CN107021242A - A kind of aircraft picketing structure - Google Patents
A kind of aircraft picketing structure Download PDFInfo
- Publication number
- CN107021242A CN107021242A CN201710271578.4A CN201710271578A CN107021242A CN 107021242 A CN107021242 A CN 107021242A CN 201710271578 A CN201710271578 A CN 201710271578A CN 107021242 A CN107021242 A CN 107021242A
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- Prior art keywords
- mooring
- aircraft
- tethered
- component
- tail
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- 230000002153 concerted effect Effects 0.000 claims abstract description 4
- 230000015572 biosynthetic process Effects 0.000 abstract description 8
- 238000010586 diagram Methods 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 210000004602 germ cell Anatomy 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000000116 mitigating effect Effects 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
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—Ground or aircraft-carrier-deck installations for anchoring aircraft
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mutual Connection Of Rods And Tubes (AREA)
Abstract
The invention discloses a kind of aircraft picketing structure, it is related to aircraft floor maintained equipment technical field.The aircraft picketing structure is tethered at that component, fuselage are tethered at component and tail is tethered at component comprising head, the head is tethered at that component, fuselage are tethered at component and tail is tethered at component and is symmetrical arranged in the both sides of fuselage, the both sides of the fuselage refer to airframe wing open up to both sides；The fuselage is tethered at component including at least two second mooring lines, two the second angles of the second mooring line formation；The tail is tethered at component including at least three the 3rd mooring lines, and one end of the 3rd mooring line is fixedly connected with aircraft tail mooring mast, and the other end is fixedly connected with Ground Mooring stake；Component of the component made a concerted effort in the horizontal direction of wherein two the 3rd mooring lines with the pulling force of another 3rd mooring line in the horizontal direction is in opposite direction.It is an advantage of the invention that：The aircraft picketing structure of the present invention reduces the stress of single mooring line, being capable of more preferable tying airplane.
Description
Technical field
The present invention relates to aircraft floor maintained equipment technical field, and in particular to a kind of aircraft picketing structure.
Background technology
The 21st, airplane design handbook《Product comprehensive coverage》(aircraft industry publishing house version in 1998) discloses a germline
The technical scheme for staying equipment to design, its composition is chain or cable wire type of attachment, and weak point is that the technical scheme is general side
Method, not for aircraft concrete structure the characteristics of take be not provided with targetedly measure, propeller class airframe it is special
It is tethered at a little, other airframe components need to be borrowed to complete to be tethered at.§ 25.519 (c) in CCAR CCAR-25-R4
It is required that：When offer is tethered at, principal series stationary point and 120 kilometers/hour of (65 section) water that structure must be able to bear any direction are tethered at
Put down wind-induced limit load.Provided in GJB2757-96 under any possible load combinations and load condition, every is tethered at
Maximum load on cable wire should be no more than 44480N, and this load is limit load.
In the prior art, certain aircraft is being tethered at being tethered under mode of cable wire, the lateral wind speed 35m/s situations of aircraft
When, main landing gear is tethered at cable wire and bears load for 63353N, and tail is tethered at outer cable wire and bears load for 20345.9N, and 45 frames are tethered at
Interior cable wire bears load for 61086.9N.Above-mentioned load is limit load, and ultimate load (design load) multiplies equal to limit load
With safety coefficient 1.5.According to LOAD FOR analysis and cable wire ordinance load, it is tethered at cable wire at main landing gear and 45 frames is tethered at interior steel
Suo Buneng meets the requirement of this tie-down loads.It is, therefore, desirable to provide a kind of new aircraft picketing structure, is wanted with meeting to be tethered at
Ask.
The content of the invention
It is an object of the invention to provide a kind of aircraft picketing structure, with solution or at least in the presence of mitigation background technology
The problem of at least one.
The technical scheme is that：A kind of aircraft picketing structure is provided, being tethered at component, fuselage comprising head is tethered at component
And tail is tethered at component, the head is tethered at that component, fuselage are tethered at component and tail is tethered at component and symmetrically set in the both sides of fuselage
Put, the both sides of the fuselage refer to airframe wing open up to both sides；
The head is tethered at component and includes the first mooring line, one end and the aircraft nose landing gear joint of first mooring line
It is fixedly connected, the other end is fixedly connected with Ground Mooring stake；
The fuselage is tethered at component including at least two second mooring lines, and one end and the aircraft master of second mooring line rise
Fall frame damper leg to be fixedly connected, the other end is fixedly connected with Ground Mooring stake；Two second mooring line formation second are pressed from both sides
Angle；
The tail is tethered at component including at least three the 3rd mooring lines, one end and the aircraft tail of the 3rd mooring line
Mooring mast is fixedly connected, and the other end is fixedly connected with Ground Mooring stake；Wherein two the 3rd mooring lines are made a concerted effort in the horizontal direction
Component and another 3rd mooring line pulling force component in the horizontal direction it is in opposite direction.
It is preferred that, define face on the basis of the both sides symmetrical centre face of fuselage；The aircraft tail mooring mast is included at two, and two
Locate the aircraft tail mooring mast to be symmetrical arranged in the both sides of the reference plane, aircraft tail mooring mast is with the exhibition of wing to being divided into
Both sides；The aircraft tail mooring mast is fixedly connected with the ground by three the 3rd mooring lines, wherein a 3rd mooring line position
In the aircraft tail mooring mast wing open up to side, in addition two the 3rd mooring lines be located at the aircraft tail mooring mast
Wing open up to opposite side.
It is preferred that, for same aircraft tail mooring mast, two the 3rd mooring lines to the same side are opened up in aircraft wing
The 3rd angle be 30 degree to 60 degree.
It is preferred that, the fuselage is tethered at component and includes two second mooring lines, and two second mooring lines pass through difference respectively
Ground Mooring stake be fixedly connected with the ground, the second angle of two second mooring lines formation is 30 degree to 60 degree.
It is preferred that, one end of first mooring line is connected with the first U-shaped ring, and the first U-shaped ring passes through quick-release stop
Pin connection is on aircraft nose landing gear joint；The other end of first mooring line is provided with the first hook, first hook
For being fixedly connected with Ground Mooring stake.
It is preferred that, one end of second mooring line is fixed by clip and the aircraft main landing gear damper leg to be connected
Connect, the other end is provided with the second hook, described second links up with for being fixedly connected with Ground Mooring stake.
It is preferred that, one end of the 3rd mooring line is connected with the second U-shaped ring, and the second U-shaped ring is bolted
On the aircraft tail mooring mast, the other end of the 3rd mooring line is fixed by the 3rd hook and Ground Mooring stake
Connection.
It is preferred that, first mooring line, the second mooring line and the 3rd mooring line are provided with adjusting means, the regulation
Device is arranged on the middle part of every mooring line, length and rate of tension for adjusting mooring line.
The advantage of the invention is that：The present invention aircraft picketing structure by reasonable Arrangement mooring line and Ground Mooring stake,
The stress of single mooring line is reduced, being capable of more preferable tying airplane.
Brief description of the drawings
Fig. 1 is the schematic diagram of the aircraft picketing structure of one embodiment of the invention.
Fig. 2 is the enlarged diagram at I in aircraft picketing structure shown in Fig. 1.
Fig. 3 is Fig. 1 other direction view.
Wherein, the mooring lines of 1- first, the mooring lines of 2- second, the mooring lines of 3- the 3rd, 4- adjusting meanss, 5- reference planes, 6- flies
Machine tail mooring mast, the stake of 7- Ground Moorings, the U-shaped rings of 8- first, 9- clips.
Embodiment
To make the purpose, technical scheme and advantage of the invention implemented clearer, below in conjunction with the embodiment of the present invention
Accompanying drawing, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label represent same or similar element or the element with same or like function.Described embodiment is the present invention
A part of embodiment, rather than whole embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to uses
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiment in the present invention, ordinary skill people
The every other embodiment that member is obtained under the premise of creative work is not made, belongs to the scope of protection of the invention.Under
Embodiments of the invention are described in detail with reference to accompanying drawing for face.
In the description of the invention, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or position relationship of the instruction such as "left", "right", " vertical ", " level ", " top ", " bottom " " interior ", " outer " is based on accompanying drawing institutes
The orientation or position relationship shown, is for only for ease of the description present invention and simplifies description, rather than indicate or imply signified dress
Put or element there must be specific orientation, with specific azimuth configuration and operation, therefore it is not intended that to present invention protection
The limitation of scope.
As shown in Figure 1, Figure 2, Figure 3 shows, a kind of aircraft picketing structure, is tethered at component, fuselage comprising head and is tethered at component and machine
Tail is tethered at component, and the head is tethered at that component, fuselage are tethered at component and tail is tethered at component and is symmetrical arranged in the both sides of fuselage, institute
State fuselage both sides refer to airframe wing open up to both sides.
The head is tethered at component and includes the first mooring line 1, and one end and the aircraft nose landing gear joint of the first mooring line 1 are consolidated
Fixed connection, the other end is fixedly connected with Ground Mooring stake.
The fuselage is tethered at component including at least two second mooring lines 2, and one end and the aircraft master of the second mooring line 2 rise and fall
Frame damper leg is fixedly connected, and the other end is fixedly connected with Ground Mooring stake；Two second mooring line 2 the second angles of formation.
The tail is tethered at component including at least three the 3rd mooring lines 3, one end and the aircraft tail system of the 3rd mooring line 3
Post is stayed to be fixedly connected, the other end is fixedly connected with Ground Mooring stake；Wherein two the 3rd mooring lines 3 are made a concerted effort in the horizontal direction
The component of the pulling force of component and another 3rd mooring line 3 in the horizontal direction is in opposite direction.
In this city embodiment aircraft picketing structure do not change aircraft in itself it is existing be tethered at a little on the premise of, fuselage is tethered at group
Part comprises at least two second mooring lines, and tail is tethered at component including at least three the 3rd mooring lines, and each mooring line passes through not
Being tethered at for aircraft is realized with Ground Mooring stake, the stress of single mooring line when alleviating aircraft picketing can meet aircraft
It is tethered at safety requirements.
In the present embodiment, face 5 on the basis of the both sides symmetrical centre face of fuselage is defined；The aircraft tail mooring mast 6 is wrapped
At two, aircraft tail mooring mast 6 is symmetrical arranged in the both sides of reference plane 5 at two, aircraft tail mooring mast with the exhibition of wing to
It is divided into both sides；Aircraft tail mooring mast 6 is fixedly connected with the ground by three the 3rd mooring lines 3, wherein the 3rd mooring line 3
Positioned at aircraft tail mooring mast 6 wing open up to side, in addition two the 3rd mooring lines 3 exist positioned at aircraft tail mooring mast 6
Wing open up to opposite side.
Specifically, for same aircraft tail mooring mast 6, two the 3rd mooring lines to the same side are opened up in aircraft wing
3 angle is 36 degree.It is understood that for same aircraft tail mooring mast 6, two to the same side are opened up in aircraft wing
The angle of the mooring line 3 of root the 3rd can be set according to actual conditions, for example, in an alternative embodiment, flying for same
Machine tail mooring mast 6, the angle that two the 3rd mooring lines 3 to the same side are opened up in aircraft wing is 45 degree；And for same
Aircraft tail mooring mast 6, aircraft wing open up angle from two the 3rd mooring lines 3 to the same side can 30 degree to 60 degree it
Between set.The advantage is that, not only can wing exhibition to tying airplane, also may be used in head to the tail line direction of aircraft
It is tethered at realizing, so as to decompose the upper power of every mooring line.
In the present embodiment, the fuselage is tethered at component and includes two second mooring lines 2, and two second mooring lines 2 are distinguished
It is fixedly connected with the ground by different Ground Mooring stakes, the second angle of two second mooring line 2 formation is 36 degree.It can manage
Solution, the second angle of two second mooring line 2 formation can also be set according to actual conditions, for example, alternative real at one
Apply in example, the second angle of two second mooring line 2 formation is 45 degree；Second angle of two second mooring lines 2 formation can be with
Set between 30 degree to 60 degree.It the advantage is that, can effectively decompose the pulling force of single mooring line, can not only realize aircraft
Wing open up to be tethered at, head being tethered to tail line direction can also be realized.
In the present embodiment, one end of the first mooring line 1 is connected with the first U-shaped ring 8, and the first U-shaped ring 8 passes through quick-release stop
Pin connection is on aircraft nose landing gear joint；The other end of first mooring line 1 is provided with the first hook, and described first links up with and be used for
It is fixedly connected with Ground Mooring stake.Ground Mooring stake is set to the closed-loop fixed on the ground, and is sunken to below ground, first
Hook uses anti-drop hook, easy to connect, and is less prone to unhook, is tethered at more safe and reliable.
In the present embodiment, one end of the second mooring line 2 is fixed by clip 9 with the aircraft main landing gear damper leg
Connection, the other end is provided with the second hook, and described second links up with for being fixedly connected with Ground Mooring stake.Second mooring line
2 ground connection end is identical with the ground connection end structure of the first mooring line 1, the advantage is that and is advantageously implemented standardization, unites
One changes, easy to use.
In the present embodiment, one end of the 3rd mooring line 3 is connected with the second U-shaped ring, and the second U-shaped ring is connected by bolt
It is connected on the aircraft tail mooring mast, the other end of the 3rd mooring line 3 is fixed by the 3rd hook and Ground Mooring stake
Connection.The ground connection end of 3rd mooring line 3 is identical with the ground connection end structure of the first mooring line 1, the advantage is that favourable
In realizing standardization, unitize, it is easy to use.
In the present embodiment, the first mooring line 1, the second mooring line 2 and the 3rd mooring line 3 are provided with adjusting means 4, institute
The middle part that adjusting means is arranged on every mooring line is stated, length and rate of tension for adjusting mooring line.For example, adjusting means 4
Two ends be connected by swivel nut screw rod, when need adjust mooring line length or rate of tension when, it is only necessary to regulation coordinate spiral shell
The length of line, it is easy to operate.
It is last it is to be noted that：The above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations.To the greatest extent
The present invention is described in detail with reference to the foregoing embodiments for pipe, it will be understood by those within the art that：It is still
Technical scheme described in foregoing embodiments can be modified, or which part technical characteristic is equally replaced
Change；And these modifications or replacement, the essence of appropriate technical solution is departed from the essence of various embodiments of the present invention technical scheme
God and scope.
Claims (8)
1. a kind of aircraft picketing structure, it is characterised in that be tethered at that component, fuselage are tethered at component and tail is tethered at group comprising head
Part, the head is tethered at that component, fuselage are tethered at component and tail is tethered at component and is symmetrical arranged in the both sides of fuselage, the fuselage
Both sides refer to airframe wing open up to both sides；
The head is tethered at component and includes the first mooring line (1), and one end of first mooring line (1) connects with aircraft nose landing gear
Head is fixedly connected, and the other end is fixedly connected with Ground Mooring stake；
The fuselage is tethered at component including at least two second mooring lines (2), one end and the aircraft master of second mooring line (2)
Undercarriage damper leg is fixedly connected, and the other end is fixedly connected with Ground Mooring stake；Two second mooring lines (2) form the
Two angles；
The tail is tethered at component including at least three the 3rd mooring lines (3), one end and the aircraft machine of the 3rd mooring line (3)
Tail mooring mast is fixedly connected, and the other end is fixedly connected with Ground Mooring stake；Wherein two the 3rd mooring lines (3) are made a concerted effort in level
The component of the pulling force of the component in direction and another 3rd mooring line (3) in the horizontal direction is in opposite direction.
2. aircraft picketing structure as claimed in claim 1, it is characterised in that：On the basis of the both sides symmetrical centre face for defining fuselage
Face；The aircraft tail mooring mast is included at two, and the aircraft tail mooring mast is symmetrically set in the both sides of the reference plane at two
Put, aircraft tail mooring mast is with the exhibition of wing to being divided into both sides；The aircraft tail mooring mast (6) passes through three the 3rd mooring lines
(3) be fixedly connected with the ground, wherein the 3rd mooring line (3) be located at the aircraft tail mooring mast wing open up to one
Side, in addition two the 3rd mooring lines (3) be located at the aircraft tail mooring mast wing open up to opposite side.
3. aircraft picketing structure as claimed in claim 2, it is characterised in that：For same aircraft tail mooring mast (6),
The 3rd angle that aircraft wing opens up two the 3rd mooring lines (3) to the same side is 30 degree to 60 degree.
4. aircraft picketing structure as claimed in claim 3, it is characterised in that：The fuselage is tethered at component
Rope (2) is stayed, two second mooring lines (2) are fixedly connected with the ground by different Ground Mooring stakes respectively, and two second are tethered at
The second angle that rope (2) is formed is 30 degree to 60 degree.
5. aircraft picketing structure as claimed in claim 4, it is characterised in that：One end of first mooring line (1) and the first U
Type ring is connected, and the first U-shaped ring is connected on aircraft nose landing gear joint by quick-release latch；First mooring line
(1) the other end is provided with the first hook, and described first links up with for being fixedly connected with Ground Mooring stake.
6. aircraft picketing structure as claimed in claim 5, it is characterised in that：One end of second mooring line (2) passes through card
Hoop is fixedly connected with the aircraft main landing gear damper leg, and the other end is provided with the second hook, described second link up be used for
The Ground Mooring stake is fixedly connected.
7. aircraft picketing structure as claimed in claim 6, it is characterised in that：One end of 3rd mooring line (3) and the 2nd U
Type ring is connected, and the second U-shaped ring is bolted on the aircraft tail mooring mast, the 3rd mooring line (3)
The other end is fixedly connected by the 3rd hook with Ground Mooring stake.
8. aircraft picketing structure as claimed in claim 7, it is characterised in that：First mooring line (1), the second mooring line
(2) and the 3rd mooring line (3) is provided with adjusting means (4), the adjusting means is arranged on the middle part of every mooring line, is used for
Adjust the length and rate of tension of mooring line.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710271578.4A CN107021242A (en) | 2017-04-24 | 2017-04-24 | A kind of aircraft picketing structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710271578.4A CN107021242A (en) | 2017-04-24 | 2017-04-24 | A kind of aircraft picketing structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107021242A true CN107021242A (en) | 2017-08-08 |
Family
ID=59527185
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710271578.4A Pending CN107021242A (en) | 2017-04-24 | 2017-04-24 | A kind of aircraft picketing structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107021242A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109533366A (en) * | 2018-11-13 | 2019-03-29 | 中国直升机设计研究所 | A kind of double freedom mooring device and its design method |
| CN109911137A (en) * | 2017-12-13 | 2019-06-21 | 中航通飞研究院有限公司 | A kind of spill connection bumper assembly of seaplane |
| CN113830322A (en) * | 2021-10-18 | 2021-12-24 | 中航通飞华南飞机工业有限公司 | Method for large-scale amphibious aircraft ground mooring |
-
2017
- 2017-04-24 CN CN201710271578.4A patent/CN107021242A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109911137A (en) * | 2017-12-13 | 2019-06-21 | 中航通飞研究院有限公司 | A kind of spill connection bumper assembly of seaplane |
| CN109533366A (en) * | 2018-11-13 | 2019-03-29 | 中国直升机设计研究所 | A kind of double freedom mooring device and its design method |
| CN113830322A (en) * | 2021-10-18 | 2021-12-24 | 中航通飞华南飞机工业有限公司 | Method for large-scale amphibious aircraft ground mooring |
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Application publication date: 20170808 |
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| WD01 | Invention patent application deemed withdrawn after publication |