CN114923724B - Gradient thermal shock and thermal fatigue test device and method for aerospace vehicle structure - Google Patents
Gradient thermal shock and thermal fatigue test device and method for aerospace vehicle structure Download PDFInfo
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- 238000009661 fatigue test Methods 0.000 title claims abstract description 46
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M99/00—Subject matter not provided for in other groups of this subclass
- G01M99/002—Thermal testing
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
- G01J5/00—Radiation pyrometry, e.g. infrared or optical thermometry
- G01J5/0066—Radiation pyrometry, e.g. infrared or optical thermometry for hot spots detection
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M99/00—Subject matter not provided for in other groups of this subclass
- G01M99/005—Testing of complete machines, e.g. washing-machines or mobile phones
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- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05B—ELECTRIC HEATING; ELECTRIC LIGHT SOURCES NOT OTHERWISE PROVIDED FOR; CIRCUIT ARRANGEMENTS FOR ELECTRIC LIGHT SOURCES, IN GENERAL
- H05B6/00—Heating by electric, magnetic or electromagnetic fields
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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
Abstract
The invention discloses a gradient thermal shock and thermal fatigue test device and method for an aerospace vehicle structure, the device comprises a control box and a clamping mechanism which is arranged on the control box in a sliding mode and used for clamping a structural sample, a heating mechanism used for heating the structural sample in an impact mode, a cooling mechanism used for cooling the structural sample and a temperature measuring mechanism used for measuring the temperature of the structural sample are further arranged on the control box, a sliding rail used for the clamping mechanism to slide is arranged on the control box, and the heating mechanism and the cooling mechanism are matched with each other, so that the structural sample can be conveniently and rapidly lifted and the gradient temperature distribution is conveniently presented. The method comprises the following steps: 1. determining a gradient temperature load target value; 2. carrying out gradient thermal shock and thermal fatigue tests; 3. applying a heating load; 4. applying a cooling load; 5. the gradient temperature field load is applied, so that long-time gradient thermal shock is carried out on the structural sample, the real service condition of the aerospace vehicle is conveniently simulated, and the gradient thermal shock and thermal fatigue test is completed.
Description
Technical Field
The invention belongs to the technical field of gradient thermal shock fatigue tests, and particularly relates to a gradient thermal shock and thermal fatigue test device and method for an aerospace vehicle structure.
Background
High-supersonic aircraft, large carrier rockets, aircraft engines and the like in the aerospace field have become the development key points of China and other countries as high-end equipment representing national advanced technologies, complex gradient thermal shock environments such as ultra-high temperature (above 2000 ℃), high temperature rise rate (200 ℃/s-300 ℃/s), high temperature fall rate (100 ℃/s) and the like are inevitably faced in the use process of the high-end equipment, and a high-temperature-resistant structure with certain gradient thermal shock resistance is required to realize the safe operation of the major equipment, so that the gradient thermal shock fatigue resistance of the high-temperature-resistant structure becomes the key problem of failure development of equipment such as the hypersonic aircraft, the large carrier rockets and the like.
The high-temperature resistant structure on the aerospace vehicle is generally made of a high-temperature resistant ceramic material, and in order to ensure that the high-temperature resistant structure can be safely used in a gradient thermal shock environment, whether the high-temperature resistant structure can bear the damage behaviors such as medium and long-term high temperature in service, the gradient thermal shock environment, fatigue damage and the like needs to be determined, so that a gradient thermal shock fatigue simulation test needs to be carried out on the high-temperature resistant structure. Through a gradient thermal shock fatigue simulation test, the real service working condition of the high-temperature-resistant structure is simulated, so that the service life and the safety and reliability of the high-temperature-resistant structure in real service can be further analyzed.
At present, the common gradient thermal shock heating modes are mainly gas heating and induction coil heating. The gas heating uses mixed combustion of oxygen, propane and other gases to generate high-temperature flame to directly heat a sample, and cooling gas is provided on the back of the sample to increase the thermal gradient of the sample, but the temperature of the high-temperature flame is difficult to accurately control, so that the problem of uneven heating of the surface of the sample is easily caused, the tail gas generated by a treatment test is very complex, and leakage or insufficient combustion of combustion gas can bring a series of potential safety hazards to the operation of equipment; induction heating inductively heats the surface region of a sample by a coil, but this method is only applicable to a conductive sample, and is not applicable to a ceramic material, and the application range is small. Therefore, it is necessary to develop a gradient thermal shock fatigue test apparatus suitable for a high temperature resistant structure in an aerospace vehicle.
Disclosure of Invention
The invention aims to solve the technical problem that in order to overcome the defects in the prior art, the gradient thermal shock and thermal fatigue test device for the aerospace craft structure is provided, and the temperature rise mechanism and the temperature fall mechanism are arranged to be matched, so that the structure sample can be quickly raised and lowered, and gradient temperature distribution is conveniently presented, the real service condition of the aerospace craft can be conveniently simulated, and the aerospace craft is convenient to popularize and use.
In order to solve the technical problems, the invention adopts the technical scheme that: aerospace vehicle structure is with gradient thermal shock and thermal fatigue test device, its characterized in that: the device comprises a control box and a clamping mechanism which is arranged on the control box in a sliding manner and is used for clamping a structural sample, wherein the control box is also provided with a heating mechanism for impact heating of the structural sample, a cooling mechanism for cooling the structural sample and a temperature measuring mechanism for measuring the temperature of the structural sample, and the control box is provided with a slide rail for the sliding of the clamping mechanism;
the clamping mechanism comprises a first sliding plate arranged on the sliding rail and a clamp arranged on the first sliding plate, and the structural sample is clamped in the clamp;
the temperature raising mechanism comprises a fiber laser positioned at the left end of the slide rail and an optical lens positioned between the fiber laser and the structural sample, a controller for controlling the power of the fiber laser is arranged in the control box, the optical lens is installed on the slide rail through a second slide plate, and laser emitted from the fiber laser is focused on the left side surface of the structural sample through the optical lens;
the cooling mechanism comprises a cold air pipe which is positioned at the right end of the slide rail and used for conveying cold air to the right side surface of the structural sample;
the temperature measuring mechanism comprises a left infrared thermometer and a right infrared thermometer which are respectively used for collecting the temperatures of the left surface and the right surface of the structural sample, and the left infrared thermometer and the right infrared thermometer are respectively positioned at the two ends of the slide rail.
The gradient thermal shock and thermal fatigue test device for the aerospace vehicle structure is characterized in that: the heights of the optical fiber laser, the optical lens and the structural sample are the same.
The gradient thermal shock and thermal fatigue test device for the aerospace vehicle structure is characterized in that: the sliding rail comprises a first rail and a second rail which are arranged on the control box, the second rail is positioned at the upper part of the first rail, and the width of the second rail is smaller than that of the first rail;
the first sliding plate and the second sliding plate are clamped on the second rail and abut against the upper surface of the first rail.
The gradient thermal shock and thermal fatigue test device for the aerospace vehicle structure is characterized in that: and the first sliding plate is provided with a U-shaped protective cover covering the outer side of the structural sample.
The gradient thermal shock and thermal fatigue test device for the aerospace vehicle structure is characterized in that: the control box is provided with a left vertical plate and a right vertical plate which are respectively positioned at two ends of the first track;
the fiber laser and the left infrared thermometer are both installed on the left vertical plate, and the right infrared thermometer and the cold air pipe are both installed on the right vertical plate.
The gradient thermal shock and thermal fatigue test device for the aerospace vehicle structure is characterized in that: and a cold air extension pipe is further arranged on the right vertical plate, one end of the cold air extension pipe is communicated with the cold air pipe, and the other end of the cold air extension pipe penetrates through the right vertical plate and extends to the right side of the structural sample.
The gradient thermal shock and thermal fatigue test device for the aerospace vehicle structure is characterized in that: the fixture is a flat plate component, a through hole and a plurality of protruding parts which are uniformly distributed on the side wall of the through hole and extend to the center of the through hole are arranged on the fixture, and the protruding parts are circumferentially clamped on the outer side wall of the structural sample.
The gradient thermal shock and thermal fatigue test device for the aerospace vehicle structure is characterized in that: the optical lens is a convex lens.
Meanwhile, the invention also discloses a gradient thermal shock and thermal fatigue test method for the aerospace vehicle structure, which has simple steps and convenient operation, adjusts the power of the fiber laser according to the acquired data, realizes the long-time gradient thermal shock on the structural sample, completes the gradient thermal shock and thermal fatigue test, realizes the accurate control of the surface temperature of the structural sample, and improves the authenticity and the accuracy of the test, and is characterized by comprising the following steps:
step one, determining a gradient temperature load target value: determining gradient temperature load target values which need to be applied to a structural sample at different moments in a gradient thermal shock and thermal fatigue test according to the real working condition of the aerospace vehicle, wherein the gradient temperature load target values comprise a first temperature load target value and a second temperature load target value;
step two, performing gradient thermal shock and thermal fatigue tests: applying temperature loads at corresponding moments to the structural sample at different moments, continuously acquiring a left real-time temperature value of the left side surface of the structural sample through a left infrared thermometer, continuously acquiring a right real-time temperature value of the right side surface of the structural sample through a right infrared thermometer, enabling the left real-time temperature value to accord with the first temperature load target value at the corresponding moment, and enabling the right real-time temperature value to accord with the second temperature load target value at the corresponding moment;
the temperature load comprises a heating load, a cooling load and a gradient temperature field load, and when the heating load needs to be applied to the structural sample, the third step is executed; when the cooling load is required to be applied to the structural sample, executing a fourth step; when gradient temperature field load needs to be applied to the structural sample, executing a fifth step;
step three, applying a heating load: opening the optical fiber laser, and adjusting the positions of the structural sample and the optical lens on a slide rail, so that laser emitted from the optical fiber laser is focused on the left side surface of the structural sample through the optical lens;
when the left real-time temperature value does not accord with the first temperature load target value, the power of the optical fiber laser is adjusted through the controller to change the heat flow density received by the structural sample until the left real-time temperature value accords with the first temperature load target value;
step four, applying a cooling load: delivering cold air to the structural sample through a cold air pipe until the right real-time temperature value meets the second temperature load target value;
step five, applying gradient temperature field load: opening the optical fiber laser, and simultaneously conveying cold air to the structural sample through a cold air pipe to enable the temperature on the structural sample to present gradient distribution;
when the left real-time temperature value does not accord with the first temperature load target value, the power of the optical fiber laser is adjusted through the controller to change the heat flow density received by the structural sample until the left real-time temperature value accords with the first temperature load target value.
