1. A space optical load outgassing test device is characterized by comprising a test tank and auxiliary equipment, the auxiliary equipment comprises a heat sink, a heating box, an optical test piece, a temperature and air pressure measurement and control unit, wherein the space optical load of the air outlet test is arranged in the test tank, the test tank is used for providing a vacuum environment, the heat sink is used for providing a low-temperature background, and absorbs part of condensable volatile matters generated by the air release, the heating box is used for increasing the temperature of the space optical load or other air release objects and increasing the air release rate and the total air release amount, the optical test piece is used for collecting condensable volatile matters released after the space optical load of the outgassing test is finished, the temperature and air pressure measurement and control unit is arranged outside the test tank and connected with the heating box and used for testing the temperature and the pressure of the heating box.

2. The space optical loading outgassing test apparatus according to claim 1, wherein the heating box is further provided with a plurality of outgassing channels.

3. A testing method of the space optical loading outgassing testing apparatus according to claim 1, comprising the steps of:

and (3) giving out air to the test tank and the equipment in the tank: after the vacuum degree in the test tank reaches P1, heating the test tank and the equipment in the test tank to a temperature T1, and recovering normal temperature and normal pressure when the duration time meets the requirement R1, so that the gas outlet of the test tank and the equipment in the test tank is finished;

placing the space optical load to be subjected to the outgassing test into the test tank, heating the optical test piece to T2 after the vacuum degree in the test tank reaches P1, heating the space optical load to T3, cooling the optical test piece to T4 when the holding time meets the requirement R2, keeping the temperature of the space optical load unchanged, collecting the condensable volatile substances by the optical test piece, and preparing to finish the test when the collecting time reaches the requirement R3;

restoring the environment of the test tank to normal temperature and normal pressure;

and judging whether the air outlet result meets the requirement R5 according to the performance test result of the optical test piece participating in the test.

4. The testing method of the space optical loading outgassing testing apparatus according to claim 3, wherein the vacuum degree P1 is less than 1.33 x 10^-3Pa。

5. The testing method of the space optical loading outgassing testing apparatus according to claim 3, wherein the temperature T1 is 90 ℃.

6. The method of testing a space optical load outgassing test apparatus according to claim 3, wherein the temperature T2 is at least 10 ℃ higher than the surface temperature of other objects in the test tank.

7. The testing method of the space optical loading outgassing testing apparatus according to claim 3, wherein the temperature T3 is the highest temperature that does not damage the load, but should be at least 10 ℃ higher than the highest in-orbit operating temperature.

8. The testing method of the space optical loading outgassing testing apparatus according to claim 3, wherein the temperature T4 is at least 10 ℃ lower than the in-orbit lowest working temperature of the load pollution sensitive part.

9. The method of testing a space-optical loaded outgassing test apparatus according to claim 3, wherein the requirement R1 is at least 36 hours.

10. The method of testing a space-optical loaded outgassing test apparatus according to claim 3, wherein the requirement R2 is at least 96 hours.

11. The testing method of the space optical loading outgassing testing apparatus according to claim 3, wherein the requirement R3 is 24 hours.

12. The testing method of the space optical loading outgassing testing apparatus according to claim 3, wherein the requirement R4 is that the content of hydrocarbon in clean nitrogen gas is not more than 15 ppm.

13. The testing method of the space optical loading outgassing testing apparatus according to claim 3, wherein the requirement R5 is: and evaluating according to the working waveband of the space optical load, wherein the ultraviolet waveband meets the requirement that the change of the reflectivity of the optical test piece at the central working wavelength is not more than 3%, and the visible waveband meets the requirement that the change of the reflectivity of the optical test piece at the wavelength of 550nm is not more than 3%.

Background

In the development process of space optical loads, pollution control and removal are important problems faced by high-precision space optical instruments, particularly space ultraviolet instruments and refrigeration infrared detectors. The data show that over half of the vacuum tests used by the U.S. aerospace agency for space-borne bake-out in one financial year at the end of the twentieth century. This is because at the surface, the most effective and critical technique for pollution control of space loads is the outgassing test.

