CN110697038B - Unmanned helicopter displacement operating mechanism - Google Patents
Unmanned helicopter displacement operating mechanism Download PDFInfo
- Publication number
- CN110697038B CN110697038B CN201911084669.2A CN201911084669A CN110697038B CN 110697038 B CN110697038 B CN 110697038B CN 201911084669 A CN201911084669 A CN 201911084669A CN 110697038 B CN110697038 B CN 110697038B
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- steering engine
- mounting seat
- torsion
- ring
- twisting
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- 238000006073 displacement reaction Methods 0.000 title claims description 3
- 238000013016 damping Methods 0.000 claims abstract description 12
- 238000009434 installation Methods 0.000 claims description 18
- 230000033001 locomotion Effects 0.000 abstract description 7
- 230000000694 effects Effects 0.000 description 5
- 238000012423 maintenance Methods 0.000 description 2
- 238000010008 shearing Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000003139 buffering effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 125000003003 spiro group Chemical group 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Remote Sensing (AREA)
- Toys (AREA)
Abstract
The invention is applicable to the technical field of unmanned helicopters, and provides an unmanned helicopter pitch-changing control mechanism which comprises a body assembly and a rotating assembly used for rotating on the body assembly, wherein the body assembly comprises a steering engine mounting seat, a gear box and a torsion-resisting ring, the torsion-resisting ring and the steering engine mounting seat are vertically arranged, a plurality of mounting holes are formed in the outer side wall of the steering engine mounting seat, and a damping sleeve is arranged on the inner side wall of the mounting hole; through setting up the mounting hole with the damping sleeve, make the steering wheel with the steering wheel mount pad passes through mounting hole and bolt fixed connection, thereby make the steering wheel mount pad with be equipped with in the mounting hole that the steering wheel links to each other the damping sleeve, can effectually reduce the impact that alternating load that produces when the steering wheel vertical movement brought, thereby improve steering wheel life-span.
Description
Technical Field
The invention belongs to the technical field of unmanned helicopters, and particularly relates to a variable-pitch control mechanism of an unmanned helicopter.
Background
At present, the operation of the main rotor wing of the unmanned helicopter mainly has two realization modes: the steering system is modified on the basis of the manned helicopter, namely a linear steering engine is arranged at the position between the original collective lever and the steering lever, the steering engine pushes the steering lever to move, and the tilting direction and the tilting size of the tilting disk are controlled, so that the operation of the main rotor wing of the unmanned helicopter is realized; and secondly, three angle steering gears are arranged below the tilting disk, the steering disk of the angle steering gears is connected with the tilting disk through a pull rod, and the combined motion of the three angle steering gears realizes the operation of the main rotor wing of the unmanned helicopter.
The existing unmanned helicopter pitch-changing control mechanism has the defects that the impact force caused by alternating load generated during vertical movement of a steering engine is large, the service life of the steering engine is greatly influenced, and on the other hand, the main rotor wing control system is complex in structure, large in structural weight and high in control connecting rod failure rate.
Disclosure of Invention
The invention provides a variable-pitch control mechanism of an unmanned helicopter, which aims to solve the problems that the impact force generated when a steering engine moves vertically is large and greatly influences the service life of the steering engine in the existing variable-pitch control mechanism of the unmanned helicopter, and on the other hand, a main rotor wing control system is complex in structure, heavy in structure and high in failure rate of a control connecting rod.
The invention discloses a variable-pitch control mechanism of an unmanned helicopter, which comprises a body assembly and a rotating assembly used for rotating on the body assembly, wherein the body assembly comprises a steering engine mounting seat, a gear box and a reverse torsion ring, the steering engine mounting seat is positioned above the gear box and is in threaded connection with the gear box, the reverse torsion ring is vertically arranged with the steering engine mounting seat, the reverse torsion ring is in threaded connection with the steering engine mounting seat, a plurality of mounting holes are formed in the outer side wall of the steering engine mounting seat, and a damping sleeve is arranged on the inner side wall of the mounting hole;
The rotating assembly comprises a steering engine, a main shaft and a moving ring, wherein an output shaft of the steering engine is provided with an fixed ring, the output shaft of the steering engine is fixedly connected with the fixed ring, one end of the steering engine, which is far away from the output shaft, is connected with the mounting hole on the steering engine mounting seat in a threaded manner, the moving ring is positioned above the fixed ring, and the main shaft penetrates through the moving ring and the fixed ring and is connected with the steering engine mounting seat in a rotating manner.
Preferably, the steering engine mounting seat is composed of a gear box cover plate, a left side rudder machine mounting seat and a right side rudder machine mounting seat, and the gear box cover plate penetrates through the left side rudder machine mounting seat and the right side rudder machine mounting seat and is fixedly connected with the left side rudder machine mounting seat and the right side rudder machine mounting seat.
Preferably, a plurality of lightening holes are formed in the upper surfaces of the left side rudder machine mounting seat and the right side rudder machine mounting seat.
Preferably, the anti-twisting ring is composed of an anti-twisting lower section, a bushing, an anti-twisting middle section and an anti-twisting upper section, wherein the anti-twisting middle section is positioned above the anti-twisting lower section, and the anti-twisting middle section is connected with the anti-twisting lower section through the bushing;
the anti-twisting upper section is positioned above the anti-twisting middle section, and the anti-twisting upper section is connected with the anti-twisting middle section through the bushing.
Preferably, the reverse twisting lower section is arranged in a ladder shape, the reverse twisting middle section is arranged in a ladder shape, and the reverse twisting upper section is arranged in a clip shape.
Preferably, the outer side wall of the anti-torsion lower section is provided with a bolt hole, and the anti-torsion ring is fixedly connected with the steering engine mounting seat through the anti-torsion lower section, the bolt hole and the bolt;
The reverse twisting upper section is in threaded connection with the stationary ring.
Preferably, the stationary ring is provided in an X-shape.
Preferably, the movable ring is provided with a T shape;
A circular groove is formed in the middle of the steering engine mounting seat, and a bearing is further arranged in the circular groove;
The outer side wall of the bearing is fixedly connected with the circular groove, the inner side wall of the bearing is fixedly connected with the main shaft, and the main shaft rotates on the steering engine mounting seat through the bearing.
Preferably, the steering engine and the steering engine mounting seat are arranged on the same vertical line.
Preferably, the steering engine is S3302.
Compared with the prior art, the invention has the beneficial effects that: the mounting holes and the damping sleeves are arranged, so that the steering engine and the steering engine mounting seat are fixedly connected through the mounting holes and bolts, the damping sleeves are arranged in the mounting holes, which are connected with the steering engine, of the steering engine mounting seat, the impact caused by alternating load generated during vertical movement of the steering engine can be effectively reduced, and the service life of the steering engine is prolonged; by arranging the steering engine and the fixed ring on the output shaft of the steering engine, the fixed ring is directly driven to rotate when the output shaft of the steering engine moves, so that an operation connecting rod transmission mechanism of a helicopter is simplified, the structure of a main rotor wing control system is compact, the structure weight is reduced, and the failure rate of the control connecting rod is reduced.
Drawings
FIG. 1 is a schematic diagram of the structure of the present invention;
FIG. 2 is a schematic view of the steering engine mount and anti-twist ring mounting structure of the present invention;
FIG. 3 is a schematic view of the structure of the anti-twist ring of the present invention;
In the figure: 1-body assembly, 11-steering engine mount, 111-gear box cover plate, 112-left side rudder machine mount, 113-right side rudder machine mount, 114-lightening hole, 12-gear box, 13-anti-torsion ring, 131-anti-torsion lower section, 132-bushing, 133-anti-torsion middle section, 134-anti-torsion upper section, 135-bolt hole, 14-mounting hole, 15-damping sleeve, 16-circular groove, 17-bearing, 2-rotating assembly, 21-steering engine, 22-main shaft, 23-moving ring, 24-stationary ring.
Detailed Description
The present invention will be described in further detail with reference to the drawings and examples, in order to make the objects, technical solutions and advantages of the present invention more apparent. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the scope of the invention.
In the description of the present invention, it should be understood that the terms "length," "width," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like indicate orientations or positional relationships based on the orientation or positional relationships shown in the drawings, merely to facilitate describing the present invention and simplify the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and therefore should not be construed as limiting the present invention. Furthermore, in the description of the present invention, the meaning of "a plurality" is two or more, unless explicitly defined otherwise.
Referring to fig. 1-3, an unmanned helicopter pitch-changing control mechanism comprises a body assembly 1 and a rotating assembly 2 for rotating on the body assembly 1, wherein the body assembly 1 comprises a steering engine installation seat 11, a gear box 12 and a reverse torsion ring 13, the steering engine installation seat 11 is positioned above the gear box 12, the steering engine installation seat 11 is in threaded connection with the gear box 12, the reverse torsion ring 13 is vertically arranged with the steering engine installation seat 11, the reverse torsion ring 13 is in threaded connection with the steering engine installation seat 11, a plurality of installation holes 14 are formed in the outer side wall of the steering engine installation seat 11, and a damping sleeve 15 is arranged on the inner side wall of the installation hole 14;
The rotating assembly 2 comprises a steering engine 21, a main shaft 22 and a movable ring 23, an output shaft of the steering engine 21 is provided with an fixed ring 24, the output shaft of the steering engine 21 is fixedly connected with the fixed ring 24, one end of the steering engine 21, which is far away from the output shaft, is in threaded connection with the fixed ring 24 through a mounting hole 14 on a steering engine mounting seat 11, the movable ring 23 is positioned above the fixed ring 24, and the main shaft 22 penetrates through the movable ring 23 and the fixed ring 24 and is in rotating connection with the steering engine mounting seat 11.
In this embodiment, the steering engine 21, the steering engine mounting seat 11 and the mounting hole 14 are arranged on the same vertical line, and because the connection point of the traditional helicopter control mechanism mounting base and the steering engine is not on the same vertical line, and the steering engine is arranged on the side surface of the steering engine, the output shaft of the linear steering engine bears larger tension and pressure, and the shearing force is smaller, so that the fault of instability and deformation of the push rod often occurs, when the steering engine 21, the steering engine mounting seat 11 and the mounting hole 14 are arranged on the same vertical line, the tension and the pressure borne by the steering engine 21 are uniform, and the borne pressure can be stably transmitted to the steering engine mounting seat 11, thereby greatly reducing the fault rate; through setting up steering wheel mount pad 11 and gear box 12 spiro union for mounting structure is firm, does not have the installation clearance, improves the driven precision of operating system, through setting up mounting hole 14 and damping sleeve 15, makes steering wheel mount pad 11 with steering wheel 21 passes through mounting hole 14, damping sleeve 15 and bolted connection, makes damping sleeve 15 effectively reduce the impact that alternating load that produces when steering wheel 21 moves perpendicularly brought, thereby improves steering wheel 21's life-span, through setting up stationary ring 24 and moving ring 23, when making steering wheel 21's output shaft motion, drives stationary ring 24 and rotates, stationary ring 24 and moving ring 23 pair to paste tightly, thereby play sealed effect.
In this embodiment, the steering engine mounting seat 11 is fixed on the gear case 12 through a bolt, the main shaft 22 is mounted on the bearing 17 on the steering engine mounting seat 11, then the stationary ring 24 and the moving ring 23 are respectively connected with the main shaft 22, the stationary ring 24 and the output shaft of the steering engine 21 are connected, finally the counter-torsion ring 13 is mounted on the stationary ring 24 through the bolt and the counter-torsion upper section 134, after the mounting is completed, the power switch of the steering engine 21 is turned on, the electric energy in the steering engine 21 is converted into mechanical energy to move, so that the output shaft of the steering engine 21 is driven to rotate, when the output shaft of the steering engine 21 rotates, the stationary ring 24 is driven to rotate, then the stationary ring 24 rotates on the steering engine mounting seat 11 through the main shaft 22, at this time, an operator can rotate the steering engine 21 at any angle between 0 degrees and 180 degrees according to instructions, and the tilting direction of the stationary ring 24 is controlled, so that the tilting direction of the stationary ring 23 is controlled, and the moving direction of the unmanned helicopter is also controlled.
Further, the steering engine mounting seat 11 is composed of a gear box cover plate 111, a left side rudder machine mounting seat 112 and a right side rudder machine mounting seat 113, and the gear box cover plate 111 penetrates through the left side rudder machine mounting seat 112 and the right side rudder machine mounting seat 113 and is fixedly connected with the left side rudder machine mounting seat 112 and the right side rudder machine mounting seat 113.
In this embodiment, left side rudder machine mount pad 112 and right side rudder machine mount pad 113 pass through bolted connection, gear box apron 111, left side rudder machine mount pad 112 and right side rudder machine mount pad 113 also pass through bolted connection, thereby make steering wheel mount pad 11 can install alone or dismantle, when making operating personnel maintain or install, only need dismantle the bolt, just can dismantle maintenance and installation with the device, and it is convenient, thereby solved traditional steering wheel mount pad and can not dismantle alone, maintain the difficulty, and the problem of consuming time and consuming power.
Further, a plurality of lightening holes 114 are formed in the upper surfaces of the left side rudder machine mounting base 112 and the right side rudder machine mounting base 113.
In this embodiment, through setting up lightening hole 114 for steering wheel mount pad 11 can also alleviate steering wheel mount pad 11's weight when guaranteeing structural strength in the installation, thereby reduce unmanned aerial vehicle's weight, make unmanned aerial vehicle power lifting performance more obvious on the one hand, on the other hand reduce the accident probability, ensure unmanned aerial vehicle's safety.
Further, the anti-twisting ring 13 is composed of an anti-twisting lower section 131, a bushing 132, an anti-twisting middle section 133 and an anti-twisting upper section 134, wherein the anti-twisting middle section 133 is positioned above the anti-twisting lower section 131, and the anti-twisting middle section 133 is connected with the anti-twisting lower section 131 through the bushing 132;
The anti-twist upper section 134 is located above the anti-twist middle section 133, and the anti-twist upper section 134 and the anti-twist middle section 133 are connected by a bushing 132.
In this embodiment, through setting up anti-twisting lower segment 131, anti-twisting middle segment 133 and anti-twisting upper segment 134 for anti-twisting ring 13 divide into three sections, thereby compare in common two section structures, when increasing anti-twisting ring length, avoid steering wheel and the motion interference of fixed ring in total stroke volume, through setting up the connection of bush 132, on the one hand reduce wearing and tearing, vibration and the noise of device, on the other hand make things convenient for mechanical equipment's maintenance, simplify the structure and the manufacturing process of equipment.
Further, the reverse twisting lower section 131 is provided in a ladder shape, the reverse twisting middle section 133 is provided in a ladder shape, and the reverse twisting upper section 134 is provided in a clip shape.
In this embodiment, through setting up anti-the lower segment 131 of turning round for the ladder form for the cavity that forms in the middle of the lower segment 131 of turning round is turned round in anti-the weight of changing, thereby the effectual weight that reduces anti-torsion ring 13, thereby on the one hand in order to the convenience when installing, on the other hand save material, stability is still fine, be trapezoidal form through setting up anti-the middle segment 133 of turning round, make anti-the middle segment 133 of turning round have stronger stability, through setting up anti-the upper segment 134 of turning round for clip form, make more fastening when installing with the stationary ring 24 on the one hand, thereby the effectual axial rotation of preventing the stationary ring, on the other hand clip form is turned round the upper segment 134 of turning round with the cavity that forms in the middle of the middle segment 133 of turning round, thereby alleviate the weight of unmanned aerial vehicle, make unmanned aerial vehicle lifting power more obvious.
Further, a bolt hole 135 is formed in the outer side wall of the anti-torsion lower section 131, and the anti-torsion ring 13 is fixedly connected with the steering engine mounting seat 11 through the anti-torsion lower section 131, the bolt hole 135 and the bolt;
the counter-twist upper section 134 is threaded with the stationary ring 24.
In this embodiment, through setting up bolt hole 135 to install anti-twist ring 13 and steering wheel mount pad 11 through bolt hole 135 and bolt, thereby conveniently dismantle and install, and alleviate operating personnel's burden, through setting up anti-twist and trade upper segment 134 and the spiral shell joint of stationary ring 24, when making stationary ring 24 rotatory, the effectual axial motion of preventing stationary ring 24, thereby reduce the probability of accident.
Further, the stationary ring 24 is provided in an X-shape.
In this embodiment, the stationary ring 24 is in an X shape, so that when the stationary ring 24 rotates through the steering engine 21, the X-shaped stationary ring 24 can effectively balance the gyro effect of the flying when rotating, so that the air force torque effect is counteracted, the flying speed is faster, the unmanned aerial vehicle is prevented from being damaged by the air force torque, and meanwhile, the external interference of the X-shaped stationary ring 24 is effectively reduced, so that the angle output error is small.
Further, the movable ring 23 is provided in a T shape;
A circular groove 16 is formed in the middle of the steering engine mounting seat 11, and a bearing 17 is further arranged in the circular groove 16;
the outer side wall of the bearing 17 is fixedly connected with the circular groove 16, the inner side wall of the bearing 17 is fixedly connected with the main shaft 22, and the main shaft 22 rotates on the steering engine mounting seat 11 through the bearing 17.
In the embodiment, the moving ring 23 is of a T shape, so that when the moving ring 23 and the fixed ring 24 are matched with each other for use, on one hand, the T-shaped moving ring 23 can press down the fixed ring 24, so that the T-shaped moving ring 23 is effectively tightly attached to the fixed ring 23, the sealing effect is better, on the other hand, the T-shaped moving ring 23 plays a role in buffering, the buffer fluctuation of an unmanned aerial vehicle is prevented, the influence on the fixed ring 24 is directly caused, and the steering engine 21 is damaged;
Through setting up bearing 17 and circular recess 16 for circular recess 16 block bearing 17, the fixed when convenient installation, and set up bearing 17, in order to reduce the rotation damage of main shaft 22, make the effect that main shaft 22 rotated better, thereby the rotatory faster of stationary ring 24.
Further, the steering engine 21 and the steering engine mounting seat 11 and the mounting hole 14 are arranged on the same vertical line.
In this embodiment, because the connection point of the installation base of the traditional helicopter control mechanism and the steering engine is not on the same vertical line, and the steering engine is arranged on the side surface of the steering engine, so that the output shaft of the linear steering engine bears large tension and pressure, and the shearing force is small, so that the push rod is often unstable and deformed, and when the steering engine 21, the steering engine installation base 11 and the installation hole 14 are arranged on the same vertical line, the tension and the pressure borne by the steering engine 21 are uniform, and can be stably transmitted to the steering engine installation base 11, so that the failure rate of the type can be greatly reduced
Further, the model of the steering engine 21 is S3302.
In this embodiment, the model of the steering engine 21 is S3302, so that the steering engine 21 is stable in rotation frequency and light in weight, and the weight of the unmanned aerial vehicle is greatly reduced.
The foregoing description of the preferred embodiments of the invention is not intended to be limiting, but rather is intended to cover all modifications, equivalents, and alternatives falling within the spirit and principles of the invention.
Claims (7)
1. The utility model provides an unmanned helicopter displacement operating mechanism, includes body subassembly (1) and is used for rotating subassembly (2) on body subassembly (1), its characterized in that: the body assembly (1) comprises a steering engine mounting seat (11), a gear box (12) and a reverse torsion ring (13), wherein the steering engine mounting seat (11) is positioned above the gear box (12), the steering engine mounting seat (11) is in threaded connection with the gear box (12), the reverse torsion ring (13) is vertically arranged with the steering engine mounting seat (11), the reverse torsion ring (13) is in threaded connection with the steering engine mounting seat (11), a plurality of mounting holes (14) are formed in the outer side wall of the steering engine mounting seat (11), and a damping sleeve (15) is arranged on the inner side wall of each mounting hole (14);
The rotating assembly (2) comprises a steering engine (21), a main shaft (22) and a movable ring (23), wherein an output shaft of the steering engine (21) is provided with an fixed ring (24), the output shaft of the steering engine (21) is fixedly connected with the fixed ring (24), one end, far away from the output shaft, of the steering engine (21) is in threaded connection with the fixed ring (24) through the mounting hole (14) in the steering engine mounting seat (11), the movable ring (23) is positioned above the fixed ring (24), and the main shaft (22) penetrates through the movable ring (23) and the fixed ring (24) and is in rotary connection with the steering engine mounting seat (11);
The steering engine mounting seat (11) consists of a gear box cover plate (111), a left side rudder machine mounting seat (112) and a right side rudder machine mounting seat (113), wherein the gear box cover plate (111) penetrates through the left side rudder machine mounting seat (112) and the right side rudder machine mounting seat (113) and is fixedly connected with the left side rudder machine mounting seat (112) and the right side rudder machine mounting seat (113);
The movable ring (23) is arranged in a T shape;
a circular groove (16) is formed in the middle position of the steering engine mounting seat (11), and a bearing (17) is further arranged in the circular groove (16);
the outer side wall of the bearing (17) is fixedly connected with the circular groove (16), the inner side wall of the bearing (17) is fixedly connected with the main shaft (22), and the main shaft (22) rotates on the steering engine mounting seat (11) through the bearing (17).
2. An unmanned helicopter pitch-shifting control as claimed in claim 1, wherein: the upper surfaces of the left side rudder machine installation seat (112) and the right side rudder machine installation seat (113) are provided with a plurality of lightening holes (114).
3. An unmanned helicopter pitch-shifting control as claimed in claim 1, wherein: the anti-torsion ring (13) consists of an anti-torsion lower section (131), a bushing (132), an anti-torsion middle section (133) and an anti-torsion upper section (134), wherein the anti-torsion middle section (133) is positioned above the anti-torsion lower section (131), and the anti-torsion middle section (133) and the anti-torsion lower section (131) are connected through the bushing (132);
The anti-twisting upper section (134) is located above the anti-twisting middle section (133), and the anti-twisting upper section (134) and the anti-twisting middle section (133) are connected through the bushing (132).
4. A unmanned helicopter pitch-shifting control as claimed in claim 3, wherein: the anti-twisting lower section (131) is arranged in a ladder shape, the anti-twisting middle section (133) is arranged in a ladder shape, and the anti-twisting upper section (134) is arranged in a clip shape.
5. An unmanned helicopter pitch-shifting control as claimed in claim 4, wherein: the outer side wall of the anti-torsion lower section (131) is provided with a bolt hole (135), and the anti-torsion ring (13) and the steering engine mounting seat (11) are fixedly connected with the bolt hole (135) and the bolt through the anti-torsion lower section (131);
the reverse twisting upper section (134) is in threaded connection with the stationary ring (24).
6. An unmanned helicopter pitch-shifting control as claimed in claim 1, wherein: the stationary ring (24) is provided in an X-shape.
7. An unmanned helicopter pitch-shifting control as claimed in claim 1, wherein: the model of the steering engine (21) is S3302.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911084669.2A CN110697038B (en) | 2019-11-07 | 2019-11-07 | Unmanned helicopter displacement operating mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911084669.2A CN110697038B (en) | 2019-11-07 | 2019-11-07 | Unmanned helicopter displacement operating mechanism |
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| Publication Number | Publication Date |
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| CN110697038A CN110697038A (en) | 2020-01-17 |
| CN110697038B true CN110697038B (en) | 2024-05-28 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911084669.2A Active CN110697038B (en) | 2019-11-07 | 2019-11-07 | Unmanned helicopter displacement operating mechanism |
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| CN (1) | CN110697038B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113119085B (en) * | 2021-03-24 | 2022-04-19 | 北京航空航天大学 | Helicopter flight driving robot system |
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| CN206417186U (en) * | 2017-01-13 | 2017-08-18 | 重庆星环航空科技有限公司 | A kind of steering wheel mounting structure |
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| CN108945426A (en) * | 2018-06-27 | 2018-12-07 | 中国直升机设计研究所 | A kind of auto-bank unit suitable for a variety of propeller hub configurations |
| CN209192226U (en) * | 2018-08-14 | 2019-08-02 | 深圳联合飞机科技有限公司 | A kind of helicopter blade pitch control mechanism |
| CN209506069U (en) * | 2019-01-09 | 2019-10-18 | 南京国器智能装备有限公司 | One kind is anti-to wave helicopter hub mechanism |
| CN211167404U (en) * | 2019-11-07 | 2020-08-04 | 南京国器智能装备有限公司 | Variable-pitch control mechanism of unmanned helicopter |
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2019
- 2019-11-07 CN CN201911084669.2A patent/CN110697038B/en active Active
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3572616A (en) * | 1969-09-18 | 1971-03-30 | United Aircraft Corp | Pitch control mechanism for bladed rotor |
| CN103318407A (en) * | 2013-06-05 | 2013-09-25 | 王开林 | Standalone control system of coaxial double-rotor unmanned helicopter control system |
| DE202015104591U1 (en) * | 2015-08-28 | 2015-09-21 | Hung-Fu Lee | Helicopter with multiple rotors and variable pitch |
| CN106477040A (en) * | 2016-11-30 | 2017-03-08 | 中国直升机设计研究所 | Rotor driver is manipulated in a kind of axle |
| CN206417186U (en) * | 2017-01-13 | 2017-08-18 | 重庆星环航空科技有限公司 | A kind of steering wheel mounting structure |
| CN108750084A (en) * | 2018-06-04 | 2018-11-06 | 北京海空行科技有限公司 | A kind of co-axial helicopter steerable system |
| CN108945426A (en) * | 2018-06-27 | 2018-12-07 | 中国直升机设计研究所 | A kind of auto-bank unit suitable for a variety of propeller hub configurations |
| CN209192226U (en) * | 2018-08-14 | 2019-08-02 | 深圳联合飞机科技有限公司 | A kind of helicopter blade pitch control mechanism |
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| CN211167404U (en) * | 2019-11-07 | 2020-08-04 | 南京国器智能装备有限公司 | Variable-pitch control mechanism of unmanned helicopter |
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| Publication number | Publication date |
|---|---|
| CN110697038A (en) | 2020-01-17 |
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