CN115435910A - Temperature measuring device and thickness design method for aircraft heat protection layer - Google Patents
Temperature measuring device and thickness design method for aircraft heat protection layer Download PDFInfo
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- CN115435910A CN115435910A CN202211057362.5A CN202211057362A CN115435910A CN 115435910 A CN115435910 A CN 115435910A CN 202211057362 A CN202211057362 A CN 202211057362A CN 115435910 A CN115435910 A CN 115435910A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K7/00—Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat ; Power supply therefor, e.g. using thermoelectric elements
- G01K7/02—Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat ; Power supply therefor, e.g. using thermoelectric elements using thermoelectric elements, e.g. thermocouples
- G01K7/04—Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat ; Power supply therefor, e.g. using thermoelectric elements using thermoelectric elements, e.g. thermocouples the object to be measured not forming one of the thermoelectric materials
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K1/00—Details of thermometers not specially adapted for particular types of thermometer
- G01K1/08—Protective devices, e.g. casings
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K1/00—Details of thermometers not specially adapted for particular types of thermometer
- G01K1/08—Protective devices, e.g. casings
- G01K1/12—Protective devices, e.g. casings for preventing damage due to heat overloading
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K1/00—Details of thermometers not specially adapted for particular types of thermometer
- G01K1/14—Supports; Fastening devices; Arrangements for mounting thermometers in particular locations
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Abstract
The application discloses a temperature measuring device and a thickness design method of an aircraft heat-proof layer, and relates to the technical field of aircraft testing, wherein the temperature measuring device comprises a measuring assembly, the measuring assembly penetrates through a bearing shell and the heat-proof layer, and the outer end face of the measuring assembly is flush with the outer surface of the heat-proof layer; a plurality of thermocouple wires for measuring temperature are arranged in the measuring assembly, the thermocouple wires are parallel to the outer end face of the measuring assembly, and the sizes of the thermocouple wires from the outer end face of the measuring assembly are different; the material of the measuring assembly is the same as that of the heat-proof layer. The temperature measuring device and the thickness design method are suitable for high heat flow conditions and can avoid cold spot effect.
Description
Technical Field
The application relates to the technical field of aircraft testing, in particular to a temperature measuring device of an aircraft heat-proof layer and a thickness design method.
Background
With the development of aircrafts towards hypersonic speed, long endurance time, near space and maneuvering flight direction, the problem of aerodynamic heating of the aircrafts is more and more serious. The conservative thermal protection design is that the outer surface of the aircraft is thickened as much as possible to be provided with a thermal heat-proof layer, so that the aircraft has large redundant mass and small effective load, and the overall performance of the aircraft is influenced; and the heat protection layer is thinned as much as possible due to the aggressive heat protection design, so that the damage of a heat protection structure in flight can be caused, and the flight is not benefited. Therefore, proper thermal protection design is very important, and heat flow as an important parameter of the thermal environment of the aircraft is a key influencing the thermal protection design and influences the selection of the thermal protection material, the thickness of the thermal protection layer and the like.
In the related art, the heat flow is mainly obtained through a test method, and the test method mainly comprises a ground test method and a flight test method. The ground test method generally utilizes a shock tunnel to simulate similar flight parameters, and tests heat flow in a mode of installing a heat flow meter on a model, but due to the limitation of the capability of ground equipment, the ground test cannot completely reflect the real flight condition, and the simulation of individual parameters is not in place, so that the result of the ground test is easy to distort. The data measured by the flight test method is real and effective, a heat flow sensor or a heat flow identification device is used for measuring, a commonly used heat flow sensor generally adopts copper as a sensitive element, temperature change in a short time is measured to determine heat flow, and the sensor cannot be applied to the conditions of high heat flow when the temperature exceeds the melting point of a material; more importantly, the use of high-thermal-conductivity materials such as copper can cause great difference in temperature between the sensor and the surrounding, and a low-temperature region corresponding to a high-temperature region of a nearby heat-proof layer is formed, which is called as a cold spot effect, so that heat flow distribution on the surface of the heat-proof layer is influenced, and the purpose of accurately testing the heat flow on the surface of the heat-proof layer cannot be achieved.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a temperature measuring device and a thickness design method of an aircraft heat protection layer, which are not only suitable for the situation of high heat flow, but also can avoid the cold spot effect.
