CN104670517A - Helicopter landing fixing and takeoff ejection system - Google Patents
Helicopter landing fixing and takeoff ejection system Download PDFInfo
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- CN104670517A CN104670517A CN201510101232.0A CN201510101232A CN104670517A CN 104670517 A CN104670517 A CN 104670517A CN 201510101232 A CN201510101232 A CN 201510101232A CN 104670517 A CN104670517 A CN 104670517A
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- fixed
- landing
- autogyro
- helicopter
- footing
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Abstract
The invention discloses a helicopter landing fixing and takeoff ejection system which comprises a fixed lattice and a ground wireless receiver, wherein the fixed lattice is composed of a plurality of fixed units, and the ground wireless receiver is electrically connected with the fixed units; the ground wireless receiver is in wireless communication with a helicopter wireless controller; each fixed unit is provided with a proximity switch and an execution element and is electrically connected with the ground wireless receiver through the proximity switch; the helicopter wireless controller is provided with a takeoff input end and a landing input end, a takeoff signal port which corresponds to a takeoff position is formed in the takeoff input end, and a landing signal port which corresponds to a landing position is formed in the landing input end. According to the helicopter landing fixing and takeoff ejection system, the final landing operation can be executed after a helicopter is fully fixed during landing, and the helicopter can be prevented from sliding or bouncing. During takeoff, the pressing of the fixed units on feet is released when the maximum takeoff power is approached, so that the helicopter is quickly ejected.
Description
Technical field
The present invention relates to one to rise and fall anchor fitting, more particularly refer to that helicopter landing is fixed and take off ejection system and method thereof.
Background technology
In prior art, at sea rescue, ocean supervision, the field such as military, use depopulated helicopter or when having people's helicopter, when landing, the situation easily producing spring or slide, thus autogyro is skidded off rise and fall region, produces unsafe accident.In order to prevent the generation of these accidents, usually can adopt and strengthen the practice of region area of rising and falling, and such practice can increase cost, such way can not the generation of completely anti-sliding stop or spring.
Therefore, be necessary to develop helicopter landing to fix and take off ejection system and method thereof.
Summary of the invention
The object of the invention is to the defect overcoming prior art, provide a kind of helicopter landing to fix and take off ejection system and method thereof.
For achieving the above object, the present invention is by the following technical solutions:
Helicopter landing is fixed and takes off ejection system, comprises the fixing dot matrix be made up of several fixed cells, and the terrestrial radio receiver be electrically connected with fixed cell; Described terrestrial radio receiver is connected with the aircraft wireless controller wireless telecommunications be located on autogyro; Each fixed cell is provided with for judging the proximity switch whether autogyro footing is close, and each fixed cell is provided with power element and is electrically connected by proximity switch and terrestrial radio receiver; Described aircraft wireless controller is provided with take off input end and landing input end; The described input end that takes off is provided with the take off signal port corresponding with the position of taking off of collective-pitch lever master cock; Described landing input end is provided with corresponding with the landing position of collective-pitch lever master cock and the falling signal port of connecting with the contact switch be located on aircraft footing.
Its further technical scheme is: described fixed cell is fixed leg, and described fixed leg upper end is provided with the lifting mechanism that vertical direction is arranged and the switching mechanism being located at lifting mechanism upper end.
Its further technical scheme is: described lifting mechanism is lift cylinder, and described switching mechanism comprises the rotary cylinder being fixed on lift cylinder movable end and the depression bar being fixed at rotary cylinder movable end.
A landing fixing means for autogyro, the method is taken to a few fixing dot matrix formed by fixed cell; When autogyro lands, the fixed cell of autogyro footing surrounding detects the close of footing, and start power element, after pushing down the footing of autogyro, helicopter operational person performs landing operation, and propeller quits work;
When autogyro takes off, when autogyro reaches maximum power, the fixed cell release power element of its footing surrounding, decontrol the footing of the autogyro pushed down, helicopter operational person performs takeoff operational, and autogyro flies away from region of rising and falling fast.
The present invention's beneficial effect is compared with prior art: the present invention can make autogyro when landing, and after being completely fixed, then performs last landing operation, can prevent autogyro from sliding or spring.When taking off, soon to reach take off maximum power time, then decontrol the pressuring action of fixed cell to footing, thus allow autogyro launch away fast.
Below in conjunction with the drawings and specific embodiments, the invention will be further described.
Accompanying drawing explanation
Fig. 1 is that helicopter landing of the present invention is fixed and take off the plan sketch (there is shown the footing of three autogyros) of ejection system specific embodiment;
Fig. 2 is that the present invention one helicopter landing is fixed and the side schematic view of the fixed cell in ejection system specific embodiment that takes off;
Fig. 3 is that helicopter landing of the present invention is fixed and take off the circuit block diagram of ejection system specific embodiment.
Reference numeral
10 fixed cell 11 proximity switches
12 power element 121 lift cylinders
122 depression bar 20 terrestrial radio receiver
21 fixing dot matrix operating switch 30 aircraft wireless controllers
31 input ends 32 that take off land input end
40 footing 41 contact switches
50 collective-pitch lever master cocies 51 are taken off position
52 landing positions
Detailed description of the invention
In order to more fully understand technology contents of the present invention, below in conjunction with specific embodiment technical scheme of the present invention being introduced further and illustrating, but being not limited to this.
As shown in Figure 1 to Figure 3, helicopter landing of the present invention is fixed and takes off ejection system, comprises the fixing dot matrix (namely forming a dot matrix region) be made up of several fixed cells 10, and the terrestrial radio receiver 20 be electrically connected with fixed cell 10; Terrestrial radio receiver 20 is connected with aircraft wireless controller 30 wireless telecommunications be located on autogyro; Each fixed cell 10 is provided with for judging the proximity switch 11 whether autogyro footing 40 is close, and each fixed cell 10 is provided with power element 12, and power element 12 is electrically connected by proximity switch 11 and terrestrial radio receiver 20; Aircraft wireless controller 30 is provided with take off input end 31 and landing input end 32; The input end 31 that takes off is provided with the take off signal port corresponding with the position 51 of taking off of collective-pitch lever master cock 50; Landing input end 32 is provided with corresponding with the landing position 52 of collective-pitch lever the master cock 50 and falling signal port of connecting with the contact switch 41 be located on aircraft footing.
During autogyro landing, collective-pitch lever master cock 50 is in landing position 52, aviator falls at operation autogyro, the footing of autogyro touches fixed cell, be located at contact switch 41 conducting on aircraft footing, so landing input end has signal to input, aircraft wireless controller 30 sends wireless signal to terrestrial radio receiver 20.Dot matrix operating switch 21 is fixed in terrestrial radio receiver 20 conducting, position is in the fixed cell of the footing surrounding of autogyro, close due to footing, its proximity switch 11 conducting, thus make the power element work of the fixed cell after these proximity switch conductings, footing is fixed.After being completely fixed footing, aviator can perform last operation, allows propeller stall, steadily stops.
When autogyro takes off, collective-pitch lever master cock is in position of taking off, and when reaching to maximum take-off power, then conducting is taken off the signal of input end; Aircraft wireless controller 30 sends wireless signal to terrestrial radio receiver 20.Terrestrial radio receiver 20 cuts off the signal of fixing dot matrix operating switch 21, and the fixed cell being originally in the state of being fixed discharges fixing footing fast, and autogyro launches away fast.
Wherein, in the present embodiment, fixed cell 10 is fixed leg, and fixed leg upper end is provided with the lifting mechanism that vertical direction is arranged and the switching mechanism being located at lifting mechanism upper end.Lifting mechanism is lift cylinder 121, and switching mechanism comprises the rotary cylinder (not shown) being fixed on lift cylinder 121 movable end and the depression bar 122 being fixed at rotary cylinder movable end.Time fixing, lift cylinder first rises, and rotary cylinder works again, and the footing of autogyro finally pushed down by depression bar.
Technical data in practical application:
Be suitable for sea situation (in fact theoretical value does not exist so large jolting) that the sea situation-initial acceleration that pitches is less than or equal to G contact to earth (warship) time at once 3-4 point fix respectively, make aircraft and (warship) face, ground geo-stationary.
The 150%-200% that bed knife-equal helicopter deadweight 100%-150% (that also can do is larger) ejection force-can accomplish is conducted oneself with dignity, produces the upwards acceleration/accel (overload of 1G is not problem for aviator) of 0.5G-1.0G.
Ejection altitude: 1 second and ejectable 2.-4 rice.Be provided with tail-rotor balance perception part (tail-rotor is unbalance is the greateset risk that helicopter launches).
Helicopter landing gear and collective-pitch lever do simple refit, and with native system UNICOM.
In other embodiment, also can adopt the fixed sturcture of other structure, such as electromagnetic brake formula structure, or adopt hydraulic power structure.
The landing fixing means of a kind of autogyro of the present invention, the method is taken to a few fixing dot matrix formed by fixed cell; When autogyro lands, the fixed cell of autogyro footing surrounding detects the close of footing, and start power element, after pushing down the footing of autogyro, helicopter operational person performs landing operation, and propeller quits work;
When autogyro takes off, when autogyro reaches maximum power, the fixed cell release power element of its footing surrounding, decontrol the footing of the autogyro pushed down, helicopter operational person performs takeoff operational, and autogyro flies away from region of rising and falling fast.
During owing to taking off and landing, the operation requirements for autogyro is higher, needs to have wireless telecommunications accurately again fast between the control system of autogyro and anchor fitting.
In sum, the present invention can make autogyro when landing, and after being completely fixed, then performs last landing operation, can prevent autogyro from sliding or spring.When taking off, soon to reach take off maximum power time, then decontrol the pressuring action of fixed cell to footing, thus allow autogyro launch away fast.
Above-mentionedly only further illustrate technology contents of the present invention with embodiment, so that reader is easier to understand, but does not represent embodiments of the present invention and be only limitted to this, any technology done according to the present invention extends or recreation, all by protection of the present invention.Protection scope of the present invention is as the criterion with claims.
Claims (4)
1. helicopter landing is fixed and takes off ejection system, it is characterized in that comprising the fixing dot matrix be made up of several fixed cells, and the terrestrial radio receiver be electrically connected with fixed cell; Described terrestrial radio receiver is connected with the aircraft wireless controller wireless telecommunications be located on autogyro; Each fixed cell is provided with for judging the proximity switch whether autogyro footing is close, and each fixed cell is provided with power element and is electrically connected by proximity switch and terrestrial radio receiver; Described aircraft wireless controller is provided with take off input end and landing input end; The described input end that takes off is provided with the take off signal port corresponding with the position of taking off of collective-pitch lever master cock; Described landing input end is provided with corresponding with the landing position of collective-pitch lever master cock and the falling signal port of connecting with the contact switch be located on aircraft footing.
2. helicopter landing according to claim 1 is fixed and takes off ejection system, it is characterized in that described fixed cell is fixed leg, and described fixed leg upper end is provided with the lifting mechanism that vertical direction is arranged and the switching mechanism being located at lifting mechanism upper end.
3. helicopter landing according to claim 2 is fixed and takes off ejection system, it is characterized in that described lifting mechanism is lift cylinder, described switching mechanism comprises the rotary cylinder being fixed on lift cylinder movable end and the depression bar being fixed at rotary cylinder movable end.
4. a landing fixing means for autogyro, is characterized in that the method is taken to a few fixing dot matrix formed by fixed cell; When autogyro lands, the fixed cell of autogyro footing surrounding detects the close of footing, and start power element, after pushing down the footing of autogyro, helicopter operational person performs landing operation, and propeller quits work;
When autogyro takes off, when autogyro reaches maximum power, the fixed cell release power element of its footing surrounding, decontrol the footing of the autogyro pushed down, helicopter operational person performs takeoff operational, and autogyro flies away from region of rising and falling fast.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510101232.0A CN104670517B (en) | 2015-03-09 | 2015-03-09 | Helicopter landing is fixed and takes off ejection system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510101232.0A CN104670517B (en) | 2015-03-09 | 2015-03-09 | Helicopter landing is fixed and takes off ejection system |
Publications (2)
| Publication Number | Publication Date |
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| CN104670517A true CN104670517A (en) | 2015-06-03 |
| CN104670517B CN104670517B (en) | 2019-11-15 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201510101232.0A Active CN104670517B (en) | 2015-03-09 | 2015-03-09 | Helicopter landing is fixed and takes off ejection system |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106428616A (en) * | 2016-12-08 | 2017-02-22 | 隋东昊 | Small aircraft landing assisting device |
| CN106477065A (en) * | 2016-12-12 | 2017-03-08 | 大连理工大学 | Anti- formula carrier-borne aircraft of throwing blocks rope device |
| CN107054632A (en) * | 2015-12-23 | 2017-08-18 | 克里斯琴.施米德 | Rotary-wing aircraft and the take-off and landing equipment for this rotary-wing aircraft |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4174081A (en) * | 1976-12-23 | 1979-11-13 | Messerschmitt-Boelkow-Blohm Gesellschaft Mit Beschraenkter Haftung | Apparatus for securing a flying craft to a starting and landing area |
| CN101000243A (en) * | 2007-01-16 | 2007-07-18 | 北京航空航天大学 | Pilotless plane landing navigation method and its device |
| CN101348166A (en) * | 2008-09-11 | 2009-01-21 | 杨举 | Takeoff and landing method for aircraft carrier-based aircraft and apparatus thereof |
| WO2012064891A2 (en) * | 2010-11-09 | 2012-05-18 | Colorado Seminary, Which Owns And Operates The University Of Denver | Intelligent self-leveling docking system |
| CN103332295A (en) * | 2013-06-27 | 2013-10-02 | 厦门天圣能源科技有限公司 | Novel helicopter carrier landing system |
-
2015
- 2015-03-09 CN CN201510101232.0A patent/CN104670517B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4174081A (en) * | 1976-12-23 | 1979-11-13 | Messerschmitt-Boelkow-Blohm Gesellschaft Mit Beschraenkter Haftung | Apparatus for securing a flying craft to a starting and landing area |
| CN101000243A (en) * | 2007-01-16 | 2007-07-18 | 北京航空航天大学 | Pilotless plane landing navigation method and its device |
| CN101348166A (en) * | 2008-09-11 | 2009-01-21 | 杨举 | Takeoff and landing method for aircraft carrier-based aircraft and apparatus thereof |
| WO2012064891A2 (en) * | 2010-11-09 | 2012-05-18 | Colorado Seminary, Which Owns And Operates The University Of Denver | Intelligent self-leveling docking system |
| CN103332295A (en) * | 2013-06-27 | 2013-10-02 | 厦门天圣能源科技有限公司 | Novel helicopter carrier landing system |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107054632A (en) * | 2015-12-23 | 2017-08-18 | 克里斯琴.施米德 | Rotary-wing aircraft and the take-off and landing equipment for this rotary-wing aircraft |
| CN106428616A (en) * | 2016-12-08 | 2017-02-22 | 隋东昊 | Small aircraft landing assisting device |
| CN106477065A (en) * | 2016-12-12 | 2017-03-08 | 大连理工大学 | Anti- formula carrier-borne aircraft of throwing blocks rope device |
| CN106477065B (en) * | 2016-12-12 | 2019-02-12 | 大连理工大学 | Anti- formula carrier-borne aircraft of throwing blocks rope device |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104670517B (en) | 2019-11-15 |
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