At present, the domestic lacks of data specially used for the gassing test. The relevant data includes: data 1, GJB1027A-2005 vehicle, upper level and spacecraft test requirements, are the general standards for thermal testing of aerospace products, and do not set specific requirements for outgassing test methods. Data 2, QJ 2321-. Data 3, GJB 2203A-2005 satellite product cleanliness and pollution control requirements, is a national standard document on aerospace product pollution control, in which general requirements are made on the temperature and time of the outgoing gas, and no specific test method is proposed. Document 4, patent CN201218000627.9 a thermal vacuum test method for navigation satellite, proposes a thermal vacuum test method for navigation satellite, which specifies the time length, vacuum degree and temperature requirements of thermal vacuum test for navigation satellite, but does not relate to the time, temperature, vacuum degree, result evaluation and other requirements of the air out test for space optical load.

Disclosure of Invention

In view of the above, it is necessary to provide a space optical loading outgassing testing apparatus and a testing method thereof, which are specially used for space optical loading outgassing.

In order to solve the problems, the invention adopts the following technical scheme:

in a first aspect, the invention provides a spatial optical load outgassing test device, which comprises a test tank and auxiliary equipment, the auxiliary equipment comprises a heat sink, a heating box, an optical test piece, a temperature and air pressure measurement and control unit, wherein the space optical load of the air outlet test is arranged in the test tank, the test tank is used for providing a vacuum environment, the heat sink is used for providing a low-temperature background, and absorbs part of condensable volatile matters generated by the air release, the heating box is used for increasing the temperature of the space optical load or other air release objects and increasing the air release rate and the total air release amount, the optical test piece is used for collecting condensable volatile matters released after the space optical load of the outgassing test is finished, the temperature and air pressure measurement and control unit is arranged outside the test tank and connected with the heating box and used for testing the temperature and the pressure of the heating box.

In some embodiments, the heating box is further provided with a plurality of air outlet channels.

In a second aspect, the invention further provides a testing method of the space optical loading outgassing testing apparatus, which includes the following steps:

after the vacuum degree in the test tank reaches P1, heating the test tank and the equipment in the test tank to a temperature T1, and recovering normal temperature and normal pressure when the duration time meets the requirement R1, so that the gas outlet of the test tank and the equipment in the test tank is finished;

placing the space optical load to be subjected to the outgassing test into the test tank, heating the optical test piece to T2 after the vacuum degree in the test tank reaches P1, heating the space optical load to T3, cooling the optical test piece to T4 when the holding time meets the requirement R2, keeping the temperature of the space optical load unchanged, collecting the condensable volatile substances by the optical test piece, and preparing to finish the test when the collecting time reaches the requirement R3;

restoring the environment of the test tank to normal temperature and normal pressure;

and judging whether the air outlet result meets the requirement R5 according to the performance test result of the optical test piece participating in the test.

In some of these embodiments, the vacuum level P1 is less than 1.33 x 10^-3Pa。

In some of these embodiments, the temperature T1 is 90 ℃.

In some of these embodiments, the temperature T2 is at least 10 ℃ higher than the surface temperature of other objects in the test tank.

In some of these embodiments, the temperature T3 is the highest temperature that does not damage the load, but should be at least 10 ℃ higher than the highest in-rail operating temperature.

In some of these embodiments, the temperature T4 is at least 10 ℃ lower than the in-orbit minimum operating temperature of the load contamination-sensitive location.

In some of these embodiments, the requirement R1 is at least 36 hours.

In some of these embodiments, the requirement R2 is at least 96 hours.

In some of these embodiments, the requirement R3 is 24 hours.

In some of these embodiments, the requirement R4 is that the hydrocarbon content of clean nitrogen gas is not more than 15 ppm.

In some of these embodiments, the requirement R5 is: and evaluating according to the working waveband of the space optical load, wherein the ultraviolet waveband meets the requirement that the change of the reflectivity of the optical test piece at the central working wavelength is not more than 3%, and the visible waveband meets the requirement that the change of the reflectivity of the optical test piece at the wavelength of 550nm is not more than 3%.

Compared with the prior art, the space optical load outgassing test device and method provided by the application can perform outgassing on the test tank and the auxiliary equipment in the tank, place the space optical load into the test tank, and after the vacuum degree in the tank reaches P1, heating the optical test piece to T2, heating the pollution sensitive device to T3, when the duration time meets the requirement of R2, cooling the optical test piece to T4, when the collecting time of the test piece reaches the requirement R3, preparing to finish the test, restoring the environment of the test tank to normal temperature and normal pressure, according to the performance test result of the optical test piece participating in the test, whether the outgassing result meets the requirement R5 is judged, the space optical load outgassing test device and the method provided by the application provide the judgment standards of pressure intensity, vacuum degree, temperature and test effect in the outgassing process, the air-out device can be used for air-out of space optical loads and other aerospace products, and the influence of pollutants on equipment is reduced.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments of the present invention or in the description of the prior art will be briefly described below, and it is obvious that the drawings described below are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.

