CN101723091A - Rotor wing pitch change control device of heligyro - Google Patents
Rotor wing pitch change control device of heligyro Download PDFInfo
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- CN101723091A CN101723091A CN200910191939A CN200910191939A CN101723091A CN 101723091 A CN101723091 A CN 101723091A CN 200910191939 A CN200910191939 A CN 200910191939A CN 200910191939 A CN200910191939 A CN 200910191939A CN 101723091 A CN101723091 A CN 101723091A
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Abstract
The invention relates to a rotor wing pitch change control device of a heligyro. A total propeller pitch sliding bush is arranged in a cavity of a main shaft supporting seat and is connected with a total propeller pitch control mechanism; a main control rod for controlling cyclic pitch changes is in clearance fit in a ball socket of the total propeller pitch sliding bush through a ball head; a synchronous control arm for controlling attack angle changes of a rotor wing is rotatablely connected on the upper part of the main control rod; the lower end of the main control rod is connected with a cyclic pitch change control mechanism; a propeller hub is rotatablely sleeved outside the main shaft supporting seat; a propeller hub torque transfer device is connected with the synchronous control arm for controlling the attack angle changes of the rotor wing; the rotor wing is arranged on the propeller hub and is connected with the synchronous control arm for controlling the attack angle changes of the rotor wing; and the circumference of the lower part of the propeller hub is provided with circumferential teeth meshed with an output gear of a gearbox. The rotor wing pitch change control device uses the propeller hub as a main shaft to shorten the axial distance between rotor wing pitch gearboxes and reduce the bearing stress of the main shaft, can reduce the manufacturing difficulty and the cost, and simultaneously is favorable for the centralized lubrication of moving parts to reduce the lubrication cost.
Description
Technical field
The present invention relates to the heligyro field, particularly a kind of rotary wing changing distance control apparatus of heligyro.
Background technology
Heligyro is in the pitching and the heeling attitude in when flight, is that mode by feathering changes the angle of attack of rotor when different angles and realizes that the lifting control during flight is to be realized by the angle of attack of total pitch control rotor.The control setup of traditional lifting airscrew change in angle of attack comprises rotor, the mast bar, total pitch sliding sleeve, toggle, tilting frame, pull bar, gear case, mast bar lower end is stretched in the gear case with gear cluster in the gear case and is connected, the mast upper end is the captive joint propeller hub circumferentially, rotor is installed on the propeller hub, total pitch sliding sleeve is enclosed within on the mast, tilting to circle or whirl in the air to be enclosed within total pitch sliding sleeve is connected with total pitch sliding sleeve by a plurality of universal-joint connecting rods outward, tilting frame is between rotor and gear case, tilting frame upper end is connected by the toggle that is provided with on pull bar and each rotor respectively, the tilting frame lower end connects steering unit by control link, the lifting of helicopter and pitching, the control of heeling attitude comes transmitting control by tilting frame.The control setup complex structure of this structure, especially tilting frame is located between rotor and gear case outside total pitch sliding sleeve, the tilting frame upper end connects the toggle of rotor by pull bar, the lower end connects steering unit by control link, taken bigger axial space distance thus, make rotor far away apart from the distance between the gear case, cause the axial length of mast longer, and the bearing of the support mast of gear case can only cooperate with mast at the hypomere of mast again, main shaft is long more, and rocking during its rotation is just big more, and the stress that is born is also just big more, the manufacturing materials of main shaft and processing are all required very high, cause cost of manufacture very high.And the linear velocity of tilting frame running is very high, its lubricated requirement is also high, but because of tilting frame is being positioned between rotor and the gear case, tilting frame radially is again to be connected with total pitch sliding sleeve by the universal-joint connecting rod, the upper end of tilting frame is to be connected with toggle on each rotor by pull bar, the tilting frame lower end is to connect steering unit by control link, this just causes the lubricating system of tilting frame can't be shared with gear case, special lubricating system must be set solve the lubricated separately of tilting frame, its manufacturing cost and lubricated cost also all increase.Be the stability of assurance device motion simultaneously, cause this device design redundant big, helicopter is unfavorable for the riding manipulation of helicopter because of mule carries the demand increase that effect causes handling strength on the back.
