CN102390541A - Anti-typhoon fixing device for helicopter - Google Patents
Anti-typhoon fixing device for helicopter Download PDFInfo
- Publication number
- CN102390541A CN102390541A CN201110265997XA CN201110265997A CN102390541A CN 102390541 A CN102390541 A CN 102390541A CN 201110265997X A CN201110265997X A CN 201110265997XA CN 201110265997 A CN201110265997 A CN 201110265997A CN 102390541 A CN102390541 A CN 102390541A
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- China
- Prior art keywords
- typhoon
- anchor fitting
- autogyro
- link
- main rotor
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Abstract
The invention discloses an anti-typhoon fixing device for a helicopter. The device is characterized by comprising a device for fixing rotation of the helicopter and a chain mechanism for stabilizing the body of the helicopter, wherein the fixing device is arranged between the end part of a main rotor of the helicopter and a landing gear; one end of the chain mechanism is arranged on the body of the helicopter, and the other end of the chain mechanism is fixed on the ground; and the root part of the main rotor of the helicopter is also provided with a spacing device for preventing each blade of the main rotor of the helicopter from independent rotation. The device has the effect of preventing the main rotor of the helicopter from swinging up and down, and also has the effect of stably landing the helicopter on the ground; and the possibility of rolling over the body of the helicopter is effectively prevented.
Description
[technical field]
The present invention relates to a kind of wind-proof device, relate to a kind of Anti-Typhoon anchor fitting of autogyro specifically.
[background technology]
Autogyro is on garrison duty coastal airport through regular meeting when carrying out the topic training, because the condition on coastal airport is relatively poor; Autogyro can only be parked in the open, and the main rotor of the autogyro that flexibility is bigger only depends on a strap to be pulled on the attachment point of airframe, following problem can occur when violent typhoon is attacked: first; The main rotor of autogyro can be to lower swing, and moment is upwards bounce-back again, several times back and forth; Strap snaps, and the main rotor of last autogyro fractures; The second, rollover appears in autogyro easily.
Take place for fear of above-mentioned accident, guarantee the normal training of army, the main rotor of being badly in need of wanting a kind of anchor fitting can limit autogyro swings up and down, and prevents that the main rotor of autogyro from fractureing; Also can make between autogyro and the ground simultaneously to have secure fixation, prevents the helicopter rollover.
[summary of the invention]
The technical matters that the present invention solves provides a kind of Anti-Typhoon anchor fitting of autogyro, and this structure has the aircraft of preventing main rotor and swings up and down, and it is stable also autogyro and ground to be parked simultaneously, effectively prevents the possibility of airframe rollover.
In order to solve the problems of the technologies described above; The technical scheme that the present invention adopts is: a kind of Anti-Typhoon anchor fitting of autogyro; It is characterized in that: comprise anchor fitting and the chain mechanism that is used for stablizing airframe; Said anchor fitting is arranged between the end and undercarriage of aircraft main rotor; One end of said chain mechanism is installed on the airframe, and the other end of said chain mechanism is fixed on ground, also is provided with the escapement that each blade of preventing the aircraft main rotor independently rotates at the root of aircraft main rotor.
The present invention's beneficial effect compared with prior art is: owing between the end of aircraft main rotor and undercarriage, be provided with anchor fitting; Chain mechanism is installed between airframe and ground; And also be provided with the escapement that each blade of preventing the aircraft main rotor independently rotates at the root of aircraft main rotor; Structure of the present invention has the aircraft of preventing main rotor and swings up and down, and it is stable also autogyro and ground to be parked simultaneously, effectively prevents the possibility of airframe rollover.
Preferably; Said anchor fitting comprises rotor anchor clamps, link span and fixed link; Said rotor anchor clamps are installed in the end of each blade of said aircraft main rotor, and said link span is fixed on the undercarriage, and said rotor anchor clamps are connected fixing with said link span through said fixed link.
Preferably; Said fixed link comprises the preceding bar of bonded assembly, king-rod and back bar successively; The end of bar and back bar is respectively arranged with and is connected the termination before said; Before said, also be provided with extensible member between bar and the king-rod, be connected through jointing between bar and the extensible member, between extensible member and the king-rod, between king-rod and the back bar before said and fix.
The adjusting screw(rod) of scalable length preferably, is installed on the said extensible member.
Preferably; One end of said link span is provided with anchor ear; Said anchor ear is fixed on the undercarriage; The other end of said link span is provided with the termination that is connected of said fixed link and connects fixing front fork, and said rotor anchor clamps are provided with the termination connection that is connected of fixed link and are fixedly coupled jaw.
Preferably, said escapement comprises cutting ferrule and pipe link, and each root of blade of aircraft main rotor is equipped with a cutting ferrule, connects fixing between the adjacent cutting ferrule through pipe link.
Preferably, telescopic adjusting parts are installed on the said pipe link.
Preferably; Said chain mechanism comprises connector, shackle, first cable wire, second cable wire and turnbuckle; Said first cable wire is connected with said connector, and said second cable wire and the said buckle of unloading are connected through turnbuckle between said first cable wire and said second cable wire.
[description of drawings]
Accompanying drawing described herein is to be used to provide further understanding of the present invention, constitutes the application's a part, but does not constitute to improper qualification of the present invention, in the accompanying drawings:
Fig. 1 is a birds-eye view of the present invention;
Fig. 2 is a lateral plan of the present invention;
Fig. 3 is a front view of the present invention;
Fig. 4 is the decomposition texture scheme drawing of fixed link of the present invention;
Fig. 5 is the structural representation of extensible member of the present invention;
Fig. 6 is the structural representation of link span of the present invention;
Fig. 7 is the structural representation of rotor anchor clamps of the present invention;
Fig. 8 is the structural representation of escapement of the present invention;
Fig. 9 is the structural representation of cutting ferrule of the present invention;
Figure 10 is the lateral plan of cutting ferrule of the present invention;
Figure 11 is the structural representation of chain of the present invention mechanism.
The 10-airframe; 12-aircraft main rotor; The 13-blade; The 14-undercarriage; The 20-escapement; The 21-cutting ferrule; The 22-shaft clevis; The 23-pipe link; The 30-fixed link; Bar before the 31-; The 32-king-rod; Bar behind the 33-; 34-connects the termination; The 35-jointing; The 36-extensible member; The 37-adjusting screw(rod); The 40-link span; The 41-anchor ear; The 42-front fork; The 43-eyenut; 50-rotor anchor clamps; The 52-coupling hook; 60-chain mechanism; The 62-connector; The 64-shackle; 66-first cable wire; 67-second cable wire; The 68-turnbuckle.
[specific embodiment]
To combine accompanying drawing and specific embodiment to specify the present invention below, be used for explaining the present invention in illustrative examples of the present invention and explanation, but not as to qualification of the present invention.
Referring to accompanying drawing 1, Fig. 2, shown in Figure 3; The invention discloses a kind of Anti-Typhoon anchor fitting of autogyro; Comprise anchor fitting and the chain mechanism 60 that is used for stablizing airframe 10; Said anchor fitting is arranged between the end and undercarriage 14 of aircraft main rotor 12, and an end of said chain mechanism 60 is installed on the airframe 10, and the other end of said chain mechanism 60 is fixed on ground; The root of said aircraft main rotor 12 also is provided with the escapement 20 of each the blade 13 independent rotation that prevents aircraft main rotor 12; Said anchor fitting comprises rotor anchor clamps 50, link span 40 and fixed link 30, and said rotor anchor clamps 50 are installed in the end of each blade 13 of said aircraft main rotor 12, and said link span 40 is fixed on the undercarriage 14; Said rotor anchor clamps 50 are connected fixing with said link span 40 through said fixed link 30; Said fixed link 30 comprises the preceding bar 31 of bonded assembly, king-rod 32 and back bar 33 successively, and the end of said preceding bar 31 and back bar 33 is respectively arranged with and is connected termination 34, before said, also is provided with extensible member 36 between bar 31 and the king-rod 32; Before said between bar 31 and the extensible member 36, between extensible member 36 and the king-rod 32, king-rod 32 fixes with afterwards being connected through jointing 35 between the bar 33; Shown in accompanying drawing 4, the adjusting screw(rod) 37 of scalable length is installed, on the said extensible member 36 shown in accompanying drawing 5.One end of said link span 40 is provided with anchor ear 41; Said anchor ear 41 is fixed on the said undercarriage 14; The other end of said link span 40 is provided with the termination 34 that is connected of said fixed link 30 and connects fixing front fork 42, and said rotor anchor clamps 50 are provided with termination 34 connections that are connected of fixed link 30 and are fixedly coupled jaw 52, aligns with the hole of undercarriage 14 in the hole on the link span 40; Insert eyenut 43; Eyenut 43 supplies fixedly usefulness of airframe 10 anterior ground, also plays the effect of Connection Bracket and aircraft nose-gear simultaneously, referring to accompanying drawing 6, shown in Figure 7.Said escapement 20 comprises cutting ferrule 21 and pipe link 23; Each blade 13 root of said aircraft main rotor 12 are equipped with a cutting ferrule 21; Connect fixing through pipe link 23 between the adjacent cutting ferrule 21; Referring to accompanying drawing 8, Fig. 9, shown in Figure 10, telescopic adjusting parts are installed on the said pipe link 23, do not show in the accompanying drawing.Said chain mechanism 60 comprises connector 62, shackle 64, first cable wire 66, second cable wire 67 and turnbuckle 68; Said first cable wire 66 is connected with said connector 62; Said second cable wire 67 is connected with said shackle 64; Be connected through turnbuckle 68 between said first cable wire 66 and said second cable wire 67, shown in accompanying drawing 11.Fixing and the airframe 10 of said head fixing basic identical; Just the connector 62 with the upper end has changed shackle 64 into; The shackle 64 of upper end is fixed on the eyenut 43, and the lower end is fixed on the attachment point of ground, and the centre is a turnbuckle 68; Said cable wire and turnbuckle 68 are buckled together, and rotating screw button 68 can tighten up anchor fitting.
Owing between the end of aircraft main rotor 12 and undercarriage 14, be provided with anchor fitting; Chain mechanism 60 is installed between airframe 10 and ground; And also be provided with the escapement 20 of each the blade 13 independent rotation that prevents aircraft main rotor 12 at the root of aircraft main rotor 12; This structure has the aircraft main rotor 12 that prevents aircraft and swings up and down, and it is stable also autogyro and ground to be parked simultaneously, effectively prevents the possibility of airframe 10 rollovers.
The above, is familiar with this technological various simple covert and modification that those skilled in the art did and still belongs to protection scope of the present invention in the spiritual category that does not break away from the present invention's creation only so that the present invention conveniently to be described.
Claims (8)
1. the Anti-Typhoon anchor fitting of an autogyro; It is characterized in that: comprise anchor fitting and the chain mechanism that is used for stablizing airframe; Said anchor fitting is arranged between the end and undercarriage of aircraft main rotor; One end of said chain mechanism is installed on the airframe, and the other end of said chain mechanism is fixed on ground, also is provided with the escapement that each blade of preventing the aircraft main rotor independently rotates at the root of aircraft main rotor.
2. according to the Anti-Typhoon anchor fitting of the said autogyro of claim 1; It is characterized in that: said anchor fitting comprises rotor anchor clamps, link span and fixed link; Said rotor anchor clamps are installed in the end of each blade of said aircraft main rotor; Said link span is fixed on the undercarriage, and said rotor anchor clamps are connected fixing with said link span through said fixed link.
3. according to the Anti-Typhoon anchor fitting of the said autogyro of claim 2; It is characterized in that: said fixed link comprises the preceding bar of bonded assembly, king-rod and back bar successively; The end of bar and back bar is respectively arranged with and is connected the termination before said; Before said, also be provided with extensible member between bar and the king-rod, be connected through jointing between bar and the extensible member, between extensible member and the king-rod, between king-rod and the back bar before said and fix.
4. according to the Anti-Typhoon anchor fitting of the said autogyro of claim 2, it is characterized in that: the adjusting screw(rod) that scalable length is installed on the said extensible member.
5. according to the Anti-Typhoon anchor fitting of claim 3 or 4 said autogyros; It is characterized in that: an end of said link span is provided with anchor ear; Said anchor ear is fixed on the undercarriage; The other end of said link span is provided with the termination that is connected of said fixed link and connects fixing front fork, and said rotor anchor clamps are provided with the termination connection that is connected of fixed link and are fixedly coupled jaw.
6. according to the Anti-Typhoon anchor fitting of autogyro shown in the claim 1, it is characterized in that: said escapement comprises cutting ferrule and pipe link, and each root of blade of aircraft main rotor is equipped with a cutting ferrule, connects fixing between the adjacent cutting ferrule through pipe link.
7. according to the Anti-Typhoon anchor fitting of autogyro shown in the claim 1, it is characterized in that: telescopic adjusting parts are installed on the said pipe link.
8. according to the Anti-Typhoon anchor fitting of autogyro shown in the claim 1; It is characterized in that: said chain mechanism comprises connector, shackle, first cable wire, second cable wire and turnbuckle; Said first cable wire is connected with said connector; Be connected through turnbuckle between said second cable wire and the said buckle of unloading, said first cable wire and said second cable wire.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110265997XA CN102390541A (en) | 2011-09-08 | 2011-09-08 | Anti-typhoon fixing device for helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110265997XA CN102390541A (en) | 2011-09-08 | 2011-09-08 | Anti-typhoon fixing device for helicopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102390541A true CN102390541A (en) | 2012-03-28 |
Family
ID=45857966
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201110265997XA Pending CN102390541A (en) | 2011-09-08 | 2011-09-08 | Anti-typhoon fixing device for helicopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102390541A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103832508A (en) * | 2013-12-03 | 2014-06-04 | 海丰通航科技有限公司 | Helicopter trailer with lifting and safeguarding functions |
| CN103895873A (en) * | 2012-12-25 | 2014-07-02 | 中国直升机设计研究所 | Helicopter mooring flight testing protective device and mooring method of helicopter mooring flight testing protective device |
| CN104890894A (en) * | 2015-04-24 | 2015-09-09 | 江西洪都航空工业集团有限责任公司 | Length and stiffness-adjustable aircraft mooring system |
| US20220297830A1 (en) * | 2021-03-20 | 2022-09-22 | Bell Textron Inc. | Rotorcraft lockout during transport |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3318414A1 (en) * | 1983-05-20 | 1984-11-22 | Blohm + Voss Ag, 2000 Hamburg | Helicopter moving device |
| WO1992019497A1 (en) * | 1991-04-26 | 1992-11-12 | Olafsen Asbjoern | A locking mechanism for the tail rotor of stationary helicopters |
| US5179968A (en) * | 1990-11-16 | 1993-01-19 | United Technologies Corporation | Climatic heat aircraft protective screen |
| US6772483B1 (en) * | 2001-09-24 | 2004-08-10 | Cheryl L. Saunders | Rope-securing device |
| US20050178901A1 (en) * | 2003-10-30 | 2005-08-18 | Violaine Warin | Device for lashing down rotorcraft blades |
| CN202244098U (en) * | 2011-09-08 | 2012-05-30 | 上海航空机械有限公司 | Typhoon-resistant fixing device for helicopter |
-
2011
- 2011-09-08 CN CN201110265997XA patent/CN102390541A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3318414A1 (en) * | 1983-05-20 | 1984-11-22 | Blohm + Voss Ag, 2000 Hamburg | Helicopter moving device |
| US5179968A (en) * | 1990-11-16 | 1993-01-19 | United Technologies Corporation | Climatic heat aircraft protective screen |
| WO1992019497A1 (en) * | 1991-04-26 | 1992-11-12 | Olafsen Asbjoern | A locking mechanism for the tail rotor of stationary helicopters |
| US6772483B1 (en) * | 2001-09-24 | 2004-08-10 | Cheryl L. Saunders | Rope-securing device |
| US20050178901A1 (en) * | 2003-10-30 | 2005-08-18 | Violaine Warin | Device for lashing down rotorcraft blades |
| CN202244098U (en) * | 2011-09-08 | 2012-05-30 | 上海航空机械有限公司 | Typhoon-resistant fixing device for helicopter |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103895873A (en) * | 2012-12-25 | 2014-07-02 | 中国直升机设计研究所 | Helicopter mooring flight testing protective device and mooring method of helicopter mooring flight testing protective device |
| CN103895873B (en) * | 2012-12-25 | 2016-02-24 | 中国直升机设计研究所 | Mooring of helicopter is taken a flight test protective device and mooring method thereof |
| CN103832508A (en) * | 2013-12-03 | 2014-06-04 | 海丰通航科技有限公司 | Helicopter trailer with lifting and safeguarding functions |
| CN103832508B (en) * | 2013-12-03 | 2016-06-29 | 海丰通航科技有限公司 | There is the helicopter trailer of landing, security function |
| CN104890894A (en) * | 2015-04-24 | 2015-09-09 | 江西洪都航空工业集团有限责任公司 | Length and stiffness-adjustable aircraft mooring system |
| US20220297830A1 (en) * | 2021-03-20 | 2022-09-22 | Bell Textron Inc. | Rotorcraft lockout during transport |
| US11760470B2 (en) * | 2021-03-20 | 2023-09-19 | Textron Innovations Inc. | Rotorcraft lockout during transport |
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| PB01 | Publication | ||
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| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20120328 |