CN112484956A - Quartz lamp radiation device with adjustable heat flux density for high-speed aircraft heat intensity test - Google Patents
Quartz lamp radiation device with adjustable heat flux density for high-speed aircraft heat intensity test Download PDFInfo
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- CN112484956A CN112484956A CN202011502306.9A CN202011502306A CN112484956A CN 112484956 A CN112484956 A CN 112484956A CN 202011502306 A CN202011502306 A CN 202011502306A CN 112484956 A CN112484956 A CN 112484956A
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- 230000005855 radiation Effects 0.000 title claims abstract description 50
- 239000010453 quartz Substances 0.000 title claims abstract description 45
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N silicon dioxide Inorganic materials O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 title claims abstract description 45
- 230000004907 flux Effects 0.000 title claims abstract description 35
- 238000012360 testing method Methods 0.000 title claims abstract description 33
- 230000007246 mechanism Effects 0.000 claims abstract description 40
- 238000001514 detection method Methods 0.000 claims abstract description 21
- 238000009413 insulation Methods 0.000 claims abstract description 10
- 238000003491 array Methods 0.000 claims abstract description 5
- 239000000523 sample Substances 0.000 claims description 15
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 8
- 230000001174 ascending effect Effects 0.000 claims description 4
- 238000004088 simulation Methods 0.000 abstract description 3
- 238000002679 ablation Methods 0.000 abstract description 2
- 230000009471 action Effects 0.000 abstract description 2
- 230000002265 prevention Effects 0.000 abstract description 2
- 238000010438 heat treatment Methods 0.000 description 7
- 239000000463 material Substances 0.000 description 3
- 238000011160 research Methods 0.000 description 3
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 2
- 239000011248 coating agent Substances 0.000 description 2
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- 230000008569 process Effects 0.000 description 2
- 239000000956 alloy Substances 0.000 description 1
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- 238000010586 diagram Methods 0.000 description 1
- KZHJGOXRZJKJNY-UHFFFAOYSA-N dioxosilane;oxo(oxoalumanyloxy)alumane Chemical compound O=[Si]=O.O=[Si]=O.O=[Al]O[Al]=O.O=[Al]O[Al]=O.O=[Al]O[Al]=O KZHJGOXRZJKJNY-UHFFFAOYSA-N 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
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- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 229910052863 mullite Inorganic materials 0.000 description 1
- 229910052759 nickel Inorganic materials 0.000 description 1
- 230000035515 penetration Effects 0.000 description 1
- 238000002310 reflectometry Methods 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
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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
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/08—Aerodynamic models
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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
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
- G01M9/04—Details
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- Fluid Mechanics (AREA)
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- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Investigating Or Analyzing Materials Using Thermal Means (AREA)
Abstract
The invention provides a quartz lamp radiation device with adjustable heat flux density for a high-speed aircraft heat intensity test, which comprises a quartz lamp radiation array, a support adjusting rod, a sliding mechanism, a fixing mechanism, a heat flux detection device and a PLC (programmable logic controller) control system, wherein the quartz lamp radiation array is arranged on the support adjusting rod; the quartz lamp radiation arrays are respectively arranged at two sides of the heat flow detection device and are connected with the sliding mechanism through the support adjusting rod; the sliding mechanism is arranged on the fixing mechanism; the heat flow detection device is fixed on the test piece; the PLC control system is electrically connected with the sliding mechanism and the heat flow detection device. The invention provides an effective pneumatic thermal environment simulation device for the thermal strength tests of high-speed aircraft structures and components, such as stress, strain, vibration, fatigue, heat insulation prevention, ablation and the like, under the action of thermal environment and thermal load.
Description
Technical Field
The invention relates to the technical field of high-speed aircraft structure thermal environment tests, in particular to a quartz lamp radiation device with adjustable heat flux density for a high-speed aircraft thermal strength test.
Background
The high-speed aircraft can achieve global long-distance rapid arrival, implement effective high-altitude high-speed penetration, complete rapid and accurate striking, has extremely important military application value, and becomes a world military research hotspot.
With the continuous increase of the designed flight Mach number of the high-speed aircraft, the aerodynamic heating effect of the aircraft structure is more and more obvious, for example, when the aircraft flies at an ultra-low altitude with the Mach number of 3, the temperature of the front edge stagnation point of the wing can reach more than 500 ℃. When the aircraft mach number is close to 4, the surface temperature can reach 700 ℃. The instantaneous heat flux density of the cone part of the radome at the front end of the hypersonic aircraft flying at 6 Mach numbers can reach 1.2MW/m2The stagnation temperature will exceed 1200 deg.c. Aiming at different high-temperature service environments of different parts of the aircraft, different thermal protection materials are required to be adopted to carry out thermal protection on the aircraft structure. In addition to the severe high temperature environment, the high-speed aircraft simultaneously bears complex mechanical loads, for example, when the speed of the aircraft reaches mach 7, the maximum pressure on the surface of the aircraft may exceed 3MPa, in addition, the high temperature generated by pneumatic heating can cause the mechanical properties such as the elastic modulus, the rigidity and the like of the material to be obviously changed, meanwhile, the uneven distribution of the temperature causes a great temperature gradient to appear in the structure, and thermal stress is generated in the structure. This causes changes in the vibration characteristics of the wing structure, such as natural frequency and mode shape, which have a significant effect on the aerodynamic and control characteristics of the aircraft. Therefore, the research on the thermal strength test of the structure in the thermal environment and the mechanical environment is important for the safe and reliable design of the high-speed aircraft.
The quartz lamp radiation heater has the advantages of small thermal inertia, excellent electric control performance, large heating power, small volume, low operation cost and the like, so that the radiation type pneumatic thermal environment simulation test technology provides a very important test method for the research of the thermal strength of a high-speed aircraft. The existing quartz lamp radiation heating equipment has a single and fixed structure, and the distance between radiation arrays and a test piece cannot be adjusted at will and can be realized only by redesigning a connecting component; the realization of the non-uniform heat flux density on the surface of the test piece is difficult, and the problems are also faced; furthermore, there is no quantitative criterion for the uniformity of the thermal environment provided by the quartz lamp radiant heating test apparatus. The defects greatly limit the application of the high-speed aircraft in the process of testing the thermal strength.
Disclosure of Invention
In order to overcome the defects of the existing quartz lamp radiation heating device, the quartz lamp radiation device with the adjustable heat flux density for the high-speed aircraft heat intensity test is provided. The device provides effective pneumatic thermal environment simulation conditions for the high-speed aircraft structure and the components to perform stress, strain, vibration, fatigue, heat insulation prevention, ablation and other thermal strength tests under the action of a thermal environment and thermal load.
The invention provides a quartz lamp radiation device with adjustable heat flux density for a high-speed aircraft heat intensity test, which comprises: the system comprises a quartz lamp radiation array, a support adjusting rod, a sliding mechanism, a fixing mechanism, a heat flow detection device and a PLC control system; the quartz lamp radiation arrays are respectively arranged at two sides of the heat flow detection device and are connected with the sliding mechanism through the support adjusting rod; the sliding mechanism is arranged on the fixing mechanism; the heat flow detection device is fixed on the test piece; the PLC control system is electrically connected with the sliding mechanism and the heat flow detection device.
Preferably, the device further comprises a laser range finder, wherein the laser range finder is arranged on the sliding mechanism; and the PLC control system is electrically connected with the laser range finder.
Preferably, the quartz lamp radiating array comprises: a radiation-enhanced thermal shield and an electrode; the electrode is connected with the radiation enhancement heat insulation plate through a bracket; the electrode is provided with an electrode water inlet and an electrode water outlet respectively; the electrode is connected with the sliding mechanism through the support adjusting rod.
Preferably, the cross section of the bracket is U-shaped.
Preferably, the sliding mechanism includes: the device comprises a sliding block, a stepping motor, a screw rod and a sliding rail; one end of the sliding block is connected with the support adjusting rod, and the other end of the sliding block is connected with the sliding rail; the stepping motor drives the screw rod to realize the ascending and descending of the sliding block; the screw rod is connected with the fixing mechanism; the laser range finder is arranged on the sliding block; the stepping motor is electrically connected with the PLC control system.
Preferably, the fixing mechanism includes: the fixing seat, the fixing plate and the support; the fixed seat is arranged at one end of the screw rod and used for fixing the screw rod; the fixed seat, the stepping motor and the slide rail are all fixed on the fixed plate through bolts; the fixing plate is fixed on the support through bolts.
