11), the top beam (13), the middle beam (14) and the bottom beam (15) provide mounting support surfaces for the side wall panel (2), the top cover (3), the large cabin door (4) and the small cabin door (5), and the structural integrity is guaranteed;
bottom plate (16) comprise bottom plate face (161), section bar (162), base (163), and base (163) and bottom plate face (161) fixed connection provide the installation interface for stand subassembly (11), and section bar (162) and bottom plate face (161) and base (163) fixed connection play the stiffening, can effectively improve bottom plate (16) pressurized indent deformation condition.
2. A test chamber for testing of space suits according to claim 1, wherein: the side wall panel (2) is made of a plate, an acrylic plate can be selected for processing in consideration of strength, quality and visualization requirements, and the side wall panel is fixed on a mounting surface through screws; through holes are formed in part of the side wall panels (2), small cabin doors (5) are installed at the through holes, transportation test equipment and personnel can conveniently enter and exit the test cabin, and the side wall panels (2) are mainly used as compression surfaces of the test cabin.
3. A test chamber for testing of space suits according to claim 1, wherein: the top cover (3) is of a special-shaped curved surface structure, the glass fiber reinforced plastic material can be selected in consideration of the pressure bearing performance, the strength and the quality requirement of the top cover, the top cover (3) is fixed on the top plate (18) through bolts, and the structural sealing performance is kept by pressing the sealing gasket between the top cover (3) and the top plate (18).
4. A test chamber for testing of space suits according to claim 1, wherein: the large cabin door (4) is mainly used as an installation interface of the space suit; the trunk structure of the space suit is arranged with the structure to achieve the effect of communicating the interior of the space suit with the outside atmosphere, and meanwhile, a sealing gasket is arranged at the mounting interface to keep the sealing performance of the structure; the cabin door (4) is also provided with a cabin penetrating flange which is used as a circuit and gas circuit interface, and the circuit interface is mainly used for carrying out real-time monitoring on cabin pressure and power supply and distribution of test equipment in the cabin; the air path interface is connected with a pumping pressure and pressure compensation device, and a pressure environment of relative negative pressure in the chamber is constructed by reducing the internal pressure of the test chamber, so that the positive pressure difference between the inside and the outside of the garment is ensured, and the simulation of the use state of the garment is realized; in the test process, the body of the subject is attached with a sensor to carry out the clothes test, the specified test operation is completed, the test result is transmitted and fed back in real time, and the motion characteristic of the space suit can be objectively and accurately evaluated.
5. A test chamber for testing of space suits according to claim 1, wherein: the small cabin door (5) comprises a cabin cover (51), a hinge (52), a base (53) and a quick locking mechanism (54); the base (53) is fixedly arranged at the position of the opening of the side wall panel (2), and the hatch cover and the base (53) are opened and closed through a hinge (52); the quick locking mechanism (54) is used for locking the hatch cover (51) and the base (53).
6. A test chamber for testing of space suits according to claim 1, wherein: the quick locking mechanism (54) comprises an installation seat (541), a rotating pin (542), a rotating rod (543), a bolt (544), a handle (545) and a locking block (546); the mounting seat (541) is fixed at the edge of the hatch cover (51) and is used as a mounting support of the quick locking mechanism (54); the locking block (546) is connected with the hatch cover (51) through a bolt (544), the handle (545) rotates around the rotating pin (542), the rotating rod (543) is in threaded fit with the handle (545), and after the hatch cover (51) is closed, the locking block (546) is squeezed to achieve the effect of locking the hatch door (5) by screwing the threads of the rotating rod (543).
