High-low temperature vibration test system and test method for attitude and orbit control engine in vacuum environment

Abstract

This invention relates to an attitude and orbit control engine simulation test apparatus and method, specifically to a high and low temperature vibration test system and method for an attitude and orbit control engine under vacuum conditions. This addresses the shortcomings of existing engine power systems, which only conduct single-item test verification and assessment of mechanical environment, thermal environment, or engine thermal test environment, and cannot perform comprehensive test verification of a coupled mechanical and thermal environment. The high and low temperature vibration test system for an attitude and orbit control engine under vacuum conditions includes a vacuum chamber, a vibration loading system, a cooling system, a heating system, a support frame, and a test piece adapter. This invention enables simulation testing of attitude and orbit control engines under mechanical and thermal environments such as vacuum, high temperature, low temperature, and vibration, which is beneficial for improving the adaptability of the power system to complex flight environments. Simultaneously, this invention discloses a high and low temperature vibration test method for an attitude and orbit control engine under vacuum conditions.

Description

Technical Field

[0001] This invention relates to an attitude and orbit control engine simulation test device and method, specifically to a high and low temperature vibration test system and test method for an attitude and orbit control engine under vacuum conditions. Background Technology

[0002] Exploring the establishment of test conditions and research on test technologies under multiple coupled environments is the main direction of attitude and orbit control engine development and testing. Among them, the various sub-techniques involved in multi-field coupled environment testing, such as high-altitude simulation test technology, low-temperature test technology, high-temperature test technology, and vibration and shock test, are gradually developing and becoming more mature.

[0003] Existing engine power systems only undergo single-item testing and verification of mechanical environment, thermal environment, or engine hot test environment, and cannot conduct comprehensive testing and verification of force-thermal coupling environment. However, with the development of miniaturization, lightweighting, fast response, and high reliability technologies, it is necessary to simulate the engine's working performance under comprehensive force-thermal coupling flight environment conditions in ground tests. Therefore, it is essential to carry out research on engine hot test technology under comprehensive force-thermal environment conditions to approximate the actual working conditions of the power system as closely as possible. From the perspective of improving the success rate of aircraft flights, this will enhance the adaptability of the power system to complex flight environments, simulate real complex flight environment conditions in ground tests, and break through the technology of simulation demonstration and verification of the power system in the real flight environment. Summary of the Invention

[0004] The purpose of this invention is to address the shortcomings of existing engine power systems, which only conduct single-item test verification and assessment of mechanical environment, thermal environment, or engine thermal test environment, and cannot conduct comprehensive test verification of mechanical and thermal coupled environment. This invention provides a high and low temperature vibration test system and test method for attitude and orbit control engines under vacuum environment.

[0005] To address the shortcomings of the existing technology, the present invention provides the following technical solution:

[0006] A high and low temperature vibration test system for attitude and orbit control engine under vacuum environment is characterized by including a vacuum chamber, a vibration loading system, a cooling system, a heating system, a support, and a test piece adapter.

[0007] The vibration loading system includes a vibration table, and a vibration control mechanism and a data acquisition mechanism connected to the vibration table respectively. The vibration table is set on a guide rail on the bottom surface of the vacuum chamber, and the support is set on the vibration table. The test piece adapter is coaxially set on the moving coil of the vibration table, and the upper end of the test piece adapter is used to set the engine to be tested. The vibration control mechanism is used to control the vibration of the vibration table, and the data acquisition mechanism is used to collect the vibration information of the vibration table.

[0008] The cooling system is used to create a low-temperature environment around the engine under test. It includes a cold plate mechanism and a refrigerant supply mechanism that are connected to each other. The cold plate mechanism is located on the top of the support and is located around and above the engine under test. The cold plate mechanism has an opening at the outlet of the engine under test. The refrigerant supply mechanism is located outside the vacuum chamber.

[0009] The heating system is used to create a high-temperature environment around the engine under test, and includes a heating device, a cooling device, and a heating control device. The heating device is located inside the cold plate mechanism and around the engine under test, and has an opening at the outlet of the engine under test. The cooling device is located on the heating device. The heating control device is connected to the heating device.

