CN204166725U - A kind of analogue means of simple and easy aircraft drive system - Google Patents
A kind of analogue means of simple and easy aircraft drive system Download PDFInfo
- Publication number
- CN204166725U CN204166725U CN201420584233.6U CN201420584233U CN204166725U CN 204166725 U CN204166725 U CN 204166725U CN 201420584233 U CN201420584233 U CN 201420584233U CN 204166725 U CN204166725 U CN 204166725U
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- rudder
- aileron
- horn
- jociey stick
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Abstract
A kind of analogue means of simple and easy aircraft drive system, comprise jociey stick, jociey stick is arranged on pedestal, promote before and after jociey stick, control wheel on jociey stick can clockwise or rotate counterclockwise, fixed pulley group is arranged on pedestal, control wheel is connected with aileron horn group by fixed pulley group, aileron horn group is connected with aileron, the upper and lower spinning movement of aileron is completed through transmission, pedal is connected with rudder horn group, pedal, rudder horn group is arranged on pedestal, rudder horn group is connected with yaw rudder, control the action of yaw rudder left rotation and right rotation, jociey stick is connected with elevator horn group, elevator horn group is connected with elevating rudder, pulled by the front and back of jociey stick and manipulate, complete the spinning movement up and down of elevating rudder, the driver's seat at jociey stick rear is arranged on pedestal, the utility model dramatic represent the whole manipulation process of aircraft and motion conditions, and it is practical and convenient, with low cost, can be used in the teaching practice of flight control system (i.e. kinematic train).
Description
Technical field
The utility model relates to aircraft technical field of mechanical transmission, is specifically related to a kind of analogue means of simple and easy aircraft drive system.
Background technology
Aircraft has very complicated kinematic train, and often through the form of language and picture, flight control system (i.e. kinematic train) is explained in traditional teaching process, not intuitively, not vivid, add the difficulty that study personnel understand, also lack the analogue means of the simple and easy aircraft drive system of teaching on the market.
Summary of the invention
In order to overcome the shortcoming of above-mentioned prior art, the purpose of this utility model is the analogue means providing a kind of simple and easy aircraft drive system, for in the teaching practice to flight control system (i.e. kinematic train), dramatic, easy to use and with low cost.
For achieving the above object, the technical scheme that the utility model is taked is:
A kind of analogue means of simple and easy aircraft drive system, comprise jociey stick 1, jociey stick 1 is installed on the base 2, jociey stick 1 can promote front and back, control wheel on jociey stick 1 can clockwise or rotate counterclockwise, fixed pulley group 6 is installed on the base 2, control wheel is connected with aileron horn group 10 by fixed pulley group 6, aileron horn group 10 is connected with aileron 9, aileron about 9 spinning movement is completed through transmission, pedal 3 is connected with rudder horn group 4, pedal 3, rudder horn group 4 is installed on the base 2, rudder horn group 4 is connected with yaw rudder 8, control the action of yaw rudder 8 left rotation and right rotation, jociey stick 1 is connected with elevator horn group 5, elevator horn group 5 is connected with elevating rudder 7, pulled by the front and back of jociey stick 1 and manipulate, complete the spinning movement up and down of elevating rudder 7, the driver's seat 11 at jociey stick 1 rear is installed on the base 2.
Described elevator horn group 5 comprises elevating rudder horizon bar group 5-1, and one end of elevating rudder horizon bar group 5-1 is connected with jociey stick 1, and the other end of elevating rudder horizon bar group 5-1 is connected with elevating rudder fork 5-2 bottom, and elevating rudder fork 5-2 top is connected with elevating rudder 7.
Described rudder horn group 4 comprises yaw rudder horizon bar group 4-1, one end of yaw rudder horizon bar group 4-1 is connected with pedal 3, the yaw rudder horizon bar group 4-1 other end is connected with connecting link 4-3 bottom by spring bearing 4-2, and connecting link 4-3 top is connected with yaw rudder 8.
Described aileron horn group 10 comprises aileron front roll bar 10-1, is connected in the middle part of aileron front roll bar 10-1 with fixed pulley group 6, and aileron front roll bar 10-1 two ends are connected with aileron 9 by fork 10-2 after aileron.
Described fixed pulley group 6 is nylon material and is connected by wire rope.
Described pedestal 2 is U-steel frame, and rudder horn group 4, elevator horn group 5, aileron horn group 10 are aluminum alloy materials, installs on the base 2, can realize translation and rotation.
Due to the utility model by simple physical construction and transmission to aircraft three control surfaces---the control of elevating rudder, yaw rudder and aileron, realize aircraft around transverse axis, vertical pivot, vertical axes, to complete the adjustment to flight attitude, completes and simulates general aircraft handling, the utility model dramatic represent the whole manipulation process of aircraft and motion conditions, and practical and convenient, with low cost, can be used in the teaching practice of flight control system (i.e. kinematic train).
Accompanying drawing explanation
Fig. 1 is one-piece construction schematic diagram of the present utility model.
Fig. 2 is the gear train schematic diagram of elevating rudder 7 of the present utility model action.
Fig. 3 is the gear train schematic diagram of yaw rudder 8 of the present utility model action.
Fig. 4 is the gear train schematic diagram of aileron 9 of the present utility model action.
Embodiment
Below in conjunction with accompanying drawing, the utility model is described in detail.
With reference to Fig. 1, a kind of analogue means of simple and easy aircraft drive system, comprise jociey stick 1, jociey stick 1 is installed on the base 2, promote before and after jociey stick 1, control wheel on jociey stick 1 can clockwise or rotate counterclockwise, fixed pulley group 6 is installed on the base 2, control wheel is connected with aileron horn group 10 by fixed pulley group 6, rotated by control wheel and manipulate, aileron horn group 10 is connected with aileron 9, aileron about 9 spinning movement is completed through transmission, pedal 3 is connected with rudder horn group 4, pedal 3, rudder horn group 4 is installed on the base 2, rudder horn group 4 is connected with yaw rudder 8, control the action of yaw rudder 8 left rotation and right rotation, jociey stick 1 is connected with elevator horn group 5, elevator horn group 5 is connected with elevating rudder 7, pulled by the front and back of jociey stick 1 and manipulate, complete the spinning movement up and down of elevating rudder 7, the driver's seat 11 at jociey stick 1 rear is installed on the base 2.
With reference to Fig. 2, described elevator horn group 5 comprises elevating rudder horizon bar group 5-1, one end of elevating rudder horizon bar group 5-1 is connected with jociey stick 1, and the other end of elevating rudder horizon bar group 5-1 is connected with elevating rudder fork 5-2 bottom, and elevating rudder fork 5-2 top is connected with elevating rudder 7.
With reference to Fig. 3, described rudder horn group 4 comprises yaw rudder horizon bar group 4-1, one end of yaw rudder horizon bar group 4-1 is connected with pedal 3, and the yaw rudder horizon bar group 4-1 other end is connected with connecting link 4-3 bottom by spring bearing 4-2, and connecting link 4-3 top is connected with yaw rudder 8.
With reference to Fig. 4, described aileron horn group 10 comprises aileron front roll bar 10-1, is connected in the middle part of aileron front roll bar 10-1 with fixed pulley group 6, and aileron front roll bar 10-1 two ends are connected with aileron 9 by fork 10-2 after aileron.
Described fixed pulley group 6 is nylon material and is connected by wire rope.
Described pedestal 2 is U-steel frame, and rudder horn group 4, elevator horn group 5, aileron horn group 10 are aluminum alloy materials, installs on the base 2, can realize translation and rotation.
Principle of work of the present utility model is:
See figures.1.and.2, pull back jociey stick 1, drive the elevating rudder horizon bar group 5-1 translation forward of installing on the base 2, elevating rudder fork 5-2 is rotated counterclockwise, promote elevating rudder 7 to upward deflect, as shown in Figure 2, the downward additional lift at this moment on tailplane produces the moment to airplane pitch axis, makes nose-up; Otherwise to stick-forword movement 1, then elevating rudder 7 deflects down, and makes nose dip.
With reference to Fig. 1 and Fig. 3, pedal 3 is installed on the base 2, when trampling Vehicular left pedal, yaw rudder horizon bar group 4-1 translation forward, drive the connecting link 4-3 be arranged in spring bearing 4-2, yaw rudder 8 is turned clockwise, as shown in Figure 3, aerodynamic force on aircraft vertical empennage produces the moment to aircraft vertical shaft, is that plane nose deflects left; Otherwise when trampling right steps, rudder of aircraft 8 deflects to the right, and head also deflects to the right.
With reference to Fig. 1 and Fig. 4, rotate counterclockwise the control wheel on jociey stick 1, by fixed pulley group 6, drive wire rope such as Fig. 4 to move, fixed pulley group 6 drives aileron front roll bar 10-1 to rotate counterclockwise, after aileron, fork 10-2 rotates clockwise, thus drives aileron 9, and port aileron upwards, starboard aileron is downward, at this moment port wing lift reduces, and starboard wing lift increases, and is that aircraft is tilted to the left; Otherwise rotate clockwise the control wheel on jociey stick 1, then upwards port aileron is downward for starboard aileron, and aircraft is tilted to the right.The utility model dramatic represent the whole manipulation process of aircraft and motion conditions, and practical and convenient, with low cost, can be used in the teaching practice of flight control system (i.e. kinematic train).
Claims (6)
1. the analogue means of a simple and easy aircraft drive system, comprise jociey stick (1), it is characterized in that: jociey stick (1) is arranged on pedestal (2), promote before and after jociey stick (1), control wheel on jociey stick (1) can clockwise or rotate counterclockwise, fixed pulley group (6) is arranged on pedestal (2), control wheel is connected with aileron horn group (10) by fixed pulley group (6), aileron horn group (10) is connected with aileron (9), aileron (9) spinning movement is up and down completed through transmission, pedal (3) is connected with rudder horn group (4), pedal (3), rudder horn group (4) is arranged on pedestal (2), rudder horn group (4) is connected with yaw rudder (8), control yaw rudder (8) left rotation and right rotation action, jociey stick (1) is connected with elevator horn group (5), elevator horn group (5) is connected with elevating rudder (7), pulled by the front and back of jociey stick (1) and manipulate, complete the spinning movement up and down of elevating rudder (7), the driver's seat (11) at jociey stick (1) rear is arranged on pedestal (2).
2. the analogue means of a kind of simple and easy aircraft drive system according to claim 1, it is characterized in that: described elevator horn group (5) comprises elevating rudder horizon bar group (5-1), one end of elevating rudder horizon bar group (5-1) is connected with jociey stick (1), the other end of elevating rudder horizon bar group (5-1) is connected with elevating rudder fork (5-2) bottom, and elevating rudder fork (5-2) top is connected with elevating rudder (7).
3. the analogue means of a kind of simple and easy aircraft drive system according to claim 1, it is characterized in that: described rudder horn group (4) comprises yaw rudder horizon bar group (4-1), one end of yaw rudder horizon bar group (4-1) is connected with pedal (3), yaw rudder horizon bar group (4-1) other end is connected with connecting link (4-3) bottom by spring bearing (4-2), and connecting link (4-3) top is connected with yaw rudder (8).
4. the analogue means of a kind of simple and easy aircraft drive system according to claim 1, it is characterized in that: described aileron horn group (10) comprises aileron front roll bar (10-1), aileron front roll bar (10-1) middle part is connected with fixed pulley group (6), and aileron front roll bar (10-1) two ends are connected with aileron (9) by fork (10-2) after aileron.
5. the analogue means of a kind of simple and easy aircraft drive system according to claim 1, is characterized in that: described fixed pulley group (6) is for nylon material and connected by wire rope.
6. the analogue means of a kind of simple and easy aircraft drive system according to claim 1, it is characterized in that: described pedestal (2) is U-steel frame, rudder horn group (4), elevator horn group (5), aileron horn group (10) are aluminum alloy materials, be arranged on pedestal (2), translation and rotation can be realized.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420584233.6U CN204166725U (en) | 2014-10-10 | 2014-10-10 | A kind of analogue means of simple and easy aircraft drive system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420584233.6U CN204166725U (en) | 2014-10-10 | 2014-10-10 | A kind of analogue means of simple and easy aircraft drive system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204166725U true CN204166725U (en) | 2015-02-18 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420584233.6U Expired - Fee Related CN204166725U (en) | 2014-10-10 | 2014-10-10 | A kind of analogue means of simple and easy aircraft drive system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204166725U (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107161324A (en) * | 2017-06-12 | 2017-09-15 | 河北天启通宇航空器材科技发展有限公司 | Gyroplane empennage assembly structure |
| CN108389499A (en) * | 2018-05-16 | 2018-08-10 | 航成（天津）科技有限公司 | A kind of rope driven rudder of aircraft safeguards training device |
| CN108630055A (en) * | 2018-05-16 | 2018-10-09 | 航成（天津）科技有限公司 | A kind of rope driven aircraft evelvator safeguards training device |
| WO2019088952A2 (en) | 2017-07-03 | 2019-05-09 | Tusas- Turk Havacilik Ve Uzay Sanayii Anonim Sirketi | An aerodynamic load test system |
| CN112053620A (en) * | 2020-09-30 | 2020-12-08 | 山东太古飞机工程有限公司 | Training aid for airplane transmission adjustment and calibration |
| CN114180030A (en) * | 2021-12-29 | 2022-03-15 | 浙江万丰飞机制造有限公司 | Light airplane rudder control device |
| CN114937391A (en) * | 2022-05-18 | 2022-08-23 | 中电科芜湖钻石飞机制造有限公司 | Teaching aid for airplane transmission system |
-
2014
- 2014-10-10 CN CN201420584233.6U patent/CN204166725U/en not_active Expired - Fee Related
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107161324A (en) * | 2017-06-12 | 2017-09-15 | 河北天启通宇航空器材科技发展有限公司 | Gyroplane empennage assembly structure |
| WO2019088952A2 (en) | 2017-07-03 | 2019-05-09 | Tusas- Turk Havacilik Ve Uzay Sanayii Anonim Sirketi | An aerodynamic load test system |
| WO2019088952A3 (en) * | 2017-07-03 | 2019-07-25 | Tusas- Turk Havacilik Ve Uzay Sanayii Anonim Sirketi | An aerodynamic load test system |
| CN108389499A (en) * | 2018-05-16 | 2018-08-10 | 航成（天津）科技有限公司 | A kind of rope driven rudder of aircraft safeguards training device |
| CN108630055A (en) * | 2018-05-16 | 2018-10-09 | 航成（天津）科技有限公司 | A kind of rope driven aircraft evelvator safeguards training device |
| CN112053620A (en) * | 2020-09-30 | 2020-12-08 | 山东太古飞机工程有限公司 | Training aid for airplane transmission adjustment and calibration |
| CN112053620B (en) * | 2020-09-30 | 2024-05-24 | 山东太古飞机工程有限公司 | Be used for aircraft transmission timing exercise teaching aid |
| CN114180030A (en) * | 2021-12-29 | 2022-03-15 | 浙江万丰飞机制造有限公司 | Light airplane rudder control device |
| CN114180030B (en) * | 2021-12-29 | 2024-02-13 | 浙江万丰飞机制造有限公司 | Steering device for light aircraft rudder |
| CN114937391A (en) * | 2022-05-18 | 2022-08-23 | 中电科芜湖钻石飞机制造有限公司 | Teaching aid for airplane transmission system |
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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: 20150218 Termination date: 20171010 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |