A device and method for comprehensive testing optical performance of extravehicular space suit helmet window

Abstract

The present invention relates to an optical performance comprehensive test device and method for an extravehicular space suit helmet visor. A mounting seat is provided on the chassis of the test device to provide a sealing interface for installing the extravehicular space suit; an operating mechanism includes an active shaft, a driven shaft and a base; the active shaft is connected to the output drive shaft through a turntable adapter and is arranged inside the extravehicular space suit; the driven shaft is installed on the transmission shaft on the lower surface of the turntable and is arranged outside the extravehicular space suit; a signal transmitting unit is installed on the driven shaft, and a signal receiving unit is installed on the active shaft; a control unit controls the operating mechanism, adjusts the positions of the signal transmitting unit and the signal receiving unit, and measures the optical performance parameters of the extravehicular space suit helmet visor based on the signal transmitted by the signal receiving unit. The present invention realizes the overall optical performance test of the helmet visor under two working conditions of the extravehicular space suit with and without air pressure filling, including the test of light transmittance, haze, angular deviation and optical distortion; and ensures the reliability of product acceptance and delivery.

Description

Technical Field

[0001] The present invention relates to the field of manned space technology, and in particular to a device and method for comprehensively testing the optical performance of a helmet face window of an extravehicular space suit. Background Art

[0002] The extravehicular space suit is an essential equipment for astronauts when performing extravehicular missions in orbit, and the helmet visor is the only window for astronauts to directly observe and understand the outside world when performing extravehicular missions after wearing the extravehicular space suit. It integrates multiple functions such as pressure protection, visual protection, thermal protection, and visual ergonomics assurance in harsh space environments such as extreme high / low temperature, vacuum, and radiation. Visual protection and visual ergonomics assurance functions are its unique special protection functions.

[0003] The helmet visor is a multi-layered window structure from the inside to the outside. Whether its overall optical performance, including light transmittance, haze, light distortion, and angular deviation, meets the requirements is the basic condition for astronauts to successfully carry out space missions and is also the guarantee for astronauts to perform refined operations. Therefore, during the ground assembly, integration, acceptance and delivery of space suits, the optical performance of the helmet visor is the key point of testing and assessment. Summary of the invention

[0004] In order to solve the problem of comprehensive testing of optical properties of helmet visors during the development and product acceptance and delivery of extravehicular space suits, the present invention provides a device and method for comprehensive testing of optical properties of helmet visors of extravehicular space suits. During the measurement process, non-contact between the instrument and the visor is required to prevent the visor from being bumped and scratched. Measurement of the inside of the clothing helmet under two working conditions, with and without pressure, is achieved, with accurate testing and convenient operation.

[0005] In order to achieve the above-mentioned object, the present invention provides an optical performance comprehensive test device for an extravehicular space suit helmet window, comprising a signal transmitting unit, a signal receiving unit, a chassis, an operating mechanism and a control unit;

[0006] The chassis is provided with a mounting seat, and the mounting seat provides a sealing interface for mounting an extravehicular space suit;

[0007] The operating mechanism comprises a driving shaft, a driven shaft and a base; the base outputs a driving shaft connected to the driving shaft, and the base can drive the driving shaft to translate horizontally in the X direction, translate horizontally in the Y direction, and rotate around the vertical Z axis; the driven shaft is fixed to the base output driving shaft and is arranged outside the extravehicular space suit, and moves synchronously with the driving shaft;

[0008] The signal transmitting unit is installed on the driven shaft; the signal receiving unit is installed on the driving shaft; the light emitted by the signal transmitting unit passes through the helmet window of the extravehicular space suit and is received by the signal receiving unit;

[0009] The control unit controls the operating mechanism, adjusts the signal transmitting unit and the position of the signal receiving unit, and measures the optical performance parameters of the helmet window of the extravehicular space suit based on the signal transmitted by the signal receiving unit.

[0010] Furthermore, the chassis includes a pressure plate, a turntable, a packing sealing strip and a support plate; the support plate is fixedly supported by a truss; the pressure plate is a circular plate structure with a central circular hole, the outer ring of the pressure plate is fixed on the flanged flange of the support plate, the pressure plate and the support plate form a accommodating space, and the turntable is arranged in the accommodating space; the central circular hole of the pressure plate provides an operating space for horizontal translation and rotation around a vertical Z-axis for a driving shaft that passes through the hole and is fixedly connected to the turntable; a transmission shaft is designed at the center of the upper and lower surfaces of the turntable, which is fixedly connected to the output drive shaft on the base of the operating mechanism through the transmission shaft at the center of the lower surface, and the transmission shaft at the center of the upper surface is fixedly connected to the driving shaft; a double sealing groove along the circumferential direction is provided on the lower surface of the turntable, and a packing sealing strip is installed in the sealing groove, so that a dynamic seal is formed between the turntable and the support plate during the rotational movement around the Z-axis and the horizontal translation in the X and Y directions.

[0011] Furthermore, a mounting seat is fixedly and sealingly mounted on the upper surface of the pressure plate, and a gas pipeline nozzle is arranged on the cylindrical wall of the mounting seat for filling and releasing the gas pressure inside the garment.

[0012] Furthermore, the driving shaft is fixed to the transmission shaft at the center of the upper surface of the turntable, rotates and translates horizontally with the turntable, and the transmission shaft on the upper surface of the turntable is arranged inside the mounting seat; a first moving component is arranged on the driving shaft, and the first moving component is used to adjust the height of the signal receiving unit, the angle between the vertical plane and the vertical Z axis, and the distance between the signal receiving unit and the surface window; the driven shaft is parallel to the driving shaft, and the driven shaft is provided with a second moving component, and the second moving component is used to adjust the height of the signal emitting unit, the distance between the signal emitting unit and the surface window, and adjust the optical axis between the signal receiving unit and the emitting unit to be coaxial.

[0013] Furthermore, the signal transmitting unit comprises: a standard C light source, a collimating lens and a target plate;

[0014] The standard C light source emits light after being powered on, and the emitted light forms parallel light after passing through the collimating lens, and the transmitted light of the parallel light after passing through the face window of the helmet of the extravehicular space suit being tested is captured and collected by the signal receiving unit, so as to be used for the light transmittance and haze test of the face window of the helmet of the extravehicular space suit;

[0015] The target plate is a flat glass sheet with a uniformly distributed black dot matrix printed on it; the parallel light passes through the dot matrix and then through the visor of the space suit helmet outside the cabin to be captured and collected by the signal receiving unit and compared with the actual distribution of the dot matrix, so as to test the light distortion and angular deviation of the visor of the space suit helmet.

[0016] Furthermore, the signal receiving unit comprises: an integrating sphere, an optical fiber, a spectrometer, a CCD camera and a distance sensor;

[0017] The CCD camera collects a new dot matrix image formed by the high-precision dot matrix on the target plate of the transmitting unit through the space suit helmet window outside the cabin, and uses the change information of the corresponding points in the new dot matrix and the dot matrix of the target plate to calculate the light distortion and angular deviation of the space suit helmet window through the software equipped by the control unit;

[0018] The integrating sphere is provided with a light inlet hole at the front, a light trap at the rear, and a test hole at the top, and the tail of the test hole is connected to the spectrometer through an optical fiber; the light trap at the rear of the integrating sphere is connected to a reflector and a shutter motor, and when the reflector covers the light trap under the action of the shutter motor, the transmitted light is collected through the test hole at the top of the integrating sphere, and the transmitted light is transmitted to the spectrometer through the optical fiber at the tail of the test hole to complete the analysis and calculation of the transmitted light flux; when the reflector is evacuated from the light trap under the action of the shutter motor, the scattered light is collected through the test hole at the top of the integrating sphere, and the scattered light is transmitted to the spectrometer through the optical fiber at the tail of the test hole to complete the analysis and calculation of the scattered light flux; the software equipped by the control unit calculates the light transmittance and haze of the space suit helmet face window based on the light flux;

[0019] The distance sensor is used to collect the distance between the space suit helmet window outside the cabin and scan the pressure window inside the space suit helmet window.

[0020] Furthermore, the control unit performs three-dimensional modeling of the space suit helmet visor based on scanning of the pressure window inside the space suit helmet visor.

[0021] Furthermore, the control unit, without placing the visor of the space suit helmet outside the cabin, turns on the standard C light source of the signal transmitting unit, the integrating sphere and the spectrometer of the signal receiving unit, and adjusts the light emitted by the standard C light source so that all the light passes through the light inlet hole at the front end of the integrating sphere, turns on the shutter motor of the integrating sphere so that the reflector connected to the shutter motor covers the light trap of the integrating sphere; the light collected by the test hole at the top of the integrating sphere is introduced into the spectrometer via the optical fiber, and the luminous flux T1 is calculated by the spectrometer; when the reflector connected to the shutter motor is evacuated from the light trap of the integrating sphere, the light collected by the test hole at the top of the integrating sphere is introduced into the spectrometer via the optical fiber, and the luminous flux T3 is calculated by the spectrometer; the CCD camera and the target plate are adjusted so that the center point of the dot matrix on the target plate is located at the center of the field of view of the CCD camera, and the CCD camera collects the original dot matrix image of the dot matrix on the target;

[0022] With the space suit helmet visor placed outside the cabin, the standard C light source of the signal transmitting unit, the integrating sphere and the spectrometer of the signal receiving unit are turned on, and the light emitted by the standard C light source is adjusted so that all the light passes through the light inlet hole at the front end of the integrating sphere, and the shutter motor of the integrating sphere is turned on so that the reflector connected to the shutter motor covers the light trap of the integrating sphere; the light collected from the test hole at the top of the integrating sphere is introduced into the spectrometer through the optical fiber, and the luminous flux T2 is calculated by the spectrometer; when the reflector connected to the shutter motor is removed from the integrating sphere light trap, the light collected from the test hole at the top of the integrating sphere is introduced into the spectrometer through the optical fiber, and the luminous flux T4 is calculated by the spectrometer; the CCD camera takes pictures to collect the new dot matrix image of the dot matrix on the target after passing through the space suit helmet visor;

[0023] Calculate light transmittance Haze

[0024] According to the original dot matrix image and the new dot matrix image taken by the CCD camera, the center O of the center origin of the target plate is obtained. i The angular deviation component E from the X-axis of the center of the detection plate ix , O captured by CCD camera i The angular deviation component E from the Y axis of the center of the detection plate iy , i is the incident angle, calculate the angular deviation

[0025] Adjust the operating mechanism to keep the CCD camera and the target plate moving synchronously. When the line connecting the center of the CCD camera's field of view and the center point of the target plate's dot matrix passes through the newly selected window test point, take a picture and calculate the angular deviation of the newly selected window test point until the angular deviation test of all test points is completed.

[0026] Measure the optical distortion value of the current window measurement point: currently, the center origin of the target plate is taken as the initial position. Every time it moves to a new position, the CCD camera captures a dot matrix image. For the collected dot matrix images, the software automatically identifies and calculates the X-axis offset and Y-axis offset of the center point on each dot matrix image. The maximum X-axis offset Max x and the minimum offset Min x, the maximum Y-axis offset Max y and the minimum offset Min y are obtained respectively. The difference between the maximum and minimum values ​​of the X-axis upward angular deviation θMax x-θMin x, and the difference between the maximum and minimum values ​​of the Y-axis upward angular deviation θMax y-θMin y are calculated, and the larger difference is used as the optical distortion value of the window at the measurement location. Among them, θMax x and θMin x are the angular deviation components E of the center origin of the target plate captured by the CCD after the window is placed, which deviate from the original target plate center point on the X-axis ix The maximum and minimum values ​​of θMax y and θMin y are the angular deviation components E of the center point of the target plate captured by CCD after the window is placed, which deviates from the original center point of the target plate on the y-axis. iy The maximum and minimum values ​​of ;

[0027] Reset to the initial position, reselect the window test point, adjust the operating mechanism to keep the CCD camera and the target plate moving synchronously, and when the line connecting the center of the CCD camera field of view and the center point of the target plate dot matrix passes through the reselected window test point, measure the light distortion value of the current window measurement point until the light distortion value measurement of all window measurement points is completed.

[0028] On the other hand, a method for performing a comprehensive optical performance test using the optical performance comprehensive testing device for an extravehicular space suit helmet face window is provided, comprising:

[0029] Mountings for attaching an extravehicular space suit to the chassis;

[0030] Adjust the position and rotation angle of the active shaft through the operating mechanism base so that the axis of the distance sensor on the active shaft signal receiving unit is basically consistent with the longitudinal neutral plane of the clothing; adjust the height of the signal receiving unit on the active shaft so that the axis of the distance sensor is basically consistent with the center height of the face window; adjust the distance between the distance sensor on the signal receiving unit and the face window so that the distance sensor can collect the distance between the distance sensor and the face window; at each height, scan the pressure face window in the face window of the space suit helmet in the horizontal direction with a set step length;

[0031] Adjust the height of the signal transmitting unit on the driven shaft so that the axis of the distance sensor on the signal transmitting unit is substantially consistent with the height of the center of the face window; adjust the distance between the distance sensor on the signal transmitting unit and the face window so that the distance sensor on the signal transmitting unit can collect the distance between the distance sensor and the face window; at each height, scan the pressure face window outside the space suit helmet face window in the horizontal direction with a set step length; and perform three-dimensional modeling of the space suit helmet face window by the control unit;

[0032] Adjust the positions of the signal transmitting unit and the signal receiving unit so that the light emitted by the optical fiber emitted by the signal transmitting unit can be fully immersed in the light inlet hole of the integrating sphere of the signal receiving unit;

[0033] The control unit measures the optical performance parameters of the helmet window of the extravehicular space suit based on the signal transmitted by the signal receiving unit.

[0034] Furthermore, it also includes: filling gas into the extravehicular space suit until the pressure reaches the working pressure of the extravehicular space suit; and measuring the optical performance parameters of the helmet window of the extravehicular space suit again.

[0035] Furthermore, the optical performance parameters of the helmet window of the extravehicular space suit are measured, including:

[0036] Without placing the visor of the space suit helmet outside the cabin, turn on the standard C light source of the signal transmitting unit, the integrating sphere and the spectrometer of the signal receiving unit, adjust so that the light emitted by the standard C light source just passes through the light inlet hole at the front end of the integrating sphere, turn on the shutter motor of the integrating sphere so that the reflector connected to the shutter motor covers the light trap of the integrating sphere; the light collected from the test hole at the top of the integrating sphere is introduced into the spectrometer through the optical fiber, and the luminous flux T1 is calculated by the spectrometer; when the reflector connected to the shutter motor is removed from the light trap of the integrating sphere, the light collected from the test hole at the top of the integrating sphere is introduced into the spectrometer through the optical fiber, and the luminous flux T3 is calculated by the spectrometer; adjust the CCD camera and the target plate so that the center point of the dot matrix on the target plate is located at the center of the field of view of the CCD camera, and the CCD camera collects the original dot matrix image of the dot matrix on the target;

[0037] With the space suit helmet visor placed outside the cabin, the standard C light source of the signal transmitting unit, the integrating sphere and the spectrometer of the signal receiving unit are turned on, and the light emitted by the standard C light source is adjusted so that all the light passes through the light inlet hole at the front end of the integrating sphere, and the shutter motor of the integrating sphere is turned on so that the reflector connected to the shutter motor covers the light trap of the integrating sphere; the light collected from the test hole at the top of the integrating sphere is introduced into the spectrometer through the optical fiber, and the luminous flux T2 is calculated by the spectrometer; when the reflector connected to the shutter motor is removed from the integrating sphere light trap, the light collected from the test hole at the top of the integrating sphere is introduced into the spectrometer through the optical fiber, and the luminous flux T4 is calculated by the spectrometer; the CCD camera takes pictures to collect the new dot matrix image of the dot matrix on the target after passing through the space suit helmet visor;

[0038] Calculate light transmittance Haze

[0039] According to the original dot matrix image and the new dot matrix image taken by the CCD camera, the center O of the center origin of the target plate is obtained. i The angular deviation component E from the X-axis of the center of the detection plate ix , O captured by CCD camera i The angular deviation component E from the Y axis of the center of the detection plate iy , i is the incident angle, calculate the angular deviation

[0040] Measure the optical distortion value of the current window measurement point: currently take the center origin of the target plate as the initial position, move the target plate according to the step length of 1mm, scan the given area of ​​3mm×3mm, and each time it moves to a new position, the CCD camera takes a dot matrix image; for the collected dot matrix image, the software automatically identifies and calculates the X-axis offset and Y-axis offset of the center point on each dot matrix image; obtain the maximum X-axis offset Max x and the minimum offset Min x, the maximum Y-axis offset Max y and the minimum offset Min y respectively; calculate the difference between the maximum and minimum values ​​of the X-axis upward angular deviation θMax x-θMin x, and the difference between the maximum and minimum values ​​of the Y-axis upward angular deviation θMax y-θMin y, and use the larger difference as the optical distortion value of the window at the measurement location; where θMax x and θMin x are the angular deviation components E of the center origin of the target plate captured by the CCD after the window is placed, which deviate from the original target plate center point on the X-axis ix The maximum and minimum values ​​of θMax y and θMin y are the angular deviation components E of the center point of the target plate captured by CCD after the window is placed, which deviates from the original center point of the target plate on the y-axis. iy The maximum and minimum values ​​of ;

[0041] Reset to the initial position, reselect the window test point, adjust the operating mechanism to keep the CCD camera and the target plate moving synchronously, and when the line connecting the center of the CCD camera field of view and the center point of the target plate dot matrix passes through the reselected window test point, measure the light distortion value of the current window measurement point until the light distortion value measurement of all window measurement points is completed.

[0042] The above technical solution of the present invention has the following beneficial technical effects:

[0043] (1) The present invention realizes the overall optical performance test of the helmet visor under two working conditions: one is filled with air pressure and the other is not filled with air pressure, including the test of light transmittance, haze, angular deviation and optical distortion; thus, the reliability of product acceptance and delivery is ensured.

[0044] (2) The optical performance comprehensive testing device of the present invention has a simple structure, convenient operation and accurate measurement. BRIEF DESCRIPTION OF THE DRAWINGS

[0045] Figure 1 It is a diagram of the structure of the device of the present invention.

[0046] Figure 2 This is a diagram of the chassis sealing structure of the equipment of the present invention.

[0047] Figure 3 It is a schematic diagram of the components of the motion mechanism unit of the equipment of the present invention.

[0048] Figure 4 This is a diagram showing the composition of the signal receiving unit of the device of the present invention.

[0049] Figure 5 This is a structural diagram of the integrating sphere of the device of the present invention.

[0050] Figure 6 It is a schematic diagram of the signal transmitting unit and receiving unit of the device of the present invention.

[0051] Figure 7 It is a local point cloud image after the curved surface profiling of the window of the present invention.

[0052] Figure 8 The figure is a schematic diagram of the helmet face window angle deviation measurement algorithm of the present invention.

[0053] Fig. 9 This is a schematic diagram of the helmet window light distortion measurement principle of the present invention. DETAILED DESCRIPTION

[0054] In order to make the purpose, technical scheme and advantages of the present invention clearer, the present invention is further described in detail below in conjunction with specific embodiments and with reference to the accompanying drawings. It should be understood that these descriptions are only exemplary and are not intended to limit the scope of the present invention. In addition, in the following description, the description of well-known structures and technologies is omitted to avoid unnecessary confusion of the concept of the present invention.

[0055] like Figure 1 As shown, the optical performance comprehensive test device for the helmet window of an extravehicular space suit comprises a box 1, a truss 2, a chassis 3, a mounting seat 4, a running mechanism 5, a signal receiving unit 6, a signal transmitting unit 7 and a control unit. It can realize the test of four optical performance indicators, namely, light transmittance, haze, light distortion and angular deviation, of the overall window of the helmet window of the extravehicular suit under two working conditions: pressurized (gas pressure condition inside the suit) and unpressurized.

[0056] The chassis 3 is installed on the truss 2 inside the box body 1, and is composed of a pressure plate, a turntable, a packing sealing strip, and a support plate. Figure 2The pressure plate is a circular plate structure with a central circular hole. The outer ring of the pressure plate is fixed on the flanged flange of the support plate. The pressure plate and the support plate form a storage space, and the turntable is arranged in the storage space. The central circular hole of the pressure plate provides a running space for horizontal translation and rotation around the vertical Z axis for the driving shaft that passes through the hole and is fixedly connected to the turntable. The pressure plate and the support plate are fixed and stationary structures. The turntable is connected to the driving shaft of the operating mechanism 5 and performs planar rotational motion with the driving shaft. The driving shaft is the figure, Figure 2 The transmission shaft in is also called the C-axis. A transmission shaft is designed in the center of the upper and lower surfaces of the turntable. The transmission shaft in the center of the lower surface is fixedly connected to the output drive shaft on the base of the operating mechanism, and the transmission shaft in the center of the upper surface is fixedly connected to the active shaft. In order to ensure the optical performance test of the helmet visor under the condition of clothing pressure, a double sealing groove is designed on the lower surface of the turntable, and a packing sealing strip is installed in each sealing groove, so that a dynamic seal is formed between the lower surface of the turntable and the upper surface of the support plate during the rotational movement, thereby maintaining the gas pressure of the internal cavity formed between the clothing, the mounting seat 4, and the chassis 3, ensuring the clothing pressure state test. In addition, a tadpole-shaped oil tank is designed on the support plate. The oil stored in the oil tank can not only provide lubrication for the turntable movement, but also increase the sealing performance between the turntable and the support plate during the movement of the turntable.

[0057] The mounting seat 4 is an elliptical cylindrical structure, with a clothing mounting interface provided at the upper part, and a sealing and fixed connection to the chassis 3 at the lower part, and together with the clothing and the chassis 3, a sealed cavity is formed. A gas pipeline nozzle 4-1 is provided in the middle of the front wall of the mounting seat 4, which is used to fill and release the gas pressure in the internal cavity.

[0058] The operating mechanism 5 includes a driving shaft, a driven shaft and a base. The main part of the driving shaft is located inside the clothing, and the driven shaft is located outside the clothing. The two cooperate with each other under the control of the control unit to form a spatial contour motion mechanism with 9 degrees of freedom. Figure 3As shown, the profiling and testing of the extravehicular suit helmet visor is completed. The base can be translated in the horizontal X direction and the horizontal Y direction, and an output drive shaft rotating around the vertical Z axis is provided, so that the active shaft connected to the output drive shaft of the base has three degrees of freedom of movement; the active shaft is fixed to the transmission shaft at the center of the upper surface of the turntable, rotates and translates horizontally with the turntable, and the transmission shaft on the upper surface of the turntable is arranged inside the mounting seat; a first moving component is arranged on the active shaft, and a device for rotating in a vertical plane and feeding along the axis direction of the component is arranged on the moving component, which is used to adjust the height of the signal receiving unit, the rotation angle in the vertical direction and the distance between the signal receiving unit and the face window, so that the signal receiving unit has three degrees of freedom of movement; the driven shaft is parallel to the active shaft, and a second moving component is arranged on the driven shaft, and a device for rotating in a vertical plane and feeding along the axis direction of the component is arranged on the moving component, which is used to adjust the height of the signal transmitting unit, the distance between the signal receiving unit and the face window, and adjust the optical axis between the signal receiving unit and the transmitting unit to be coaxial, so that the signal transmitting unit also has three degrees of freedom of movement. Adjust the optical axis between the signal receiving unit and the transmitting unit to be coaxial, and the central control processing unit can collect the operating data of the transmitting unit optical device and combine the structural dimensions to automatically calculate the target position of the optical device corresponding to the receiving unit. It can also be adjusted manually, or it can be judged based on whether all the emitted light enters the light inlet of the integrating sphere.

[0059] The signal receiving unit 6 is installed on the driving shaft of the operating mechanism 5, and is mainly composed of an integrating sphere, an optical fiber, a spectrometer (Note: the spectrometer is set in the control unit cabinet), a distance sensor and a "CCD+lens", etc. Figure 4 The integrating sphere has a diameter of φ60mm, a light inlet hole with a diameter of φ10mm is arranged at the front, a light trap with a diameter of φ9.5mm is arranged at the rear, and a test hole is arranged at the top. The tail of the test hole is connected to the spectrometer through an optical fiber; the light trap at the rear of the integrating sphere is connected to the reflector and the shutter motor. When the reflector covers the light trap under the action of the shutter motor, the transmitted light is collected through the test hole at the top of the integrating sphere, and the optical fiber at the tail of the test hole is transmitted to the spectrometer to complete the analysis and calculation of the transmitted light flux; when the reflector is evacuated from the light trap under the action of the shutter motor, the scattered light is collected through the test hole at the top of the integrating sphere, and the optical fiber at the tail of the test hole is transmitted to the spectrometer to complete the analysis and calculation of the scattered light flux. Furthermore, the transmittance and haze of the space suit helmet window are calculated by the software equipped by the control unit.

[0060] In order to adapt to the narrow space inside the clothing, the integrating sphere is miniaturized on the basis of meeting the optical performance test (light transmittance, haze), and finally the integrating sphere diameter is φ60mm, the light inlet diameter is φ10mm, and the light trap opening diameter is φ9.5mm, achieving the characteristics of small integrating sphere space volume, automatic shutter, and high exit aperture accuracy. Figure 6 . The CCD uses a high-performance camera with 3.45um pixels, 2448×2048 pixels, and global shutter (frame exposure), and is equipped with a lens with a 65mm zoom and 2x optical magnification. The "CCD+lens" group can ensure the capture and collection of visual images during the test of the performance index of the helmet window light distortion and angular deviation. In order to ensure that the optical performance measurement of the helmet window is non-contact measurement, the distance sensor uses a spectral confocal sensor with a spot diameter of φ9μm, a linear range of 3mm, an absolute error of displacement measurement of 0.75μm, and a spectral resolution of 36nm, which is used to locate the receiving unit 6 during the test and prevent the instrument from contacting, bumping or scratching the window. The CCD camera uses the high-precision dot matrix on the target plate of the transmitting unit to form a new dot matrix image after passing through the space suit helmet window outside the cabin, and uses the change information of the corresponding points in the new dot matrix and the target plate dot matrix to calculate the light distortion and angular deviation of the space suit helmet window through the software equipped by the control unit.

[0061] The high-precision confocal spectral distance sensor installed on the operating mechanism 5 and the signal receiving unit 6, combined with the dedicated software algorithm on the control unit, can perform profiling scanning and discrete grid point reconstruction on the spatial curved surface of the window, thereby realizing the optical performance test of the specified point or area on the window. In the process of surface profiling scanning and reconstruction, automatic scanning and reconstruction can be performed according to the set area boundary and step size, or it can be performed by manually locating the acquisition point on the window.

[0062] The signal transmitting unit 7 is installed on the driven shaft of the operating mechanism 5, and is mainly composed of a "target plate", a "collimating lens + a standard C light source", such as Figure 6 The target plate is a flat glass sheet with a size of 40mm×40mm×2.3mm, on which is printed a diameter The target plate is used in conjunction with the CCD on the signal receiving unit 6 to complete the test of light distortion and angular deviation of the helmet window. The light source in the "collimating lens + light source" is a C light source that meets the requirements of the 1931 standard colorimetry of the International Commission on Illumination (CIE), and after the divergent light is converted into parallel light by the collimating lens at the front end, it is used in conjunction with the integrating sphere on the signal receiving unit 6 to complete the test of light transmittance and haze of the helmet window. The proximity sensor (the contact end is designed with a flexible contact surface) is used to locate the signal transmitting unit 7 during the test and to prevent the instrument from contacting, bumping or scratching the window, so as to ensure that the entire measurement is non-contact.

[0063] The control unit in the above technical solution is a cabinet structure, the upper part of the cabinet is a display operation table, and the lower part of the cabinet is equipped with an industrial computer, a spectrometer, and a distance sensor controller. The entire control unit is connected to the operating mechanism 5, the signal receiving unit 6, and the signal transmitting unit 7 inside the box 1 through a signal cable, and the "human-machine" interactive control software is used to control the operation of the entire device, input the excitation and signal acquisition and processing, and store and output the test results. The distance sensor controller is used in conjunction with the distance sensor. The working principle of the distance sensor is: the distance sensor emits a beam of complex light (white) with a wide spectrum, which is spectrally dispersed by the dispersion lens of the distance sensor itself to form different monochromatic lights, and each wavelength corresponds to a distance to the object to be measured. After the measuring light is reflected back from the surface of the object, only the (reflected) monochromatic light that meets the confocal condition can pass through the collection hole on the distance sensor itself and be introduced into the distance sensor controller through the optical fiber at the end of the sensor. The distance sensor controller inductively analyzes and reversely calculates the measuring distance between the distance sensor lens and the object to be measured.

[0064] Control unit optical performance test data processing and calculation:

[0065] The "human-machine" interactive control software of the control unit has algorithms for light transmittance / haze and algorithms for angular deviation / light distortion compiled into it.

[0066] The transmittance / haze test includes: the parallel light generated by the "standard C light source + collimating lens" of the signal transmitting unit enters the integrating sphere through the "light inlet" at the front end of the "integrating sphere" of the signal receiving unit without or after passing through the extravehicular space suit helmet window and is collected. It is then introduced by the "optical fiber" to the "spectrometer (Note: the spectrometer is placed in the control unit cabinet)" for analysis to obtain the incident light flux T1 or T3 and the scattered light flux T2 or T4. The analysis data can be calculated by the dedicated software of the control unit to obtain the transmittance and haze of the extravehicular space suit helmet window.

[0067] Light distortion / angular deviation test: The 5×5 dot matrix on the "target board" of the signal transmitting unit is collected by the signal receiving unit "CCD" without or after passing through the extravehicular space suit helmet window. After comparison and calculation by the dedicated software of the control unit, the light distortion and angular deviation of the extravehicular space suit helmet window can be obtained.

[0068] ①Transmittance / haze

[0069] The transmittance / haze is calculated according to GJB 1253 "Test Methods for Transmittance, Haze and Chromaticity of Transparent Materials": Transmittance calculation formula:

[0070] Without placing the visor of the space suit helmet outside the cabin, turn on the standard C light source of the signal transmitting unit, the integrating sphere and the spectrometer of the signal receiving unit, adjust so that the light emitted by the standard C light source just passes through the light inlet hole at the front end of the integrating sphere, turn on the integrating sphere shutter motor so that the reflector connected to the shutter motor covers the integrating sphere light trap; the light collected by the test hole at the top of the integrating sphere is introduced into the spectrometer through the optical fiber, and the luminous flux T1 is calculated by the spectrometer; when the reflector connected to the shutter motor is evacuated from the integrating sphere light trap, the light collected by the test hole at the top of the integrating sphere is introduced into the spectrometer through the optical fiber, and the luminous flux T3 is calculated by the spectrometer. With the visor of the extravehicular space suit helmet placed, the standard C light source of the signal transmitting unit, the integrating sphere and the spectrometer of the signal receiving unit are turned on, and the light emitted by the standard C light source is adjusted so that all the light passes through the light inlet hole at the front end of the integrating sphere, and the shutter motor of the integrating sphere is turned on so that the reflector connected to the shutter motor covers the integrating sphere light trap; the light collected by the test hole at the top of the integrating sphere is introduced into the spectrometer through the optical fiber, and the luminous flux T2 is calculated by the spectrometer; when the reflector connected to the shutter motor is evacuated from the integrating sphere light trap, the light collected by the test hole at the top of the integrating sphere is introduced into the spectrometer through the optical fiber, and the luminous flux T4 is calculated by the spectrometer.

[0071] Haze calculation formula:

[0072] Where T1 is the total incident light flux, T2 is the total transmitted light flux through the sample, T3 is the scattered light flux of the instrument, and T4 is the scattered light flux of the instrument and sample.

[0073] ②Angle deviation

[0074] The angular deviation is calculated according to the "collimation telescope measurement method" in GJB503 "General Test Methods for Aircraft Laminated Glass". The calculation formula for angular deviation is as follows:

[0075]

[0076] in,

[0077] In the formula, E i is the absolute value of the angular deviation vector (i is the incident angle), unit: second;

[0078] E ix To obtain the center O of the target plate center origin according to the original dot matrix image and the new dot matrix image captured by CCD i The angular deviation component from the center X axis of the detection plate, see Figure 8 ; where x1 is O i The offset of the point in the X-axis direction, in mm. d1 is the straight-line distance from the CCD lens to the center of the measured area on the window surface, in mm. iy To obtain the center O of the target plate center origin according to the original dot matrix image and the new dot matrix image captured by CCD i The angular deviation component of the Y axis from the center of the detection plate, see Figure 8 where y1 is O i The offset of the point in the Y-axis direction, in mm.

[0079] The testing process of angular deviation includes:

[0080] (1) When the space suit helmet visor is not in place, adjust the CCD and the target board so that the center point of the 5×5 dot matrix on the target board is located at the center of the CCD field of view, and the CCD takes a photo to collect the original dot matrix image of the 5×5 dot matrix on the target;

[0081] (2) After placing the space suit helmet visor, the CCD camera collects the new dot matrix image of the 5×5 dot matrix on the target after passing through the space suit helmet visor;

[0082] (3) Due to the optical performance of the window, the position of the center dot on the new dot matrix image will be offset relative to the original position; the absolute value of the angular deviation vector of the center point is calculated according to the formula as the optical angular deviation value of the test point;

[0083] (4) Adjust the operating mechanism to keep the CCD and the target plate moving synchronously. When the line connecting the center of the CCD field of view and the center point of the target plate matrix passes through the newly selected window test point, take a CCD photo.

[0084] (5) Return to step (3) until the calculation of the optical angle deviation values ​​of all test points is completed.

[0085] ③ Optical distortion

[0086] The optical distortion is measured and calculated according to the "projection (point by point) measurement method" in GJB503 "General Test Method for Aircraft Laminated Glass". First, the maximum offset Max x and the minimum offset Min x in the X-axis direction, and the maximum offset Max y and the minimum offset Min y in the Y-axis direction are calculated. Fig. 9 , calculate the corresponding angular deviation values ​​θMax x, θMin x, θMax y, θMin y. Get the maximum algebraic difference of the angular deviation component on the X axis θMax x-θMin x, and the maximum algebraic difference of the angular deviation component on the Y axis θMax y-θMin y, and take the maximum value of the two as the optical distortion value of the specimen. θx is the angular deviation component E of the center point of the target plate captured by the CCD after the window is placed, which deviates from the center point of the original target plate on the X axis ix ; θMax x, θMin x are the angle deviation components E ix The maximum and minimum values ​​of θMax y and θMin y are respectively the values ​​of O captured by the CCD camera. i The angular deviation component E from the Y axis of the center of the detection plate iy The maximum and minimum values ​​of .

[0087] The optical distortion value test process includes:

[0088] (1) When the space suit helmet visor is not in place, adjust the CCD and the target board so that the center point of the 5×5 dot matrix on the target board is located at the center of the CCD field of view, and the CCD takes a photo to collect the original dot matrix image of the 5×5 dot matrix on the target;

[0089] (2) After placing the space suit helmet visor, the CCD camera collects the new dot matrix image of the 5×5 dot matrix on the target after passing through the space suit helmet visor;

[0090] (3) With a step length of 1mm and the initial position of step 2 as the center, automatically scan the given area of ​​3mm×3mm and traverse all the acquisition points. Every time it moves to a new position, the CCD automatically takes a new dot pattern; for the acquired dot patterns, the software automatically identifies and calculates the X-axis offset and Y-axis offset of the center point on each dot pattern; obtains the maximum and minimum offsets in the X-axis and Y-axis directions respectively; calculates the difference between the maximum and minimum values ​​of the X-axis upward angular deviation θMax x-θMinx, and the difference between the maximum and minimum values ​​of the Y-axis upward angular deviation θMax y-θMin y, and uses the larger difference as the optical distortion value of the surface window at the measurement location.

[0091] (4) Reset to the initial position of step (2), adjust the operating mechanism to keep the CCD and the target plate moving synchronously, and when the line connecting the center of the CCD field of view and the center point of the target plate matrix passes through the newly selected window test point, return to step (2) until the optical distortion test calculation of all test points on the window is completed.

[0092] On the other hand, a method for performing a comprehensive optical performance test using the optical performance comprehensive testing device for an extravehicular space suit helmet face window is provided, comprising the following steps:

[0093] 1. Start the comprehensive optical performance test device to check the conductivity of the signal input / output of the operating mechanism, optical instrument, control unit, etc., and the smoothness of the mechanism operation.

[0094] 2. Debug the operating mechanism 5 to the symmetrical position in the middle of the left and right sides of the equipment, separate the active shaft and the driven shaft on the operating mechanism 5 and move them back to the appropriate position, and also adjust the signal receiving unit 6 on the active shaft and the signal transmitting unit 7 on the driven shaft backward to the appropriate position to provide space for the installation of the tested clothing on the equipment.

[0095] 2.1 Adjust the position and rotation angle of the active shaft through the operating mechanism base so that the axis of the distance sensor on the active shaft signal receiving unit is basically consistent with the longitudinal neutral plane of the clothing.

[0096] 2.2 Adjust the height of the signal receiving unit on the active shaft so that the axis of the distance sensor is roughly consistent with the center height of the window;

[0097] 2.3 Adjust the distance between the distance sensor and the window to a suitable distance through the adjustment structure on the signal receiving unit.

[0098] 2.4 Given the left / right moving step length (1mm) of the distance sensor, that is, the horizontal Y-axis moving step length of the operating mechanism base, first scan the window in the horizontal direction; after the line scan, move to the new height line according to the up / down moving step length (1mm), that is, the moving step length of the signal receiving unit on the active axis, to complete the horizontal scanning of the window in the new height line.

[0099] 3. Move the garment from top to bottom to cover the driving shaft of the operating mechanism 5 and the signal receiving unit 6 thereon. Finally, the garment must be installed and fixed on the mounting base 4 of the equipment, and ensure the sealing and connection reliability between the interfaces. During the entire installation process, the garment helmet window must not be bumped or touched.

[0100] 4. Scan the pressure window inside the space suit helmet window, and the control unit performs three-dimensional modeling on the space suit helmet window. The distance sensor is used to collect the distance between the space suit helmet window outside the cabin and scan the pressure window inside the space suit helmet window, including:

[0101] 4.1 Adjust the position and rotation angle of the active shaft through the operating mechanism base so that the axis of the distance sensor on the active shaft signal receiving unit is basically consistent with the longitudinal neutral plane of the clothing;

[0102] 4.2 Adjust the height of the signal receiving unit on the active axis so that the axis of the distance sensor is roughly consistent with the center height of the window;

[0103] 4.3 Adjust the distance between the distance sensor and the window to a suitable distance through the adjustment structure on the signal receiving unit;

[0104] 4.4 Given the left / right moving step length of the distance sensor (1mm) (Note: that is, the horizontal Y-axis moving step length of the operating mechanism base, see Figure 3 ), first scan the window horizontally; after the line scan, move to a new height row (Note: that is, the moving step of the signal receiving unit on the active axis) according to the up / down moving step (1mm) to complete the horizontal scan of the window at the new height row.

[0105] 5. Through manual input control, the active shaft and the driven shaft of the operating mechanism 5 are moved toward each other to a suitable position. With the assistance of the distance measuring sensors on the signal receiving unit 6 and the signal transmitting unit 7, the signal receiving unit 6 on the active shaft and the signal transmitting unit 7 on the driven shaft are moved toward each other and adjusted to a suitable distance from the window.

[0106] 6. Finely adjust the position of the signal transmitting unit 7 by manually inputting the signal step-by-step approximation method to ensure that the light source emitted therefrom can just enter the light inlet hole of the integrating sphere on the signal receiving unit 6, thereby ensuring the coaxiality of the optical axes of the optical instruments at the reflecting end and the collecting end. At this time, the window point through which the optical axis passes is the initial point or the zero point.

[0107] 7. Carry out light transmittance and haze test at zero point of the face window; Note: the point position and test results are automatically collected, calculated and produced by the equipment software. How to adjust the transmitting and receiving equipment, measure the incident light flux T1, the total light flux transmitted through the face window of the space suit helmet T2, the scattered light flux of the instrument T3, and the scattered light flux of the instrument and the face window of the space suit helmet T4; calculate the light transmittance Haze

[0108] Automatically or manually select new test points as needed to conduct transmittance and haze performance tests at the new points.

[0109] 8. Return the signal receiving unit 6 and the signal transmitting unit 7 to the initial position or the zero position; start the rotary motor between the signal receiving unit 6 and the driving shaft as needed, switch the positions of the integrating sphere and the CCD camera, and adjust the CCD camera to the working position;

[0110] 9. Start the CCD camera of the signal receiving unit 6 and the CCD power supply of the signal transmitting unit 7, and carry out the optical distortion and angular deviation performance test of the zero point of the window. Note: the point position and test results are automatically collected, calculated and produced by the equipment software.

[0111] According to the CCD acquisition module capture image, obtain the O captured by CCD i The angular deviation component E from the X-axis of the center of the detection plate ix , O captured by CCD i The angular deviation component E from the Y axis of the center of the detection plate iy , i is the incident angle, calculate the angular deviation Based on the image captured by the CCD acquisition module, the maximum offset Max x and minimum offset Minx in the X-axis direction, the maximum offset Max y and minimum offset Min y in the Y-axis direction are counted, and the corresponding angular deviation values ​​θMax x, θMin x, θMax y, and θMin y are calculated; the maximum algebraic difference of the angular deviation component on the X-axis line θMax x-θMin x, and the maximum algebraic difference of the angular deviation component on the Y-axis line θMax y-θMin y are obtained, and the maximum value of the two is taken as the optical distortion value.

[0112] Automatically or manually select new test points according to needs, and carry out optical distortion and angular deviation optical performance tests at new test points;

[0113] 10. Return the signal receiving unit 6 and the signal transmitting unit 7 to the initial position or the zero position.

[0114] 11. Inflate and pressurize the interior of the garment through the air nozzle 4-1 on the mounting seat 4, and maintain a stable pressure inside the garment by continuously replenishing air;

[0115] 12. Repeat steps 7 to 9 above to carry out optical performance test of helmet visor under garment pressurized working condition;

[0116] 13. The space suit is depressurized and returns to its pre-pressurized state;

[0117] 14. Separate the driving shaft and the driven shaft on the operating mechanism 5 and move them back to a suitable position. Also adjust the signal receiving unit 6 on the driving shaft and the signal transmitting unit 7 on the driven shaft backward to a suitable position to prepare for the evacuation of the garment from the equipment.

[0118] 15. First, pull the mobile clothing upwards, and after the driving shaft of the operating mechanism 5 and the signal receiving unit 6 thereon are completely out of the bottom of the clothing, move the clothing horizontally to complete the removal and recycling of the clothing.

[0119] 16. Turn off the control unit, turn off the power of each component, turn off the main power, and take protective measures after the equipment is tested.

[0120] In summary, the present invention relates to a comprehensive optical performance test device and method for an extravehicular space suit helmet visor. The chassis of the test device is provided with a mounting seat to provide a sealing interface for installing the extravehicular space suit; the operating mechanism includes an active shaft, a driven shaft and a base; the active shaft is connected to the output drive shaft through the adapter of the turntable and is arranged inside the extravehicular space suit; the driven shaft is installed on the transmission shaft on the lower surface of the turntable and is arranged outside the extravehicular space suit; the signal transmitting unit is installed on the driven shaft, and the signal receiving unit is installed on the active shaft; the control unit controls the operating mechanism, adjusts the positions of the signal transmitting unit and the signal receiving unit, and measures the optical performance parameters of the extravehicular space suit helmet visor based on the signal transmitted by the signal receiving unit. The present invention realizes the overall optical performance test of the helmet visor under two working conditions of the extravehicular space suit with and without air pressure filling, including the test of light transmittance, haze, angular deviation, and light distortion; and ensures the reliability of product acceptance and delivery.

[0121] It should be understood that the above specific embodiments of the present invention are only used to illustrate or explain the principles of the present invention, and do not constitute a limitation of the present invention. Therefore, any modifications, equivalent substitutions, improvements, etc. made without departing from the spirit and scope of the present invention should be included in the protection scope of the present invention. In addition, the appended claims of the present invention are intended to cover all changes and modifications that fall within the scope and boundaries of the appended claims, or the equivalent forms of such scope and boundaries.

