CN110697038A - Variable-pitch control mechanism of unmanned helicopter - Google Patents
Variable-pitch control mechanism of unmanned helicopter Download PDFInfo
- Publication number
- CN110697038A CN110697038A CN201911084669.2A CN201911084669A CN110697038A CN 110697038 A CN110697038 A CN 110697038A CN 201911084669 A CN201911084669 A CN 201911084669A CN 110697038 A CN110697038 A CN 110697038A
- Authority
- CN
- China
- Prior art keywords
- steering engine
- mounting seat
- ring
- engine mounting
- control mechanism
- 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.)
- Granted
Links
- 230000007246 mechanism Effects 0.000 title claims abstract description 22
- 238000013016 damping Methods 0.000 claims abstract description 8
- 230000007704 transition Effects 0.000 claims 4
- 230000008859 change Effects 0.000 description 5
- 238000006243 chemical reaction Methods 0.000 description 5
- 230000000694 effects Effects 0.000 description 5
- 238000009434 installation Methods 0.000 description 5
- 230000033001 locomotion Effects 0.000 description 3
- 238000012423 maintenance Methods 0.000 description 3
- 230000035939 shock Effects 0.000 description 3
- 230000005540 biological transmission Effects 0.000 description 2
- 230000003139 buffering effect Effects 0.000 description 2
- 238000010008 shearing Methods 0.000 description 2
- 125000003003 spiro group Chemical group 0.000 description 2
- 238000005299 abrasion Methods 0.000 description 1
- 230000009286 beneficial effect Effects 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
Images
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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Remote Sensing (AREA)
- Toys (AREA)
Abstract
The invention is suitable for the technical field of unmanned helicopters, and provides a variable-pitch control mechanism of an unmanned helicopter, which comprises a body assembly and a rotating assembly, wherein the rotating assembly is used for rotating on the body assembly; through setting up the mounting hole with the damping sleeve makes the steering wheel with the steering wheel mount pad passes through mounting hole and bolt fixed connection, thereby makes the steering wheel mount pad with the steering wheel links to each other be equipped with in the mounting hole the damping sleeve can effectual reduction the impact that the alternating load that produces when the steering wheel moves perpendicularly brought, thereby improves the 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
The main rotor of the existing unmanned helicopter is mainly controlled by two realization forms: one is to refit the control system on the basis of the unmanned helicopter, namely, a linear steering engine is arranged between the original collective pitch rod and an operating lever, the operating lever is pushed by the steering engine to move, the tilting direction and the tilting size of a tilting disk are controlled, and the control of the main rotor of the unmanned helicopter is realized; and secondly, three-angle steering gears are arranged below the tilting disk, the steering gear of the angle steering gears is connected with the tilting disk through a pull rod, and the control of the main rotor of the unmanned helicopter is realized through the combined motion of the three-angle steering gears.
The existing variable-pitch control mechanism of the unmanned helicopter has the advantages that the impact force caused by alternating load generated when the steering engine vertically moves is large, the service life of the steering engine is greatly influenced, and on the other hand, a main rotor control system is complex in structure, large in structural weight and high in failure rate of control connecting rods.
Disclosure of Invention
The invention provides a variable-pitch control mechanism of an unmanned helicopter, aiming at solving the problems that the conventional variable-pitch control mechanism of the unmanned helicopter has large impact force generated when a steering engine vertically moves and greatly influences the service life of the steering engine, and on the other hand, a main rotor control system has a complex structure, large structural weight and high failure rate of a control connecting rod.
The invention is realized in such a way that an unmanned helicopter pitch-changing control mechanism 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 counter-torsion ring, the steering engine mounting seat is positioned above the gear box and is in threaded connection with the gear box, the counter-torsion ring and the steering engine mounting seat are vertically arranged and are in threaded connection with each other, a plurality of mounting holes are formed in the outer side wall of the steering engine mounting seat, and damping sleeves are arranged on the inner side walls of the mounting holes;
the rotating assembly comprises a steering engine, a main shaft and a rotating ring, an immovable ring is arranged on an output shaft of the steering engine, the output shaft of the steering engine is fixedly connected with the immovable ring, one end, far away from the output shaft, of the steering engine is connected with the mounting hole in a threaded mode on the steering engine mounting seat, the rotating ring is located above the immovable ring, and the main shaft penetrates through the rotating ring and the immovable ring and is connected with the steering engine mounting seat in a rotating mode.
Preferably, the steering engine mounting seat comprises a gear box cover plate, a left steering engine mounting seat and a right steering engine mounting seat, wherein the gear box cover plate penetrates through the left steering engine mounting seat and the right steering engine mounting seat and is fixedly connected with the left steering engine mounting seat and the right steering engine mounting seat.
Preferably, a plurality of lightening holes are formed in the upper surfaces of the left steering engine mounting seat and the right steering engine mounting seat.
Preferably, the anti-torsion ring comprises an anti-torsion lower section, a bushing, an anti-torsion middle section and an anti-torsion upper section, the anti-torsion middle section is located above the anti-torsion lower section, and the anti-torsion middle section and the anti-torsion lower section are connected through the bushing;
the upper antitorque conversion section is located above the middle antitorque conversion section, and the upper antitorque conversion section is connected with the middle antitorque conversion section through the bushing.
Preferably, the lower antitwisting section is arranged to be ladder-shaped, the middle antitwisting section is arranged to be ladder-shaped, and the upper antitwisting section is arranged to be clip-shaped.
Preferably, the outer side wall of the lower anti-torsion section is provided with a bolt hole, and the anti-torsion ring and the steering engine mounting seat are fixedly connected through the lower anti-torsion section, the bolt hole and the bolt;
the upper anti-twist section is in threaded connection with the stationary ring.
Preferably, the stationary ring is provided in an X-shape.
Preferably, the movable ring is arranged in a T shape;
a circular groove is further formed in the middle of the steering engine mounting seat, and a bearing is further arranged inside 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 mounting seat and the mounting hole are arranged on the same vertical line.
Preferably, the steering engine is S3302 in model number.
Compared with the prior art, the invention has the beneficial effects that: the steering engine and the steering engine mounting seat are fixedly connected through the mounting holes and the bolts by arranging the mounting holes and the damping sleeves, so that the damping sleeves are arranged in the mounting holes formed in the connection of the steering engine mounting seat and the steering engine, the impact caused by alternating load generated when the steering engine vertically moves can be effectively reduced, and the service life of the steering engine is prolonged; the steering engine and the output shaft of the steering engine are provided with the immobile ring, so that the output shaft of the steering engine directly drives the immobile ring to rotate when moving, the operating connecting rod transmission mechanism of the helicopter is simplified, the main rotor wing operating system is compact in structure, the structural weight is reduced, and the failure rate of the operating connecting rod is reduced.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic view of a mounting structure of a steering engine mounting seat and a turn-back ring according to the present invention;
FIG. 3 is a schematic view of a twist-resistant ring according to the present invention;
in the figure: 1-body component, 11-steering engine mounting seat, 111-gear box cover plate, 112-left steering engine mounting seat, 113-right steering engine mounting seat, 114-lightening hole, 12-gear box, 13-reverse torsion ring, 131-reverse torsion lower section, 132-lining, 133-reverse torsion middle section, 134-reverse torsion upper section, 135-bolt hole, 14-mounting hole, 15-damping sleeve, 16-circular groove, 17-bearing, 2-rotating component, 21-steering engine, 22-main shaft, 23-rotating ring and 24-stationary ring.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
In the description of the present invention, it is to be understood that the terms "length," "width," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used in the orientations and positional relationships indicated in the drawings for convenience in describing the present invention and for simplicity in description, and are not intended to indicate or imply that the referenced devices or elements must have a particular orientation, be constructed in a particular orientation, and be operated in a particular manner, and thus should not be construed as limiting the present invention. Further, in the description of the present invention, "a plurality" means two or more unless specifically defined otherwise.