Preferably, the fixing plate includes: two transverse plates and a vertical plate; the two transverse plates are respectively and vertically fixed at two ends of the vertical plate; the sliding rail is fixed on the vertical plate through a bolt; the stepping motor is fixed on the transverse plate through a bolt; and the two transverse plates are fixed on the support through bolts.
Preferably, the heat flow detection device includes: the plug type flat heat flow probe and the height adjusting bolt are arranged on the plug type flat heat flow probe; the plug type flat plate heat flow probes are arranged on two sides of the test piece respectively; the two plug type flat plate heat flow probes are connected through a height adjusting bolt.
Compared with the prior art, the invention has the beneficial effects that: the heat flux density of the quartz lamp radiation array is tested through the heat flux detection device, the heat flux density is compared with a target heat flux curve, the single side or the whole height of the quartz lamp radiation array is adjusted by controlling the sliding mechanism through the PLC control system, the distance and the angle between the quartz lamp radiation array and the heat flux detection device are adjusted, and the real-time regulation and control of the heat flux density and the uniformity are realized by combining two adjusting modes of current.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
FIG. 1 is a schematic structural diagram of a quartz lamp radiation device with adjustable heat flux density according to an embodiment of the present invention;
FIG. 2 is a partial schematic view of a quartz lamp radiation device with adjustable heat flux density according to an embodiment of the present invention.
Description of reference numerals:
1: a radiation-enhanced thermal insulation board; 2: supporting the adjusting rod; 3: a double-T-shaped fixing plate; 4: a stepping motor; 5: a screw rod; 6: a slider; 7: a fixed seat; 8: a slide rail; 9: an electrode water inlet; 10: an electrode; 11: an electrode water outlet; 12: a height adjustment bolt; 13: a plug type flat plate heat flow probe; 14: a laser range finder; 15: a support; 16: and (4) a support.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the following embodiments, and it should be understood that the described embodiments are some, but not all, embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", and the like, indicate orientations and positional relationships based on those shown in the drawings, and are used only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be considered as limiting the present invention.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, features defined as "first", "second", may explicitly or implicitly include one or more of the described features. In the description of the present invention, "a plurality" means two or more unless specifically defined otherwise. Furthermore, the terms "mounted," "connected," and "connected" are to be construed broadly and may, for example, be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
As shown in fig. 1 and fig. 2, the invention provides a quartz lamp radiation device with adjustable heat flux density for high-speed aircraft heat intensity test, comprising: the device comprises a quartz lamp radiation array, a support adjusting rod 2, a sliding mechanism, a fixing mechanism, a heat flow detection device and a PLC control system. Two groups of quartz lamp radiation arrays are respectively arranged at two sides of the heat flow detection device, and four corners of each quartz lamp radiation array are respectively connected with the sliding mechanism through the supporting and adjusting rod 2. The sliding mechanism is arranged on the fixing mechanism, and the heat flow detection device is fixed on the test piece. The PLC control system is electrically connected with the sliding mechanism and the heat flow detection device.
In a more preferred embodiment, the device further comprises a laser range finder 14, wherein the laser range finder 14 is arranged on the sliding mechanism; the PLC control system is electrically connected to the laser rangefinder 14.
In a more preferred embodiment, the quartz lamp radiating array comprises: the radiation-enhanced heat insulation plate comprises a radiation-enhanced heat insulation plate 1 and an electrode 10, wherein the electrode 10 is connected with the radiation-enhanced heat insulation plate 1 through a support 15, and an electrode water inlet 9 and an electrode water outlet 11 are respectively formed in the electrode 10. The electrode 10 is connected with the sliding mechanism through the support adjusting rod 2. The radiation-enhanced heat insulation plate 1 is preferably made of mullite fiber heat insulation tile material, and if the test temperature is less than or equal to 650 ℃, the surface is preferably sprayed with a high-reflectivity coating; if the test temperature is higher than 650 ℃, the surface is preferentially sprayed with the high-emissivity coating.
In a more preferred embodiment, the bracket 15 is U-shaped in cross-section. The U-shaped support 15 is preferably made of a nickel-based high-temperature alloy material, and the radiation-enhanced heat-insulating plate 1 is connected with the U-shaped support 15 through inorganic high-temperature curing glue.
