CN110510111B - Static brake protection circuit with anti-interference capability and design method thereof - Google Patents
Static brake protection circuit with anti-interference capability and design method thereof Download PDFInfo
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- CN110510111B CN110510111B CN201910857828.1A CN201910857828A CN110510111B CN 110510111 B CN110510111 B CN 110510111B CN 201910857828 A CN201910857828 A CN 201910857828A CN 110510111 B CN110510111 B CN 110510111B
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- 230000003068 static effect Effects 0.000 title claims abstract description 133
- 238000000034 method Methods 0.000 title claims abstract description 11
- 238000004519 manufacturing process Methods 0.000 claims abstract description 3
- 230000007704 transition Effects 0.000 claims 1
- 230000000694 effects Effects 0.000 abstract description 12
- 238000010586 diagram Methods 0.000 description 2
- 238000004891 communication Methods 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000012938 design process Methods 0.000 description 1
- 230000003137 locomotive effect Effects 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60T—VEHICLE BRAKE CONTROL SYSTEMS OR PARTS THEREOF; BRAKE CONTROL SYSTEMS OR PARTS THEREOF, IN GENERAL; ARRANGEMENT OF BRAKING ELEMENTS ON VEHICLES IN GENERAL; PORTABLE DEVICES FOR PREVENTING UNWANTED MOVEMENT OF VEHICLES; VEHICLE MODIFICATIONS TO FACILITATE COOLING OF BRAKES
- B60T8/00—Arrangements for adjusting wheel-braking force to meet varying vehicular or ground-surface conditions, e.g. limiting or varying distribution of braking force
- B60T8/17—Using electrical or electronic regulation means to control braking
- B60T8/1701—Braking or traction control means specially adapted for particular types of vehicles
- B60T8/1703—Braking or traction control means specially adapted for particular types of vehicles for aircrafts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/42—Arrangement or adaptation of brakes
- B64C25/44—Actuating mechanisms
- B64C25/46—Brake regulators for preventing skidding or aircraft somersaulting
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Transportation (AREA)
- Regulating Braking Force (AREA)
- Emergency Protection Circuit Devices (AREA)
Abstract
A static brake protection circuit with anti-interference capability and a design method thereof, wherein an operational amplifier is adopted to manufacture a comparison circuit; the comparison circuit comprises an operational amplifier, 6 resistors and 3 diodes; wherein: the 1 st pin, the 3 rd pin, the third diode and the fifth resistor of the operational amplifier form a static brake protection hysteresis comparison characteristic circuit. The 1 st pin, the 3 rd pin, the second diode and the sixth resistor of the operational amplifier form a hysteresis comparison characteristic circuit, and the hysteresis characteristic of the static brake protection circuit is improved to correspond to the difference value between the static brake effect and the static brake protection voltage, so that the capability of the static brake protection circuit for resisting instant speed change is improved, the capability of the brake system for resisting external vibration and comprehensive electromagnetic environment interference under the condition of outputting static brake pressure is improved, the automatic switching of the static brake effect and static brake failure state caused by external interference is eliminated, and the stability of the static brake system is improved.
Description
Technical Field
The utility model relates to the field of anti-skid brake systems of airplanes, in particular to a static brake protection circuit with anti-interference capability and a design method thereof.
Background
4.3.2.2.1 static brake of HB6761-93 specifies "when the brake device temperature is at ambient temperature, the brake handle should have enough static brake torque in the effective travel range to brake the wheel, causing the aircraft to brake on a 33℃ramp at maximum design total weight. The static brake protection function is one of the main control logics of the existing aircraft anti-skid brake control box.
The prior art structure is shown in detail in fig. 1. The static brake protection circuit is characterized in that a comparison circuit is manufactured by an operational amplifier U1, and the 8 th pin of the operational amplifier U1 is communicated with a +18V.DC power supply; reference speed signal V of aircraft ωR The output end is communicated with the anode of the first diode D1; the cathode of the first diode D1 is communicated with one end of a first resistor R1, the other end of the first resistor R1 is communicated with a power supply ground, and the cathode of the first diode D1 is simultaneously communicated with the 2 nd pin of the operational amplifier U1; the 4 th pin of the operational amplifier U1 is communicated with the power ground.
The power supply +18V.DC is communicated with one end of a fourth resistor R4, the other end of the fourth resistor R4 is communicated with one end of a second resistor, the other end of the second resistor is communicated with one end of a third resistor, and the other end of the third resistor is communicated with power supply ground; the other end of the second resistor is simultaneously communicated with the 3 rd pin of the operational amplifier U1, the 3 rd pin of the operational amplifier U1 is communicated with one end of the fifth resistor, and the other end of the fifth resistor is communicated with the 1 st pin of the operational amplifier U1; the operational amplifier U1 is formed into a circuit having hysteresis comparison characteristics by the fifth resistor R5.
When the maximum speed of the airplane is 330Km/h, the corresponding airplane wheel speed signal f is 2750Hz and V p_p Frequency signal of more than or equal to 0.6V and corresponding wheel speed voltage V ωk 12.5V, corresponding reference speed voltage V ωR 12.4V, slip failure rate of 30 +8 Km/h, corresponding wheel speed voltage V ωk 4V, corresponding reference speed voltage V ωR 3.9V;
when the static brake is effective, the 1 st pin output voltage of the operational amplifier U1 is 16.5V, the 3 rd pin voltage of the operational amplifier U1 is 4.42V, and the corresponding aircraft speed value is 34.8Km/h;
during static brake protection, the 1 st pin output voltage of the operational amplifier U1 is 0.5V, and the 3 rd pin voltage of the operational amplifier U1 is 5.72V; the corresponding aircraft speed value is 65.45Km/h. The hysteresis characteristic of the comparison circuit formed by the operational amplifier U1 corresponds to the aircraft speed difference of 65.45-34.8=30.65 Km/h; the corresponding reference speed voltage difference is 5.72-4.42=1.3v, because the difference between the static braking protection and static braking action state comparison points in the prior art is 1.3V, the corresponding speed of the aircraft is about 30km/h, and the aircraft static braking process is a dynamic process and is often interfered by vibration, electromagnetic interference, temperature, noise and other environments, so that the static braking action state and the static braking protection state are instantaneously switched, the static braking is unstable, the static braking effect of the aircraft is seriously influenced, and a certain hidden danger is caused to the safety of the aircraft.
Through searching, the utility model patent with the application number of 201620188009 mentions a comparison circuit which improves the capability of resisting external interference, but the circuit is only effective for interference signals in a certain frequency range, and is difficult to adapt to environments such as vibration, electromagnetic interference, temperature, noise and the like.
Disclosure of Invention
In order to overcome the defect that the static braking state is unstable due to small pressure difference between the static braking protection voltage and the static braking effect voltage in the prior art, the utility model provides a static braking protection circuit with anti-interference capability and a design method thereof.
The static brake protection circuit with the anti-interference capability provided by the utility model adopts an operational amplifier to manufacture a comparison circuit; the comparison circuit comprises an operational amplifier, 6 resistors and 3 diodes; the 6 resistors are sequentially woven into a first resistor to a sixth resistor, and the 3 diodes are sequentially woven into a first diode to a third diode; wherein: the 8 th pin of the operational amplifier is a power input end and is communicated with a +18V.DC power supply; and the 4 th pin of the operational amplifier is communicated with a ground wire. The 1 st pin of the operational amplifier is simultaneously communicated with one end of the fifth resistor and one end of the sixth resistor; the other end of the fifth resistor is communicated with the cathode of a third diode, and the anode of the third diode is communicated with the 3 rd pin of the operational amplifier; the other end of the sixth resistor is communicated with the anode of a second diode, and the cathode of the second diode is communicated with the 3 rd pin of the operational amplifier; the 3 rd pin of the operational amplifier is simultaneously communicated with one end of the second resistor and one end of the third resistor; the other end of the second resistor is communicated with one end of a fourth resistor, and the other end of the fourth resistor is communicated with a +18V.DC power supply; the other end of the third resistor is communicated with the ground wire. The 2 nd pin of the operational amplifier is communicated with the cathode of the first diode, and is simultaneously communicated with one end of a first resistor, and the other end of the first resistor is communicated with a ground wire. The anode of the first diode is communicated with the output end of the reference speed module in the aircraft brake control box.
The 1 st pin, the 3 rd pin, the third diode and the fifth resistor of the operational amplifier form a static brake protection hysteresis comparison characteristic circuit. The 1 st pin, the 3 rd pin, the second diode and the sixth resistor of the operational amplifier form an effective hysteresis comparison characteristic circuit.
When the speed of the aircraft changes from high to low, the static brake protection circuit is switched from a static brake protection state to a static brake active state. In the static brake protection state, the 3 rd pin voltage of the operational amplifier is 10.15V, and the 1 st pin output voltage of the operational amplifier is 0.5V; when the voltage of the 2 nd pin of the operational amplifier drops below 4.42V, the output voltage of the 1 st pin of the operational amplifier is 16.5V, and the static brake is effective; meanwhile, the 3 rd foot voltage of the operational amplifier is 4.42V, and the corresponding aircraft speed value is 34.8Km/h.
When the speed of the aircraft changes from low to high, the static brake protection circuit is changed from a static brake active state to a static brake protection state, and when the static brake is active, the 1 st foot output voltage of the operational amplifier is 16.5V, and the 3 rd foot voltage of the operational amplifier is 4.42V; when the voltage of the 2 nd pin of the operational amplifier is increased to above 10.15V, and the output voltage of the 1 st pin of the operational amplifier is changed to 0.5V, the voltage of the 3 rd pin of the operational amplifier is 10.15V, and the corresponding aircraft speed is 190.8Km/h.
The design process of the static brake protection circuit with the anti-interference capability provided by the utility model is as follows:
step one: parameters of all electronic components in the static brake protection hysteresis comparison characteristic circuit are determined:
and determining parameters of all electronic components in the static brake protection hysteresis comparison characteristic circuit according to the static brake protection voltage.
And setting the static brake protection voltage according to the speed of the airplane. The static brake protection voltage is a voltage value corresponding to the static brake protection speed.
Each electronic component comprises a fifth resistor, an operational amplifier and a third diode; the parameters of each electronic component comprise the resistance value of each resistor, the model of an operational amplifier and the model of a diode.
And setting the static brake protection speed of the airplane, wherein the voltage value corresponding to the speed is the voltage of the 3 rd pin of the operational amplifier.
Step two: determining parameters of all electronic components in the active hysteresis comparison characteristic circuit:
determining parameters of all electronic components in the actuation hysteresis comparison characteristic circuit according to the static brake actuation voltage:
each electronic component comprises a sixth resistor and a second diode; the parameters of each electronic component comprise the resistance value of the sixth resistor and the model of the second diode. And setting the effective speed of the aircraft static brake, wherein the voltage value corresponding to the speed is the voltage of the 3 rd pin of the operational amplifier.
Setting the aircraft static brake acting speed, wherein the voltage value corresponding to the speed is the aircraft static brake acting voltage; the aircraft static brake active voltage is the voltage of the 3 rd pin of the operational amplifier.
The operational amplifier is an F158 operational amplifier, and each diode is BZ03C. The resistance value of the first resistor is determined to be 10KΩ, the resistance value of the second resistor is determined to be 0.681KΩ, the resistance value of the third resistor is determined to be 4.64KΩ, the resistance value of the fourth resistor is determined to be 12KΩ, the resistance value of the fifth resistor is determined to be 43KΩ, and the resistance value of the sixth resistor is determined to be 5.1KΩ.
Thus, the design of the static brake protection circuit with the anti-interference capability is completed.
The utility model improves the voltage value during static brake protection and improves the voltage difference between the static brake effect and the static brake protection, thereby achieving the purpose of improving the anti-interference capability of the static brake protection circuit.
When the maximum speed of the airplane is 330Km/h, the corresponding airplane wheel speed signal f is 2750Hz and V p_p Frequency signal of more than or equal to 0.6V and corresponding wheel speed voltage V ωk 12.5V, corresponding reference speed voltage V ωR 12.4V, slip failure rate of 30 +8 Km/h, corresponding wheel speed voltage V ωk 4V, corresponding reference speed voltage V ωR 3.9V;
when the static brake is effective, the 1 st foot output voltage of the operational amplifier U1 is 16.5V, and the operational amplifier U1 forms a hysteresis comparison characteristic circuit through the second diode D2 and the sixth resistor R6. The static braking action voltage is 4.42V, and the corresponding aircraft speed value is 34.8Km/h.
During static braking protection, the output voltage of the 1 pin of the operational amplifier U1 is 0.5V, and the operational amplifier U1 forms a hysteresis comparison characteristic circuit through the third diode D3 and the fifth resistor R5. The static brake protection voltage is 10.15V, and the corresponding aircraft speed value is 190.8Km/h.
The hysteresis characteristic of the static brake protection circuit corresponds to the aircraft speed difference of 190.8-34.8=156 Km/h; the corresponding reference speed voltage difference is 10.15-4.42=5.73V.