Fig. 1 is a schematic structural diagram of a spatial optical loading outgassing test apparatus provided in an embodiment of the present invention.

Fig. 2 is a flowchart illustrating steps of a spatial optical outgassing testing method according to an embodiment of the present invention.

Detailed Description

Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention.

In the description of the present invention, it is to be understood that the terms "upper", "lower", "horizontal", "inside", "outside", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are only for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention.

Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless specifically defined otherwise.

In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments.

Please refer to fig. 1, which is a schematic structural diagram of a space optical load outgassing test apparatus provided in the present application, including a test tank 1 and auxiliary equipment, where the auxiliary equipment includes a heat sink 2, a heating box 3, an optical test piece 6, and a temperature and pressure measurement and control unit 7. The connection and operation of the components will be described in detail below.

Treat the space optics load 5 of giving vent to anger experimental set up in the test jar 1, test jar 1 is used for providing vacuum environment, 2 positions on heat sink are used for providing the low temperature background to absorb the part of gassing production and can congeal the volatile matter, heating cabinet 3 is used for improving the temperature of space optics load 5 or other objects of giving vent to anger and increase gassing rate and total gassing volume, optics test block 6 is used for collecting the volatile matter that can congeal that releases after 5 completions of the space optics load of waiting to give vent to anger experimental give vent to anger, temperature and atmospheric pressure observe and control unit 7 set up in outside the test jar 1, temperature and atmospheric pressure observe and control unit 7 connect heating cabinet 3 is used for the test the temperature and the pressure of heating cabinet 3.

In some embodiments, the heating box 3 is further provided with a plurality of air outlet channels 4.

Referring to fig. 2, the present invention further provides a testing method of the space optical loading outgassing testing apparatus, including the following steps:

step S110: and (3) giving vent to the atmosphere of the test tank and the equipment in the test tank, heating the test tank and the equipment in the test tank to the temperature T1 after the vacuum degree in the test tank reaches P1, and recovering normal temperature and normal pressure when the duration time meets the requirement R1, wherein the gas giving of the test tank and the equipment in the test tank is completed.

In some of these embodiments, the vacuum level P1 is less than 1.33 x 10^-3Pa, the temperature T1 being 90 ℃, the requirement R1 being at least 36 hours.

Step S120: putting the space optical load to be subjected to the air outlet test into the test tank, heating the optical test piece to T2 after the vacuum degree in the test tank reaches P1, heating the space optical load to T3, and when the holding time meets the requirement R2, cooling the optical test piece to T4, simultaneously keeping the temperature of the space optical load unchanged, collecting the condensable volatile substances by the optical test piece, and when the collection time reaches the requirement R3, preparing to end the test.

In some of these embodiments, the temperature T2 is at least 10 ℃ higher than the surface temperature of other objects in the test tank, the temperature T3 is the maximum temperature that will not damage the load, but should be at least 10 ℃ higher than the maximum in-rail operating temperature, the requirement R2 is at least 96 hours, the temperature T4 is at least 10 ℃ lower than the minimum in-rail operating temperature of the load contamination-sensitive area, and the requirement R3 is 24 hours.

Step S130: and (5) restoring the environment of the test tank to normal temperature and normal pressure.

Specifically, the re-pressing and re-warming are carried out by using clean nitrogen with hydrocarbon content not exceeding 15 ppm. In the repressing process, controlling the gas flow to prevent particle pollutants in the tank from depositing on the surface of a pollution sensitive part of the load or entering the load; meanwhile, the temperature return processes of the test tank and the equipment in the tank are controlled, the temperature of the load is kept higher than that of other objects in the test tank, and the optical test piece, the load and other equipment involved in testing are prevented from being polluted by pollutants on the heat sink in the temperature return process.

Step S140: and judging whether the air outlet result meets the requirement R5 according to the performance test result of the optical test piece participating in the test.

In some of these embodiments, the requirement R5 is: and evaluating according to the working waveband of the space optical load, wherein the ultraviolet waveband meets the requirement that the change of the reflectivity of the optical test piece at the central working wavelength is not more than 3%, and the visible waveband meets the requirement that the change of the reflectivity of the optical test piece at the wavelength of 550nm is not more than 3%.

The space optical load outgassing test device and method provided by the application are used for outgassing of space optical loads and auxiliary equipment in a tank, the space optical loads are placed in the test tank, after the vacuum degree in the tank reaches P1, an optical test piece is heated to T2, pollution sensitive equipment is heated to T3, when the duration time meets the requirement R2, the optical test piece is cooled to T4, when the test piece collection duration time reaches the requirement R3, the test is prepared to be finished, the environment of the test tank is restored to normal temperature and normal pressure, whether the outgassing result meets the requirement R5 is judged according to the performance test result of the optical test piece participating in the test.

The technical solution of the present invention will be described in detail with reference to the following detailed examples.

Example 1:

the first step, give vent to anger in test jar and jar interior heat sink, heating cabinet, test block placement equipment and inside cable etc.. The test tank is vacuumized, and the vacuum degree in the tank reaches 1.33 multiplied by 10^-3The pressure of Pa meets the requirement of air pressure, the equipment in the tank is heated to 90 ℃, and the heat preservation time is not less than 36 hours. And then entering a temperature return process, keeping a vacuum state, recovering normal temperature and normal pressure, and finishing air outlet of the test tank and the auxiliary equipment in the tank. In the repressing process, clean nitrogen with the hydrocarbon content not greater than the content of the hydrocarbon is used, and meanwhile, the gas flow is controlled, so that the pollution of the tank body is prevented.

And step two, exhausting the load. Placing the optical load and the optical test piece into a test tank, closing the tank door, vacuumizing until the vacuum degree in the tank reaches 1.33 multiplied by 10^-3And Pa, raising the temperature of the optical test piece to be at least 10 ℃ higher than the surface temperature of other objects in the vacuum tank, raising the temperature of the load to the highest temperature without damaging the load, but at least 10 ℃ higher than the highest working temperature of the on-track, after the holding time reaches 96 hours, reducing the temperature of the optical test piece to be at least 10 ℃ lower than the lowest working temperature of the on-track of the load pollution sensitive part, simultaneously keeping the temperature of the load unchanged, starting sample collection, and after 24 hours of sample collection, preparing to end the test.

And thirdly, restoring the environment of the test tank to normal temperature and normal pressure. The re-pressing and re-warming are carried out by using clean nitrogen with the hydrocarbon content not exceeding 15 ppm. In the repressing process, the gas flow is controlled, and particle pollutants in the tank are prevented from depositing on the surface of a pollution sensitive part of the load or entering the load. Meanwhile, the temperature return processes of the test tank and the equipment in the tank are controlled, the temperature of the load is kept higher than that of the test tank, and the optical test piece, the load and other equipment involved in testing are prevented from being polluted by pollutants on the heat sink in the temperature return process.

And fourthly, evaluating results. And judging the air-out test effect according to the performance test result of the optical test piece participating in the test. And evaluating according to the optical load working wave band, wherein the ultraviolet wave band meets the requirement that the change of the reflectivity of the optical test piece at the central working wavelength is not more than 3%, and the visible wave band meets the requirement that the change of the reflectivity of the optical test piece at the wavelength of 550nm is not more than 3%.

Compared with the prior art, the embodiment of the invention has the following advantages: 1) the pressure requirement. According to the data 4 and the contents of related technical data at home and abroad, the effective test pressure is determined to be 1.33 multiplied by 10^-3Pa, the precision requirement and the European and American universal vacuum test pressure requirement are 10^-5mm Hg (or 10)^-5Torr) is less than 0.5 percent, which is convenient for the unification of the requirements in international cooperation. 2) Temperature requirements. According to the condition that the highest temperature is generally not more than 80 ℃ in the space load thermal test, the requirement that the gas outlet temperature of the test tank is 90 ℃ is provided, and pollutants remained in the tank can be effectively removed. Meanwhile, the temperature difference requirement of more than 10 ℃ is kept for other characteristic temperatures, and the quality and the evaluation reliability of the outgassing test can be ensured. 3) And (5) testing time requirements. According to theoretical calculation and experimental verification, the experimental requirements of high gas outlet quality and low economic and time cost are provided. The invention aims to provide a simple and operable test method for space optical loads, and other aviation and aerospace products can be used as reference.

The above are merely examples of the present application and are not intended to limit the present application. Various modifications and changes may occur to those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application should be included in the scope of the claims of the present application.