Referring to fig. 1-3, a variable-pitch control mechanism of an unmanned helicopter comprises a body assembly 1 and a rotating assembly 2 used for rotating on the body assembly 1, wherein the body assembly 1 comprises a steering engine mounting seat 11, a gear box 12 and a torsion ring 13, 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 torsion ring 13 is perpendicular to the steering engine mounting seat 11, the 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 damping sleeves 15 are arranged on the inner side wall of the mounting holes 14;
the rotating assembly 2 comprises a steering engine 21, a main shaft 22 and a movable ring 23, a fixed ring 24 is arranged on an output shaft of the steering engine 21, 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 a mounting hole 14 in the steering engine mounting seat 11, the movable ring 23 is located above the fixed ring 24, and the main shaft 22 penetrates through the movable ring 23 and the fixed ring 24 and is rotatably connected with the steering engine mounting seat 11.
In the embodiment, the steering engine 21, the steering engine mounting seat 11 and the mounting hole 14 are arranged on the same vertical line, because the connecting points of the mounting base of the traditional helicopter control mechanism and the steering engine are 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 tensile force and pressure, and the shearing force is smaller, so that the instability and deformation faults of the push rod often occur, when the steering engine 21, the steering engine mounting seat 11 and the mounting hole 14 are arranged on the same vertical line, the tensile force 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, so that the fault rate can be greatly reduced; through setting up steering wheel mount pad 11 and gear box 12 spiro union for the mounting structure is firm, does not have the installation clearance, improves the driven precision of operating system, through setting up mounting hole 14 and shock attenuation cover 15, make steering wheel mount pad 11 with steering wheel 21 passes through mounting hole 14, shock attenuation cover 15 and bolted connection, make shock attenuation cover 15 can effectively reduce the impact that the alternating load that produces brought when steering wheel 21 vertically moves, thereby improve the life-span of steering wheel 21, through setting up stationary ring 24 and rotating ring 23, make the output shaft of steering wheel 21 move, drive stationary ring 24 and rotate, stationary ring 24 and rotating ring 23 pair, and paste tightly, thereby play sealed effect.
In the embodiment, a steering engine mounting seat 11 is fixed on a gear box 12 through bolts, a main shaft 22 is mounted on a bearing 17 on the steering engine mounting seat 11, then a stationary ring 24 and a rotating ring 23 are respectively connected with the main shaft 22, the connection of the stationary ring 24 and an output shaft of a steering engine 21 is completed, finally a reverse torsion ring 13 is mounted on the stationary ring 24 through bolts and a reverse torsion conversion upper section 134, after the mounting is completed, a power switch of the steering engine 21 is turned on, electric energy is converted into mechanical energy to move inside the steering engine 21, 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 the moment, an operator can rotate the steering engine 21 at any angle between 0 degree and 180 degrees according to instructions, control the inclination direction of the stationary ring 24, so as to control the inclination direction of the stationary ring 23, the moving direction of the unmanned helicopter is also controlled.
Further, steering wheel mount pad 11 comprises gear box apron 111, left side steering wheel mount pad 112 and right side steering wheel mount pad 113, and gear box apron 111 runs through left side steering wheel mount pad 112 and right side steering wheel mount pad 113 to with left side steering wheel mount pad 112 and right side steering wheel mount pad 113 fixed connection.
In this embodiment, left side steering wheel mount pad 112 and right side steering wheel mount pad 113 pass through bolted connection, gear box apron 111, left side steering wheel mount pad 112 and right side steering wheel mount pad 113 also pass through bolt fixed connection, thereby make steering wheel mount pad 11 install alone or dismantle, make operating personnel maintain or when installing, only need dismantle the bolt, just can pull down the maintenance and the installation with the device, and convenient, thereby solved traditional steering wheel installation base and can not dismantle alone, the maintenance difficulty, and the problem of consuming time and wasting force.
Furthermore, a plurality of lightening holes 114 are formed in the upper surfaces of the left steering engine mounting seat 112 and the right steering engine mounting seat 113.
In this embodiment, through setting up lightening hole 114 for when steering wheel mount pad 11 guaranteed structural strength in the installation, can also lighten steering wheel mount pad 11's weight, thereby reduce unmanned aerial vehicle's weight, make unmanned aerial vehicle power promotion performance more obvious on the one hand, on the other hand reduces the accident probability, ensures unmanned aerial vehicle's safety.
Further, the anti-twist ring 13 is composed of an anti-twist lower section 131, a bushing 132, an anti-twist middle section 133 and an anti-twist upper section 134, the anti-twist middle section 133 is located above the anti-twist lower section 131, and the anti-twist middle section 133 and the anti-twist lower section 131 are connected through the bushing 132;
the upper anti-reverse section 134 is located above the middle anti-reverse section 133, and the upper anti-reverse section 134 and the middle anti-reverse section 133 are connected by the bushing 132.
In this embodiment, the anti-torsion ring 13 is divided into three sections by arranging the anti-torsion lower section 131, the anti-torsion middle section 133 and the anti-torsion upper section 134, so that the length of the anti-torsion ring is increased and the interference of the steering engine with the movement of the stationary ring in the total stroke is avoided when compared with a common two-section structure, and the connection of the bushing 132 is arranged, so that the abrasion, vibration and noise of the device are reduced, the maintenance of mechanical equipment is facilitated, and the structure and the manufacturing process of the equipment are simplified.
Further, the lower antitorque segment 131 is configured as a ladder, the middle antitorque segment 133 is configured as a ladder, and the upper antitorque segment 134 is configured as a clip.
In this embodiment, it is ladder-shaped to change hypomere 131 through setting up the antitorque commentaries on classics, make the antitorque commentaries on classics change the cavity that forms in the middle of the hypomere 131, the effectual weight that reduces antitorque commentaries on classics ring 13, thereby convenience when on the one hand is for the installation, in the time of on the other hand material saving, stability is still fine, change middle section 133 through setting up the antitorque commentaries on classics, make antitorque commentaries on classics middle section 133 have stronger stability, change upper segment 134 through setting up the antitorque commentaries on classics and be clip-shaped, make on the one hand and more fasten when installing with immobile ring 24, thereby the effectual axial that prevents immobile ring rotates, the antitorque commentaries on classics of on hand clip-shaped changes the cavity that middle section 133 was formed with antitorque.
Further, a bolt hole 135 is formed in the outer side wall of the lower anti-torsion section 131, and the anti-torsion ring 13 and the steering engine mounting seat 11 are fixedly connected through the lower anti-torsion section 131, the bolt hole 135 and a bolt;
the reverse torque upper section 134 is threadably engaged with the stationary ring 24.
In this embodiment, through setting up bolt hole 135 to install antitorque 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, change upper segment 134 and motionless ring 24 spiro union through setting up antitorque, when making motionless ring 24 rotatory, the effectual axial motion that prevents motionless ring 24, thereby reduce the probability that the accident took place.
Further, the stationary ring 24 is provided in an X shape.
In this embodiment, be the X shape through setting up immobile ring 24 for immobile ring 24 is when rotating through steering wheel 21, and the immobile ring 24 of X shape can effectual balanced flight gyro effect when rotatory, makes the air force moment of torsion effect all offset, makes the flight speed faster, prevents that the air force moment of torsion from haring unmanned aerial vehicle, and the effectual external disturbance that has reduced of immobile ring 24 of X type makes angle output error little simultaneously.
Further, the movable ring 23 is arranged in a T shape;
a circular groove 16 is further formed in the middle of the steering engine mounting seat 11, and a bearing 17 is further arranged inside 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 movable ring 23 is arranged to be T-shaped, so that when the movable ring 23 and the stationary ring 24 are used in cooperation with each other, on one hand, the movable ring 23 of the T-shaped can press down the stationary ring 24, so that the movable ring 23 of the T-shaped can be effectively attached to the stationary ring 23, and the sealing effect is better, and on the other hand, the movable ring 23 of the T-shaped has a buffering effect, so that the buffering fluctuation of the unmanned aerial vehicle is prevented, the influence on the stationary 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, fixed when easy to assemble, and set up bearing 17, be for reducing main shaft 22's rotation damage, make main shaft 22 pivoted effect better, thereby do not move ring 24 pivoted faster.
Furthermore, the steering engine 21, the steering engine mounting seat 11 and the mounting hole 14 are arranged on the same vertical line.
In the embodiment, because the connecting points of the traditional helicopter control mechanism mounting base and the steering engine are 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 large tensile force and pressure, the shearing force is small, so that the instability and deformation faults of the push rod often occur, when the steering engine 21, the steering engine mounting seat 11 and the mounting hole 14 are arranged on the same vertical line, the tensile force and the pressure borne by the steering engine 21 are uniform, and the unstable transmission to the steering engine mounting seat 11 can be realized, so that the fault rate of the type can be greatly reduced
Further, the model number of the steering engine 21 is S3302.
In this embodiment, the model that sets up steering wheel 21 is S3302 for steering wheel 21 rotational frequency is stable, and light in weight makes unmanned aerial vehicle' S weight reduce by a wide margin.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention.
Claims (10)
1. A variable-pitch control mechanism of an unmanned helicopter comprises a body assembly (1) and a rotating assembly (2) rotating on the body assembly (1), and is characterized in that: the body assembly (1) comprises a steering engine mounting seat (11), a gear box (12) and a torsion ring (13), the steering engine mounting seat (11) is located above the gear box (12), the steering engine mounting seat (11) is in threaded connection with the gear box (12), the torsion ring (13) is perpendicular to the steering engine mounting seat (11), the 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 damping sleeves (15) are arranged on the inner side wall of the mounting holes (14);
the rotating assembly (2) comprises a steering engine (21), a main shaft (22) and a movable ring (23), wherein a fixed ring (24) is arranged on an output shaft of the steering engine (21), 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 passed through the mounting hole (14) in the steering engine mounting seat (11) in a screwed mode, the movable ring (23) is located above the fixed ring (24), and the main shaft (22) penetrates through the movable ring (23) and the fixed ring (24) and is rotatably connected with the steering engine mounting seat (11).
2. The pitch control mechanism of an unmanned helicopter of claim 1 wherein: steering wheel mount pad (11) comprise gear box apron (111), left side steering wheel mount pad (112) and right side steering wheel mount pad (113), gear box apron (111) run through left side steering wheel mount pad (112) with right side steering wheel mount pad (113), and with left side steering wheel mount pad (112) with right side steering wheel mount pad (113) fixed connection.
3. The pitch control mechanism of an unmanned helicopter of claim 2 wherein: and a plurality of lightening holes (114) are formed in the upper surfaces of the left steering engine mounting seat (112) and the right steering engine mounting seat (113).
4. The pitch control mechanism of an unmanned helicopter of claim 1 wherein: the anti-twisting ring (13) consists of an anti-twisting lower section (131), a bushing (132), an anti-twisting middle section (133) and an anti-twisting upper section (134), the anti-twisting middle section (133) is positioned above the anti-twisting lower section (131), and the anti-twisting middle section (133) and the anti-twisting lower section (131) are connected through the bushing (132);
the upper antitorque transition section (134) is located above the intermediate antitorque transition section (133), and the upper antitorque transition section (134) and the intermediate antitorque transition section (133) are connected through the bushing (132).
5. The pitch control mechanism of an unmanned helicopter of claim 4 wherein: the reverse-twist-off lower section (131) is arranged to be ladder-shaped, the reverse-twist-off middle section (133) is arranged to be ladder-shaped, and the reverse-twist-off upper section (134) is arranged to be clip-shaped.
6. The pitch control mechanism of an unmanned helicopter of claim 5 wherein: the outer side wall of the reverse-twisting lower section (131) is provided with a bolt hole (135), and the reverse-twisting ring (13) and the steering engine mounting seat (11) are fixedly connected through the reverse-twisting lower section (131), the bolt hole (135) and the bolt;
the upper antitorque section (134) is threadedly engaged with the stationary ring (24).
7. The pitch control mechanism of an unmanned helicopter of claim 1 wherein: the stationary ring (24) is provided in an X-shape.
8. The pitch control mechanism of an unmanned helicopter of claim 1 wherein: the movable ring (23) is arranged in a T shape;
a circular groove (16) is further formed in the middle of the steering engine mounting seat (11), and a bearing (17) is further arranged inside 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).