[0010] Furthermore, the vibration control mechanism includes a vibration controller and a power amplifier installed outside the vacuum chamber. The output of the vibration controller is connected to the input of the power amplifier, and the output of the power amplifier is connected to the moving coil of the vibration table. The data acquisition mechanism includes a sensor installed on the moving coil of the vibration table and a data acquisition device installed outside the vacuum chamber. The output of the sensor is connected to the input of the data acquisition device.

[0011] Furthermore, a power supply through-chamber flange is provided on the wall of the vacuum chamber, and the heating control device is located outside the vacuum chamber and is connected to the heating device by cable through the power supply through-chamber flange. The part of the cable located inside the vacuum chamber is provided with a cold-pressed sleeve, the end of the cold-pressed sleeve is covered with insulating tape, and the insulating tape is covered with a heat shrink tubing.

[0012] Furthermore, the power supply through-chamber flange includes a conductive rod and a sealing element sleeved on the conductive rod; the sealing element has a first protective sleeve and a second protective sleeve sleeved on the conductive rod at both ends; the conductive rod passes through the vacuum chamber wall, the sealing element is fixed to the outer wall of the vacuum chamber, and the second protective sleeve extends into the vacuum chamber.

[0013] Furthermore, the sealing element includes a first sealing ring connected to the first protective sleeve, a second sealing ring connected to the second protective sleeve, a sealing ring disposed between the first sealing ring and the second sealing ring, and a pressure ring disposed between the sealing ring and the second sealing ring.

[0014] Furthermore, the heating system also includes a cooling device, which uses a combination of multiple tungsten filament quartz lamp arrays. The cooling device uses nitrogen as the medium, and the inert gas layer slows down the rate at which evaporated tungsten particles deposit on the inner wall of the lamp tube, thus extending the service life of the lamp tube.

[0015] Furthermore, the internal medium of the cold plate mechanism is liquid nitrogen and / or cryogenic alcohol, and the refrigerant supply mechanism includes a cryogenic circulation pump and a cryogenic medium channel passing through the vacuum chamber wall. The cryogenic circulation pump is interconnected with the cold plate mechanism through the cryogenic medium channel.

[0016] Furthermore, the vibration control mechanism also includes a cooling shroud disposed around the moving coil of the vibration table.

[0017] Meanwhile, this invention provides a method for high and low temperature vibration testing of an attitude and orbit control engine under vacuum conditions, using the aforementioned high and low temperature vibration testing system for an attitude and orbit control engine under vacuum conditions. Its unique feature is that it includes the following steps:

[0018] Step 1: Set the engine to be tested onto the moving coil of the vibration table via the test piece adapter, and connect the vibration control mechanism, data acquisition mechanism, cooling system, and heating system.

[0019] Step 2: Set temperature measuring points at preset positions on the cold plate mechanism, vibration table, and engine to be tested by spot welding or pasting.

[0020] Step 3: Close the vacuum chamber and perform vacuuming until the pressure drops below 1000 Pa.

[0021] Step 4: Vacuum low-temperature vibration test;

[0022] The cooling system is turned on. Once the engine temperature reaches the preset low temperature value, the vibration loading system is started and a random vibration test is conducted using the random vibration mode. After vibration initialization and equalization, random vibration is started. After the test is completed, the temperature and vibration data are output through the data acquisition mechanism, and the cooling system and vibration loading system are turned off, thus completing the low-temperature vibration test of the engine.

[0023] Step 5: Vacuum high-temperature vibration test;

[0024] The heating system is turned on. When the engine temperature reaches the preset high temperature value, the vibration loading system is started and a random vibration test is conducted using the random vibration mode. After vibration initialization and equalization, random vibration is started. After the test is completed, the temperature and vibration data are output through the data acquisition mechanism, and the heating system and vibration loading system are turned off, thus completing the high temperature vibration test of the engine.

[0025] Step 6: Impact environment simulation test;

[0026] The vibration loading system is started, and the impact vibration mode is adopted. The impact magnitude and interval duration are set. After vibration initialization and equalization, the impact vibration is started. After the test, the vibration data is output through the data acquisition mechanism, and the vibration loading system is turned off, thus completing the engine impact environment simulation test.

[0027] Compared with the prior art, the beneficial effects of the present invention are:

[0028] (1) The present invention provides a high and low temperature vibration test system for attitude and orbit control engine under vacuum environment, including a vacuum chamber, a vibration loading system, a cooling system, a heating system, a support, and a test piece adapter; the present invention can realize the simulation test of attitude and orbit control engine under force and heat environment such as vacuum, high temperature, low temperature, and vibration, which is beneficial to improving the adaptability of the power system to complex flight environment.

[0029] (2) The present invention provides a high and low temperature vibration test system for attitude and orbit control engine under vacuum environment. In order to facilitate the control of the temperature uniformity of the low temperature environment and reduce the cost of the refrigerant consumed for cooling the entire cabin, the present invention adopts a local cooling method, that is, a cold plate structure is used to control the local temperature, and the temperature is precisely controlled by adjusting the refrigerant supply mechanism. The present invention can achieve low temperature simulation of the target temperature of attitude and orbit control engine ±2℃, which meets the requirements of cold start in low temperature environment.

[0030] (3) The present invention provides a high and low temperature vibration test system for attitude and orbit control engine under vacuum environment. It uses multiple sets of tungsten filament quartz lamp arrays as heating devices to simulate high heat flux density. The multiple sets of tungsten filament quartz lamp arrays are used to simulate the thermal environment in the coupled environment through thermal radiation and convection. A high temperature environment is formed around the test engine through heat exchange, which can achieve high temperature heating. Nitrogen gas is used as the medium of the cooling device to cool down the multiple sets of tungsten filament quartz lamp arrays. The inert gas layer slows down the rate at which the evaporated tungsten particles are deposited on the inner wall of the lamp tube, thus extending the service life of the lamp tube.

[0031] (4) In the vacuum environment attitude control engine high and low temperature vibration test system of the present invention, the heating control device is connected to the heating device by a power supply through the chamber flange. The part of the cable located in the vacuum chamber is provided with a cold-pressed sleeve. The end of the cold-pressed sleeve is covered with insulating tape. The insulating tape is covered with heat shrink tubing to avoid vacuum discharge and damage to the equipment and products. Attached Figure Description

[0032] Figure 1 This is a schematic diagram of an embodiment of the high and low temperature vibration test system for attitude and orbit control engine under vacuum environment according to the present invention;

[0033] Figure 2 This is a schematic diagram of the power supply through-cabin flange in an embodiment of the present invention.

[0034] The reference numerals in the attached drawings are explained as follows: 1-vacuum chamber, 11-guide rail; 21-vibration table, 211-moving coil, 221-vibration controller, 222-power amplifier, 231-sensor, 232-data acquisition unit; 31-cold plate mechanism, 32-refrigerant supply mechanism; 41-heating device, 42-heating control device; 5-support; 6-test piece adapter; 7-power supply through-chamber flange, 71-conductive rod, 72-sealing element, 721-first sealing ring, 722-second sealing ring, 723-sealing ring, 724-pressure ring, 73-first protective sleeve, 74-second protective sleeve. Detailed Implementation

[0035] The present invention will be further described below with reference to the accompanying drawings and exemplary embodiments.

[0036] Reference Figure 1 A high and low temperature vibration test system for attitude and orbit control engine under vacuum environment includes a vacuum chamber 1, a vibration loading system, a cooling system, a heating system, a support 5, and a test piece adapter 6.

