CN105498250A - Azimuth controller applicable to aircraft - Google Patents
Azimuth controller applicable to aircraft Download PDFInfo
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- CN105498250A CN105498250A CN201410546407.4A CN201410546407A CN105498250A CN 105498250 A CN105498250 A CN 105498250A CN 201410546407 A CN201410546407 A CN 201410546407A CN 105498250 A CN105498250 A CN 105498250A
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- position controller
- aircraft position
- aviation aircraft
- applicable
- tail vane
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Abstract
The invention provides an azimuth controller applicable to an aircraft. The azimuth controller is composed of a main body and an integrated control chip, wherein a kinetic energy display signal lamp and a plurality of control buttons are arranged on a panel; the control buttons include a mode conversion switch, a positive and negative direction control button, a retarded regulator and a maximum stroke regulator; and the various control buttons are electrically connected to the integrated control chip. According to the azimuth controller applicable to the aircraft, an inductor is integrally combined with the controller and the modes of a steering engine are switched and selected by virtue of the mode conversion switch; therefore, the azimuth controller is not only applicable to a digital steering engine but also suitable for an analog steering engine.
Description
Technical field
The present invention relates to a kind of model plane product, relate to the applicable aviation aircraft position controller on a kind of model of an airplane specifically.
Background technology
When mould aircraft is in hover state aloft, be subject to blowing of crosswind sometimes, now the tail vane of helicopter can produce the phenomenon of horizontal direction skew, for correcting this shift phenomenon, the applicable aviation aircraft position controller meeting sending control signal being installed on helicopter tail vane, to tail vane steering wheel, resists the skew of tail vane with contrary direction.When tail vane stops skew, the control signal being suitable for aviation aircraft position controller also disappears thereupon.If when crosswind blows helicopter constantly, tail vane can be caused constantly to offset, now be suitable for the skew that aviation aircraft position controller can resist tail vane always, until tail vane moves to leeward, weathercock effect that Here it is, thus cause tail vane to produce shift phenomenon, and original position cannot be kept; Secondly, tradition is suitable for aviation aircraft position controller and only has when the tail vane of helicopter moves, and just meeting sending control signal is to tail vane steering wheel, when tail vane stops mobile, control signal also makes zero thereupon, thus causes applicable aviation aircraft position controller cannot control tail vane steering wheel in time; In addition, traditional applicable aviation aircraft position controller volume is comparatively large, and heavier-weight, can consume energy during aircraft flight, thus decreases the flight time of aircraft.
Therefore, being suitable for the many disadvantages of aviation aircraft position controller to overcome tradition, urgently providing that a kind of manipulation is flexible, mobility is good, and modest, the lightweight applicable aviation aircraft position controller of build.
Summary of the invention
The object of this invention is to provide a kind of manipulation flexibly, mobility is good, and the applicable aviation aircraft position controller that build is modest, lightweight, flight resistance is little.
The invention provides one and be suitable for aviation aircraft position controller, it has the body of control surface by one and the integrating control chip be built in wherein forms, panel is provided with Fumction display signal lamp and several control buttons, control button comprises mode conversion switch, forward and reverse control button, delays adjuster, range adjuster, and each control button and integrating control chip are electrically connected.
The model of an airplane is provided with further the receiving system of tail vane steering wheel, motor and reception remote controller control signal, this is suitable for aviation aircraft position controller and also comprises the error transfer factor device and tail vane adjuster of being drawn by integrating control chip further, the sensitivity channel of error transfer factor device and receiving system is electrically connected, and tail vane adjuster and tail vane steering wheel are electrically connected.
Compared with prior art, applicable aviation aircraft position controller of the present invention has the following advantages:
(1) build slight of stature, lighter in weight, thus be convenient to be installed on aircraft, and effectively can reduce flight resistance, thus reduce flight energy consumption, increase the cruising time of mould aircraft;
(2) inductor and controller are combined as a whole, and by the pattern of the changeable selection steering wheel of mode conversion switch, make it not be only applicable to data signal steering wheel, are also suitable for analog signal steering wheel;
(3) the running speed of tail vane control signal can be adjusted by control lag adjustment knob, when being applicable to slow steering wheel, by increasing the mode of time delay, eliminating and turning over phenomenon.
For making the present invention easier to understand, set forth a kind of specific embodiment being suitable for aviation aircraft position controller of the present invention further below in conjunction with accompanying drawing.
Accompanying drawing explanation
Fig. 1 is the operating surface structural representation that the present invention is suitable for aviation aircraft position controller;
Fig. 2 is the structural representation that the present invention is suitable for aviation aircraft position controller and is connected with tail vane steering wheel and receiving system.
Detailed description of the invention
Illustrated applicable aviation aircraft position controller, aim at designed by model helicopter, inductor and controller are combined, because the effect being suitable for aviation aircraft position controller is to adjust steering wheel, the mainly skew of tail vane steering wheel, hold concurrently and adjust turning to of model helicopter, make its flight control more accurate.
As depicted in figs. 1 and 2, be suitable for aviation aircraft position controller and by one, there is the body of control surface 100 and the integrating control chip be built in wherein forms, control button on control surface 100 is electrically connected to the corresponding functional module on integrating control chip respectively, integrating control chip electrically connects tail vane steering wheel and receiving system, wherein, the signal of telecommunication of remote controller is sent to applicable aviation aircraft position controller by receiving system, applicable aviation aircraft position controller sends and controls signal to tail vane steering wheel, the skew of adjustment tail vane steering wheel.
The control surface 100 being suitable for aviation aircraft position controller is provided with Fumction display signal lamp 10 and several control buttons, wherein, control button comprises mode conversion switch 11, forward and reverse control button 12, delays adjuster 13, range adjuster 14, and the integrating control chip be built in body also connects error transfer factor device 15 and tail vane adjuster 16 by cable.The top in the middle part of control surface 100 is located at by Fumction display signal lamp 10, mode conversion switch 11 is positioned at the below of Fumction display signal lamp 10, forward and reverse control button 12 is positioned at the below of mode conversion switch 11, the middle upper position of control surface 100 is provided with delays adjuster 13, and the upper right corner of control surface 100 is also provided with range adjuster 14.Each control button is electrically connected with the corresponding functional module on integrating control chip, by each control button on control surface 100, realizes the various function point analysis being suitable for aviation aircraft position controller.
Fumction display signal lamp 10 is generally LED, for showing the duty that this is suitable for aviation aircraft position controller.When its fast blink, after representing power-on, be suitable for aviation aircraft position controller and carrying out the initialized program of data; When its permanent bright time, represent be suitable for aviation aircraft position controller initialize complete, be positioned at locking (AVCS) pattern; When it glimmers at a slow speed, represent that being suitable for aviation aircraft position controller does not receive the tail vane control signal sent by remote controller, now tail vane steering wheel cannot operate; Glimmer twice expression when locking mode, and the tail vane control signal received at present is different from being stored in the neutrality point signal being suitable for aviation aircraft position controller, all there will be this lamp flicker twice: a) stirring tail vane rocking bar in following situation; B) central point of tail vane offsets, and must reset central point.
Mode conversion switch 11, i.e. digital rudder controller mode switch, when the steering wheel used is for digital rudder controller, need position mode conversion switch being switched to ON; And when the steering wheel used is general steering wheel, then mode conversion switch is switched to the position of OFF, at this moment, if switch to the position of ON, if just easily cause steering wheel to burn when steering gear power is lower.Correspondingly, integrating control chip also on be configured with the circuit being applied to general steering wheel and digital rudder controller respectively, the selection of support mode translation function.The setting up of mode conversion switch make to be suitable for aviation aircraft position controller can not only with general steering wheel with the use of, also can with digital rudder controller with the use of, versatility strengthens greatly.
Forward and reverse control button 12 for switch the controlling party that is suitable for aviation aircraft position controller to, user can do correct switching according to the direction of the main rotor direction of rotation of model helicopter and tail vane connecting rod.
Delaying adjuster 13 for adjusting the running speed of tail vane control signal, if the steering wheel that operating speed is slower, when but finding that the tail vane of model helicopter produces tracking phenomenon, can knob be rotated clockwise, increasing the time postponed, tracking phenomenon can be eliminated; If during tail vane use high speed steering wheel, such as digital rudder controller, user needs position knob being adjusted to 0, according to the running speed of the steering wheel adjustment tail vane control signal used.
Steering wheel range adjustment knob 14 is for setting the range amount of tail vane steering wheel, tail vane rocking bar is made rudder to from left to right, adjustment knob makes the path increment of tail vane steering wheel can not exceed the FROM of tail pitch sliding sleeve, rotates clockwise knob for increasing path increment.
Error transfer factor device 15, drawn by the integrating control chip being suitable for aviation aircraft position controller, and the sensitivity channel of the receiving system of the model of an airplane is electrically connected, can be used as to switch the sensitivity and the pattern that are suitable for aviation aircraft position controller, the pattern of selection be locking mode or general modfel simultaneously.
Tail vane adjuster 16, is drawn by the integrating control chip being suitable for aviation aircraft position controller, and electrically connects with the tail vane steering wheel of the model of an airplane, for controlling direction and the fine setting of tail vane.
Be suitable for aviation aircraft position controller can paste or weld or be installed on the model of an airplane by the mode of screw riveted, and this bottom being suitable for aviation aircraft position controller must be vertical with the main shaft of helicopter, otherwise left and right can be affected sidewinder and the direction of somersault; When being installed on electric model airplane by this applicable aviation aircraft position controller, this spacing be suitable between aviation aircraft position controller and the motor of the model of an airplane must be equal to or greater than 10cm, disturbs to avoid producing with motor.
When the tail vane of the model of an airplane be subject to crosswind blow and produce the phenomenon of skew time, be suitable for the skew that aviation aircraft position controller can resist tail vane, be suitable for the angle that aviation aircraft position controller can calculate skew simultaneously, and continue sending control signal to resist crosswind, even if when therefore crosswind ceaselessly blows helicopter, tail vane still can not produce skew.In other words, aviation aircraft position controller meeting auto modification is suitable for because of the tail vane skew caused by crosswind.In addition, this applicable aviation aircraft position controller build slight of stature, lighter in weight, is convenient to be installed on helicopter, and can effectively reduce flight energy consumption, extends the flight time.By increasing the sensitivity being suitable for aviation aircraft position controller gradually, and then increasing the time postponed, tracking phenomenon can be eliminated.
A kind of preferred embodiment being suitable for aviation aircraft position controller of the above disclosed the present invention of being only, certainly the interest field of the present invention can not be limited with this, therefore according to the equivalent variations that the present patent application the scope of the claims is done, the scope that the present invention is contained still is belonged to.
Claims (5)
1. an applicable aviation aircraft position controller, it has the body of control surface by one and the integrating control chip be built in wherein forms, it is characterized in that: panel is provided with Fumction display signal lamp and several control buttons, control button comprises mode conversion switch, forward and reverse control button, delays adjuster, range adjuster, and each control button and integrating control chip are electrically connected.
2. applicable aviation aircraft position controller according to claim 1, is characterized in that: this is suitable for aviation aircraft position controller and also comprises the error transfer factor device and tail vane adjuster of being drawn by integrating control chip further.
3. applicable aviation aircraft position controller according to claim 2, is characterized in that: comprise the receiving system being provided with and receiving remote controller control signal further, the sensitivity channel of described error transfer factor device and receiving system is electrically connected.
4. applicable aviation aircraft position controller according to claim 2, is characterized in that: the model of an airplane is provided with tail vane steering wheel further, and described tail vane adjuster and tail vane steering wheel are electrically connected.
5. applicable aviation aircraft position controller according to claim 1, is characterized in that: this applicable aviation aircraft position controller is applicable to digital rudder controller and simulation steering wheel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410546407.4A CN105498250A (en) | 2014-10-15 | 2014-10-15 | Azimuth controller applicable to aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410546407.4A CN105498250A (en) | 2014-10-15 | 2014-10-15 | Azimuth controller applicable to aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105498250A true CN105498250A (en) | 2016-04-20 |
Family
ID=55706786
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410546407.4A Pending CN105498250A (en) | 2014-10-15 | 2014-10-15 | Azimuth controller applicable to aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105498250A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105771275A (en) * | 2014-12-25 | 2016-07-20 | 许美兰 | Toy aircraft remote control intelligent control system |
-
2014
- 2014-10-15 CN CN201410546407.4A patent/CN105498250A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105771275A (en) * | 2014-12-25 | 2016-07-20 | 许美兰 | Toy aircraft remote control intelligent control system |
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Legal Events
| Date | Code | Title | Description |
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| C06 | Publication | ||
| PB01 | Publication | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20160420 |