CN220096647U - Thermal strength assessment test device for connection part of conical cabin section of aircraft - Google Patents
Thermal strength assessment test device for connection part of conical cabin section of aircraft Download PDFInfo
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- CN220096647U CN220096647U CN202320739772.1U CN202320739772U CN220096647U CN 220096647 U CN220096647 U CN 220096647U CN 202320739772 U CN202320739772 U CN 202320739772U CN 220096647 U CN220096647 U CN 220096647U
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- 238000012360 testing method Methods 0.000 title claims abstract description 122
- 238000004088 simulation Methods 0.000 claims abstract description 68
- 230000007246 mechanism Effects 0.000 claims abstract description 9
- 230000000452 restraining effect Effects 0.000 claims abstract description 9
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 75
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims description 69
- 229910052802 copper Inorganic materials 0.000 claims description 69
- 239000010949 copper Substances 0.000 claims description 69
- 238000001816 cooling Methods 0.000 claims description 20
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims description 18
- 239000010453 quartz Substances 0.000 claims description 12
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N silicon dioxide Inorganic materials O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 12
- 239000007788 liquid Substances 0.000 claims description 11
- 230000001105 regulatory effect Effects 0.000 claims description 10
- 239000000498 cooling water Substances 0.000 claims description 9
- 229910052757 nitrogen Inorganic materials 0.000 claims description 9
- 239000000919 ceramic Substances 0.000 claims description 4
- 230000008859 change Effects 0.000 claims description 3
- 230000001276 controlling effect Effects 0.000 claims description 3
- 238000010438 heat treatment Methods 0.000 claims description 3
- 238000012544 monitoring process Methods 0.000 claims description 2
- 230000003044 adaptive effect Effects 0.000 claims 1
- 238000005192 partition Methods 0.000 description 8
- 238000000034 method Methods 0.000 description 6
- 230000008569 process Effects 0.000 description 5
- 230000008878 coupling Effects 0.000 description 3
- 238000010168 coupling process Methods 0.000 description 3
- 238000005859 coupling reaction Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 238000005452 bending Methods 0.000 description 2
- 230000006378 damage Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000005611 electricity Effects 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- 208000027418 Wounds and injury Diseases 0.000 description 1
- 230000002159 abnormal effect Effects 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 208000014674 injury Diseases 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000013021 overheating Methods 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 230000035945 sensitivity Effects 0.000 description 1
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
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- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The utility model relates to the technical field of aircraft tests, and discloses a thermal strength assessment test device for a conical cabin section joint of an aircraft, which comprises a test piece fixing tool, a conical cylindrical pneumatic thermal simulation device and a pneumatic pressure simulation device, wherein the conical cylindrical pneumatic thermal simulation device is arranged at the front end of the test piece fixing tool along the central axis of the test piece fixing tool; the pneumatic thermal simulation device is arranged on the position adjusting mechanism capable of linearly moving to adjust the front and back positions of the pneumatic thermal simulation device, the pneumatic thermal simulation device is used for providing thermal load for the connection position between the front section and the rear section of the test piece restrained by the restraining mechanism at the rear end and the front and back regions of the test piece, and the pneumatic pressure simulation device is arranged below the cone-shaped front section of the test piece and applies upward force load to the lower side of the front section of the test piece. The utility model can more truly reproduce the flight environment of the aircraft during flight, and satisfies the reproduction of aerodynamic heat and aerodynamic pressure of the aircraft during high-speed flight in the high-altitude environment.
Description
Technical Field
The utility model relates to the technical field of aircraft tests, in particular to a thermal strength assessment test device for a conical cabin section joint of an aircraft.
Background
The flight environment is complex and variable when the aircraft flies in high altitude environment and hypersonic speed. In order to ensure the safe and stable flight of the aircraft in the high-altitude environment, the complex stress load caused by aerodynamic heat and air flow when the aircraft flies is required to be reproduced, so that the combined test of the ground force and the heat is an important means for realizing the aim. At present, the ground force heat combination test device of the heat assessment test of the connection part of the conical cabin section of the aircraft has great value in practical application. In high altitude environment, the geometrical shape of the aircraft is different, so that the aerodynamic heat and the aerodynamic pressure are complex and changeable during the flight. The existing ground force heat combination test adopts a single pneumatic thermal simulation device and a pneumatic pressure simulation device, so that a larger error can be caused to a test result.
Disclosure of Invention
The utility model aims at solving the technical defects existing in the prior art, and provides a thermal strength checking test device for the connection part of a conical cabin section of an aircraft, which is a force thermal coupling test device for simulating the actual flight environment of high-altitude flight.