The gradient thermal shock and thermal fatigue test method for the aerospace vehicle structure is characterized in that in the third step and the fifth step, the specific process of adjusting the power of the optical fiber laser is as follows: according to the formula
To obtain a control rate
Further adjusting the power of the optical fiber laser;
wherein the content of the first and second substances,
is a proportional term, an
，
Is a weight parameter of the proportional term,
as a function of the residual error of the left real-time temperature value and the first temperature load target value,
the working time of the optical fiber laser is;
wherein the content of the first and second substances,
is a differential term, and
，
a weight parameter which is a differential term;
wherein the content of the first and second substances,
in order to attenuate the integral term,
and is and
get
Or
，
In order to attenuate the weight parameter of the integral term,
for working said fiber laser
At the time of day, the user may,
from time 0 to time 0
The variable between the time of day is,
in order to be able to obtain the attenuation coefficient,
is as follows
A residual error value of the left real-time temperature value and the first temperature load target value at the time,
in order to find the minimum function,
in order to be the maximum amplitude of the attenuation,
in order to find the maximum function,
is the minimum amplitude of the attenuation;
wherein, the first and the second end of the pipe are connected with each other,
is an integral of the feed forward term, an
，
To integrate the weight parameters of the feed forward term,
for the first temperature load target value
The curve gradient at that moment;
wherein the content of the first and second substances,
is a dynamic compensation term, and
，
is a weight parameter for the dynamic compensation term,
for the first temperature load target value
The gradient of the curve at the time immediately preceding the time.
Compared with the prior art, the invention has the following advantages:
1. according to the invention, the temperature rise mechanism is arranged to facilitate the temperature rise of the structural sample, and the temperature reduction mechanism is arranged to facilitate the temperature reduction of the structural sample, so that the structural sample can be rapidly heated and reduced, the simulation of various complex temperature curve environments is realized, the simulation of the real service condition of the aerospace vehicle is facilitated, and the gradient temperature distribution is presented in the structural sample, so that the gradient thermal shock and thermal fatigue test is performed on the structural sample, the subsequent analysis of the service life and the safety and reliability of the high-temperature-resistant structure in real service on the aerospace vehicle is facilitated, and the practicability is strong.
2. According to the invention, the fiber laser is matched with the optical lens, so that laser emitted by the fiber laser irradiates on the structural sample, the remote non-contact heating of the structural sample is realized, and the heating mode is safe and high in efficiency; can remove on the slide rail through setting up optical lens, be convenient for according to the distance between structure sample and the fiber laser, need shine the difference of the model of target location and fiber laser on the structure sample, adjust optical lens's position, make the laser focus on the structure sample that fiber laser jetted out, make the energy of laser concentrate more, the heat affected zone is more accurate, and the heating method is reliable and stable, avoids causing the pollution to the structure sample, excellent in use effect.
3. According to the invention, the left infrared thermometer and the right infrared thermometer are respectively arranged at the two ends of the slide rail, so that the heating temperature at the left side and the cooling temperature at the right side of the structural sample can be conveniently and respectively collected, more accurate and effective real-time temperature values can be conveniently obtained, the test error is reduced, and the practicability is strong.
4. The method has simple steps and convenient and fast operation, and the real-time temperature values of the left side and the right side of the structural sample are transmitted to the controller, so that the controller can conveniently adjust the power of the fiber laser according to the calculation result, thereby not only realizing long-time gradient thermal shock on the structural sample and completing the gradient thermal shock and thermal fatigue test, but also realizing the accurate control on the surface temperature of the structural sample, improving the authenticity and the accuracy of the test and being convenient for popularization and use.
In conclusion, the gradient thermal shock and thermal fatigue test device adopted by the invention is convenient for quickly lifting and lowering the structural sample and presenting gradient temperature distribution by arranging the heating mechanism and the cooling mechanism to be matched, thereby being convenient for simulating the real service condition of the aerospace vehicle; the gradient thermal shock and thermal fatigue test method is simple in steps and convenient and fast to operate, the power of the fiber laser is adjusted according to the collected data, long-time gradient thermal shock on the structural sample is achieved, the gradient thermal shock and thermal fatigue test is completed, the surface temperature of the structural sample is accurately controlled, and the authenticity and accuracy of the test are improved.
The technical solution of the present invention is further described in detail by the accompanying drawings and embodiments.
Drawings
FIG. 1 is a schematic structural diagram of the gradient thermal shock and thermal fatigue testing apparatus according to the present invention.
Fig. 2 is a schematic view of the structure in the direction a of fig. 1.
FIG. 3 is a front view of the gradient thermal shock and thermal fatigue testing apparatus of the present invention.
Fig. 4 is a schematic structural view of the jig of the present invention.
FIG. 5 is a block flow diagram of a method of the present invention.
Description of reference numerals:
1-control box; 2-structural sample; 3-a first track;
4-a second track; 5-a first slide plate; 6-a clamp mounting bar;
7, clamping; 8-a through hole; 9-a boss;
10-a second slide; 11-a lens mount; 12-an optical lens;
13-left vertical plate; 14-fiber laser; 15-left infrared thermometer;
16-a right vertical plate; 17-right infrared thermometer; 18-a cold air pipe;
19-a cold air extension pipe; 20-U-shaped shield; 21-graduated scale.
Detailed Description
The aerospace vehicle structure gradient thermal shock and thermal fatigue test device shown in fig. 1-4 comprises a control box 1, a clamping mechanism for clamping a structure sample 2, a heating mechanism for impact heating of the structure sample 2, a cooling mechanism for cooling the structure sample 2 and a temperature measuring mechanism for collecting the temperature of the structure sample 2, wherein the control box 1 is provided with a slide rail for sliding the clamping mechanism.
The clamping mechanism comprises a first sliding plate 5 arranged on the sliding rail and a clamp 7 arranged on the first sliding plate 5, and the structural sample 2 is clamped in the clamp 7.
The heating mechanism comprises a fiber laser 14 positioned at the left end of the slide rail and an optical lens 12 positioned between the fiber laser 14 and the structural sample 2, a controller for controlling the power of the fiber laser 14 is arranged in the control box 1, the optical lens 12 is installed on the slide rail through a second sliding plate 10, and laser emitted from the fiber laser 14 is focused on the left side surface of the structural sample 2 through the optical lens 12.
The cooling mechanism comprises a cold air pipe 18 which is positioned at the right end of the slide rail and used for conveying cold air to the right side surface of the structural sample 2.
The temperature measuring mechanism comprises a left infrared thermometer 15 and a right infrared thermometer 17 which are respectively used for collecting the temperatures of the left surface and the right surface of the structural sample 2, and the left infrared thermometer 15 and the right infrared thermometer 17 are respectively positioned at the two ends of the slide rail.
When the test piece is used, the structural sample 2 is a test piece of a high-temperature resistant ceramic structure used for aerospace vehicles and parts thereof such as hypersonic aircrafts, large carrier rockets, aero-engines and the like, the temperature of the structural sample 2 is conveniently raised by arranging the temperature raising mechanism, and the temperature of the structural sample 2 is conveniently lowered by arranging the temperature lowering mechanism, so that the structural sample 2 can be rapidly raised and lowered, the simulation of various complex temperature curve environments is realized, the real service condition of the aerospace vehicles is conveniently simulated, the gradient temperature distribution can be presented in the structural sample 2, the gradient thermal shock and thermal fatigue test can be carried out on the structural sample 2, and the service life and the safety and reliability of the high-temperature resistant structure in real service on the aerospace vehicles can be conveniently analyzed subsequently.
In an actual test, the optical fiber laser 14 is matched with the optical lens 12, so that laser emitted by the optical fiber laser 14 is irradiated on the structural sample 2, the remote non-contact heating of the structural sample 2 is realized, and the heating mode is safe and high in efficiency; can remove on the slide rail through setting up optical lens 12, be convenient for according to the distance between structural sample 2 and fiber laser 14, need shine the difference of the target location on structural sample 2 and fiber laser 14's model, adjust the position of optical lens 12, make the laser focus that fiber laser 14 jetted out to structural sample 2 on, and make the energy of laser more concentrate, the heat affected zone is more accurate, the heating methods is reliable and stable, avoid causing the pollution to structural sample 2, excellent in use effect.
During actual test, the left infrared thermometer 15 and the right infrared thermometer 17 are arranged at the two ends of the slide rail respectively, so that the left heating temperature and the right cooling temperature of the structural sample 2 can be collected conveniently, more accurate and effective real-time temperature values can be obtained conveniently, test errors are reduced, and the practicability is high.
It should be noted that, the layer of Pt film is disposed on the outer surface of the structural sample 2, which can not only prevent the laser from penetrating through the Pt film and damaging the structural sample 2, but also avoid affecting the heating of the structural sample 2, thereby effectively protecting the safety of the structural sample 2, and better meeting the actual situation.
In the present embodiment, the heights of the fiber laser 14, the optical lens 12, and the structural sample 2 are the same.
In an actual test, the optical lens 12 is mounted on the second sliding plate 10 through the lens mounting rod 11, the clamp 7 is mounted on the first sliding plate 5 through the clamp mounting rod 6, and the heights of the optical fiber laser 14, the optical lens 12 and the structural sample 2 are the same, so that laser emitted by the optical fiber laser 14 can accurately irradiate on the structural sample 2.
In this embodiment, the slide rail includes a first rail 3 and a second rail 4 disposed on the control box 1, the second rail 4 is located on the upper portion of the first rail 3, and the width of the second rail 4 is smaller than the width of the first rail 3; the first sliding plate 5 and the second sliding plate 10 are both clamped on the second rail 4 and abut against the upper surface of the first rail 3.
During the in-service use, first track 3 and second track 4 are the flat board, through setting up the width that the width of second track 4 is less than first track 3, and second track 4 is located the central point on first track 3 upper portion, be convenient for form the wrong platform in the both sides of first track 3 and second track 4, with first slide 5 and the equal joint of second slide 10 on second track 4 and butt first track 3's upper surface, the butt is wrong platform promptly, thereby make the technical staff can manually promote first slide 5 and second slide 10 and slide along the length direction of second track 4, realize the adjustment to optical lens 12 and structure sample 2 position.
It should be noted that, a scale 21 for acquiring the moving distance of the first sliding plate 5 and the second sliding plate 10 is arranged on the control box 1, and the scale 21 is located at the side of the first rail 3 and is arranged along the length direction of the first rail 3.
In this embodiment, a U-shaped shield 20 covering the outside of the structural sample 2 is disposed on the first rail 3.
During the in-service use, the both ends of U type protection casing 20 all are provided with the bending plate of inwards buckling, the bending plate inserts between first slide 5 and the first track 3, be convenient for utilize the upper portion of first slide 5 joint bending plate, the realization is spacing to U type protection casing 20, and U type protection casing 20 can remove along with the removal of first slide 5, through setting up U type protection casing 20, the structural sample 2 direct contact of having avoided technical staff and being in the high temperature state, thereby played the guard action to technical staff.
In this embodiment, the control box 1 is provided with a left vertical plate 13 and a right vertical plate 16 respectively located at two ends of the slide rail, that is, the left vertical plate 13 and the right vertical plate 16 are respectively located at two ends of the first rail 3 and the second rail 4; the fiber laser 14 and the left infrared thermometer 15 are both installed on the left vertical plate 13, and the right infrared thermometer 17 and the cold air pipe 18 are both installed on the right vertical plate 16.
In this embodiment, the right vertical plate 16 is further provided with a cold air extension tube 19, one end of the cold air extension tube 19 is communicated with the cold air tube 18, and the other end of the cold air extension tube 19 penetrates through the right vertical plate 16 and extends to the right side of the structural sample 2.
During the actual use, fiber laser 14 installs in the below of left infrared radiation thermometer 15, air conditioning extension pipe 19 is located the below of right infrared radiation thermometer 17, air conditioning extension pipe 19 is the open hollow structure in both ends, the one end and the air conditioning pipe 18 of air conditioning extension pipe 19 are connected, air conditioning pipe 18 is connected with the air compressor machine, the right flank of structure sample 2 is aimed at to the other end of air conditioning extension pipe 19, the air compressor machine of being convenient for passes through the cooperation of air conditioning pipe 18 with air conditioning extension pipe 19, carry air conditioning to the right flank of structure sample 2, realize the cooling of structure sample 2.
As shown in fig. 4, in this embodiment, the fixture 7 is a flat plate member, the fixture 7 is provided with a through hole 8 and a plurality of protrusions 9 uniformly distributed on a sidewall of the through hole 8 and extending to a center of the through hole 8, and the plurality of protrusions 9 are circumferentially clamped on an outer sidewall of the structural sample 2.
