CN203528811U - Module structure for fixing tail wheel and machine body - Google Patents
Module structure for fixing tail wheel and machine body Download PDFInfo
- Publication number
- CN203528811U CN203528811U CN201320496049.1U CN201320496049U CN203528811U CN 203528811 U CN203528811 U CN 203528811U CN 201320496049 U CN201320496049 U CN 201320496049U CN 203528811 U CN203528811 U CN 203528811U
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- CN
- China
- Prior art keywords
- tail wheel
- tail
- mounting groove
- wheel unit
- wheel
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Abstract
The utility model provides a module structure for fixing a tail wheel and a machine body. The module structure comprises the machine body, nuts, bolts, a reinforcing plate and a tail-wheel installing groove, wherein the tail-wheel installing groove is arranged at the tail part of the machine body; the nuts are embedded in the tail-wheel installing groove; the installing surface of a tail-wheel unit is fixedly connected with the lower end surface of the tail-wheel installing groove by the bolts and the nuts; and the reinforcing plate is arranged between the tail-wheel installing groove and the tail-wheel unit. The module structure provided by the utility model has the advantages and the beneficial effects that after the tail-wheel unit is impacted or damaged, the normal work of the other parts of the tail part of the machine body is not influenced, the structure and the flying performance of a plane are not damaged after the tail-wheel unit fails and damaged, the maintenance is convenient when the tail-wheel unit goes wrong or is damaged, fast replacement also can be achieved, the directional control for the tail-wheel unit can be well realized, the problems of high cost and difficulty in manufacturing in the traditional mode are solved, and the potential safety hazard and unnecessary property loss are reduced.
Description
Technical field
The utility model belongs to aerospace flight vehicle field, especially relates to the fixing modular construction of a kind of tail wheel and fuselage.
Background technology
Existing tail wheel and fuselage are fixing is roughly divided into two kinds.
A kind of mode is that tail wheel is directly directly connected with vertical tail lower surface, and such connection mode is worked as tail wheel and suffered that shock can directly cause the damage of afterbody, destroys structure and the airworthiness of aircraft.After damage, be also not easy to maintenance, this connection mode also should not be implemented when the steering structure of design tail wheel simultaneously, can not well realize the control of directivity.
Another kind of mode is the rear lift linkage of a set of complete complexity of design, and in state of flight, tail wheel is received in collection space, and before land, ejecting mechanism ejects tail wheel to land.The high difficulty of manufacturing of such cost design, in the situation that going wrong, tail wheel can not eject simultaneously, and aircraft can not normal landing.Cause very large potential safety hazard, and unnecessary property damage.
Summary of the invention
Problem to be solved in the utility model is a kind of tail wheel and the fixing modular construction of fuselage.
For solving the problems of the technologies described above, the technical solution adopted in the utility model is:
The modular construction that a kind of tail wheel and fuselage are fixing, comprise fuselage, nut, bolt, brace panel, tail wheel mounting groove, the afterbody of described fuselage is provided with described tail wheel mounting groove, in described tail wheel mounting groove, stud with described nut, the attachment face of described tail wheel unit and the lower surface of described tail wheel mounting groove are affixed by described screw bolt and nut, and described brace panel is arranged in the middle of described tail wheel mounting groove and tail wheel unit.
Airframe afterbody generally adopts curved design, as tail wheel unit is directly installed on its curved surface, has larger installation difficulty.Also be difficult to guarantee Joint strenght simultaneously.One tail wheel mounting groove is set, tail wheel unit is installed on the lower surface of tail wheel mounting groove.There is larger horizontal mounting surface mounting portion, and tail wheel unit can be firmly installed.The external impacts being subject to when taking off or land in order to reduce tail wheel unit and afterbody tail wheel mounting groove, increases its service life simultaneously.It is brace panel that spy arranges an interlayer, is used for sharing and offsets tail wheel unit and afterbody tail wheel mounting groove is subject to impulsive force.
Further, the attachment face shape of described tail wheel mounting groove, brace panel and tail wheel unit cooperatively interacts, and described brace panel and tail wheel unit are just arranged in described tail wheel mounting groove.
The attachment face of brace panel and tail wheel unit is lying in described tail wheel mounting groove completely, not merely can plays the object of tail wheel unit, accurate location, and can well reduce the friction force between tail wheel unit, brace panel and tail wheel mounting groove.
Further, described brace panel is carbon fiber sheet.
Selecting carbon fiber sheet is because carbon fiber material has the advantages such as the tough not easy fracture of hardness macrostructure as brace panel.Especially be suitable as the parts use of strengthening intensity.Can well absorb the power that when taking off and landing, airplane tail wheel unit is subject to.
Further, described carbon fiber sheet is 3 layers and is formed by stacking.
Multiple-structure is further gained in strength.
Further, described nut is anti-pawl nut.
Advantage and the good effect that the utlity model has are:
Tail wheel unit clashed into or damage after do not affect the normal work of other parts of afterbody.
2. break down and damage after do not destroy structure and the airworthiness of aircraft.
3. go wrong or damage and be convenient to maintenance, also fast changeable.
4. the control of directivity can well be realized in pair tail wheel unit.
5. solve in traditional approach cost high, manufactured difficult problem.
6. potential safety hazard and unnecessary property damage have been reduced.
Accompanying drawing explanation
Fig. 1 is structural representation of the present utility model;
Fig. 2 is mounting portion of the present utility model part sectional view.
In figure:
1, fuselage 2, tail wheel servomechanism cabin 3, nut
4, bolt 5, tail wheel unit 6, tail wheel mounting groove
7, brace panel
The specific embodiment
As illustrated in fig. 1 and 2, the fixing modular construction of a kind of tail wheel and fuselage comprises fuselage 1, nut 3, bolt 4, brace panel 7, tail wheel mounting groove 6, the afterbody of described fuselage 1 is provided with described tail wheel mounting groove 6, in described tail wheel mounting groove 6, stud with described nut 3, the attachment face of described tail wheel unit 5 and the lower surface of described tail wheel mounting groove 6 are affixed by described bolt 4 and nut 3, and described brace panel 7 is arranged in the middle of described tail wheel mounting groove 6 and tail wheel unit 5.
Airframe afterbody generally adopts curved design, as 5 of the tail wheel unit larger installation difficulty of existence is directly installed on its curved surface.Also be difficult to guarantee Joint strenght simultaneously.One tail wheel mounting groove 6 is set, tail wheel unit 5 is installed on the lower surface of tail wheel mounting groove 6.There is larger horizontal mounting surface mounting portion, and tail wheel unit 5 can be firmly installed.The external impacts being subject to when taking off or land in order to reduce tail wheel unit 5 and fuselage 1 afterbody tail wheel mounting groove 6, increases its service life simultaneously.It is brace panel 7 that spy arranges an interlayer, is used for sharing and offsets tail wheel unit 5 and fuselage 1 afterbody tail wheel mounting groove 6 is subject to impulsive force.The attachment face shape of tail wheel mounting groove 6, brace panel 7 and tail wheel unit 5 cooperatively interacts, and described brace panel 7 and tail wheel unit 5 are just arranged on described tail wheel mounting groove interior 6.The attachment face of brace panel 7 and tail wheel unit 5 is lying in described tail wheel mounting groove to 6 completely, not merely can plays the object of tail wheel unit, accurate location 5, and can well reduce the friction force between tail wheel unit 5, brace panel 7 and tail wheel mounting groove 6.Described brace panel 7 is carbon fiber sheet.Selecting carbon fiber sheet is because carbon fiber material has the advantages such as the tough not easy fracture of hardness macrostructure as brace panel 7.Especially be suitable as the parts use of strengthening intensity.Can well absorb the power that when taking off and landing, airplane tail wheel unit 5 is subject to.Described carbon fiber sheet is that 1-3 layer is formed by stacking.Multiple-structure is further gained in strength.Described nut 3 is anti-pawl nut.Common nut is used for a long time and can produce the loosening situation of vibrations, if this thing happens in aircraft navigation, no matter to the people in equipment or flight range, has very large potential safety hazard, need to select a kind ofly can reduce to shake loosening nut and install.So selecting nut is that anti-pawl nut reaches required working effect.
The working process of this example: during installation, carbon fiber sheet is put into tail wheel mounting groove 6, then tail wheel unit 5 is lying into mounting groove 6 is built under carbon fiber sheet, bolt 4 mounting holes of alignment tail wheel mounting groove 6, carbon fiber sheet, tail wheel unit 5.Packing bolt 4 into is connected with the anti-pawl nut thread of tail wheel mounting groove 6 interior edges.After screwing, installation.
Above an embodiment of the present utility model is had been described in detail, but described content is only preferred embodiment of the present utility model, can not be considered to for limiting practical range of the present utility model.All equalization variations of doing according to the utility model application range and improvement etc., within all should still belonging to patent covering scope of the present utility model.
Claims (5)
1. a tail wheel and the fixing modular construction of fuselage, it is characterized in that: comprise fuselage (1), nut (3), bolt (4), brace panel (7), tail wheel mounting groove (6), the afterbody of described fuselage (1) is provided with described tail wheel mounting groove (6), in described tail wheel mounting groove (6), stud with described nut (3), the lower surface of the attachment face of tail wheel unit (5) and described tail wheel mounting groove (6) is affixed by described bolt (4) and nut (3), and described brace panel is arranged in the middle of described tail wheel mounting groove (6) and tail wheel unit (5).
2. a kind of tail wheel according to claim 1 and the fixing modular construction of fuselage, it is characterized in that: the attachment face shape of described tail wheel mounting groove (6), brace panel (7) and tail wheel unit (5) cooperatively interacts, and described brace panel (7) and tail wheel unit (5) are just arranged in described tail wheel mounting groove (6).
3. a kind of tail wheel according to claim 1 and the fixing modular construction of fuselage, is characterized in that: described brace panel (7) is carbon fiber sheet.
4. a kind of tail wheel according to claim 1 and 2 and the fixing modular construction of fuselage, is characterized in that: described carbon fiber sheet is that 1-3 layer is formed by stacking.
5. a kind of tail wheel according to claim 1 and the fixing modular construction of fuselage, is characterized in that: described nut (3) is anti-pawl nut.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320496049.1U CN203528811U (en) | 2013-08-14 | 2013-08-14 | Module structure for fixing tail wheel and machine body |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320496049.1U CN203528811U (en) | 2013-08-14 | 2013-08-14 | Module structure for fixing tail wheel and machine body |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203528811U true CN203528811U (en) | 2014-04-09 |
Family
ID=50415055
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320496049.1U Expired - Fee Related CN203528811U (en) | 2013-08-14 | 2013-08-14 | Module structure for fixing tail wheel and machine body |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203528811U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105752322A (en) * | 2016-04-19 | 2016-07-13 | 上海交通大学 | Electrically-driven undercarriage system and aircraft comprising same |
-
2013
- 2013-08-14 CN CN201320496049.1U patent/CN203528811U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105752322A (en) * | 2016-04-19 | 2016-07-13 | 上海交通大学 | Electrically-driven undercarriage system and aircraft comprising same |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140409 Termination date: 20150814 |
|
| EXPY | Termination of patent right or utility model |