CN109305382A - Tie-down point and jacking bracket structure on a kind of aircraft - Google Patents
Tie-down point and jacking bracket structure on a kind of aircraft Download PDFInfo
- Publication number
- CN109305382A CN109305382A CN201811205730.XA CN201811205730A CN109305382A CN 109305382 A CN109305382 A CN 109305382A CN 201811205730 A CN201811205730 A CN 201811205730A CN 109305382 A CN109305382 A CN 109305382A
- Authority
- CN
- China
- Prior art keywords
- hole
- tie
- down point
- rod
- jacking bracket
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- 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—Anchoring
- B64F1/125—Mooring or ground handling devices for helicopters
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B66—HOISTING; LIFTING; HAULING
- B66F—HOISTING, LIFTING, HAULING OR PUSHING, NOT OTHERWISE PROVIDED FOR, e.g. DEVICES WHICH APPLY A LIFTING OR PUSHING FORCE DIRECTLY TO THE SURFACE OF A LOAD
- B66F3/00—Devices, e.g. jacks, adapted for uninterrupted lifting of loads
-
- 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
Abstract
The present invention relates to tie-down point on a kind of aircraft and jacking bracket integral structures, belong to field of airplane structure.Tie-down point and jacking bracket structure on a kind of aircraft, including connector, rod-like element；The connector is set in body, and top is connect with the primary load bearing component of housing construction, and bottom, which is provided with, holds the through-hole I that rod-like element passes through；The through-hole II opposite with through-hole I is provided on the covering of housing construction；One end of rod-like element passes through through-hole I, through-hole II and fixes with connector, the other end be provided with jacking bracket matched at the top of jack, be provided with that appearance tie-down point passes through on the body of rod of rod-like element is tethered at hole.Compared with the prior art, the invention has the following advantages: 1, arrange connector in airframe, the external tie point that only protrudes eliminates while meeting tie-down point and jacking bracket requirement and is tethered at lid, reduces the influence to Aerodynamic Configuration of Aireraft.2, the function of tie-down point and both jacking brackets is integrated, reduces the arrangement of docking point on housing construction, alleviated body mechanism weight, reduce assembly work amount.
Description
Technical field
The present invention relates to tie-down point on a kind of aircraft and jacking bracket integral structures, belong to aeroplane structure design neck
Domain.
Background technique
On aircraft tie-down point be aircraft park in long or short term and transportational process in, by aircraft and Ground Mooring connector
Or car-mounted device is connected by mooring guy, guarantees aircraft not by vibration, the inertia etc. in high wind, rainwater, wave and transportational process
It impacts and generates displacement, it is ensured that aircraft is parked and the safety of transportational process.Jacking bracket is to fix aboard, is provided very heavy
Top jacks up supporting point required when aircraft.
Tie-down point on existing aircraft is arranged in forebody, undercarriage and airplane tail group mostly, in order to not influence pneumatic
Shape, part aircraft can be disposed at the tie-down point on fuselage and be tethered at lid, and jacking bracket and tie-down point separate
Arrangement, wastes weight, increases the complexity of assembly.
Summary of the invention
Present invention aim to address problems of the prior art, provide it is a kind of it is light-weight, assembly efficiency is high, simultaneously
Tie-down point and jacking bracket structure on the aircraft that the function of both tie-down point and jacking bracket is integrated.
To achieve the goals above, the present invention adopts the following technical scheme: tie-down point and very heavy topmast on a kind of aircraft
Holder structure, including connector, rod-like element；The connector is set in body, the primary load bearing component at top and housing construction
Connection, bottom, which is provided with, holds the through-hole I that rod-like element passes through；Opposite with through-hole I lead to is provided on the covering of housing construction
Hole II；One end of rod-like element passes through through-hole I, through-hole II is fixed with connector, and the other end is provided with matched with jack top
Jacking bracket, be provided on the body of rod of rod-like element hold tie-down point pass through be tethered at hole.
Preferably, the connector is triangular framing, wherein one side is adapted to the primary load bearing member profile of housing construction；
Remaining two sides is adapted to fuselage appearance, and through-hole I is set to the angle of two sides formation.
Preferably, the angle that two sides is formed is provided with boss, boss is upwardly extended along the central axis of connector, through-hole
I along boss axial direction be arranged.
Preferably, the through-hole I is stepped throughhole, and top diameter is less than base diameter.
Preferably, the shape adaptation of the rod-like element and through-hole I, the end for being pierced by boss are provided with screw thread, pass through spiral shell
Mother fixes with connector.
Preferably, washer is equipped between nut and boss.
Preferably, it is tethered at the extending direction of the extending direction and connector and the primary load bearing component joint face of housing construction in hole
Unanimously.
Preferably, the jacking bracket is hemispherical projections.
In use, rod-like element passes to external load on the primary load bearing component of aircraft body structure by connector, boss
The stability of triangle frame frame connector is increased, stepped throughhole limits moving up and down for rod-like element.
Compared with the prior art, the invention has the following advantages:
1, connector is arranged in airframe, it is external only to protrude tie point, meeting tie-down point and jacking bracket requirement
While, it eliminates and is tethered at lid, reduce the influence to Aerodynamic Configuration of Aireraft.
2, the function of tie-down point and both jacking brackets is integrated, reduces the cloth of docking point on housing construction
It sets, alleviates body mechanism weight, reduce assembly work amount.
Detailed description of the invention
Fig. 1 is perspective view of the embodiment of the present invention；
Fig. 2 is structural schematic diagram of the embodiment of the present invention；
Fig. 3 is the A-A view of Fig. 2；
Fig. 4 is base structure schematic diagram in Fig. 2；
Fig. 5 is the A-A view of Fig. 4；
Fig. 6 is screw-rod structure schematic diagram in Fig. 2；
In figure, 1., pedestal；2, screw rod；3, nut；4, washer；5, it is tethered at hole.
Specific embodiment
It should be noted that top described in the present embodiment, bottom etc. are described according to shown in attached drawing, not structure
At limitation of the present invention.
1-6 is further described the present invention with reference to the accompanying drawing: as shown in Figure 1-3, on a kind of aircraft tie-down point and
Jacking bracket structure mainly includes screw rod 2, pedestal 1, nut 3 and washer 4.
As illustrated in figures 4-5, pedestal 1 is triangular framing, wherein one side is adapted to the primary load bearing member profile of housing construction；
Remaining two sides is adapted to fuselage appearance, and through-hole I is set to the angle of two sides formation；In order to increase the stability of pedestal 1, two
Boss is arranged in the angle that face is formed, and boss is upwardly extended along the central axis of pedestal, and through-hole I is arranged along the axial direction of boss, certainly
Reinforcing rib can also be set between the face and face of pedestal 1；In order to preferably limit moving up and down for screw rod 2, through-hole I is arranged
For stepped throughhole, and top diameter is less than base diameter.
As shown in fig. 6,2 screw rod of screw rod is steelwork, be adapted to through-hole I, to be ladder-like, at the top of (be pierced by boss
Part) setting external screw thread, what setting appearance tie-down point in bottom passed through is tethered at hole 5, and the end of bottom is jacking bracket, i.e. hemisphere
Shape protrusion；Screw rod 2 sequentially passes through the through-hole II being opened in aircraft fuselage skin, through-hole I, fixed by nut 3 and pedestal 1；
It is connected the friction of end face in order to reduce nut 3 with pedestal 1, washer 4 is laid between nut 3 and pedestal 1.
As shown in Fig. 2, the load in order to receiving is bigger, it is tethered at the extending direction and pedestal 1 and housing construction in hole 5
The extending direction of primary load bearing component joint face is consistent.
Pedestal is the exchanging structure between the primary load bearing component and screw rod of housing construction, is set in body, can be according to machine
Body contour is designed；Hole and its jacking bracket are tethered on screw rod as the only tie point of aircraft exterior.When assembly, by spiral shell
Bar is inserted into pedestal through-hole I, and the cascade groove face paste of ladder-like boss face and pedestal through-hole I on the screw rod body of rod is closed, installation
Washer and nut tighten nut, and carry out locking, finally connect pedestal with aircaft configuration.Overall structure will be outer by pedestal 1
In portion's load transmission to the primary load bearing component of aircraft body structure.
When being tethered at hole on screw rod for aircraft picketing be tethered at rope slocket and connect, screw rod end is hemispherical, it is convenient with it is very heavy
The nest cooperation of top top jacks up aircraft, the balance of aircraft when guaranteeing to jack up.
Above-described embodiment is only the preferred embodiment of the present invention, and the structure of pedestal is not limited to above-mentioned triangle frame
Frame can also be other more firm polygons.Those of ordinary skill in the art are in the base for not departing from basic structure of the present invention
Made any modification, extension are within the scope of the invention on plinth.
Claims (8)
1. tie-down point and jacking bracket structure on a kind of aircraft, it is characterised in that: including connector, rod-like element；The company
Fitting is set in body, and top is connect with the primary load bearing component of housing construction, and bottom, which is provided with, holds what rod-like element passed through
Through-hole I；The through-hole II opposite with through-hole I is provided on the covering of housing construction；One end of rod-like element passes through through-hole I, through-hole
II fixes with connector, the other end be provided with matched jacking bracket at the top of jack, be arranged on the body of rod of rod-like element
Have hold tie-down point pass through be tethered at hole.
2. tie-down point and jacking bracket structure on aircraft according to claim 1, it is characterised in that: the connector
For triangular framing, wherein one side is adapted to the primary load bearing member profile of housing construction；Remaining two sides is adapted to fuselage appearance, is led to
Hole I is set to the angle of two sides formation.
3. tie-down point and jacking bracket structure on aircraft according to claim 2, it is characterised in that: formed on two sides
Angle be provided with boss, boss is upwardly extended along the central axis of connector, through-hole I along boss axial direction be arranged.
4. tie-down point and jacking bracket structure on aircraft described in any claim in -3 according to claim 1, special
Sign is: the through-hole I is stepped throughhole, and top diameter is less than base diameter.
5. tie-down point and jacking bracket structure on aircraft according to claim 4, it is characterised in that: the rod-like element
With the shape adaptation of through-hole I, the end for being pierced by boss is provided with screw thread, is fixed by nut and connector.
6. tie-down point and jacking bracket structure on aircraft according to claim 5, it is characterised in that: nut with it is convex
Washer is equipped between platform.
7. tie-down point and jacking bracket structure on aircraft according to claim 2, it is characterised in that: be tethered at prolonging for hole
It is consistent with the extending direction of primary load bearing component joint face of connector and housing construction to stretch direction.
8. tie-down point and jacking bracket structure on aircraft according to claim 1, it is characterised in that: the jack
Support is hemispherical projections.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811205730.XA CN109305382B (en) | 2018-10-17 | 2018-10-17 | Mooring joint and jack support structure on airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811205730.XA CN109305382B (en) | 2018-10-17 | 2018-10-17 | Mooring joint and jack support structure on airplane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109305382A true CN109305382A (en) | 2019-02-05 |
| CN109305382B CN109305382B (en) | 2022-06-03 |
Family
ID=65224554
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811205730.XA Active CN109305382B (en) | 2018-10-17 | 2018-10-17 | Mooring joint and jack support structure on airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109305382B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112758331A (en) * | 2020-12-29 | 2021-05-07 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft front lifting point structure |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1072494A (en) * | 1965-05-11 | 1967-06-14 | Charles Gibbs Potts | Screw-actuated lifting jacks |
| EP0457530A1 (en) * | 1990-05-15 | 1991-11-21 | MacTaggart Scott (Holdings) Ltd. | Improvements in or relating to apparatus for controlling aircraft on ships or the like |
| CN1312890A (en) * | 1998-06-18 | 2001-09-12 | 索斯科公司 | Jack-out captivated screw |
| CN103466496A (en) * | 2013-08-23 | 2013-12-25 | 中国航空工业集团公司西安飞机设计研究所 | Airplane jacking device |
| CN105109665A (en) * | 2015-09-24 | 2015-12-02 | 江西洪都航空工业集团有限责任公司 | Multi-functional wing jack pit |
| CN207046803U (en) * | 2017-08-02 | 2018-02-27 | 中国航空工业集团公司西安飞机设计研究所 | A kind of airframe jack top pad |
| CN207089683U (en) * | 2017-08-11 | 2018-03-13 | 精功（绍兴）复合材料有限公司 | A kind of easy unmanned plane mooring device |
-
2018
- 2018-10-17 CN CN201811205730.XA patent/CN109305382B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1072494A (en) * | 1965-05-11 | 1967-06-14 | Charles Gibbs Potts | Screw-actuated lifting jacks |
| EP0457530A1 (en) * | 1990-05-15 | 1991-11-21 | MacTaggart Scott (Holdings) Ltd. | Improvements in or relating to apparatus for controlling aircraft on ships or the like |
| CN1312890A (en) * | 1998-06-18 | 2001-09-12 | 索斯科公司 | Jack-out captivated screw |
| CN103466496A (en) * | 2013-08-23 | 2013-12-25 | 中国航空工业集团公司西安飞机设计研究所 | Airplane jacking device |
| CN105109665A (en) * | 2015-09-24 | 2015-12-02 | 江西洪都航空工业集团有限责任公司 | Multi-functional wing jack pit |
| CN207046803U (en) * | 2017-08-02 | 2018-02-27 | 中国航空工业集团公司西安飞机设计研究所 | A kind of airframe jack top pad |
| CN207089683U (en) * | 2017-08-11 | 2018-03-13 | 精功（绍兴）复合材料有限公司 | A kind of easy unmanned plane mooring device |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112758331A (en) * | 2020-12-29 | 2021-05-07 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft front lifting point structure |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109305382B (en) | 2022-06-03 |
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