CN112255476A - Automatic control circuit applied to aircraft rudder surface lock - Google Patents
Automatic control circuit applied to aircraft rudder surface lock Download PDFInfo
- Publication number
- CN112255476A CN112255476A CN202011005014.4A CN202011005014A CN112255476A CN 112255476 A CN112255476 A CN 112255476A CN 202011005014 A CN202011005014 A CN 202011005014A CN 112255476 A CN112255476 A CN 112255476A
- Authority
- CN
- China
- Prior art keywords
- resistor
- surface lock
- diode
- power supply
- control
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000012545 processing Methods 0.000 claims abstract description 45
- 230000033001 locomotion Effects 0.000 claims abstract description 4
- 239000003990 capacitor Substances 0.000 claims description 39
- 238000001514 detection method Methods 0.000 claims description 37
- 239000000126 substance Substances 0.000 claims description 10
- 230000003287 optical effect Effects 0.000 claims description 8
- 102100039435 C-X-C motif chemokine 17 Human genes 0.000 claims description 6
- 101000889048 Homo sapiens C-X-C motif chemokine 17 Proteins 0.000 claims description 6
- 206010063385 Intellectualisation Diseases 0.000 abstract description 3
- 238000010586 diagram Methods 0.000 description 5
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000009347 mechanical transmission Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
- G01R31/005—Testing of electric installations on transport means
- G01R31/008—Testing of electric installations on transport means on air- or spacecraft, railway rolling stock or sea-going vessels
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
- G01R31/34—Testing dynamo-electric machines
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Control Of Electric Motors In General (AREA)
Abstract
The invention provides an automatic control circuit of an aircraft control surface lock, which comprises: the control surface lock power supply control circuit, the control surface lock drive control circuit and the logic processing module are arranged on the control surface lock; the control surface lock power supply control circuit receives the wheel load signal, is connected to the motor body through the control surface lock drive control circuit, and sends a power on/off instruction of the control surface lock motor to the control surface lock drive control circuit according to the wheel load signal; the logic processing module receives the wheel load signal and the instruction, generates enabling control according to the received wheel load signal and/or the instruction, or generates enabling control and a control surface lock unlocking/locking instruction, and sends the enabling control and the control surface lock unlocking/locking instruction to the control surface lock driving circuit; the rudder surface lock driving control circuit is used for controlling the movement direction of the motor according to an unlocking/locking instruction when the power supply of the rudder surface lock motor is switched on according to a power supply switching-on/switching-off instruction and an enabling control switching-on/switching-off power supply of the rudder surface lock motor. Can realize intellectualization and automation.
Description
Technical Field
The invention belongs to the automatic control and fault detection technology of an airplane rudder surface lock, and relates to an automatic control circuit of the airplane rudder surface lock.
Background
The current rudder surface lock comprises a mechanical transmission part and a brush direct current motor part, is used for locking the rudder surface of an airplane after the airplane is stopped, and prevents the damage to the rudder surface of the airplane caused by strong wind and the like, wherein the rudder surface lock of the airplane comprises a left auxiliary wing rudder surface lock, a right auxiliary wing rudder surface lock, a left elevator rudder surface lock, a right elevator rudder surface lock and a rudder surface lock, and the structures and the principles of the five rudder surface locks are the same. The control of the rudder surface locks adopts a series connection control mode, namely, the positive pole/negative pole of the brushed direct current motor of the five rudder surface locks are connected in series into the same loop, the unlocking/locking of the five rudder surface locks can be realized by controlling one switch, if one rudder surface lock fails, the other rudder surface locks cannot be normally unlocked/locked, and the fault positioning of the failed rudder surface lock needs to be manually carried out.
With the development of avionics, an aircraft control system is converting to a multi-electric and full-electric direction, the conventional method for manually controlling an aircraft rudder surface lock at present cannot meet the requirement of automatic control, cannot realize automatic fault detection and accurate positioning of the rudder surface lock, causes great inconvenience to users, and cannot realize intellectualization and automation.
Disclosure of Invention
The purpose of the invention is: the invention provides an automatic control circuit of an aircraft control surface lock, which can realize intellectualization and automation.
The technical scheme of the invention is as follows:
the invention provides an automatic control circuit of an aircraft control surface lock, which comprises: the control surface lock power supply control circuit, the control surface lock drive control circuit and the logic processing module are arranged on the control surface lock; wherein the content of the first and second substances,
the input end of the control surface lock power supply control circuit receives wheel load signals, the output end of the control surface lock power supply control circuit is connected to the input end of the control surface lock drive control circuit, and the output end of the control surface lock drive control circuit is connected to the motor body;
the control surface lock power supply control circuit is used for receiving the wheel load signal and sending a power on/off instruction of the control surface lock motor to the control surface lock drive control circuit according to the wheel load signal;
the input end of the logic processing module receives the wheel load signal and the instruction, the output end of the logic processing module is connected with the input end of the control surface lock drive control circuit,
the logic processing module is used for generating enabling control or generating enabling control and rudder surface lock unlocking/locking instructions according to the received wheel load signals and/or instructions and sending generated information to the rudder surface lock driving control circuit;
the rudder surface lock driving control circuit is used for controlling the movement direction of the motor according to an unlocking/locking instruction when the power supply of the rudder surface lock motor is switched on according to a power supply switching-on/switching-off instruction of the rudder surface lock motor and enabling control to switch on/off the power supply of the rudder surface lock motor.
Optionally, the automatic control circuit of the aircraft rudder surface lock further includes: a rudder surface lock current detection circuit;
the input end of the rudder surface lock current detection circuit is connected with the output end of the rudder surface lock drive control circuit, the output end of the rudder surface lock current detection circuit is connected to the input end of the logic processing module, and the output end of the logic processing module is connected to the fault display;
the control surface lock current detection circuit is used for detecting the current in the control circuit of the motor and sending the current to the logic processing module;
the logic processing module is used for judging whether the motor fails according to the circuit information provided by the control surface lock current detection circuit, and if the motor fails, sending failure information to a failure display;
and the fault display is used for displaying according to the received fault information.
Optionally, the control surface lock power supply control circuit includes: the circuit comprises a first resistor R1, a second resistor R2, a third resistor R3, a fourth resistor R4, a first diode V1, a second diode V2, a first optocoupler D1, a triode Q1 and a relay J1; wherein the content of the first and second substances,
the first end of the first resistor R1 is connected with a first direct current power supply end from an airplane, the first direct current power supply end provides +28V, the second end of the first resistor R1 is connected with the input anode of a first optical coupler D1, the cathode of a first diode V1 receives a wheel load signal, and the anode of the first diode V1 is connected with the input cathode of a first optical coupler D1;
a first end of the second resistor R2 is connected with a second direct current power supply end VCC, a second end of the second resistor R2 is connected with an output anode of the first optocoupler D1 and a first end of the third resistor R3, and an output cathode of the first optocoupler D1 is grounded;
the second end of the third resistor R3 is connected with the first end of the fourth resistor R4 and the base of the triode Q1, the emitter of the triode Q1 is grounded, the second end of the fourth resistor R4 is connected with the collector of the triode Q1 and the negative end of the coil of the relay J1, the positive end of the coil of the relay J1 is connected with the second direct current power supply terminal VCC, the positive output electrode of the relay J1 is connected with the negative electrode of the second diode V2 and the third direct current power supply terminal from the airplane, the third direct current power supply terminal provides +28V, and the negative output electrode of the relay J1 is connected with the positive electrode of the second diode V2 and the power supply terminal of the control circuit for controlling the rudder surface lock power supply.
Optionally, the control surface lock power supply control circuit further includes: a first capacitor C1, a second capacitor C2, and a third capacitor C3;
a second end of the first resistor R1 is connected with a first end of the first capacitor C1, and a positive electrode of the first diode V1 is connected with a second end of the first capacitor C1;
a second end of the second resistor R2 is connected with a first end of the second capacitor C2, and a second end of the second capacitor C2 is grounded;
the second end of the third resistor R3 is connected to the first end of the third capacitor C3, and the second end of the third capacitor C3 is grounded.
Optionally, the rudder surface lock driving control circuit includes: a fifth resistor R5, a sixth resistor R6, a seventh resistor R7, an eighth resistor R8, a fourth capacitor C4, a fifth capacitor C5, a third diode V3, a fourth diode V4, a fifth diode V5, a sixth diode V6, a seventh diode V7, an eighth diode V8, a second optical coupler D2, a third optical coupler D3 and a driver U1; wherein the content of the first and second substances,
a first end of the fifth resistor R5 is connected with the fourth direct-current power supply end VCC1, a second end of the fifth resistor R5 is connected with an input anode of the second optocoupler D2, a cathode of the seventh diode V7 receives enabling control output by the logic processing module, an anode of the seventh diode V7 is connected with an input cathode of the second optocoupler D2, a first end of the seventh resistor R7 is connected with the second direct-current power supply end VCC, and a second end of the seventh resistor R7 is connected with an output anode of the second optocoupler D2 and an enabling input end of the driver U1;
a first end of a sixth resistor R6 is connected with a fourth direct current power supply end VCC1, a second end of a sixth resistor R6 is connected with an input anode of a third optocoupler D3, a cathode of an eighth diode V8 receives a control surface lock unlocking/locking instruction output by a logic processing module, an anode of an eighth diode V7 is connected with an input cathode of a third optocoupler D3, a first end of an eighth resistor R8 is connected with the second direct current power supply end VCC, and a second end of the eighth resistor R8 is connected with an output anode of a third optocoupler D3 and a forward and reverse control end of a driver U1;
a first motor drive output end of the driver U1 is connected with a cathode of the fifth diode V5 and an anode of the sixth diode V6, a second motor drive output end of the driver U1 is connected with a cathode of the fifth diode V3 and an anode of the sixth diode V4, a power supply end of the driver U1 is connected with a first end of the fourth capacitor C4, a first end of the fifth capacitor C5 and an output end of the control surface lock power supply control circuit, an anode of the third diode V3 is connected with a lock-on end of the motor, a cathode of the fourth diode V4 is connected with an unlock + end of the motor, an anode of the fifth diode V5 is connected with an unlock-on end of the motor, and a cathode of the sixth diode V6 is connected with a lock-on end of the motor.
Optionally, the rudder surface lock driving control circuit further includes: a ninth resistor R9 and a tenth resistor R10;
a forward rotation current collecting end of the driver U1 is connected with a first end of a ninth resistor R9 and an input end of the first control surface lock current detection circuit, and a second end of the ninth resistor R9 is grounded;
the reverse current collecting end of the driver U1 is connected with the first end of the tenth resistor R10 and the input end of the second rudder surface lock current detection circuit, and the second end of the tenth resistor R10 is grounded.
Optionally, the first control surface lock current detection circuit includes: an eleventh resistor R11, a twelfth resistor R12, a thirteenth resistor R13, a fourteenth resistor R14 and a first operational amplifier U2; wherein the content of the first and second substances,
an inverting input end of the first operational amplifier U2 is connected with a second end of the eleventh resistor R11 and a first end of the fourteenth resistor R14, and a first end of the eleventh resistor R11 is grounded;
the non-inverting input end of the first operational amplifier U2 is connected with the second end of the twelfth resistor R12 and the first end of the thirteenth resistor R13, the first end of the twelfth resistor R12 is connected with the forward rotation current collecting end of the driver U1, and the second end of the thirteenth resistor R13 is grounded;
the output end of the first operational amplifier U2 is connected with the second end of the fourteenth resistor R14 and the current collecting end of the logic processing module.
Optionally, the second control surface lock current detection circuit includes: a fifteenth resistor R15, a sixteenth resistor R16, a seventeenth resistor R17, an eighteenth resistor R18 and a second operational amplifier U3; wherein the content of the first and second substances,
the inverting input end of the second operational amplifier U3 is connected with the second end of the fifteenth resistor R15 and the first end of the eighteenth resistor R18, and the first end of the fifteenth resistor R15 is grounded;
the non-inverting input end of the second operational amplifier U3 is connected with the second end of the sixteenth resistor R16 and the first end of the seventeenth resistor R17, the first end of the sixteenth resistor R16 is connected with the inverting current collecting end of the driver U1, and the second end of the seventeenth resistor R17 is grounded;
the output end of the second operational amplifier U3 is connected with the second end of the eighteenth resistor R18 and the current collecting end of the logic processing module.
Optionally, the logic processing module is configured to determine whether the motor fails according to circuit information provided by the first control surface lock current detection circuit or the second control surface lock current detection circuit.
The automatic control circuit of the aircraft rudder surface lock provided by the invention can realize locking and unlocking control of the rudder surface lock, can realize rapid fault detection and positioning of the rudder surface lock, adopts a standardized, modularized and functionalized design mode, is beneficial to popularization and application of a control device, reduces the cost and the weight, and meets the automatic control requirement of the novel aircraft rudder surface lock.
Drawings
FIG. 1 is a schematic structural diagram of an automatic control circuit of an aircraft control surface lock provided by the invention;
FIG. 2 is a schematic structural diagram of a control surface lock power supply control circuit provided by the invention;
FIG. 3 is a schematic structural diagram of a control surface lock driving control circuit provided by the invention;
FIG. 4a is a first schematic structural diagram of a control surface lock current detection circuit provided by the present invention;
fig. 4b is a schematic structural diagram of the control surface lock current detection circuit provided by the invention.
Detailed Description
The present invention is described in further detail below. The structure and the principle of the five control surface locks are the same, and referring to fig. 1, the automatic control and fault detection circuit of the airplane control surface lock comprises a control surface lock power supply control circuit, a control surface lock drive control circuit, a control surface lock current detection circuit and a logic processing module.
The input end of the control surface lock power supply control circuit is connected with a wheel load signal, the output end of the control surface lock power supply control circuit is connected to the input end of a control surface lock drive control circuit, the input end of the control surface lock drive control circuit is also connected to the output end of a logic processing module, the output end of the control surface lock drive control circuit is connected to a motor body, the output end of the control surface lock drive control circuit is also connected to the input end of a control surface lock current detection circuit, the output end of the control surface lock current detection circuit is connected to the input end of the logic processing module, the output end of the logic processing module is connected to a fault display, and the input end of the logic processing module is connected to;
the control surface lock power supply control circuit is used for detecting the wheel load signal and judging whether to switch on/off the power supply to the control surface lock drive circuit;
the control surface lock driving control circuit is used for controlling the motion direction of the motor according to an unlocking/locking instruction when the power supply of the control surface lock motor is switched on;
the control surface lock current detection circuit is used for detecting the current of the motor control circuit, and inputting the current into the logic processing module after calculation;
the logic processing module outputs an enabling control instruction or an enabling control and unlocking locking instruction to the control surface lock driving control circuit according to the received wheel load and instruction, analyzes a signal input by the control surface lock current detection circuit, judges whether the motor is in fault or not, and sends fault information to fault display if the motor is judged to be in fault.
As shown in fig. 2, the control surface lock power supply control circuit includes a first resistor R1, a second resistor R2, a third resistor R3, a fourth resistor R4, a first capacitor C1, a second capacitor C2, a third capacitor C3, a first diode V1, a second diode V2, a first optocoupler D1, a triode Q1, a relay J1,
wherein, a first end of the first resistor R1 is connected to +28VII from an airplane, a second end of the first resistor R1 is connected to a first end of a first optocoupler D1 and a first end of a first capacitor C1, a first end of a first diode V1 is connected to the wheel load, a second end of the first diode V1 is connected to a second end of the first optocoupler D1 and a second end of a first capacitor C1, a first end of a second resistor R2 is connected to VCC, a second end of the second resistor R2 is connected to a fifth end of the first optocoupler D1, a first end of a second capacitor C2 and a first end of a third resistor R3, a second end of the second capacitor C2 is connected to a fourth end of the first optocoupler D1, a second end of the third resistor R3 is connected to a first end of a third capacitor C3, a first end of a fourth resistor R4 and a first end of a triode Q9, a second end of a third capacitor C82 3 is connected to a first end of a third terminal Q56, a second end of the fourth resistor R8653 and a second end of the triode R8658, the first end of the relay J1 is connected with VCC, the fourth end of the relay J1 is connected with the first end of the second diode V2 and +28V1 from the airplane, and the third end of the relay J1 is connected with the second end of the second diode V2 and the third end of the U1 of the control surface lock power supply control circuit;
as shown in fig. 3, the control surface lock driving control circuit includes a fifth resistor R5, a sixth resistor R6, a seventh resistor R7, an eighth resistor R8, a ninth resistor R9, a tenth resistor R10, a fourth capacitor C4, a fifth capacitor C5, a third diode V3, a fourth diode V4, a fifth diode V5, a sixth diode V6, a seventh diode V7, an eighth diode V8, a second optocoupler D2, a third optocoupler D3, and a driver U1;
a first end of the fifth resistor R5 is connected with VCC1, a second end of the fifth resistor R5 is connected with a first end of a second optocoupler D2, a first end of a seventh diode V7 is connected with an output end from the logic processing module, a second end of a seventh diode V7 is connected with a second end of a second optocoupler D2, a first end of the seventh resistor R7 is connected with VCC, and a second end of the seventh resistor R7 is connected with a fifth end of a second optocoupler D2 and a tenth end of a driver U1;
a first end of a sixth resistor R6 is connected with VCC1, a second end of a sixth resistor R6 is connected with a first end of a third optocoupler D3, a first end of an eighth diode V8 is connected with an output end from a logic processing module, a second end of an eighth diode V7 is connected with a second end of a third optocoupler D3, a first end of an eighth resistor R8 is connected with VCC, and a second end of an eighth resistor R8 is connected with a fifth end of a third optocoupler D3 and a seventh end of a driver U1;
the fourth end of the driver U1 is connected with the first end of a ninth resistor R9 and the first end of a twelfth resistor R12 of the control surface lock current detection circuit; a second end of the driver U1 is connected with a first end of a tenth resistor R10 and a first end of a sixteenth resistor R16 of the control surface lock current detection circuit, a first end of the driver U1 is connected with a first end of a fifth diode V5 and a second end of a sixth diode V6, a fifth end of the driver U1 is connected with a first end of a fifth diode V3 and a second end of a sixth diode V4, a third end of the driver U1 is connected with a first end of a fourth capacitor C4, a first end of a fifth capacitor C5 and a second end of a second diode V2 of the control surface lock power supply control circuit, a second end of a third diode V3 is connected with a lock of the motor, a first end of a fourth diode V4 is connected with an unlock of the motor, a second end of a fifth diode V5 is connected with an unlock of the motor, and a first end of a sixth diode V6 is connected with the lock of the motor +;
as shown in fig. 4a, the rudder surface lock current detection circuit includes an eleventh resistor R11, a twelfth resistor R12, a thirteenth resistor R13, a fourteenth resistor R14, a fifteenth resistor R15, a sixteenth resistor R16, a seventeenth resistor R17, an eighteenth resistor R18, a first operational amplifier U2, and a second operational amplifier U3;
the second end of the first operational amplifier U2 is connected with the second end of the eleventh resistor R11 and the first end of the fourteenth resistor R14, the third end of the first operational amplifier U2 is connected with the second end of the twelfth resistor R12 and the first end of the thirteenth resistor R13, the first end of the twelfth resistor R12 is connected with the first end of the ninth resistor R9 of the control surface lock drive control circuit, and the sixth end of the first operational amplifier U2 is connected with the input end of the logic processing module;
as shown in fig. 4b, the second end of the second operational amplifier U3 is connected to the second end of the fifteenth resistor R15 and the first end of the eighteenth resistor R18, the third end of the first operational amplifier U2 is connected to the second end of the sixteenth resistor R16 and the first end of the seventeenth resistor R17, the first end of the sixteenth resistor R16 is connected to the first end of the tenth resistor R10 of the rudder surface lock driving control circuit, and the sixth end of the second operational amplifier U3 is connected to the input end of the logic processing module.
