CN105775126A - Propeller rotation plane adjustment mechanism for aircrafts - Google Patents
Propeller rotation plane adjustment mechanism for aircrafts Download PDFInfo
- Publication number
- CN105775126A CN105775126A CN201610291380.8A CN201610291380A CN105775126A CN 105775126 A CN105775126 A CN 105775126A CN 201610291380 A CN201610291380 A CN 201610291380A CN 105775126 A CN105775126 A CN 105775126A
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- CN
- China
- Prior art keywords
- semiaxis
- axle bed
- frame
- axle
- governor motion
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/52—Tilting of rotor bodily relative to fuselage
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
Abstract
The invention relates to a propeller rotation plane adjustment mechanism for aircrafts. The propeller rotation plane adjustment mechanism comprises a frame and a propeller. A girder is arranged above the frame and mounting seats are arranged on the girder at two ends of the upper end of the frame. The propeller rotation plane adjustment mechanism is characterized in that half shafts are arranged between two ends of the upper end of the frame and the girder and are connected with the girder. The inner end of each half shaft is provided with a central hole, and screws are arranged at the inner ends of the half shafts and connected with the girder. The upper end of a stern shaft is connected with a first belt pulley. A power mechanism is arranged between the two screws, two output shafts and a second belt pulley are arranged on the power mechanism, and a transmission belt is arranged between the first belt pulley and the second belt pulley. A first pushing and pulling mechanism is connected on the haft shafts. The outer ends of the half shafts are connected with shaft seats, the upper section of the stern shaft of the propeller extends into the shaft seats and are rotarily matched with it. The outer walls of the opposite sites of the shaft seats are provided with spindle noses, forks are arranged on the outer sections of the half shafts, and a second pushing and pulling mechanism is connected between the inner ends of the forks and the lower end of the shaft seats. By the propeller rotation plane adjustment mechanism, power loss of the small aircrafts can be reduced, and effective lift can be increased. The propeller rotation plane adjustment mechanism is applicable to small aircrafts.
Description
Technical field
The present invention relates to a kind of small aircraft.Specifically, be can under the narrow and small MODEL OVER COMPLEX TOPOGRAPHY of high mountain or valley etc the propeller Plane of rotation governor motion on the small aircraft of landing.
Background technology
China's ZL2013104235571 patent disclosure is a kind of can at the small aircraft of complicated landform landing, this small aircraft includes body frame, two ducts, transverse directions are put the wing, longitudinally put the wing, direction control mechanism, electromotor and support, and the axis of described two ducts is parallel.There is axle bed at the center of described duct inner chamber, has oar axle and the cooperation in rotatable shape between the two in axle bed.There is propeller oar axle upper end, is connected by link between the outer wall of described two ducts.Described body frame is connected to the bottom of link, and there is seat the front side of body frame.The output shaft of described electromotor is connected by the first drive mechanism and two oar axles.Described direction control mechanism is on body frame, and direction control mechanism is connected with the laterally pendulum wing and longitudinal pendulum wing respectively by the second drive mechanism.Wherein, direction control mechanism is positioned at below two propellers so that the longitudinal rudder plate in direction control mechanism and horizontal rudder plate are respectively positioned under propeller Plane of rotation.Owing to the longitudinal rudder plate in direction control mechanism and horizontal rudder plate are respectively positioned under propeller Plane of rotation, during aircraft flight, the airflow function below its propeller is on rudder plate, in order to the attitude of change of flight device, thus controlling the heading of aircraft.Owing to change of flight device attitude is to realize on rudder plate by the airflow function below propeller, so, acts on the air-flow on rudder plate and can consume a part of power.Through Theoretical Calculation and verification experimental verification, due to the stop of rudder plate, the power of aircraft can be made to reduce by more than 10%.As can be seen here, the power attenuation of above-mentioned small aircraft is relatively big, and useful lift is little.
Summary of the invention
The problem to be solved in the present invention is to provide a kind of aircraft propeller Plane of rotation governor motion.Adopt this governor motion, it is possible to decrease the power attenuation of small aircraft, improve useful lift.