During the in-service use, through setting up a plurality of bellying 9 centre gripping structure sample 2, the clamping-force is high, and stability is strong, through with structure sample 2 centre gripping in through-hole 8, makes to have the clearance between structure sample 2 and the anchor clamps 7, is convenient for reduce the contact surface area of structure sample 2 and anchor clamps 7 to the influence of the temperature of anchor clamps 7 to structure sample 2 has been reduced.
In this embodiment, the optical lens 12 is a convex lens, which facilitates focusing of the laser emitted by the fiber laser 14, and enhances the heating efficiency of the laser.
The method for testing the gradient thermal shock and the thermal fatigue of the aerospace vehicle structure shown in FIG. 5 comprises the following steps:
step one, determining a gradient temperature load target value: according to the real working condition of the aerospace vehicle, gradient temperature load target values needing to be applied to the structural sample 2 at different moments in the gradient thermal shock and thermal fatigue tests are determined, and the gradient temperature load target values comprise a first temperature load target value and a second temperature load target value.
Step two, performing gradient thermal shock and thermal fatigue tests: applying temperature loads at corresponding moments to the structural sample 2 at different moments, continuously acquiring a left real-time temperature value of the left side surface of the structural sample 2 through the left infrared thermometer 15, and continuously acquiring a right real-time temperature value of the right side surface of the structural sample 2 through the right infrared thermometer 17, so that the left real-time temperature value conforms to the first temperature load target value at the corresponding moment, and the right real-time temperature value conforms to the second temperature load target value at the corresponding moment.
The temperature loads comprise a heating load, a cooling load and a gradient temperature field load, and when the heating load needs to be applied to the structural sample 2, the third step is executed; when the cooling load is required to be applied to the structural sample 2, executing a fourth step; and when gradient temperature field loading needs to be applied to the structural sample 2, executing a fifth step.
The temperature increasing load means a load for increasing the temperature of the structure sample 2, the temperature decreasing load means a load for decreasing the temperature of the structure sample 2, and the gradient temperature field load means a load for expressing the temperature of the structure sample 2 as a gradient temperature.
In the actual test, the target value of the gradient temperature load in the gradient thermal shock and thermal fatigue test changes along with the time, namely different target values of the gradient temperature load are set at different moments, and when the temperature-raising load, the temperature-lowering load and the gradient temperature field load need to be repeatedly applied to the structural sample 2, the third step, the fourth step and the fifth step are repeatedly executed according to the target value of the gradient temperature load.
Step three, applying a heating load: turning on the optical fiber laser 14, and adjusting the positions of the structural sample 2 and the optical lens 12 on the slide rail, so that the laser emitted from the optical fiber laser 14 is focused on the left side surface of the structural sample 2 through the optical lens 12; when the left real-time temperature value does not meet the first temperature load target value, the controller adjusts the power of the optical fiber laser 14 to change the heat flow density received by the structural sample 2 until the left real-time temperature value meets the first temperature load target value.
During an actual test, when the optical fiber laser 14 works for the first time, after the optical fiber laser 14 starts to work for 10s, when a left real-time temperature value on the structural sample 2 does not accord with a first temperature load target value, the power of the optical fiber laser 14 is adjusted again, the position of the structural sample 2 is adjusted according to different test requirements and different models of the optical fiber laser 14, the structural sample 2 is made to be in an irradiation range of the optical fiber laser 14, and the position of the optical lens 12 is adjusted again, so that laser of the optical fiber laser 14 is focused on the structural sample 2.
Step four, applying a cooling load: and delivering cold air to the structural sample 2 through a cold air pipe 18 until the right real-time temperature value meets the second temperature load target value.
During actual test, the air compressor conveys cold air to the right side surface of the structural sample 2 through the cold air pipe 18, the flow rate of the conveyed cold air is 3L/min, the accelerated cooling of the structural sample 2 is facilitated, the right real-time temperature value on the structural sample 2 is changed rapidly, and the real working environment of a high-temperature-resistant structure on an aerospace vehicle is met better.
Step five, applying gradient temperature field load: opening the optical fiber laser 14, and simultaneously delivering cold air to the structural sample 2 through a cold air pipe 18 to enable the temperature on the structural sample 2 to present gradient distribution; when the left real-time temperature value does not meet the first temperature load target value, the power of the optical fiber laser 14 is adjusted to change the heat flux density received by the structural sample 2 until the left real-time temperature value meets the first temperature load target value.
In this embodiment, in the third step and the fifth step, the specific process of adjusting the power of the fiber laser 14 by the controller is as follows: according to the formula
To obtain a control rate
And outputting the control signal to a power regulator, wherein the power regulator controls the power supply according to the control rate
The power of the fibre laser 14 is adjusted.
Wherein the content of the first and second substances,
is a proportional term, an
，
Is a weight parameter of the proportional term,
as a function of the residual error of the left real-time temperature value and the first temperature load target value,
is the operating time of the fiber laser 14.
Wherein the content of the first and second substances,
is a differential term, and
，
is the weight parameter of the derivative term.
Wherein, the first and the second end of the pipe are connected with each other,
in order to attenuate the integral term,
and is made of
Get the
Or
，
In order to attenuate the weight parameter of the integral term,
second to operate said fiber laser 14
At the moment of time, the time of day,
from time 0 to time 0
The variation between the time of day is such that,
in order to be able to obtain the attenuation coefficient,
is as follows
A residual error value of the left real-time temperature value and the first temperature load target value at the time,
in order to find the minimum function of the function,
in order to be the maximum amplitude of the attenuation,
in order to find the maximum function,
is the minimum amplitude of the attenuation.
Wherein the content of the first and second substances,
is an integral of the feed forward term, an
，
To integrate the weight parameters of the feed forward term,
for the first temperature load target value
The gradient of the curve at time.
Wherein the content of the first and second substances,
is a dynamic compensation term, and
，
is a weight parameter for the dynamic compensation term,
for the first temperature load target value
The gradient of the curve at the time immediately preceding the time.
In actual experiments, when fiber laser 14 is operated to time 10,
is a variable from time 0 to time 10, i.e.
And is and
taking an integer;
for the gradient of the curve at the 10 th moment of the first temperature load target value,
the curve gradient of the first temperature load target value at the 9 th moment is shown.
According to the invention, the real-time temperature values of the left side and the right side of the structural sample 2 are transmitted to the controller, so that the controller can conveniently adjust the power of the fiber laser 14 according to the calculation result, thereby not only realizing long-time gradient thermal shock on the structural sample 2 and completing gradient thermal shock and thermal fatigue tests, but also realizing accurate control on the surface temperature of the structural sample 2, being more in line with the real service condition of a high-temperature-resistant structure on an aerospace vehicle, and improving the authenticity and accuracy of the test.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and all simple modifications, changes and equivalent structural changes made to the above embodiment according to the technical spirit of the present invention still fall within the protection scope of the technical solution of the present invention.
Claims (8)
1. The gradient thermal shock and thermal fatigue test method for the aerospace vehicle structure is characterized by comprising the following steps: the method for testing the gradient thermal shock and the thermal fatigue through the gradient thermal shock and thermal fatigue testing device for the aerospace vehicle structure comprises a control box (1) and a clamping mechanism which is arranged on the control box (1) in a sliding mode and used for clamping a structural sample (2), wherein a heating mechanism used for heating the structural sample (2) in an impact mode, a cooling mechanism used for cooling the structural sample (2) and a temperature measuring mechanism used for measuring the temperature of the structural sample (2) are further arranged on the control box (1), and a sliding rail used for the clamping mechanism to slide is arranged on the control box (1);
the clamping mechanism comprises a first sliding plate (5) arranged on the sliding rail and a clamp (7) arranged on the first sliding plate (5), and the structural sample (2) is clamped in the clamp (7);
the temperature raising mechanism comprises a fiber laser (14) positioned at the left end of the slide rail and an optical lens (12) positioned between the fiber laser (14) and the structural sample (2), a controller used for controlling the power of the fiber laser (14) is arranged in the control box (1), the optical lens (12) is installed on the slide rail through a second sliding plate (10), and laser emitted from the fiber laser (14) is focused on the left side surface of the structural sample (2) through the optical lens (12);
the cooling mechanism comprises a cold air pipe (18) which is positioned at the right end of the slide rail and used for conveying cold air to the right side surface of the structural sample (2);
the temperature measuring mechanism comprises a left infrared thermometer (15) and a right infrared thermometer (17) which are respectively used for collecting the temperatures of the left surface and the right surface of the structural sample (2), and the left infrared thermometer (15) and the right infrared thermometer (17) are respectively positioned at the two ends of the slide rail;
the method comprises the following steps:
step one, determining a gradient temperature load target value: according to the real working condition of the aerospace vehicle, determining gradient temperature load target values which need to be applied to a structural sample (2) at different moments in a gradient thermal shock and thermal fatigue test, wherein the gradient temperature load target values comprise a first temperature load target value and a second temperature load target value;
step two, performing gradient thermal shock and thermal fatigue tests: applying temperature loads at corresponding moments to the structural sample (2) at different moments, continuously acquiring a left real-time temperature value of the left side surface of the structural sample (2) through a left infrared thermometer (15), and continuously acquiring a right real-time temperature value of the right side surface of the structural sample (2) through a right infrared thermometer (17), so that the left real-time temperature value conforms to the first temperature load target value at the corresponding moment, and the right real-time temperature value conforms to the second temperature load target value at the corresponding moment;
the temperature load comprises a heating load, a cooling load and a gradient temperature field load, and when the heating load needs to be applied to the structural sample (2), the third step is executed; when the structural sample (2) needs to be applied with a cooling load, executing a fourth step; when gradient temperature field load needs to be applied to the structural sample (2), executing a fifth step;
step three, applying a heating load: turning on the optical fiber laser (14), adjusting the positions of the structural sample (2) and the optical lens (12) on a slide rail, and focusing laser emitted from the optical fiber laser (14) on the left side surface of the structural sample (2) through the optical lens (12);
when the left real-time temperature value does not accord with the first temperature load target value, the controller adjusts the power of the optical fiber laser (14) to change the heat flow density received by the structural sample (2) until the left real-time temperature value accords with the first temperature load target value;
step four, applying a cooling load: delivering cold air to the structural sample (2) through a cold air pipe (18) until the right real-time temperature value meets the second temperature load target value;
step five, applying gradient temperature field load: opening the optical fiber laser (14), and simultaneously delivering cold air to the structural sample (2) through a cold air pipe (18) to enable the temperature on the structural sample (2) to present a gradient distribution;
when the left real-time temperature value does not accord with the first temperature load target value, the controller adjusts the power of the optical fiber laser (14) to change the heat flow density received by the structural sample (2) until the left real-time temperature value accords with the first temperature load target value;
in the third step and the fifth step, the specific process of adjusting the power of the optical fiber laser (14) by the controller is as follows: according to the formula
Obtaining a control rate
And thereby adjusting the power of the fiber laser (14);
wherein the content of the first and second substances,
is a proportional term, an
，
Is a weight parameter of the proportional term,
as a function of the residual error of the left real-time temperature value and the first temperature load target value,
is the working time of the fiber laser (14);
wherein the content of the first and second substances,
is a differential term, and
，
a weight parameter which is a differential term;
wherein, the first and the second end of the pipe are connected with each other,
in order to attenuate the integral term,
and is and
get
Or
，
In order to attenuate the weight parameter of the integral term,
a second operating for the fiber laser (14)
At the moment of time, the time of day,
from time 0 to time 0
The variable between the time of day is,
in order to be able to obtain a damping factor,
is as follows
A residual error value between the left real-time temperature value and the first temperature load target value at the time,
in order to find the minimum function,
in order to be the maximum amplitude of the attenuation,
in order to find the maximum function,
is the minimum amplitude of the attenuation;
wherein the content of the first and second substances,
is an integral of the feed forward term, an
，
To integrate the weight parameters of the feed forward term,
for the first temperature load target value
The curve gradient at that moment;
wherein the content of the first and second substances,
is a dynamic compensation term, and
，
is a weight parameter for the dynamic compensation term,
for the first temperature load target value
The gradient of the curve at the time immediately preceding the time.
2. The aerospace vehicle structure gradient thermal shock and fatigue test method of claim 1, wherein: the fiber laser (14), the optical lens (12) and the structural sample (2) have the same height.
3. The aerospace vehicle structure gradient thermal shock and fatigue test method of claim 1, wherein: the sliding rail comprises a first rail (3) and a second rail (4) which are arranged on the control box (1), the second rail (4) is positioned at the upper part of the first rail (3), and the width of the second rail (4) is smaller than that of the first rail (3);
the first sliding plate (5) and the second sliding plate (10) are clamped on the second rail (4) and abut against the upper surface of the first rail (3).
4. The aerospace vehicle structure gradient thermal shock and fatigue test method of claim 1, wherein: and a U-shaped protective cover (20) which covers the outer side of the structural sample (2) is arranged on the first sliding plate (5).
5. The aerospace vehicle structure gradient thermal shock and fatigue test method of claim 1, wherein: a left vertical plate (13) and a right vertical plate (16) which are respectively positioned at two ends of the slide rail are arranged on the control box (1);
the fiber laser (14) and the left infrared thermometer (15) are both installed on the left vertical plate (13), and the right infrared thermometer (17) and the cold air pipe (18) are both installed on the right vertical plate (16).
6. The aerospace vehicle structure gradient thermal shock and thermal fatigue test method of claim 5, wherein: the right vertical plate (16) is further provided with a cold air extension pipe (19), one end of the cold air extension pipe (19) is communicated with the cold air pipe (18), and the other end of the cold air extension pipe (19) penetrates through the right vertical plate (16) and extends to the right side of the structural sample (2).
7. The aerospace vehicle structure gradient thermal shock and fatigue test method of claim 1, wherein: the fixture (7) is a flat plate component, a through hole (8) and a plurality of bosses (9) are uniformly distributed on the side wall of the through hole (8) and extend to the center of the through hole (8), and the bosses (9) are clamped on the outer side wall of the structural sample (2) in the circumferential direction.
8. The aerospace vehicle structure gradient thermal shock and fatigue test method of claim 1, wherein: the optical lens (12) is a convex lens.
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