CN110683062B - Helicopter tail protection device - Google Patents
Helicopter tail protection device Download PDFInfo
- Publication number
- CN110683062B CN110683062B CN201910931894.9A CN201910931894A CN110683062B CN 110683062 B CN110683062 B CN 110683062B CN 201910931894 A CN201910931894 A CN 201910931894A CN 110683062 B CN110683062 B CN 110683062B
- Authority
- CN
- China
- Prior art keywords
- rocking arm
- helicopter
- rocker arm
- protection device
- buffer
- 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.)
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Links
- 239000011358 absorbing material Substances 0.000 claims description 19
- 239000006096 absorbing agent Substances 0.000 claims description 6
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 4
- 229910052782 aluminium Inorganic materials 0.000 claims description 4
- AZDRQVAHHNSJOQ-UHFFFAOYSA-N alumane Chemical group [AlH3] AZDRQVAHHNSJOQ-UHFFFAOYSA-N 0.000 claims description 3
- 239000002131 composite material Substances 0.000 claims description 3
- 239000007787 solid Substances 0.000 claims description 3
- 239000000463 material Substances 0.000 claims description 2
- 238000010521 absorption reaction Methods 0.000 description 5
- 230000003139 buffering effect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 229910052751 metal Inorganic materials 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 150000002739 metals Chemical class 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Vibration Dampers (AREA)
Abstract
The invention discloses a helicopter tail protection device which comprises a rocker arm (4), a buffer (3), a retractable rocker arm (1) and an actuator (2), wherein the rocker arm (4) comprises a rocker arm main body (12), a bearing seat (13) and a rocker arm joint (11), the rocker arm main body (12) is connected between the rocker arm joint (11) and the bearing seat (13), one end of the buffer (3) is connected to the bearing seat (13) of the rocker arm (4), the other end of the buffer is connected with one end of the retractable rocker arm (1), the actuator (2) has the functions of stretching and locking up and down, one end of the actuator (2) is connected to the retractable rocker arm (1), the other end of the actuator is connected with the buffer (3), and the helicopter tail protection device is connected with a helicopter body through the rocker arm joint (11) and the other end of the rocker arm (1). The helicopter tail protection device is used for protecting the tail structure when the helicopter is over-lifted to land or take off, can be folded and unfolded, and can meet the space requirement of the tail of the helicopter.
Description
Technical Field
The invention belongs to the field of structural design of helicopters, and particularly relates to a tail protection device of a helicopter.
Background
The tail protection device is usually installed at the tail of the helicopter to prevent the tail structure or the tail rotor from touching the ground and being damaged when the helicopter lands abnormally. For a transport helicopter, in order to meet the loading and unloading of goods or vehicles, the ground clearance of a helicopter body is lower, and a conventional tail protection device meets the requirements of buffering and energy absorption, and is generally larger in structural size, so that the tail space of the helicopter is severely limited, and a transport passage of goods is obstructed.
Disclosure of Invention
In view of the above-mentioned state of the art, the present invention provides a helicopter tail protection device that can provide protection function when the helicopter lands and can be folded and retracted on the ground.
The above object of the present invention is achieved by the following technical solutions:
the utility model provides a helicopter afterbody protection device, including the rocking arm, the buffer, receive and release rocking arm and actuator, the rocking arm includes the rocking arm main part, bearing seat and rocking arm joint, rocking arm main part one end and rocking arm articulate, the other end is connected with the bearing seat, the one end of buffer is connected on the bearing seat of rocking arm, the other end with receive and release rocking arm one end and be connected, the actuator has flexible and last lower locking function, actuator one end is connected on receiving and releasing the rocking arm, the other end is connected with the buffer, helicopter afterbody protection device passes through the rocking arm and connects, the other end and the fuselage that receive and release the rocking arm are connected.
Further, the buffer includes a crushing energy absorption buffer, an oil-gas buffer, and the like. The crushing energy-absorbing buffer comprises an outer barrel, a crushing energy-absorbing material and a piston rod, wherein the piston rod is connected with the outer barrel through a snap ring and moves axially along the inner circle of the outer barrel, the crushing energy-absorbing material is placed inside the outer barrel of the buffer, and a certain gap is reserved between the crushing energy-absorbing material and the outer barrel. In addition, supporting sleeves can be arranged among the upper part, the middle part and the lower part of the crushing energy-absorbing material and the outer barrel of the buffer, so that the crushing energy-absorbing material is prevented from being unstable after being compressed. The crushing energy-absorbing material is preferably a foamed aluminum core, and can be other foamed metals or a honeycomb structure.
The rocker arm main body enables the rocker arm joint to keep a certain span, so that the transverse stability is kept, and the size of the span can be specifically selected according to specific conditions. The rocker arm main body can be of an A-shaped structure and a solid triangular structure, or consists of two round pipes with a certain included angle. The material of the rocker arm main body is preferably aluminum or composite material, so that the structural weight is greatly reduced.
The helicopter tail protection device is used for protecting the tail structure when the helicopter is over-lifted to land or take off, and can be folded and unfolded to meet the space requirement of the tail of the helicopter.
Drawings
Fig. 1 is a schematic view of the structural composition of the tail protection device of the helicopter of the present invention.
Fig. 2 is a cross-sectional view of a crush absorber of the helicopter tail protection of the present invention.
Fig. 3 is a schematic view of the structure of the rocker arm of the tail protection device of the helicopter of the present invention.
Fig. 4 is a schematic diagram of the energy absorption operation of the helicopter tail protection apparatus of the present invention.
Fig. 5 is a schematic view of the retraction and extension operation of the helicopter tail protection device of the present invention.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Fig. 1 is a schematic view of the structural composition of the tail protection device of the helicopter of the present invention. As shown in the figure, the helicopter tail protection device comprises a rocker arm 4, a buffer 3, a retractable rocker arm 1 and an actuator 2. The rocker arm 4 includes a rocker arm body 12, a retainer 13, and a rocker joint 11, and the rocker arm body 12 is connected to the rocker joint 11 at one end by a rivet and connected to the retainer 13 at the other end by a rivet (see fig. 3). The buffer 3 can adopt a crushing energy absorption buffer, an oil-gas buffer and the like. One end of the buffer 3 is connected to the bearing seat 13 of the rocker arm 4 through a bolt, and the other end is connected with one end of the retractable rocker arm 1. The actuator 2 has the functions of expansion and up-down locking, one end of the actuator 2 is connected to the retractable rocker arm 11, and the other end of the actuator 2 is connected with the buffer 3. The helicopter tail protection device is connected with the helicopter body through the rocker joint 11 and the other end of the retractable rocker 1.
In the present embodiment, the bumper 3 is a crush absorber. Fig. 2 is a cross-sectional view of a crush absorber of the helicopter tail protection of the present invention. As shown in the figure, the crush absorber includes an outer tube 6, a crush energy absorbing material 7, and a piston rod 9. The piston rod 9 is connected with the outer cylinder 6 through a snap ring, moves axially along the inner circle of the outer cylinder 6, the crushing energy-absorbing material 7 achieves the crushing energy-absorbing function and is placed inside the outer cylinder 6 of the buffer, and after the crushing energy-absorbing buffer is compressed, a certain gap is reserved between the crushing energy-absorbing material 7 and the outer cylinder 6 for meeting the placing space of the crushed volume of the crushing energy-absorbing material 7 and the crushing energy-absorbing material 7. Supporting sleeves 8 can be arranged among the upper part, the middle part and the lower part of the crushing energy-absorbing material 7 and the outer barrel 6 of the buffer, so that the crushing energy-absorbing material 7 is prevented from being unstable after being compressed. The crushing energy-absorbing material 7 is preferably a foamed aluminum core, and the foamed aluminum crushing energy-absorbing buffer can greatly reduce the weight of the structure and can also be of other foamed metals or a honeycomb structure.
The rocker arm body 12 maintains the rocker joint 11 at a certain span, which may be selected as appropriate, thereby maintaining lateral stability. Can be in an A-shaped structure, a solid triangular structure, or formed by two round pipes with a certain included angle, as shown in figure 3. The rocker arm body 12 is preferably made of aluminum or a composite material, so that the structural weight is greatly reduced.
Fig. 4 is a schematic diagram of the energy absorption operation of the helicopter tail protection device of the present invention. As shown in the figure, the actuator 2 locks the tail protection device at the laying-down position, and when the bearing seat at the bottom of the rocker arm 4 is impacted, the rocker arm 4 is driven to rotate anticlockwise, and meanwhile, the buffer 3 is compressed, so that the buffering and energy-absorbing functions are realized.
Fig. 5 is a schematic view of the retraction and extension operation of the helicopter tail protection device of the present invention. As shown in fig. 5, when the helicopter tail protection device is folded, the actuator 2 is retracted to drive the folding and unfolding rocker arm 1 and the buffer 3 to fold around the joint of the folding and unfolding rocker arm 1 and the buffer 3, and the rocker arm 4 is driven to rotate around the bolt at the joint of the rocker arm joint 11 and the helicopter body until the helicopter tail protection device is folded up. When the helicopter is put down, the tail protection device of the helicopter is in a retracting position, the actuator 2 extends to drive the retractable rocker arm 1 and the buffer 3 to extend around the joint of the retractable rocker arm 1 and the buffer 3, and the rocker arm 4 is driven to rotate around the bolt at the joint of the rocker arm joint 11 and the helicopter body until the tail protection device is put down.
The helicopter tail protection device is used for protecting the tail structure when the helicopter is over-lifted to land or take off, and can be folded and unfolded to meet the space requirement of the tail of the helicopter.
Claims (8)
1. The utility model provides a helicopter afterbody protection device, including rocking arm (4), buffer (3), receive and release rocking arm (1) and actuator (2), rocking arm (4) are including rocking arm main part (12), bearing (13) and rocking arm joint (11), rocking arm main part (12) one end is connected with rocking arm joint (11), the other end is connected with bearing (13), the one end of buffer (3) is connected on bearing (13) of rocking arm (4), the other end with receive and release rocking arm (1) one end and be connected, actuator (2) have flexible and upper and lower position locking function, actuator (2) one end is connected on receiving and releasing rocking arm (1), the other end is connected with buffer (3), helicopter afterbody protection device passes through rocking arm joint (11), the other end and the fuselage of rocking arm (1) are connected.
2. The helicopter tail protection device of claim 1 wherein said bumper (3) is a crush energy absorber or a gas-oil bumper.
3. The helicopter tail protection device according to claim 2 wherein the crush energy absorber comprises an outer cylinder (6), a crush energy absorbing material (7) and a piston rod (9), the piston rod (9) is connected with the outer cylinder (6) through a snap ring and moves axially along the inner circle of the outer cylinder (6), the crush energy absorbing material (7) is placed inside the outer cylinder (6) of the bumper, and a certain gap is reserved between the crush energy absorbing material (7) and the outer cylinder (6).
4. A helicopter tail protection according to claim 3 wherein support sleeves (8) are provided between the upper, middle and lower portions of the crush-energy absorbing material (7) and the bumper outer barrel (6).
5. Helicopter tail protection according to claim 3 or 4 wherein the crush-absorbing material (7) is a foamed aluminium core or a honeycomb structure.
6. The helicopter tail protection apparatus of claim 1 wherein the rocker arm body (12) is of an a-configuration or a solid triangular configuration.
7. The helicopter tail protection apparatus of claim 1 wherein the rocker arm body (12) is formed from two tubes having an included angle.
8. The helicopter tail protection device of claim 6 or 7 wherein the material of the rocker arm body (12) is aluminum or a composite material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910931894.9A CN110683062B (en) | 2019-09-29 | 2019-09-29 | Helicopter tail protection device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910931894.9A CN110683062B (en) | 2019-09-29 | 2019-09-29 | Helicopter tail protection device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110683062A CN110683062A (en) | 2020-01-14 |
| CN110683062B true CN110683062B (en) | 2023-04-18 |
Family
ID=69110930
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910931894.9A Active CN110683062B (en) | 2019-09-29 | 2019-09-29 | Helicopter tail protection device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110683062B (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2088478C1 (en) * | 1995-02-28 | 1997-08-27 | Акционерное общество открытого типа "ОКБ Сухого" | Flying vehicle retractable landing gear |
| CA2744503A1 (en) * | 2008-12-05 | 2010-06-10 | Messier-Dowty Sa | Device for retracting aircraft landing gear |
| WO2011157807A1 (en) * | 2010-06-16 | 2011-12-22 | Messier-Bugatti-Dowty | Main landing gear of an aircraft, comprising two walking beams joined to the structure of the aircraft in an articulated manner |
| CN202624629U (en) * | 2012-04-27 | 2012-12-26 | 中国直升机设计研究所 | Rocker type landing gear |
| CN104176244A (en) * | 2014-09-17 | 2014-12-03 | 江西洪都航空工业集团有限责任公司 | Linked landing gear cabin door folding and unfolding device |
| CN104290902A (en) * | 2014-08-26 | 2015-01-21 | 中国直升机设计研究所 | Rocking arm-type undercarriage |
| CN109204789A (en) * | 2018-10-23 | 2019-01-15 | 中航飞机起落架有限责任公司 | Undercarriage buffer gear and undercarriage |
Family Cites Families (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7857590B1 (en) * | 2006-08-11 | 2010-12-28 | Neal Larry R | Folding rotor for a rotorcraft |
| JP2010112404A (en) * | 2008-11-04 | 2010-05-20 | Wel Research Co Ltd | Buffer and landing device |
| CN103241392B (en) * | 2013-04-25 | 2016-04-20 | 上海卫星工程研究所 | Deep space weak gravitation celestial body attachment device and construction method thereof |
| CN105438486B (en) * | 2015-12-11 | 2017-06-16 | 中国航空工业集团公司西安飞机设计研究所 | A kind of afterbody protection system |
| CN106965922B (en) * | 2016-01-13 | 2020-06-09 | 哈尔滨飞机工业集团有限责任公司 | Novel rocker arm type undercarriage |
| 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 |
| CN106516137A (en) * | 2016-11-30 | 2017-03-22 | 中国直升机设计研究所 | Tail protection device |
| CN108058817B (en) * | 2017-12-03 | 2021-05-11 | 中国直升机设计研究所 | Undercarriage buffer |
| CN109808873B (en) * | 2019-03-20 | 2022-05-27 | 西北工业大学 | Linear self-locking tail part folding and unfolding buffer device |
-
2019
- 2019-09-29 CN CN201910931894.9A patent/CN110683062B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2088478C1 (en) * | 1995-02-28 | 1997-08-27 | Акционерное общество открытого типа "ОКБ Сухого" | Flying vehicle retractable landing gear |
| CA2744503A1 (en) * | 2008-12-05 | 2010-06-10 | Messier-Dowty Sa | Device for retracting aircraft landing gear |
| WO2011157807A1 (en) * | 2010-06-16 | 2011-12-22 | Messier-Bugatti-Dowty | Main landing gear of an aircraft, comprising two walking beams joined to the structure of the aircraft in an articulated manner |
| CN202624629U (en) * | 2012-04-27 | 2012-12-26 | 中国直升机设计研究所 | Rocker type landing gear |
| CN104290902A (en) * | 2014-08-26 | 2015-01-21 | 中国直升机设计研究所 | Rocking arm-type undercarriage |
| CN104176244A (en) * | 2014-09-17 | 2014-12-03 | 江西洪都航空工业集团有限责任公司 | Linked landing gear cabin door folding and unfolding device |
| CN109204789A (en) * | 2018-10-23 | 2019-01-15 | 中航飞机起落架有限责任公司 | Undercarriage buffer gear and undercarriage |
Non-Patent Citations (1)
| Title |
|---|
| 黄辰.主起落架可控变速收放作动器设计与仿真.《北京航天航空大学学报》.2015,第31-36页. * |
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| Publication number | Publication date |
|---|---|
| CN110683062A (en) | 2020-01-14 |
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