The technical scheme adopted for realizing the purpose of the utility model is as follows:
the hot strength examination test device comprises a test piece fixing tool, a conical cylindrical pneumatic heat simulation device and a pneumatic pressure simulation device, wherein the conical cylindrical pneumatic heat simulation device is arranged at the front end of the test piece fixing tool along the central axis of the test piece fixing tool, and the pneumatic pressure simulation device is arranged at the front end of the pneumatic heat simulation device; the pneumatic thermal simulation device is arranged on the position adjusting mechanism capable of linearly moving to adjust the front and back positions of the test piece, the pneumatic thermal simulation device is used for providing the pneumatic thermal temperature ranging from normal temperature to 1000 ℃ for the connection position between the front section and the rear section of the test piece restrained by the restraining mechanism at the rear end and the front and back areas of the test piece, and the pneumatic pressure simulation device is arranged below the conical front section of the test piece and is used for applying the force load ranging from 0 MPa to 0.2MPa to the lower side of the front section of the test piece so as to carry out the thermal assessment test on the connection position of the front section.
The test device can convert electric energy into heat energy through the pneumatic thermal simulation device in the ground force thermal coupling test, and provides the surface of the aircraft with the required temperature; the pressure is regulated by a pneumatic pressure simulation device through a pressure regulating valve, and the temperature and the target pressure are precisely controlled through a thermal load system and a force load system.
The test device of the utility model can be designed for cylindrical and conical aircraft with geometry to provide a force load of 0-0.2MPa (relative to atmospheric pressure) and a thermal load of normal temperature to 1000 ℃. According to the test device, the safety and reliability of the test are ensured by arranging the maintenance equipment, the supporting system for the normal operation of the test piece and the temperature upper limit alarm system.
Drawings
FIG. 1 is a control flow chart of the test apparatus of the present utility model.
FIG. 2 is a schematic view showing the overall structure of the test device of the present utility model.
FIG. 3 is an illustration of a cooling control flow of the circulating water cooling of the safety control system of the present utility model.
Fig. 4 is a thermal load backup control flow diagram of the thermal load system of the present utility model.
FIG. 5 is a schematic diagram of the thermal strength test piece according to the present utility model.
Fig. 6 is a schematic view of a reflection plate and a pneumatic thermal simulator according to the present utility model.
Fig. 7 is a general schematic of a pneumatic thermal simulation apparatus of the present utility model.
Fig. 8 is an assembly schematic view of the first reflecting plate of the present utility model.
Fig. 9 is an assembled sectional view of the first reflecting plate of the present utility model.
Fig. 10 is an assembly schematic view of the second reflecting plate of the present utility model.
Fig. 11 is a schematic cross-sectional view of the second reflecting plate of the present utility model.
Fig. 12 is a schematic view of the pneumatic pressure simulator of the present utility model.
FIG. 13 is a schematic view of the support and securing tool of the present utility model.
Fig. 14 is a schematic diagram of pressure regulation control of the pneumatic pressure simulator of the present utility model.
Reference numerals illustrate:
1. a quartz lamp tube; 2-1, a first copper bar; 2-2, a second copper bar; 3. copper pipe; 4. an insulating ceramic ring; 5-1, a first copper bar clamp at the small end; 5-2, a second copper bar clamp at the small end; 5-3, a first copper bar clamp at the large end; 5-4, a second copper bar clamp at the large end; 6-1, a first reflecting plate; 6-2, a second reflecting plate; 7. a power line connection device; 8. a thermal load system; 9. a force loading system; 10. a safety control system; 11. a water bag; 12. loading a tool; 13. a gas-liquid mixing device; 14. a pressure regulating valve; 15. an industrial personal computer; 16. a data collector; 17. a pressure sensor; 18. a cooling circulating water inlet; 19. a cooling circulating water outlet; 20. a cooling water cavity; 21. a load-bearing cross beam; 22. a load-bearing upright; 23. a fixed bottom plate; 24. fixing a test piece; 25. a conformal structure; 26. a shape-following structure restraining bar; 27. a conformal structural support; 28. a reflective plate support; 29. a slide rail; 30. a jack; 31. loading a tool support; 100. a rear section; 200. a front section; 300. a connection location; 400. and a restraining mechanism.
Detailed Description
The utility model is described in further detail below with reference to the drawings and the specific examples. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the scope of the utility model.