In a more preferred embodiment, the sliding mechanism comprises: slider 6, step motor 4, lead screw 5 and slide rail 8. One end of the sliding block 6 is connected with the supporting and adjusting rod 2, and the other end is connected with the sliding rail 8. The end of the supporting and adjusting rod 2 is provided with a long straight hole, and the sliding block 6 slides on the sliding rail 8 through a rail groove on the structure of the sliding block. The stepping motor 4 drives the screw rod 5 to realize the ascending and descending of the slide block 6. The screw rod 5 is connected with the fixing mechanism. The laser range finder 14 is bonded to the slider 6 for measuring the position in real time. The stepping motor 4 is electrically connected with the PLC control system. Each slide block 6 is provided with a laser range finder 14, and 8 laser range finders 14 are used for measuring the specific height positions of the upper quartz lamp radiation array and the lower quartz lamp radiation array in real time respectively. The single side or the whole automatic rising or falling of the upper quartz lamp radiation array and the lower quartz lamp radiation array is controlled by the stepping motor 4, so that the adjustment of the size and the uniformity of the flat plate heat flux density is achieved.
In a more preferred embodiment, the fixing mechanism comprises: a fixed seat 7, a fixed plate 3 and a support 16. The fixing seat 7 is arranged at one end of the screw rod 5 and used for fixing the screw rod 5. The fixing seat 7, the stepping motor 4 and the sliding rail 8 are all fixed on the fixing plate 3 through bolts, and the fixing plate 3 is fixed on the support 16 through bolts.
In a more preferred embodiment, the fixing plate 3 comprises: two transverse plates and a vertical plate; the two transverse plates are respectively and vertically fixed at two ends of the vertical plate; the slide rail 8 is fixed on the vertical plate through a bolt; the stepping motor 4 is fixed on the transverse plate through a bolt; the two transverse plates are fixed on the support 16 through bolts.
In a more preferred embodiment, the heat flow detection means comprises: a plug type flat heat flow probe 13 and a height adjusting bolt 12. The plug type flat heat flow probes 13 are two and are respectively positioned at two sides of the test piece. The plug flat heat flow probe 13 is the same size as the quartz lamp array to measure heat flow size and distribution throughout the heating area. The two plug-type flat heat flow probes 13 are connected by height adjusting bolts 12 and the distance is adjusted.
The working principle of the invention is as follows: firstly, the distance between the upper and lower groups of flat heat flow probes 13 is adjusted according to the thickness of a test piece. After the power supply is turned on, the heat flux densities measured by the upper and lower groups of flat heat flux probes 13 are displayed on a computer and compared with a target heat flux density value, the PLC control system is used for controlling the work of the stepping motor 4 to realize the unilateral or integral position ascending or descending of the quartz lamp radiation array by combining the data of the laser range finder 14, or the PLC control system is used for controlling the magnitude of the loading current, the adjusted heat flux densities are compared with the target heat flux, and the process is repeated until the heat flux densities are basically consistent with the target heat flux.
The invention utilizes the laser range finder 14 to accurately determine the height position of the quartz lamp radiation array, the precision reaches millimeter level, and the heat flow density can be cooperatively adjusted by two means of current or the distance between the quartz lamp radiation array and the flat heat flow probe 13.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present invention.
Claims (8)
1. High-speed aircraft is quartz lamp radiant device of heat flux density adjustable for heat intensity is experimental, its characterized in that includes: the device comprises a quartz lamp radiation array, a support adjusting rod (2), a sliding mechanism, a fixing mechanism, a heat flow detection device and a PLC control system; the quartz lamp radiation arrays are respectively arranged at two sides of the heat flow detection device and are connected with the sliding mechanism through the support adjusting rod (2); the sliding mechanism is arranged on the fixing mechanism; the heat flow detection device is fixed on the test piece; the PLC control system is electrically connected with the sliding mechanism and the heat flow detection device.
2. The quartz lamp irradiation device with the adjustable heat flux density for the high-speed aircraft heat intensity test according to claim 1, characterized by further comprising a laser range finder (14), wherein the laser range finder (14) is arranged on the sliding mechanism; the PLC control system is electrically connected with the laser range finder (14).
3. The quartz lamp radiation device with adjustable heat flux density for the high-speed aircraft heat intensity test according to claim 2, wherein the quartz lamp radiation array comprises: a radiation-enhanced thermal baffle (1) and an electrode (10); the electrode (10) is connected with the radiation-enhanced heat insulation plate (1) through a support (15); the electrode (10) is respectively provided with an electrode water inlet (9) and an electrode water outlet (11); the electrode (10) is connected with the sliding mechanism through the support adjusting rod (2).
4. The quartz lamp radiation device with the adjustable heat flux density for the high-speed aircraft heat intensity test according to claim 3, characterized in that the cross section of the bracket (15) is U-shaped.
5. The quartz lamp radiation device with adjustable heat flux density for the high-speed aircraft heat intensity test according to claim 3, wherein the sliding mechanism comprises: the device comprises a sliding block (6), a stepping motor (4), a screw rod (5) and a sliding rail (8); one end of the sliding block (6) is connected with the support adjusting rod (2), and the other end of the sliding block is connected with the sliding rail (8); the stepping motor (4) drives the screw rod (5) to realize the ascending and descending of the sliding block (6); the screw rod (5) is connected with the fixing mechanism; the laser range finder (14) is arranged on the sliding block (6); the stepping motor (4) is electrically connected with the PLC control system.
6. The quartz lamp radiation device with adjustable heat flux density for the high-speed aircraft heat intensity test according to claim 5, wherein the fixing mechanism comprises: a fixed seat (7), a fixed plate (3) and a support (16); the fixed seat (7) is arranged at one end of the screw rod (5) and is used for fixing the screw rod (5); the fixed seat (7), the stepping motor (4) and the slide rail (8) are fixed on the fixed plate (3) through bolts; the fixing plate (3) is fixed on the support (16) through bolts.
7. The quartz lamp irradiation device with adjustable heat flux density for high-speed aircraft heat intensity test according to claim 6, wherein the fixing plate (3) comprises: two transverse plates and a vertical plate; the two transverse plates are respectively and vertically fixed at two ends of the vertical plate; the sliding rail (8) is fixed on the vertical plate through a bolt; the stepping motor (4) is fixed on the transverse plate through a bolt; the two transverse plates are fixed on the support (16) through bolts.
8. The quartz lamp radiation device with adjustable heat flux density for the high-speed aircraft heat intensity test according to claim 1, wherein the heat flux detection device comprises: a plug type flat heat flow probe (13) and a height adjusting bolt (12); the plug type flat heat flow probes (13) are two and are respectively positioned on two sides of the test piece; the two plug type flat heat flow probes (13) are connected through height adjusting bolts (12).
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011502306.9A CN112484956A (en) | 2020-12-17 | 2020-12-17 | Quartz lamp radiation device with adjustable heat flux density for high-speed aircraft heat intensity test |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011502306.9A CN112484956A (en) | 2020-12-17 | 2020-12-17 | Quartz lamp radiation device with adjustable heat flux density for high-speed aircraft heat intensity test |
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Cited By (4)
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| CN113237785A (en) * | 2021-07-12 | 2021-08-10 | 中国飞机强度研究所 | Heat flow control test method |
| CN114308176A (en) * | 2021-12-30 | 2022-04-12 | 湖北三江航天红阳机电有限公司 | Adjustable radiant heating test device |
| CN114633901A (en) * | 2022-05-23 | 2022-06-17 | 中国飞机强度研究所 | Test of aerospace plane is with extreme high temperature thermal strength experimental system of complicated curved surface structure |
| CN114852369A (en) * | 2022-07-11 | 2022-08-05 | 中国飞机强度研究所 | Heating adjustment control method for high-temperature heat strength test of aircraft nose cone structure |
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| CN114633901B (en) * | 2022-05-23 | 2022-07-22 | 中国飞机强度研究所 | Test of aerospace plane is with extreme high temperature thermal strength experimental system of complicated curved surface structure |
| CN114852369A (en) * | 2022-07-11 | 2022-08-05 | 中国飞机强度研究所 | Heating adjustment control method for high-temperature heat strength test of aircraft nose cone structure |
| CN114852369B (en) * | 2022-07-11 | 2022-09-06 | 中国飞机强度研究所 | Heating adjustment control method for high-temperature thermal strength test of aircraft nose cone structure |
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