CN110646315A - Wide-temperature-zone rapid temperature impact test system for product based on liquid nitrogen immersion deep space detection - Google Patents
Wide-temperature-zone rapid temperature impact test system for product based on liquid nitrogen immersion deep space detection Download PDFInfo
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- CN110646315A CN110646315A CN201910948409.9A CN201910948409A CN110646315A CN 110646315 A CN110646315 A CN 110646315A CN 201910948409 A CN201910948409 A CN 201910948409A CN 110646315 A CN110646315 A CN 110646315A
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Abstract
The invention discloses a liquid nitrogen soaking-based wide-temperature-zone rapid temperature impact test system for a deep space exploration product, which comprises an infrared heating system, a liquid nitrogen soaking system and a test piece lifting device, wherein the infrared heating system is connected with the liquid nitrogen soaking system; the liquid nitrogen soaking system is used for arranging the test piece in a low-temperature environment at the temperature lower than-150 ℃; the infrared heating system realizes high-temperature closed-loop temperature control on the test piece; the test piece lifting device is used for adjusting the position of a test piece according to test requirements. The invention is safe and reliable, can effectively control the temperature, can control the power of the infrared heating system and the distance between the infrared heating system and a test piece through the condition, can be flexibly configured according to the test requirement, and has low realization cost.
Description
Technical Field
The invention belongs to the technical field of crossing of environmental tests and deep space exploration, and particularly relates to a liquid nitrogen soaking-based wide-temperature-zone rapid temperature impact test system for a deep space exploration product.
Background
The temperature impact test is a test for carrying out rapid temperature cycle on the product under normal pressure, can fully expose potential material defects and manufacturing quality defects in the product, eliminates early failure, improves the reliability of the product, and is an important means for checking the environmental adaptability of the product. Temperature impact test generally adopts temperature and humidity circulation test box to provide temperature alternation environment, wherein low temperature is generally obtained through mechanical refrigeration or auxiliary liquid nitrogen refrigeration, the maximum capacity of equipment is about-120 ℃, and for test working conditions with lower temperature, especially ultra-low temperature environment below-150 ℃, ground simulation is generally realized through liquid nitrogen soaking in engineering. With the development of aerospace industry, the requirements for development and verification of deep space exploration products are more and more urgent. Compared with the prior aerospace products, the application environment of the deep space exploration products is more severe, a high-low temperature alternating environment of-150 ℃ to 160 ℃ needs to be faced, and whether the products can reliably work under the environment is yet to be verified, so that a wide-temperature-region rapid temperature impact test under an extreme high-low temperature alternating environment needs to be carried out on the ground.
In order to achieve the purpose of comprehensively verifying the star surface spacecrafts such as a deep space probe, a high-temperature environment of 160 ℃, an extremely low-temperature environment lower than-150 ℃ and a temperature change rate of more than 10 ℃/min need to be provided. The test piece needs to be constantly switched between a high-temperature environment and a liquid nitrogen soaking environment, and great risks such as unstable temperature control, rapid volatilization of liquid nitrogen, suffocation of liquid nitrogen of testers and the like exist in the test process. Therefore, how to provide a wide-temperature-zone rapid temperature impact test system based on liquid nitrogen soaking, provide extreme temperature environmental conditions for truly simulating deep space exploration type products and effectively carry out temperature impact tests is a technical problem to be solved in the field.
Disclosure of Invention
The invention aims to provide a liquid nitrogen soaking-based wide-temperature-zone rapid temperature impact test system for deep space exploration type products, which is used for carrying out test tests of the deep space exploration type products in an extremely-low-temperature and high-temperature thermal impact cycle environment.