The problem above that the invention solves the problems that is realized by techniques below scheme:
The aircraft propeller Plane of rotation governor motion of the present invention includes frame, and all there is propeller the frame left and right sides, and described propeller is made up of the blade of oar axle and lower end thereof.Frame, arranged above with crossbeam, crossbeam corresponding with two, frame upper end is respectively and fixedly provided with mounting seat, and two mounting seats are connected with two, upper end of frame by support bar respectively.Being characterized between two, frame upper end and crossbeam all has semiaxis.Semiaxis parallel with crossbeam and the two between be connected by the second axle sleeve, in clearance fit between the circumference of semiaxis and the second axle sleeve.There is centre bore semiaxis inner end, and there is screw rod semiaxis inner end, and screw rod is fixed on the relevant position of crossbeam by connector.Oar axle upper end is connected with the first belt wheel.Dynamic mechanism between two screw rods, this actuating unit has two output shafts being parallel to each other, and output shaft all has the second belt wheel, is connected with transmission band between that adjacent the first belt wheel and second belt wheel.Semiaxis the first push-pull mechanism making semiaxis rotate an angle forward or backwards arranged below.Semiaxis outer end is all connected with axle bed, and described oar axle epimere stretches in axle bed and coordinates in rotatable shape between the two.Axle bed offside outer wall all there is spindle nose, the outer section of semiaxis has crotch, all coordinates in rotatable shape between crotch and two spindle noses.The second push-pull mechanism it is connected with between crotch inner end and axle bed lower end.
Further improvement of the present invention scheme is, described connector includes the first nut and the second nut, and described first nut and the second nut are all screwed on screw rod, and the first nut top therein is fixed in mounting seat.
Further improvement of the present invention scheme is, described semiaxis includes body, and body inner end is connected with the junction block being used as described centre bore.Having bearing in junction block inner end, the respective end of described screw rod stretches in bearing.
Described first push-pull mechanism is electric cylinder, and the piston rod of this electric cylinder is connected with described junction block by connecting rod.
Described second push-pull mechanism is electric cylinder.
Further improvement of the present invention scheme is, described axle bed epimere internal diameter is more than its hypomere, and described first belt wheel is positioned at axle bed epimere, and all has two to be easy to the transmission flat hole with traverse on the epimere of axle bed.
Further improvement of the present invention scheme is, described crotch includes base portion, base portion has the longitudinal hole for coordinating with semiaxis, one end lower surface of base portion has the protuberance being easy to be connected with first push-pull mechanism one end, all there is integral forked pin ear the other end both sides of base portion, and forked pin ear all has coaxial axis hole；Correspondingly, two spindle noses on described axle bed penetrate in the axis hole on two forked pin ears in moving type respectively so that axle bed and oar axle can rotate an angle around spindle nose.
The further improvement project of the present invention is, described crotch is docked by the first half and lower half and forms, the described first half and lower half all include one and half base portions, and the proximal surface of half base portion all has arcuate groove, constitute a longitudinal hole coordinated with semiaxis after two arcuate groove docking.One end of two and half base portions is all connected with half pin ear, and the interface of two and half pin ears all has arcuate groove, constitutes described axis hole after two arcuate groove docking.
As can be seen from the above scheme, owing to all there being semiaxis between two, frame upper end and crossbeam.Semiaxis parallel with crossbeam and the two between be connected by the second axle sleeve, in clearance fit between the circumference of semiaxis and the second axle sleeve.There is centre bore semiaxis inner end, and there is screw rod semiaxis inner end, and screw rod is fixed on the relevant position of crossbeam by connector.Oar axle upper end is connected with the first belt wheel.Dynamic mechanism between two screw rods, this actuating unit has two output shafts being parallel to each other, and output shaft all has the second belt wheel, is connected with transmission band between that adjacent the first belt wheel and second belt wheel.Semiaxis the first push-pull mechanism making semiaxis rotate an angle forward or backwards arranged below.Semiaxis outer end is all connected with axle bed, and described oar axle epimere stretches in axle bed and coordinates in rotatable shape between the two.Axle bed 4 offside outer wall all there is spindle nose, the outer section of semiaxis has crotch, all coordinates in rotatable shape between crotch and two spindle noses.The second push-pull mechanism it is connected with between crotch inner end and axle bed lower end.In aircraft flight process, semiaxle tube can be driven to rotate an angle forward or backwards by the first push-pull mechanism, and then band is automatically connected in the propeller of oar axle lower end and carries out the pitch regulation on fore-and-aft direction.Flexible carrying screws again through the second push-pull mechanism carries out the pitch regulation on left and right directions.So, by changing the luffing angle of propeller Plane of rotation, reach to control the purpose in aircraft flight direction.Compared with background technology, do not need the laterally pendulum wing to put the wing with longitudinal, eliminate and handle laterally the pendulum wing and longitudinal rudder plate putting the wing.Owing to eliminating rudder plate, it is to avoid the consumption to craft power on rudder plate of the airflow function below propeller, improve the useful lift of aircraft.
Accompanying drawing explanation
Fig. 1 is the aircraft propeller Plane of rotation governor motion structural representation of the present invention；
Fig. 2 is the I place enlarged diagram of Fig. 1；
Fig. 3 is the A-A cross-sectional schematic of Fig. 2；
Fig. 4 is the fork structure schematic diagram in Fig. 1.
Specific implementation method
As shown in Figure 1, Figure 2, Figure 3 shows, the aircraft propeller Plane of rotation governor motion of the present invention includes frame 22, and frame 22 left and right sides is provided with propeller.Described propeller is made up of the blade 1 of oar axle 2 and lower end thereof.Frame 22 is provided above crossbeam 12, and crossbeam 12 corresponding with two, frame 22 upper end is respectively and fixedly provided with mounting seat 16, and two mounting seats 16 are connected with two, upper end of frame 22 by support bar 27 respectively.Be provided with semiaxis between two, frame 22 upper end and crossbeam 12, semiaxis parallel with crossbeam 12 and the two between be connected by the second axle sleeve 14, in clearance fit between the circumference of semiaxis and the second axle sleeve 14.Second axle sleeve 14 therein has two, and said two axle sleeve 14 is rectangle, and on it, processing has a upper hole and a lower opening, and described crossbeam 12 penetrates in tight shape in the upper hole of two axle sleeves 14.Wherein, the outer end of that axle sleeve 14 and mounting seat 16 of being close to mounting seat 16 is fixed together.
The processing of semiaxis inner end has centre bore, semiaxis inner end to be provided with screw rod 20, and screw rod 20 is fixed on the relevant position of crossbeam 12 by a connector.Described connector contains the first nut 18, and this first nut 18 is rectangle, and on it, processing has a through hole and a screw, and described crossbeam 12 penetrates in through hole in tight shape.Described screw is positioned under crossbeam 12, and described screw rod 20 screws in screw.The outer end of screw rod 20 has screwed the second nut 19, utilizes the second nut 19 can realize the locking between screw rod 20 and the first nut 18.
Oar axle 2 upper end is provided with the first belt wheel 8.Being provided with actuating unit 23 between two screw rods 20, this actuating unit 23 has two output shafts being parallel to each other 21, output shaft 21 is mounted on the second belt wheel 24, is connected with transmission band 28 between that adjacent the first belt wheel 8 and second belt wheel 24.Semiaxis is arranged below the first push-pull mechanism 26 that semiaxis can be made to rotate an angle forward or backwards.Semiaxis outer end is all connected with axle bed 4, and described oar axle 2 epimere stretches in axle bed 4 and coordinates in rotatable shape by upper bearing (metal) 10, middle (center) bearing 7 and lower bearing 5 between the two.On axle bed 4 offside outer wall, all processing has integral spindle nose, the outer section of semiaxis is fixed with crotch 11, all coordinates in rotatable shape between crotch 11 with two spindle noses.Being connected with the second push-pull mechanism 29 between crotch 11 inner end and axle bed 4 lower end, described second push-pull mechanism 29 is electric cylinder.Axle bed 4 top and bottom are respectively fixed with the upper cover 9 for blocking upper bearing (metal) 10 and for blocking the lower cover 3 of lower bearing 5.
For saving material, described semiaxis includes a body 13, and body 13 inner end is connected with the junction block 15 being used as described centre bore.Being provided with bearing 17 in junction block 15 inner end, the respective end of described screw rod 20 stretches in bearing 17.
Described first push-pull mechanism 26 is electric cylinder, and the piston rod of this electric cylinder is connected with described junction block 15 by connecting rod 25.
Described axle bed 4 epimere internal diameter is more than its hypomere, and described first belt wheel 8 is positioned at axle bed 4 epimere, and on the epimere of axle bed 4, all processing has two to be easy to the transmission flat hole with 28 traverses.
As shown in Figure 4, described crotch 11 includes base portion, on base portion, processing has the longitudinal hole 11-1 for coordinating with semiaxis 13, on one end lower surface of base portion, processing has the protuberance 11-2 being easy to be connected with second push-pull mechanism 29 one end, the other end both sides of base portion all process integral forked pin ear, and on forked pin ear, all processing has coaxial axis hole 11-3.Correspondingly, two spindle noses on described axle bed 4 penetrate in the coaxial axis hole 11-3 on two forked pin ears in moving type respectively so that axle bed 4 and oar axle 2 can rotate an angle around spindle nose.
For ease of assembling, described crotch 11 is docked by the first half and lower half and forms, and the described first half and lower half all include one and half base portions, and on the proximal surface of half base portion, all processing has arcuate groove, constitutes a longitudinal hole 11-1 coordinated with semiaxis 13 after two arcuate groove docking.One end of two and half base portions is all connected with half pin ear 11-4, and on the interface of two and half pin ear 11-4, all processing has arcuate groove, constitutes described cylinder axle axis hole 11-3 after two arcuate groove docking.
Aircraft is in flight course, by the first push-pull mechanism 26 and connecting rod 25, the blade 1 that can drive the oar axle 2 in junction block 15 and semiaxis 13, axle bed and axle bed 4 and oar axle lower end rotates an angle together forward or backwards, thus realizing the adjustment of propeller pitch angles.Stretching by the second push-pull mechanism 29, can drive the oar axle 2 in axle bed 4 and axle bed 4 to carry out the angle that swings, thus the left and right angle of pitch realizing propeller regulates.So, by changing the luffing angle of propeller Plane of rotation, reach to control the purpose in aircraft flight direction.
Claims (8)
1. aircraft propeller Plane of rotation governor motion, including frame (22), all there is propeller frame (22) left and right sides, and described propeller is made up of the blade (1) of oar axle (2) and lower end thereof；Frame (22), arranged above with crossbeam (12), crossbeam (12) corresponding with frame (22) two, upper end is respectively and fixedly provided with mounting seat (16), and two mounting seats (16) two, upper end by support bar (27) with frame (22) respectively is connected；It is characterized in that all there is semiaxis between frame (22) two, upper end and crossbeam (12)；Semiaxis parallel with crossbeam (12) and the two between be connected by the second axle sleeve (14), in clearance fit between the circumference of semiaxis and the second axle sleeve (14)；Semiaxis inner end has centre bore, semiaxis inner end to have screw rod (20), and screw rod (20) is fixed on the relevant position of crossbeam (12) by connector；Oar axle (2) upper end is connected with the first belt wheel (8)；Dynamic mechanism (23) between two screw rods (20), this actuating unit has two output shafts being parallel to each other (21), output shaft (21) all has the second belt wheel (24), between that adjacent the first belt wheel (8) and second belt wheel (24), is connected with transmission band (28)；Semiaxis the first push-pull mechanism (26) making semiaxis rotate an angle forward or backwards arranged below；Semiaxis outer end is all connected with axle bed (4), and described oar axle (2) epimere stretches in axle bed (4) and coordinates in rotatable shape between the two；All having spindle nose on axle bed (4) offside outer wall, the outer section of semiaxis has crotch (11), crotch (11) all coordinates in rotatable shape with between two spindle noses；The second push-pull mechanism (29) it is connected with between crotch (11) inner end and axle bed (4) lower end.
2. aircraft propeller Plane of rotation governor motion according to claim 1, it is characterized in that described connector includes the first nut (18) and the second nut (19), described first nut (18) and the second nut (19) are all screwed on screw rod (20), and the first nut (18) top therein is fixed in mounting seat (16).
3. aircraft propeller Plane of rotation governor motion according to claim 1, it is characterised in that described semiaxis includes body (13), and body (13) inner end is connected with the junction block (15) being used as described centre bore；((17), the respective end of described screw rod (20) stretches in bearing (17) bearing in junction block (15) inner end.
4. aircraft propeller Plane of rotation governor motion according to claim 3, it is characterised in that described first push-pull mechanism (26) is electric cylinder, the piston rod of this electric cylinder is connected with described junction block (15) by connecting rod (25).
5. aircraft propeller Plane of rotation governor motion according to claim 1, it is characterised in that described second push-pull mechanism (29) is electric cylinder.
6. aircraft propeller Plane of rotation governor motion according to claim 1, it is characterized in that described axle bed (4) epimere internal diameter is more than its hypomere, described first belt wheel (8) is positioned at axle bed (4) epimere, and all has two flat holes being easy to transmission band (28) traverse on the epimere of axle bed (4).
7. aircraft propeller Plane of rotation governor motion according to claim 1, it is characterized in that described crotch (11) includes base portion, base portion has the longitudinal hole for coordinating with semiaxis (13), one end lower surface of base portion has the protuberance (11-2) being easy to be connected with the second push-pull mechanism (29) one end, all there is integral forked pin ear the other end both sides of base portion, and forked pin ear all has coaxial axis hole (11-3)；Correspondingly, two spindle noses on described axle bed (4) penetrate in the coaxial axis hole (11-3) on two forked pin ears in moving type respectively so that axle bed (4) and oar axle (2) can rotate an angle around spindle nose.
