CN108100274A - A kind of destruction endergonic structure of helicopter tail part protection ducted tail rotor - Google Patents
A kind of destruction endergonic structure of helicopter tail part protection ducted tail rotor Download PDFInfo
- Publication number
- CN108100274A CN108100274A CN201710574669.5A CN201710574669A CN108100274A CN 108100274 A CN108100274 A CN 108100274A CN 201710574669 A CN201710574669 A CN 201710574669A CN 108100274 A CN108100274 A CN 108100274A
- Authority
- CN
- China
- Prior art keywords
- helicopter
- duct
- side wall
- endergonic structure
- laminate
- 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.)
- Pending
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
- B64D45/04—Landing aids; Safety measures to prevent collision with earth's surface
- B64D45/06—Landing aids; Safety measures to prevent collision with earth's surface mechanical
Abstract
The present invention relates to a kind of endergonic structures, it is especially useful in helicopter tailskid and endpiece common eigenvector absorb tailskid and landing impact energy, which is used for the collision energy-absorbing of empennage of helicopter duct, which has side wall and bottom wall；The side wall and bottom wall is laminate；At least 3 layers of laminate；The end of side wall has flange, and the flange is used to be fixedly connected with duct substructure.It solves existing mounting structure and includes the parts such as tailskid connector, stent and reinforcer, the technical issues of complicated, weight is big, and installation is difficult in maintenance, and production cost is high.
Description
Technical field
The present invention relates to a kind of destruction endergonic structures of helicopter tail part protection ducted tail rotor.
Background technology
Existing ducted tail rotor protective device is to install tailskid in duct lower part, in order to prevent the duct in helicopter landing
Tail-rotor hits ground, and tailskid landings impact energy by being connected common eigenvector absorption with endpiece, and tailskid is designed to rigid body, passes through
It is bolted on duct lower mounting configuration.
The content of the invention
Goal of the invention
According to 411 articles of airworthiness requirements of CCAR-29-R1 §, during helicopter normally landing, if tail rotor is likely to contact
Ground, then requirement provides special protection to tail rotor, to prevent it from touching landing surface.Tail rotor must not in normally landing
Ground may be contacted；If necessary to protective device, then this protective device and its support construction must be able to bear appropriate design load
Lotus.
Existing ducted tail rotor protective device is mainly the tail sled of installation below duct.After ducted tail rotor hits ground,
In order to ensure ducted tail rotor and tail sled can common eigenvector absorb Impact energy, it is necessary to inside duct set tailskid install connect
The structures such as head, stent and reinforcer, complicated, weight is big, and installation is difficult in maintenance.So the present invention devise it is a kind of simple,
Light-weight, Fast Installation and the endergonic structure of maintenance by the way of energy-absorbing is destroyed, achieve the purpose that protect ducted tail rotor.
Technical solution
To achieve the above object, endergonic structure is installed in ducted tail rotor structure bottom, reaches suction by the structural damage
The effect of energy, main feature are as follows：The endergonic structure is used for the collision energy-absorbing of empennage of helicopter duct, which has side
Wall and bottom wall；The side wall and bottom wall is laminate；At least 3 layers of laminate；The end of side wall has flange, and described turns over
Side is used to be fixedly connected with duct substructure.
Further, the laminate is heated to obtain by glass fibre and/or epoxy composite material prepreg overlay.
Further, on flange also there is the reinforcement laying of layer 2-4, match with covering rigidity under duct, so as to real
When endergonic structure is by absorption whole Impact energy is destroyed during present stern settlement landing attitude, ducted tail rotor structure is without destruction.
The endergonic structure is located at ducted tail rotor structural base, is connected to by hinged bolt on lower covering nut, meets B
Class exchanges requirement.Covering is located at duct bottom under duct, and using composite material sandwich structure, installation position is provided for endergonic structure
It puts, as shown in Figure 1.
For helicopter in stern settlement landing attitude, endergonic structure can contact ground prior to undercarriage, and collision triggers first
Shape trigger point is destroyed, and then forms stable progressive conquassation mode absorbent impact energy, which, which can rely on to destroy, absorbs
Kinetic energy during least favorable position of centre of gravity.The endergonic structure maximum appearance and size is 1445 × 630 × 245, and bottom is cut at trigger point
Face is tilted with the horizontal certain angle, both ends into certain arc-shaped curved surface, and trigger position and appearance and size are as shown in Figure 2；
Technique effect
This structure design meets 411 articles of airworthiness requirements of CCAR-29-R1 §.It is simple in structure compared with conventional tailskid structure,
Part is few, light-weight, dismantles, is easy to maintenance, reducing production, maintenance cost.
Description of the drawings
Fig. 1 endergonic structure scheme of installation；
Fig. 2 endergonic structure appearance schematic diagrams；
Another appearance schematic diagram of Fig. 3 endergonic structures；
The top view of Fig. 4 endergonic structures；
Fig. 5 is the Section A-A schematic diagram of Fig. 3；
Wherein：1. empennage of helicopter duct, 2. duct substructures (covering under duct), 3. endergonic structures, 4. side walls, 5.
Bottom wall.
Specific embodiment
A kind of endergonic structure is provided, which is used for the collision energy-absorbing of empennage of helicopter duct 1, the endergonic structure
With side wall 4 and bottom wall 5；The side wall and bottom wall is laminate；At least 3 layers of laminate；The end of side wall has flange,
The flange is used to be fixedly connected with duct substructure 2.
Further, the laminate is heated to obtain by glass fibre and/or epoxy composite material prepreg overlay.
Further, on flange also there is the reinforcement laying of layer 2-4, match with covering rigidity under duct, so as to real
When endergonic structure is by absorption whole Impact energy is destroyed during present stern settlement landing attitude, ducted tail rotor structure is without destruction.
Claims (3)
1. a kind of endergonic structure, which is used for the collision energy-absorbing of empennage of helicopter duct, which has side wall
With bottom wall；The side wall and bottom wall is laminate；At least 3 layers of laminate；The end of side wall has flange, and described turns over
Side is used to be fixedly connected with duct substructure.
2. a kind of endergonic structure as described in claim 1, it is characterised in that：The laminate is by glass fibre and/or epoxy
Material prepreg laying heats to obtain.
3. a kind of endergonic structure as described in claim 1, it is characterised in that：Also there is the reinforcement laying of layer 2-4 on flange.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710574669.5A CN108100274A (en) | 2017-07-14 | 2017-07-14 | A kind of destruction endergonic structure of helicopter tail part protection ducted tail rotor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710574669.5A CN108100274A (en) | 2017-07-14 | 2017-07-14 | A kind of destruction endergonic structure of helicopter tail part protection ducted tail rotor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108100274A true CN108100274A (en) | 2018-06-01 |
Family
ID=62207136
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710574669.5A Pending CN108100274A (en) | 2017-07-14 | 2017-07-14 | A kind of destruction endergonic structure of helicopter tail part protection ducted tail rotor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108100274A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109850137A (en) * | 2019-03-18 | 2019-06-07 | 西安爱生技术集团公司 | A kind of quick-detachable rear fulcrum damping of parachuting unmanned plane |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN86105175A (en) * | 1985-08-23 | 1987-04-08 | 格鲁曼航天公司 | Endergonic foam-fabric laminate |
| CN103661917A (en) * | 2012-09-07 | 2014-03-26 | 尤洛考普特德国有限公司 | Empennage of helicopter |
| WO2015193795A1 (en) * | 2014-06-16 | 2015-12-23 | Sabic Global Technologies B.V. | Method of making a laminate, an energy absorbing device, an energy absorbing device composition, and a forming tool |
| CN105438486A (en) * | 2015-12-11 | 2016-03-30 | 中国航空工业集团公司西安飞机设计研究所 | Rear fuselage protection system |
| CN105947195A (en) * | 2015-03-09 | 2016-09-21 | 瑞士玛瑞恩克直升机公司 | Tail rotor device of a helicopter |
| CN206278277U (en) * | 2016-11-30 | 2017-06-27 | 中国直升机设计研究所 | A kind of jack of helicopter tail part protection device |
-
2017
- 2017-07-14 CN CN201710574669.5A patent/CN108100274A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN86105175A (en) * | 1985-08-23 | 1987-04-08 | 格鲁曼航天公司 | Endergonic foam-fabric laminate |
| CN103661917A (en) * | 2012-09-07 | 2014-03-26 | 尤洛考普特德国有限公司 | Empennage of helicopter |
| WO2015193795A1 (en) * | 2014-06-16 | 2015-12-23 | Sabic Global Technologies B.V. | Method of making a laminate, an energy absorbing device, an energy absorbing device composition, and a forming tool |
| CN105947195A (en) * | 2015-03-09 | 2016-09-21 | 瑞士玛瑞恩克直升机公司 | Tail rotor device of a helicopter |
| CN105438486A (en) * | 2015-12-11 | 2016-03-30 | 中国航空工业集团公司西安飞机设计研究所 | Rear fuselage protection system |
| CN206278277U (en) * | 2016-11-30 | 2017-06-27 | 中国直升机设计研究所 | A kind of jack of helicopter tail part protection device |
Non-Patent Citations (2)
| Title |
|---|
| 张德和等: "《中国人民解放军陆军航空兵》", 31 October 2013, 五洲传播出版社 * |
| 昂海松等: "《现代航空工程》", 30 September 2012, 国防工业出版社 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109850137A (en) * | 2019-03-18 | 2019-06-07 | 西安爱生技术集团公司 | A kind of quick-detachable rear fulcrum damping of parachuting unmanned plane |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20180601 |
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| RJ01 | Rejection of invention patent application after publication |