[0037] The vibration loading system includes a vibration table 21, and a vibration control mechanism and a data acquisition mechanism connected to the vibration table 21. The vibration table 21 is mounted on a guide rail 11 on the bottom surface of the vacuum chamber 1 for easy movement. The support 5 is mounted on the vibration table 21. The test piece adapter 6 is coaxially mounted on the moving coil 211 of the vibration table 21. The upper end of the test piece adapter 6 is used to mount the engine to be tested. A cooling shroud is provided around the moving coil 211 of the vibration table 21. The vibration control mechanism is used to control the vibration of the vibration table 21. It includes a vibration controller 221 and a power amplifier 222 located outside the vacuum chamber 1. The output end of the vibration controller 221 is connected to the input end of the power amplifier 222, and the output end of the power amplifier 222 is connected to the moving coil 211 of the vibration table 21. The data acquisition mechanism is used to collect vibration information of the vibration table 21. It includes a sensor 231 installed on the moving coil 211 of the vibration table 21 and a data acquisition device 232 installed outside the vacuum chamber 1. The output end of the sensor 231 is connected to the input end of the data acquisition device 232.

[0038] The cooling system is used to create a low-temperature environment around the engine under test. It includes a cold plate mechanism 31 and a refrigerant supply mechanism 32 connected to each other. The cold plate mechanism 31 is located on top of the support 5 and around and above the engine under test. The cold plate mechanism 31 has an opening at the outlet of the engine under test. The internal medium of the cold plate mechanism 31 is liquid nitrogen or cryogenic alcohol. The refrigerant supply mechanism 32 is located outside the vacuum chamber 1. It includes a cryogenic circulation pump and a cryogenic medium channel passing through the wall of the vacuum chamber 1. The cryogenic circulation pump is connected to the cold plate mechanism 31 through the cryogenic medium channel.

[0039] The heating system is used to create a high-temperature environment around the engine under test. It includes a heating device 41, a cooling device, and a heating control device 42. The heating device 41 is located inside the cold plate mechanism 31 and around the engine under test. The heating device 41 has an opening at the outlet of the engine under test. In this embodiment, the heating device 41 uses a combination of multiple tungsten filament quartz lamp arrays. The cooling device is installed on the heating device 41, and the cooling medium is nitrogen. A power supply through-chamber flange 7 is provided on the wall of the vacuum chamber 1. The heating control device 42 is located outside the vacuum chamber 1 and is connected to the heating device 41 via the power supply through-chamber flange 7 using a cable. The portion of the cable inside the vacuum chamber 1 is fitted with a cold-pressed sleeve, and the end of the cold-pressed sleeve is covered with insulating tape. A heat-shrink tubing is then placed over the insulating tape. The cable is wired according to the three phases A, B, and C, with each phase maintaining a certain distance to ensure the safety of vacuum power supply heating.

[0040] Reference Figure 2 The power supply through-chamber flange 7 includes a conductive rod 71 and a sealing element 72 sleeved on the conductive rod 71. A first protective sleeve 73 and a second protective sleeve 74, both sleeved on the conductive rod 71, are respectively provided at both ends of the sealing element 72. The conductive rod 71 passes through the wall of the vacuum chamber 1, the sealing ring is fixed to the outer wall of the vacuum chamber 1, and the second protective sleeve 74 extends into the vacuum chamber 1. The sealing element 72 includes a first sealing ring 721 connected to the first protective sleeve 73, a second sealing ring 722 connected to the second protective sleeve 74, a sealing ring 723 disposed between the first sealing ring 721 and the second sealing ring 722, and a pressure ring 724 disposed between the sealing ring 723 and the second sealing ring 722.

[0041] Based on the above-mentioned high and low temperature vibration test system for attitude and orbit control engines under vacuum conditions, this invention provides a method for high and low temperature vibration test of attitude and orbit control engines under vacuum conditions, comprising the following steps:

[0042] Step 1: Place the engine to be tested onto the moving coil 211 of the vibration table 21 via the test piece adapter 6; and connect the vibration control mechanism, data acquisition mechanism, cooling system, and heating system.

[0043] Step 2: Set temperature measuring points at preset positions on the cold plate mechanism 31, vibration table 21, and engine to be tested by spot welding or pasting.

[0044] Step 3: Close vacuum chamber 1 and perform vacuuming until the pressure drops below 1000 Pa.

[0045] Step 4: Vacuum low-temperature vibration test;

[0046] Turn on the cooling system. When the engine temperature reaches the preset low temperature value, start the vibration loading system and use the random vibration mode. The parameter settings are shown in Table 1. Perform the random vibration test. After vibration initialization and equalization, the random vibration is started. After the test is completed, the temperature and vibration data are output through the data acquisition mechanism, and the cooling system and vibration loading system are turned off, thus completing the low temperature vibration test of the engine.

[0047] Table 1

[0048]

[0049] Step 5: Vacuum high-temperature vibration test;

[0050] Turn on the heating system. When the engine temperature reaches the preset high temperature value, start the vibration loading system and use the random vibration mode. The parameter settings are shown in Table 2. Perform the random vibration test. After vibration initialization and equalization, the random vibration is started. After the test, output the temperature and vibration data through the data acquisition mechanism, and turn off the heating system and vibration loading system to complete the engine high temperature vibration test.

[0051] Table 2

[0052]

[0053] Step 6: Impact environment simulation test;

[0054] The vibration loading system was started, and the impact vibration mode was adopted. The impact magnitude and interval duration were set as shown in Table 3. After vibration initialization and equalization, the impact vibration was started. After the test, the vibration data was output through the data acquisition mechanism, and the vibration loading system was turned off, thus completing the engine impact environment simulation test.

[0055] Table 3

[0056] Experimental direction Order of magnitude (g) Duration Number of impacts +Z direction 90g 6ms 2 times

[0057] The above embodiments are only used to illustrate the technical solutions of the present invention, and are not intended to limit them. For those skilled in the art, modifications can be made to the specific technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. However, these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions protected by the present invention.

Claims

1. A high and low temperature vibration test system for an attitude and orbit control engine under vacuum conditions, characterized in that, Includes a vacuum chamber (1), a vibration loading system, a cooling system, a heating system, a support (5), and a test specimen adapter (6); The vibration loading system includes a vibration table (21), and a vibration control mechanism and a data acquisition mechanism connected to the vibration table (21); the vibration table (21) is set on the guide rail (11) on the bottom surface of the vacuum chamber (1), the support (5) is set on the vibration table (21), the test piece adapter (6) is coaxially set on the moving coil (211) of the vibration table (21), and the upper end of the test piece adapter (6) is used to set the engine to be tested; the vibration control mechanism is used to control the vibration of the vibration table (21), and the data acquisition mechanism is used to collect the vibration information of the vibration table (21); The cooling system is used to create a low-temperature environment around the engine to be tested. It includes a cold plate mechanism (31) and a refrigerant supply mechanism (32) connected to each other. The cold plate mechanism (31) is located on the top of the support (5) and around and above the engine to be tested. The cold plate mechanism (31) has an opening at the outlet of the engine to be tested. The refrigerant supply mechanism (32) is located outside the vacuum chamber (1). The heating system is used to create a high-temperature environment around the engine to be tested. It includes a heating device (41) and a heating control device (42). The heating device (41) is located inside the cold plate mechanism (31) and around the engine to be tested. The heating device (41) has an opening at the outlet of the engine to be tested. A cooling device is installed on the heating device (41). The heating control device (42) is connected to the heating device (41).

2. The high and low temperature vibration test system for attitude and orbit control engine under vacuum environment according to claim 1, characterized in that: The vibration control mechanism includes a vibration controller (221) and a power amplifier (222) installed outside the vacuum chamber (1). The output end of the vibration controller (221) is connected to the input end of the power amplifier (222), and the output end of the power amplifier (222) is connected to the moving coil (211) of the vibration table (21). The data acquisition mechanism includes a sensor (231) installed on the moving coil (211) of the vibration table (21) and a data acquisition device (232) installed outside the vacuum chamber (1). The output end of the sensor (231) is connected to the input end of the data acquisition device (232).

3. The high and low temperature vibration test system for attitude and orbit control engine under vacuum environment according to claim 2, characterized in that: The vacuum chamber (1) is provided with a power supply through-chamber flange (7) on its wall. The heating control device (42) is located outside the vacuum chamber (1) and is connected to the heating device (41) by cable through the power supply through-chamber flange (7). The part of the cable located inside the vacuum chamber (1) is provided with a cold-pressed sleeve. The end of the cold-pressed sleeve is covered with insulating tape, and the insulating tape is covered with a heat shrink tube.

4. The high and low temperature vibration test system for attitude and orbit control engine under vacuum environment according to claim 3, characterized in that: The power supply through-chamber flange (7) includes a conductive rod (71) and a sealing element (72) sleeved on the conductive rod (71); the sealing element (72) has a first protective sleeve (73) and a second protective sleeve (74) sleeved on the conductive rod (71) at both ends; the conductive rod (71) passes through the wall of the vacuum chamber (1), the sealing element (72) is fixed to the outer wall of the vacuum chamber (1), and the second protective sleeve (74) extends into the vacuum chamber (1).

5. The high and low temperature vibration test system for attitude and orbit control engine under vacuum environment according to claim 4, characterized in that: The sealing element (72) includes a first sealing ring (721) connected to the first protective sleeve (73), a second sealing ring (722) connected to the second protective sleeve (74), a sealing ring (723) disposed between the first sealing ring (721) and the second sealing ring (722), and a pressure ring (724) disposed between the sealing ring (723) and the second sealing ring (722).

6. The high and low temperature vibration test system for attitude and orbit control engine under vacuum environment according to claim 5, characterized in that: The heating system also includes a cooling device. The heating device (41) uses a combination of multiple tungsten filament quartz lamp arrays, and the cooling device uses nitrogen as the medium.

7. The high and low temperature vibration test system for attitude and orbit control engine under vacuum environment according to claim 6, characterized in that: The internal medium of the cold plate mechanism (31) is liquid nitrogen and / or cryogenic alcohol. The refrigerant supply mechanism (32) includes a cryogenic circulation pump and a cryogenic medium channel passing through the wall of the vacuum chamber (1). The cryogenic circulation pump is connected to the cold plate mechanism (31) through the cryogenic medium channel.

8. The high and low temperature vibration test system for attitude and orbit control engine under vacuum environment according to any one of claims 1 to 7, characterized in that: The vibration control mechanism also includes a cooling fan shroud located around the moving coil (211) of the vibration table (21).

9. A method for high and low temperature vibration testing of an attitude and orbit control engine under vacuum conditions, using the high and low temperature vibration testing system for an attitude and orbit control engine under vacuum conditions as described in claim 1, characterized in that, Includes the following steps: Step 1: Place the engine to be tested on the moving coil (211) of the vibration table (21) through the test piece adapter (6), and connect the vibration control mechanism, data acquisition mechanism, cooling system and heating system; Step 2: Set temperature measuring points at preset positions on the cold plate mechanism (31), vibration table (21) and engine to be tested by spot welding or pasting; Step 3: Close the vacuum chamber (1) and perform vacuuming until the vacuum level is below 1000Pa; Step 4: Vacuum low-temperature vibration test; The cooling system is turned on. Once the engine temperature reaches the preset low temperature value, the vibration loading system is started and a random vibration test is conducted using the random vibration mode. After vibration initialization and equalization, random vibration is started. After the test is completed, the temperature and vibration data are output through the data acquisition mechanism, and the cooling system and vibration loading system are turned off, thus completing the low-temperature vibration test of the engine. Step 5: Vacuum high-temperature vibration test; The heating system is turned on. When the engine temperature reaches the preset high temperature value, the vibration loading system is started and a random vibration test is conducted using the random vibration mode. After vibration initialization and equalization, random vibration is started. After the test is completed, the temperature and vibration data are output through the data acquisition mechanism, and the heating system and vibration loading system are turned off, thus completing the high temperature vibration test of the engine. Step 6: Impact environment simulation test; The vibration loading system is started, and the impact vibration mode is adopted. The impact magnitude and interval duration are set. After vibration initialization and equalization, the impact vibration is started. After the test, the vibration data is output through the data acquisition mechanism, and the vibration loading system is turned off, thus completing the engine impact environment simulation test.

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