8. aircraft propeller Plane of rotation governor motion according to claim 7, it is characterized in that described crotch (11) is docked by the first half and lower half to form, the described first half and lower half all include one and half base portions, the proximal surface of half base portion all has arcuate groove, after two arcuate groove docking, constitutes a longitudinal hole coordinated with semiaxis (13)；One end of two and half base portions is all connected with half pin ear (11-4), and the interface of two and half pins ear (11-4) all has arcuate groove, constitutes described coaxial axis hole (11-3) after two arcuate groove docking.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610291380.8A CN105775126B (en) | 2016-05-05 | 2016-05-05 | Aircraft propeller Plane of rotation governor motion |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610291380.8A CN105775126B (en) | 2016-05-05 | 2016-05-05 | Aircraft propeller Plane of rotation governor motion |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105775126A true CN105775126A (en) | 2016-07-20 |
| CN105775126B CN105775126B (en) | 2017-11-07 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610291380.8A Active CN105775126B (en) | 2016-05-05 | 2016-05-05 | Aircraft propeller Plane of rotation governor motion |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106628124A (en) * | 2016-11-08 | 2017-05-10 | 瀚伦贝尔通用航空器有限公司 | Automatic balance adjusting mechanism for left and right rotors of twin-rotor air vehicle |
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| US8152096B2 (en) * | 2005-10-18 | 2012-04-10 | Smith Frick A | Apparatus and method for vertical take-off and landing aircraft |
| CN203486141U (en) * | 2013-09-17 | 2014-03-19 | 无锡振华机械有限公司 | Aircraft direction operating mechanism |
| CN204527626U (en) * | 2015-03-19 | 2015-08-05 | 河南金原碟科技有限公司 | Bevel gear set, shaft drive four rotor wing unmanned aerial vehicle |
| CN105000176A (en) * | 2015-08-10 | 2015-10-28 | 徐金鹏 | Jet aircraft |
| CN205770155U (en) * | 2016-05-05 | 2016-12-07 | 杨国社 | Aircraft propeller Plane of rotation governor motion |
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2016
- 2016-05-05 CN CN201610291380.8A patent/CN105775126B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8152096B2 (en) * | 2005-10-18 | 2012-04-10 | Smith Frick A | Apparatus and method for vertical take-off and landing aircraft |
| CN203486141U (en) * | 2013-09-17 | 2014-03-19 | 无锡振华机械有限公司 | Aircraft direction operating mechanism |
| CN204527626U (en) * | 2015-03-19 | 2015-08-05 | 河南金原碟科技有限公司 | Bevel gear set, shaft drive four rotor wing unmanned aerial vehicle |
| CN105000176A (en) * | 2015-08-10 | 2015-10-28 | 徐金鹏 | Jet aircraft |
| CN205770155U (en) * | 2016-05-05 | 2016-12-07 | 杨国社 | Aircraft propeller Plane of rotation governor motion |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106628124A (en) * | 2016-11-08 | 2017-05-10 | 瀚伦贝尔通用航空器有限公司 | Automatic balance adjusting mechanism for left and right rotors of twin-rotor air vehicle |
| CN106628124B (en) * | 2016-11-08 | 2023-06-06 | 瀚伦贝尔通用航空器有限公司 | Automatic adjusting and balancing mechanism for left rotor wing and right rotor wing of double-rotor aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105775126B (en) | 2017-11-07 |
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Effective date of registration: 20170816 Address after: Suzhou City, Jiangsu province 215155 Xiangcheng District Wang Ting Zhen Hua Yang Cun Hua Lu Qiang Applicant after: HELIPELLER GENERAL AIRCRAFT CO.,LTD. Address before: Yang Town, Huishan District of Wuxi City, Jiangsu Province, Yang Village 214156 Guo Zhuang 45 Applicant before: Yang Guoshe |
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Effective date of registration: 20230801 Address after: Room 202, No. 11 Dexing Lane, Chong'an District, Wuxi City, Jiangsu Province, 214000 Patentee after: Yang Haiyan Address before: 215155 Qianghua Road, Huayang Village, Wangting Town, Xiangcheng District, Suzhou City, Jiangsu Province Patentee before: HELIPELLER GENERAL AIRCRAFT CO.,LTD. |