CN102417035A - Coaxial helicopter capable of controlling flying speed change completely by buttons - Google Patents
Coaxial helicopter capable of controlling flying speed change completely by buttons Download PDFInfo
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- CN102417035A CN102417035A CN2011102898186A CN201110289818A CN102417035A CN 102417035 A CN102417035 A CN 102417035A CN 2011102898186 A CN2011102898186 A CN 2011102898186A CN 201110289818 A CN201110289818 A CN 201110289818A CN 102417035 A CN102417035 A CN 102417035A
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Abstract
The invention relates to a coaxial helicopter capable of controlling flying speed change completely by buttons. The coaxial helicopter comprises a machine body (1), a tail rotor direction expansion piece (14), a flywheel gear (15) and a tail rotor distance expansion piece (21); two rotor wings are arranged on an engine output shaft in an engine cabin at the upper layer of the machine body (1) and rotate to run in reverse directions by virtue of gears, a front-back inclined expansion piece (2) and a left-right inclined expansion piece (3) are arranged on a fixing disc on a sheath of the engine output shaft, and the fixing disc is connected with an inclined movable disc; and the distance, direction and angle of the tail rotor direction expansion piece (14) are controlled by the buttons, and the lower part of the tail rotor direction expansion piece (14) is connected with a tail rotor angle rod (17) so that the distance and angle of a tail rotor (26) are switched and changed. Besides the existing coaxial rotor wing distance reversion technique, especially an original technique of randomly changing tail rotor angle as an important pushing and pulling power, the coaxial helicopter capable of controlling the flying speed change completely by the buttons, disclosed by the invention, is an ideal air transportation tool for transporting relief materials for persons in disaster area at the highest speed.
Description
(1) technical field
The present invention relates to the improvement invention of helicopter.
(2) background technology
In the prior art, social known helicopter beam riding still depends on push-and-pull and foot-operated dispatch control system, original driving technique as before fly, ground, about flight feel loaded down with trivial details.Though, having reached advanced level through the good transformation of many-sided technology, the beam riding operative technique is still leaned on push-and-pull and foot-operated dispatch control system, and this control system manufacturing process is complicated, and performance is on the low side flexibly.At present, this control system has been done good transformation, technological deficiency but flying speed remains unchanged etc.
(3) summary of the invention
In view of the defective that prior art exists, the present invention aims to provide a kind ofly to have full button switch and controls comprehensive flight, effectively improves flying speed and flexible performance, and chaufeur is felt not only easily but also happy.
The present invention accomplishes through following scheme, and a kind of full push button control conversion coaxal helicopter at full speed comprises that body, tail-rotor direction pipe expansion joint, flywheel gear, tail-rotor are apart from pipe expansion joint; Be provided with on the engine output shaft sheath on the described body be provided with on the reaction plate before and after the inclination pipe expansion joint with tilt pipe expansion joint and be connected the inclination Advance plate, stretch on the inclination Advance plate and draw the pitch dish to establish up and down pitch pipe expansion joint control bispin wing rotating disk and last pitch rotating disk and go up pitch counter-rotating dish pitch angle to mate; The movable tail-rotor angle rod of installing of described tail-rotor direction pipe expansion joint; Tail-rotor angle rod stage casing falls into and is contained on the gear wheel shaft bearing; Establish shaft gear and tail-rotor shaft gear in the middle of the gear wheel shaft bearings at both ends; The gear wheel shaft upper end is provided with tailing axle gear and the hinged operation of flywheel gear, and flywheel gear and tail-rotor angle rod front end tail-rotor direction change operation.
Described tailrotorpiston and tail-rotor mate apart from the controller angle.
Described tail-rotor matees apart from stretching pull bar pitch angle apart from pipe expansion joint and tail-rotor.
Pipe link of pitch up and down on the described bispin wing rotating disk and last pitch rotating disk (11) are stretched synchronously and are drawn pitch angle coupling.
Described flywheel gear unidirectional rotation operation.
The invention solves existing disclosed push button control flight system, but the manufacturing process more complicated.This technology is except existing co-axial rotor pitch inversion technique, and particularly the tail-rotor of the transformation at any time angle of original creation is carried the desirable aerial transportation of disaster relief supplies as pushing away and draw important motivity with the fastest speed for the disaster area people.
(4) description of drawings
The present invention has following accompanying drawing
Fig. 1 is the full push button control conversion of a present invention coaxal helicopter sectional view at full speed.
Fig. 2 is a cutaway view (Fig. 2 ratio is 5 times of Fig. 1) behind the full push button control conversion of the present invention coaxal helicopter at full speed.
(5) specific embodiment
Accompanying drawing discloses technical pattern of the present invention, and the structure accompanying drawing describes in further detail embodiment more below: comprise that body (1), tail-rotor direction pipe expansion joint (14), flywheel gear (15), tail-rotor are apart from pipe expansion joint (21); Engine output shaft in the machinery space of described body (1) upper strata is provided with two rotors up and down; A solid axle (10); Another hollow shaft (7), two rotors make two rotors along the opposite spin operation through gear, on the engine output shaft sheath reaction plate are set; Inclination pipe expansion joints (2) are with the pipe expansion joint that tilts (3) and be connected the inclination Advance plate before and after being provided with on the reaction plate; Purpose be play forwards, backwards about and balance flight effect, be provided with some on the inclination Advance plate and be movably hinged and stretch that to draw pitch dish (5), purpose be that stable stretching drawn pitch dish (5) up-down stretch active action; Stretch and draw pitch dish (5) lower edge that pitch pipe expansion joint (4) up and down is set; Pitch pipe expansion joint (4) connection is stretched and is drawn on pitch dish (5) the edge bar up and down, stretches and draws pitch dish (5) center to establish recessed dish, and recessed dish inwall is handled smooth; Recessed dish inwall is established several roller ball positions; Roller ball protrude recessed dish inwall and bispin wing rotating disk (6) movable fall into to pack into to stretch to draw rotate coupling in pitch dish (5) the central fovea dish, bispin wing rotating disk (6) central fovea dish is established Advance plate again, straight elongated slot and the up and down coupling of the recessed dish internal fixation of bispin wing rotating disk (6) post tip ball are offered in the Advance plate outer ring; Half-section is offered concave station and the hinged rotation coupling of roller ball under bispin wing rotating disk (6) outer ring; After again with bispin wing rotating disk (6) down half-section bispin wing rotating disk (6) lid load onto with screw and install and fix, bispin wing rotating disk (6) draws pitch dish (5) and Advance plate one cover movable set on hollow shaft (7) upper boss with stretching, bispin wing rotating disk (6) connect down several pitches of rotor blade root root left side stretch pull bar (8) with under the equidirectional rotation of rotor; Described solid axle (10) upper boss is slidingly connected and goes up pitch rotating disk (11); Recessed dish is established at last pitch rotating disk (11) center; Recessed dish inwall is handled smooth; Recessed dish inwall is established several roller ball positions; Roller ball protrudes recessed dish inwall and the movable upward interior running coupling of pitch rotating disk (11) central fovea dish of packing into that falls into of last pitch counter-rotating dish (12); Last pitch counter-rotating dish (12) central fovea dish is established Advance plate again; Straight elongated slot and the up and down coupling of the recessed dish internal fixation of last pitch counter-rotating dish (12) post tip ball are offered in the Advance plate outer ring, and half-section is offered the hinged running coupling of concave station and last pitch rotating disk (11) roller ball under last pitch counter-rotating dish (12) outer ring, after will go up under the pitch counter-rotating dish (12) on the half-section pitch counter-rotating dish (12) again and cover with screw and install and fix; Last pitch counter-rotating dish (12) and last pitch rotating disk (11) and Advance plate one cover movable set are on solid axle (10) upper boss and with Spring Card and fixed by nut; Last pitch rotating disk (11) be provided with some up and down pitch pipe link (9) connect bispin wing rotating disks (6), through pitch pipe link (9) up and down realize pitch rotating disk (11) and bispin wing rotating disk (6) and then down the same direction of rotor rotate, the while plays again to stretch and draws pitch dish (5) to make down the angle variation round about of rotor pitch and last rotor pitch under the stretched vertically effect up and down; In last pitch counter-rotating dish (12) connection rotor blade root root right side on several pitch stretch pull bar (13) and follow the same direction of rotor and rotate; Operation procedure is that pitch pipe expansion joint (4) is according to the pitch angle speed operation of button settings up and down, and choice direction presses the button on button, makes down rotor pitch and last rotor pitch phase reversal direction constantly change the operation of pitch angle synchronously; Described tail-rotor direction pipe expansion joint (14) rear end is movably arranged on the aircraft tail shelf; Tail-rotor direction pipe expansion joint (14) is controlled by pitch orientation angle button switch; Tail-rotor direction pipe expansion joint (14) front stretching masthead end movable button is contained