Summary of the invention
The objective of the invention is deficiency at the prior art existence, a kind of rotary wing changing distance control apparatus of heligyro is provided, it is with the double main shaft of doing of propeller hub, rotor is shortened apart from the axial distance between the change speed gear box, strengthen main axe intensity, reduce meeting with stresses of main shaft, and saved tilting frame, can reduce manufacture difficulty and cost-cutting, help the central oiling of movement parts simultaneously, reduce lubricated expense.
The object of the present invention is achieved like this: comprise rotor, total pitch sliding sleeve, described total pitch sliding sleeve is located in the chamber of a main shaft support seat, the top, chamber of main shaft support seat is the guiding straight hole, the bottom is tubaeform taper hole, total pitch sliding sleeve top is the right cylinder section, the intersegmental crack of this right cylinder is engaged in the guiding straight hole of main shaft support seat, total pitch sliding sleeve bottom is oblique extension along the tubaeform taper hole surface of main shaft support seat bottom, be used to connect total pitch-control mechanism, one master-control lever that is used for the control cycle displacement passes from total pitch sliding sleeve, the stage casing of this master-control lever is provided with the bulb that is used for fulcrum, in the ball-and-socket that this bulb free-running fit is provided with in total pitch sliding sleeve right cylinder section, total pitch sliding sleeve is stretched out on master-control lever top, be used to control the rotating master-control lever top that is connected of synchro control arm of rotor change in angle of attack, the master-control lever lower end is used to connect cyclic pitch control mechanism, one propeller hub is rotating to be enclosed within outside the main shaft support seat, propeller hub is connected with the synchro control arm that is used to control the rotor change in angle of attack by a torque transfer, the uniform propeller hub top that is installed in of a plurality of rotors, the pivoted arm that each rotor is installed is connected with the synchro control arm that is used to control the rotor change in angle of attack by pull bar respectively, the propeller hub lower circumference is provided with circumferential teeth, is used for the output gear engagement with change speed gear box.
Described propeller hub comprises sleeve-type main shaft, upper cover plate, described sleeve-type main shaft top is provided with the radially extension arm that is used to install rotor, each radially fixedly installs rotor installation axle sleeve on the extension arm, sleeve-type main shaft lower circumference is provided with circumferential teeth, upper cover plate be provided with the sleeve-type main shaft on be used to install the cooresponding radially extension arm of radially extension arm of rotor, after upper cover plate is fixedly connected on the sleeve-type main shaft, the root axostylus axostyle of rotor is inserted rotor axle sleeve is installed is installed in radially extension arm and radially between the extension arm of upper cover plate on the sleeve-type main shaft.
Described sleeve-type main shaft bottom is tubaeform, and axle center, sleeve-type main shaft top is provided with taper hole, and this taper hole is communicated with the formation axis hole with bellmouth orifice, circumferential teeth is set in the portion that outwards turns back of sleeve-type main shaft lower end constitutes reaction gear.
Between the cone bush that is threaded on the taper hole on described sleeve-type main shaft top and the main shaft support seat needle bearing is set, between the bellmouth orifice of sleeve-type main shaft bottom and the main shaft support seat needle bearing is set.
The described synchro control arm that is used to control the rotor change in angle of attack has the cantilever identical with rotor quantity, and these cantilevers are distributed on the axes sleeve, and axes sleeve cooperates with the master-control lever that is used for the control cycle displacement by bearing.
Described torque transfer comprises permanent seat, yoke and connecting arm, permanent seat is eccentrically set on the propeller hub, yoke is stuck in the axes sleeve of the synchro control arm that is used to control the rotor change in angle of attack, captive joint by bearing pin and axes sleeve are circumferential, and form hinged, connecting arm is connected between permanent seat and the yoke, and the two ends of connecting arm are hinged with yoke, permanent seat respectively.
Described pivoted arm one end is captiveed joint with the root axostylus axostyle of rotor, and the other end and the pull bar of pivoted arm are hinged, and pull bar is hinged with the synchro control arm that is used to control the rotor change in angle of attack.
Described total pitch-control mechanism is the total pitch control stalk that is connected with two shift forks, and two shift forks are hinged with total pitch sliding sleeve respectively.
Described cyclic pitch control mechanism comprises first control stalk and second control stalk, first control stalk passes through hinged with the master-control lever lower end that is used for the control cycle displacement, second control stalk is vertical with first control stalk from horizontal direction, be connected with first control stalk by universal-joint, and near first control stalk and the hinged place that is used for the master-control lever of control cycle displacement.
The lower part of described main shaft support seat is positioned at the change speed gear box that is fixed on the fuselage.
Owing to adopt such scheme, the rotary wing changing distance control apparatus of heligyro of the present invention had the following advantages:
1. total pitch sliding sleeve is located in the chamber of a main shaft support seat, total pitch sliding sleeve lower end is used to connect total pitch-control mechanism.One master-control lever that is used for the control cycle displacement passes from total pitch sliding sleeve, the stage casing of this master-control lever is provided with the ball-and-socket free-running fit that the bulb that is used for fulcrum and total pitch sliding sleeve are provided with, the synchro control arm that the rotating connection of total pitch sliding sleeve is used to control the rotor change in angle of attack is stretched out on master-control lever top, and the master-control lever lower end is used to connect cyclic pitch control mechanism.Can slide over to slide up and down in the post supporting seat by total pitch like this and drive the master-control lever lifting that is used for the control cycle displacement, the dipping and heaving of control helicopter, tilt to different directions by the master-control lever that is used for the control cycle displacement, the synchro control arm that control is used to control the rotor change in angle of attack drives each rotor and realizes change in angle of attack synchronously, finishes the pitching and the heeling of helicopter.Adopt the total pitch sliding sleeve of this structure and the lifting, pitching and the heeling that are used for the master-control lever combination control helicopter of control cycle displacement, compare with existing tilting frame control setup, structure is compact more, control is stable more, flexible, owing to do not adopt the tilting frame control setup, rotor is shortened apart from the axial distance between the change speed gear box, strengthen main axe intensity, reduce meeting with stresses of main shaft.
2. be enclosed within outside the main shaft support seat propeller hub is rotating, propeller hub is connected with the synchro control arm that is used to control the rotor change in angle of attack by a torque transfer, the uniform propeller hub top that is installed in of a plurality of rotors, the pivoted arm that each rotor is installed is connected with the synchro control arm that is used to control the rotor change in angle of attack by pull bar respectively, the propeller hub lower circumference is provided with circumferential teeth, is used for the output gear engagement with change speed gear box.Like this with the main shaft support seat as dead axle, propeller hub rotates around the main shaft support seat as S. A., propeller hub is subjected to the direct drive of change speed gear box output gear, compare with the main shaft of existing helicopter, this possess S. A. simultaneously and the propeller hub of rotor function be installed, and its diameter obtains increasing, length obtains shortening, rotation is rocked and can be reduced to minimum, even eliminates, and stability of rotation and stress bearing strength all are enhanced.
3. described propeller hub comprises sleeve-type main shaft, upper cover plate, sleeve-type main shaft bottom is tubaeform, axle center, sleeve-type main shaft top is provided with taper hole, between the cone bush that is threaded on the taper hole on its top and the main shaft support seat needle bearing is set, between the bellmouth orifice of bottom and the main shaft support seat needle bearing is set.Make propeller hub can prevent end float misalignment again like this, guarantee the control accuracy of helicopter around the rotation of main shaft support seat; The installation of rotor is also easy and convenient simultaneously.
4. described torque transfer comprises permanent seat, yoke and connecting arm, permanent seat is eccentrically set on the propeller hub, yoke is stuck in the axes sleeve of the synchro control arm that is used to control the rotor change in angle of attack, captive joint by bearing pin and axes sleeve are circumferential, and form hinged, connecting arm is connected between permanent seat and the yoke, and the two ends of connecting arm are hinged with yoke, permanent seat respectively.Can drive the synchro control arm be used to control the rotor change in angle of attack by torque transfer like this rotates synchronously with propeller hub, fork can guarantee be used to control the synchro control arm of rotor change in angle of attack with the master-control lever lifting that is used for the control cycle displacement, inclination the time, the yoke of torque transfer and connecting arm can pass through the hinge activity, and the transmission of torsion can not interfered.
5. be located at total pitch sliding sleeve owing to be used for the master-control lever of control cycle displacement, total pitch sliding sleeve is located in the chamber of main shaft support seat, the outside of main shaft support seat cooperates propeller hub by bearing, make the compact conformation of this rotary wing changing distance control apparatus like this, the point that each parts matching part need lubricate is concentrated relatively, and main shaft support seat part is located in the change speed gear box, can utilize the lubricating system of change speed gear box that it is lubricated, and can save manufacturing cost and the lubricated funds of establishing independent lubricating system in addition.
Compact conformation of the present invention is simple, is applicable to the helicopter and the model helicopter of single rotor structure.
The invention will be further described below in conjunction with drawings and Examples.
Description of drawings
Fig. 1 is a structural representation of the present invention;
Fig. 2 is the partial schematic diagram on top of the present invention;
Fig. 3 is the partial schematic diagram of bottom of the present invention.
In the accompanying drawing, 1 is rotor, and 2 is total pitch sliding sleeve, 2a is a leg, and 3 is the main shaft support seat, and 3a is a cone bush, 4 is total pitch-control mechanism, and 4a is total pitch control stalk, and 4b is a shift fork, 5 is master-control lever, and 6 is bulb, and 7 is the synchro control arm, 7a is a cantilever, and 7b is an axes sleeve, and 8 is bearing, 9 are cyclic pitch control mechanism, and 9a is first control stalk, and 9b is second control stalk, 10 is propeller hub, and 10a is the sleeve-type main shaft, and 10b is extension arm radially, 10c is the portion of turning back, and 11 is torque transfer, and 11a is a permanent seat, 11b is a yoke, and 11c is a connecting arm, and 12 is upper cover plate, 13 are rotor installation axle sleeve, and 14 is circumferential teeth, and 15 is pivoted arm, 16 is pull bar, and 17 is shaft alignment spare, and 19 is change speed gear box, 20 is output gear, and 21 is needle bearing.
The specific embodiment
Referring to Fig. 1 to Fig. 3, a kind of embodiment of the rotary wing changing distance control apparatus of heligyro, this rotary wing changing distance control apparatus comprise rotor 1, total pitch sliding sleeve 2, main shaft support seat 3, the master-control lever 5 that is used for the control cycle displacement, propeller hub 10, be used to control the synchro control arm 7 of rotor change in angle of attack etc.Described total pitch sliding sleeve 2 is located in the chamber of a main shaft support seat 3, and the lower part of main shaft support seat 3 is positioned at the change speed gear box 19 that is fixed on the fuselage.The top, chamber of main shaft support seat 3 is the guiding straight hole, the bottom is tubaeform taper hole, total pitch sliding sleeve 2 tops are the right cylinder section, the intersegmental crack of this right cylinder is engaged in the guiding straight hole of main shaft support seat 3, total pitch sliding sleeve 2 bottoms are oblique extension along the tubaeform taper hole surface of main shaft support seat 3 bottoms, for reducing occupied space, the part of this oblique extension can be arranged to the leg 2a of two symmetries, is used to connect total pitch-control mechanism 4.Described total pitch-control mechanism 4 is for being connected with total pitch control stalk 4a of two shift fork 4b, two shift fork 4b are hinged with two leg 2a of total pitch sliding sleeve 2 respectively, two shift fork 4b are fixed on total pitch control stalk 4a, rotate total pitch control stalk 4a and can drive total pitch sliding sleeve 2 by shift fork 4b and carry out dipping and heaving.One master-control lever 5 that is used for the control cycle displacement passes from total pitch sliding sleeve 2, the stage casing of this master-control lever 5 is provided with the bulb 6 that is used for fulcrum, bulb 6 is captiveed joint with master-control lever 5, it is fastening to adopt interference fit or screw thread fit to connect, in the ball-and-socket that these bulb 6 free-running fits are provided with in total pitch sliding sleeve 2 right cylinder sections.Total pitch sliding sleeve 2 is stretched out on master-control lever 5 tops, be used to control synchro control arm 7 rotating master-control lever 5 tops that are connected of rotor change in angle of attack, the described synchro control arm 7 that is used to control the rotor change in angle of attack has the cantilever 7a identical with rotor quantity, these cantilevers 7a is distributed on the axes sleeve 7b, axes sleeve 7b cooperates with the master-control lever 5 that is used for the control cycle displacement by bearing 8, described master-control lever 5 lower ends are used to connect cyclic pitch control mechanism 9, this cyclic pitch control mechanism 9 comprises the first control stalk 9a and the second control stalk 9b, the first control stalk 9a is hinged by universal-joint with master-control lever 5 lower ends that are used for the control cycle displacement, the second control stalk 9b is vertical with the first control stalk 9a from horizontal direction, be connected with the first control stalk 9a by universal-joint, and near first control stalk and the hinged place that is used for the master-control lever of control cycle displacement.One propeller hub, 10 rotating being enclosed within outside the main shaft support seat 3, propeller hub 10 is connected with the synchro control arm 7 that is used to control the rotor change in angle of attack by a torque transfer 11,2～9 rotor 1 uniform propeller hub 10 tops that are installed in, present embodiment adopts 5 rotors, propeller hub 10 lower circumference are provided with circumferential teeth 14, are used for output gear 20 engagements with change speed gear box 19.Described propeller hub 10 comprises sleeve-type main shaft 10a, upper cover plate 12, described sleeve-type main shaft 10a bottom is tubaeform, axle center, sleeve-type main shaft 10a top is provided with taper hole, this taper hole is communicated with the formation axis hole with bellmouth orifice, circumferential teeth 14 is set on the 10c of the portion that outwards turns back of sleeve-type main shaft 10a lower end constitutes reaction gears.Between the cone bush 3a that is threaded on the taper hole of described sleeve-type main shaft top 10a and the main shaft support seat 3 needle bearing 21 is set, between the bellmouth orifice of sleeve-type main shaft 10a bottom and the main shaft support seat 3 needle bearing is set, after can making propeller hub 10 like this and main shaft support seat 3 cooperating by bearing formation rolling, form axial limiting, prevent that propeller hub 10 from producing end float misalignment when rotated.Described sleeve-type main shaft 10a top is provided with the radially extension arm 10b that is used to install rotor, each radially fixedly installs rotor installation axle sleeve 13 on the extension arm 10b, sleeve-type main shaft 10a lower circumference is provided with circumferential teeth 14, upper cover plate 12 be provided with the sleeve-type main shaft on the cooresponding radially extension arm of radially extension arm 10b that is used to install rotor, after upper cover plate 12 is connected on the sleeve-type main shaft 10a by riveted joint or bolt, the root axostylus axostyle of rotor 1 is inserted rotor axle sleeve 13 is installed is installed in radially between the extension arm of radially extension arm on the sleeve-type main shaft 10a and upper cover plate 12, the pivoted arm 15 that each rotor 1 is installed is connected with the synchro control arm 7 that is used to control the rotor change in angle of attack by pull bar 16 respectively.Described pivoted arm 15 1 ends are connected with the root axostylus axostyle spline of rotor 1, and with shaft alignment spare 17 shaft alignments, shaft alignment spare 17 can adopt nut in the fastening location of axle head, also can adopt the alignment pin location, perhaps pivoted arm 15 1 ends also can adopt locating dowel pin to captive joint with the root axostylus axostyle of rotor 1, form circumferential axial restraint, the other end of pivoted arm 15 and pull bar 16 are hinged, and pull bar 16 is hinged with the cantilever 7a of the synchro control arm 7 that is used to control the rotor change in angle of attack.Described torque transfer 11 comprises permanent seat 11a, yoke 11b and connecting arm 11c, permanent seat 11a is eccentrically set on the upper cover plate 12 of propeller hub 10, adopt welding or riveted and fixed, yoke 11b is stuck in the axes sleeve 7a of the synchro control arm 7 that is used to control the rotor change in angle of attack, captive joint with axes sleeve 7a is circumferential by bearing pin, and form hingedly, and connecting arm 11c is connected between permanent seat 11a and the yoke 11b, and the two ends of connecting arm 11c are hinged with yoke 11b, permanent seat 11a respectively.
This device drives the propeller hub rotation by the output gear of change speed gear box, propeller hub drives the rotor rotation and drives helicopter flight, propeller hub drives the synchro control arm be used to control the rotor change in angle of attack by torque transfer simultaneously and rotates synchronously with propeller hub, controlling total pitch-control mechanism by operating control slides in the main shaft support seat total pitch to move up and down, drive is used for the master-control lever lifting of control cycle displacement, makes helicopter realize lifting flight by the change in angle of attack of the synchro control arm control rotor that is used to control the rotor change in angle of attack; The master-control lever that is used in the control cycle displacement by operating control control cycle pitch control mechanism tilts, and drive is used to control the synchro control arm inclination of rotor change in angle of attack, and drive each rotor and form relative change in angle of attack, make helicopter realize pitching and heeling attitude.
Claims (10)
1. the rotary wing changing distance control apparatus of a heligyro, comprise rotor, total pitch sliding sleeve, it is characterized in that: described total pitch sliding sleeve is located in the chamber of a main shaft support seat, the top, chamber of main shaft support seat is the guiding straight hole, the bottom is tubaeform taper hole, total pitch sliding sleeve top is the right cylinder section, the intersegmental crack of this right cylinder is engaged in the guiding straight hole of main shaft support seat, total pitch sliding sleeve bottom is oblique extension along the tubaeform taper hole surface of main shaft support seat bottom, be used to connect total pitch-control mechanism, one master-control lever that is used for the control cycle displacement passes from total pitch sliding sleeve, the stage casing of this master-control lever is provided with the bulb that is used for fulcrum, in the ball-and-socket that this bulb free-running fit is provided with in total pitch sliding sleeve right cylinder section, total pitch sliding sleeve is stretched out on master-control lever top, be used to control the rotating master-control lever top that is connected of synchro control arm of rotor change in angle of attack, the master-control lever lower end is used to connect cyclic pitch control mechanism, one propeller hub is rotating to be enclosed within outside the main shaft support seat, propeller hub is connected with the synchro control arm that is used to control the rotor change in angle of attack by a torque transfer, the uniform propeller hub top that is installed in of a plurality of rotors, the pivoted arm that each rotor is installed is connected with the synchro control arm that is used to control the rotor change in angle of attack by pull bar respectively, the propeller hub lower circumference is provided with circumferential teeth, is used for the output gear engagement with change speed gear box.
2. the rotary wing changing distance control apparatus of heligyro according to claim 1, it is characterized in that: described propeller hub comprises the sleeve-type main shaft, upper cover plate, described sleeve-type main shaft top is provided with the radially extension arm that is used to install rotor, each radially fixedly installs rotor installation axle sleeve on the extension arm, sleeve-type main shaft lower circumference is provided with circumferential teeth, upper cover plate be provided with the sleeve-type main shaft on be used to install the cooresponding radially extension arm of radially extension arm of rotor, after upper cover plate is fixedly connected on the sleeve-type main shaft, the root axostylus axostyle of rotor is inserted rotor axle sleeve is installed is installed in radially extension arm and radially between the extension arm of upper cover plate on the sleeve-type main shaft.
3. the rotary wing changing distance control apparatus of heligyro according to claim 2, it is characterized in that: described sleeve-type main shaft bottom is tubaeform, axle center, sleeve-type main shaft top is provided with taper hole, this taper hole is communicated with the formation axis hole with bellmouth orifice, circumferential teeth is set in the portion that outwards turns back of sleeve-type main shaft lower end constitutes reaction gear.
4. the rotary wing changing distance control apparatus of heligyro according to claim 3, it is characterized in that: between the cone bush that is threaded on the taper hole on described sleeve-type main shaft top and the main shaft support seat needle bearing is set, between the bellmouth orifice of sleeve-type main shaft bottom and the main shaft support seat needle bearing is set.
5. the rotary wing changing distance control apparatus of heligyro according to claim 1, it is characterized in that: the described synchro control arm that is used to control the rotor change in angle of attack has the cantilever identical with rotor quantity, these cantilevers are distributed on the axes sleeve, and axes sleeve cooperates with the master-control lever that is used for the control cycle displacement by bearing.
6. the rotary wing changing distance control apparatus of heligyro according to claim 1, it is characterized in that: described torque transfer comprises permanent seat, yoke and connecting arm, permanent seat is eccentrically set on the propeller hub, yoke is stuck in the axes sleeve of the synchro control arm that is used to control the rotor change in angle of attack, captive joint by bearing pin and axes sleeve are circumferential, and form hingedly, and connecting arm is connected between permanent seat and the yoke, and the two ends of connecting arm are hinged with yoke, permanent seat respectively.
7. the rotary wing changing distance control apparatus of heligyro according to claim 1, it is characterized in that: described pivoted arm one end is captiveed joint with the root axostylus axostyle of rotor, the other end and the pull bar of pivoted arm are hinged, and pull bar is hinged with the synchro control arm that is used to control the rotor change in angle of attack.
8. the rotary wing changing distance control apparatus of heligyro according to claim 1, it is characterized in that: described total pitch-control mechanism is the total pitch control stalk that is connected with two shift forks, two shift forks are hinged with total pitch sliding sleeve respectively.
9. the rotary wing changing distance control apparatus of heligyro according to claim 1, it is characterized in that: described cyclic pitch control mechanism comprises first control stalk and second control stalk, first control stalk is hinged with the master-control lever lower end that is used for the control cycle displacement, second control stalk is vertical with first control stalk from horizontal direction, be connected with first control stalk by universal-joint, and near first control stalk and the hinged place that is used for the master-control lever of control cycle displacement.
10. the rotary wing changing distance control apparatus of heligyro according to claim 1, it is characterized in that: the lower part of described main shaft support seat is positioned at the change speed gear box that is fixed on the fuselage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200910191939XA CN101723091B (en) | 2009-12-16 | 2009-12-16 | Rotor wing pitch change control device of heligyro |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200910191939XA CN101723091B (en) | 2009-12-16 | 2009-12-16 | Rotor wing pitch change control device of heligyro |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101723091A true CN101723091A (en) | 2010-06-09 |
| CN101723091B CN101723091B (en) | 2012-04-18 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200910191939XA Expired - Fee Related CN101723091B (en) | 2009-12-16 | 2009-12-16 | Rotor wing pitch change control device of heligyro |
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Cited By (10)
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| CN101961559A (en) * | 2010-10-21 | 2011-02-02 | 哈尔滨工程大学 | Rotor wing supporting device of model helicopter |
| CN102663195A (en) * | 2012-04-17 | 2012-09-12 | 北京航空航天大学 | Design method for reducing vibration and dynamic stress level of rotor blade |
| CN102658865A (en) * | 2012-05-17 | 2012-09-12 | 李游 | Coaxial drive and control structure for coaxial contrarotation rotor helicopter |
| CN103482063A (en) * | 2013-09-29 | 2014-01-01 | 中国航空动力机械研究所 | Supporting structure of propeller pitch operating lever |
| CN106516105A (en) * | 2016-11-08 | 2017-03-22 | 瀚伦贝尔通用航空器有限公司 | Aircraft propeller surface regulating mechanism |
| CN107719661A (en) * | 2017-11-08 | 2018-02-23 | 沈阳旋飞航空技术有限公司 | A kind of unmanned plane rotor pulp distance varying mechanism |
| WO2018095042A1 (en) * | 2016-11-25 | 2018-05-31 | 深圳光启空间技术有限公司 | Variable blade pitch transmission mechanism |
| CN108116674A (en) * | 2016-11-30 | 2018-06-05 | 空客直升机 | Control member, rotor craft and method |
| CN109533304A (en) * | 2018-10-19 | 2019-03-29 | 上海交通大学 | Have both rotor, fixed-wing offline mode single machine rotor aircraft and mode switching method |
| CN112601698A (en) * | 2018-09-04 | 2021-04-02 | 赛峰电子与防务公司 | Device for controlling the flight of an aircraft |
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| US4245801A (en) * | 1979-02-15 | 1981-01-20 | United Technologies Corporation | Tail rotor control cable-pylon fold accommodation |
| CN2324062Y (en) * | 1998-03-26 | 1999-06-16 | 李应奇 | Improved rotorcraft |
| CN101804863A (en) * | 2010-05-04 | 2010-08-18 | 刘辉 | Rotor wing helicopter |
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- 2009-12-16 CN CN200910191939XA patent/CN101723091B/en not_active Expired - Fee Related
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN101961559A (en) * | 2010-10-21 | 2011-02-02 | 哈尔滨工程大学 | Rotor wing supporting device of model helicopter |
| CN101961559B (en) * | 2010-10-21 | 2012-02-01 | 哈尔滨工程大学 | Rotor wing supporting device of model helicopter |
| CN102663195A (en) * | 2012-04-17 | 2012-09-12 | 北京航空航天大学 | Design method for reducing vibration and dynamic stress level of rotor blade |
| CN102663195B (en) * | 2012-04-17 | 2014-01-22 | 北京航空航天大学 | Design method for reducing vibration and dynamic stress level of rotor blade |
| CN102658865A (en) * | 2012-05-17 | 2012-09-12 | 李游 | Coaxial drive and control structure for coaxial contrarotation rotor helicopter |
| CN102658865B (en) * | 2012-05-17 | 2014-05-28 | 李游 | Coaxial drive and control structure for coaxial contrarotation rotor helicopter |
| CN103482063A (en) * | 2013-09-29 | 2014-01-01 | 中国航空动力机械研究所 | Supporting structure of propeller pitch operating lever |
| CN103482063B (en) * | 2013-09-29 | 2015-12-02 | 中国航空动力机械研究所 | A kind of pitch joystick supporting structure |
| CN106516105A (en) * | 2016-11-08 | 2017-03-22 | 瀚伦贝尔通用航空器有限公司 | Aircraft propeller surface regulating mechanism |
| CN106516105B (en) * | 2016-11-08 | 2023-07-04 | 瀚伦贝尔通用航空器有限公司 | Aircraft oar face adjustment mechanism |
| WO2018095042A1 (en) * | 2016-11-25 | 2018-05-31 | 深圳光启空间技术有限公司 | Variable blade pitch transmission mechanism |
| CN108116674A (en) * | 2016-11-30 | 2018-06-05 | 空客直升机 | Control member, rotor craft and method |
| CN108116674B (en) * | 2016-11-30 | 2020-12-29 | 空客直升机 | Control member, rotorcraft and method |
| CN107719661A (en) * | 2017-11-08 | 2018-02-23 | 沈阳旋飞航空技术有限公司 | A kind of unmanned plane rotor pulp distance varying mechanism |
| CN112601698A (en) * | 2018-09-04 | 2021-04-02 | 赛峰电子与防务公司 | Device for controlling the flight of an aircraft |
| CN112601698B (en) * | 2018-09-04 | 2022-07-05 | 赛峰电子与防务公司 | Device for controlling the flight of an aircraft |
| CN109533304A (en) * | 2018-10-19 | 2019-03-29 | 上海交通大学 | Have both rotor, fixed-wing offline mode single machine rotor aircraft and mode switching method |
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