In order to achieve the purposes, the technical scheme is as follows: a temperature measuring device of an aircraft heat-proof layer comprises a measuring assembly, wherein the measuring assembly penetrates through a force bearing shell and the heat-proof layer, and the outer end face of the measuring assembly is flush with the outer surface of the heat-proof layer; a plurality of thermocouple wires for measuring temperature are arranged in the measuring assembly, the thermocouple wires are parallel to the outer end face of the measuring assembly, and the sizes of the thermocouple wires from the outer end face of the measuring assembly are different; the material of the measuring assembly is the same as that of the heat-proof layer.
On the basis of the technical scheme, the measuring assembly comprises a measuring core and a protective sleeve, the protective sleeve penetrates through the bearing shell and the heat-proof layer, the protective sleeve is in interference fit with the heat-proof layer, and a certain allowance gap is reserved between the circumferential surface of the protective sleeve and the bearing shell; the measuring core is arranged in the center of the protective sleeve in an interference manner; the thermocouple wire penetrates through the measuring core.
On the basis of the technical scheme, the outermost thermocouple wires in the plurality of thermocouple wires are arranged at a set distance from the outer end face of the measurement core, and the rest thermocouple wires are arranged at equal intervals from outside to inside.
On the basis of the technical scheme, the measuring core is provided with a plurality of radial penetrating holes for accommodating the thermocouple wires, and the sensitive part of the thermocouple wires is positioned in the center of the radial penetrating holes in the length direction.
On the basis of the technical scheme, the diameter of the radial penetrating hole is larger than that of the thermocouple wire, and resin is filled in the rest gaps of the radial penetrating hole after the thermocouple wire is installed.
On the basis of the technical scheme, the temperature measuring device further comprises a compression cover plate, the compression cover plate is fixed on the inner surface of the bearing shell through a set screw, and the compression cover plate is tightly attached to the inner end face of the measuring core; a lead hole is formed in the center of the pressing cover plate; and the two ends of the measuring core are led out to the inner end surface through the line collecting grooves and penetrate out of the line leading holes.
The application also discloses a thickness design method based on the temperature measurement device, which comprises the following steps:
mounting holes are formed in the force bearing shell and the heat-proof layer; meanwhile, a plurality of thermocouple wires are arranged in the measuring assembly and are parallel to the outer end face of the measuring assembly; the heat-proof layer is designed to be thick;
carrying out a flight test on the aircraft, and measuring temperature data during flight by using a thermocouple wire;
and calculating the surface heat flow by adopting an inversion algorithm according to the temperature data, comparing and analyzing the calculated surface heat flow with a predicted value of the surface heat flow, and thickening or thinning the design thickness of the heat-proof layer according to an analysis result.
On the basis of the technical scheme, the measuring assembly comprises a measuring core and a protective sleeve, the protective sleeve penetrates through the bearing shell and the heat-proof layer, the protective sleeve is in interference fit with the heat-proof layer, and a certain allowance gap is reserved between the circumferential surface of the protective sleeve and the bearing shell; the measuring core is arranged in the center of the protective sleeve in an interference mode; the thermocouple wire penetrates through the measuring core.
On the basis of the technical scheme, the measuring core is provided with a plurality of radial penetrating holes for accommodating thermocouple wires, and the sensitive part of the thermocouple wires is positioned in the center of the radial penetrating holes in the length direction; the diameter of the radial penetrating hole is larger than that of the thermocouple wire, and the rest gaps of the radial penetrating hole after the thermocouple wire is installed are filled with resin.
On the basis of the technical scheme, the temperature measuring device further comprises a compression cover plate, the compression cover plate is fixed on the inner surface of the bearing shell through a set screw, and the compression cover plate is tightly attached to the inner end face of the measuring core; a lead hole is formed in the center of the pressing cover plate; and the two ends of the measuring core are led out to the inner end surface through the line collecting grooves and penetrate out of the line leading holes.
The beneficial effect that technical scheme that this application provided brought includes:
1. the temperature measuring device is applied to a flight test method, the outer end face of the measuring component is flush with the outer surface of the heat-proof layer, the material of the measuring component is the same as that of the heat-proof layer, the temperature measuring device can be applied to high heat flow, the situation that the material melts does not need to be worried about, the cold spot effect can be effectively avoided appearing by the same material and the smooth outer surface, stable and balanced heat flow distribution is formed on the outer surfaces of the measuring component and the heat-proof layer, the measuring structure is accurate, and the design of the heat-proof layer can be effectively completed in an auxiliary mode. The temperature measuring device of this application can acquire the temperature data of the different degree of depth departments of thermal protection layer in the flight process, distinguishes aircraft surface heat flow according to the temperature data of actual measurement for guide and revise the design of thermal protection layer.
2. According to the temperature measuring method, a measuring assembly made of the same material as a heat-proof layer is used, the measuring assembly is in a cylindrical plug shape and is tightly plugged in the heat-proof layer and a bearing shell, thermocouple wires are arranged at different positions in the depth direction, and surface heat flow is obtained by utilizing inversion calculation according to the actually measured temperature course in the flight process; the temperature measurement method avoids the problems of cold spot effect and structural heat matching of the traditional heat flow meter, can also accurately measure the temperature distribution along the wall thickness direction of the heat-proof layer, has important significance on ablation and real heat transfer under the action of thermal physical and chemical effects, can powerfully promote the refinement degree of heat protection design, designs the heat-proof layer with small thickness, promotes the weight reduction optimization of the heat-proof layer, and promotes the overall performance of an aircraft.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings required to be used in the description of the embodiments are briefly introduced below, and it is obvious that the drawings in the description below are only some embodiments of the present application, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.
Fig. 1 is a schematic cross-sectional view of an installed temperature measuring device according to an embodiment of the present disclosure;
FIG. 2 is a partially cut-away schematic view of a temperature measurement device provided in an embodiment of the present application installed in a cabin section of an aircraft;
FIG. 3 is a schematic structural diagram of a measurement core provided in an embodiment of the present application;
FIG. 4 is a cross-sectional view of FIG. 3;
FIG. 5 is a comparison graph of the measured time-temperature curve and the predicted time-temperature curve of five thermocouple wires provided in the embodiment of the present application;
reference numerals: 1. a measurement core; 2. a protective sleeve; 3. a heat shield layer; 4. a force bearing shell; 5. pressing the cover plate; 6. a thermal matching layer; 7. a set screw; 8. a thermocouple wire; 11. a radial penetration hole; 12. a line concentration groove; 51. and a lead hole.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and do not limit the invention. In addition, the technical features involved in the embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.
As shown in fig. 1, the application discloses an embodiment of a temperature measuring device of an aircraft heat protection layer, the temperature measuring device comprises a measuring assembly, the measuring assembly penetrates through a force bearing shell 4 and the heat protection layer 3, and the outer end face of the measuring assembly is flush with the outer surface of the heat protection layer 3; a plurality of thermocouple wires 8 used for measuring temperature are arranged inside the measuring component, and the thermocouple wires 8 are parallel to the outer end face of the measuring component. The thermocouple wires 8 are different in size from the outer end face of the measurement assembly. The material of the measurement component is the same as that of the heat shield layer 3.
The temperature measuring device is applied to a flight test method, the outer end face of the measuring component is flush with the outer surface of the heat-proof layer 3, the material of the measuring component is the same as that of the heat-proof layer 3, the temperature measuring device can be applied to high heat flow, the situation that the material melts does not need to be worried about, the cold spot effect can be effectively avoided appearing by the same material and the smooth outer surface, stable and balanced heat flow distribution is formed on the outer surfaces of the measuring component and the heat-proof layer 3, the measuring structure is accurate, and the design of the heat-proof layer can be effectively assisted and completed.
The temperature measuring device of this application can acquire the temperature data of 3 different degree of depth departments of thermal protection layer in the flight process, distinguishes aircraft surface heat flow according to the temperature data of actual measurement for guide and revise 3 designs of thermal protection layer.
In one embodiment, the measuring assembly comprises a measuring core 1 and a protective sleeve 2, the protective sleeve 2 penetrates through a bearing shell 4 and a heat-proof layer 3, the protective sleeve 2 is in interference fit with the heat-proof layer 3, and a certain allowance gap is reserved between the circumferential surface of the protective sleeve 2 and the bearing shell 4; the measuring core 1 is arranged in the center of the protective sleeve 2 in an interference manner; thermocouple wires 8 are arranged in the measuring core 1 in a penetrating manner.
The temperature measuring device of this application looks at the microstructure, and 2 interference fit of protective sheath are in heat protection layer 3, measure 1 interference of core and wear to locate protective sheath 2 central authorities, have eliminated the space that probably exists, are convenient for form balanced heat flow. Meanwhile, the thermal insulation layer 3 of the aircraft can generate thermal deformation under the action of pneumatic heating during long-time hypersonic flight, dislocation can occur between the thermal insulation layer 3 and the bearing shell 4, a certain allowance gap is reserved between the circumferential surface of the protective sleeve 2 and the bearing shell 4, the measurement assembly can be prevented from being damaged by dislocation and extrusion collision can be avoided between the measurement assembly and the bearing shell 4 when the measurement assembly moves along with the thermal insulation layer 3, and the safety performance is improved.
In one embodiment, the outermost thermocouple wire 8 of the plurality of thermocouple wires 8 is a set distance from the outer end face of the measurement core 1 at which the thermocouple wire 8 is both effective in measuring temperature and does not pneumatically rub to expose the thermocouple wire 8 in the event of high speed flight of the aircraft. The rest thermocouple wires 8 are arranged at equal intervals from outside to inside, and temperature measurement can be carried out at high quality.
Preferably, the number of thermocouple wires 8 is five, the set distance is 3mm, and the distances of the remaining thermocouple wires 8 from the outer end face of the measurement core 1 are 5mm, 7mm, 9mm, and 11mm, respectively.
In one embodiment, the measuring core 1 is provided with a plurality of radial through holes 11 for accommodating the thermocouple wires 8, and the sensitive part of the thermocouple wires 8 is located at the center of the radial through holes 11 in the length direction. Specifically, the thermocouple wire 8 is a K-type thermocouple wire having two wire wires partially wound to form a sensitive portion. The remaining portions of the thermocouple wires 8 are respectively passed out from both ends of the radial through holes 11.
Further, the diameter of the radial penetration hole 11 is larger than that of the thermocouple wire 8, and the remaining space of the radial penetration hole 11 after the thermocouple wire 8 is mounted is filled with resin. Specifically, the diameter of the radial penetration hole 11 is 1mm, and the diameter of the thermocouple wire 8 is 0.5mm. According to the temperature measuring device, the radial penetrating hole 11 is filled with resin, so that the thermocouple wire 8 is prevented from shaking in the radial penetrating hole 11, and the measurement stability is ensured; and the resin is the same as the component resin of the heat-proof layer 3 (a constituent material of the heat-proof layer 3), namely the resin is the same as the component resin of the protective sleeve 2, so that the measuring core 1 and the protective sleeve 2 have strong material compatibility and good connection reliability.
In one embodiment, the temperature measuring device further comprises a compression cover plate 5, the compression cover plate 5 is fixed on the inner surface of the bearing shell 4 through a set screw 7, and the compression cover plate 5 is tightly attached to the inner end face of the measuring core 1. And the compression cover plate 5 compresses the measuring assembly in the mounting holes of the bearing shell 4 and the heat-proof layer 3. The center of the pressing cover plate 5 is provided with a lead hole 51; the two ends of the measuring core 1 are provided with line concentration grooves 12 communicated to the inner end face of the measuring core 1 at the two ends of the radial penetrating holes 11, and the two ends of the measuring core 1 are led out to the inner end face through the line concentration grooves 12, penetrate out of the line leading holes 51 and are connected to data acquisition equipment after penetrating out. The radial through holes 11 are arranged in the radial direction, and the line concentration grooves 12 are arranged in the axial direction. The application compresses tightly apron 5, has further strengthened connection stability.
Specifically, the protective sheath 2 includes a large-diameter cylinder and a medium-diameter cylinder, the measurement core 1 includes a large-diameter cylinder and a small-diameter cylinder, and the large-diameter cylinder of the protective sheath 2 and the large-diameter cylinder of the measurement core 1 are the same in size. The small diameter cylinder of the measuring core 1 penetrates the large diameter cylinder, the medium diameter cylinder of the protective sheath 2. The large-diameter cylinder of the measuring core 1 is tightly attached to the large-diameter cylinder of the protective sleeve 2, and the pressing cover plate 5 is tightly attached to the large-diameter cylinder of the measuring core 1.
