CN210243678U - Aircraft engine speed detection circuit and system - Google Patents
Aircraft engine speed detection circuit and system Download PDFInfo
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- CN210243678U CN210243678U CN201921086724.7U CN201921086724U CN210243678U CN 210243678 U CN210243678 U CN 210243678U CN 201921086724 U CN201921086724 U CN 201921086724U CN 210243678 U CN210243678 U CN 210243678U
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Abstract
The utility model discloses an aircraft engine rotational speed detection circuitry and system, aircraft engine rotational speed detection circuitry includes clamp circuit module, instrument amplifier module and high-speed comparison circuit module, instrument amplifier module is connected with clamp circuit module and high-speed comparison circuit module respectively, the clamp circuit module is received from the differential signal that aircraft engine came and is confirmed input instrument amplifier module within +/-0.7V with this differential signal's voltage range, instrument amplifier module will receive through the differential signal of clamp processing and will carry out the high magnification with this differential signal through clamp processing and enlarge and handle into single-ended signal, high-speed comparison circuit module receives this single-ended signal and becomes TTL signal with this single-ended signal processing. The utility model is used for measure aircraft engine's rotational speed state, can be used to SCX-12.2.C and SCX-4.4. D.
Description
Technical Field
The utility model relates to an aircraft performance detects, in particular to aircraft engine rotational speed detection circuitry and system.
Background
The engine speed signal of an aircraft has the following characteristics:
1. the rotating speed signal is a sinusoidal signal with the amplitude in direct proportion to the rotating speed, and the amplitude is larger when the rotating speed is higher;
2. when the rotating speed is too low, the gentle zero-crossing signal can generate burrs to interfere the measurement result;
3. at engine shut down, a sinusoidal disturbance signal is generated.
For the reasons, the rotating speed signal needs to be specially processed and then measured, and because the uncertain factors of the rotating speed signal of the aircraft engine are more, the conventional measuring method has limitations, direct measurement cannot be performed, the measuring method is complex, the measuring equipment is expensive and large in size, and direct measurement cannot be performed by a simple method.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide an aircraft engine rotational speed detection circuitry, this aircraft engine rotational speed detection circuitry is used for measuring aircraft engine's rotational speed state.
The technical scheme is as follows: the aircraft engine rotating speed detection circuit comprises a clamping circuit module, an instrument amplifier module and a high-speed comparison circuit module, wherein the instrument amplifier module is respectively connected with the clamping circuit module and the high-speed comparison circuit module, the clamping circuit module receives a differential signal from an aircraft engine and determines the voltage range of the differential signal within +/-0.7V to be input into the instrument amplifier module, the instrument amplifier module carries out high-magnification amplification on the received differential signal subjected to clamping processing and the differential signal subjected to clamping processing to obtain a single-ended signal, and the high-speed comparison circuit module receives the single-ended signal and processes the single-ended signal to obtain a TTL signal.
Preferably, the high magnification is 10 to 20 times.
Preferably, the clamping circuit module comprises a resistor R2, a resistor R3, a resistor R6, a diode D1 and a diode D2, the diode D1 is connected in parallel with the diode D2, the diode D1 is opposite to the diode D2, one end of the resistor R3 is connected to the positive terminal of the differential signal from the aircraft engine, the other end of the resistor R2 is connected to the negative terminal of the differential signal from the aircraft engine, one end of the resistor R2 is connected to the positive terminal of the differential signal from the aircraft engine, the other end of the resistor R3829 is connected to the forward output end of the diode D2, one end of the resistor R6 is connected to the negative terminal of the differential signal from the aircraft engine, and the other end of the resistor R6 is connected to the forward input end of the diode D2.
Preferably, the instrumentation amplifier module comprises an amplifier INA128, and the amplifier INA128 is provided with an amplifier first pin, an amplifier second pin, an amplifier third pin, an amplifier fourth pin, an amplifier fifth pin, an amplifier sixth pin, an amplifier seventh pin, and an amplifier eighth pin; the instrumentation amplifier module further comprises a resistor R1, a first power source and a first ground source, one end of the resistor R1 is connected with a first pin of the amplifier, the other end of the resistor R1 is connected with an eighth pin of the amplifier, a second pin of the amplifier is connected with a forward output end of a diode D2, a third pin of the amplifier is connected with a forward input end of a diode D2, a fourth pin of the amplifier is connected with the cathode of the first power source, a seventh pin of the amplifier is connected with the anode of the first power source, a fifth pin of the amplifier is connected with the first ground source, and a sixth pin of the amplifier is an output end of the amplifier.
Preferably, the high-speed comparison circuit module comprises a high-speed comparator, a resistor R5, a resistor R8, a resistor R7, a resistor R4, an electrolytic capacitor C1, an electrolytic capacitor C2, a second ground source, a third ground source, a fourth ground source and a second power supply, the high-speed comparator is provided with a comparator input positive terminal, a comparator input negative terminal and a comparator output terminal, the comparator input positive terminal and the comparator output terminal are connected with the second power supply positive terminal, the comparator input negative terminal and the comparator output terminal are connected with the second power supply negative terminal, one end of the resistor R5 is connected with the sixth pin of the amplifier, the other end of the resistor R5 is connected with the comparator input positive terminal, one end of the electrolytic capacitor C1 is connected with the second ground source, the other end of the capacitor C1 is connected with the comparator input positive terminal, one end of the resistor R7 is connected with the third ground source, the other end of the resistor R2 is connected with the comparator input negative terminal, the other end is connected with the input negative end of the comparator, one end of a resistor R8 is connected with the input negative end of the comparator, and one end of a resistor R4 is connected with the output end of the comparator.
Preferably, the high-speed comparison circuit module further comprises a reference voltage, and the reference voltage is connected with the other end of the resistor R8.
Preferably, the diode D1 is 1N4148, and the diode D2 is 1N 4148.
The utility model discloses a second purpose of the utility model is to provide an aircraft engine rotational speed detection circuitry.
The technical scheme is as follows: the aircraft engine rotating speed detection circuit system comprises a controller and an aircraft engine rotating speed detection circuit, wherein the controller is connected with the aircraft engine rotating speed detection circuit, the aircraft engine rotating speed detection circuit receives a differential signal from an aircraft engine and processes the differential signal into a TTL (transistor-transistor logic) signal with rotating speed signal characteristics, and the TTL signal with the rotating speed signal characteristics is input into the controller and is measured and calculated by the controller.
Preferably, the aircraft engine speed detection circuit is the aircraft engine speed detection circuit described above.
Preferably, the controller is an FPGA, or a DSP, or a CPU.
Compared with the prior art, the beneficial effects of the utility model reside in that:
the utility model discloses an use the diode to constitute two-way clamp circuit module, keep input signal in certain voltage range, enlarge through instrumentation amplifier module and handle for single-ended signal, adopt high-speed comparator module to acquire its frequency again, measure and calculate signal frequency by the controller module to accomplish the detection achievement to engine speed.
The utility model can be used for SCX-12.2.C and SCX-4.4. D.
Description of the terms
The TTL signal-refers to a TTL level signal, where TTL is a Transistor Logic, and the level signal refers to a signal represented by a level value, which is divided into a high level "1" and a low level value "0".
Drawings
FIG. 1 is a schematic diagram of a circuit system for detecting the rotation speed of an aircraft engine according to the present invention;
fig. 2 is a schematic diagram of a clamping circuit module of the present invention;
FIG. 3 is a schematic diagram of a high-speed comparison circuit module according to the present invention;
fig. 4 is a schematic diagram of a reference circuit of the present invention;
fig. 5 is a circuit diagram of the circuit for detecting the rotation speed of the aircraft engine of the present invention.
Detailed Description
The present invention will be further explained with reference to the accompanying drawings.
In the description of the present invention, it should be further noted that, unless otherwise explicitly specified or limited, the terms "disposed," "opened," "mounted," "connected," and "connected" are to be construed broadly, e.g., as either a fixed connection, a detachable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.
Example 1
Referring to fig. 1-5, an aircraft engine speed detection circuit system comprises a controller and an aircraft engine speed detection circuit, wherein the controller is connected with the aircraft engine speed detection circuit, the aircraft engine speed detection circuit receives a differential signal from an aircraft engine and processes the differential signal into a TTL signal with speed signal characteristics, and the TTL signal with speed signal characteristics is input into the controller, and the controller measures and calculates the TTL signal with speed signal characteristics.
It is further required to explain, the utility model discloses in, aircraft engine rotational speed detection circuitry includes the clamp circuit module, instrument amplifier module and high-speed comparison circuit module, instrument amplifier module is connected with clamp circuit module and high-speed comparison circuit module respectively, the clamp circuit module is received from the differential signal that aircraft engine came and is confirmed input instrument amplifier module within 0.7V with this differential signal's voltage range, instrument amplifier module will receive through the differential signal of clamp processing and carry out the amplification of high magnification (10 ~ 20 times) and handle into single-ended signal with this differential signal through clamp processing, high-speed comparison circuit module receives this single-ended signal and becomes TTL signal with this single-ended signal processing, this TTL signal has the rotational speed signal characteristic.
It should be further noted that, in the present invention, the clamping circuit module includes a resistor R2, a resistor R3, a resistor R6, a diode D1 and a diode D2, the diode D1 is connected in parallel with the diode D2, the diode D1 and the diode D2 are in opposite directions, one end of the resistor R3 is connected to the positive terminal of the differential signal from the aircraft engine, the other end of the resistor R2 is connected to the negative terminal of the differential signal from the aircraft engine, one end of the resistor R2 is connected to the positive terminal of the differential signal from the aircraft engine, the other end of the resistor R733 is connected to the forward output terminal of the diode D2, one end of the resistor R6 is connected to the negative terminal of the differential signal from the aircraft engine, and the other end of the resistor R6 is connected to the forward input terminal of the.
The utility model discloses in, the clamp circuit module is with the engine state difference signal of input through current-limiting resistor and the parallelly connected clamp circuit of two diodes, confirms the voltage range of signal within 0.7V, input instrumentation amplifier module.
The utility model discloses a two-way clamp circuit of diode under the condition that does not change signal frequency, has solved the variable problem of rotational speed signal amplitude variation of input, with rotational speed signal control at certain voltage range.
It is further noted that, in the present invention, the instrumentation amplifier module includes an amplifier INA128, and the amplifier INA128 is provided with a first pin of an amplifier, a second pin of the amplifier, a third pin of the amplifier, a fourth pin of the amplifier, a fifth pin of the amplifier, a sixth pin of the amplifier, a seventh pin of the amplifier, and an eighth pin of the amplifier.
It is further required to explain, the utility model discloses in, the instrumentation amplifier module still includes resistance R1, first power and first ground source that connects, resistance R1 one end is connected with the first pin of amplifier, the other end is connected with amplifier eighth pin, amplifier second pin is connected with diode D2's forward output, amplifier third pin is connected with diode D2's forward input end, first power negative pole is connected to amplifier fourth pin, amplifier seventh pin is connected first power anodal, amplifier fifth pin is connected first ground source, amplifier sixth pin is the amplifier output.
The utility model discloses in, instrumentation amplifier module adopts the instrumentation amplifier of high magnification, enlargies the input signal, becomes precipitous with mild zero crossing signal, has eliminated the rotational speed and has crossed the hidden danger that the comparison signal probably produced the burr when low excessively.
It should be further noted that, in the present invention, the high-speed comparison circuit module includes a high-speed comparator, a resistor R5, a resistor R8, a resistor R7, a resistor R4, an electrolytic capacitor C1, an electrolytic capacitor C2, a second ground source, a third ground source, a fourth ground source and a second power supply, the high-speed comparator is provided with a comparator input positive terminal, a comparator input negative terminal and a comparator output terminal, the comparator input positive terminal is connected with the comparator output terminal through the second power supply positive terminal, the comparator input negative terminal is connected with the comparator output terminal through the second power supply negative terminal, one end of the resistor R5 is connected with the sixth pin of the amplifier, the other end is connected with the comparator input positive terminal, one end of the electrolytic capacitor C1 is connected with the second ground source, the other end is connected with the comparator input negative terminal, one end of the resistor R7 is connected with the third ground source, the other end is connected with the comparator input negative terminal, one end of the electrolytic capacitor C2 is connected with the third grounding source, the other end is connected with the input negative terminal of the comparator, one end of the resistor R8 is connected with the input negative terminal of the comparator, and one end of the resistor R4 is connected with the output terminal of the comparator.
It should be further noted that, in the present invention, the high-speed comparison circuit module further includes a reference voltage, and the reference voltage is connected to the other end of the resistor R8.
It should be further noted that, in the present invention, the reference voltage comprises a voltage reference chip and an emitter follower circuit, the voltage reference chip generates the reference voltage, and the reference voltage is provided after the emitter follower circuit is isolated.
Further, in the present invention, the voltage reference chip is preferably ADR421, and the emitter follower circuit is preferably an amplifier AD8031 ART.
The utility model discloses in, high-speed comparator and reference voltage carry out the comparison with the characteristic signal of instrumentation amplifier module output after the filtering input high-speed comparator, and the amplitude of the sinusoidal interference signal that produces when reference voltage is a little higher than the engine shut down after the partial pressure is handled, and the controller module adopts the mode of fixed number timing to calculate the rotational speed when measuring.
The utility model discloses in, high-speed comparator is when comparing, and the voltage that is higher than sinusoidal interference signal amplitude is selected to the reference voltage, and the signal after will enlargiing compares with it, and the interference signal who produces when can avoiding shutting down acquires the pulse signal who has at the rotational speed signal characteristic.
It should be further noted that, in the present invention, LM119 is preferred as the high-speed comparator.
It should be further noted that, in the present invention, the controller module may be FPGA, DSP, CPU, preferably FPGA.
It should be further noted that, in the present invention, the diodes D1 and D2 are preferably 1N 4148.
The utility model discloses in, through the instrumentation amplifier who adopts two-way clamp circuit and high magnification to and through the reference voltage who adjusts the comparator, solved following three problem: 1. the amplitude is unstable in the measurement of the rotating speed of the aircraft engine; 2. when the rotating speed is too slow, burrs are easily generated by comparison signals; 3. there is a sinusoidal interference signal at shutdown.
In FIG. 5, the engine speed differential signal freq +/freq-to-be-measured is stabilized within + -0.7V by the clamping circuit module; the instrument amplifier module amplifies the signal by 11 times and processes the signal into a single-ended signal; the high-speed comparator compares the filtered single-ended signal with a reference voltage, the reference voltage is slightly higher than the amplitude of the sinusoidal interference signal after voltage division, and a freqtest signal with the characteristic of the engine speed is output; the controller module measures and calculates freqtest signals to detect the rotating speed of the engine.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. An aircraft engine speed detection circuit, characterized by: the aircraft engine rotating speed detection circuit comprises a clamping circuit module, an instrument amplifier module and a high-speed comparison circuit module, wherein the instrument amplifier module is respectively connected with the clamping circuit module and the high-speed comparison circuit module, the clamping circuit module receives a differential signal from an aircraft engine and determines the voltage range of the differential signal within +/-0.7V to be input into the instrument amplifier module, the instrument amplifier module carries out high-magnification amplification on the received differential signal subjected to clamping processing and the differential signal subjected to clamping processing to obtain a single-ended signal, and the high-speed comparison circuit module receives the single-ended signal and processes the single-ended signal to obtain a TTL signal.
2. The aircraft engine speed detection circuit according to claim 1, wherein: the multiplying power of the high multiplying power is 10-20 times.
3. The aircraft engine speed detection circuit according to claim 1, wherein: the clamping circuit module comprises a resistor R2, a resistor R3, a resistor R6, a diode D1 and a diode D2, the diode D1 and the diode D2 are connected in parallel, the diode D1 and the diode D2 are in reverse directions, one end of the resistor R3 is connected with the positive end of a differential signal from an aircraft engine, the other end of the resistor R2 is connected with the negative end of the differential signal from the aircraft engine, one end of the resistor R2 is connected with the positive end of the differential signal from the aircraft engine, the other end of the resistor R633 is connected with the forward output end of the diode D2, one end of the resistor R6 is connected with the negative end of the differential signal from the aircraft engine, and the other end of the resistor R6 is connected with the forward input end of the diode.
4. An aircraft engine speed detection circuit according to claim 3, wherein: the instrumentation amplifier module comprises an amplifier INA128, wherein the amplifier INA128 is provided with an amplifier first pin, an amplifier second pin, an amplifier third pin, an amplifier fourth pin, an amplifier fifth pin, an amplifier sixth pin, an amplifier seventh pin and an amplifier eighth pin; the instrumentation amplifier module further comprises a resistor R1, a first power source and a first ground source, one end of the resistor R1 is connected with a first pin of the amplifier, the other end of the resistor R1 is connected with an eighth pin of the amplifier, a second pin of the amplifier is connected with a forward output end of a diode D2, a third pin of the amplifier is connected with a forward input end of a diode D2, a fourth pin of the amplifier is connected with the cathode of the first power source, a seventh pin of the amplifier is connected with the anode of the first power source, a fifth pin of the amplifier is connected with the first ground source, and a sixth pin of the amplifier is an output end of the amplifier.
5. The aircraft engine speed detection circuit according to claim 4, wherein: the high-speed comparison circuit module comprises a high-speed comparator, a resistor R5, a resistor R8, a resistor R7, a resistor R4, an electrolytic capacitor C1, an electrolytic capacitor C2, a second ground source, a third ground source, a fourth ground source and a second power supply, wherein the high-speed comparator is provided with a comparator input positive end, a comparator input negative end and a comparator output end, the comparator input positive end and the comparator output end are connected with the positive electrode of the second power supply, the comparator input negative end and the comparator output end are connected with the negative electrode of the second power supply, one end of a resistor R5 is connected with a sixth pin of the amplifier, the other end of the resistor R5 is connected with the input positive end of the comparator, one end of an electrolytic capacitor C1 is connected with the second ground source, the other end of the capacitor C1 is connected with the input positive end of the comparator, one end of the resistor R7 is connected with the third ground source, the other end of the resistor R2 is connected with the, the other end is connected with the input negative end of the comparator, one end of a resistor R8 is connected with the input negative end of the comparator, and one end of a resistor R4 is connected with the output end of the comparator.
6. The aircraft engine speed detection circuit according to claim 5, wherein: the high-speed comparison circuit module further comprises a reference voltage, and the reference voltage is connected with the other end of the resistor R8.
7. An aircraft engine speed detection circuit according to claim 3, wherein: the diode D1 is 1N4148, and the diode D2 is 1N 4148.
8. An aircraft engine speed detection circuitry characterized by: the aircraft engine rotating speed detection circuit system comprises a controller and an aircraft engine rotating speed detection circuit, wherein the controller is connected with the aircraft engine rotating speed detection circuit, the aircraft engine rotating speed detection circuit receives a differential signal from an aircraft engine and processes the differential signal into a TTL (transistor-transistor logic) signal with rotating speed signal characteristics, and the TTL signal with the rotating speed signal characteristics is input into the controller and measured and calculated by the controller.
9. The aircraft engine speed detection circuitry of claim 8, wherein: the aircraft engine speed detection circuit is the aircraft engine speed detection circuit of any one of claims 1 to 7.
10. The aircraft engine speed detection circuitry of claim 9, wherein: the controller is FPGA, or DSP, or CPU.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921086724.7U CN210243678U (en) | 2019-07-12 | 2019-07-12 | Aircraft engine speed detection circuit and system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921086724.7U CN210243678U (en) | 2019-07-12 | 2019-07-12 | Aircraft engine speed detection circuit and system |
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| CN210243678U true CN210243678U (en) | 2020-04-03 |
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| CN201921086724.7U Active CN210243678U (en) | 2019-07-12 | 2019-07-12 | Aircraft engine speed detection circuit and system |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113202653A (en) * | 2021-05-21 | 2021-08-03 | 成都凯天电子股份有限公司 | Automatic measuring system for engine running data |
| CN113740087A (en) * | 2021-07-23 | 2021-12-03 | 西尼机电（杭州）有限公司 | Elevator balance coefficient detection equipment |
-
2019
- 2019-07-12 CN CN201921086724.7U patent/CN210243678U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113202653A (en) * | 2021-05-21 | 2021-08-03 | 成都凯天电子股份有限公司 | Automatic measuring system for engine running data |
| CN113740087A (en) * | 2021-07-23 | 2021-12-03 | 西尼机电（杭州）有限公司 | Elevator balance coefficient detection equipment |
| CN113740087B (en) * | 2021-07-23 | 2024-03-19 | 西尼机电（杭州）有限公司 | Elevator balance coefficient detection equipment |
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