9. The pitch control mechanism of an unmanned helicopter of claim 1 wherein: the steering engine (21), the steering engine mounting seat (11) and the mounting hole (14) are arranged on the same vertical line.
10. The pitch control mechanism of an unmanned helicopter of claim 1 wherein: the model number 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 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110697038A true CN110697038A (en) | 2020-01-17 |
| CN110697038B CN110697038B (en) | 2024-05-28 |
Family
ID=69204613
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911084669.2A Active CN110697038B (en) | 2019-11-07 | 2019-11-07 | Unmanned helicopter displacement operating mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110697038B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113119085A (en) * | 2021-03-24 | 2021-07-16 | 北京航空航天大学 | Helicopter flight driving robot system |
Citations (10)
| 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 |
| 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 |
-
2019
- 2019-11-07 CN CN201911084669.2A patent/CN110697038B/en active Active
Patent Citations (10)
| 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 |
| 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 |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113119085A (en) * | 2021-03-24 | 2021-07-16 | 北京航空航天大学 | Helicopter flight driving robot system |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110697038B (en) | 2024-05-28 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109703752B (en) | Double-rotor unmanned aerial vehicle | |
| JP2768826B2 (en) | Duct fan and pitch controller for tail rotor of rotary wing aircraft | |
| EP3533710B1 (en) | A passive pitch angle adjustment apparatus | |
| CN101973398A (en) | Tilt rotation driving mechanism for tilt rotation nacelle of tilt rotor craft | |
| US10479494B2 (en) | Rotorcraft tail rotor, a rotorcraft fitted with such a tail rotor, and a method of statically and/or dynamically balancing a rotorcraft tail rotor | |
| CN108313268B (en) | Aileron control system of light aircraft | |
| CA2113179C (en) | Ducted tail rotor for rotary wing aircraft providing torque reaction and yaw attitude control | |
| CN113232852B (en) | Transmission mechanism for tilting rotorcraft wing | |
| CN211167404U (en) | Variable-pitch control mechanism of unmanned helicopter | |
| CN113371191A (en) | Rotor wing tilting mechanism, tilting rotor wing aerocar and flying device | |
| CN110697038A (en) | Variable-pitch control mechanism of unmanned helicopter | |
| KR100558462B1 (en) | A vertical takeoff and landing aircraft | |
| CN112429223A (en) | Straight-wing type bionic flapping-wing flying robot | |
| KR100558463B1 (en) | A vertical takeoff and landing aircraft | |
| CN112550693B (en) | Automatic inclinator structure of unmanned helicopter | |
| US4650400A (en) | Helicopter blade pitch adjusting system | |
| CN115303474A (en) | Electric drive variable-pitch propeller device with large torque output | |
| CN109677603B (en) | Helicopter rotor wing control device and rotor wing device | |
| CN109018334B (en) | Tilt rotor helicopter and transmission device thereof | |
| CN210634749U (en) | Double rotor unmanned plane | |
| CN216734743U (en) | Manipulation mounting structure of tail steering engine and throttle steering engine of unmanned helicopter | |
| CN214930606U (en) | Rotor wing tilting device and autorotation rotor wing aircraft | |
| CN109703757B (en) | Unmanned aerial vehicle rotor wing system | |
| KR100810725B1 (en) | A vertical takeoff and landing aircraft | |
| KR102614592B1 (en) | A cyclic pitch angle adjustment apparatus |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| TA01 | Transfer of patent application right |
Effective date of registration: 20230625 Address after: 210000 building 12-537, 29 buyue Road, Qiaolin street, Pukou District, Nanjing City, Jiangsu Province Applicant after: Nanjing aerospace Guoqi Intelligent Equipment Co.,Ltd. Address before: 210000 4th floor, block B, No.6 Yuhe North Road, Jiangpu street, Jiangbei new district, Nanjing City, Jiangsu Province Applicant before: NANJING GUOQI INTELLIGENT EQUIPMENT Co.,Ltd. Applicant before: NANJING LIJIAN UNMANNED PLANE TECHNOLOGY Co.,Ltd. |
|
| TA01 | Transfer of patent application right | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |