CN109533366A - A kind of double freedom mooring device and its design method - Google Patents
A kind of double freedom mooring device and its design method Download PDFInfo
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- CN109533366A CN109533366A CN201811347531.2A CN201811347531A CN109533366A CN 109533366 A CN109533366 A CN 109533366A CN 201811347531 A CN201811347531 A CN 201811347531A CN 109533366 A CN109533366 A CN 109533366A
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- 238000000034 method Methods 0.000 title claims abstract description 13
- 239000000463 material Substances 0.000 claims description 11
- 238000009434 installation Methods 0.000 claims description 4
- 230000000694 effects Effects 0.000 abstract description 4
- 238000010276 construction Methods 0.000 abstract 1
- 229910000831 Steel Inorganic materials 0.000 description 7
- 239000010959 steel Substances 0.000 description 7
- 230000003068 static effect Effects 0.000 description 6
- 238000010586 diagram Methods 0.000 description 4
- 238000005452 bending Methods 0.000 description 3
- 238000006356 dehydrogenation reaction Methods 0.000 description 3
- 238000010008 shearing Methods 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 239000004593 Epoxy Substances 0.000 description 1
- 238000005299 abrasion Methods 0.000 description 1
- 230000003044 adaptive effect Effects 0.000 description 1
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- VIROINNDOPNTDI-UHFFFAOYSA-N cadmium titanium Chemical compound [Ti].[Cd] VIROINNDOPNTDI-UHFFFAOYSA-N 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 239000011248 coating agent Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000011900 installation process Methods 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 239000004973 liquid crystal related substance Substances 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000007747 plating Methods 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 125000006850 spacer group Chemical group 0.000 description 1
- 230000007306 turnover Effects 0.000 description 1
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
- B64D47/00—Equipment not otherwise provided for
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/12—Ground or aircraft-carrier-deck installations for anchoring aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Manufacturing & Machinery (AREA)
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- Mechanical Engineering (AREA)
- Connection Of Plates (AREA)
- Clamps And Clips (AREA)
Abstract
The application belongs to aircraft picketing modular construction design field, on the one hand a kind of double freedom mooring device, including locating piece, connector and tie downs are provided, wherein tie downs can be overturn relative to connector, it can be rotated together with connector relative to locating piece again, there is double freedom；On the other hand a kind of aircraft is provided, its evidence has above-mentioned mooring device, by be tethered at cable wire cooperation the aircraft is fixed when, it can be occurred accordingly to rotate within the scope of double freedom according to the actual angle for being tethered at cable wire, reduce the shear stress between its component, reinforce the fixed effect to the aircraft, and is able to extend its service life.In addition, also disclosing a kind of design method of above-mentioned mooring device, the number of iterations is few, and the design of above-mentioned mooring device can be completed in short cycle.
Description
Technical Field
The application belongs to the field of structural design of airplane mooring components, and particularly relates to a double-freedom-degree system device and a design method thereof.
Background
The ship is located on the sea, and is often in an extremely unstable shaking state under the influence of sea wind and sea waves, so that an airplane on the ship is kept stable relative to the airplane, currently, a mooring device is mostly arranged on the airplane and is connected with a fixed point on the ship through a mooring steel cable, and therefore the airplane on the ship is fixed. In the prior art, the mooring device usually adopts a fixed joint form or a mooring ring form, and has the following defects:
1) the whole mooring device is fixed, so that the mooring device is very inconvenient to disassemble and maintain;
2) the connection point can not rotate in multiple angles, which limits the connection mode and angle of the mooring steel cable, and usually has larger shearing stress, which easily causes damage to the mooring steel cable and affects the fixing effect of the airplane.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
It is an object of the present application to provide a two degree of freedom mooring device and method of designing the same that overcomes or mitigates at least one of the above-mentioned disadvantages.
The technical scheme of the application is as follows:
one aspect provides a two degree-of-freedom mooring device comprising:
the positioning piece is provided with a positioning through hole;
the connecting piece is provided with two ends, wherein one end is called a hinged end, the other end is called a positioning end, the positioning end penetrates through the positioning through hole and is provided with a limiting nut; the connecting piece can rotate around the axis of the connecting piece relative to the positioning piece;
and the mooring piece is hinged with the end face of the hinged end.
According to at least one embodiment of the present application, a positioning member includes: positioning the bushing;
and the positioning bolt is in threaded fit connection with the inner wall of the positioning bushing and is provided with a positioning through hole along the axial direction.
According to at least one embodiment of the application, the outer wall of the positioning bushing, which is close to one end of the head of the positioning bolt, is provided with a positioning bulge along the circumferential direction.
According to at least one embodiment of the present application, the positioning projection periphery has two mutually parallel faces.
According to at least one embodiment of the application, a connector comprises:
one end of the connecting shaft is a hinged end, the other end of the connecting shaft is a positioning end, and the connecting shaft can rotate relative to the positioning piece;
the outer wall of the hinged end is provided with a limiting protrusion along the circumferential direction.
According to at least one embodiment of the application, the connector further comprises:
the limiting gasket is arranged at the positioning end;
and the limiting cotter pin is arranged at the positioning end.
In accordance with at least one embodiment of the present application,
the mooring element comprises a mooring ring, and the outer ring surface of the mooring ring is hinged with the end surface of the hinged end.
According to at least one embodiment of the present application, the mooring device further comprises:
the double lug plates are fixedly arranged on the outer ring surface of the mooring ring;
the single lug plate is fixedly arranged on the end face of the hinged end and positioned between the double lug plates, and a hinged channel is formed by the upper through hole of the single lug plate and the through hole of the double lug plate;
the top end of the hinge bolt penetrates through the hinge channel and is in threaded fit connection with the hinge nut;
the hinge cotter pin is arranged at the top end of the hinge bolt;
and one of the two hinged gaskets is arranged between the hinged nut and the double lug pieces, and the other hinged gasket is arranged between the head part of the hinged bolt and the double lug pieces.
Another aspect provides an aircraft having at least one predetermined mounting location thereon, and comprising:
at least one of any of the above mentioned mooring devices, the locating bush 7 of each mooring device being threadably arranged in a predetermined mounting position;
at least one mooring cable, each mooring cable having one end for connection to a mooring ring of a mooring device and another end for connection to a predetermined fixing point on the vessel.
In another aspect, a method for designing a mooring device is provided, and in particular, any one of the above mooring devices comprises the steps of:
step one, determining the use load F of a mooring device;
step two, calculating the minimum inner ring diameter R0 of a mooring ring of the mooring device;
thirdly, based on the R0 and a preset installation position corresponding to the mooring device, performing proofing design on each part of the mooring device;
step four, carrying out loading analysis on the given component to obtain the loading condition of each component;
and step five, determining the material of each part according to the loading condition of each part, and correcting the section size of each part according to the material of each part.
The application has at least the following beneficial technical effects: on one hand, the two-degree-of-freedom mooring device comprises a positioning piece, a connecting piece and a mooring piece, wherein the mooring piece can turn over relative to the connecting piece and can rotate relative to the positioning piece together with the connecting piece, and the two-degree-of-freedom mooring device has two degrees of freedom; on the other hand, when the airplane is fixed by matching with the mooring steel cable, the mooring device can correspondingly rotate in a two-degree-of-freedom range according to the actual angle of the mooring steel cable, so that the shearing stress between the parts is reduced, the fixing effect of the airplane is enhanced, and the service life of the airplane can be prolonged. In addition, the design method of the mooring device is further disclosed, the iteration times are few, and the design of the mooring device can be completed in a short period.
Drawings
FIG. 1 is a schematic structural diagram of a two-degree-of-freedom mooring device provided in an embodiment of the present application;
FIG. 2 is a schematic illustration of a swivel arrangement of a two-degree-of-freedom mooring device provided in an embodiment of the present application;
FIG. 3 is a schematic flow chart illustrating a method for designing a two-degree-of-freedom mooring device according to an embodiment of the present disclosure;
FIG. 4 is a schematic diagram of a mechanical model of a mooring ring provided by an embodiment of the present application;
FIG. 5 is a schematic diagram of a force model of a section of a mooring ring provided in an embodiment of the present application;
FIG. 6 is a bending moment view of a cross section of a mooring ring body provided by an embodiment of the application.
Detailed Description
The present application will be described in further detail with reference to the following drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the relevant application and are not limiting of the application. It should be noted that, for convenience of description, only the portions related to the present application are shown in the drawings.
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.
It should be noted that in the description of the present application, the terms of direction or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the directions or positional relationships shown in the drawings, which are merely for convenience of description, and do not indicate or imply that the device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present application. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
Furthermore, it should be noted that, in the description of the present application, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as being 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 skilled in the art as the case may be.
The present application is described in further detail below with reference to fig. 1 to 6.
One aspect provides a two degree-of-freedom mooring device comprising:
the positioning piece is provided with a positioning through hole;
the connecting piece is provided with two ends, wherein one end is called a hinged end, the other end is called a positioning end, and the positioning end penetrates through the positioning through hole; the connecting piece can rotate relative to the positioning piece;
and a mooring member hingedly connected to the hinge end and capable of being turned in a predetermined direction with respect to the connecting member.
In some alternative embodiments, the positioning member comprises: a positioning bush 7; and the positioning bolt 3 is in threaded fit connection with the inner wall of the positioning bush 7 and is provided with a positioning through hole along the axial direction. Above-mentioned, the design can avoid producing direct wearing and tearing between positioning bolt 2 and the aircraft, increase of service life, and the dismouting between realization spacer 7 that can be convenient and positioning bolt 3, easy to overhaul and maintain.
In some alternative embodiments, the positioning bush 7 is provided with a positioning protrusion along the circumferential direction near the outer wall of the head end of the positioning bolt 3. When the positioning device is used, the positioning protrusion is abutted with the surface of an airplane, the degree of freedom of the structure moving towards the inner side of the airplane can be limited, and the damage to the airplane body caused by the swinging of the mooring device and the auxiliary structure thereof caused by uncertain factors in the installation process of the mooring device can be reduced to a certain extent.
In some alternative embodiments, the positioning projection periphery has two mutually parallel faces. By the arrangement, the positioning bush 7 can be conveniently disassembled and assembled on the airplane.
In some alternative embodiments, the connector comprises: one end of the connecting shaft 2 is a hinged end, the other end of the connecting shaft is a positioning end, and the connecting shaft 2 can rotate relative to the positioning piece; the outer wall of the hinged end is circumferentially provided with a limiting protrusion; the positioning end is provided with a limit nut 5 in a threaded fit manner. The connecting shaft 2 is provided with a limiting protrusion and a limiting nut 5, so that the connecting shaft can be prevented from moving along the axial direction.
In some optional embodiments, the connector further comprises: the limiting gasket 4 is arranged at the positioning end; and the limiting cotter pin 6 is arranged at the positioning end. The limiting gasket 4 can reduce the direct abrasion between the limiting nut 5 and the end face of the positioning through hole of the positioning piece, and the limiting split pin 6 can prevent the limiting nut 5 from loosening.
In some alternative embodiments, the mooring element comprises a mooring ring 1, the outer circumferential surface of which is hingedly connected to the end surface of the hinge end.
In some alternative embodiments, the hinge comprises: the double lug plates 13 are fixedly arranged on the outer ring surface of the mooring ring 1; the single lug plate 14 is fixedly arranged on the end face of the hinged end and is positioned between the double lug plates, and a hinged channel is formed by the upper through hole of the single lug plate and the through hole of the double lug plate 13; the top end of the hinge bolt 8 passes through the hinge channel and is in threaded fit connection with a hinge nut 10; a hinge cotter pin 11 provided at the top end of the hinge bolt 8; two hinge gaskets 9, wherein one hinge gasket is arranged between the hinge nut 10 and the double-lug piece 13, and the other hinge gasket is arranged between the head of the hinge bolt 8 and the double-lug piece 13; wherein the double lugs can be turned over around the hinge bolt 8.
Another aspect provides an aircraft having at least one predetermined mounting location thereon, and comprising:
at least one of any of the above mentioned mooring devices, the locating bush 7 of each mooring device being threadably arranged in one mooring position;
at least one mooring cable, each mooring cable having one end for connection to a mooring ring 1 of a mooring device and another end for connection to a predetermined fixing point on the vessel.
In another aspect, a method for designing a mooring device is provided, and in particular, to a method for designing any one of the mooring devices, comprising the steps of:
step one, determining the use load F of a mooring device;
specifically, when determining the use load F of a certain mooring device, the preset installation position of the mooring device on the aircraft and the use working conditions of the aircraft, such as sea conditions, the ship surface where the mooring device is located and other factors, are specifically considered, a corresponding simplified model is established, and the design margin is fully considered;
step two, calculating the minimum inner ring diameter R0 of the mooring ring 1 of the mooring device according to the industry standard;
specifically, the industry standard may be HB-7077, and the minimum inner ring diameter R0 in step two should be sufficient to account for the number of mooring cables and their associated structures required to accommodate the airplane to be moored.
Thirdly, based on the R0 and a preset installation position corresponding to the mooring device, performing proofing design on each part of the mooring device;
specifically, a three-dimensional model of the mooring device structure is constructed by using CATIA (3D design engineering software), and the assembly relation among all parts is determined.
Step four, carrying out loading analysis on the given component to obtain the loading condition of each component;
specifically, separating each component, determining the connection relationship and interaction between each component and other components, finding out acting force and support reaction force according to static balance conditions, and drawing a stress analysis graph, so as to analyze and determine the loading condition of each component, wherein the stress analysis graph can comprise a force balance graph, an internal force graph and the like;
more specifically, the first and second liquid crystal display devices are, for example,
the loaded analysis of the mooring ring 1 can be concluded as a typical symmetrical static indeterminate problem, the mechanical model is shown as figure 4, the three-degree internal force is static indeterminate, a corresponding system is selected to analyze the stress of the cross section of the mooring ring, as shown in figure 5, wherein FNB is F/2, the only unknown static indeterminate redundant force MB is bending moment, and the deformation coordination condition is the relative corner between the cross sections at the two sides of the incision partIs zero, i.e.A mooring ring bending moment diagram can be calculated, as shown in fig. 6; wherein,
FNB: static and indeterminate excess force;
MB: unknown static indeterminate redundant force;
: the relative corner between the two side sections of the cutting part;
f, using the load;
r: mooring ring radius (R > R0)
Pi: circumferential ratio
And step five, determining the material of each part according to the loading condition of each part, correcting the section size of each part according to the material of each part, determining the structural section size of each part, and providing enough strength and rigidity support for the connection of the mooring steel cable.
Specifically, the load borne by each part is multiplied by the safety factor required by the design of the part to obtain the breaking load of the part, the material of the part is selected according to the breaking load, the adaptive strength of the material is mainly considered when the material of the part is determined, and the material can be selected from various types of steel and other metal materials; multiplying the fracture limit of the selected material of the component by the cross-sectional area of the component to obtain a nominal fracture force, and if the nominal fracture force is less than the fracture load, reducing the cross-sectional size of the component, and conversely, increasing the cross-sectional size of the component until the ratio of the nominal fracture force to the fracture load falls within a predetermined safety range, wherein the predetermined safety range can be determined according to the actual requirements of the component.
In some optional embodiments, the method further comprises performing anticorrosion design on each part, specifically, plating cadmium-titanium on each part and coating a moisture-resistant environment use type anticorrosion epoxy primer, and then performing dehydrogenation treatment according to a dehydrogenation standard, wherein the dehydrogenation standard can be HB/Z318.
In some optional embodiments, the method further comprises the step of designing a part of the component to be anti-loose; specifically, for example, when the adapter sleeve (7) is screwed into the machine body, anaerobic adhesive Y-150 is coated at the designed thread; the split pin anti-loose design can be referred to HB 0-2-A.
So far, the technical solutions of the present application have been described in connection with the preferred embodiments shown in the drawings, but it is easily understood by those skilled in the art that the scope of the present application is obviously not limited to these specific embodiments. Equivalent changes or substitutions of related technical features can be made by those skilled in the art without departing from the principle of the present application, and the technical scheme after the changes or substitutions will fall into the protection scope of the present application.
Claims (10)
1. A two degree-of-freedom mooring device, comprising:
the positioning piece is provided with a positioning through hole;
a limit nut (5);
one end of the connecting piece is called as a hinged end, the other end of the connecting piece is called as a positioning end, the positioning end penetrates through the positioning through hole and is provided with the limiting nut (5); the connecting piece can rotate around the axis of the connecting piece relative to the positioning piece;
and the mooring piece is hinged with the end face of the hinged end.
2. The mooring device of claim 1, wherein the retainer comprises:
a positioning bush (7);
and the positioning bolt (3) is in threaded fit connection with the inner wall of the positioning bush (7), and is provided with the positioning through hole along the axial direction.
3. Mooring device according to claim 2, characterized in that the outer wall of the positioning bushing (7) near the end of the head of the positioning bolt (3) is provided with a positioning projection in the circumferential direction.
4. The mooring device of claim 3, wherein the locating lug perimeter has two mutually parallel faces.
5. The mooring device of claim 1, wherein the connector comprises:
one end of the connecting shaft (2) is the hinged end, and the other end of the connecting shaft is the positioning end;
the outer wall of the hinged end is provided with a limiting protrusion along the circumferential direction.
6. The mooring device of claim 5, wherein the connector further comprises:
the limiting gasket (4) is arranged at the positioning end;
and the limiting split pin (6) is arranged at the positioning end.
7. Mooring device according to claim 1, characterized in that the mooring element comprises a mooring ring (1) having an outer circumferential surface hingedly connected to the hinge end face.
8. The mooring device of claim 7, further comprising:
the double lug plates are fixedly arranged on the outer ring surface of the mooring ring (1);
the single lug plate is fixedly arranged on the end surface of the hinged end and positioned between the double lug plates, and a through hole on the single lug plate and the through hole on the double lug plate form a hinged channel;
the top end of the hinge bolt (8) penetrates through the hinge channel and is in threaded fit connection with a hinge nut (10);
a hinge cotter pin (11) provided at a top end of the hinge bolt (8);
two hinged gaskets (9), wherein one is arranged between the hinged nut (10) and the double lug plate, and the other is arranged between the head of the hinged bolt (8) and the double lug plate.
9. An aircraft having at least one predetermined mounting location thereon, comprising:
at least one mooring device according to any one of claims 1-8, the positioning bushing (7) of each mooring device being arranged in a threaded manner in one of said predetermined mounting positions;
at least one mooring cable, each of said mooring cables having one end for connection to a mooring ring (1) of one of said mooring devices and another end for connection to a predetermined fixing point on the vessel.
10. A method of designing a mooring device, in particular according to any one of claims 1-8, comprising the steps of:
step one, determining the using load F of one mooring device;
step two, calculating the minimum inner ring diameter R0 of a mooring ring (1) of the mooring device;
thirdly, based on R0 and a preset installation position corresponding to the mooring device, performing proofing design on each component of the mooring device;
step four, carrying out loading analysis on the given components to obtain the loading conditions of the components;
and fifthly, determining the material of each part according to the loading condition of each part, and correcting the section size of each part according to the material of each part.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811347531.2A CN109533366B (en) | 2018-11-13 | 2018-11-13 | Double-freedom-degree mooring device and design method thereof |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811347531.2A CN109533366B (en) | 2018-11-13 | 2018-11-13 | Double-freedom-degree mooring device and design method thereof |
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| Publication Number | Publication Date |
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| CN109533366A true CN109533366A (en) | 2019-03-29 |
| CN109533366B CN109533366B (en) | 2021-04-30 |
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| CN201811347531.2A Active CN109533366B (en) | 2018-11-13 | 2018-11-13 | Double-freedom-degree mooring device and design method thereof |
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| CN110823433A (en) * | 2019-10-18 | 2020-02-21 | 中国直升机设计研究所 | Five-freedom-degree device for rotor load measurement |
| CN110884675A (en) * | 2019-12-04 | 2020-03-17 | 中国直升机设计研究所 | Helicopter blade mooring device |
| CN112249260A (en) * | 2020-10-26 | 2021-01-22 | 广船国际有限公司 | Design method of hull structure equipment fixing seat |
| CN113848083A (en) * | 2021-12-01 | 2021-12-28 | 中国飞机强度研究所 | Freezing and thawing prevention terrace for airplane test and freezing and thawing prevention parameter optimization method |
| CN114872924A (en) * | 2022-06-15 | 2022-08-09 | 中国民用航空飞行学院 | Aircraft structure repair fixture |
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| CN110884675A (en) * | 2019-12-04 | 2020-03-17 | 中国直升机设计研究所 | Helicopter blade mooring device |
| CN112249260A (en) * | 2020-10-26 | 2021-01-22 | 广船国际有限公司 | Design method of hull structure equipment fixing seat |
| CN113848083A (en) * | 2021-12-01 | 2021-12-28 | 中国飞机强度研究所 | Freezing and thawing prevention terrace for airplane test and freezing and thawing prevention parameter optimization method |
| CN113848083B (en) * | 2021-12-01 | 2022-02-18 | 中国飞机强度研究所 | Freezing and thawing prevention terrace for airplane test and freezing and thawing prevention parameter optimization method |
| CN114872924A (en) * | 2022-06-15 | 2022-08-09 | 中国民用航空飞行学院 | Aircraft structure repair fixture |
| CN114872924B (en) * | 2022-06-15 | 2023-07-07 | 中国民用航空飞行学院 | Repair type frame for aircraft structure |
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