The invention is realized by the following technical scheme:
liquid nitrogen soaking-based rapid temperature impact test system for wide temperature zone of deep space exploration product, comprising: the device comprises an infrared heating system, a liquid nitrogen soaking system and a test piece lifting device;
wherein, liquid nitrogen soaks the system and mainly comprises liquid nitrogen container, level sensor, liquid nitrogen pipeline, control circuit and valve etc. and: the liquid nitrogen container is used for forming a relatively closed space and keeping the liquid nitrogen in the container from obviously volatilizing and leaking, and the top of the container is provided with an installation platform for installing an infrared heating device; a liquid level sensor is arranged in the container and used for monitoring the liquid level of the liquid nitrogen in real time; the liquid nitrogen pipeline is connected with the liquid nitrogen container through the self-control electromagnetic valve; the outer side of the container is provided with a PLC control cabinet, and the inner part of the container is provided with a liquid level control PLC control circuit for closed-loop control of liquid nitrogen liquid level.
Wherein, infrared heating system mainly comprises heating device, temperature measurement sensor, measurement cable, control signal cable, accuse temperature appearance, heating power, heating cable: the heating device is fixed on a liquid nitrogen container top mounting platform through a fixing tool, the heating device is placed towards the test piece, the temperature measuring sensor is mounted on the surface of the test piece in an adhesion mode and used for measuring the temperature of a product, and the temperature measuring sensor is connected into the temperature controller through a measuring cable; the temperature controller generates a control signal according to a measurement signal of the temperature sensor, transmits the control signal to the heating power supply through the control signal cable, enables the heating power supply to generate certain direct current and voltage output, and transmits the direct current and the voltage output to the heating device through the heating cable in sequence, so that the heating device is electrified, heat flow is output to the surface of a test piece under the working condition of high-temperature test, the surface temperature of the connector is changed, and the measurement signal of the temperature sensor is changed; the control signal of the temperature controller is adjusted in real time along with the measuring signal of the temperature measuring sensor, thereby realizing closed-loop temperature control.
Wherein, test piece elevating gear mainly comprises driving motor, fixed pulley, lifting rope, product mounting platform, guide bar, limit switch: the driving motor provides a power source for the whole lifting device, and the rope is driven to lift through the output shaft of the motor; the fixed pulleys are respectively arranged on the top beams of the lifting devices and used for reversing lifting ropes so as to drive the product mounting platform to lift; one end of the guide rod is connected with the product mounting platform, and the other end of the guide rod is fixed on the outer side wall of the liquid nitrogen container so as to guide the platform; the limit switch is arranged on the vertical beam of the lifting device and used for controlling the lifting stroke of the test piece; the product mounting platform is connected with the lifting rope through the hook, the lower end of the platform is hoisted through the screw, and the switching of high-temperature and low-temperature test working conditions is realized through the lifting of the test piece.
Preferably, the liquid nitrogen container is made of stainless steel and is a vertical cylinder;
preferably, the liquid nitrogen pipeline valve adopts a self-control electromagnetic valve;
preferably, the guide rod and the mounting platform are welded in an argon arc welding mode;
preferably, the hoisting ropes are steel wires;
preferably, the heating device adopts an infrared quartz lamp;
preferably, the temperature measuring sensor is a T-shaped thermocouple or a platinum resistor;
preferably, one end of the guide rod is connected with the product mounting platform by welding.
The invention has the following beneficial effects:
(1) safe and reliable: the liquid nitrogen soaking-based wide-temperature-zone rapid temperature impact test system for the deep space exploration type products effectively avoids the risks possibly occurring in the lifting process of a test piece from the structural design, and meanwhile, the control circuit is designed outside the test container, so that the reliability of the test device is effectively improved.
(2) And (3) effective control: in the liquid nitrogen soaking-based wide-temperature-zone rapid temperature impact test system for the deep space exploration type products, the temperature control, the liquid level control and the lifting control adopt the design ideas of closed-loop control and independent control of each system, are independent of each other, do not influence each other, are easy to control, and are convenient to maintain and replace.
(3) Flexible combination: the high-temperature test condition is controlled by the power of the infrared heating system and the distance between the infrared heating system and the test piece, and can be flexibly configured according to test requirements, so that the low cost is realized.
Drawings
FIG. 1 is a schematic diagram of a liquid nitrogen soaking-based wide-temperature-zone rapid temperature impact test system for deep space exploration type products.
Wherein: 1 heating the cable; 2 measuring the cable; 3 controlling the signal cable; 4, infrared lamps; 5 lifting device vertical beam; 6 lifting device top beam; 7, a fixed pulley; 8, a product mounting platform; 9 a temperature sensor; 10 test pieces; 11 a guide rod; 12 a liquid nitrogen container; 13 temperature control instrument; 14, a measurement and control integrated machine; 15 a direct current power supply; 16PLC control cabinets; 17 a liquid level sensor; 18 a hoist driving motor; 19 hoisting a winch drum; 20, automatically controlling a large electromagnetic valve; 21 self-control small electromagnetic valve; 22 liquid nitrogen line.
Detailed Description
The present invention will be described in detail with reference to the accompanying drawings, and the specific embodiments are only for illustrative purposes and are not intended to limit the scope of the present invention.
Referring to fig. 1, fig. 1 shows a schematic diagram of a wide-temperature-zone rapid temperature impact test system for a deep space exploration type product based on liquid nitrogen soaking. The drawing shows that the system for testing the rapid temperature impact of the wide temperature zone of the deep space exploration type product based on liquid nitrogen soaking comprises a heating cable 1; a measuring cable 2; a control signal cable 3; an infrared lamp 4; a lifting device vertical beam 5; a lifting device top beam 6; a fixed pulley 7; a product mounting platform 8; a temperature sensor 9; a test piece 10; a guide rod 11; a liquid nitrogen container 12; a temperature controller 13; a measurement and control integrated machine 14; a DC power supply 15; a PLC control cabinet 16; a liquid level sensor 17; a hoist drive motor 18; a winch drum 19; a self-controlled large electromagnetic valve 20; a self-controlled small electromagnetic valve 21; a liquid nitrogen line 22; a wire rope 23; an upper limit switch 24; and a lower limit switch 25.
In one embodiment, the liquid nitrogen container 12 of the liquid nitrogen soaking-based deep space exploration type product wide temperature area rapid temperature impact test system is placed on the ground of a special test site through a pulley arranged at the bottom and can be moved to any liquid nitrogen pipeline in the site; the liquid nitrogen pipeline is connected to a liquid inlet of the liquid nitrogen container through a large and small self-control electromagnetic valve; the liquid level sensor 17 is installed on the side wall in the liquid nitrogen container, is connected to a control circuit in the PLC control cabinet 16, and is connected to the large automatic control electromagnetic valve 20 and the small automatic control electromagnetic valve 21 through cables after signal control and acquisition are carried out by the control circuit; a winch driving motor 18 and a winch drum 19 are fixed on the bottom plate outside the liquid nitrogen container 12 through screw threads, one end of the winch driving motor is connected to a control circuit inside the PLC control cabinet 16 through a cable, and the other end of the winch driving motor is connected with the product mounting platform 8 through a steel wire rope 23 through a pulley 7; the test piece 10 is screwed on the product mounting platform 8; an upper limit switch 24 and a lower limit switch 25 are screwed on the vertical beam 5 of the lifting device and are connected to a control circuit in the PLC control cabinet 16 through cables; the upper end and the lower end of the guide rod 11 are respectively welded and fixed with the product mounting platform 8 and the outer bottom plate of the liquid nitrogen container 12; one end of the measuring cable 2 is connected with the temperature sensor 9, and the other end is connected with the temperature controller 13; the infrared lamp 4 is placed on the product mounting platform 8 opposite the test piece 10 and is connected to the direct current power supply 15 through the heating cable 1; a control circuit in the PLC control cabinet 16 is connected to the measurement and control integrated machine through a control signal cable 3, and liquid level control collection and automatic lifting control are achieved through the measurement and control integrated machine.
The development principle of the liquid nitrogen soaking-based wide-temperature-zone rapid temperature impact test system for deep space exploration type products is as follows:
under the condition that a relatively closed space is formed in the liquid nitrogen container 12, the large self-control electromagnetic valve 20 is opened, liquid nitrogen enters the liquid nitrogen container 12 through the pipeline 22, the volume of the liquid nitrogen in the liquid nitrogen container 12 reaches a preset value, and the large self-control electromagnetic valve 20 is closed. At this time, the liquid level sensor 17 is used for collecting the liquid level height in the liquid nitrogen container, a liquid level signal is transmitted to a control circuit in the PLC control cabinet 16 through a cable, the control circuit compares the measured value of the liquid level with a given target value, a control signal is generated after calculation and transmitted to the small self-control electromagnetic valve 21, the liquid nitrogen capacity in the liquid nitrogen container is enabled to always accord with the preset upper limit and the preset lower limit in the test process by controlling the opening and closing of the small self-control electromagnetic valve, and the ultralow temperature environment of-196 ℃ is established in the liquid nitrogen container 12.
Placing an infrared lamp on a platform at the top of a liquid nitrogen container, measuring a temperature value on the surface of a test piece 10 by using a temperature sensor 9, transmitting a measurement signal into a temperature controller 13 through a measurement cable 2, comparing a temperature measurement value with a given target value by the temperature controller 13, generating a control signal after calculation, transmitting the control signal into a direct current power supply 15, enabling the power supply 15 to generate certain direct current and voltage output, and powering up the power supply through a heating cable in sequence, so that specific radiation heat flow is output to the surface of the test piece 10 in a high-temperature region of a test system, the surface temperature of the test piece is changed, and the measurement signal of the temperature sensor 9 is changed; the control signal of the temperature controller 13 is adjusted in real time along with the measurement signal of the temperature sensor 9, thereby realizing closed-loop temperature control, realizing temperature rise and temperature maintenance of the test piece 10 according to a given temperature value and a temperature change rate, and establishing a high-temperature environment with the deep space detection type product being more than 160 ℃ in a high-temperature area at the top of the liquid nitrogen container.
A heating cable 1; a measuring cable 2; a control signal cable 3; an infrared lamp 4; a lifting device vertical beam 5; a lifting device top beam 6; a fixed pulley 7; a product mounting platform 8; a temperature sensor 9; a test piece 10; a guide rod 11; a liquid nitrogen container 12; a temperature controller 13; a measurement and control integrated machine 14; a DC power supply 15; a PLC control cabinet 16; a liquid level sensor 17; a hoist drive motor 18; a winch drum 19; a self-controlled large electromagnetic valve 20; a self-controlled small electromagnetic valve 21; a liquid nitrogen line 22; a wire rope 23; an upper limit switch 24; and a lower limit switch 25.
The inside of the liquid nitrogen container is a low-temperature area of-196 ℃, the top of the container is a high-temperature area of 160 ℃, the test piece lifting device drives the winding drum 19 to rotate through the winch driving motor 18, so that the steel wire rope 23 drives the product mounting platform to ascend or descend through the fixed pulley 7, when the platform ascends to trigger the upper limit switch or descends to trigger the lower limit switch, the control circuit controls the driving motor 18 to enable the platform to rotate in the opposite direction, the cyclic reciprocating motion of the test piece in the high-temperature area and the low-temperature area is realized, and the environment condition of the rapid temperature impact test is established.
The liquid nitrogen soaking-based wide-temperature-zone rapid temperature impact test system for the deep space exploration type products can provide extreme low-temperature and high-temperature impact environment tests for the deep space exploration type products, and can be used for checking the tolerance capability of the deep space exploration type products to the extreme temperature environment.
The invention relates to a liquid nitrogen soaking-based wide-temperature-zone rapid temperature impact test system for deep space exploration type products, which comprises the following steps: the low temperature can reach-196 ℃, the high temperature can reach 160 ℃ and above, and the temperature rise and fall speed is more than 100 ℃/min.
Although particular embodiments of the present invention have been described and illustrated in detail, it should be noted that various changes and modifications could be made to the above-described embodiments without departing from the spirit of the invention and the scope of the appended claims.
Claims (9)
1. Liquid nitrogen soaking-based rapid temperature impact test system for wide temperature zone of deep space exploration product, comprising: the device comprises an infrared heating system, a liquid nitrogen soaking system and a test piece lifting device;
wherein, liquid nitrogen soaks the system and mainly comprises liquid nitrogen container, level sensor, liquid nitrogen pipeline, control circuit and valve etc. and: the liquid nitrogen container is used for forming a relatively closed space and keeping the liquid nitrogen in the container from obviously volatilizing and leaking, and the top of the container is provided with an installation platform for installing an infrared heating device; a liquid level sensor is arranged in the container and used for monitoring the liquid level of the liquid nitrogen in real time; the liquid nitrogen pipeline is connected with the liquid nitrogen container through the self-control electromagnetic valve; the outer side of the container is provided with a PLC control cabinet, and the inner part of the container is provided with a liquid level control PLC control circuit which is used for closed-loop control of liquid level of liquid nitrogen;
wherein, infrared heating system mainly comprises heating device, temperature measurement sensor, measurement cable, control signal cable, accuse temperature appearance, heating power, heating cable: the heating device is fixed on a liquid nitrogen container top mounting platform through a fixing tool, the heating device is placed towards the test piece, the temperature measuring sensor is mounted on the surface of the test piece in an adhesion mode and used for measuring the temperature of a product, and the temperature measuring sensor is connected into the temperature controller through a measuring cable; the temperature controller generates a control signal according to a measurement signal of the temperature sensor, transmits the control signal to the heating power supply through the control signal cable, enables the heating power supply to generate certain direct current and voltage output, and transmits the direct current and the voltage output to the heating device through the heating cable in sequence, so that the heating device is electrified, heat flow is output to the surface of a test piece under the working condition of high-temperature test, the surface temperature of the connector is changed, and the measurement signal of the temperature sensor is changed; the control signal of the temperature controller is adjusted in real time along with the measurement signal of the temperature measurement sensor, so that closed-loop temperature control is realized;
wherein, test piece elevating gear is used for carrying out position adjustment with the test piece according to experimental demand.
2. The system for testing the rapid temperature shock of the wide temperature zone of the deep space exploration product based on the soaking in liquid nitrogen according to claim 1, wherein the test piece lifting device mainly comprises a driving motor, a fixed pulley, a lifting rope, a product mounting platform, a guide rod and a limit switch: the driving motor provides a power source for the whole lifting device, and the rope is driven to lift through the output shaft of the motor; the fixed pulleys are respectively arranged on the top beams of the lifting devices and used for reversing lifting ropes so as to drive the product mounting platform to lift; one end of the guide rod is connected with the product mounting platform, and the other end of the guide rod is fixed on the outer side wall of the liquid nitrogen container so as to guide the platform; the limit switch is arranged on the vertical beam of the lifting device and used for controlling the lifting stroke of the test piece; the product mounting platform is connected with the lifting rope through the hook, the lower end of the platform is hoisted through the screw, and the switching of high-temperature and low-temperature test working conditions is realized through the lifting of the test piece.
3. The system for rapid temperature shock test of wide temperature zone of deep space exploration product based on liquid nitrogen soaking according to claim 1, wherein the liquid nitrogen container is made of stainless steel and is a vertical cylinder.
4. The system for rapid temperature shock test of wide temperature zone of deep space exploration product based on liquid nitrogen soaking according to claim 1, wherein liquid nitrogen pipeline valve employs self-controlled electromagnetic valve.
5. The system for testing the rapid temperature shock of the wide temperature zone of the deep space exploration product based on liquid nitrogen soaking according to claim 1, wherein the guide rod and the mounting platform are welded by argon arc welding.
6. The liquid nitrogen soaking-based wide-temperature-zone rapid temperature shock test system for deep space exploration products according to claim 2, wherein the lifting rope is made of steel wire.