The thermal strength test device for the connection part of the conical cabin section of the aircraft is suitable for verifying the influence of pneumatic heat and pneumatic pressure on the connection part of the cabin section of the aircraft in a high-altitude environment, can provide a force load of 0-0.2MPa and a thermal load of normal temperature-1000 ℃, and meets the requirement of the reproduction of the pneumatic heat and the pneumatic pressure when the aircraft flies at high speed in the high-altitude environment.
The test object of the test device of the embodiment of the utility model is mainly an aircraft (hereinafter referred to as a test piece) with a cylindrical or conical shape, and the bottom of the test piece is arranged on a test piece fixing tool during test; moving the pneumatic thermal simulation device to enable the joint of the test piece to be located in the thermal radiation range of the pneumatic thermal simulation device, wherein the pneumatic thermal simulation device can provide a temperature ranging from normal temperature to 1000 ℃; the front end of the test piece is located above a pneumatic pressure simulator which is capable of applying a force load of 0-0.2MPa (relative to atmospheric pressure) in an upward direction to the front end of the test piece.
As shown in fig. 1 to 14, the thermal strength test device for the connection part of the conical cabin section of the aircraft according to the embodiment of the utility model is a force thermal coupling test device, and comprises a test piece fixing tool, a conical cylindrical pneumatic thermal simulation device arranged at the front end of the test piece fixing tool along the central axis of the test piece fixing tool, and a pneumatic pressure simulation device arranged at the front end of the pneumatic thermal simulation device; the pneumatic thermal simulation device is arranged on a position adjusting mechanism capable of linearly moving back and forth and adjusting the front and back positions of the pneumatic thermal simulation device, the pneumatic thermal simulation device is used for providing thermal load for the connection position 300 of the front section 200 and the rear section 100 of the test piece-aircraft restrained by the restraining mechanism 400 at the rear end and the front and back regions of the front section, and the pneumatic pressure simulation device is arranged below the conical front section 200 of the test piece and is used for applying upward force load to the lower side of the front section of the test piece so as to carry out thermal assessment test on the connection position of the front section (such as a conical cabin section).
In some embodiments, the aerodynamic thermal simulation device includes a plurality of quartz lamp tubes, arranged at intervals along a width direction, and arranged obliquely with respect to a central axis of the tapered cylindrical aerodynamic thermal simulation device, and a reflecting plate having a water cooling function is arranged at an outer side of the quartz lamp tubes to reflect heat generated by the quartz lamp tubes to a surface of the test piece.
In some embodiments, the positive and negative electrodes of the quartz lamp tubes are embedded into a copper bar for supplying electricity to the quartz lamp tubes, and the internal threads of the conductive copper bar are connected with the external threads of one end of the conductive copper tube in a threaded mode; the insulating ceramic ring 4 is connected with the copper pipe 3 and the copper bar clamp, is sleeved outside the copper pipe 3, enables the copper pipe 3 to be separated from the copper bar clamp, is connected with the reflecting plate of the pneumatic thermal simulation device and is arranged on the reflecting plate, the insulating ceramic ring 4 is utilized to separate the copper pipe 3 from the copper bar clamp, high-voltage leakage is prevented, the test device is ensured not to leak electricity and support the thermal load device in the electrifying process, and damage to test pieces and injury to operators are prevented. In addition, copper pipe 3 is connected with power cord connecting device 7, and power cord connecting device 7 passes through the power cord to be connected with direct current power cabinet, ensures the stable output of power in the test process.
The temperature born by the surface of the aircraft is different in the actual flight process, such as uneven aerodynamic heat distribution of the windward side and the leeward side of the conical aircraft in the flight process. In order to make the ground test environment more close to the real flight environment, in some embodiments of the utility model, the pneumatic thermal simulation device is divided into an upper half partition and a lower half partition; of course, the method is not limited to the arrangement of the two partitions, and more partitions can be arranged according to the actual flight environment.
Under the embodiment that the pneumatic thermal simulation device is divided into an upper half partition and a lower half partition for heating simulation, the copper bar comprises a first copper bar 2-1 and a second copper bar 2-2, the first copper bar 2-1 and the second copper bar 2-2 can respectively comprise two semicircular copper bars, the two matched semicircular copper bars are arranged at two ends of the conical tubular pneumatic thermal simulation device and are arranged at intervals relatively in a buckling mode, the two semicircular copper bars of the first copper bar 2-1 are arranged at the small diameter end of the conical tubular pneumatic thermal simulation device, and the two semicircular copper bars of the second copper bar 2-2 are arranged at the large diameter end of the conical tubular pneumatic thermal simulation device.
In some embodiments, the copper bar clamp may include a copper bar clamp located at a small diameter end side of the conical cylindrical pneumatic thermal simulator, including a small end first copper bar clamp 5-1, a small end second copper bar clamp 5-2, and a copper bar clamp located at a large diameter end side of the conical cylindrical pneumatic thermal simulator, including a large end first copper bar clamp 5-3 and a large end second copper bar clamp 5-4, specifically, three copper bar clamps may be configured for each semicircular copper bar, taking one semicircular copper bar as an example, two copper bar clamps are disposed at positions near two ends of the semicircular copper bar, and one copper bar clamp is disposed at a position near the middle of the semicircular copper bar, which is not limited in this embodiment.
In some embodiments, the reflecting plate includes a first reflecting plate 6-1 and a second reflecting plate 6-2, the first reflecting plate 6-1 and the second reflecting plate 6-2 are respectively similar to semicircular structures, and the first reflecting plate 6-1 and the second reflecting plate 6-2 can form a conical cylindrical structure adapted to the shape of the conical cylinder of the pneumatic thermal simulator after being buckled and connected by bolts through the connecting edges at two ends.
In some embodiments, in order to prevent the pneumatic thermal simulation device from overheating, a safety control system 10 is provided to cool the copper bar and the reflective plate of the pneumatic thermal simulation device, and cooling circulating water is provided to cool the copper bar and the reflective plate. The reflecting plate and the copper bars are respectively provided with a cooling cavity, and respective cooling water inlet and outlet pipelines of the reflecting plate and the copper bars are connected with a cooling water circulation pipeline; the cooling circulating water flows out of the water inlet water separator in two ways, and the circulating water is conveyed to the copper bar from the water separator in one way, so that the circulating water flows into the water outlet water separator after flowing through the copper bar; the other circulating water flows into the reflecting plate and then flows into the water outlet separator. Taking a semicircular reflecting plate as an example, the reflecting plate is provided with a cooling circulating water inlet 18 and a cooling circulating water outlet 19, and is communicated with an internal cooling water cavity 20. Wherein, the copper bar realizes the inlet and outlet of cooling circulating water through the connected copper pipe 3.
In some embodiments, in order to solve the problem that the cooling effect of the circulating water is insufficient due to the overhigh temperature, a heat exchanger is arranged, and the heat exchanger is connected with a low-temperature nitrogen source through a low-temperature nitrogen valve and a water inlet water separator, so that the connected circulating water enters the water inlet water separator after the temperature of the circulating water is reduced through heat exchange of the heat exchanger; when the cooling effect of the circulating water is insufficient due to the fact that the temperature is too high, the low-temperature nitrogen valve is automatically opened, the temperature of the circulating water is reduced by introducing the heat exchanger, and the cooling capacity of the circulating water is improved. When the circulating water cooling capacity is enough, the nitrogen valve is closed to prevent the circulating water from crystallizing.
Thermocouples are adhered to the wall surface of the reflecting plate and the positions of the ports of the tube of the quartz lamp, the temperature of the corresponding positions is detected, if the temperature of the corresponding positions is detected to be too high, an alarm is given, a nitrogen valve is opened, nitrogen heat exchange is introduced, the temperature of cooling water is reduced, the temperature of the reflecting plate is ensured not to overheat in the heat test process, and a specific flow can be shown by referring to FIG. 3. When cooling, the cooled water is introduced into the water inlet water separator, flows into the reflecting plate through the water inlet water separator, flows into the water outlet water separator after flowing through the reflecting plate, and meanwhile, a temperature sensor is arranged in the water outlet water separator to detect the temperature of the water outlet, and is connected with the thermal load system 8.
For this reason, in some embodiments, the thermal load system for controlling the operation of the pneumatic thermal simulation device adopts a PID control mode, the adjustment mode is feedback adjustment, the temperature target value set by the upper computer is compared with the thermocouple measurement value (the upper half partition and the lower half partition) through the PID controller, the output voltage is controlled to be 0-10V, the sensitivity is adjusted, the magnitude of the output voltage is controlled, and the output power of the pneumatic thermal simulation device is adjusted to realize thermal feedback adjustment by controlling the power supply of the direct current power cabinet. Specifically, a thermocouple (such as a K-type thermocouple) can be stuck on the test piece, the temperature of the surface of the test piece is measured, the measured temperature is fed back to the thermal load system 8, the thermal load system 8 adjusts and controls the output power of the direct current power supply cabinet through a PID, the closed loop control of the thermal load is realized, and the temperature monitoring of important measuring points is realized.
To ensure accuracy of the test, in some embodiments, the thermal load system backs up the temperature control data, i.e., two thermocouples (e.g., K-type thermocouples) are used at the temperature control point; comparing the data collected by the two thermocouples when a thermal load is applied; when temperature control data continuously collected for a plurality of times (such as 10 times or other preset times) exceeds a set error (such as exceeding tolerance 10%), comparing the temperature control data with a target value, selecting data close to the target value as control data, outputting an optimal value to a thermal load system, and outputting a signal to a power cabinet to control power supply output by the thermal load system according to the optimal value, so that the accuracy of a test is ensured. The specific control flow is shown in fig. 4.
In some embodiments, the pneumatic pressure simulation device comprises a water bag for loading, such as a rubber water bag, the water bag is pressurized, such as a water bag, the water bag is embedded into the loading tool, a certain amount of water is injected into the water bag, the water bag is connected with the gas-liquid mixing device, and the pressure regulating valve is used for pressurizing the gas-liquid mixing device, so that the regulation of the stress of the water bag is realized. In some embodiments, the pneumatic pressure simulation device can control the force load through a force load system 9, and compare the pressure target value set by the upper computer with the pressure sensor measurement value through a PID controller, wherein the force load system controls the output signal of the industrial personal computer through a PID adjustment mode, controls the opening of a pressure adjusting valve, and the pressure adjusting valve acts after receiving the signal to adjust the gas pressure; the pressure sensor arranged on the gas-liquid mixing device feeds back the force load to the industrial personal computer, so that closed-loop control of the force load is realized. Specifically, the pressure regulating valve 14 is connected with the gas-liquid mixing device 13, the gas-liquid mixing device 13 is connected with the water bag 11, and the water bag 11 is embedded into a limit groove on the surface of the loading tool 12; the gas-liquid mixing device 13 is in threaded connection with a pressure sensor 17, the pressure sensor 17 is connected with a data acquisition unit 16, the data acquisition unit 16 transmits data to the industrial personal computer 15, and the industrial personal computer 15 adjusts the pressure regulating valve 14 through the feedback force load data, as shown in fig. 14.
In some embodiments, the pneumatic pressure simulation device comprises a loading tool support 31, and the top end surface of the loading tool support 31 is connected with the jack 30. In some embodiments, the number of the jacks 30 is preferably four, and the jacks 30 are arranged at the positions near four corners of the top end surface of the loading tool support 31, and the loading tool 12 is arranged at the top end of the jacks 30.
Because the combination of the aircraft connection is mainly tested when a force load is applied, in some embodiments, in order to protect the bottom of the test piece and the test piece fixing tool from being damaged under the action of the bending moment, a wooden conformal structure is adopted to offset the bending moment on the bottom of the test piece when the force load is applied. In some embodiments, a semicircular shape following structure 25 is arranged above the bearing beam 21 between the reflecting plate supporting piece 28 and the test piece fixing tool 24, the shape following structure 25 adopts a wooden structure, two ends of the shape following structure 25 are connected with the top ends of at least two shape following structure restraining rods 26 which are vertically arranged and are spaced apart, and the bottom ends of the shape following structure restraining rods 26 are connected with shape following structure supporting pieces 27 which are horizontally arranged on the upper end face of the bearing beam 21.
In some embodiments, a bearing upright 22 is disposed on one side of a top end surface of the bearing beam 21, a front side surface of the bearing upright 22 is connected with a fixed bottom plate 23, and the fixed bottom plate 23 is connected with a rear end of a test piece fixing tool 24, so that the test piece fixing tool is mounted on the bearing upright 22.
In some embodiments, two sliding rails 29 without a space between the sliding rails 29 in the width direction are disposed at the top end of the bearing beam 21, the sliding rails 29 are connected with a reflecting plate supporting member 28, the reflecting plate supporting member 28 is slidably supported, the reflecting plate supporting member 28 supports the reflecting plate of the aerodynamic thermal simulation device, and the reflecting plate can be moved along the direction of the sliding rails to adjust the position so as to adapt to the position of a test piece for heating, and provide a test thermal load.
The upper end surface of the bearing beam 21 is provided with the loading tool support 31, and the loading tool support 31 is connected with the bearing beam 21 by bolts.
When a force load is applied, the test piece often deforms, in order to monitor the change of strain of the important part of the test piece when the force load and the heat load are applied, in some embodiments, strain gauges are arranged on the test piece to detect the corresponding change data of the force load and the heat load, the deformation degree of the strain gauges is monitored, the strain gauges are connected with a data acquisition unit 16, the monitored data are fed back to the data acquisition unit, and the data acquisition unit 16 is connected with an industrial personal computer 15. The strain gauge can adopt a strain gauge with a 1/4 bridge connection mode.
When a test is carried out, a test piece is arranged on the test piece fixing tool 24, and the follow-up structure 25 is tightly attached to the upper part of the test piece; placing the aerodynamic thermal simulation device at a designated position of the test piece by utilizing the slide rail 29; fine-tuning the first copper bar 2-1 and the second copper bar 2-2, and fastening the first copper bar 2-1 and the second copper bar 2-2 by using a copper bar clamp; placing the assembled pneumatic pressure simulation device at a designated position, and adjusting the jack 30 to enable the water bag 11 on the loading tool 12 and the test piece to be gapless; connecting the external circulating water to a water inlet water separator to enable the external circulating water to flow into the reflecting plate; the direct-current power supply cabinet is connected with the copper pipe 3 through a power line, the power line connecting device is used for checking whether the pneumatic thermal simulation device is insulated or not, and electric leakage is avoided after the pneumatic thermal simulation device is electrified. The K-type thermocouple and the strain gauge on the test piece are respectively connected with a thermal load system 8 and a data acquisition unit 16; checking whether the data display is normal or not, and ensuring the normal channel; connecting the pressure sensor 17 to a data collector; the direct-current power supply cabinet is connected with the thermal load system 8, and the emergency stop key extension line is placed on an industrial control desk, so that when the temperature is abnormal, the emergency stop key extension line is convenient to beat; and connecting an external power supply with the direct-current power supply cabinet.
Before the test starts, a force load loading curve is set in the industrial personal computer 15, whether the regulating valve operates normally or not is detected, and whether the data acquired by the data acquisition unit 16 are normal or not is detected. After the force load is over, a thermal load is applied to the test piece, a temperature loading curve is set in a thermal load system 8, and the direct current cabinet, the water inlet water separator and the water outlet water separator are started; in the heat load system 8, whether the measured temperature value of the K-type thermocouple is normal or not is observed, and whether the temperature of the water separator is too high or not is observed. After all the display is normal, a formal test is performed.
During the formal test, the circulating water cooling device, the pneumatic heat simulation device and the pneumatic pressure simulation device are firstly turned on, after the safety is checked and the connection is normal, the loading curve is edited, the power supply and the regulating valve are turned on, and the formal test is started.
While the fundamental and principal features of the utility model and advantages of the utility model have been shown and described, it will be apparent to those skilled in the art that the utility model is not limited to the details of the foregoing exemplary embodiments, but may be embodied in other specific forms without departing from the spirit or essential characteristics thereof;
the present embodiments are, therefore, to be considered in all respects as illustrative and not restrictive, the scope of the utility model being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein.
Furthermore, it should be understood that although the present disclosure describes embodiments, not every embodiment is provided with a separate embodiment, and that this description is provided for clarity only, and that the disclosure is not limited to the embodiments described in detail below, and that the embodiments described in the examples may be combined as appropriate to form other embodiments that will be apparent to those skilled in the art.
Claims (12)
1. The device is characterized by comprising a test piece fixing tool, a conical cylindrical pneumatic thermal simulation device and a pneumatic pressure simulation device, wherein the conical cylindrical pneumatic thermal simulation device is arranged at the front end of the test piece fixing tool along the central axis of the test piece fixing tool, and the pneumatic pressure simulation device is arranged at the front end of the pneumatic thermal simulation device; the pneumatic thermal simulation device is arranged on a position adjusting mechanism capable of linearly moving to adjust the front and back positions of the test piece, the pneumatic thermal simulation device is used for providing a thermal load of ambient temperature ranging from normal temperature to 1000 ℃ for the connection position of the front section and the rear section of the test piece restrained by the restraint mechanism at the rear end and the front and back regions of the test piece, and the pneumatic pressure simulation device is arranged below the conical front section of the test piece and is used for applying a force load ranging from 0 MPa to 0.2MPa upwards to the lower part of the front section of the test piece so as to carry out thermal assessment test on the connection position of the front section.
2. The device for testing the thermal strength of the connection part of the conical cabin section of the aircraft according to claim 1, wherein the aerodynamic heat simulation device comprises a plurality of quartz lamp tubes which are arranged at intervals along the width direction and are inclined to the central axis of the aerodynamic heat simulation device in a conical shape, and a reflecting plate with a water cooling function is arranged on the outer side of each quartz lamp tube so as to reflect heat generated by the quartz lamp tube to the surface of the test piece.
3. The device for testing the thermal strength of the connection part of the conical cabin section of the aircraft according to claim 2, wherein the reflecting plate comprises a first reflecting plate and a second reflecting plate, and the first reflecting plate and the second reflecting plate are buckled and connected together and can form a conical cylindrical structure which is adaptive to the shape of the conical cylinder of the aerodynamic thermal simulation device after being buckled.
4. The thermal strength assessment test device for the connection position of the conical cabin section of the aircraft according to claim 2, wherein the anode and the cathode of the quartz lamp tube are connected to two groups of copper bars which are arranged at intervals along the axial direction of the aerodynamic thermal simulation device, the copper bars are connected with copper tubes, the copper tubes are connected with a power line connecting device, and the power line connecting device is connected with a direct current power cabinet through a power line; the copper pipe is covered with an insulating ceramic ring outside, the copper pipe is separated from the copper bar clamp, and the copper bar clamp is arranged on the end face of the reflecting plate.
5. The device for testing the thermal strength of the connection part of the conical cabin section of the aircraft according to claim 4, wherein the reflecting plate and the copper bar are respectively provided with a cooling cavity, a cooling water inlet and outlet pipeline of each reflecting plate and a cooling water circulation pipeline of each copper bar are connected, a heat exchanger is arranged on the cooling water circulation pipeline, the heat exchanger is connected with a low-temperature nitrogen source, and the low-temperature nitrogen source is connected with a low-temperature nitrogen valve; temperature sensors are respectively arranged on the wall surface of the reflecting plate, the port positions of the quartz lamp tubes and the water outlet and water distribution device of the cooling circulating water, and the cooling water inlet and outlet pipes of the copper bars are copper pipes.
6. The device for testing the thermal strength of the connection part of the conical cabin section of the aircraft according to claim 1, wherein a thermocouple is arranged on the test piece to measure the temperature of the surface of the test piece, and the measured temperature is fed back to the thermal load system; the thermal load system is based on a PID control mode, and the output power of the pneumatic thermal simulation device is adjusted by controlling the output voltage so as to realize thermal feedback adjustment;
two thermocouples are arranged at each temperature monitoring point of the test piece, and when a thermal load is applied, temperature control data acquired by the two thermocouples are compared; when the temperature control data continuously collected for a plurality of times exceeds the set error, comparing the temperature control data with the target value, outputting an optimal value to a thermal load system, and outputting a signal to a power cabinet to control power output by the thermal load system according to the optimal value.
7. The device for testing the thermal strength of the connection part of the conical cabin section of the aircraft according to claim 2, wherein the pneumatic pressure simulation device comprises a water bag for loading, the water bag is pressurized, the water bag is embedded into the loading tool, a preset amount of water is injected into the water bag, the water bag is connected with the gas-liquid mixing device, the gas-liquid mixing device is pressurized through the pressure regulating valve, the gas-liquid mixing device is connected with the pressure sensor, the pressure sensor is connected with the data collector, the data collector is connected with the industrial personal computer, the pressure regulating valve is controlled by the industrial personal computer through the force loading system based on PID regulation to realize the pressurization control of the gas-liquid mixing device, and the regulation of the stress of the water bag is realized.
8. The device for testing the thermal strength of the connection part of the conical cabin section of the aircraft according to claim 7, wherein the water bag is embedded into a limiting groove on the surface of a loading tool, the loading tool is arranged at the top end of a jack, and the jack is arranged at the top end surface of a supporting piece of the loading tool; the four jacks are arranged at the positions near four corners of the top end surface of the loading tool supporting piece, and the loading tool supporting piece is fixedly connected with the bearing cross beam.
9. The device for testing the thermal strength of the connection part of the conical cabin section of the aircraft according to claim 8, wherein a semicircular follow-up structure is arranged in front of the test piece fixing tool, a reflecting plate supporting piece for supporting a reflecting plate of the aerodynamic thermal simulation device is arranged in front of the follow-up structure, two ends of the follow-up structure are connected with the top ends of at least two follow-up structure restraining rods which are vertically arranged and are spaced apart, and the bottom ends of the follow-up structure restraining rods are connected with the follow-up structure supporting pieces which are horizontally arranged on the upper end face of the bearing cross beam.
10. The device for testing the thermal strength of the connection part of the conical cabin section of the aircraft according to claim 8, wherein the bearing upright post is arranged on one side of the top end face of the bearing cross beam, the front side face of the bearing upright post is connected with the fixing bottom plate, and the fixing bottom plate is connected with the rear end of the test piece fixing tool, so that the test piece fixing tool is installed on the bearing upright post.
11. The device for testing the thermal strength of the connection of the conical cabin segments of the aircraft according to claim 8, wherein two sliding rails spaced apart in the width direction are arranged at the top end of the bearing beam, and are connected with the reflecting plate supporting member to slidably support the reflecting plate supporting member, so that the reflecting plate can be moved in the direction of the sliding rails to adjust the position, so as to adapt to the heating of the position of the test piece, and provide the thermal load for the test.
12. The thermal strength assessment test device for the connection part of the conical cabin section of the aircraft according to claim 1, wherein a strain gauge is arranged on the surface of the test piece to detect the force load and the change of the thermal load at the corresponding position, the deformation degree is monitored, the strain gauge is connected with a data acquisition unit, the monitored data is fed back to the data acquisition unit, and the data acquisition unit is connected with an industrial personal computer.
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| CN202310049458.5A CN115806058A (en) | 2023-02-01 | 2023-02-01 | Thermal strength examination test device for aircraft conical cabin section joint |
| CN2023100494585 | 2023-02-01 |
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| CN202320739772.1U Active CN220096647U (en) | 2023-02-01 | 2023-04-06 | Thermal strength assessment test device for connection part of conical cabin section of aircraft |
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| CN116399715B (en) * | 2023-06-09 | 2023-08-29 | 天津航天瑞莱科技有限公司 | Aviation pipeline's hot strength test device |
| CN117664584B (en) * | 2024-01-30 | 2024-04-19 | 天津航天瑞莱科技有限公司 | Thermal noise test device for test piece |
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| CN201229251Y (en) * | 2008-05-22 | 2009-04-29 | 北京航空航天大学 | Infrared thermal source water cooling device for high-temperature aerodynamic heat simulation test for missile aircraft |
| CN201618902U (en) * | 2010-02-05 | 2010-11-03 | 中国北方车辆研究所 | Liquid nitrogen gasification circulating water cooling device |
| CN102809438B (en) * | 2012-08-16 | 2014-02-05 | 北京航空航天大学 | Measuring device for high surface temperature of cylindrical nonmetallic housing of high-speed aircraft |
| CN103234815B (en) * | 2013-04-15 | 2015-04-22 | 哈尔滨工业大学 | Test jig for testing K type composite material joint intensity |
| CN104925269B (en) * | 2015-05-08 | 2016-09-21 | 湖北航天技术研究院总体设计所 | The assay device of a kind of high hypervelocity aircraft cabin section thermal environment and method |
| US9976925B2 (en) * | 2015-10-16 | 2018-05-22 | Kidde Technologies, Inc. | Apparatus and method for testing linear thermal sensors |
| CN105734245B (en) * | 2016-03-29 | 2018-04-20 | 广东龙丰精密铜管有限公司 | Copper pipe processing online annealing equipment protection gas power-economizing method and system |
| CN205426665U (en) * | 2016-04-01 | 2016-08-03 | 中国特种设备检测研究院 | Brittle material tensile test anchor clamps |
| CN106604420A (en) * | 2016-11-21 | 2017-04-26 | 上海航天精密机械研究所 | Large cylinder structure test piece static heating test profiling heating device |
| CN108918582A (en) * | 2018-07-05 | 2018-11-30 | 北京强度环境研究所 | A kind of hot external pressure test system and method for aircraft cargo tank structure |
| CN108945535A (en) * | 2018-07-12 | 2018-12-07 | 上海卫星装备研究所 | A kind of Space environment simulation facility nitrogen cooling type chilled water unit |
| RU2695514C1 (en) * | 2018-10-12 | 2019-07-23 | Акционерное общество "Военно-промышленная корпорация "Научно-производственное объединение машиностроения" | Test bench for load tests of aircraft compartment |
| CN110361318B (en) * | 2019-06-04 | 2020-09-01 | 浙江大学 | Steel bridge deck corrosion fatigue coupling test method and device thereof |
| CN112351517B (en) * | 2020-11-05 | 2022-10-18 | 北京机电工程研究所 | Fixed heating device for testing infrared radiation characteristics of high-temperature air inlet channel and testing method |
| CN112504684B (en) * | 2020-12-16 | 2024-07-09 | 天津航天瑞莱科技有限公司 | Outer culvert casing static, thermal and internal pressure load test device |
| CN114739821A (en) * | 2022-06-14 | 2022-07-12 | 中国飞机强度研究所 | Aerospace plane wall plate structure load simulation test device and method |
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