CN207889998U - A kind of anti-friction tail apparatus of aircraft and the aircraft with it - Google Patents
A kind of anti-friction tail apparatus of aircraft and the aircraft with it Download PDFInfo
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- CN207889998U CN207889998U CN201720326257.5U CN201720326257U CN207889998U CN 207889998 U CN207889998 U CN 207889998U CN 201720326257 U CN201720326257 U CN 201720326257U CN 207889998 U CN207889998 U CN 207889998U
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- aircraft
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- tail apparatus
- friction
- reinforcing plate
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Abstract
The utility model discloses a kind of anti-friction tail apparatus of aircraft and with its aircraft.The anti-friction tail apparatus of aircraft includes：Main body is connected, the connection main body is installed to the afterbody is default and wiped at tail position；Wearing piece (1), the wearing piece (1) are removably mounted in the connection main body.The anti-friction tail apparatus of aircraft in the utility model is designed with wearing piece, can judge whether to replace component, replacement process is simple, ensure that turning out for work for aircraft according to state of wear after use.Invention design is simple, occupies little space, cost is relatively low, very applicable for middle-size and small-size airplane in transportation category；Pure structure type brings high reliability and safety.
Description
Technical field
The utility model is related to the anti-friction tail technical fields of aircraft, more particularly to a kind of anti-friction tail apparatus of aircraft and have it
Aircraft.
Background technology
In the prior art, general method external at present is scalable anti-friction tail apparatus device, when aircraft angle of attack is larger, machine
When system judges that anti-friction tail apparatus need to be used, scalable anti-friction tail apparatus is opened close to ground in body tail portion.Anti-friction tail apparatus itself
Including energy absorption device, vibrates and relatively small to body injury when contacting to earth.It retracts when not used fuselage, does not destroy underbelly air-flow
Distribution.
But scalable anti-friction tail apparatus design is complicated, and occupied space is big, and cost is higher, for middle-size and small-size airplane in transportation category
For and be not suitable for；Cause whole reliability and safety not high due to adding hydraulic system and electronic system.
Thus, it is desirable to have a kind of technical solution overcomes or at least mitigates at least one drawbacks described above of the prior art.
Utility model content
The purpose of this utility model is to provide a kind of anti-friction tail apparatus of aircraft to overcome or at least mitigate the prior art
At least one drawbacks described above.
To achieve the above object, the utility model provides a kind of anti-friction tail apparatus of aircraft, the anti-friction tail apparatus of aircraft
Including：Main body is connected, the connection main body is installed to the afterbody is default and wiped at tail position；Wearing piece, the wearing piece
It is removably mounted in the connection main body.
Preferably, the connection main body includes：Bracket component, the bracket component are installed to the afterbody is default and are wiped
Tail position；Connection component, the connection component are arranged on the bracket component, and the connection component is described wear-resisting for installing
Part.
Preferably, the bracket component includes：Holder, the holder are installed to the afterbody is default and wipe tail position；
Reinforcing plate, the reinforcing plate is mounted in the space that forebody frame, rear body frame, left stringer and right stringer are surrounded, described
Holder is connect with a face of the reinforcing plate.
Preferably, the bracket component further comprises that the first connector, first connector are connect with the reinforcing plate, institute
Holder is stated to connect with the reinforcing plate by first connector.
Preferably, the connection component includes：Second connector, second connector are provided with first with the reinforcing plate
The face that the face of connector is opposite connects；Connector, the connector and second connector, forebody frame bottom and rear body frame bottom
Portion connects.
Preferably, the holder includes with the collection of first junction contacts middle part and from collection middle part to far from reinforcing plate
The first branch and the second branch that direction extends, first branch and second branch are fixed at forebody frame
And on the web of rear body frame.
Preferably, connecting groove and weight loss groove are provided in first branch and second branch.
Preferably, it is provided with after-frame interface and front frame interface on the face that the connector is connect with second connector,
The after-frame interface with rear body frame bottom for connecting, and the front frame interface with forebody frame bottom for connecting.
Preferably, the connection component further comprises that radome fairing, the radome fairing are arranged on the connector.
Present invention also provides a kind of aircraft, the aircraft includes the anti-friction tail apparatus of aircraft as described above.
The anti-friction tail apparatus of aircraft in the utility model is designed with wearing piece, can be judged after use according to state of wear
Whether component is replaced, and replacement process is simple, ensure that turning out for work for aircraft.Invention design is simple, occupies little space, cost compared with
It is low, it is very applicable for middle-size and small-size airplane in transportation category；Pure structure type brings high reliability and safety.
Description of the drawings
Fig. 1 is the structural schematic diagram according to the anti-friction tail apparatus of aircraft of one embodiment of the utility model.
Fig. 2 is the Structure explosion diagram of the anti-friction tail apparatus of aircraft shown in FIG. 1.
Reference numeral：
Specific implementation mode
To keep the purpose, technical scheme and advantage that the utility model is implemented clearer, below in conjunction with the utility model
Attached drawing in embodiment, is further described in more detail the technical scheme in the embodiment of the utility model.In the accompanying drawings, from beginning
Same or similar element or element with the same or similar functions are indicated to same or similar label eventually.Described reality
It is the utility model a part of the embodiment to apply example, instead of all the embodiments.Below with reference to the embodiment of attached drawing description
It is exemplary, it is intended to for explaining the utility model, and should not be understood as limiting the present invention.It is new based on this practicality
Embodiment in type, the every other implementation that those of ordinary skill in the art are obtained without creative efforts
Example, shall fall within the protection scope of the present invention.The embodiments of the present invention are described in detail below in conjunction with the accompanying drawings.
In the description of the present invention, it should be understood that term "center", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom" "inner", "outside" is based on attached drawing institute
The orientation or positional relationship shown, is merely for convenience of describing the present invention and simplifying the description, rather than indicates or imply and is signified
Device or element must have a particular orientation, with specific azimuth configuration and operation, therefore should not be understood as to this practicality
The limitation of novel protected range.
Fig. 1 is the structural schematic diagram according to the anti-friction tail apparatus of aircraft of one embodiment of the utility model.Fig. 2 is shown in Fig. 1
The anti-friction tail apparatus of aircraft Structure explosion diagram.
The anti-friction tail apparatus of aircraft as shown in Figures 1 and 2 includes connection main body and wearing piece 1, connection main body install to
Afterbody is default to be wiped at tail position；Wearing piece 1 is removably mounted in connection main body.
The anti-friction tail apparatus of aircraft in the utility model is designed with wearing piece, can be judged after use according to state of wear
Whether component is replaced, and replacement process is simple, ensure that turning out for work for aircraft.Invention design is simple, occupies little space, cost compared with
It is low, it is very applicable for middle-size and small-size airplane in transportation category；Pure structure type brings high reliability and safety.
Referring to Fig. 1 and Fig. 2, in the present embodiment, connection main body includes bracket component 2 and connection component 3, bracket component
2 installations wipe tail position to afterbody is default；Connection component 3 is arranged on bracket component 2, and connection component 3 is wear-resisting for installing
Part 1.
Referring to Fig. 1 and Fig. 2, in the present embodiment, bracket component includes holder 21 and reinforcing plate 22, and holder 21 is installed extremely
Afterbody is default to wipe tail position；Reinforcing plate 22 is mounted on what forebody frame, rear body frame, left stringer and right stringer were surrounded
In space, holder 21 is connect with a face of reinforcing plate 22.
Increase reinforcing plate, the bonding strength between bracket component and connection component can be increased.
Referring to Fig. 1 and Fig. 2, in the present embodiment, bracket component further comprises the first connector 23, the first connector 23 with plus
Strong plate 22 connects, and holder is connect by the first connector 23 with reinforcing plate 22.
Referring to Fig. 1 and Fig. 2, in the present embodiment, connection component includes the second connector 31 and connector 32, the second connector
The 31 face connections opposite with the face for being provided with the first connector of reinforcing plate 22；Connector 32 and the second connector, forebody frame bottom
It is connected with rear body frame bottom.
Referring to Fig. 1 and Fig. 2, in the present embodiment, holder 21 includes collecting with the collection of the first junction contacts middle part 211 and oneself
The first branch 212 and the second branch 213 that middle part extends to separate reinforcing plate direction, the first branch 212 and the second branch
213 are fixed on the web of forebody frame and rear body frame.
Holder is provided with the structure using the first branch and the second branch, can further mitigate the weight of holder, and
Individually load, timely branch damage will not influence another branch for Liang Ge branches.
Referring to Fig. 1 and Fig. 2, in the present embodiment, be provided in the first branch 212 and the second branch 213 connecting groove with
And weight loss groove.It, being capable of further loss of weight using this structure.
Referring to Fig. 1 and Fig. 2, it is provided with after-frame in the present embodiment, on the face that connector 32 is connect with the second connector 31 and connects
Mouth and front frame interface, the after-frame interface with rear body frame bottom for connecting, and the front frame interface is used for and forebody frame bottom
Connection.
Referring to Fig. 1 and Fig. 2, in the present embodiment, connection component further comprises radome fairing 33, and the setting of radome fairing 33 is even
On fitting.Since the anti-friction tail apparatus of the aircraft of the application is obform body, aircraft can be influenced unavoidably in aircraft flight
Air-flow, interference of the anti-friction tail apparatus of aircraft of the application to the air-flow of entire aircraft can be reduced to the greatest extent by increasing the radome fairing.
Present invention also provides a kind of aircraft, the aircraft includes the anti-friction tail apparatus of aircraft as described above.
It is last it is to be noted that：Above example is only to illustrate the technical solution of the utility model, rather than limits it
System.Although the utility model is described in detail with reference to the foregoing embodiments, those skilled in the art should manage
Solution：Its still can with technical scheme described in the above embodiments is modified, or to which part technical characteristic into
Row equivalent replacement；And these modifications or replacements, various embodiments of the utility model that it does not separate the essence of the corresponding technical solution
The spirit and scope of technical solution.
Claims (8)
1. a kind of anti-friction tail apparatus of aircraft, which is characterized in that the anti-friction tail apparatus of aircraft includes：
Main body is connected, the connection main body is installed to afterbody is default and wiped at tail position；
Wearing piece (1), the wearing piece (1) are removably mounted in the connection main body,
The connection main body includes：
Bracket component (2), bracket component (2) installation wipe tail position to the afterbody is default；
Connection component (3), the connection component (3) are arranged on the bracket component (2), and the connection component (3) is for pacifying
The wearing piece (1) is filled,
The bracket component includes：
Holder (21), holder (21) installation wipe tail position to the afterbody is default；
Reinforcing plate (22), the reinforcing plate (22) are mounted on what forebody frame, rear body frame, left stringer and right stringer were surrounded
In space, the holder (21) connect with a face of the reinforcing plate (22).
2. the anti-friction tail apparatus of aircraft as described in claim 1, which is characterized in that the bracket component further comprises that first connects
Head (23), first connector (23) connect with the reinforcing plate (22), and the holder passes through first connector (23) and institute
State reinforcing plate (22) connection.
3. the anti-friction tail apparatus of aircraft as claimed in claim 2, which is characterized in that the connection component includes：
Second connector (31), second connector (31) face opposite with the face for being provided with the first connector of the reinforcing plate (22)
Connection；
Connector (32), the connector (32) connect with second connector, forebody frame bottom and rear body frame bottom.
4. the anti-friction tail apparatus of aircraft as claimed in claim 3, which is characterized in that the holder (21) includes being connect with described first
Head contact collection in the middle part of (211) and from collection middle part to far from reinforcing plate direction extend the first branch (212) and second point
Branch (213), first branch (212) and second branch (213) are fixed at forebody frame and rear body frame
Web on.
5. the anti-friction tail apparatus of aircraft as claimed in claim 4, which is characterized in that first branch (212) and described second
Branch is provided with connecting groove and weight loss groove on (213).
6. the anti-friction tail apparatus of aircraft as claimed in claim 5, which is characterized in that the connector (32) and second connector
(31) after-frame interface and front frame interface are provided on the face connected, the after-frame interface with rear body frame bottom for connecting, institute
Front frame interface is stated for being connect with forebody frame bottom.
7. the anti-friction tail apparatus of aircraft as claimed in claim 6, which is characterized in that the connection component further comprises radome fairing
(33), the radome fairing (33) is arranged on the connector.
8. a kind of aircraft, which is characterized in that the aircraft includes that aircraft as claimed in any of claims 1 to 7 in one of claims is anti-friction
Tail apparatus.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720326257.5U CN207889998U (en) | 2017-03-30 | 2017-03-30 | A kind of anti-friction tail apparatus of aircraft and the aircraft with it |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720326257.5U CN207889998U (en) | 2017-03-30 | 2017-03-30 | A kind of anti-friction tail apparatus of aircraft and the aircraft with it |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207889998U true CN207889998U (en) | 2018-09-21 |
Family
ID=63546427
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720326257.5U Active CN207889998U (en) | 2017-03-30 | 2017-03-30 | A kind of anti-friction tail apparatus of aircraft and the aircraft with it |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207889998U (en) |
-
2017
- 2017-03-30 CN CN201720326257.5U patent/CN207889998U/en active Active
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