7. The liquid nitrogen soaking-based wide-temperature-zone rapid temperature impact test system for deep space exploration products according to claim 1, wherein the heating device adopts an infrared quartz lamp.
8. The liquid nitrogen soaking-based wide-temperature-zone rapid temperature shock test system for deep space exploration products according to claim 1, wherein the temperature measuring sensor is a T-shaped thermocouple or a platinum resistor.
9. The liquid nitrogen soaking-based wide-temperature-zone rapid temperature impact test system for deep space exploration products according to any one of claims 1 to 8, wherein one end of the guide rod is connected with the product mounting platform by welding.
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Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1603778A (en) * | 2004-11-05 | 2005-04-06 | 中国科学院上海技术物理研究所 | High and low temperature recycle unit with wide temperature range |
| CN1916795A (en) * | 2006-09-11 | 2007-02-21 | 中国科学院上海技术物理研究所 | Automatic control system and method for cyclic test in multiple service positions and at high and low temperatures |
| CN201116908Y (en) * | 2007-08-29 | 2008-09-17 | 中国电子科技集团公司第二研究所 | High and low temperature shock test box |
| CN103253607A (en) * | 2013-05-02 | 2013-08-21 | 北京卫星环境工程研究所 | Elevator system of vacuum heat test environment |
| CN106644801A (en) * | 2016-12-30 | 2017-05-10 | 中国电子科技集团公司第十八研究所 | Dual-working-condition high-low temperature impact testing equipment for aerospace solar cell |
| CN108168878A (en) * | 2017-12-15 | 2018-06-15 | 北京卫星环境工程研究所 | Spatial rotational mechanism floor synthetic verification test system based on the moment of reaction |
| CN108414260A (en) * | 2018-03-15 | 2018-08-17 | 北京卫星环境工程研究所 | Martian surface thermal environment simulation system |
| CN109799184A (en) * | 2019-03-12 | 2019-05-24 | 北京卫星环境工程研究所 | Knockdown spacecraft cable assembly temperature and irradiation comprehensive test system |
| CN109799421A (en) * | 2019-03-12 | 2019-05-24 | 北京卫星环境工程研究所 | The combined environment test of aerospace optical connector studies system |
-
2019
- 2019-10-08 CN CN201910948409.9A patent/CN110646315A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1603778A (en) * | 2004-11-05 | 2005-04-06 | 中国科学院上海技术物理研究所 | High and low temperature recycle unit with wide temperature range |
| CN1916795A (en) * | 2006-09-11 | 2007-02-21 | 中国科学院上海技术物理研究所 | Automatic control system and method for cyclic test in multiple service positions and at high and low temperatures |
| CN201116908Y (en) * | 2007-08-29 | 2008-09-17 | 中国电子科技集团公司第二研究所 | High and low temperature shock test box |
| CN103253607A (en) * | 2013-05-02 | 2013-08-21 | 北京卫星环境工程研究所 | Elevator system of vacuum heat test environment |
| CN106644801A (en) * | 2016-12-30 | 2017-05-10 | 中国电子科技集团公司第十八研究所 | Dual-working-condition high-low temperature impact testing equipment for aerospace solar cell |
| CN108168878A (en) * | 2017-12-15 | 2018-06-15 | 北京卫星环境工程研究所 | Spatial rotational mechanism floor synthetic verification test system based on the moment of reaction |
| CN108414260A (en) * | 2018-03-15 | 2018-08-17 | 北京卫星环境工程研究所 | Martian surface thermal environment simulation system |
| CN109799184A (en) * | 2019-03-12 | 2019-05-24 | 北京卫星环境工程研究所 | Knockdown spacecraft cable assembly temperature and irradiation comprehensive test system |
| CN109799421A (en) * | 2019-03-12 | 2019-05-24 | 北京卫星环境工程研究所 | The combined environment test of aerospace optical connector studies system |
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Application publication date: 20200103 |