Preferably, a thermal matching layer 6 is arranged between the heat-proof layer 3 and the force bearing shell 4 for further heat insulation.
The application also discloses a temperature measuring method based on the temperature measuring device, which comprises the following steps:
mounting holes are arranged on the bearing shell 4 and the heat-proof layer 3 and used for mounting a temperature measuring device. Meanwhile, a plurality of thermocouple wires 8 are arranged in the measuring component, and the thermocouple wires 8 are parallel to the outer end face of the measuring component; the heat-shielding layer 3 is designed to have a thickness.
The aircraft carries out flight test, and thermocouple wire 8 measures the temperature data when flying to feed back to data acquisition device. Specifically, the thermocouple wires 8 extend inward after passing through both ends of the radial penetration holes 11 and are connected to a data acquisition device.
And calculating the surface heat flow by adopting an inversion algorithm according to the temperature data, comparing and analyzing the calculated predicted values of the surface heat flow and the surface heat flow, and thickening or thinning the heat-proof layer on the basis of the designed thickness. The data analysis device carries out calculation and analysis of an inversion algorithm according to the data obtained from the data acquisition device. Specifically, the inversion algorithm has been well-established in China.
According to the temperature measuring method, a measuring assembly made of the same material as the heat-proof layer 3 is used, the measuring assembly is in a cylindrical plug shape and is tightly plugged in the heat-proof layer 3 and the bearing shell, thermocouple wires 8 are arranged at different positions in the depth direction, and surface heat flow is obtained through inversion calculation according to the actually measured temperature course in the flight process; the temperature measurement method avoids the problems of cold spot effect and structural heat matching of the traditional heat flow meter, meanwhile, the temperature distribution along the wall thickness direction of the heat protection layer 3 can be accurately measured, the method has important significance on ablation and real heat transfer under the action of thermal physical and chemical effects, the refinement degree of the heat protection design can be powerfully promoted, the heat protection layer 3 which is not thick and thin is designed, the weight reduction optimization of the heat protection layer 3 is promoted, and the overall performance of an aircraft is improved.
In one embodiment, a comparison graph of the measured time temperature curve and the predicted time temperature curve of five thermocouple wires is shown in fig. 5, and the comparison analysis of the two curves shows that the heat-proof layer is designed with a certain margin, and the comprehensive judgment (the rule of the comprehensive judgment is not described in detail in the application) can thin the heat-proof layer by 2-3mm.
Regarding the temperature measurement method, in one embodiment, the measurement assembly comprises a measurement core 1 and a protective sleeve 2, the protective sleeve 2 penetrates through a bearing shell 4 and a heat-proof layer 3, the protective sleeve 2 is in interference fit with the heat-proof layer 3, and a certain allowance gap is reserved between the circumferential surface of the protective sleeve 2 and the bearing shell 4; the measuring core 1 is arranged in the center of the protective sleeve 2 in an interference mode; thermocouple wires 8 are arranged in the measuring core 1 in a penetrating manner.
According to the temperature measuring method, the protective sleeve 2 is in interference fit with the heat-proof layer 3, the measuring core 1 is arranged in the center of the protective sleeve 2 in an interference penetrating mode, possible gaps are eliminated, and formation of balanced heat flow is facilitated. Meanwhile, the heat-proof layer 3 of the aircraft can generate thermal deformation under the action of pneumatic heating during long-time hypersonic flight, dislocation can occur between the heat-proof layer 3 and the bearing shell 4, a certain allowance gap is reserved between the circumferential surface of the protective sleeve 2 and the bearing shell 4, a measurement assembly can be prevented from being damaged by dislocation, extrusion collision between the measurement assembly and the bearing shell 4 can be avoided when the measurement assembly moves along with the heat-proof layer 3, and safety performance is improved.
With respect to the temperature measurement method, in one embodiment, the outermost thermocouple wire 8 of the plurality of thermocouple wires 8 is a set distance from the outer end surface of the measurement core 1, at which the thermocouple wire 8 can effectively measure temperature without exposing the thermocouple wire 8 to aerodynamic friction in the event of high-speed flight of the aircraft. The rest thermocouple wires 8 are arranged at equal intervals from outside to inside, and temperature measurement can be performed with high quality.
Regarding the temperature measurement method, in one embodiment, the measurement core 1 is provided with a plurality of radial penetration holes 11 for accommodating the thermocouple wires 8, and the sensitive portion of the thermocouple wires 8 is located at the center in the length direction of the radial penetration holes 11. Specifically, the thermocouple wire 8 is a K-type thermocouple wire having two wire wires partially wound to form a sensitive portion. The rest of the thermocouple wire 8 is passed out from both ends of the radial through hole 11, respectively.
With respect to the temperature measurement method, further, the diameter of the radial penetration hole 11 is larger than that of the thermocouple wire 8, and the remaining space of the radial penetration hole 11 after the thermocouple wire 8 is mounted is filled with resin. Specifically, the diameter of the radial penetration hole 11 is 1mm, and the diameter of the thermocouple wire 8 is 0.5mm. According to the temperature measuring device, the radial penetrating hole 11 is filled with resin, so that the thermocouple wire 8 is prevented from shaking in the radial penetrating hole 11, and the measurement stability is ensured; and the resin is the same as the component resin of the heat-proof layer 3 (a constituent material of the heat-proof layer 3), namely the resin is the same as the component resin of the protective sleeve 2, so that the measuring core 1 and the protective sleeve 2 have strong material compatibility and good connection reliability.
Regarding the temperature measuring method, in one embodiment, the temperature measuring device further comprises a pressing cover plate 5, the pressing cover plate 5 is fixed on the inner surface of the bearing shell 4 through a set screw 7, and the pressing cover plate 5 is tightly attached to the inner end face of the measuring core 1. And the compression cover plate 5 compresses the measuring assembly in the mounting holes of the bearing shell 4 and the heat-proof layer 3. The center of the pressing cover plate 5 is provided with a lead hole 51; the two ends of the measuring core 1 are provided with line collecting grooves 12 communicated to the inner end surface of the measuring core 1 at the two ends of the radial penetrating hole 11, the two ends of the measuring core 1 are led out to the inner end surface through the line collecting grooves 12, penetrate out of the lead holes 51 and are connected to data acquisition equipment after penetrating out. The radial through holes 11 are arranged in the radial direction, and the line concentration grooves 12 are arranged in the axial direction. The application compresses tightly apron 5, has further strengthened connection stability.
In the description of the present application, it should be noted that the terms "upper", "lower", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, which are only for convenience in describing the present application and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and operate, and thus, should not be construed as limiting the present application. Unless expressly stated or limited otherwise, the terms "mounted," "connected," and "connected" are intended to be inclusive and mean, for example, that they may 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 meaning of the above terms in the present application can be understood by those of ordinary skill in the art as appropriate.
It is noted that, in the present application, relational terms such as "first" and "second", and the like, are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrases "comprising a," "8230," "8230," or "comprising" does not exclude the presence of additional like elements in a process, method, article, or apparatus that comprises the element.
The above description is merely exemplary of the present application and is presented to enable those skilled in the art to understand and practice the present application. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the application. Thus, the present application is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (10)
1. A temperature measuring device of an aircraft heat shield layer, characterized in that:
the temperature measuring device comprises a measuring assembly, wherein the measuring assembly penetrates through the bearing shell (4) and the heat-proof layer (3), and the outer end face of the measuring assembly is flush with the outer surface of the heat-proof layer (3); a plurality of thermocouple wires (8) for measuring temperature are arranged in the measuring assembly, the thermocouple wires (8) are parallel to the outer end face of the measuring assembly, and the distance between each thermocouple wire (8) and the outer end face of the measuring assembly is different in size; the material of the measuring component is the same as that of the heat-proof layer (3).
2. A temperature measuring device for an aircraft thermal protection layer according to claim 1, characterized in that: the measuring assembly comprises a measuring core (1) and a protective sleeve (2), the protective sleeve (2) penetrates through the bearing shell (4) and the heat-proof layer (3) and is in interference fit with the heat-proof layer (3), and a certain allowance gap is reserved between the circumferential surface of the protective sleeve (2) and the bearing shell (4); the measuring core (1) is arranged in the center of the protective sleeve (2) in a penetrating manner in an interference manner; the thermocouple wire (8) penetrates through the measuring core (1).
3. A temperature measuring device for an aircraft heat shield according to claim 2, characterized in that: the thermocouple wires (8) on the outermost side of the plurality of thermocouple wires (8) are at a set distance from the outer end face of the measuring core (1), and the rest thermocouple wires (8) are arranged at equal intervals from outside to inside.
4. A temperature measuring device for an aircraft heat shield according to claim 2, characterized in that: the measuring core (1) is provided with a plurality of radial penetrating holes (11) used for accommodating the thermocouple wires (8), and the sensitive part of the thermocouple wires (8) is located in the center of the radial penetrating holes (11) in the length direction.
5. A temperature measuring device for an aircraft heat shield according to claim 4, wherein: the diameter of the radial penetrating hole (11) is larger than that of the thermocouple wire (8), and the rest gap of the radial penetrating hole (11) after the thermocouple wire (8) is installed is filled with resin.
6. A temperature measuring device for an aircraft thermal protection layer according to claim 4, characterized in that: the temperature measuring device also comprises a pressing cover plate (5), the pressing cover plate (5) is fixed on the inner surface of the bearing shell (4) through a set screw (7), and the pressing cover plate (5) is tightly attached to the inner end surface of the measuring core (1); a lead hole (51) is formed in the center of the compression cover plate (5); the measuring core (1) is provided with line collecting grooves (12) communicated to the inner end face of the measuring core at two ends of the radial penetrating holes (11), and two ends of the measuring core (1) are led out to the inner end face through the line collecting grooves (12) and penetrate out of the lead holes (51).
7. A method for designing the thickness of a heat shield layer of an aircraft based on the temperature measuring device of claim 1, comprising the steps of:
mounting holes are formed in the bearing shell (4) and the heat-proof layer (3); meanwhile, a plurality of thermocouple wires (8) are arranged in the measuring component, and the thermocouple wires (8) are parallel to the outer end face of the measuring component; the heat-proof layer (3) is designed to be thick;
the aircraft carries out a flight test, and the thermocouple wire (8) measures temperature data during flight;
and calculating the surface heat flow by adopting an inversion algorithm according to the temperature data, comparing and analyzing the calculated predicted values of the surface heat flow and the surface heat flow, and thickening or thinning the design thickness of the heat-proof layer according to the analysis result.
8. The method for designing the thickness of an aircraft heat protection layer according to claim 7, wherein: the measuring component comprises a measuring core (1) and a protective sleeve (2), the protective sleeve (2) penetrates through the bearing shell (4) and the heat-proof layer (3), the protective sleeve (2) is in interference fit with the heat-proof layer (3), and a certain allowance gap is reserved between the circumferential surface of the protective sleeve (2) and the bearing shell (4); the measuring core (1) is arranged in the center of the protective sleeve (2) in an interference manner; the thermocouple wire (8) penetrates through the measuring core (1).
9. The method for designing the thickness of an aircraft heat protection layer according to claim 8, wherein: the measuring core (1) is provided with a plurality of radial penetrating holes (11) for accommodating thermocouple wires (8), and the sensitive part of the thermocouple wires (8) is positioned in the center of the radial penetrating holes (11) in the length direction; the diameter of the radial penetrating hole (11) is larger than that of the thermocouple wire (8), and the remaining gap of the radial penetrating hole (11) after the thermocouple wire (8) is installed is filled with resin.
10. The method for designing the thickness of an aircraft heat protection layer according to claim 9, wherein: the temperature measuring device also comprises a compression cover plate (5), the compression cover plate (5) is fixed on the inner surface of the bearing shell (4) through a set screw (7), and the compression cover plate (5) is tightly attached to the inner end surface of the measuring core (1); a lead hole (51) is formed in the center of the pressing cover plate (5); the measuring core (1) is provided with line collecting grooves (12) communicated to the inner end face of the measuring core at two ends of the radial penetrating holes (11), and two ends of the measuring core (1) are led out to the inner end face through the line collecting grooves (12) and penetrate out of the lead holes (51).
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| CN202211057362.5A CN115435910A (en) | 2022-08-31 | 2022-08-31 | Temperature measuring device and thickness design method for aircraft heat protection layer |
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