7. The method for accurately testing the motion characteristics of the space suit by using the test chamber for the test of the space suit as claimed in claim 1, wherein: realizing semi-open type clothing pressure simulation by using test cabin equipment;
before testing, connecting pipelines and circuits; the vacuum pump, the air compressor and the cabin pressure monitoring equipment are communicated with the test cabin through a test cabin penetrating flange; meanwhile, a test subject installs a sensor at a position to be measured on the body of the test subject and penetrates into the suit from the back of the space suit from an opening of a big cabin door (4) of the test cabin; a circuit of the sensor penetrates through an opening communicated with the outside atmosphere on the back of the space suit and is connected with an input end of the information acquisition equipment, and a signal acquired by the sensor is transmitted back to the information acquisition equipment in real time through the circuit; the cabin pressure monitoring equipment is used for feeding back and monitoring the internal pressure in the experiment cabin and the relative pressure in the clothing in real time;
in the test process, the vacuum pump and the air compressor are simultaneously opened and are always in a working state; the air inlet flow of the air compressor is adjusted to reduce the pressure in the test chamber, and finally the pressure in the test chamber is maintained at a test pressure value, so that the simulation of the real pressure environment of the clothes is completed; after the simulation of the pressure environment is completed, the subject performs a series of specified test actions in the clothing, and test data are accurately transmitted back to the information acquisition equipment in real time through the sensor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911385307.7A CN111044365B (en) | 2019-12-28 | 2019-12-28 | Test cabin for testing space suit |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911385307.7A CN111044365B (en) | 2019-12-28 | 2019-12-28 | Test cabin for testing space suit |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111044365A true CN111044365A (en) | 2020-04-21 |
| CN111044365B CN111044365B (en) | 2022-05-10 |
Family
ID=70240957
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911385307.7A Active CN111044365B (en) | 2019-12-28 | 2019-12-28 | Test cabin for testing space suit |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111044365B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111044401A (en) * | 2019-12-28 | 2020-04-21 | 中国人民解放军63919部队 | Portable dust abrasion testing device with vacuum chamber |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6216984B1 (en) * | 1999-10-15 | 2001-04-17 | Akbar F. Brinsmade | Gravity habitat module for space vehicle |
| CN105594315B (en) * | 2013-02-05 | 2015-07-15 | 上海卫星工程研究所 | A kind of satellite structure of assembling fast |
| CN107963241A (en) * | 2017-12-21 | 2018-04-27 | 中国科学院沈阳自动化研究所 | Developing space inflation bay section |
| US20180186479A1 (en) * | 2015-09-13 | 2018-07-05 | Michael David Johnson | Spacecraft systems airlock for international space station access and interface and methods of operation |
| CN110076010A (en) * | 2019-04-28 | 2019-08-02 | 浙江大学 | Superelevation gravity geotechnique's centrifugal device vacuum cavity structure |
-
2019
- 2019-12-28 CN CN201911385307.7A patent/CN111044365B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6216984B1 (en) * | 1999-10-15 | 2001-04-17 | Akbar F. Brinsmade | Gravity habitat module for space vehicle |
| CN105594315B (en) * | 2013-02-05 | 2015-07-15 | 上海卫星工程研究所 | A kind of satellite structure of assembling fast |
| US20180186479A1 (en) * | 2015-09-13 | 2018-07-05 | Michael David Johnson | Spacecraft systems airlock for international space station access and interface and methods of operation |
| CN107963241A (en) * | 2017-12-21 | 2018-04-27 | 中国科学院沈阳自动化研究所 | Developing space inflation bay section |
| CN110076010A (en) * | 2019-04-28 | 2019-08-02 | 浙江大学 | Superelevation gravity geotechnique's centrifugal device vacuum cavity structure |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111044401A (en) * | 2019-12-28 | 2020-04-21 | 中国人民解放军63919部队 | Portable dust abrasion testing device with vacuum chamber |
Also Published As
| Publication number | Publication date |
|---|---|
| CN111044365B (en) | 2022-05-10 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111044365B (en) | Test cabin for testing space suit | |
| CN107215488B (en) | A kind of manned spacecraft repairs ground total factor simulation system out of my cabin | |
| CN208383632U (en) | Environmental chamber at low temperature for split hopkinson press bar experimental rig | |
| CN107255938A (en) | A kind of outer maintainable technology on-orbit ground quick response of spacecraft module supports method | |
| CN112432795A (en) | Dummy for children | |
| CN107714357A (en) | A kind of high original course civil aircraft boiler-plate and its method for building up | |
| Cañas et al. | A new in situ peeling test for the characterisation of composite bonded joints | |
| Bertolini et al. | Multi-level experimental and numerical analysis of composite stiffener debonding. Part 2: Element and panel level | |
| Kermanidis et al. | Bird strike simulation on a novel composite leading edge design | |
| Cabrera et al. | Seeing the Big Picture: Improving the prosthetic design cycle using 360 3D digital image correlation | |
| Ross | Z-1 prototype space suit testing summary | |
| Young et al. | Residual strength pressure tests and nonlinear analyses of stringer-and frame-stiffened aluminum fuselage panels with longitudinal cracks | |
| CN203520744U (en) | Universal loading device for ankle | |
| DE10232216A1 (en) | Device for putting on a protective suit | |
| CN207248608U (en) | A kind of external bionical power of shoulder joint loads and its Function detection experiment porch | |
| CN208921355U (en) | A kind of wing body Butt sealing experimental cabin | |
| Chen et al. | Stress singularity coefficients in an infinite plate containing rigid line and applied by concentrated forces | |
| CN207147866U (en) | A kind of creep ageing two-direction pull press experimental rig | |
| Boyle et al. | Suitport Feasibility-Development and Test of a Suitport and Space Suit for Human Pressurized Space Suit Donning Tests | |
| Sublett | Fault-tolerance in Human Exploration Systems | |
| CN211568283U (en) | Observation port cover | |
| White | Manufacturing and Structural Characterization of Flexible and Dual-Matrix Deployable Composites for Space Application. | |
| Chambers et al. | 3-D Woven Preform Joint Experimental Testing Results to Support the D8 Double-Bubble Composite Fuselage Design | |
| CN213632859U (en) | Sealed air pressure sampling device of full liquefaction air separation system | |
| Tserpes et al. | The structural integrity of a novel composite adhesively bonded flap-track beam |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |