CN113697117B - Mounting structure of aircraft intake duct - Google Patents
Mounting structure of aircraft intake duct Download PDFInfo
- Publication number
- CN113697117B CN113697117B CN202111095149.9A CN202111095149A CN113697117B CN 113697117 B CN113697117 B CN 113697117B CN 202111095149 A CN202111095149 A CN 202111095149A CN 113697117 B CN113697117 B CN 113697117B
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- air inlet
- fuselage
- heat
- flange
- intake duct
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- 238000002955 isolation Methods 0.000 claims description 17
- 238000009413 insulation Methods 0.000 claims description 15
- 238000005452 bending Methods 0.000 claims description 4
- 230000000149 penetrating effect Effects 0.000 claims description 4
- 230000037431 insertion Effects 0.000 claims 1
- 238000003780 insertion Methods 0.000 claims 1
- 238000009434 installation Methods 0.000 abstract description 20
- 230000008878 coupling Effects 0.000 abstract description 2
- 238000010168 coupling process Methods 0.000 abstract description 2
- 238000005859 coupling reaction Methods 0.000 abstract description 2
- 238000000034 method Methods 0.000 description 6
- 230000009471 action Effects 0.000 description 3
- 238000002485 combustion reaction Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 238000007789 sealing Methods 0.000 description 3
- 230000002265 prevention Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
- B64D2033/0266—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants
- B64D2033/0273—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants for jet engines
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Aviation & Aerospace Engineering (AREA)
- Professional, Industrial, Or Sporting Protective Garments (AREA)
Abstract
The invention relates to a mounting structure for an aircraft air inlet, comprising: a body including a body front portion, a body, and a body rear portion; the intake duct, it is located the fuselage front portion with one side of fuselage body, the rear portion of intake duct with the fuselage rear portion is fixed, the side of intake duct is equipped with a plurality of regulation holes, passes through vertical mounting the regulation hole will the side with this body coupling of fuselage, the interior contour size of regulation hole is greater than the size of the cross section of vertical mounting, consequently, the intake duct leaves the space with the fuselage junction and supplies intake duct heat altered shape to remove, satisfies the heat altered shape matching installation of intake duct and fuselage.
Description
Technical Field
The invention relates to the field of aircraft air inlets, in particular to an installation structure of an aircraft air inlet.
Background
The ramjet is the core part of an aircraft and mainly comprises an air inlet channel, an isolation section, a combustion chamber and a tail nozzle. The high-speed head-on airflow is decelerated and pressurized through the air inlet channel, directly enters the combustion chamber to be mixed and combusted with fuel, and the generated high-temperature fuel gas is expanded and accelerated through the tail nozzle and then is discharged, so that thrust is generated. The air inlet channel, one of the key components of the ramjet engine, determines the energy conversion efficiency of the incoming flow and the flow field quality of the incoming flow of the combustion chamber.
In the related art, the air inlet duct and the fuselage of the current novel aircraft are usually designed in an integrated manner, and when the aircraft flies at a high speed, the air inlet duct exposed to the atmosphere is subjected to severe aerodynamic thermal load and aerodynamic load. The temperature of the air inlet channel rises sharply under high-temperature heating, the air inlet channel is easy to thermally deform at high temperature, and the thermal deformation matching installation of the air inlet channel and an aircraft fuselage is a great difficulty in air inlet channel installation. How to realize the reliable installation of the air inlet and the fuselage and meet the requirement of thermal deformation is a key technology in the engineering application of the air inlet of the aircraft.
Disclosure of Invention
The embodiment of the invention provides an installation structure of an air inlet of an aircraft, which aims to solve the problem that the air inlet and an aircraft fuselage in the related technology are difficult to install in a thermal deformation matching manner.
In a first aspect, there is provided a mounting structure for an aircraft air inlet, comprising: a fuselage including a fuselage front, a fuselage body, and a fuselage rear; the intake duct, it is located the fuselage front portion with one side of fuselage body, the rear portion of intake duct with the fuselage rear portion is fixed, the side of intake duct is equipped with a plurality of regulation holes, passes through vertical mounting the regulation hole will the side with this body coupling of fuselage, the interior overall dimension of regulation hole is greater than the size of the cross section of vertical mounting.
In some embodiments, the inside at fuselage rear portion is equipped with the isolation section, the isolation section through first mounting with the back installing frame at fuselage rear portion is fixed, the rear portion of intake duct has the rear portion flange, the rear portion flange is fixed with the isolation section through second mounting.
In some embodiments, one side of the rear mounting frame, which is close to the air inlet, is provided with a rear heat-proof plate, and the rear heat-proof plate comprises a rear heat-proof plate body and a bending portion, the bending portion is located on one side of the rear heat-proof plate body, which is close to the rear flange, and the bending portion is bent from one side, which is close to the isolation section, of the joint of the rear heat-proof plate body.
In some embodiments, the body has a front mounting frame, the front mounting frame has a U-shaped opening structure, and a guide shaft is transversely arranged in the front mounting frame in a penetrating manner; the front portion of intake duct has the anterior flange, the anterior flange is equipped with the guiding hole, the anterior flange inserts in the preceding installing frame, just the guiding axle passes the guiding hole is followed the length direction of guiding axle, preceding installing frame open-ended size is greater than the thickness of anterior flange.
In some embodiments, a front heat shield is disposed inside the front mounting frame, an outer contour of the front heat shield is matched with an inner contour of the front mounting frame in size, two sides of the front heat shield both protrude outward from the front mounting frame and are respectively bent in a direction away from each other to wrap the two sides of the front mounting frame, and the front flange and the guide shaft are both located inside the front heat shield.
In some embodiments, a first heat insulation preventing layer is arranged at the contact position of the air inlet and the front part of the fuselage.
In some embodiments, a front skin is arranged on one side of the front flange close to the front part of the fuselage, and the front skin is respectively attached to the front heat-proof plate and the first heat-proof insulation layer.
In some embodiments, the first thermal insulation prevention layer is provided with a groove, the front skin is inserted into the groove, the bottom surface of the groove is attached to the front skin, and a space is reserved between the side wall of the groove and the front skin for thermal deformation movement of the front skin.
In some embodiments, a second thermal insulation preventing layer is arranged between the machine body and the air inlet channel, and the vertical fixing piece penetrates through the adjusting hole to connect the side edge, the second thermal insulation preventing layer and the machine body.
In some embodiments, the size of the adjusting hole along the length direction of the air inlet channel is larger than the size of the adjusting hole along the width direction of the air inlet channel.
The technical scheme provided by the invention has the beneficial effects that:
the embodiment of the invention provides an installation structure of an air inlet channel of an aircraft, wherein a machine body comprises a machine body front part, a machine body and a machine body rear part, the rear part of the air inlet channel is fixed with the machine body rear part, a plurality of adjusting holes are formed in the side edge of the air inlet channel, a vertical fixing part penetrates through the adjusting holes to connect the side edge with the machine body, the inner contour size of each adjusting hole is larger than the cross section size of the vertical fixing part, a space is reserved in each adjusting hole for the air inlet channel to move transversely or laterally, and when the air inlet channel is heated, the air inlet channel can move in transverse and lateral thermal deformation relative to the machine body, so that a space is reserved at the connection position of the air inlet channel and the machine body for the thermal deformation movement of the air inlet channel, and the thermal deformation matching installation of the air inlet channel and the machine body is met.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed to be used in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
FIG. 1 is a schematic view of an air scoop mounted to an aircraft of a mounting structure for an air scoop of an aircraft according to an embodiment of the present invention;
FIG. 2 is a schematic structural view of an air intake duct of an aircraft air intake duct mounting arrangement according to an embodiment of the present invention;
FIG. 3 isbase:Sub>A cross-sectional view A-A of FIG. 1;
FIG. 4 is a cross-sectional view of B-B of FIG. 3;
FIG. 5 is an enlarged view at C of FIG. 3;
FIG. 6 is an enlarged view at D of FIG. 4;
fig. 7 is an enlarged view of fig. 4 at E.
In the figure:
1. a body; 101. a front part of the fuselage; 102. a body; 103. a rear part of the body; 104. a front mounting frame; 105. a rear mounting frame; 2. an air inlet channel; 21. a front flange; 22. a guide hole; 23. a side edge; 24. an adjustment hole; 25. a front skin; 26. a rear flange; 27. mounting holes; 3. an isolation section; 31. mounting a plate; 4. a vertical fixing member; 5. a second heat-proof and insulating layer; 6. a front heat shield; 7. a guide shaft; 8. a first thermal insulation prevention layer; 9. a groove; 10. a first fixing member; 11. a second fixing member; 12. a rear heat shield; 121. a rear heat shield body; 122. a curved portion.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, are within the scope of the present invention.
The embodiment of the invention provides an installation structure of an air inlet channel of an aircraft, which can solve the problem that the air inlet channel and an aircraft fuselage are difficult to install in a thermal deformation matching manner in the related technology.
Referring to fig. 1, 2 and 5, an installation structure of an aircraft air inlet provided by an embodiment of the invention may include: the airplane body 1, the airplane body 1 can be composed of three parts, namely an airplane body front part 101, an airplane body 102 and an airplane body rear part 103; the air inlet 2 can be located on one side of the front part 101 and one side of the main body 102 of the fuselage, in this embodiment, the air inlet 2 is installed below the front part 101 and the main body 102 of the fuselage, in other embodiments, the air inlet 2 can be installed on other positions of the front part 101 and the main body 102 of the fuselage, the rear part of the air inlet 2 can be fixed with the rear part 103 of the fuselage, the side 23 of the air inlet 2 can be provided with a plurality of adjusting holes 24, in this embodiment, the air inlet 2 has two left and right sides 23, the two left and right sides 23 are respectively provided with two adjusting holes 24, in other embodiments, the two left and right sides 23 can be respectively provided with other numbers of adjusting holes 24, the side 23 can be connected with the main body 102 of the fuselage through the adjusting holes 24 by passing through the vertical fixing members 4, in the above connection manner, the side 23 and the main body 102 of the fuselage are fixed in a vertical direction, the inner contour size of the adjusting holes 24 is larger than the cross-section size of the vertical fixing members 4, namely, gaps are left between the adjusting holes 24 and the vertical fixing members 4, when the air inlet 2 is deformed by heat, the air inlet 2 can be moved in a direction in which the direction, so that the air inlet 2 is matched with the thermal deformation of the main body 1 of the air inlet 2, and the installation of the air inlet 2, and the installation of the air inlet 2 can be matched with the installation of the air inlet 2, and the main body 1, and the installation.
Referring to fig. 1 and 6, in some embodiments, an isolation section 3 may be disposed inside a rear portion 103 of a fuselage, an inner cavity of the isolation section 3 may be in communication with an intake cavity of an intake duct 2, the isolation section 3 may be fixed to a rear mounting frame 105 of the rear portion 103 of the fuselage by a first fixing member 10, in this embodiment, a mounting plate 31 may protrude from an outer wall of the isolation section 3, and the mounting plate 31 may be in cross contact with the rear mounting frame 105, and the mounting plate 31 may be fixed to the rear mounting frame 105 by the first fixing member 10, in other embodiments, the isolation section 3 may be fixed to the rear mounting frame 105 by another structure, a rear flange 26 may be disposed at a rear portion of the intake duct 2, and a plurality of mounting holes 27 may be disposed on the rear flange 26, in this embodiment, the rear flange 26 may be provided with four mounting holes 27 by the second fixing member 11 penetrating through the mounting holes 27, and the rear flange 26 may be fixed to the isolation section 3 by the second fixing member 11 penetrating through the mounting holes 27, in this embodiment, the rear flange 26 may be fixed to the isolation section 3, and may be fixed to the rear portion of the intake duct 2 by such a fixing means, and may prevent heat from being indirectly transferred to the intake duct 2, and the intake duct 2.
Referring to fig. 1 and 6, in some embodiments, a rear heat shield 12 may be disposed on a side of the rear mounting frame 105 close to the air inlet 2, the rear heat shield 12 may insulate transmission of heat, the rear heat shield 12 may include a rear heat shield body 121 and a bent portion 122, the bent portion 122 may be disposed on a side of the rear heat shield body 121 close to the rear flange 26, and the bent portion 122 may be bent from a connection with the rear heat shield body 121 toward a direction close to the mounting plate 31 of the isolating section 3, while the bent portion 122 is bent to extend to be in contact with the mounting plate 31 of the isolating section 3, and the bent portion 122 may separate the rear flange 26 from the rear mounting frame 105, which may increase heat sealing performance of the air inlet 2, and further insulate heat of the air inlet 2 from being transferred to the rear portion 103 of the fuselage.
Referring to fig. 2 and 7, in some embodiments, the body 102 may have a front mounting frame 104, the front mounting frame 104 may have a U-shaped opening structure, and at least one guide shaft 7 may transversely penetrate through the inside of the front mounting frame 104, in this embodiment, the guide shaft 7 is a long rod; the front part of the air inlet channel 2 can be provided with a front flange 21, the front flange 21 can be provided with at least one guide hole 22, the number of the guide holes 22 is the same as that of the guide shafts 7, the positions of the guide holes 22 are in one-to-one correspondence with the positions of the guide shafts 7, the front flange 21 can be inserted into the front mounting frame 104, each guide shaft 7 can penetrate through one guide hole 22, in the embodiment, the inside of the front mounting frame 104 is transversely provided with three guide shafts 7, the front flange 21 is provided with three guide holes 22 in one-to-one correspondence with the positions of the three guide shafts 7, when the front flange 21 is inserted into the front mounting frame 104, each guide shaft 7 penetrates through one corresponding guide hole 22, in other embodiments, other numbers of the guide shafts 7 and the guide holes 22 can be arranged, the size of the opening of the front mounting frame 104 can be larger than the thickness of the front flange 21 along the length direction of the guide shafts 7, the thickness of the front flange 21 refers to the size of the front flange 21 along the length direction of the guide shafts 7, in the structure, a gap is left between the front mounting frame 104 and the front flange 21 can be used for the thermal deformation of the front flange 21, and the thermal deformation of the air inlet channel 2 can be further matched with the thermal deformation of the guide shafts 7, therefore, the thermal deformation of the air inlet channel 2 can be further satisfied.
Referring to fig. 7, in some embodiments, a front heat shield 6 may be disposed inside the front mounting frame 104, the size of the outer contour of the front heat shield 6 may be adapted to the size of the inner contour of the front mounting frame 104, that is, the front heat shield 6 is also in a U-shaped open structure, the front heat shield 6 is embedded in the front mounting frame 104, both sides of the front heat shield 6 protrude outward from the front mounting frame 104, and both sides of the front heat shield 6 are bent respectively in a direction away from each other to wrap both sides of the front mounting frame 104, the front mounting frame 104 is further bent in a direction close to the body 102 after being wrapped on both sides of the front mounting frame 104, so that the front heat shield 6 is attached to the front portion 101 of the body, the front flange 21 and the guide shaft 7 are both located in the front heat shield 6, the guide shaft 7 is inserted into the front heat shield 6, the front flange 21 and the front mounting frame 104, the front heat shield 6 may separate the front mounting frame 104 from the front flange 21, thereby increasing the tightness of the installation of the air intake duct 2, and further increasing the tightness of the air intake duct 2.
Referring to fig. 1 and 7, in some embodiments, a first thermal insulation preventing layer 8 may be disposed at a contact portion of the air intake duct 2 and the front portion 101 of the fuselage, and the first thermal insulation preventing layer 8 may block heat transfer, may prevent heat transfer from the air intake duct 2 to the front portion 101 of the fuselage, and may further increase the thermal airtightness of the installation of the air intake duct 2.
Referring to fig. 2 and 7, in some embodiments, a side of the front flange 21 close to the fuselage front 101 may be provided with a front skin 25, one side of the front skin 25 is fixed to the front flange 21, the other side of the front skin 25 may be closely attached to the front heat-proof plate 6 and the first heat-proof layer 8, respectively, and the front skin 25 directly functions to form a streamlined outer surface and ensure an aerodynamic shape and improve heat sealing reliability.
Referring to fig. 7, in some embodiments, the first insulating layer may be provided with a recess 9, the recess 9 may be adapted to receive the frontal skin 25, and the bottom surface of the recess 9 may be adapted to fit the frontal skin 25, and a space may be left between the side walls of the recess 9 and the frontal skin 25, the space being adapted to allow the frontal skin 25 to move by thermal deformation, in such a way as to match the thermal deformation of the frontal skin 25, in this embodiment, a space is left between the side walls of the recess 9 in the length direction of the air inlet duct 2 and the frontal skin 25, and when the frontal skin 25 is deformed by thermal deformation, the frontal skin 25 may move by thermal deformation in the length direction of the air inlet duct 2, or a space may be left between both the side walls of the recess 9 and the frontal skin 25, in other embodiments, the recess 9 may be adapted to move by thermal deformation in the width direction of the air inlet duct 2, and the frontal skin 25 may move by thermal deformation in the length direction and width direction of the air inlet duct 2, and the frontal skin 25 may be adapted to more closely fit the frontal skin 6 and the first insulating layer 8 after thermal deformation of the frontal skin 25, thereby increasing the thermal deformation and the thermal tightness of the frontal skin 2.
Referring to fig. 3 and 4, in some embodiments, a second thermal insulation preventing layer 5 may be disposed between the body 102 and the air inlet 2, the second thermal insulation preventing layer 5 may serve to prevent heat transfer, the vertical fixing member 4 may pass through the adjusting hole 24 to connect the side 23 of the air inlet 2, the second thermal insulation preventing layer 5 and the body 102, and constrain the air inlet 2 in the vertical direction, so that the air inlet 2 is fixed in the vertical direction, and the second thermal insulation preventing layer 5 may prevent heat on the air inlet 2 from being transferred to the body 102, thereby further increasing heat tightness of installation of the air inlet 2.
Referring to fig. 2 and 5, in some embodiments, the size of the adjustment hole 24 in the length direction of the inlet 2 may be greater than the size of the adjustment hole 24 in the width direction of the inlet 2, in this embodiment, the adjustment hole 24 may be a kidney-shaped hole, and the longer length in the kidney-shaped hole is arranged along the length direction of the inlet 2, the inlet 2 may move toward the length direction and the width direction of the inlet 2 by thermal deformation, and the deformation space reserved along the length direction of the inlet 2 is greater than the deformation space reserved along the width direction of the air duct, such a structure may satisfy the thermal deformation amount of the inlet 2 in the length direction and the width direction, and may also ensure the stability of the installation structure of the inlet 2, in other embodiments, the specific size of the adjustment hole 24 may be designed according to the deformation amount of the inlet 2 in the length direction of the inlet 2 at a high temperature and the deformation amount in the width direction of the inlet 2, and may also increase the heat sealing performance of the inlet 2 and make the inlet 2 installed more stable while satisfying the thermal matching installation of the inlet 2 and the fuselage 1.
The principle of the installation structure of the aircraft air inlet provided by the embodiment of the invention is as follows:
because the fuselage 1 can include fuselage front 101, fuselage body 102 and fuselage rear 103, air intake duct 2 can be installed to one side of fuselage front 101 and fuselage body 102, the rear portion of air intake duct 2 can be fixed with fuselage rear 103, can be equipped with two regulation holes 24 on two sides 23 of air intake duct 2 respectively, the shape of regulation hole 24 can be the shape of waist type hole, and the longer length in the waist type hole arranges along the length direction of side 23, can be provided with second thermal protection layer 5 between side 23 and the air intake duct 2 body, can pass regulation hole 24 through vertical mounting 4 and be connected side 23 and second thermal protection layer 5 and fuselage body 102, can restrain the removal of air intake duct 2 in the vertical direction, the interior overall dimension of regulation hole 24 can be greater than the size of the cross section of vertical mounting 4, leave the space between vertical mounting 4 and the regulation hole 24, this space can supply air intake duct 2 to thermally deform and move, therefore, when air intake duct 2 is under high temperature, air intake duct 2 can move along air intake duct 2 and fuselage 1's matching thermal deformation.
In the description of the present invention, 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 merely for convenience of describing the present invention and simplifying the description, but do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention. 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 meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
It is to be noted that, in the present invention, 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 foregoing are merely exemplary embodiments of the present invention, which enable those skilled in the art to understand or practice the present invention. 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 invention. Thus, the present invention 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 (8)
1. An aircraft air inlet duct mounting structure, comprising:
a fuselage (1) comprising a fuselage front (101), a fuselage body (102) and a fuselage rear (103);
the air inlet channel (2) is located on one side of the front portion (101) of the machine body and one side of the machine body (102), the rear portion of the air inlet channel (2) is fixed to the rear portion (103) of the machine body, a plurality of adjusting holes (24) are formed in the side edge (23) of the air inlet channel (2), the side edge (23) is connected with the machine body (102) through the vertical fixing piece (4) by penetrating the adjusting holes (24), and the inner contour size of each adjusting hole (24) is larger than the size of the cross section of the vertical fixing piece (4);
an isolation section (3) is arranged in the rear part (103) of the machine body, the isolation section (3) is fixed with a rear mounting frame (105) of the rear part (103) of the machine body through a first fixing piece (10), a rear flange (26) is arranged at the rear part of the air inlet channel (2), and the rear flange (26) is fixed with the isolation section (3) through a second fixing piece (11);
back installing frame (105) are close to one side of intake duct (2) is equipped with back heat protection board (12), just back heat protection board (12) are including back heat protection board body (121) and flexion (122), flexion (122) are located back heat protection board body (121) are close to one side of rear portion flange (26), just flexion (122) from with back heat protection board body (121) junction orientation is close to one side bending of isolation section (3).
2. The mounting structure for an aircraft air intake according to claim 1, wherein:
the machine body (102) is provided with a front mounting frame (104), the front mounting frame (104) is of a U-shaped opening structure, and a guide shaft (7) transversely penetrates through the interior of the front mounting frame (104);
the front portion of intake duct (2) has front flange (21), front flange (21) are equipped with guiding hole (22), front flange (21) insert in preceding installing frame (104), just guiding shaft (7) pass guiding hole (22), follow the length direction of guiding shaft (7), preceding installing frame (104) open-ended size is greater than the thickness of front flange (21).
3. The mounting structure for an aircraft air intake according to claim 2, wherein:
the front heat-proof plate (6) is arranged in the front mounting frame (104), the size of the outer contour of the front heat-proof plate (6) is matched with the size of the inner contour of the front mounting frame (104), two sides of the front heat-proof plate (6) extend outwards towards the front mounting frame (104) and are bent towards the directions away from each other to wrap the two sides of the front mounting frame (104), and the front flange (21) and the guide shaft (7) are both located in the front heat-proof plate (6).
4. The mounting structure for an aircraft air intake according to claim 3, wherein:
and a first heat-insulating layer (8) is arranged at the contact part of the air inlet channel (2) and the front part (101) of the machine body.
5. The mounting structure for an aircraft air intake according to claim 4, wherein:
one side of the front flange (21) close to the front part (101) of the fuselage is provided with a front skin (25), and the front skin (25) is respectively attached to the front heat-proof plate (6) and the first heat-proof layer (8).
6. The mounting structure for an aircraft air intake according to claim 5, wherein:
the first thermal insulation preventing layer (8) is provided with a groove (9), the groove (9) is used for the insertion of the front skin (25), the bottom surface of the groove (9) is attached to the front skin (25), and a space is reserved between the side wall of the groove (9) and the front skin (25) and used for the thermal deformation movement of the front skin (25).
7. The mounting structure for an aircraft air intake according to claim 1, wherein:
the air inlet duct is characterized in that a second heat insulation layer (5) is arranged between the machine body (102) and the air inlet duct (2), and the vertical fixing piece (4) penetrates through the adjusting hole (24) to connect the side edge (23), the second heat insulation layer (5) and the machine body (102).
8. The mounting structure for an aircraft air intake according to claim 1, wherein:
adjust hole (24) and follow intake duct (2) length direction's size is greater than adjust hole (24) and follow intake duct (2) width direction's size.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111095149.9A CN113697117B (en) | 2021-09-17 | 2021-09-17 | Mounting structure of aircraft intake duct |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111095149.9A CN113697117B (en) | 2021-09-17 | 2021-09-17 | Mounting structure of aircraft intake duct |
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| CN113697117A CN113697117A (en) | 2021-11-26 |
| CN113697117B true CN113697117B (en) | 2023-03-17 |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB578176A (en) * | 1944-08-07 | 1946-06-18 | Martin James | An improved intake duct for supplying air to the engines of aircraft |
| FR2998547B1 (en) * | 2012-11-23 | 2016-01-29 | Airbus Operations Sas | AIRCRAFT NACELLE COMPRISING A DEFORMABLE CONNECTION BETWEEN AN AIR INLET AND A MOTORIZATION |
| EP2995556B1 (en) * | 2014-09-12 | 2018-11-07 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | An aircraft with an air intake for an air breathing propulsion engine |
| FR3060522A1 (en) * | 2016-12-15 | 2018-06-22 | Airbus Operations (S.A.S.) | AIRCRAFT INSULATING MATTRESS INTEGRATING AT LEAST ONE AIR CONDITIONING CANALIZATION |
| US10723474B2 (en) * | 2017-05-24 | 2020-07-28 | Sikorsky Aircraft Corporation | Variable geometry engine inlet for high speed aircraft |
| CN107215473B (en) * | 2017-06-08 | 2018-08-31 | 南京航空航天大学 | A kind of and integrated nothing of aircraft is every road Subsonic inlet |
| CN112829955B (en) * | 2021-03-03 | 2022-07-26 | 上海机电工程研究所 | Aircraft air inlet duct and cabin axial installation area heat seal structure |
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2021
- 2021-09-17 CN CN202111095149.9A patent/CN113697117B/en active Active
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| Publication number | Publication date |
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| CN113697117A (en) | 2021-11-26 |
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