CN205469782U - Aircraft flight direction controlling means - Google Patents
Aircraft flight direction controlling means Download PDFInfo
- Publication number
- CN205469782U CN205469782U CN201620112245.8U CN201620112245U CN205469782U CN 205469782 U CN205469782 U CN 205469782U CN 201620112245 U CN201620112245 U CN 201620112245U CN 205469782 U CN205469782 U CN 205469782U
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- Prior art keywords
- bearing block
- girder
- bearing
- aircraft flight
- control apparatus
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- 239000002184 metal Substances 0.000 claims description 9
- 239000004677 Nylon Substances 0.000 claims description 6
- 229920001778 nylon Polymers 0.000 claims description 6
- 238000007789 sealing Methods 0.000 claims description 6
- 230000005540 biological transmission Effects 0.000 claims description 4
- 230000033228 biological regulation Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000012795 verification Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 1
- 238000012876 topography Methods 0.000 description 1
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Abstract
The utility model discloses an aircraft flight direction controlling means. It includes girder, two screws, and its characteristics are that the girder is hollow pipe, have adjusting screw in the middle of its inner chamber, and the adjusting screw both ends all revolve to twist there is the nut. All there is the semi -axis pipe at the adjusting screw both ends, but semi -axis pipe inner end is the rotating shape cover on corresponding nut. Having the arc hole on the girder lower wall corresponding with adjusting screw both ends, all having the electronic jar and the rotatory arm of force with the arc corresponding girder below in hole, the telescopic shaft and the revolving force underarm end of electronic jar link to each other, and rotatory arm of force upper end is managed with the semi -axis and is linked firmly mutually. All there is the bearing frame outer end of two halves central siphon, all has the oar axle in the diaxon bearing. All there is the band pulley upper end of two oar axles, and it has the drive belt to link between two band pulleys. The lower extreme at two oar axles is connected respectively to the screw. Adopt this kind of adjustment mechanism, can reduce small aircraft's power consumption, improve the useful lift. Be applicable to that small aircraft is left and right, the control of upper and lower all directions.
Description
Technical field
This utility model 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 pitch angle governor motion on the small aircraft of landing.It is applicable to that small aircraft is left and right, the control of upper and lower all directions.
Background technology
China's ZL2013104235571 patent disclose a kind of can be at the small aircraft of complicated landform landing, this small aircraft includes body frame, two ducts, laterally puts the wing, longitudinally the pendulum 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, have in axle bed oar axle and the two between coordinate in rotatable shape.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 longitudinal rudder plate and horizontal rudder plate in direction control mechanism 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, on rudder plate, in order to the attitude of change of flight device, thus controls the heading of aircraft.Due to change of flight device attitude be by propeller below airflow function realize on rudder plate, so, act on the air-flow on many plates 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.
Utility model content
Problem to be solved in the utility model is to provide a kind of aircraft flight direction-control apparatus.Use this governor motion, it is possible to decrease the power attenuation of small aircraft, improve useful lift.
Problem above to be solved in the utility model is realized by techniques below scheme:
Aircraft flight direction-control apparatus of the present utility model includes girder, two propellers, is characterized in that girder is hollow circular-tube, has adjusting screw rod in the middle of its inner chamber.All there is external screw thread at the two ends of adjusting screw rod and has all screwed nut, and the direction of rotation of two nuts is contrary.Adjusting screw rod two ends all have semiaxle tube, semiaxle tube inner end to be that rotatable shape is enclosed within respective nut.Arcuate socket is had on girder lower wall corresponding with adjusting screw rod two ends, electric cylinder and rotary arm is all had below girder corresponding with arcuate socket, the telescopic shaft of electric cylinder is connected with rotary arm lower end, rotary arm upper end is fixedly connected with semiaxle tube after corresponding arcuate socket, thus the telescopic shaft and rotary arm by electric cylinder drives semiaxle tube can rotate an angle along the circumferencial direction of girder.The outer end of two halves central siphon is all connected with bearing block, bearing block axially the most vertical with girder so that being axially arranged vertically of bearing block.All there is oar axle in two bearings seat, coordinate and dynamic cooperation in fixed respectively between oar axle with the axial direction of corresponding bearing block and between circumferencial direction.All there is belt wheel the upper end of two oar axles, is connected with transmission band between two belt wheels.Described propeller is connected to the lower end of two oar axles.
Further improvement of the utility model scheme is, has nylon jacket between girder and semiaxle tube, and described nylon jacket is made up of two intermediate sleeve and two end sets.
Further improvement of the utility model scheme is, described semiaxle tube includes adapter sleeve and body, and the inner end of body is fixed together with the outer end of corresponding adapter sleeve.
Further improvement of the utility model scheme is, the semiaxle tube tube wall corresponding with arcuate socket has radial hole, rotary arm upper end penetrate and be fixed in respective radial holes.
Further improvement of the utility model scheme is, described bearing block side is connected with horizontal pipe, and the outer end of horizontal pipe is socketed on the outer end of corresponding semiaxle tube.The epimere internal diameter of bearing block and hypomere internal diameter are all higher than its interlude internal diameter so that interlude and epimere and under intersegmental all have step.Part oar axle epimere diameter and lower end diameter in bearing block are all higher than its interlude so that oar axle interlude and epimere and under intersegmental all have step, the interlude between two steps has back-up ring.Have upper bearing (metal) between more than the upper step of bearing block and oar axle, below the lower step of bearing block and oar axle between have lower bearing, the inner ring of upper bearing (metal) offsets with described back-up ring upper end, and lower bearing upper end offsets with back-up ring lower end.Bearing block upper end is connected with upper end cover, and bearing block lower end is connected with bottom end cover.
Wherein, there is the first sealing ring between bearing block upper end and upper end cover, between bearing block lower end and bottom end cover, have the second sealing ring.
Described upper bearing (metal) is taper roll bearing, and described lower bearing is thrust ball bearing.
Further improvement project of the present utility model is, the girder outside two rotary arms has fixed cover, and the downside of two fixed covers is connected to the fuselage roof of aircraft by support.
As can be seen from the above scheme, owing to girder is hollow cylinder, have in the middle of its inner chamber between adjusting screw rod, and the circumference of adjusting screw rod and girder in secure fit.All there is external screw thread at the two ends of adjusting screw rod and has all screwed nut, and the direction of rotation of described two nuts is contrary.Adjusting screw rod two ends all have semiaxle tube, semiaxle tube inner end to be that rotatable shape is enclosed within respective nut.Girder lower wall corresponding with adjusting screw rod two ends has arcuate socket, electric cylinder is all had with below two corresponding girders of arcuate socket, the telescopic shaft of electric cylinder is connected with rotary arm lower end, rotary arm upper end is fixedly connected with semiaxle tube after corresponding arcuate socket, thus the telescopic shaft and rotary arm by electric cylinder drives semiaxle tube can along the circumferential direction rotate an angle.The outer end of two halves central siphon is all connected with bearing block, bearing block axially the most vertical with girder so that being axially arranged vertically of bearing block.All there is oar axle in two bearings seat, coordinate and dynamic cooperation in fixed respectively between oar axle with the axial direction of corresponding bearing block and between circumferencial direction.All there is belt wheel the upper end of two oar axles, is connected with transmission band between two belt wheels.Described oar axle lower end is all connected with propeller.During aircraft flight, semiaxle tube can be driven to rotate an angle around adjusting screw rod by electric cylinder, rotary arm, and then band is automatically connected in the propeller of oar axle lower end and carries out pitch regulation.By changing the luffing angle of propeller Plane of rotation, reach to control the purpose in aircraft flight direction.Compared with background technology, it is not required to laterally put the wing and longitudinally put the wing, eliminates 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 aircraft flight direction-control apparatus structural representation of the present utility model；
Fig. 2 is enlarged diagram at the I of Fig. 1；
Fig. 3 is enlarged diagram at the J of Fig. 1.
Detailed description of the invention
As shown in Figure 1, Figure 2 and Figure 3, aircraft flight direction-control apparatus of the present utility model includes 15, two propellers 1 of girder.Described girder 15 is hollow circular-tube, is provided with adjusting screw rod 24 in the middle of its inner chamber.The two ends of adjusting screw rod 24 are all machined with external screw thread and have all screwed nut 22, and the direction of rotation of two nuts 22 is contrary.Adjusting screw rod 24 two ends are provided with semiaxle tube, and semiaxle tube inner end is that rotatable shape is enclosed within respective nut 22.Arcuate socket all it is machined with on corresponding girder 15 lower wall of adjusting screw rod 24 two ends, electric cylinder 27 and rotary arm 20 it is provided with below girder 15 corresponding with arcuate socket, the telescopic shaft of electric cylinder 27 is connected with rotary arm 20 lower end, rotary arm 20 upper end is fixedly connected with corresponding semiaxle tube after corresponding arcuate socket, thus the telescopic shaft and rotary arm 20 by electric cylinder 27 drives semiaxle tube can rotate an angle along the circumferencial direction of girder 15.All being machined with radial hole on the semiaxle tube tube wall corresponding with arcuate socket, rotary arm 20 upper end penetrates and is fixed in respective radial holes.
The outer end of two semiaxle tubes is all connected with bearing block 6, bearing block 6 axially the most vertical with girder 15 so that being axially arranged vertically of bearing block 6.It is mounted on oar axle 2 in two bearings seat 6, coordinates and dynamic cooperation in fixed respectively between oar axle 2 with the axial direction of corresponding bearing block 6 and between circumferencial direction.The upper end of two oar axles 2 is mounted on belt wheel 12, is connected with transmission band 16 between two belt wheels 12.Described oar axle 2 lower end is all connected with propeller 1.
Wherein, between girder 15 and semiaxle tube, nylon jacket is installed.Described nylon jacket is made up of two intermediate sleeve 18 and two end sets 14.
Described semiaxle tube includes that adapter sleeve 19 and body 13, the inner end of body 13 are fixed together with the outer end of corresponding adapter sleeve 19.
The vertical side of described bearing block 6 is provided with integral horizontal pipe 6-1, and the outer end of horizontal pipe 6-1 is socketed on the outer end of corresponding semiaxle tube.The epimere internal diameter of bearing block 6 and hypomere internal diameter are all higher than its interlude internal diameter so that interlude and epimere and under intersegmental all have step.Part oar axle 2 epimere diameter and lower end diameter in bearing block 6 are all higher than its interlude so that oar axle 2 interlude and epimere and under intersegmental be each formed with step, the interlude between two steps is provided with back-up ring 8.Upper bearing (metal) 9 is installed between more than the upper step of bearing block 6 and oar axle 2, below the lower step of bearing block 6 and oar axle 2 between be provided with lower bearing 5, the inner ring of upper bearing (metal) 9 offsets with described back-up ring 8 upper end, and the upper end of lower bearing 5 offsets with back-up ring 8 lower end.Wherein, described upper bearing (metal) 9 is taper roll bearing, and described lower bearing 5 is thrust ball bearing.
Bearing block 6 upper end is connected with upper end cover 10, and bearing block 6 lower end is connected with bottom end cover 3.And be provided with between bearing block 6 upper end and upper end cover 10 between the first sealing ring 11, bearing block 6 lower end and bottom end cover 3 second sealing ring 4 is installed.
Being connected for ease of the fuselage 28 with aircraft, the girder 15 outside two rotary arms 20 is respectively and fixedly provided with fixed cover 17, the downside of two fixed covers 17 is connected to fuselage 28 top of aircraft by support 29.
During aircraft flight, semiaxle tube can be driven to rotate an angle around adjusting screw rod 24 by electric cylinder 27, rotary arm 20, and then band is automatically connected in the propeller 1 of oar axle 2 lower end and carries out pitch regulation.By changing the luffing angle of propeller 1 Plane of rotation, it is achieved that control the purpose in aircraft flight direction.
Claims (10)
1. aircraft flight direction-control apparatus, including girder (15), two propellers (1), it is characterised in that girder (15) is hollow circular-tube, has adjusting screw rod (24) in the middle of its inner chamber；All there is external screw thread at the two ends of adjusting screw rod (24) and has all screwed nut (22), and the direction of rotation of two nuts (22) is contrary；Adjusting screw rod (24) two ends all have semiaxle tube, semiaxle tube inner end to be that rotatable shape is enclosed within respective nut (22)；Arcuate socket is had with on corresponding girder (15) lower wall of adjusting screw rod (24) two ends, all there are electric cylinder (27) and rotary arm (20) in girder (15) corresponding with arcuate socket lower section, the telescopic shaft of electric cylinder (27) is connected with rotary arm (20) lower end, rotary arm (20) upper end is fixedly connected with semiaxle tube after corresponding arcuate socket, thus the telescopic shaft and rotary arm (20) by electric cylinder (27) drives semiaxle tube can rotate an angle along the circumferencial direction of girder (15)；The outer end of two halves central siphon is all connected with bearing block (6), bearing block (6) axially the most vertical with girder (15) so that being axially arranged vertically of bearing block (6)；Oar axle (2), oar axle (2) is all had to coordinate and dynamic cooperation in fixed respectively with between the axial direction of corresponding bearing block (6) and between circumferencial direction in two bearings seat (6)；All there is belt wheel (12) upper end of two oar axles (2), is connected with transmission band (16) between two belt wheels (12)；Described propeller (1) is connected to the lower end of two oar axles (2).
Aircraft flight direction-control apparatus the most according to claim 1, it is characterised in that have nylon jacket between girder (15) and semiaxle tube.
Aircraft flight direction-control apparatus the most according to claim 2, it is characterised in that described nylon jacket is made up of two intermediate sleeve (18) and two ends set (14).
Aircraft flight direction-control apparatus the most according to claim 1, it is characterised in that described semiaxle tube includes adapter sleeve (19) and body (13), the inner end of body (13) is fixed together with the outer end of corresponding adapter sleeve (19).
Aircraft flight direction-control apparatus the most according to claim 1, it is characterised in that have radial hole, rotary arm (20) upper end to penetrate and be fixed in respective radial holes on the semiaxle tube tube wall corresponding with arcuate socket.
Aircraft flight direction-control apparatus the most according to claim 1, it is characterised in that described bearing block (6) side is connected with horizontal pipe (6-1), the outer end of horizontal pipe (6-1) is socketed on the outer end of corresponding semiaxle tube；The epimere internal diameter of bearing block (6) and hypomere internal diameter are all higher than its interlude internal diameter so that interlude and epimere and under intersegmental all have step；Part oar axle (2) epimere diameter and lower end diameter in bearing block (6) are all higher than its interlude so that oar axle interlude and epimere and under intersegmental all have step, the interlude between two steps has back-up ring (8)；Upper bearing (metal) (9) is had between more than the upper step of bearing block (6) and oar axle (2), lower bearing (5) is had between below the lower step of bearing block (6) and oar axle (2), the inner ring of upper bearing (metal) (9) offsets with described back-up ring (8) upper end, and lower bearing (5) upper end offsets with back-up ring (8) lower end；Bearing block (6) upper end is connected with upper end cover (10), and bearing block (6) lower end is connected with bottom end cover (3).
Aircraft flight direction-control apparatus the most according to claim 6, it is characterised in that have the first sealing ring (11) between bearing block (6) upper end and upper end cover (10), have the second sealing ring (4) between bearing block (6) lower end and bottom end cover (3).
Aircraft flight direction-control apparatus the most according to claim 6, it is characterised in that described upper bearing (metal) (9) is taper roll bearing.
Aircraft flight direction-control apparatus the most according to claim 6, it is characterised in that described lower bearing (5) is thrust ball bearing.
10. according to the aircraft flight direction-control apparatus according to any one of claim 1 ~ 9, it is characterized in that there is fixed cover (17) on the girder (15) in two rotary arm (20) outsides, the downside of two fixed covers (17) is connected to fuselage (28) top of aircraft by support (29).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620112245.8U CN205469782U (en) | 2016-02-04 | 2016-02-04 | Aircraft flight direction controlling means |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620112245.8U CN205469782U (en) | 2016-02-04 | 2016-02-04 | Aircraft flight direction controlling means |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205469782U true CN205469782U (en) | 2016-08-17 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620112245.8U Withdrawn - After Issue CN205469782U (en) | 2016-02-04 | 2016-02-04 | Aircraft flight direction controlling means |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205469782U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105564636A (en) * | 2016-02-04 | 2016-05-11 | 杨国社 | Flight direction control device of aircraft |
-
2016
- 2016-02-04 CN CN201620112245.8U patent/CN205469782U/en not_active Withdrawn - After Issue
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105564636A (en) * | 2016-02-04 | 2016-05-11 | 杨国社 | Flight direction control device of aircraft |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C41 | Transfer of patent application or patent right or utility model | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20161128 Address after: Suzhou City, Jiangsu province 215155 Xiangcheng District Wang Ting Zhen Hua Yang Cun Hua Lu Qiang Patentee after: General aircraft Co. Ltd. Han Lemberg Address before: Yang Town, Huishan District of Wuxi City, Jiangsu Province, Yang Village 214156 Guo Zhuang 45 Patentee before: Yang Guoshe |
|
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20160817 Effective date of abandoning: 20180413 |