CN107618676B

CN107618676B - Profiling heating test device for aircraft

Info

Publication number: CN107618676B
Application number: CN201710780186.0A
Authority: CN
Inventors: 敖良波; 岳珠峰; 程连品; 耿小亮; 何新党; 刘超; 赵晨
Original assignee: Northwestern Polytechnical University
Current assignee: Northwestern Polytechnical University
Priority date: 2017-09-01
Filing date: 2017-09-01
Publication date: 2021-03-02
Anticipated expiration: 2037-09-01
Also published as: CN107618676A

Abstract

The utility model provides an aircraft profile modeling heating test device relates to aircraft technical field, and the aircraft profile modeling heating test device of this disclosure includes shell, a plurality of connecting rods, a plurality of first spherical hinge subassembly, a plurality of second spherical hinge subassembly, a plurality of fixation clamp and a plurality of heating fluorescent tube. The shell is formed by splicing a plurality of detachably connected side plates. A plurality of connecting rods are disposed within the housing, each connecting rod having a first end and a second end. The first ends of the connecting rods are arranged in one-to-one correspondence mode through the first spherical hinge assemblies, each first spherical hinge assembly can be detachably connected to any one side plate, and each connecting rod can rotate relative to the side plates and is positioned at a plurality of positions. The plurality of second spherical hinge assemblies are arranged at the second end of each connecting rod in a one-to-one correspondence manner. The plurality of fixing clamps are connected to the second spherical hinge assemblies in a one-to-one correspondence mode, and the fixing clamps can rotate relative to the connecting rod and are positioned at a plurality of positions. A plurality of heating lamp tubes, any heating lamp tube can be clamped in the fixing clamp.

Description

Profiling heating test device for aircraft

Technical Field

The utility model relates to an aircraft technical field particularly, relates to an aircraft profile modeling heating test device.

Background

In the case of aircraft such as airplanes, aerodynamic heating occurs during flight, i.e. when high-speed airflow generates strong friction with the aircraft surface, the temperature of the airflow in the boundary layer rises. This may reduce the rigidity and strength of the aircraft structure, cause phenomena such as material ablation, and cause deterioration of the working environment inside the aircraft. Therefore, during development, thermal environment tests are required to simulate the thermal environment of the aircraft during flight in order to analyze the thermal response of the aircraft in order to improve performance.

In the prior art, thermal environment tests are mainly divided into three categories, namely convection heating, conduction heating and radiation heating. Wherein, radiant heating is comparatively commonly used, and current radiant heating device generally includes that a plurality of heating module of assembling heat the aircraft, because the difference of the appearance of aircraft is great, current radiant heating device's structure usually and the shape phase-match of aircraft to the thermal environment of simulation flight in-process as lifelike as far as possible. This makes the existing radiant heating devices generally usable only for aircraft of one shape, but are difficult to adapt for aircraft of other shapes, and have low versatility. Thus, multiple types of radiant heating equipment are required to meet the heating requirements of different aircraft, increasing costs.

It is to be noted that the information disclosed in the above background section is only for enhancement of understanding of the background of the present disclosure, and thus may include information that does not constitute prior art known to those of ordinary skill in the art.

Disclosure of Invention

It is an object of the present disclosure to provide an aircraft profiling heating test apparatus, thereby overcoming, at least to some extent, one or more of the problems due to the limitations and disadvantages of the related art.

According to one aspect of the present disclosure, there is provided an aircraft profiling heating test device, comprising:

the shell is formed by splicing a plurality of detachably connected side plates;

a plurality of links disposed within the housing, each link having a first end and a second end;

the first spherical hinge assemblies are correspondingly arranged at the first ends of the connecting rods one by one, and each first spherical hinge assembly can be detachably connected to any one side plate, so that each connecting rod can rotate relative to the side plate and is positioned at a plurality of positions;

the second spherical hinge assemblies are arranged at the second ends of the connecting rods in a one-to-one correspondence manner;

the fixing clamps are connected to the second spherical hinge assemblies in a one-to-one correspondence mode, and can rotate relative to the connecting rod and are positioned at a plurality of positions;

and any heating lamp tube can be clamped in the fixing clamp.

In an exemplary embodiment of the present disclosure, the first ball hinge assembly includes:

the first ball seat can be detachably connected with the side plate;

the first spherical piece is rotatably arranged in the first ball seat and can be connected to the first end of the connecting rod;

and the first fastening screw is in threaded connection with the first ball seat and can be tightly pressed against the first ball-shaped member.

In an exemplary embodiment of the present disclosure, each of the side plates is provided with a plurality of mounting holes, and each of the first ball seats is connected to the side plate by a connection screw passing through the mounting hole.

In an exemplary embodiment of the present disclosure, the number of the mounting holes on each of the side plates is the same, and the mounting holes are distributed in the same shape array.

In an exemplary embodiment of the present disclosure, the second spherical hinge assembly includes:

the second ball seat can be connected with the fixing clamp;

the second spherical piece is rotatably arranged in the second ball seat and can be connected with the second end of the connecting rod;

and the second fastening screw is in threaded connection with the second ball seat and can be tightly pressed against the second ball-shaped part.

In an exemplary embodiment of the present disclosure, each of the links is a telescopic rod.

In an exemplary embodiment of the present disclosure, the connecting rod includes a plurality of sleeves which are sequentially inserted, and the sleeves into which the sleeves are inserted are provided with locking screws for tightly pushing the sleeves inserted therein.

In an exemplary embodiment of the present disclosure, each of the side plates is made of red copper.

In an exemplary embodiment of the present disclosure, the heating lamp tube includes a tube body and supports at two ends of the tube body, and the supports can be clamped in the fixing clip.

In an exemplary embodiment of the present disclosure, the tube is made of quartz.

The aircraft profiling heating test device can enable the connecting rod to rotate relative to the side plate and can be positioned at a plurality of positions through the first spherical hinge assembly, and enable the fixing clamp to rotate relative to the connecting rod and be positioned at a plurality of positions through the second spherical hinge assembly. So that the connecting rod and the fixing clamp have multiple degrees of freedom, and the position of the heating lamp tube clamped in the fixing clamp can be adjusted by rotating the connecting rod and/or the fixing clamp so as to be matched with the shape of the tested aircraft. Simultaneously, each first spherical hinge subassembly homoenergetic detachably connects in arbitrary curb plate to can confirm the quantity and the position of first spherical hinge subassembly as required, and install on corresponding curb plate, make the connecting rod in the shell and the quantity of heating fluorescent tube can select, in order to do benefit to the demand that satisfies different aircraft. In addition, the heating lamp tube can be clamped in the fixing clamp, so that the heating lamp tube is convenient to disassemble and assemble, and the shell is formed by splicing a plurality of detachably connected side plates and is also convenient to assemble and disassemble.

It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the disclosure.

Drawings

The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the present disclosure and together with the description, serve to explain the principles of the disclosure. It is to be understood that the drawings in the following description are merely exemplary of the disclosure, and that other drawings may be derived from those drawings by one of ordinary skill in the art without the exercise of inventive faculty.

FIG. 1 is a schematic view of the internal structure of a profiling heating test device according to an exemplary embodiment of the present disclosure.

Fig. 2 is an enlarged view of a portion a in fig. 1.

Fig. 3 is an enlarged view of a portion B in fig. 1.

FIG. 4 is a schematic view of an enclosure of a profiling heating test device according to an example embodiment of the present disclosure.

FIG. 5 is a partial view of a connecting rod of a profiling heating test apparatus according to an example embodiment of the present disclosure.

FIG. 6 is a schematic view of a first spherical hinge assembly of a profiling heating test apparatus according to an example embodiment of the present disclosure.

FIG. 7 is a schematic view of a second spherical hinge assembly of a profiling heating test apparatus according to an example embodiment of the present disclosure.

FIG. 8 is a schematic view of a retaining clip of a profiling heating test device according to an exemplary embodiment of the present disclosure.

FIG. 9 is a schematic view of a heating bulb of a profiling heating test device according to an example embodiment of the present disclosure.

In the figure: 1. a housing; 11. a side plate; 111. mounting holes; 2. a connecting rod; 21. a sleeve; 3. a first spherical hinge assembly; 31. a first ball seat; 311. a first base plate; 312. a first spherical shell; 32. a first spherical member; 33. a first fastening screw; 4. a second spherical hinge assembly; 41. a second ball seat; 411. a second base plate; 412. a second spherical shell; 42. a second spherical member; 43. a second fastening screw; 5. a fixing clip; 6. heating the lamp tube; 61. a pipe body; 62. a support; 7. locking the screw; 8. and connecting screws.

Detailed Description

Example embodiments will now be described more fully with reference to the accompanying drawings. Example embodiments may, however, be embodied in many different forms and should not be construed as limited to the embodiments set forth herein; rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the concept of example embodiments to those skilled in the art. The same reference numerals in the drawings denote the same or similar structures, and thus their detailed description will be omitted.