Claims

1. A comprehensive test device for optical performance of extravehicular space suit helmet window, characterized in that: It includes a signal transmitting unit, a signal receiving unit, a chassis, a running mechanism and a control unit; The chassis is provided with a mounting seat, and the mounting seat provides a sealing interface for mounting an extravehicular space suit; The operating mechanism comprises a driving shaft, a driven shaft and a base; the base outputs a driving shaft connected to the driving shaft, and the base can drive the driving shaft to translate horizontally in the X direction, translate horizontally in the Y direction, and rotate around the vertical Z axis; the driven shaft is fixed to the base output driving shaft and is arranged outside the extravehicular space suit, and moves synchronously with the driving shaft; The signal transmitting unit is installed on the driven shaft; the signal receiving unit is installed on the driving shaft; the light emitted by the signal transmitting unit passes through the helmet window of the extravehicular space suit and is received by the signal receiving unit; The control unit controls the operating mechanism, adjusts the positions of the signal transmitting unit and the signal receiving unit, and measures optical performance parameters of the helmet window of the extravehicular space suit based on the signal transmitted by the signal receiving unit; The chassis comprises a pressure plate, a turntable, a packing sealing strip and a support plate; the support plate is fixedly supported by a truss; the pressure plate is a circular plate structure with a central circular hole, the outer ring of the pressure plate is fixed on the flange flange of the support plate, the pressure plate and the support plate form a receiving space, and the turntable is arranged in the receiving space; the central circular hole of the pressure plate provides a running space for horizontal translation and rotation around the vertical Z axis for the driving shaft that passes through the hole and is fixedly connected to the turntable; a transmission shaft is designed at the center of the upper and lower surfaces of the turntable, and the transmission shaft at the center of the lower surface is fixedly connected to the output drive shaft on the base of the operating mechanism, and the transmission shaft at the center of the upper surface is fixedly connected to the driving shaft; a double sealing groove along the circumferential direction is provided on the lower surface of the turntable, and a packing sealing strip is installed in the sealing groove, so that a dynamic seal is formed between the turntable and the support plate during the rotation movement around the Z axis and the horizontal X and Y directions; a mounting seat is fixedly installed on the upper surface of the pressure plate, and a gas pipeline nozzle is provided on the cylinder wall of the mounting seat for filling and releasing the gas pressure inside the clothing; The driving shaft is fixed to the transmission shaft at the center of the upper surface of the turntable, and rotates and translates horizontally with the turntable. The transmission shaft on the upper surface of the turntable is arranged inside the mounting seat; a first moving component is arranged on the driving shaft, and the first moving component is used to adjust the height of the signal receiving unit, the angle between the vertical plane and the vertical Z axis, and the distance between the signal receiving unit and the surface window; the driven shaft is parallel to the driving shaft, and the driven shaft is provided with a second moving component, and the second moving component is used to adjust the height of the signal emitting unit, the distance between the signal emitting unit and the surface window, and adjust the optical axis between the signal receiving unit and the emitting unit to be coaxial.

2. The optical performance comprehensive testing device for the helmet window of an extravehicular space suit according to claim 1, characterized in that: The signal transmitting unit comprises: a standard C light source, a collimating lens and a target plate; The standard C light source emits light after being powered on, and the emitted light forms parallel light after passing through the collimating lens, and the transmitted light of the parallel light after passing through the face window of the helmet of the extravehicular space suit being tested is captured and collected by the signal receiving unit, so as to be used for the light transmittance and haze test of the face window of the helmet of the extravehicular space suit; The target plate is a flat glass sheet with a uniformly distributed black dot matrix printed on it; the parallel light passes through the dot matrix and then through the visor of the space suit helmet outside the cabin to be captured and collected by the signal receiving unit and compared with the actual distribution of the dot matrix, so as to test the light distortion and angular deviation of the visor of the space suit helmet.

3. The optical performance comprehensive testing device for the helmet window of an extravehicular space suit according to claim 2, characterized in that: The signal receiving unit includes: an integrating sphere, an optical fiber, a spectrometer, a CCD camera and a distance sensor; The CCD camera collects a new dot matrix image formed by the high-precision dot matrix on the target plate of the transmitting unit through the space suit helmet window outside the cabin, and uses the change information of the corresponding points in the new dot matrix and the dot matrix of the target plate to calculate the light distortion and angular deviation of the space suit helmet window through the software equipped by the control unit; The integrating sphere is provided with a light inlet hole at the front, a light trap at the rear, and a test hole at the top, and the tail of the test hole is connected to the spectrometer through an optical fiber; the light trap at the rear of the integrating sphere is connected to a reflector and a shutter motor, and when the reflector covers the light trap under the action of the shutter motor, the transmitted light is collected through the test hole at the top of the integrating sphere, and the transmitted light is transmitted to the spectrometer through the optical fiber at the tail of the test hole to complete the analysis and calculation of the transmitted light flux; when the reflector is evacuated from the light trap under the action of the shutter motor, the scattered light is collected through the test hole at the top of the integrating sphere, and the scattered light is transmitted to the spectrometer through the optical fiber at the tail of the test hole to complete the analysis and calculation of the scattered light flux; the software equipped by the control unit calculates the light transmittance and haze of the space suit helmet face window based on the light flux; The distance sensor is used to collect the distance between the space suit helmet window outside the cabin and scan the pressure window inside the space suit helmet window.

4. The optical performance comprehensive testing device for the helmet window of an extravehicular space suit according to claim 3 is characterized in that: The control unit performs three-dimensional modeling of the space suit helmet window based on scanning of the pressure window inside the space suit helmet window.

5. The optical performance comprehensive testing device for the helmet window of an extravehicular space suit according to claim 4, characterized in that: The control unit, without placing the space suit helmet window outside the cabin, turns on the standard C light source of the signal transmitting unit, the integrating sphere and the spectrometer of the signal receiving unit, adjusts so that all the light emitted by the standard C light source just passes through the light inlet hole at the front end of the integrating sphere, turns on the shutter motor of the integrating sphere so that the reflector connected to the shutter motor covers the light trap of the integrating sphere; the light collected by the test hole at the top of the integrating sphere is introduced into the spectrometer through the optical fiber, and the luminous flux T1 is calculated by the spectrometer; When the reflector connected to the shutter motor is removed from the integrating sphere light trap, the light collected by the test hole on the top of the integrating sphere is introduced into the spectrometer through the optical fiber and the luminous flux T3 is calculated by the spectrometer; the CCD camera and the target plate are adjusted so that the center point of the dot matrix on the target plate is located at the center of the CCD camera's field of view, and the CCD camera collects the original dot matrix image of the dot matrix on the target; With the helmet window of the space suit placed outside the cabin, turn on the standard C light source of the signal transmitting unit, the integrating sphere and the spectrometer of the signal receiving unit, adjust so that the light emitted by the standard C light source just passes through the light inlet hole at the front end of the integrating sphere, turn on the shutter motor of the integrating sphere so that the reflector connected to the shutter motor covers the light trap of the integrating sphere; the light collected by the test hole at the top of the integrating sphere is introduced into the spectrometer through the optical fiber and the luminous flux T2 is calculated by the spectrometer; When the reflector connected to the shutter motor is removed from the integrating sphere light trap, the light collected by the test hole on the top of the integrating sphere is introduced into the spectrometer through the optical fiber and the luminous flux T4 is calculated by the spectrometer; The CCD camera takes pictures to collect the new dot matrix image on the target after the dot matrix passes through the face window of the space suit helmet; Calculate the transmittance: , haze ; According to the original dot matrix image and the new dot matrix image taken by the CCD camera, the angular deviation component Eix of the center Oi of the center origin of the target plate from the X-axis of the detection plate center and the angular deviation component E of Oi taken by the CCD camera from the Y-axis of the detection plate center are obtained. iy , i is the incident angle, calculate the angular deviation ; Adjust the operating mechanism to keep the CCD camera and the target plate moving synchronously. When the line connecting the center of the CCD camera's field of view and the center of the target plate's dot matrix passes through the newly selected surface window test point, take a picture and calculate the angular deviation of the newly selected surface window test point until the angular deviation test of all test points is completed. Measure the optical distortion value of the current window measurement point: currently, the center origin of the target plate is taken as the initial position. Every time it moves to a new position, the CCD camera captures a dot matrix image. For the collected dot matrix images, the software automatically identifies and calculates the X-axis offset and Y-axis offset of the center point on each dot matrix image. The maximum X-axis offset Max x and the minimum offset Min x, the maximum Y-axis offset Max y and the minimum offset Min y are obtained respectively. The difference between the maximum and minimum values ​​of the X-axis upward angular deviation θMax x-θMin x, and the difference between the maximum and minimum values ​​of the Y-axis upward angular deviation θMax y-θMin y are calculated, and the larger difference is used as the optical distortion value of the window at the measurement location. Among them, θMax x and θMin x are the angular deviation components E of the center origin of the target plate captured by the CCD after the window is placed, which deviate from the original target plate center point on the X-axis ix The maximum and minimum values ​​of θMax y and θMin y are the angular deviation components E of the center point of the target plate captured by CCD after the window is placed, which deviates from the original center point of the target plate on the y-axis. iy The maximum and minimum values ​​of ; Reset to the initial position, reselect the window test point, adjust the operating mechanism to keep the CCD camera and the target plate moving synchronously, and when the line connecting the center of the CCD camera field of view and the center point of the target plate dot matrix passes through the reselected window test point, measure the light distortion value of the current window measurement point until the light distortion value measurement of all window measurement points is completed.

6. A method for performing comprehensive optical performance testing using the optical performance comprehensive testing device for an extravehicular space suit helmet visor according to any one of claims 1 to 5, characterized in that: include: Mountings for attaching an extravehicular space suit to the chassis; Adjust the position and rotation angle of the active shaft through the operating mechanism base so that the axis of the distance sensor on the active shaft signal receiving unit is basically consistent with the longitudinal neutral plane of the garment; adjust the height of the signal receiving unit on the active shaft so that the axis of the distance sensor is basically consistent with the center height of the face window; adjust the distance between the distance sensor on the signal receiving unit and the face window so that the distance sensor can collect the distance between the distance sensor and the face window; At each altitude, scan the pressure surface window inside the space suit helmet surface window in the horizontal direction with a set step length; Adjust the height of the signal transmitting unit on the driven shaft so that the axis of the distance sensor on the signal transmitting unit is substantially consistent with the center height of the window; adjust the distance between the distance sensor on the signal transmitting unit and the window so that the distance sensor on the signal transmitting unit can collect the distance between the window; At each height, the pressure window outside the space suit helmet window is scanned in the horizontal direction with a set step length; the control unit performs three-dimensional modeling on the space suit helmet window; Adjust the positions of the signal transmitting unit and the signal receiving unit so that the light emitted by the optical fiber emitted by the signal transmitting unit can be fully immersed in the light inlet hole of the integrating sphere of the signal receiving unit; The control unit measures the optical performance parameters of the helmet window of the extravehicular space suit based on the signal transmitted by the signal receiving unit.

7. The method for comprehensive optical performance testing according to claim 6, characterized in that: Also includes: Filling the extravehicular space suit with gas until the pressure reaches the working pressure of the extravehicular space suit; The optical performance parameters of the extravehicular space suit helmet window were measured again.

8. The method for comprehensive optical performance testing according to claim 7, characterized in that: Measure the optical performance parameters of the helmet window of the extravehicular space suit, including: Without placing the visor of the space suit helmet outside the cabin, turn on the standard C light source of the signal transmitting unit, the integrating sphere and the spectrometer of the signal receiving unit, adjust so that the light emitted by the standard C light source just passes through the light inlet hole at the front end of the integrating sphere, turn on the shutter motor of the integrating sphere so that the reflector connected to the shutter motor covers the light trap of the integrating sphere; the light collected from the test hole at the top of the integrating sphere is introduced into the spectrometer through the optical fiber, and the luminous flux T1 is calculated by the spectrometer; when the reflector connected to the shutter motor is removed from the light trap of the integrating sphere, the light collected from the test hole at the top of the integrating sphere is introduced into the spectrometer through the optical fiber, and the luminous flux T3 is calculated by the spectrometer; adjust the CCD camera and the target plate so that the center point of the dot matrix on the target plate is located at the center of the field of view of the CCD camera, and the CCD camera collects the original dot matrix image of the dot matrix on the target; With the space suit helmet visor placed outside the cabin, the standard C light source of the signal transmitting unit, the integrating sphere and the spectrometer of the signal receiving unit are turned on, and the light emitted by the standard C light source is adjusted so that all the light passes through the light inlet hole at the front end of the integrating sphere, and the shutter motor of the integrating sphere is turned on so that the reflector connected to the shutter motor covers the light trap of the integrating sphere; the light collected from the test hole at the top of the integrating sphere is introduced into the spectrometer through the optical fiber, and the luminous flux T2 is calculated by the spectrometer; when the reflector connected to the shutter motor is removed from the integrating sphere light trap, the light collected from the test hole at the top of the integrating sphere is introduced into the spectrometer through the optical fiber, and the luminous flux T4 is calculated by the spectrometer; the CCD camera takes pictures to collect the new dot matrix image of the dot matrix on the target after passing through the space suit helmet visor; Calculate the transmittance: , haze ; According to the original dot matrix image and the new dot matrix image taken by the CCD camera, the angular deviation component E of the center Oi of the center origin of the target plate from the X-axis of the center of the detection plate is obtained. ix , the angle deviation component E of Oi captured by the CCD camera from the Y axis of the center of the detection plate iy , i is the incident angle, Calculate angular deviation ; Measure the optical distortion value of the current window measurement point: currently take the center origin of the target plate as the initial position, move the target plate with a step length of 1mm, scan the given area of ​​3mm×3mm, and each time it moves to a new position, the CCD camera takes a dot matrix image; for the collected dot matrix images, the software automatically identifies and calculates the X-axis offset and Y-axis offset of the center point on each dot matrix image; obtain the maximum X-axis offset Max x and the minimum offset Min x, the maximum Y-axis offset Max y and the minimum offset Miny respectively; calculate the difference between the maximum and minimum values ​​of the X-axis upward angular deviation θMax x-θMin x, and the difference between the maximum and minimum values ​​of the Y-axis upward angular deviation θMax y-θMin y, and use the larger difference as the optical distortion value of the window at the measurement location; where θMaxx and θMinx are the angular deviation components E of the center origin of the target plate captured by the CCD after the window is placed, which deviate from the original target plate center point on the X-axis ix The maximum and minimum values ​​of θMax y and θMin y are the angular deviation components E of the center point of the target plate captured by CCD after the window is placed, which deviates from the original center point of the target plate on the y-axis. iy The maximum and minimum values ​​of ; Reset to the initial position, reselect the window test point, adjust the operating mechanism to keep the CCD camera and the target plate moving synchronously, and when the line connecting the center of the CCD camera field of view and the center point of the target plate dot matrix passes through the reselected window test point, measure the light distortion value of the current window measurement point until the light distortion value measurement of all window measurement points is completed.

Images