According to the utility model, by improving the difference between the static brake effect and the static brake protection voltage corresponding to the hysteresis characteristic of the static brake protection circuit, the difference between the static brake effect voltage and the static brake protection voltage is improved from 1.3V to 5.73V, and the corresponding aircraft speed difference is improved from 30.65Km/h to 156Km/h, so that the capability of the static brake protection circuit for resisting instant speed change is improved, the capability of the brake system for resisting external vibration and comprehensive electromagnetic environment interference under the condition of outputting static brake pressure is improved, the automatic switching between the static brake effect and static brake failure state caused by external interference is eliminated, and the stability of the static brake system is improved.
Drawings
FIG. 1 is a schematic diagram of a static brake protection circuit of the prior art
FIG. 2 is a schematic diagram of the static brake protection circuit of the present utility model
Detailed Description
Example 1
The embodiment is a static brake protection circuit with anti-interference capability.
The static brake protection circuit with the anti-interference capability is a comparison circuit manufactured by an operational amplifier U1 and comprises the operational amplifier U1, 6 resistors and 3 diodes. The 6 resistors are respectively marked as a first resistor R1 to a sixth resistor R6; the 3 diodes are respectively marked as a first diode D1 to a third diode D3.
In this embodiment, the 8 th pin of the operational amplifier U1 is a power input end and is in communication with the +18v.dc power supply, and the 8 th pin of the operational amplifier U1 is a power input end; and the 4 th pin of the operational amplifier U1 is communicated with a ground wire. The 1 st pin of the operational amplifier U1 is simultaneously communicated with one end of a fifth resistor R5 and one end of a sixth resistor R6; the other end of the fifth resistor R5 is communicated with the cathode of a third diode, and the anode of the third diode is communicated with the 3 rd pin of the operational amplifier U1; the other end of the sixth resistor R6 is communicated with the anode of a second diode, and the cathode of the second diode is communicated with the 3 rd pin of the operational amplifier U1; the 3 rd pin of the operational amplifier U1 is simultaneously communicated with one end of the second resistor R2 and one end of the third resistor R3; the other end of the second resistor R2 is communicated with one end of a fourth resistor R4, and the other end of the fourth resistor R4 is communicated with a +18V.DC power supply; the other end of the third resistor R3 is communicated with the ground wire. The 2 nd pin of the operational amplifier U1 is communicated with the cathode of the first diode, and is simultaneously communicated with one end of a first resistor R1, and the other end of the first resistor R1 is communicated with a ground wire. The positive pole of the first diode is communicated with the output end of the reference speed module in the aircraft brake control box.
The output voltage of the 1 st pin of the operational amplifier U1 is 0.5V, and the 1 st pin and the 3 rd pin of the operational amplifier U1 form a static brake protection hysteresis comparison characteristic circuit through a third diode D3 and a fifth resistor R5.
The output voltage of the 1 st pin of the operational amplifier U1 is 16.5V, and the 1 st pin, the 3 rd pin, the second diode and the sixth resistor R6 of the operational amplifier U1 form a static brake effect hysteresis comparison characteristic circuit.
The first diode D1, the second diode D2 and the third diode D3 all adopt BZ03C diodes.
In this embodiment, when the maximum speed of the aircraft is 330Km/h, the corresponding parameters are: the speed signal f of the wheel is 2750Hz, V p_p Frequency signal not less than 0.6V, and speed voltage V of locomotive ωk 12.5V, reference speed voltage V ωR Is 12.4V. The anti-slip failure speed is 30 +8 When Km/h, the corresponding wheel speed voltage V ωk 4V, reference speed voltage V ωR Is 3.9V. During static brake protection, the 3 rd foot voltage of the operational amplifier U1 is 10.15V, and the speed of the airplane is 190.8Km/h. When the static brake is effective, the 3 rd foot voltage of the operational amplifier U1 is 4.42V, and the speed of the airplane is 34.8Km/h.
When in operation, the device comprises:
when the speed of the aircraft changes from high to low, the static brake protection circuit changes from static brake protection to static brake effect. During static brake protection, the 3 rd pin voltage of the operational amplifier U1 is 10.15V, and the 1 st pin output voltage of the operational amplifier U1 is 0.5V; when the voltage of the 2 nd pin of the operational amplifier U1 drops below 4.42V, the output voltage of the 1 st pin of the operational amplifier U1 is 16.5V, and the static brake is effective; the 3 rd leg voltage of the operational amplifier U1 is 4.42V, which corresponds to an aircraft speed value of 34.8Km/h.
When the speed of the aircraft changes from low to high, the static brake protection circuit changes from the static brake effect to the static brake protection, and when the static brake effect is achieved, the 1 st foot output voltage of the operational amplifier U1 is 16.5V, and the 3 rd foot voltage of the operational amplifier U1 is 4.42V; when the voltage of the 2 nd pin of the operational amplifier U1 is increased to above 10.15V, and the output voltage of the 1 st pin of the operational amplifier U1 is changed to 0.5V, the voltage of the 3 rd pin of the operational amplifier U1 is 10.15V, and the corresponding aircraft speed value is 190.8Km/h.
Example 2
The embodiment provides a design method of the static brake protection circuit with the anti-interference capability, which comprises the following specific processes:
step one: parameters of all electronic components in the static brake protection hysteresis comparison characteristic circuit are determined:
and determining parameters of all electronic components in the static brake protection hysteresis comparison characteristic circuit according to the static brake protection voltage.
When the static brake is effective, the output voltage of the 1 pin of the operational amplifier U1 is 16.5V, and the operational amplifier U1 forms a static brake protection hysteresis comparison characteristic circuit through the third diode D3 and the sixth resistor R6.
The static brake protection voltage is set according to the aircraft speed by adopting a conventional method. The static brake protection voltage is a voltage value corresponding to the static brake protection speed.
Each electronic component comprises a resistor, an operational amplifier and a diode; the parameters of each electronic component comprise the resistance value of each resistor, the model of an operational amplifier and the model of a diode.
In this embodiment, the aircraft static brake protection speed is set to be 190.8Km/h, and the voltage value corresponding to the speed is set to be 10.15V, namely the voltage of the 3 rd pin of the set operational amplifier U1.
In this embodiment, the operational amplifier U1 is an F158 operational amplifier. The resistance value of the first resistor R1 is determined to be 10kΩ, the resistance value of the second resistor R2 is determined to be 0.681kΩ, the resistance value of the third resistor R3 is determined to be 4.64kΩ, the resistance value of the fourth resistor R4 is determined to be 12kΩ, the resistance value of the fifth resistor R5 is determined to be 43kΩ, and the third diode D3 is a BZ03C diode.
Step two: determining parameters of all electronic components in the active hysteresis comparison characteristic circuit:
determining parameters of all electronic components in the actuation hysteresis comparison characteristic circuit according to the static brake actuation voltage:
each electronic component comprises a sixth resistor R6 and a second diode D2; the parameters of each electronic component include the resistance value of the sixth resistor R6 and the model of the second diode D2. And setting the effective speed of the aircraft static brake, wherein the voltage value corresponding to the speed is the voltage of the 3 rd pin of the operational amplifier U1.
And determining the model and parameters of the second diode D2 and the sixth resistor R6 through ohm's law according to the set static brake protection effective voltage.
In this embodiment, the second diode D2 is a BZ03C diode, and the resistance of the sixth resistor R6 is 5.1kΩ.
Thus, the design of the static brake protection circuit with the anti-interference capability is completed.
Claims (5)
1. A static brake protection circuit with anti-interference capability is characterized in that an operational amplifier is adopted to manufacture a comparison circuit; the comparison circuit comprises an operational amplifier, 6 resistors and 3 diodes; the 6 resistors are sequentially marked as a first resistor to a sixth resistor, and the 3 diodes are sequentially marked as a first diode to a third diode; wherein:
the 8 th pin of the operational amplifier is a power input end and is communicated with a +18V.DC power supply; the 4 th pin of the operational amplifier is communicated with a ground wire; the 1 st pin of the operational amplifier is simultaneously communicated with one end of the fifth resistor and one end of the sixth resistor; the other end of the fifth resistor is communicated with the cathode of a third diode, and the anode of the third diode is communicated with the 3 rd pin of the operational amplifier; the other end of the sixth resistor is communicated with the anode of a second diode, and the cathode of the second diode is communicated with the 3 rd pin of the operational amplifier; the 3 rd pin of the operational amplifier is simultaneously communicated with one end of the second resistor and one end of the third resistor; the other end of the second resistor is communicated with one end of a fourth resistor, and the other end of the fourth resistor is communicated with a +18V.DC power supply; the other end of the third resistor is communicated with a ground wire; the 2 nd pin of the operational amplifier is communicated with the cathode of the first diode, and is simultaneously communicated with one end of a first resistor, and the other end of the first resistor is communicated with a ground wire; the anode of the first diode is communicated with the output end of the reference speed module in the aircraft brake control box;
the design method of the static brake protection circuit with the anti-interference capability comprises the following specific processes:
step one: parameters of all electronic components in the static brake protection hysteresis comparison characteristic circuit are determined:
determining parameters of all electronic components in the static brake protection hysteresis comparison characteristic circuit according to the static brake protection voltage;
setting static brake protection voltage according to the aircraft speed; the static brake protection voltage is a voltage value corresponding to the static brake protection speed;
each electronic component comprises a fifth resistor, an operational amplifier and a third diode; the parameters of each electronic component comprise the resistance value of each resistor, the model of an operational amplifier and the model of a diode;
setting the static brake protection speed of the aircraft, wherein the voltage value corresponding to the speed is the voltage of the 3 rd pin of the operational amplifier;
step two: determining parameters of all electronic components in the active hysteresis comparison characteristic circuit:
determining parameters of all electronic components in the actuation hysteresis comparison characteristic circuit according to the static brake actuation voltage:
each electronic component comprises a sixth resistor and a second diode; the parameters of each electronic component comprise the resistance value of the sixth resistor and the model of the second diode;
setting the aircraft static brake acting speed, wherein the voltage value corresponding to the speed is the aircraft static brake acting voltage; the aircraft static brake active voltage is the voltage of the 3 rd pin of the operational amplifier;
thus, the design of the static brake protection circuit with the anti-interference capability is completed.
2. The static brake protection circuit with anti-interference capability as claimed in claim 1, wherein the 1 st pin, the 3 rd pin, the third diode and the fifth resistor of the operational amplifier form a static brake protection hysteresis comparison characteristic circuit; the 1 st pin, the 3 rd pin, the second diode and the sixth resistor of the operational amplifier form an effective hysteresis comparison characteristic circuit.
3. The static brake protection circuit with anti-jamming capability according to claim 1, wherein the static brake protection circuit transitions from a static brake protection state to a static brake active state when the speed of the aircraft changes from high to low; in the static brake protection state, the 3 rd pin voltage of the operational amplifier is 10.15V, and the 1 st pin output voltage of the operational amplifier is 0.5V; when the voltage of the 2 nd pin of the operational amplifier drops below 4.42V, the output voltage of the 1 st pin of the operational amplifier is 16.5V, and the static brake is effective; meanwhile, the 3 rd foot voltage of the operational amplifier is 4.42V, and the corresponding aircraft speed value is 34.8Km/h.
4. The static brake protection circuit with anti-jamming capability according to claim 1, wherein when the speed of the aircraft changes from low to high, the static brake protection circuit is switched from a static brake active state to a static brake protection state, and when the static brake is active, the 1 st foot output voltage of the operational amplifier is 16.5V, and the 3 rd foot voltage of the operational amplifier is 4.42V; when the voltage of the 2 nd pin of the operational amplifier is increased to above 10.15V, and the output voltage of the 1 st pin of the operational amplifier is changed to 0.5V, the voltage of the 3 rd pin of the operational amplifier is 10.15V, and the corresponding aircraft speed is 190.8Km/h.
5. The static brake protection circuit with anti-interference capability as claimed in claim 1, wherein said operational amplifier is an F158 operational amplifier, and each of said diodes is BZ03C; the resistance value of the first resistor is determined to be 10KΩ, the resistance value of the second resistor is determined to be 0.681KΩ, the resistance value of the third resistor is determined to be 4.64KΩ, the resistance value of the fourth resistor is determined to be 12KΩ, the resistance value of the fifth resistor is determined to be 43KΩ, and the resistance value of the sixth resistor is determined to be 5.1KΩ.
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| CN204068770U (en) * | 2013-10-30 | 2014-12-31 | 星辉互动娱乐股份有限公司 | Telecar brake polar protective circuit |
| CN105438453A (en) * | 2014-09-28 | 2016-03-30 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft static brake and protection system thereof |
| CN107804453A (en) * | 2017-10-31 | 2018-03-16 | 西安航空制动科技有限公司 | The quiet brake pressure linear control method of digital FBW anti-skid brake system (ABS) |
| CN208472287U (en) * | 2018-05-17 | 2019-02-05 | 河北工业大学 | A kind of embedded braking vane of High Speed Rapier Loom convenient for monitoring |
| CN210761278U (en) * | 2019-09-09 | 2020-06-16 | 西安航空制动科技有限公司 | Static brake protection circuit with anti-interference capability |
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