Although relative terms, such as "upper" and "lower," may be used in this specification to describe one element of an icon relative to another, these terms are used in this specification for convenience only, e.g., in accordance with the orientation of the examples described in the figures. It will be appreciated that if the device of the icon were turned upside down, the element described as "upper" would become the element "lower". Other relative terms. When a structure is "on" another structure, it may mean that the structure is integrally formed with the other structure, or that the structure is "directly" disposed on the other structure, or that the structure is "indirectly" disposed on the other structure via another structure.

The terms "a," "an," "the," "said," and "at least one" are used to indicate the presence of one or more elements/components/parts/etc.; the terms "comprising" and "having" are intended to be inclusive and mean that there may be additional elements/components/etc. other than the listed elements/components/etc.; the terms "first," "second," and the like are used merely as labels, and are not limiting on the number of their objects.

The disclosed example embodiment provides an aircraft profiling heating test device used for carrying out thermal environment tests on an aircraft. As shown in fig. 1 to 8, the aircraft profiling heating test device of the present exemplary embodiment may include a housing 1, a connecting rod 2, a first spherical hinge assembly 3, a second spherical hinge assembly 4, a fixing clip 5, and a heating lamp tube 6.

The shape of the shell 1 can be a cuboid, a cylinder or other shapes, the shell 1 can comprise a plurality of side plates 11, and the shell can be a closed box body formed by splicing a plurality of side plates 11, and an aircraft can be placed in the shell 1. The number and shape of the side panels 11 are not particularly limited, provided that the shell 1 can be assembled and placed in an aircraft. The adjacent two side plates 11 can be connected in a detachable mode such as clamping or bolt connection, so that the installation and the disassembly are convenient, and the aircraft can be conveniently placed in the shell 1. Meanwhile, each side plate 11 can be made of red copper so as to improve the heat dissipation effect, and of course, other metal or nonmetal materials can be used, which are not listed.

Each side plate 11 may be provided with a plurality of mounting holes 111, and the shape and size of each mounting hole 111 are the same. The number of the mounting holes 111 on each side plate 11 may be the same, and the distribution may be a rectangular array distribution, but is not limited thereto, and may also be a circular array distribution, and the like. Of course, the number and distribution of the mounting holes 111 on different side plates 11 may also be different.

For example, as shown in fig. 1 and 3, the housing 1 includes six identical side plates 11, which may be a regular hexahedral box body formed by splicing six side plates 11, and two adjacent side plates 11 are connected by bolts. A plurality of mounting holes 111 have all been seted up on each curb plate 11, and the same and all be the rectangular array distribution of the quantity of mounting hole 111 on any curb plate 11.

The number of the connecting rods 2 is multiple, namely, greater than or equal to two, for example, ten, twenty, etc., the specific number is not limited in particular, and the number of the connecting rods 2 in the housing 1 can be determined according to the size of the aircraft and the requirement of a thermal environment test. The cross-sectional shape of the connecting rod 2 may be circular, and the diameter thereof is not particularly limited thereto, and the length thereof is limited so as to be able to be placed in the housing 1. Of course, the shape of the cross section of the connecting rod 2 may also be rectangular or other shapes. The link 2 has two ends, a first end that can be used to connect with the side plate 11 and a second end that can be used to connect with the fixing clip 5. The connecting rod 2 may be a telescopic rod to facilitate length adjustment.

For example, as shown in fig. 5, the connecting rod 2 may include a plurality of sleeves 21, and the plurality of sleeves 21 may have different diameters but the same length, so that the plurality of sleeves 21 may be inserted in sequence in the axial direction, and thus the overall length of the connecting rod 2 may be adjusted by relatively moving the sleeves 21. Meanwhile, in order to keep the connecting rod 2 at a certain length and prevent the sleeve 21 from moving randomly, a locking screw 7 is arranged on the sleeve 21 inserted with another sleeve 21, and the sleeve 21 inserted in the locking screw 7 can be tightly pressed by screwing the locking screw 7 to prevent the sleeve 21 from moving randomly; when the length of the connecting rod 2 needs to be adjusted, the locking screw 7 can be screwed and loosened, and the length of the connecting rod 2 can be adjusted by pulling the sleeve 21.

Of course, the connecting rod 2 may also be a cylindrical solid rod body, or may have other structures, which are not listed here.

The number of the first ball joint assemblies 3 may also be plural, and the number thereof may be the same as the number of the connecting rods 2. The plurality of first spherical hinge components 3 can be arranged at the first end of each connecting rod 2 in a one-to-one correspondence manner, and each first spherical hinge component 3 can be connected to any side plate 11, so that the connecting rod 2 can rotate relative to the side plates 11 and can be positioned at a plurality of positions.

For example, as shown in fig. 2 and 6, the first ball hinge assembly 3 may include a first ball seat 31, a first ball member 32, and a first fastening screw 33, wherein:

the first ball holder 31 may include a first base plate 311 and a first ball housing 312. The first bottom plate 311 may have a screw hole, and the first bottom plate 311 may be attached to any one of the side plates 11 and may be aligned with any one of the mounting holes 111 on the side plate 11. The first bottom plate 311 is detachably coupled to the side plate 11 by a coupling screw 8 passing through the mounting hole 111 and being screw-coupled to the screw hole. Alternatively, a boss that matches the mounting hole 111 may be provided on the first bottom plate 311, and the first bottom plate 311 and the side plate 11 may be detachably connected by engaging the boss with the mounting hole 111. Of course, other approaches are possible and are not listed here. The first spherical shell 312 may be a hollow spherical structure, and the first spherical shell 312 may have an opening. The first spherical shell 312 may be fixed on the first base plate 311 by welding or the like, or the first spherical shell 312 and the first base plate 311 may be of an integral structure.

The first ball member 32 may have a spherical or semi-spherical structure, and may be fitted into the first spherical shell 312 of the first ball seat 31. The opening of the first spherical shell 312 may expose a partial area of the first spherical member 32; the opening may be smaller than the diameter of the first ball member 32 to prevent the first ball member 32 from escaping the opening of the first ball housing 312, thereby allowing multi-angular rotation of the first ball member 32 within the first ball housing 312. Meanwhile, the first spherical member 32 may be fixedly connected to the first end of the connecting rod 2 by welding or the like, may be connected by fastening, screwing or the like, and may be integrally formed at the first end of the connecting rod 2.

The first fastening screw 33 may be provided on the first ball seat 31, and specifically, the first fastening screw 33 may pass through a sidewall of the first ball housing 312 and be threadedly coupled with the first ball housing 312. When the connecting rod 2 needs to be rotated, the first fastening screw 33 can be loosened, and at the moment, the first spherical part 32 can rotate along with the connecting rod 2; when the position of the connecting rod 2 needs to be fixed, the first fastening screw 33 can be screwed, the first fastening screw 33 can tightly press against the first spherical member 32, the position of the first spherical member 32 is locked, and the position of the connecting rod 2 can be fixed. Thereby, the rotation and positioning of the connecting rod 2 can be realized.

Of course, the first spherical hinge assembly 3 may have other structures, which are not illustrated, as long as the connecting rod 2 can be rotated relative to the side plate 11 and can be positioned at a plurality of positions.

The number of the second spherical hinge assemblies 4 may also be the same as the number of the connecting rods 2, and the plurality of second spherical hinge assemblies 4 may be correspondingly arranged at the second end of each connecting rod 2. The structure of the second spherical hinge assembly 4 can refer to the first spherical hinge assembly 3 described above.

For example, as shown in fig. 3 and 7, the second ball hinge assembly 4 may include a second ball seat 41, a second ball member 42, and a second fastening screw 43, wherein:

the second ball seat 41 may include a second base plate 411 and a second ball housing 412, and the second ball housing 412 may be provided on the second base plate 411, and the second ball housing 412 may also have an opening. The fixing clip 5 can be fixed on the second base plate 411 by welding, clipping, etc., and the specific structure of the second ball seat 41 can refer to the first ball seat 31 described above, and will not be described in detail here.

The second ball member 42 may be a spherical or hemispherical structure and may be rotatably disposed within the second spherical shell 412. And the second spherical member 42 can be fixedly connected with the second end of the connecting rod 2 by welding, clamping or threaded connection, and can also be integrally formed at the second end of the connecting rod 2. Reference may be made in particular to said first spherical element 32. Thus, the fixing clip 5 can rotate with the second ball seat 41 at a plurality of angles with respect to the connecting rod 2.

The second fastening screw 43 and the second ball seat 41 can be installed in a manner similar to the first fastening screw 33 and the first ball seat 31, and will not be described in detail herein. When the fixing clamp 5 needs to be rotated, the second fastening screw 43 can be loosened, and at the moment, the fixing clamp 5 can rotate relative to the connecting rod 2 along with the second ball seat 41; when the position of the fixing clip 5 needs to be fixed, the second fastening screw 43 can be screwed, the second ball-shaped member 42 is pressed against by the second fastening screw 43, and the position of the second ball-shaped member 42 is locked, so that the position of the fixing clip 5 is fixed.

Of course, the second spherical hinge assembly 4 may have other structures, which are not listed here, as long as the fixing clip 5 can rotate relative to the connecting rod 2 and can be positioned at a plurality of positions.

As shown in fig. 8, the fixing clip 5 may be a U-shaped structure, the heating lamp 6 may be clamped in the U-shaped structure, and the number of the fixing clips 5 is also plural, and may be the same as that of the connecting rods 2. A plurality of fixing clips 5 may be connected to the second ball seats 41 of the respective second ball hinge assemblies 4 in a one-to-one correspondence, and as described above, any one of the fixing clips 5 can rotate and be positioned at a plurality of positions with respect to the connecting rod 2 on which it is located.

The fixing clip 5 may also adopt other structures as long as it can clamp the heating lamp tube 6, and is not listed here.

The number of the heating lamp tubes 6 may be plural, and for one heating lamp tube 6, any fixing clip 5 can clamp it. Meanwhile, in order to keep the stability of the heating lamp 6, two fixing clips 5 may be used to clamp both ends of the heating lamp 6. That is, the same heating lamp 6 may be fixed by two fixing clips 5, and the heating lamp 6 may be supported by the corresponding two links 2.

For example, as shown in fig. 3 and 9, the heating lamp tube 6 may include a tube body 61 and a holder 62, wherein:

the tube 61 may be cylindrical and may be made of quartz, i.e. the heating lamp 6 is a quartz lamp. Of course, it may be of other materials.

The quantity of the support 62 of a heating lamp tube 6 is two, and the both ends of body 61 are located to two supports 62 cover respectively, and the shape and the size of support 62 can match with fixation clamp 5 to can be with the centre gripping of two supports 62 one-to-one in two fixation clamps 5, realize the fixed to heating lamp tube 6.

The heating lamp 6 may also comprise circuitry and electronics, and reference may be made in particular to existing lamps having the same function, which will not be described in detail here. In addition, the heating lamp 6 may have other structures, which are not listed here.

The aircraft profiling heating test device of the disclosed example embodiment is characterized in that each connecting rod 2 is connected with the side plate 11 through the first spherical hinge assembly 3, and the fixing clamp 5 is connected with the connecting rod 2 through the second spherical hinge assembly 4. So that the link 2 and the fixing clip 5 can be rotated independently or simultaneously, respectively, and each has a plurality of degrees of freedom. When different aircrafts are subjected to thermal environment tests, the connecting rod 2 can be rotated to adjust the heating lamp tube 6 to a proper position, and then the position of the connecting rod 2 is locked so as to heat various aircrafts; the position of the heating lamp tube 6 can be finely adjusted by rotating the fixing clamp 5 so as to be better suitable for various aircrafts. Meanwhile, each first spherical hinge component 3 is connected to the side plate 11 in a detachable connection mode, so that the number and the positions of the first spherical hinge components 3 can be determined as required and are installed on the corresponding side plates 11, the connecting rods 2 and the heating lamp tubes 6 in the shell 1 can be changed, and the requirements of different aircrafts can be met.

Other embodiments of the disclosure will be apparent to those skilled in the art from consideration of the specification and practice of the disclosure disclosed herein. This application is intended to cover any variations, uses, or adaptations of the disclosure following, in general, the principles of the disclosure and including such departures from the present disclosure as come within known or customary practice within the art to which the disclosure pertains. It is intended that the specification and examples be considered as exemplary only, with a true scope and spirit of the disclosure being indicated by the following claims.

Claims

1. An aircraft profile modeling heating test device which characterized in that includes:

and any heating lamp tube can be clamped in the fixing clamp.

2. The aircraft profiling heating testing device of claim 1, wherein the first spherical hinge assembly comprises:

the first ball seat can be detachably connected with the side plate;

3. The aircraft profiling heating test device according to claim 2, wherein a plurality of mounting holes are formed in each side plate, and each first ball seat can be connected with the side plate through a screw passing through the mounting hole.

4. The aircraft profiling heating test device according to claim 3, wherein the number of the mounting holes on each side plate is the same and the mounting holes are distributed in the same shape array.

5. The aircraft profiling heating testing device of claim 1, wherein the second spherical hinge assembly comprises:

the second ball seat can be connected with the fixing clamp;

6. The aircraft profiling heating testing device of claim 1, wherein each connecting rod is a telescoping rod.

7. The aircraft profiling heating test device according to claim 6, wherein the connecting rod comprises a plurality of sleeves which are sequentially inserted, and the sleeves in which the sleeves are inserted are provided with locking screws for tightly pushing the sleeves inserted in the locking screws.

8. The aircraft profiling heating test device according to claim 1, wherein each side plate is made of red copper.

9. The aircraft profiling heating test device according to claim 1, wherein the heating lamp tube comprises a tube body and supports at two ends of the tube body, and the supports can be clamped in the fixing clamp.

10. The aircraft profiling heating test device according to claim 9, wherein the tube body is made of quartz.