CN105398573A - Jet drive type rotor wing mechanism and helicopter with same - Google Patents
Jet drive type rotor wing mechanism and helicopter with same Download PDFInfo
- Publication number
- CN105398573A CN105398573A CN201510966965.0A CN201510966965A CN105398573A CN 105398573 A CN105398573 A CN 105398573A CN 201510966965 A CN201510966965 A CN 201510966965A CN 105398573 A CN105398573 A CN 105398573A
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- Prior art keywords
- jet
- reaction driving
- driving rotor
- rotor
- rotor mechanism
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
- B64C27/16—Drive of rotors by means, e.g. propellers, mounted on rotor blades
- B64C27/18—Drive of rotors by means, e.g. propellers, mounted on rotor blades the means being jet-reaction apparatus
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- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
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Abstract
The invention provides a jet drive type rotor wing mechanism and a helicopter with the same. The jet drive type rotor wing mechanism comprises a rotor wing main shaft, a rotor wing and a jetting system, wherein the rotor wing main shaft is provided with a ventilation channel; the rotor wing is arranged on the rotor wing main shaft in a rotating mode, and the jetting system is arranged on the rotor wing, is communicated with the ventilation channel and jets high-pressure gas for enabling the rotor wing to rotate. According to the mechanism, the jetting system jets the high-pressure gas for enabling the rotor wing to rotate, and therefore the rotor wing main shaft is insusceptible to reaction torque in the rotation process, the structure of the rotor wing is simplified, and the weight of the jet drive type rotor wing mechanism is effectively reduced. The problems that drive type rotor wing mechanisms in the prior art are complex in structure and heavy in weight are solved.
Description
Technical field
The present invention relates to vehicle technology field, in particular to a kind of reaction driving rotor mechanism and the helicopter with it.
Background technology
Fixed wing aircraft landing in general sense needs the landing distance quite grown, and cannot hover, and this makes its application scenario be subject to many restrictions.The feature of helicopter to realize vertical takeoff and landing, spot hover, has good applicability.This is represented in practice fully, and particularly it wins unusual merits repeatedly in disaster rescue action in recent years and local war.Therefore helicopter is also more and more subject to the favor of people.
But helicopter has an inherent defect: in order to effectively drive rotor wing rotation, the power that driving engine produces is transmitted with moment by the turning cylinder being connected to rotor, and this drive torque reacts on moment reverse greatly such as body grade.
For balancing this moment, pure helicopter adds tail-rotor at afterbody, also will install transmission shaft and retarder for driving this tail-rotor simultaneously.We have to by a part of power division of driving engine to tail-rotor like this, and thus efficiency reduce.Mechanism complicates simultaneously, and reliability reduces, and structural weight increases.
In order to address this problem, former researcher proposes method driving engine being arranged on blade tip and rotates to drive blade, like this, would not produce for the counteractive moment of torsion of body.But available engine has the rotor of High Rotation Speed, sizable gyro torque can be produced along with when blade rotates, blade is made to bear and to destroy.Cannot normally use.
Summary of the invention
Main purpose of the present invention is the helicopter providing a kind of reaction driving rotor mechanism and have it, to solve in prior art the problem driving rotor mechanism complex structure, weight heavy.
To achieve these goals, according to an aspect of the present invention, provide a kind of reaction driving rotor mechanism, comprising: mast, there is venting channels; Rotor, is rotatably arranged in mast; Jet system, arranges and is connected with venting channels with on rotor, and jet system is by spraying high pressure gas making rotor wing rotation.
Further, jet system comprises: jet pipe, and one end of jet pipe is connected with venting channels, and the other end of jet pipe is arranged on rotor, and jet pipe has spout.
Further, one end to the area of the cross-sectional plane of the nozzle of the other end of jet pipe of jet pipe reduces gradually.
Further, jet pipe comprises: linkage section, and one end of linkage section is connected with venting channels; Jet section, one end of jet section is connected with the other end of linkage section, and the other end of jet section is provided with spout, the jet section of inside being arranged at rotor, or jet section is arranged in the rib on the surface of rotor.
Further, reaction driving rotor mechanism also comprises rotor permanent seat, has bearing, and bearing is connected with the top of mast, and be provided with blade holder to the bilateral symmetry of the axis of bearing, rotor is arranged on blade holder.
Further, rotor comprises: the first Rotary-Wing Department, is positioned at the side of blade holder, the first Rotary-Wing Department is provided with the first spout of jet system; Second Rotary-Wing Department, is positioned at the opposite side of the first Rotary-Wing Department, the second Rotary-Wing Department is provided with the second spout of the jet system contrary with the jet direction of the first spout.
Further, jet system comprises two jet pipes, and two jet pipes are arranged on the first Rotary-Wing Department and the second Rotary-Wing Department respectively.
Further, reaction driving rotor mechanism also comprises: auto-bank unit, is arranged in mast; Connecting rod, one end of connecting rod is connected with rotor permanent seat, and the other end of connecting rod is connected with auto-bank unit.
Further, auto-bank unit comprises three steering wheel united controllers, and steering wheel united controller controls the direction of tilt of auto-bank unit.
Further, reaction driving rotor mechanism also comprises bearing seat, bearing seat arrange with the bottom of mast on and be positioned at the below of auto-bank unit, bearing seat has high pressure admission passage, and high pressure admission passage is connected with venting channels.
Further, the inwall of the high pressure admission passage of bearing seat is provided with sealed bearings, sealed bearings is positioned at high pressure admission passage and venting channels connection.
Further, high pressure admission passage and venting channels connection are provided with tightening seal washer.
According to a further aspect in the invention, provide a kind of helicopter, comprise reaction driving rotor mechanism, reaction driving rotor mechanism be above-mentioned in reaction driving rotor mechanism.
Apply technical scheme of the present invention, the invention provides a kind of reaction driving rotor mechanism, comprise mast, rotor and jet system.Mast has venting channels.Rotor is rotatably arranged in mast.Jet system arranges and is connected with venting channels with on rotor, and jet system is by spraying high pressure gas making rotor wing rotation.By arranging jet system ejection high pressure gas to make rotor wing rotation, being arranged so that the effect of mast not by reactive torque in the process rotated like this, simplifying rotor structure simultaneously, efficiently reduce the weight of reaction driving rotor mechanism.
Accompanying drawing explanation
The Figure of description forming a application's part is used to provide a further understanding of the present invention, and schematic description and description of the present invention, for explaining the present invention, does not form inappropriate limitation of the present invention.In the accompanying drawings:
Fig. 1 is the overall schematic of blade reaction driving rotor mechanism of the present invention;
Fig. 2 is the front elevation of blade reaction driving rotor mechanism of the present invention;
Fig. 3 is the partial elevation view of blade reaction driving rotor mechanism of the present invention;
Fig. 4 is blade reaction driving rotor mechanism bearing seat schematic diagram of the present invention;
Fig. 5 is the partial side view of blade reaction driving rotor mechanism of the present invention;
Fig. 6 is blade reaction driving rotor mechanism bearing seat birds-eye view of the present invention.
Detailed description of the invention
It should be noted that, when not conflicting, the embodiment in the application and the feature in embodiment can combine mutually.Below with reference to the accompanying drawings and describe the present invention in detail in conjunction with the embodiments.
As shown in Figures 1 to 6, according to one embodiment of present invention, provide a kind of reaction driving rotor mechanism, comprise mast 10, rotor 20 and jet system.Mast 10 has venting channels 11.Rotor 20 is rotatably arranged in mast 10.Jet system arranges and is connected with venting channels 11 with on rotor 20, and jet system to rotate to make rotor 20 by spraying high pressure gas.
In the present embodiment, rotate to make rotor 20 by arranging jet system ejection high pressure gas, be arranged so that the effect of mast 10 not by reactive torque in the process rotated like this, simplify rotor 20 structure simultaneously, efficiently reduce the weight of reaction driving rotor mechanism.
In the present embodiment, jet system comprises jet pipe 30.One end of jet pipe 30 is connected with venting channels 11, and the other end of jet pipe 30 is arranged on rotor 20, jet pipe 30 has spout 310.
Wherein, one end to the area of the cross-sectional plane at spout 310 place of the other end of jet pipe 30 of jet pipe 30 reduces gradually.The trailing edge ejection that actv. accelerates the jet blade to rotor 20 is set like this, provides thrust for blade rotates, thus maintain the High Rotation Speed of blade.
Further, jet pipe 30 comprises linkage section 31 and jet section 32.One end of linkage section 31 is connected with venting channels 11.One end of jet section 32 is connected with the other end of linkage section 31, the other end of jet section 32 is provided with spout 310, the inside being arranged at rotor 20 for jet section 32.Certainly, also can be arranged in for jet section 32 in the rib 21 on the surface of rotor 20.
Reaction driving rotor mechanism also comprises rotor permanent seat 40, has bearing 41, and bearing 41 is connected with the top of mast 20, and be provided with blade holder 42 to the bilateral symmetry of the axis of bearing 41, rotor 20 is arranged on blade holder 42.
Rotor 20 comprises the first Rotary-Wing Department 22 and the second Rotary-Wing Department 23.First Rotary-Wing Department 22 is positioned at the side of blade holder 42, the first Rotary-Wing Department 22 is provided with the first spout 220 of jet system.Second Rotary-Wing Department 23 is positioned at the opposite side of the first Rotary-Wing Department 22, the second Rotary-Wing Department 23 is provided with the second spout 230 of the jet system contrary with the jet direction of the first spout 220.
Jet system comprises two jet pipes, 30, two jet pipes 30 and is arranged at respectively on the first Rotary-Wing Department 22 and the second Rotary-Wing Department 23.
Reaction driving rotor mechanism also comprises auto-bank unit 50.Auto-bank unit 50 is arranged in mast 10; Connecting rod 60, one end of connecting rod 60 is connected with rotor permanent seat 40, and the other end of connecting rod 60 is connected with auto-bank unit 50.
Preferably, auto-bank unit 50 comprises three steering wheel united controllers, and steering wheel united controller controls the direction of tilt of auto-bank unit 50.Three steering wheels can realize the rising of auto-bank unit 50, decline and all directions and tilt.
Three servos control, feathering and total distance that can realize blade are handled.
Jet section 32 of blade inside, at blade spar rear portion, and provides structural strength.
When auto-bank unit 50 rises, connecting rod 60 rises thereupon, and the bearing 41 of blade holder 42 in rotor permanent seat 40 rotates, and the angle of attack of blade increases, and total distance of rotor 20 increases, and the angle of attack of blade reduces, and total distance of rotor reduces; When auto-bank unit 50 tilts, blade in the process of rotating, connecting rod 60 along with the periodic rising of auto-bank unit 50 and decline, the periodic rotation of the bearing 41 of blade holder 42 also thereupon in rotor permanent seat 40, performance period displacement function.
Reaction driving rotor mechanism also comprises bearing seat 70, bearing seat 70 arrange with the bottom of mast 10 on and be positioned at the below of auto-bank unit 50, bearing seat 70 has high pressure admission passage 71, and high pressure admission passage 71 is connected with venting channels 11.
The inwall of the high pressure admission passage 71 of bearing seat 70 is provided with sealed bearings 72, and sealed bearings 72 is positioned at high pressure admission passage 71 and venting channels 11 connection.
Further, high pressure admission passage 71 and venting channels 11 connection are provided with tightening seal washer 73.
Tightening seal washer 73, sealed bearings 70, tightening seal washer 73, sealed bearings 70 to top, are settled by bottom in order in bearing seat 70 inside.
Sealed bearings 72 and tightening seal washer 73 are used to increase air-tightness, reduce the loss of gas.
According to one embodiment of present invention, provide a kind of helicopter, comprise reaction driving rotor mechanism, reaction driving rotor mechanism is the reaction driving rotor mechanism in above-described embodiment.By interference fit, lining cement and boss transmitted load between mast 10 and sealed bearings 72.
Mast 10 also carries the function of gas transmission while rotating, and sealed bearings 10 is used for ensureing that the slight drag of mast 10 is rotated, and tightening seal washer 10 is used for guaranteeing that gas transmission system has good air-tightness.
As shown in Figure 3, high pressure gas enter in the gas transmission system of blade reaction driving rotor mechanism from the high pressure admission passage 71 of bearing seat 70, when mast 10, be two strands of air-flows in threeway punishment, two strands of air-flows lead to rotor 20 place by two jet pipes 30.Wherein, two strands of air-flows, each via after connecting tube 31, enter blade inner to form jet section 32.The air-flow of inflow is guided to the nozzle being placed in blade by jet section 32 of blade.Finally, air-flow is by the spout 310 of necking in, and the trailing edge accelerated to blade sprays, and provides thrust for blade rotates, and the thrust of two panels blade forms moment, maintains the High Rotation Speed of blade.Wherein, blade reaction driving rotor wing rotation, spout 310 position can be not limited to blade tips in blade tips.
The foregoing is only the preferred embodiments of the present invention, be not limited to the present invention, for a person skilled in the art, the present invention can have various modifications and variations.Within the spirit and principles in the present invention all, any amendment done, equivalent replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (13)
1. a reaction driving rotor mechanism, is characterized in that, comprising:
Mast (10), has venting channels (11);
Rotor (20), is rotatably arranged in described mast (10);
Jet system, arrange upper with described rotor (20) and be connected with described venting channels (11), described jet system is rotated to make described rotor (20) by ejection high pressure gas.
2. reaction driving rotor mechanism according to claim 1, is characterized in that, described jet system comprises:
Jet pipe (30), one end of described jet pipe (30) is connected with described venting channels (11), and the other end of described jet pipe (30) is arranged on described rotor (20), described jet pipe (30) has spout (310).
3. reaction driving rotor mechanism according to claim 2, is characterized in that, one end of described jet pipe (30) reduces gradually to the area of the cross-sectional plane at spout (310) place of the other end of described jet pipe (30).
4. reaction driving rotor mechanism according to claim 2, is characterized in that, described jet pipe (30) comprising:
Linkage section (31), one end of described linkage section (31) is connected with described venting channels (11);
Jet section (32), the one end of described jet section (32) is connected with the other end of described linkage section (31), the other end of described jet section (32) is provided with described spout (310), described jet section (32) are arranged at the inside of described rotor (20), or described jet section (32) are arranged in the rib (21) on the surface of described rotor (20).
5. reaction driving rotor mechanism according to claim 1, it is characterized in that, described reaction driving rotor mechanism also comprises rotor permanent seat (40), there is bearing (41), described bearing (41) is connected with the top of described mast (20), be provided with blade holder (42) to the bilateral symmetry of the axis of described bearing (41), described rotor (20) is arranged on described blade holder (42).
6. reaction driving rotor mechanism according to claim 5, is characterized in that, described rotor (20) comprising:
First Rotary-Wing Department (22), is positioned at the side of described blade holder (42), described first Rotary-Wing Department (22) is provided with first spout (220) of described jet system;
Second Rotary-Wing Department (23), is positioned at the opposite side of described first Rotary-Wing Department (22), described second Rotary-Wing Department (23) is provided with second spout (230) of the described jet system contrary with the jet direction of described first spout (220).
7. reaction driving rotor mechanism according to claim 6, it is characterized in that, described jet system comprises two jet pipes (30), and two described jet pipes (30) are arranged on described first Rotary-Wing Department (22) and described second Rotary-Wing Department (23) respectively.
8. reaction driving rotor mechanism according to claim 5, is characterized in that, described reaction driving rotor mechanism also comprises:
Auto-bank unit (50), is arranged in described mast (10);
Connecting rod (60), one end of described connecting rod (60) is connected with described rotor permanent seat (40), and the other end of described connecting rod (60) is connected with described auto-bank unit (50).
9. reaction driving rotor mechanism according to claim 8, is characterized in that, described auto-bank unit (50) comprises three steering wheel united controllers, and described steering wheel united controller controls the direction of tilt of described auto-bank unit (50).
10. reaction driving rotor mechanism according to claim 9, it is characterized in that, described reaction driving rotor mechanism also comprises bearing seat (70), described bearing seat (70) arrange with the bottom of described mast (10) on and be positioned at the below of described auto-bank unit (50), described bearing seat (70) has high pressure admission passage (71), and described high pressure admission passage (71) is connected with described venting channels (11).
11. reaction driving rotor mechanisms according to claim 10, it is characterized in that, the inwall of the described high pressure admission passage (71) of described bearing seat (70) is provided with sealed bearings (72), and described sealed bearings (72) is positioned at described high pressure admission passage (71) and described venting channels (11) connection.
12. reaction driving rotor mechanisms according to claim 10, is characterized in that, described high pressure admission passage (71) and described venting channels (11) connection are provided with tightening seal washer (73).
13. 1 kinds of helicopters, comprise reaction driving rotor mechanism, it is characterized in that, described reaction driving rotor mechanism is the reaction driving rotor mechanism described in any one of claim 1 to 12.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510966965.0A CN105398573A (en) | 2015-12-21 | 2015-12-21 | Jet drive type rotor wing mechanism and helicopter with same |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510966965.0A CN105398573A (en) | 2015-12-21 | 2015-12-21 | Jet drive type rotor wing mechanism and helicopter with same |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105398573A true CN105398573A (en) | 2016-03-16 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510966965.0A Pending CN105398573A (en) | 2015-12-21 | 2015-12-21 | Jet drive type rotor wing mechanism and helicopter with same |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105398573A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113120229A (en) * | 2021-05-20 | 2021-07-16 | 李可 | Centrifugal wind wheel air inlet wing tip jet rotor |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4371314A (en) * | 1981-04-06 | 1983-02-01 | Henderson & Sturm | Air jet helicopter rotor hub and air distribution system |
| US4589611A (en) * | 1983-03-01 | 1986-05-20 | Maurice Ramme | Air jet reaction contrarotating rotor gyrodyne |
| JPH06198697A (en) * | 1992-10-14 | 1994-07-19 | Karl Hehl | Hydraulic pressure controller for injection molding machine |
| US20040056144A1 (en) * | 2002-09-24 | 2004-03-25 | Bass Steven M. | Dual-flight mode tandem rotor wing |
| WO2014075706A1 (en) * | 2012-11-13 | 2014-05-22 | Unmanned Systems Ag | Helicopter |
| CN204527614U (en) * | 2015-01-21 | 2015-08-05 | 西北农林科技大学 | A kind of steering unit of small capacity double rotor wing unmanned aerial vehicle |
| CN105050894A (en) * | 2013-03-25 | 2015-11-11 | 艾里莉个人独资有限公司 | System for operating helicopter blades with compressed air |
| CN205203382U (en) * | 2015-12-21 | 2016-05-04 | 保定维特瑞交通设施工程有限责任公司 | Jet -propelled helicopter that drives vane actuated mechanism and have it |
-
2015
- 2015-12-21 CN CN201510966965.0A patent/CN105398573A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4371314A (en) * | 1981-04-06 | 1983-02-01 | Henderson & Sturm | Air jet helicopter rotor hub and air distribution system |
| US4589611A (en) * | 1983-03-01 | 1986-05-20 | Maurice Ramme | Air jet reaction contrarotating rotor gyrodyne |
| JPH06198697A (en) * | 1992-10-14 | 1994-07-19 | Karl Hehl | Hydraulic pressure controller for injection molding machine |
| US20040056144A1 (en) * | 2002-09-24 | 2004-03-25 | Bass Steven M. | Dual-flight mode tandem rotor wing |
| WO2014075706A1 (en) * | 2012-11-13 | 2014-05-22 | Unmanned Systems Ag | Helicopter |
| CN105050894A (en) * | 2013-03-25 | 2015-11-11 | 艾里莉个人独资有限公司 | System for operating helicopter blades with compressed air |
| CN204527614U (en) * | 2015-01-21 | 2015-08-05 | 西北农林科技大学 | A kind of steering unit of small capacity double rotor wing unmanned aerial vehicle |
| CN205203382U (en) * | 2015-12-21 | 2016-05-04 | 保定维特瑞交通设施工程有限责任公司 | Jet -propelled helicopter that drives vane actuated mechanism and have it |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113120229A (en) * | 2021-05-20 | 2021-07-16 | 李可 | Centrifugal wind wheel air inlet wing tip jet rotor |
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| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20160316 |
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