CN202670092U - Light aircraft flap control device - Google Patents
Light aircraft flap control device Download PDFInfo
- Publication number
- CN202670092U CN202670092U CN 201220257762 CN201220257762U CN202670092U CN 202670092 U CN202670092 U CN 202670092U CN 201220257762 CN201220257762 CN 201220257762 CN 201220257762 U CN201220257762 U CN 201220257762U CN 202670092 U CN202670092 U CN 202670092U
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- CN
- China
- Prior art keywords
- wing flap
- flap
- control
- circuit
- controller
- 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.)
- Expired - Lifetime
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Abstract
The utility model discloses a light aircraft flap control device, which comprises a flap (7), a flap control pipe (5) and a linear motor (4), wherein a control end of the linear motor (4) is connected with a flap controller (1), the flap controller (1) is connected with a shift control switch and a power supply (2), a push rod of the linear motor (4) is in transmission connection with the flap control pipe (5) by a swinging arm (6), and the flap control pipe (5) drives the flap (7) to rotate. Only a flap target angle is required to be selected, the controller automatically controls the flap to reach a target position, the light aircraft flap control device is simple to operate, has high adjustability and high control precision, and manipulation efficiency and flying safety are improved.
Description
Technical field
The utility model relates to a kind of wing flap control setup, especially relates to a kind of aviette wing flap controller and control setup.
Background technology
Wing flap be used for to increase lift, improve the taking off of aircraft, landing data, and is significant to handling and the safety of aircraft.The direct impact of the angle that wing flap is transferred is taken off, the size of the lift when landing.M/C in the past is difficult to grasp the angle of wing flap, need to carry out angle and detect and show; Angle continuous control or step by step control are generally adopted in existing electronic control, also need to increase the wing flap angle and detect and the electronic devices and components that show, could hold the angle of wing flap reality.
The utility model content
Technical problem to be solved in the utility model provides a kind of control accuracy height, controls efficient to the aviette wing flap control setup high with flight safety.
In order to solve the problems of the technologies described above, the aviette wing flap control setup that the utility model provides, comprise wing flap, wing flap control tube and linear electric motors, the control end of described linear electric motors is connected with the wing flap controller, described wing flap controller is connected with gear master cock and power supply, and the push rod of described linear electric motors and described wing flap control tube are in transmission connection.
Described gear master cock is the fourth gear master cock.
The push rod of described linear electric motors is in transmission connection by rocking arm and described wing flap control tube.
Described wing flap controller comprises circuit card, and circuit card is installed in the control capsule, and described circuit card comprises by the selection circuit that is electrically connected, follows circuit, protective circuit, comparator circuit and driving circuit.
Adopt the aviette wing flap control setup of technique scheme, by handling the fourth gear master cock, select the angle on target position of wing flap, the wing flap controller is according to the selected switch position, the push rod expanding-contracting action of control linear electric motors, the push rod of linear electric motors promotes or spurs the rocking arm of wing flap control tube, and rocking arm drives the wing flap control tube and rotates, the wing flap control tube drives wing flap and rotates, until rest on this position after reaching selected angle on target position.
The utility model is different from wing flap control commonly used, can directly select the required angle that reaches, rather than continuous control or select in order the step by step control of adjacent shelves, as long as select required angle, controller is automatically controlled wing flap and is reached the target location, control accuracy is high, has improved and has controlled efficient and flight safety.
The utility model is as long as select the wing flap angle on target, and controller is automatically controlled wing flap and reached the target location, and simple to operate, controllability is strong, and control accuracy is high, has improved and has controlled efficient and flight safety.
Description of drawings
Fig. 1 is wing flap control setup structural representation of the present utility model.
Fig. 2 is wing flap controller circuitry module composition frame chart of the present utility model.
The specific embodiment
The utility model is described in further detail below in conjunction with the drawings and specific embodiments.
Referring to Fig. 1, the control end of linear electric motors 4 is connected with wing flap controller 1, and wing flap controller 1 is connected with fourth gear master cock 3 and power supply 2, and the push rod of linear electric motors 4 is in transmission connection by rocking arm 6 and wing flap control tube 5.
Referring to Fig. 1, fourth gear master cock 3 given signals are to wing flap controller 1, and wing flap controller 1 output signal also drives linear electric motors 4 actions, and the push rod of linear electric motors 4 promotes wing flap control tube 5 and drives wing flaps 7 and rotate, and reach the given angle of fourth gear master cock 3.
Referring to Fig. 2, wing flap controller 1 comprises circuit card, and circuit card is installed in the control capsule, is fixed, vibrationproof and insulation processing, and circuit card comprises to be selected circuit 8, follow circuit 9, protective circuit 10, comparator circuit 11, driving circuit 12.
Select circuit 8 to set 4 grades, 4 different angles of the corresponding wing flap 7 of difference, corresponding with it, the length that the push rod of desired linear electric motors 4 stretches out also has 4.Select the voltage of circuit 8 every grade of outputs, the feedback voltage when reaching corresponding length with the push rod of linear electric motors 4 equates.One grade in 4 grades that select circuit 8 is connected respectively in four positions of fourth gear master cock 3, to selecting circuit 8 given position instructions, selects circuit 8 to output signal to and follows circuit 9.
Follow circuit 9 outputs 2 road signals, 1 tunnel break-make through protective circuit 10 control linear electric motors 4 circuit; 1 the tunnel passes through the direction that comparator circuit 11 is controlled the pushrod movement of linear electric motors 4 in addition.
When wing flap controller 1 or 8 outages of selection circuit, when perhaps selecting the output of circuit 8 no signals, follow circuit 9 no-outputs, protective circuit 10 output signals disconnect the circuit of linear electric motors 4, make the push rod of linear electric motors 4 keep original position to be failure to actuate.
Comparator circuit 11 is relatively followed the output voltage of circuit 9 and the feedback voltage of linear electric motors 4, when the desired push rod extension elongation of wing flap angle of selecting circuit 8 to select during greater than the actual extension elongation of push rod, comparator circuit 11 output forward signals make push rod continue to stretch out to driving circuit 12, otherwise output reverse signal driving circuit makes push rod do opposite action, when the desired push rod extension elongation of wing flap angle of selecting equals the actual extension elongation of push rod in the permissible error scope, the comparator circuit non-output signal.
Driving circuit 12 receives the signal of comparator circuit 11 outputs, when the signal that receives is forward signal, and control relay output, the push rod of control linear electric motors 4 extends outward; When the signal that receives is reverse signal, control relay output, the inward indentation of push rod of control linear electric motors 4; When comparator circuit 11 non-output signal, the relay no-output, linear electric motors are failure to actuate.
The utility model is different from wing flap control commonly used, can directly select the required angle that reaches, rather than continuous control or select in order the step by step control of adjacent shelves, as long as select required angle, controller is automatically controlled wing flap and is reached the target location, control accuracy is high, has improved and has controlled efficient and flight safety.
Claims (4)
1. aviette wing flap control setup, comprise wing flap (7) and wing flap control tube (5), it is characterized in that: the control end of linear electric motors (4) is connected with wing flap controller (1), described wing flap controller (1) is connected with gear master cock and power supply (2), and the push rod of described linear electric motors (4) and described wing flap control tube (5) are in transmission connection.
2. according to right 1 described aviette wing flap control setup, it is characterized in that: described gear master cock is fourth gear master cock (3).
3. according to right 1 or 2 described aviette wing flap control setups, it is characterized in that: the push rod of described linear electric motors (4) is in transmission connection by rocking arm (6) and described wing flap control tube (5).
4. according to right 1 or 2 described aviette wing flap control setups; it is characterized in that: described wing flap controller (1) comprises circuit card; circuit card is installed in the control capsule, and described circuit card comprises by the selection circuit (8) that is electrically connected, follows circuit (9), protective circuit (10), comparator circuit (11) and driving circuit (12).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220257762 CN202670092U (en) | 2012-06-01 | 2012-06-01 | Light aircraft flap control device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220257762 CN202670092U (en) | 2012-06-01 | 2012-06-01 | Light aircraft flap control device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202670092U true CN202670092U (en) | 2013-01-16 |
Family
ID=47491014
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220257762 Expired - Lifetime CN202670092U (en) | 2012-06-01 | 2012-06-01 | Light aircraft flap control device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202670092U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106428529A (en) * | 2016-09-23 | 2017-02-22 | 江西洪都航空工业集团有限责任公司 | Control mechanism for trailing edge flap of agriculture light airplane |
-
2012
- 2012-06-01 CN CN 201220257762 patent/CN202670092U/en not_active Expired - Lifetime
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106428529A (en) * | 2016-09-23 | 2017-02-22 | 江西洪都航空工业集团有限责任公司 | Control mechanism for trailing edge flap of agriculture light airplane |
| CN106428529B (en) * | 2016-09-23 | 2018-08-24 | 江西洪都航空工业集团有限责任公司 | A kind of agricultural light aerocraft trailing edge flap control mechanism |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20130116 |