on the tail-rotor angle rod (17), the design of tail-rotor angle rod (17) " U " shape, and tail-rotor angle rod (17) two side lever stage casings are provided with bear box and fall into and are contained on two bearings in gear wheel shaft (18) stage casing; Covering the bear box cover-use screw then installs and fixes; Gear wheel shaft (18) two ends are provided with bearing, establish shaft gear (19) in the middle of gear wheel shaft (18) bearings at both ends again, and gear wheel shaft (19) bearings at both ends falls into to be contained in tail tail-rotor (26) the circle ring upper and lower sides bear box and installs and fixes with screw; Gear wheel shaft (19) upper end is provided with tailing axle gear (16); Tailing axle gear (16) and the hinged operation of flywheel gear (15), flywheel gear (15) are limited to single transhipment row, and the direction commentaries on classics belongs to idle running in addition; Purpose is to cooperate tail-rotor (26) the slave afterbody side of tail-rotor angle rod (17) front end to adjust to tail to rectify the back power-assisted and promote helicopter and advance fast; Tail-rotor (26) returns original drive end unit side from the positive back of machine tail end again and helps the pulling force operation, but under flywheel gear (15) neutral rotary action, makes tail-rotor (26) from 90 ° of clog-free repeatedly angle; The hinged tail-rotor shaft gear of described shaft gear (19) (20); Tail-rotor shaft gear (20) is arranged on both tail-rotor (26) shaft rear ends of tail-rotor angle rod (17) front end inboard; Tail-rotor angle rod (17) front end frame respectively is provided with bear box with the protrusion position, falls into the bearing on dress tail-rotor (26) axle then, covers bear box and covers and fix with screw; Tail-rotor angle rod (17) front end frame protuberance position connects hog frame (25) again; Bearing is set at hog frame (25) two ends and sunken tail tail-rotor (26) the circle ring that is contained in upward installs and fixes with screw in the bear box of lower edge, and hog frame (25) and tail-rotor angle rod (17) are synchronous to rotate, and purpose is to improve the normal operation of stablizing tail-rotor (26); Tail-rotor is set on described tail-rotor (26) axle to be stretched and draws dish (22); Tail-rotor is stretched and is drawn dish (22) center to establish recessed dish; Recessed dish inwall is handled smooth; Recessed dish inwall is established several roller ball positions; Roller ball protrudes the movable tail-rotor of packing into that falls into of recessed dish inwall and tail-rotor rotating disk (23) to be stretched and drawing running coupling in dish (22) the central fovea dish, tail-rotor rotating disk (23) to connect several tail-rotors of tail-rotor (26) blade root root apart from stretching pull bar (24) and following the rotation of tail-rotor direction of principal axis, and tail-rotor rotating disk (23) central fovea dish is established Advance plate again; Straight elongated slot and the up and down coupling of the recessed dish internal fixation of tail-rotor rotating disk (23) post tip ball are offered in the Advance plate outer ring; Half-section is offered concave station and tail-rotor and is stretched and draw the hinged running coupling of dish (22) roller ball under tail-rotor rotating disk (23) outer ring, after again with tail-rotor rotating disk (23) down half-section cover with screw and install and fix, tail-rotor rotating disk (23) and tail-rotor are stretched and are drawn dish (22) and Advance plate one to overlap movable set on tail-rotor (26) axle and with Spring Card and fixed by nut; Tail-rotor is stretched to draw and is connected tail-rotor on dish (22) edge bars apart from controller (21) expansion link, and tail-rotor connects tail-rotor angle rod (17) front-end control tail-rotor (26) pitch to be changed apart from controller (21) bottom.
Claims (5)
1. a full push button control conversion coaxal helicopter at full speed comprises that body (1), tail-rotor direction pipe expansion joint (14), flywheel gear (15), tail-rotor apart from pipe expansion joint (21), is characterized in that; Described body (1) go up be provided with on the engine output shaft sheath be provided with on the reaction plate before and after inclination pipe expansion joints (2) with the pipe expansion joint that tilts (3) and be connected the inclination Advance plate, stretch on the inclination Advance plate draw pitch dish (5) establish up and down pitch pipe expansion joint (4) control bispin wing rotating disk (6) and last pitch rotating disk (11) and upward pitch counter-rotating dish (12) pitch angle mate; The movable tail-rotor angle rod (17) of installing of described tail-rotor direction pipe expansion joint (14); Tail-rotor angle rod (17) stage casing falls into and is contained on gear wheel shaft (18) bearing; Establish shaft gear (19) and tail-rotor shaft gear (20) in the middle of gear wheel shaft (18) bearings at both ends; Gear wheel shaft (18) upper end is provided with tailing axle gear (16) and the hinged operation of flywheel gear (15), and flywheel gear (15) changes operation with tail-rotor angle rod (17) front end tail-rotor (26) direction.
2. a kind of full push button control conversion as claimed in claim 1 coaxal helicopter at full speed is characterized in that; Described tail-rotor (26) pitch and tail-rotor mate apart from controller (21) angle.
3. a kind of full push button control conversion as claimed in claim 1 coaxal helicopter at full speed is characterized in that; Described tail-rotor matees apart from stretching pull bar (24) pitch angle apart from pipe expansion joint (21) and tail-rotor.
4. a kind of full push button control conversion as claimed in claim 1 coaxal helicopter at full speed is characterized in that; The pipe link of pitch up and down (9) on the described bispin wing rotating disk (6) is stretched synchronously with last pitch rotating disk (11) and is drawn pitch angle coupling.Moving operation.
5. a kind of full push button control conversion as claimed in claim 1 coaxal helicopter at full speed is characterized in that; The unidirectional commentaries on classics of described flywheel gear (15).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011102898186A CN102417035A (en) | 2011-09-17 | 2011-09-17 | Coaxial helicopter capable of controlling flying speed change completely by buttons |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011102898186A CN102417035A (en) | 2011-09-17 | 2011-09-17 | Coaxial helicopter capable of controlling flying speed change completely by buttons |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102417035A true CN102417035A (en) | 2012-04-18 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011102898186A Pending CN102417035A (en) | 2011-09-17 | 2011-09-17 | Coaxial helicopter capable of controlling flying speed change completely by buttons |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102417035A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103072689A (en) * | 2013-01-28 | 2013-05-01 | 黄春水 | Low-rotating-speed double-layer propcopter |
| CN103832584A (en) * | 2012-11-26 | 2014-06-04 | 罗勇 | Contra-rotating rotor wing airplane with stationary wings and foldable empennage |
| CN104401482A (en) * | 2014-10-28 | 2015-03-11 | 燕山大学 | Fully-differential coaxial helicopter operating mechanism |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2207997Y (en) * | 1993-09-04 | 1995-09-20 | 许静峰 | Single helicopter |
| CN1384019A (en) * | 2001-05-08 | 2002-12-11 | 赵润生 | Airplane with multi-point deflecting wings |
| CN1857965A (en) * | 2006-05-18 | 2006-11-08 | 胡俊峰 | Rotor shaft controllable tilting coaxial rotor wing helicopter |
| US20090084891A1 (en) * | 2005-05-26 | 2009-04-02 | Darrow Jr David A | De-rotation system suitable for use with a shaft fairing system |
| CN101423117A (en) * | 2008-12-05 | 2009-05-06 | 北京航空航天大学 | Tilt-rotor plane operated and propelled by thrust scull and slipstream rudder |
-
2011
- 2011-09-17 CN CN2011102898186A patent/CN102417035A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2207997Y (en) * | 1993-09-04 | 1995-09-20 | 许静峰 | Single helicopter |
| CN1384019A (en) * | 2001-05-08 | 2002-12-11 | 赵润生 | Airplane with multi-point deflecting wings |
| US20090084891A1 (en) * | 2005-05-26 | 2009-04-02 | Darrow Jr David A | De-rotation system suitable for use with a shaft fairing system |
| CN1857965A (en) * | 2006-05-18 | 2006-11-08 | 胡俊峰 | Rotor shaft controllable tilting coaxial rotor wing helicopter |
| CN101423117A (en) * | 2008-12-05 | 2009-05-06 | 北京航空航天大学 | Tilt-rotor plane operated and propelled by thrust scull and slipstream rudder |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103832584A (en) * | 2012-11-26 | 2014-06-04 | 罗勇 | Contra-rotating rotor wing airplane with stationary wings and foldable empennage |
| CN103072689A (en) * | 2013-01-28 | 2013-05-01 | 黄春水 | Low-rotating-speed double-layer propcopter |
| CN103072689B (en) * | 2013-01-28 | 2016-04-13 | 黄春水 | Slow speed of revolution double-layer propeller helicopter |
| CN104401482A (en) * | 2014-10-28 | 2015-03-11 | 燕山大学 | Fully-differential coaxial helicopter operating mechanism |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20120418 |