CN203123579U - Debugger of running state of model airplane steering engine - Google Patents
Debugger of running state of model airplane steering engine Download PDFInfo
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- CN203123579U CN203123579U CN 201220724600 CN201220724600U CN203123579U CN 203123579 U CN203123579 U CN 203123579U CN 201220724600 CN201220724600 CN 201220724600 CN 201220724600 U CN201220724600 U CN 201220724600U CN 203123579 U CN203123579 U CN 203123579U
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Abstract
The utility model discloses a debugger of a running state of a model airplane steering engine. The debugger is composed of a 6V direct-current power source, a power source indicating circuit, a rectangular wave generating circuit, a pulse time adjusting circuit, a deadline time adjusting circuit and a steering engine control signal output end. The debugger of the running state of the model airplane steering engine is characterized in that the model number of a double-D triggering integrated circuit IC1 of the rectangular wave generating circuit is 74LS74, and the model number of a phase inverter IC2 is 74 LS 14. The debugger of the running state of the model airplane steering engine is capable of generating continuous adjustable steering engine signals, used for replacing a remote transmitter and a receiver device of a model airplane and used for debugging the running sate of the model airplane steering engine in an outside or an inside. The debugger of the running state of the model airplane steering engine is not only capable of being used for debugging a wireless remote-control model airplane steering engine, but also capable of examining and judging bugs on earth exist in the steering engine or the receiver device or the remote transmitter when the steering engine can not normally work.
Description
Technical field
The utility model belongs to model plane and electronic technology field, is about a kind of airplane model steering engine running status debugger.
Background technology
At present, airplane model steering engine operation debugging apparatus has multiple brands such as Hitec, JR on the market, they have automatic test, neutral the more full function of function ratio such as determine, and have volume little, carry advantages such as practical and convenient, but price RMB is all in thousands of units, and not general airplane hobbyist can accept.For popularizing and the raising of model plane technical merit of model plane activity, according to work characteristics and the technical parameter of airplane model steering engine, use common digital integrated electronic circuit to be combined into steering wheel dry run debugger.Facts have proved: debugger circuit not only technical scheme is feasible, and the circuit production cost is low, is suitable for factory and develops in batches.
Below describe in detail this airplane model steering engine running status debugger in manufacturing process in related correlation technique content.
The utility model content
Goal of the invention and beneficial effect: airplane model steering engine running status debugger can produce continuously adjustable steering wheel signal, be used for replacing model plane telecontrol transmitter, receiver device to be used for outfield or each steering wheel duty of indoor debugging model plane, it not only can be used for the debugging of wireless remote control airplane model steering engine, can be used for checking, judge the steering wheel cisco unity malfunction that fault is at steering wheel or receiver or telecontrol transmitter actually.Sometimes or some occasion needn't rely on the customary practice that remote control equipment could be debugged airplane model steering engine again, and can replace electron speed regulator to be used for brushless electric machine debugging work.
Technical characterictic: airplane model steering engine running status debugger, it by 6V dc source, power indicating circuit, rectangle wave generation circuit, burst length regulating circuit, deadline regulating circuit and steering wheel control signal output form, its feature comprises:
The rectangle wave generation circuit: it triggers IC 1 by two D, inverter ic 2 is formed, the model that two D trigger IC 1 employing is 74LS74, the model that inverter ic 2 adopts is 74LS14, the 1st pin of two D triggering ICs 1 connects the 10th pin of inverter ic 2, the 11st pin of inverter ic 2 links to each other with the 12nd pin, the 13rd pin of inverter ic 2 links to each other with the positive pole of the positive pole of switching diode D1 and tantalum capacitor C 1, the 4th pin of two D triggering ICs 1 connects the 4th pin of inverter ic 2, the 3rd pin of inverter ic 2 links to each other with the 2nd pin, the 1st pin of inverter ic 2 links to each other with the positive pole of the positive pole of switching diode D2 and electrochemical capacitor C2, and the 14th pin that two D trigger IC 1 meets 6V dc power anode VCC;
The burst length regulating circuit: it is made up of potentiometer W1, resistance R 1, switching diode D1 and tantalum capacitor C 1, the 6th pin that two D trigger IC 1 connects the end of potentiometer W1 and the negative pole of switching diode D1, the other end of potentiometer W1 links to each other with the positive pole of switching diode D1, the positive pole of tantalum capacitor C 1 and the 13rd pin of inverter ic 2 by resistance R 1, and the negative pole of tantalum capacitor C 1 links to each other with the 7th pin and circuit ground GNG with the 2nd pin that two D trigger IC 1;
Deadline regulating circuit: it is made up of half variable fine setting W2, resistance R 2, switching diode D2, electrochemical capacitor C2, the 5th pin that two D trigger IC 1 connects the end of half variable fine setting W2 and the negative pole of switching diode D2, the other end of half variable fine setting W2 links to each other with the positive pole of switching diode D2, the positive pole of electrochemical capacitor C2, the 1st pin of inverter ic 2 by an end of resistance R 2, and the negative pole of electrochemical capacitor C2 links to each other with circuit ground GNG;
Steering wheel control signal output: the contact pin that adopts DIP Du Pont standard, signal output part contact pin the 1st pin connection circuit ground GNG, signal output part patches pin the 2nd pin and meets 6V dc power anode VCC, and signal output part contact pin the 3rd pin meets two D and triggers the 5th pin of IC 1 and the negative pole of switching diode D2.
The circuit working principle: when the two D of two rising edges triggered IC 1 initial state, the 6th pin that the two D of two rising edges trigger IC 1 passed through W1, resistance R 1 to 1 charging of tantalum capacitor C, and its current potential is raise; When reaching reset level, trigger overturns, and the 5th pin transfers high level to, and the 6th pin transfers low level to, and this moment, tantalum capacitor C 1 was discharged through diode D1, and electrochemical capacitor C2 is through half variable fine setting W2, resistance R 2 chargings; When reaching triggering level, trigger overturns again and finishes a pulse period, so goes round and begins again;
Burst length T1=0.66 * C1 * (W1+R1); Deadline T2=0.66 * C2 * (W2+R2); Pulse frequency f=1/ (T1+T2).Can draw from the above-mentioned relation formula: regulator potentiometer W1, resistance R 1 or W2, resistance R 2 can be regulated dutycycle.The effect of potentiometer W1 and resistance R 1 is the regulating impulse time in the circuit, and the effect of half variable fine setting W2 and resistance R 2 is to regulate deadline.
In fact the control signal of airplane model steering engine is a kind of square wave pulse, and when dutycycle changed, the steering wheel angle of steering wheel changed thereupon; Square wave duty of ratio regulating circuit changes between 0.05～0.10, and its frequency is constant to be 50Hz, and pulse width is between 1～2ms.Steering wheel when rotating, each pulse width corresponding a fixed angle of steering wheel steering wheel.
Description of drawings
Accompanying drawing 1 is airplane model steering engine running status debugger employed circuit working schematic diagram in an embodiment.
The specific embodiment
Accompanying drawing 1 and description of drawings to specifications are further described relative production technology of the present utility model in conjunction with the embodiments below.
Components and parts are selected and technical parameter
The two D circuits for triggering of the two rising edges of integrated circuit abbreviate as: two D circuits for triggering, and the model of two D circuits for triggering IC1 is 74LS74 or 74S74, only uses wherein half among the embodiment, its operating voltage: 4.8～6.5V;
Logic circuit adopts the hex inverter that Schmidt trigger is arranged, and only uses wherein four phase inverters in the present embodiment; The model of inverter ic 2 is 74LS14, its pin corresponding function and data: the 1st pin: 1A; The 2nd pin: 1Y; The 3rd pin: 2A; 4 pin: 2Y; 10 pin: 5Y; The 11st pin: 5A; 12 pin: 6Y; The 13rd pin: 6A; The 14th pin: VCC is 6V dc source input pin; The 7th pin: GND is circuit ground;
The capacity of tantalum capacitor C 1 is that the capacity of 1 μ F/10V, C2 is 10 μ F/10V, requires its capacity accurate;
D1, D2 select fast reaction switching diode 1N4148 for use, and LED is red light emitting diodes;
R1, R2 are semifixed resistor, and recommendation is 510 Ω; R3 is dropping resistor, and resistance is 510 Ω;
W1 is linear potentiometer, and W2 is half variable fine setting, and its resistance is 5.1K Ω;
Accompanying drawing 1 centered rudder machine control signal output uses the contact pin of DIP Du Pont standard, be used for inserting the plug (negative plug) of debugged steering wheel lead-in wire, signal output part contact pin 1 pin connection circuit ground, signal output part contact pin 2 pin connect the positive pole of 6V dc source, and signal output part contact pin 3 pin are the control signal output pin.
Device is made main points and circuit debugging
Requirement components and parts layout and connecting line want compact when making, and connecting line is short as far as possible, otherwise may cause components and parts to produce interference each other, even the serious rudder phenomenon of jumping of debugged steering wheel generation can take place.If the rudder phenomenon takes place to jump in circuit debugging, at first should be by the filtering measures of stiffening device power supply;
Requirement selects for use tantalum capacitor C 1 and electrochemical capacitor C2 capability value more accurate, suitably adjusts the resistance of half variable fine setting, makes circuit output square wave pulse frequency f=50Hz; What W2 adopted is half variable fine setting, gets final product sealing after adjusting is finished; Potentiometer W1 is for the anglec of rotation of adjusting the steering wheel steering wheel, to observe tested steering wheel working order;
Suggestion: the knob that potentiometer W1 can select for use model plane remote controller control stick to have back middle positioning function makes the function of dry run debugger, fidelity better.
Claims (1)
1. airplane model steering engine running status debugger, it by 6V dc source, power indicating circuit, rectangle wave generation circuit, burst length regulating circuit, deadline regulating circuit and steering wheel control signal output form, its feature comprises:
Described rectangle wave generation circuit triggers IC 1 by two D, inverter ic 2 is formed, the model that two D trigger IC 1 employing is 74LS74, the model that inverter ic 2 adopts is 74LS14, the 1st pin of two D triggering ICs 1 connects the 10th pin of inverter ic 2, the 11st pin of inverter ic 2 links to each other with the 12nd pin, the 13rd pin of inverter ic 2 links to each other with the positive pole of the positive pole of switching diode D1 and tantalum capacitor C 1, the 4th pin of two D triggering ICs 1 connects the 4th pin of inverter ic 2, the 3rd pin of inverter ic 2 links to each other with the 2nd pin, the 1st pin of inverter ic 2 links to each other with the positive pole of the positive pole of switching diode D2 and electrochemical capacitor C2, and the 14th pin that two D trigger IC 1 meets 6V dc power anode VCC;
Described burst length regulating circuit is made up of potentiometer W1, resistance R 1, switching diode D1 and tantalum capacitor C 1, the 6th pin that two D trigger IC 1 connects the end of potentiometer W1 and the negative pole of switching diode D1, the other end of potentiometer W1 links to each other with the positive pole of switching diode D1, the positive pole of tantalum capacitor C 1 and the 13rd pin of inverter ic 2 by resistance R 1, and the negative pole of tantalum capacitor C 1 links to each other with the 7th pin and circuit ground GNG with the 2nd pin that two D trigger IC 1;
Described deadline, regulating circuit was made up of half variable fine setting W2, resistance R 2, switching diode D2, electrochemical capacitor C2, the 5th pin that two D trigger IC 1 connects the end of half variable fine setting W2 and the negative pole of switching diode D2, the other end of half variable fine setting W2 links to each other with the positive pole of switching diode D2, the positive pole of electrochemical capacitor C2, the 1st pin of inverter ic 2 by an end of resistance R 2, and the negative pole of electrochemical capacitor C2 links to each other with circuit ground GNG;
Described steering wheel control signal output adopts the contact pin of DIP Du Pont standard, signal output part contact pin the 1st pin connection circuit ground GNG, signal output part patches pin the 2nd pin and meets 6V dc power anode VCC, and signal output part contact pin the 3rd pin meets two D and triggers the 5th pin of IC 1 and the negative pole of switching diode D2.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220724600 CN203123579U (en) | 2012-12-25 | 2012-12-25 | Debugger of running state of model airplane steering engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220724600 CN203123579U (en) | 2012-12-25 | 2012-12-25 | Debugger of running state of model airplane steering engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203123579U true CN203123579U (en) | 2013-08-14 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220724600 Expired - Fee Related CN203123579U (en) | 2012-12-25 | 2012-12-25 | Debugger of running state of model airplane steering engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203123579U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103984251A (en) * | 2014-05-12 | 2014-08-13 | 南通中远船务自动化有限公司 | Portable debugger for autopilot |
-
2012
- 2012-12-25 CN CN 201220724600 patent/CN203123579U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103984251A (en) * | 2014-05-12 | 2014-08-13 | 南通中远船务自动化有限公司 | Portable debugger for autopilot |
| CN103984251B (en) * | 2014-05-12 | 2016-06-08 | 南通中远船务自动化有限公司 | The portable debugger of autopilot |
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| Date | Code | Title | Description |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20130814 Termination date: 20131225 |