When the wheel load of the first end of the first diode V1 of the control surface lock power supply control circuit is low level, the airplane is considered to be in a shutdown state at the moment, the power supply of the airplane control surface lock can be switched on, the front stage of the first optocoupler D1 is conducted at the moment, the rear stage of the first optocoupler D1 is low level at the moment, the third resistor R3 and the fourth resistor R4 are in low level due to voltage division, the first end and the third end of the triode Q1 cause voltage difference at the moment, the second end and the third end of the triode Q1 are conducted, the first end and the second end of the relay J1 have current, the third end and the fourth end of the relay J1 are switched on, and the third end of the driver U1 of the control surface lock drive control circuit is;
when the first end of the first diode V1 of the control surface lock power supply control circuit is in an open circuit, the airplane is considered to be in a flying state at the moment, the front stage of the first optocoupler D1 is not conducted, the first end and the third end of the triode Q1 have no voltage difference, the second end and the third end of the triode Q1 cannot be conducted, the coils of the first end and the second end of the relay J1 have no current, the third end and the fourth end of the relay J1 cannot be conducted, and the third end of the driver U1 of the control surface lock drive control circuit cannot be conducted with the +28V1, so that the safety of the airplane in the flying state is ensured;
when the first end of a seventh diode V7 of the control surface lock driving control circuit is at a low level, the fifth end of a second optocoupler D2 is pulled down, the tenth end of a driver U1 is enabled to be turned on at the moment, a motor can be driven, otherwise the motor cannot be driven, when the first pin of an eighth diode V8 is at a low level, the fifth end of a third optocoupler D3 is pulled down, the seventh end of a driver U1 is at a low level, the motor starts unlocking, namely the fifth end of the U1 driver outputs high voltage, the first end of the motor is connected through a fourth diode V4, the high voltage flows through the motor, the high voltage enters the first end of the U1 driver through a fifth diode V5, and the control surface lock starts unlocking;
when the first end of a seventh diode V7 of the control surface lock driving control circuit is at a low level, the fifth end of a second optocoupler D2 is pulled down, the tenth end of a driver U1 is enabled to be turned on at the moment, a motor can be driven, otherwise the motor cannot be driven, when the first pin of an eighth diode V8 is at a high level, the fifth end of the third optocoupler D3 is pulled up, the seventh end of the driver U1 is at a high level, the motor starts to be locked, namely the first end of the U1 driver outputs a high voltage, the second end of the motor is connected through a sixth diode V6, the high voltage flows through the motor, the high voltage enters the fifth end of the U1 driver through the third diode V3, and the control surface lock starts to be locked;
when the first end of a seventh diode V7 of the control surface lock driving control circuit is at a high level, the fifth end of a second optocoupler D2 is pulled high, and at the moment, the tenth end of a driver U1 cannot be opened to drive a motor;
when the control surface lock current detection circuit unlocks the motor, the fourth end of the driver U1 converts current into voltage through a ninth resistor R9, and the voltage is calculated through an operational amplifier U2 and output to the logic processing module; when the control surface lock current detection circuit locks the motor, the second end of the driver U1 converts the current into voltage through a tenth resistor R10, and the voltage is calculated through an operational amplifier U3 and output to the logic processing module;
the logic processing module receives an instruction and a wheel load from an airplane, when the wheel load is at a low level, an enabling control instruction and an unlocking/locking instruction are output to the control surface lock driving control circuit, the driving motor is unlocked/locked, meanwhile, the unlocking/locking current is detected, when the current exceeds a threshold value, or the logic processing module sends the driving instruction to the control surface lock driving control circuit and the motor current is zero, the motor fault is judged, and the fault display is reported through the logic processing module.
The logic processing module receives an instruction and a wheel load from the airplane, the wheel load is on, the control plane lock drive control circuit is not controlled by output enable, and the motor cannot act.
Finally, it should be noted that the above examples are only illustrative of the implementation of the present invention and are not limiting. Although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical proposal described in the embodiments can be modified, or some technical features can be equally replaced; such modifications and substitutions do not substantially depart from the spirit and scope of the present invention, and are intended to be included within the scope of the appended claims.
Claims (9)
1. An automatic control circuit for an aircraft control surface lock, comprising: the control surface lock power supply control circuit, the control surface lock drive control circuit and the logic processing module are arranged on the control surface lock; wherein the content of the first and second substances,
the input end of the control surface lock power supply control circuit receives wheel load signals, the output end of the control surface lock power supply control circuit is connected to the input end of the control surface lock drive control circuit, and the output end of the control surface lock drive control circuit is connected to the motor body;
the control surface lock power supply control circuit is used for receiving the wheel load signal and sending a power on/off instruction of the control surface lock motor to the control surface lock drive control circuit according to the wheel load signal;
the input end of the logic processing module receives the wheel load signal and the instruction, the output end of the logic processing module is connected with the input end of the control surface lock drive control circuit,
the logic processing module is used for generating enabling control or generating enabling control and rudder surface lock unlocking/locking instructions according to the received wheel load signals and/or instructions and sending generated information to the rudder surface lock driving control circuit;
the rudder surface lock driving control circuit is used for controlling the movement direction of the motor according to an unlocking/locking instruction when the power supply of the rudder surface lock motor is switched on according to a power supply switching-on/switching-off instruction of the rudder surface lock motor and enabling control to switch on/off the power supply of the rudder surface lock motor.
2. The circuit of claim 1, further comprising: a rudder surface lock current detection circuit;
the input end of the rudder surface lock current detection circuit is connected with the output end of the rudder surface lock drive control circuit, the output end of the rudder surface lock current detection circuit is connected to the input end of the logic processing module, and the output end of the logic processing module is connected to the fault display;
the control surface lock current detection circuit is used for detecting the current in the control circuit of the motor and sending the current to the logic processing module;
the logic processing module is used for judging whether the motor fails according to the circuit information provided by the control surface lock current detection circuit, and if the motor fails, sending failure information to a failure display;
and the fault display is used for displaying according to the received fault information.
3. The circuit of claim 1, wherein the control surface lock power supply control circuit comprises: the circuit comprises a first resistor R1, a second resistor R2, a third resistor R3, a fourth resistor R4, a first diode V1, a second diode V2, a first optocoupler D1, a triode Q1 and a relay J1; wherein the content of the first and second substances,
the first end of the first resistor R1 is connected with a first direct current power supply end from an airplane, the first direct current power supply end provides +28V, the second end of the first resistor R1 is connected with the input anode of a first optical coupler D1, the cathode of a first diode V1 receives a wheel load signal, and the anode of the first diode V1 is connected with the input cathode of a first optical coupler D1;
a first end of the second resistor R2 is connected with a second direct current power supply end VCC, a second end of the second resistor R2 is connected with an output anode of the first optocoupler D1 and a first end of the third resistor R3, and an output cathode of the first optocoupler D1 is grounded;
the second end of the third resistor R3 is connected with the first end of the fourth resistor R4 and the base of the triode Q1, the emitter of the triode Q1 is grounded, the second end of the fourth resistor R4 is connected with the collector of the triode Q1 and the negative end of the coil of the relay J1, the positive end of the coil of the relay J1 is connected with the second direct current power supply terminal VCC, the positive output electrode of the relay J1 is connected with the negative electrode of the second diode V2 and the third direct current power supply terminal from the airplane, the third direct current power supply terminal provides +28V, and the negative output electrode of the relay J1 is connected with the positive electrode of the second diode V2 and the power supply terminal of the control circuit for controlling the rudder surface lock power supply.
4. The circuit of claim 1, wherein the control surface lock power supply control circuit further comprises: a first capacitor C1, a second capacitor C2, and a third capacitor C3;
a second end of the first resistor R1 is connected with a first end of the first capacitor C1, and a positive electrode of the first diode V1 is connected with a second end of the first capacitor C1;
a second end of the second resistor R2 is connected with a first end of the second capacitor C2, and a second end of the second capacitor C2 is grounded;
the second end of the third resistor R3 is connected to the first end of the third capacitor C3, and the second end of the third capacitor C3 is grounded.
5. The circuit of claim 2, wherein the rudder surface lock drive control circuit comprises: a fifth resistor R5, a sixth resistor R6, a seventh resistor R7, an eighth resistor R8, a fourth capacitor C4, a fifth capacitor C5, a third diode V3, a fourth diode V4, a fifth diode V5, a sixth diode V6, a seventh diode V7, an eighth diode V8, a second optical coupler D2, a third optical coupler D3 and a driver U1; wherein the content of the first and second substances,
a first end of the fifth resistor R5 is connected with the fourth direct-current power supply end VCC1, a second end of the fifth resistor R5 is connected with an input anode of the second optocoupler D2, a cathode of the seventh diode V7 receives enabling control output by the logic processing module, an anode of the seventh diode V7 is connected with an input cathode of the second optocoupler D2, a first end of the seventh resistor R7 is connected with the second direct-current power supply end VCC, and a second end of the seventh resistor R7 is connected with an output anode of the second optocoupler D2 and an enabling input end of the driver U1;
a first end of a sixth resistor R6 is connected with a fourth direct current power supply end VCC1, a second end of a sixth resistor R6 is connected with an input anode of a third optocoupler D3, a cathode of an eighth diode V8 receives a control surface lock unlocking/locking instruction output by a logic processing module, an anode of an eighth diode V7 is connected with an input cathode of a third optocoupler D3, a first end of an eighth resistor R8 is connected with the second direct current power supply end VCC, and a second end of the eighth resistor R8 is connected with an output anode of a third optocoupler D3 and a forward and reverse control end of a driver U1;
a first motor drive output end of the driver U1 is connected with a cathode of the fifth diode V5 and an anode of the sixth diode V6, a second motor drive output end of the driver U1 is connected with a cathode of the fifth diode V3 and an anode of the sixth diode V4, a power supply end of the driver U1 is connected with a first end of the fourth capacitor C4, a first end of the fifth capacitor C5 and an output end of the control surface lock power supply control circuit, an anode of the third diode V3 is connected with a lock-on end of the motor, a cathode of the fourth diode V4 is connected with an unlock + end of the motor, an anode of the fifth diode V5 is connected with an unlock-on end of the motor, and a cathode of the sixth diode V6 is connected with a lock-on end of the motor.
6. The circuit of claim 5, wherein the rudder surface lock drive control circuit further comprises: a ninth resistor R9 and a tenth resistor R10;
a forward rotation current collecting end of the driver U1 is connected with a first end of a ninth resistor R9 and an input end of the first control surface lock current detection circuit, and a second end of the ninth resistor R9 is grounded;
the reverse current collecting end of the driver U1 is connected with the first end of the tenth resistor R10 and the input end of the second rudder surface lock current detection circuit, and the second end of the tenth resistor R10 is grounded.
7. The circuit of claim 6, wherein the first control plane lock current detection circuit comprises: an eleventh resistor R11, a twelfth resistor R12, a thirteenth resistor R13, a fourteenth resistor R14 and a first operational amplifier U2; wherein the content of the first and second substances,
an inverting input end of the first operational amplifier U2 is connected with a second end of the eleventh resistor R11 and a first end of the fourteenth resistor R14, and a first end of the eleventh resistor R11 is grounded;
the non-inverting input end of the first operational amplifier U2 is connected with the second end of the twelfth resistor R12 and the first end of the thirteenth resistor R13, the first end of the twelfth resistor R12 is connected with the forward rotation current collecting end of the driver U1, and the second end of the thirteenth resistor R13 is grounded;
the output end of the first operational amplifier U2 is connected with the second end of the fourteenth resistor R14 and the current collecting end of the logic processing module.
8. The circuit of claim 6, wherein the second rudder surface locking current detecting circuit comprises: a fifteenth resistor R15, a sixteenth resistor R16, a seventeenth resistor R17, an eighteenth resistor R18 and a second operational amplifier U3; wherein the content of the first and second substances,
the inverting input end of the second operational amplifier U3 is connected with the second end of the fifteenth resistor R15 and the first end of the eighteenth resistor R18, and the first end of the fifteenth resistor R15 is grounded;
the non-inverting input end of the second operational amplifier U3 is connected with the second end of the sixteenth resistor R16 and the first end of the seventeenth resistor R17, the first end of the sixteenth resistor R16 is connected with the inverting current collecting end of the driver U1, and the second end of the seventeenth resistor R17 is grounded;
the output end of the second operational amplifier U3 is connected with the second end of the eighteenth resistor R18 and the current collecting end of the logic processing module.
9. The circuit of claim 6, wherein the logic processing module is configured to determine whether the motor is faulty according to circuit information provided by the first control surface lock current detection circuit or the second control surface lock current detection circuit.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011005014.4A CN112255476A (en) | 2020-09-22 | 2020-09-22 | Automatic control circuit applied to aircraft rudder surface lock |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011005014.4A CN112255476A (en) | 2020-09-22 | 2020-09-22 | Automatic control circuit applied to aircraft rudder surface lock |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112255476A true CN112255476A (en) | 2021-01-22 |
Family
ID=74232603
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011005014.4A Pending CN112255476A (en) | 2020-09-22 | 2020-09-22 | Automatic control circuit applied to aircraft rudder surface lock |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112255476A (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103303466A (en) * | 2012-03-09 | 2013-09-18 | 陕西飞机工业（集团）有限公司 | Error-preventing electrical control method and system for airplane control plane lock |
| CN103324202A (en) * | 2013-07-12 | 2013-09-25 | 无锡华航电子科技有限责任公司 | Fault tolerance flight control system and method based on control surface faults |
| CN103475297A (en) * | 2013-09-27 | 2013-12-25 | 中国航天科技集团公司烽火机械厂 | Electric steering gear control method and electric steering gear controller |
| CN106184812A (en) * | 2016-08-17 | 2016-12-07 | 中国航空工业集团公司西安飞行自动控制研究所 | A kind of aircraft handling rudder face automatic zero-setting method |
| CN109521750A (en) * | 2018-03-16 | 2019-03-26 | 陕西飞机工业（集团）有限公司 | A kind of parking brake steerable system |
| CN109703777A (en) * | 2018-10-26 | 2019-05-03 | 中国飞行试验研究院 | A kind of rudder face card resistance system for fax airplane in transportation category flight test |
| CN109703780A (en) * | 2018-10-26 | 2019-05-03 | 中国飞行试验研究院 | A kind of fax airplane in transportation category flight test rudder face card resistance implementation method |
-
2020
- 2020-09-22 CN CN202011005014.4A patent/CN112255476A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103303466A (en) * | 2012-03-09 | 2013-09-18 | 陕西飞机工业（集团）有限公司 | Error-preventing electrical control method and system for airplane control plane lock |
| CN103324202A (en) * | 2013-07-12 | 2013-09-25 | 无锡华航电子科技有限责任公司 | Fault tolerance flight control system and method based on control surface faults |
| CN103475297A (en) * | 2013-09-27 | 2013-12-25 | 中国航天科技集团公司烽火机械厂 | Electric steering gear control method and electric steering gear controller |
| CN106184812A (en) * | 2016-08-17 | 2016-12-07 | 中国航空工业集团公司西安飞行自动控制研究所 | A kind of aircraft handling rudder face automatic zero-setting method |
| CN109521750A (en) * | 2018-03-16 | 2019-03-26 | 陕西飞机工业（集团）有限公司 | A kind of parking brake steerable system |
| CN109703777A (en) * | 2018-10-26 | 2019-05-03 | 中国飞行试验研究院 | A kind of rudder face card resistance system for fax airplane in transportation category flight test |
| CN109703780A (en) * | 2018-10-26 | 2019-05-03 | 中国飞行试验研究院 | A kind of fax airplane in transportation category flight test rudder face card resistance implementation method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US10854405B2 (en) | Relay diagnostic circuit | |
| CN205880149U (en) | Well power relay contact adhesion detection circuitry | |
| CN105281552A (en) | Gate drive under-voltage detection | |
| CN102060220A (en) | Automatic rescue device for elevator | |
| CN101593961A (en) | DC power supply short-circuit protection circuit based on contactless current sample | |
| CN210924252U (en) | Electric automobile direct current rifle signal processing circuit that charges and affirmation system | |
| CN109596940A (en) | The detection device of power battery charging contacts of contactor adhesion, vehicle | |
| CN112255476A (en) | Automatic control circuit applied to aircraft rudder surface lock | |
| CN101860185A (en) | Frequency converter drive protecting circuit | |
| CN109532497B (en) | High-voltage interlocking control and detection circuit of electric automobile | |
| CN113506706B (en) | Contactor driving circuit with high reliability and working method | |
| CN112511051B (en) | High-reliability miniaturized motor control system for aerospace | |
| CN214450304U (en) | Motor controller power supply device of electric automobile and electric automobile | |
| CN112802241B (en) | Remote vehicle locking control method for pure electric vehicle | |
| CN104375034A (en) | On-board equipment on-off output channel online self-checking system of subway signal system | |
| CN105882421A (en) | Limp control system and limp control method for electric automobile and electric automobile | |
| CN116945948A (en) | Electric automobile fills electric pile CP detecting system | |
| CN214492564U (en) | Locking and unlocking fault detection circuit for electronic lock of direct-current charging gun | |
| CN105730562B (en) | A kind of anti-theft system of electromotor car and a kind of electric vehicle anti-theft method | |
| CN112659935A (en) | High-safety electronic lock control circuit of direct-current charging gun | |
| CN106285247A (en) | A kind of electric door lock controller of automobile | |
| CN210001353U (en) | elevator system | |
| CN113602094A (en) | New energy automobile power-on method and device | |
| CN112440803A (en) | Redundancy monitoring scheme for series modules of medium-high voltage electric vehicle charging station | |
| CN208469767U (en) | A kind of control system of parking braking |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |