CN203767067U - Centre-of-gravity shift yawing device for helicopters - Google Patents
Centre-of-gravity shift yawing device for helicopters Download PDFInfo
- Publication number
- CN203767067U CN203767067U CN201420054478.8U CN201420054478U CN203767067U CN 203767067 U CN203767067 U CN 203767067U CN 201420054478 U CN201420054478 U CN 201420054478U CN 203767067 U CN203767067 U CN 203767067U
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- China
- Prior art keywords
- guide rail
- helicopter
- centre
- gravity shift
- rail
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Abstract
The utility model discloses a centre-of-gravity shift yawing device for helicopters. The centre-of-gravity shift yawing device comprises a straight guide rail, a central motor, a rail motor, a heavy object and a circumferential guide rail, wherein the circumferential guide rail is parallel to a rotating plane of a main propeller, the circle center of the circumferential guide rail is located on the axial line of a rotating shaft of the main propeller, the central motor is located at the circle center of the circumferential guide rail, one end of the straight guide rail is fastened with a rotating shaft of the central motor, the other end of the straight guide rail is slidably connected with the circumferential guide rail, the straight guide rail is provided with the rail motor which can carry out reciprocating motion along the rail, and the heavy object is fixed on the rail motor. According to the utility model, a helicopter can achieve a yawing effect by adopting a simple main rotor structure, and the original flight control basic functions of the helicopter are not affected, therefore, compared with existing helicopter yawing control modes, the centre-of-gravity shift yawing device for helicopters disclosed by the utility model has the advantages of good safety, strong adaptability, simple structure and low cost.
Description
Technical field
The utility model relates to a kind of helicopter flight control device, is specifically related to a kind of helicopter centre-of gravity shift yaw device.
Background technology
The control of helicopter can be divided into vertical control, direction control, laterally control and longitudinal control etc., wherein longitudinally control and can be described as yawed flight control, and the mode of control all realizes by rotor.Specifically, except empennage can be controlled left and right turn, yawed flight is to tilt towards corresponding direction by main rotor propeller hub, and now auto-bank unit drives propellerpiston to tilt towards corresponding direction, thereby the horizontal component of generation the party lift upwards reaches the object of controlling heading.This yaw device complex structure, safety performance is lower, and military helicopter is also existed to the poor feature of barrier propterty, and production and maintenance cost are higher.
Utility model content
Goal of the invention: in order to overcome the defect existing in prior art, the utility model provides a kind of helicopter centre-of gravity shift yaw device simple in structure.
Technical scheme: a kind of helicopter centre-of gravity shift of the utility model yaw device, comprise straight guide, middle electrocardiograph, orbit motor, weight and circumference guide rail, described circumference guide rail is parallel with the plane of rotation of main screw, the circumference guide rail center of circle is positioned on the axis of main screw S. A., described middle electrocardiograph is positioned at circumference guide rail circle centre position, the rotating shaft of described straight guide one end and middle electrocardiograph is fixed, the other end and circumference guide rail sliding block joint, on straight guide, being provided with can be along the reciprocating orbit motor of its track, and described weight is fixed on orbit motor.
The guide rail that described straight guide and circumference guide rail adopt manganese steel material to make.
This device is for model helicopter, and described weight is battery.
Beneficial effect: the utility model makes helicopter adopt simple main rotor structure just can reach driftage effect, and do not affect the original flight control of helicopter basic function, compare existing helicopter driftage mode and have advantages of that safety is good, strong adaptability, simple in structure, with low cost.
Brief description of the drawings
Fig. 1 is the utility model integral structure schematic diagram.
Fig. 2 is the utility model running part structural representation.
Detailed description of the invention
Embodiment: as Fig. 1, shown in Fig. 2, the helicopter centre-of gravity shift yaw system of the present embodiment, comprise straight guide 1, middle electrocardiograph 2, orbit motor 3, weight 4 and circumference guide rail 5, described circumference guide rail 5 is parallel with the plane of rotation of main screw 6, the center of circle of circumference guide rail 5 is positioned on the axis of main screw 6 S. A.s, described middle electrocardiograph 2 is positioned at the circle centre position of circumference guide rail 5, the rotating shaft of described straight guide 1 one end and middle electrocardiograph 2 is fixed, the other end and circumference guide rail 5 sliding block joints, on straight guide 1, being provided with can be along the reciprocating orbit motor 3 of its track, described weight 4 is fixed on orbit motor 3.Wherein, this device is for model helicopter, and weight 4 is battery, and straight guide 1 and circumference guide rail 5 adopt manganese steel material.
In the present embodiment, straight guide 1 can rotate around middle electrocardiograph 2 in the orbit plane parallel with main screw 6 plane of rotations, the weight 4 that is provided with orbit motor 3 on straight guide 1 and drives, orbit motor 3 can move back and forth by gear driven weight 4 on straight guide 1.
When needing helicopter hovering in helicopter flight process or moving up and down; chaufeur makes weight 4 move to the circle centre position of above-mentioned orbit plane by control system; make helicopter centre-of gravity shift to main screw 6 S. A. extended lines; now; main screw 6 plane of rotation levels, then by regulating engine output realize helicopter in hover or move up and down.
When helicopter need fly forward, in control system manipulation, electrocardiograph 2 drives straight guide 1 to turn to, make it to point to heading, move forward weight 4, now helicopter center of gravity reach, causes main screw 6 plane of rotations to turn forward again, strengthen engine output simultaneously, main screw 6 power produce component backward, and component and gravitational equilibrium downwards can realize flight forward.
Backward, left and right flight can adopt similar operation to realize.
The above is only preferred implementation of the present utility model; be noted that for those skilled in the art; do not departing under the prerequisite of the utility model principle; can also make some improvements and modifications, these improvements and modifications also should be considered as protection domain of the present utility model.
Claims (3)
1. a helicopter centre-of gravity shift yaw device, it is characterized in that: comprise straight guide, middle electrocardiograph, orbit motor, weight and circumference guide rail, described circumference guide rail is parallel with the plane of rotation of main screw, the circumference guide rail center of circle is positioned on the axis of main screw S. A., described middle electrocardiograph is positioned at circumference guide rail circle centre position, the rotating shaft of described straight guide one end and middle electrocardiograph is fixed, the other end and circumference guide rail sliding block joint, on straight guide, being provided with can be along the reciprocating orbit motor of its track, and described weight is fixed on orbit motor.
2. a kind of helicopter centre-of gravity shift yaw device according to claim 1, is characterized in that: the guide rail that described straight guide and circumference guide rail adopt manganese steel material to make.
3. a kind of helicopter centre-of gravity shift yaw device according to claim 1, is characterized in that: this device is for model helicopter, and described weight is battery.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420054478.8U CN203767067U (en) | 2014-01-28 | 2014-01-28 | Centre-of-gravity shift yawing device for helicopters |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420054478.8U CN203767067U (en) | 2014-01-28 | 2014-01-28 | Centre-of-gravity shift yawing device for helicopters |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203767067U true CN203767067U (en) | 2014-08-13 |
Family
ID=51284288
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420054478.8U Expired - Fee Related CN203767067U (en) | 2014-01-28 | 2014-01-28 | Centre-of-gravity shift yawing device for helicopters |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203767067U (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105966179A (en) * | 2016-05-19 | 2016-09-28 | 贵州詹阳动力重工有限公司 | All-terrain vehicle |
| CN105966610A (en) * | 2016-06-29 | 2016-09-28 | 南京信息工程大学 | Centre-of-gravity shift and yaw single-rotor helicopter |
| CN106081086A (en) * | 2016-08-03 | 2016-11-09 | 安阳全丰航空植保科技股份有限公司 | The dynamic many rotors agricultural plant protection unmanned helicopter flight attitude regulation device of oil |
| CN106218877A (en) * | 2016-08-03 | 2016-12-14 | 安阳全丰航空植保科技股份有限公司 | The dynamic many rotors plant protection unmanned plane during flying pose adjustment changeable device of oil |
| CN109421921A (en) * | 2017-08-24 | 2019-03-05 | 臧晓今 | A kind of tilt rotor aircraft method that actively intervention controls center of gravity |
| CN112124555A (en) * | 2020-09-28 | 2020-12-25 | 广州蜃境信息科技有限公司 | High-end unmanned aerial vehicle |
| CN112550508A (en) * | 2020-12-03 | 2021-03-26 | 北京理工大学 | Double-rotor wheel type ground/wall movement robot |
-
2014
- 2014-01-28 CN CN201420054478.8U patent/CN203767067U/en not_active Expired - Fee Related
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105966179A (en) * | 2016-05-19 | 2016-09-28 | 贵州詹阳动力重工有限公司 | All-terrain vehicle |
| CN105966179B (en) * | 2016-05-19 | 2018-08-24 | 贵州詹阳动力重工有限公司 | A kind of all-terrain vehicle |
| CN105966610A (en) * | 2016-06-29 | 2016-09-28 | 南京信息工程大学 | Centre-of-gravity shift and yaw single-rotor helicopter |
| CN106081086A (en) * | 2016-08-03 | 2016-11-09 | 安阳全丰航空植保科技股份有限公司 | The dynamic many rotors agricultural plant protection unmanned helicopter flight attitude regulation device of oil |
| CN106218877A (en) * | 2016-08-03 | 2016-12-14 | 安阳全丰航空植保科技股份有限公司 | The dynamic many rotors plant protection unmanned plane during flying pose adjustment changeable device of oil |
| CN109421921A (en) * | 2017-08-24 | 2019-03-05 | 臧晓今 | A kind of tilt rotor aircraft method that actively intervention controls center of gravity |
| CN112124555A (en) * | 2020-09-28 | 2020-12-25 | 广州蜃境信息科技有限公司 | High-end unmanned aerial vehicle |
| CN112550508A (en) * | 2020-12-03 | 2021-03-26 | 北京理工大学 | Double-rotor wheel type ground/wall movement robot |
| CN112550508B (en) * | 2020-12-03 | 2021-11-09 | 北京理工大学 | Double-rotor wheel type floor movement robot |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140813 Termination date: 20170128 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |