CN114995225A - Controller based on cockpit cover operating device - Google Patents
Controller based on cockpit cover operating device Download PDFInfo
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- CN114995225A CN114995225A CN202210579375.2A CN202210579375A CN114995225A CN 114995225 A CN114995225 A CN 114995225A CN 202210579375 A CN202210579375 A CN 202210579375A CN 114995225 A CN114995225 A CN 114995225A
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- 238000012545 processing Methods 0.000 claims description 20
- 238000004891 communication Methods 0.000 claims description 16
- 238000001514 detection method Methods 0.000 claims description 15
- 239000003990 capacitor Substances 0.000 claims description 6
- 238000004132 cross linking Methods 0.000 claims description 6
- 239000013585 weight reducing agent Substances 0.000 claims description 6
- 230000009471 action Effects 0.000 claims description 3
- 230000017525 heat dissipation Effects 0.000 claims description 3
- 238000012423 maintenance Methods 0.000 claims description 3
- 230000003287 optical effect Effects 0.000 claims description 3
- 238000000034 method Methods 0.000 description 4
- 238000013461 design Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
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Classifications
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B19/00—Programme-control systems
- G05B19/02—Programme-control systems electric
- G05B19/04—Programme control other than numerical control, i.e. in sequence controllers or logic controllers
- G05B19/042—Programme control other than numerical control, i.e. in sequence controllers or logic controllers using digital processors
- G05B19/0423—Input/output
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B2219/00—Program-control systems
- G05B2219/20—Pc systems
- G05B2219/24—Pc safety
- G05B2219/24215—Scada supervisory control and data acquisition
-
- 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
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Control Of Motors That Do Not Use Commutators (AREA)
Abstract
The invention provides a controller based on a cockpit cover control device, which comprises an MCU (microprogrammed control unit), a switching signal acquisition circuit, a clutch control circuit, a motor drive circuit, a clutch control circuit and a motor drive circuit. The driving control of the aircraft canopy operating device is realized, the aircraft canopy can be safely, stably and reliably opened and closed, and the service life, the fault state and the working state of the aircraft canopy operating device can be conveniently mastered by pilots and ground service personnel.
Description
Technical Field
The invention relates to the technical field of control of aircraft canopy covers, in particular to a controller based on a canopy control device.
Background
With the development of avionics, aircraft canopy operators are shifting from conventional hydraulic control to fly-by-wire control.
The motor driving control of the aircraft canopy operating device has the advantages of high reliability, small volume, light weight and simple and convenient control.
In order to meet the requirements of reliability, simplicity and weight and volume of the driving control of the aircraft canopy manipulating device, a controller of the aircraft canopy manipulating device is needed.
Disclosure of Invention
The invention provides a controller based on a cockpit cover operating device, which has the characteristics of high reliability, small volume, light weight (high power density) and high intelligent degree.
The invention provides a controller based on a cockpit cover control device, which comprises: a first aviation socket 1, a second aviation socket 2, a control board assembly 5 and a brushless motor driver 10; the control board assembly 5 includes: the device comprises an MCU control circuit, a clutch control circuit and an electromagnet control circuit; wherein,
a first aviation socket 1 is installed on a front panel of the controller and is in cross-linking with an airplane, the first aviation socket is used for supplying power to the controller by the airplane, a pilot sends an instruction for opening and closing a hatch cover to the controller through a control switch, and RS422 bus communication is carried out between the pilot and an upper computer;
a second aviation socket 2 is installed on a front panel of the controller and is crosslinked with a canopy control device, and a clutch and a motor in the canopy control device are controlled to work in a power supply and power off mode;
the MCU control circuit is used for completing the acquisition of input signals, hatch cover positions, bus current and the like, generating PWM (pulse-width modulation) waves and F/R (frequency/radio) signals to the brushless motor driver 10 according to corresponding logics, and outputting clutch control signals to the clutch control circuit to control the hatch cover control device to open or close the hatch cover; outputting an electromagnet control signal to an electromagnet control circuit to control the electromagnet;
the clutch control circuit is used for controlling the on-off of the power supply of the clutch in the cockpit cover control device through an MOS pipe;
the electromagnet control circuit is used for controlling the on-off of the electromagnet power supply through a relay with 5V coil voltage, when the controller controls the cabin cover operating device to complete the action of opening or closing the cabin cover according to the instruction of a pilot, the controller supplies power to the electromagnet on the cabin cover through the electromagnet control circuit, the electromagnet automatically resets the onboard operating switch, the instruction of opening the cabin cover or closing the cabin cover is automatically cancelled, and the pilot does not need to manually reset the operating switch.
Optionally, the method further includes: a filter component 4;
the filter assembly 4 is used for converting two input DC28V from the airplane into two DC28V with different working currents and one DC 15V;
wherein, the maximum current of one path of DC28V is 50A, and the DC28V is used for supplying power to a motor driver in the cockpit lid control device; the maximum current of one DC28V is 3.5A and is used for supplying power to the electromagnet on the motor, and the maximum current of one DC15V is 2A and is used for supplying power to a secondary power supply processing circuit of the control board.
Optionally, the control board assembly 5 further includes: an input signal processing circuit;
and the input signal processing circuit uses an optical coupler to electrically isolate a command signal from the airplane and a limit position signal in the hatch cover operating device and send the signal to the MCU control circuit after redundancy processing.
Optionally, the control board assembly 5 further includes: a fault storage circuit and an RS422 communication circuit;
the RS422 communication circuit uses SM3490 as an interface circuit for RS422 communication with an upper computer; reporting the working current, the service life, the feedback related position signal and the fault state in an RS422 bus form;
the fault storage circuit uses an EEPROM as a storage chip and adopts an IIC bus to communicate with the MCU control circuit;
and the MCU control circuit stores the fault information into the EEPROM after detecting the fault, thereby facilitating the maintenance of the controller.
Optionally, the method further includes: a collection plate assembly 6;
the acquisition board assembly 6 comprises a support capacitor circuit and a bus current sensor;
the supporting capacitor circuit is used for supplying one DC28V output from the filter component 4 to the brushless motor driver 10;
and the bus current sensor converts the current generated on one path of DC28V output by the filter component 4 into a 0.5-4.5V voltage analog quantity signal to finish bus current acquisition.
Optionally, the control board assembly 5 further includes: a position detection circuit and a bus current detection circuit;
the position detection circuit is used for converting a cabin cover position signal output by the cabin cover control device into a 0-3.19V signal through the operational amplifier to act on the MCU control circuit, and acquiring the position of the cabin cover in real time to realize an accurate position protection function; the hatch cover position signal is a 0-15V potentiometer signal;
the bus current detection circuit is used for converting a 0.5-4.5V voltage analog quantity signal acquired by a bus current sensor in the acquisition board assembly 6 into 0.33-3V voltage through an operational amplifier and then sending the voltage into the MCU control circuit, and the MCU control circuit acquires the bus voltage in real time to realize the overcurrent protection of the cockpit cover control device.
Optionally, the control board assembly 5 further includes: a secondary power supply processing circuit;
the secondary power supply processing circuit converts one path of DC15V voltage output by the filter component 4 into DC5V and DC3.3V, wherein the DC5V is used for supplying power to the electromagnet control circuit, and DC3.3V is used for supplying power to the fault storage circuit, the RS422 communication circuit, the input signal processing circuit and the MCU control circuit.
Optionally, the method further includes: a controller case 3;
the controller shell 3 is designed by adopting a standard case, and the surface of the controller shell is provided with a weight reduction groove for effective weight reduction and heat dissipation treatment.
Optionally, the brushless motor driver 10 is configured to receive the PWM wave and the F/R signal from the control board assembly 5 to control the motor in the canopy manipulating device to rotate clockwise and counterclockwise to open and close the canopy.
The invention provides a controller based on a cockpit cover control device, which comprises an MCU (microprogrammed control unit), a switching signal acquisition circuit, a clutch control circuit, a motor drive circuit, a clutch control circuit and a motor drive circuit. The driving control of the aircraft canopy operating device is realized, the aircraft canopy can be safely, stably and reliably opened and closed, and the service life, the fault state and the working state of the aircraft canopy operating device can be conveniently mastered by pilots and ground service personnel.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed to be used in the description of the embodiments or the prior art will be briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
FIG. 1 is a schematic front view of the present invention;
FIG. 2 is a schematic view of the internal arrangement of the present invention;
FIG. 3 is a schematic view of the internal arrangement of the present invention;
FIG. 4 is a block diagram of the canopy operator-based controller of the present invention;
description of reference numerals:
the device comprises a first aviation socket 1, a second aviation socket 2, a controller shell 3, a filter assembly 4, a control board assembly 5, an acquisition board assembly 6, a lead 7, a lead 8, a binding wire 9 and a brushless motor driver 10.
Detailed Description
The controller based on the aircraft hatch operating device provided by the invention is explained in the following with reference to the attached drawings.
As shown in fig. 1, the present invention provides a controller based on an aircraft canopy manipulator, which has the characteristics of high reliability, small size, light weight (high power density) and high degree of intelligence. The device not only can meet the functions of unlocking and opening the hatch cover and locking and closing the hatch cover of the aircraft canopy operating device, but also can quickly realize fault detection and positioning of the canopy operating device and the canopy operating device, can report the working current, service life and feedback of relevant position signals and fault states of a product in time in an RS422 bus form, and can realize the function of software on-line upgrading.
As shown in fig. 2 and 3, the present invention provides a controller based on an aircraft canopy manipulating device, comprising: the device comprises a first aviation socket 1, a second aviation socket 2, a controller shell 3, a filter assembly 4, a control board assembly 5, an acquisition board assembly 6, a lead 7, a lead 8, a binding wire 9 and a brushless motor driver 10.
Further, a first aviation socket 1 is installed on a front panel of the controller and is in cross-linking with the airplane, the first aviation socket is used for supplying power to the controller by the airplane, a pilot sends commands for opening and closing the hatch cover to the controller through a control switch, and RS422 bus communication is carried out between the pilot and an upper computer.
Furthermore, a second aviation socket 2 is installed on a front panel of the controller and is in cross-linking with the canopy operating device, and a clutch and a motor in the canopy operating device are controlled to work in a power supply and power failure mode.
Further, the controller housing 3 adopts a standard chassis design, and the controller housing 3 is designed with a weight reduction groove for effective weight reduction and heat dissipation treatment.
Further, the filter assembly 4 shown in fig. 4 enables the controller to meet the requirements of power supply characteristics and electromagnetic compatibility of the whole machine. Meanwhile, two input DC28V from the airplane (the two input DC28V are used for redundancy power supply, and the controller can normally work when any one input power supply is effective) are converted into two DC28V with different working currents (one DC28V is 50A in maximum current and is used for supplying power to a motor driver in the cockpit cover operating device, one DC28V is 3.5A in maximum current and is used for supplying power to an electromagnet on the airplane), and one DC15V (2A in maximum current and is used for supplying power to a secondary power supply processing circuit, a position detection circuit and a bus current detection circuit of a control panel).
Further, as shown in fig. 4, the collecting plate assembly 6 includes a supporting capacitor circuit and a bus current sensor. One DC28V output from the filter assembly 4 is passed through a support capacitor circuit to power the brushless motor driver 10. The bus current sensor converts the current generated by one path of DC28V output by the filter component 4 into a 0.5-4.5V voltage analog quantity signal (corresponding to-100A of the bus current) and then sends the signal into the control board component 5.
Further, as shown in fig. 4, the control board assembly 5 includes a secondary power supply processing circuit, an input signal processing circuit, a position detection circuit, a bus current detection circuit, an MCU control circuit, an RS422 communication circuit, a fault storage circuit, a clutch control circuit, and an electromagnet control circuit.
The secondary power supply processing circuit in the control panel assembly 5 converts one path of DC15V voltage which is not output from the filter assembly 4 into DC5V (used for supplying power to the electromagnet control circuit) and DC3.3V (used for supplying power to the fault storage circuit, the RS422 communication circuit, the input signal processing circuit and the MCU control circuit).
The MCU in the control panel component 5 finishes the collection of input signals, hatch cover positions, bus current and the like, transmits corresponding logic PWM waves and F/R signals to the brushless motor driver 10, and outputs clutch control signals to the clutch control circuit to control the hatch cover control device to open or close the hatch cover; and outputting an electromagnet control signal to an electromagnet control circuit to control the electromagnet.
The input signal processing circuit in the control board assembly 5 uses an optical coupler to electrically isolate and process redundancy of a command signal from an airplane and a limit position signal in a hatch cover control device, and the command signal and the limit position signal are collected by the MCU control circuit.
The position detection circuit in the control board assembly 5 converts a cabin cover position signal (0-15V analog voltage quantity) from the cabin cover operating device into 0-3.19V voltage through an operational amplifier and then enters an AD acquisition port of the MCU, and the MCU acquires the position of the cabin cover in real time to realize an accurate position protection function.
The bus current detection circuit in the control board assembly 5 converts a 0.5-4.5V voltage analog quantity signal output by a bus current sensor in the acquisition board assembly 6 into 0.33-3V voltage through an operational amplifier and then enters an AD acquisition port of the MCU, and the MCU acquires the bus voltage in real time to realize the overcurrent protection of the cockpit cover control device.
The RS422 communication circuit in the control board assembly 5 uses SM3490 as an interface circuit for RS422 communication with an upper computer. The controller reports the working current, the service life, the feedback related position signal and the fault state of the product in an RS422 bus mode. The online upgrade data of the controller software is also sent to the MCU through the RS422 communication circuit, and the fault storage circuit in the control panel component 5 uses the EEPROM as a storage chip and adopts the IIC bus to communicate with the MCU. And after the MCU detects the fault, the fault information is stored in the EEPROM, so that the maintenance of the controller is facilitated.
And a clutch control circuit in the control board assembly 5 controls the on-off of the power supply of a clutch in the canopy operating device through an MOS pipe.
And an electromagnet control circuit in the control board assembly 5 controls the on-off of the power supply of the electromagnet through a relay with 5V coil voltage. After the controller controls the cabin cover operating device to complete the action of opening or closing the cabin cover according to the instruction of a pilot, the controller supplies power to the onboard electromagnet through the electromagnet control circuit, the onboard control switch is automatically reset by the electromagnet, the instruction of opening or closing the cabin cover is automatically cancelled, and the pilot does not need to manually reset the control switch.
Further, as shown in fig. 4, the brushless motor driver 10 receives the PWM wave and the F/R signal from the MCU control circuit in the control board assembly 5 to control the motor in the canopy manipulating device to rotate clockwise and counterclockwise to open and close the canopy.
Illustratively, the lead wires 7 are used for signal cross-linking between the acquisition board assembly 6 and the control board assembly 5; the wire 8 is used for signal cross-linking between the control board assembly 5 and the brushless motor driver 10 and the second aviation socket 2; the binding 9 is used to fix the lead 8.
In one embodiment of the invention, the controller of the aircraft canopy manipulator basically comprises an MCU, a switching signal acquisition circuit, a clutch control circuit, a motor drive circuit, a clutch control circuit and a motor drive circuit. The driving control of the aircraft canopy operating device is realized, the aircraft canopy can be safely, stably and reliably opened and closed, and the service life, the fault state and the working state of the aircraft canopy operating device can be conveniently mastered by pilots and ground service personnel.
Claims (9)
1. A controller based on an aircraft canopy manipulator, comprising: the device comprises a first aviation socket (1), a second aviation socket (2), a control board assembly (5) and a brushless motor driver (10); the control board assembly (5) comprises: the device comprises an MCU control circuit, a clutch control circuit and an electromagnet control circuit; wherein,
a first aviation socket (1) is installed on a front panel of the controller and is in cross-linking with the airplane, the airplane supplies power to the controller, a pilot sends commands for opening and closing the hatch cover to the controller through a control switch, and RS422 bus communication is carried out between the pilot and an upper computer;
a second aviation socket (2) is installed on a front panel of the controller and is crosslinked with the canopy control device, and a clutch and a motor in the canopy control device are controlled to work in a power supply and power failure mode;
the MCU control circuit is used for completing the acquisition of input signals, hatch cover positions, bus current and the like, generating PWM (pulse-width modulation) waves and F/R (frequency/current) signals to the brushless motor driver (10) according to corresponding logics, and outputting clutch control signals to the clutch control circuit to control the hatch cover control device to open or close the hatch cover; outputting an electromagnet control signal to an electromagnet control circuit to control the electromagnet;
the clutch control circuit is used for controlling the on-off of the power supply of the clutch in the cockpit cover control device through an MOS pipe;
the electromagnet control circuit is used for controlling the on-off of the electromagnet power supply through a relay with 5V coil voltage, when the controller controls the hatch cover operating device to complete the hatch cover opening or closing action according to the pilot instruction, the controller supplies power to the electromagnet on the aircraft through the electromagnet control circuit, the electromagnet automatically resets the on-aircraft operating switch, the hatch cover opening or closing instruction is automatically cancelled, and the pilot does not need to manually reset the operating switch.
2. The controller of claim 1, further comprising: a filter assembly (4);
the filter assembly (4) is used for converting two paths of input DC28V from the airplane into two paths of DC28V with different working currents and one path of DC 15V;
wherein, the maximum current of one path of DC28V is 50A, and the DC28V is used for supplying power to a motor driver in the cockpit lid control device; one path of DC28V has a maximum current of 3.5A and is used for supplying power to the electromechanical magnet, and the other path of DC15V has a maximum current of 2A and is used for supplying power to the secondary power supply processing circuit of the control board.
3. A controller according to claim 2, wherein the control board assembly (5) further comprises: an input signal processing circuit;
and the input signal processing circuit uses an optical coupler to electrically isolate a command signal from the airplane and a limit position signal in the hatch cover operating device and send the signal to the MCU control circuit after redundancy processing.
4. A controller according to claim 3, wherein the control board assembly (5) further comprises: the fault storage circuit and the RS422 communication circuit;
the RS422 communication circuit uses SM3490 as an interface circuit for RS422 communication with an upper computer; reporting the working current, the service life, the feedback related position signal and the fault state in an RS422 bus form;
the fault storage circuit uses an EEPROM as a storage chip and adopts an IIC bus to communicate with the MCU control circuit;
and the MCU control circuit stores the fault information into the EEPROM after detecting the fault, thereby facilitating the maintenance of the controller.
5. The controller of claim 4, further comprising: a collection plate assembly (6);
the acquisition board assembly (6) comprises a supporting capacitor circuit and a bus current sensor;
the supporting capacitor circuit is used for supplying one DC28V output from the filter component (4) to the brushless motor driver (10);
and the bus current sensor converts the current generated on one path of DC28V output by the filter component 4 into a 0.5-4.5V voltage analog quantity signal to finish bus current acquisition.
6. A controller according to claim 5, characterized in that the control board assembly (5) further comprises: a position detection circuit and a bus current detection circuit;
the position detection circuit is used for converting a cabin cover position signal output by the cabin cover control device into a 0-3.19V signal through the operational amplifier to act on the MCU control circuit, and acquiring the position of the cabin cover in real time to realize an accurate position protection function; the hatch cover position signal is a 0-15V potentiometer signal;
the bus current detection circuit is used for converting a 0.5-4.5V voltage analog quantity signal acquired by a bus current sensor in the acquisition board assembly (6) into 0.33-3V voltage through an operational amplifier and then sending the voltage into the MCU control circuit, and the MCU control circuit acquires the bus voltage in real time to realize the overcurrent protection of the cockpit cover control device.
7. A controller according to claim 6, wherein the control board assembly (5) further comprises: a secondary power supply processing circuit;
the secondary power supply processing circuit converts one path of DC15V voltage output by the filter component (4) into DC5V and DC3.3V, wherein the DC5V is used for supplying power to the electromagnet control circuit, and DC3.3V is used for supplying power to the fault storage circuit, the RS422 communication circuit, the input signal processing circuit and the MCU control circuit.
8. The controller of claim 1, further comprising: a controller case (3);
the controller shell (3) is designed by adopting a standard case, and the surface of the controller shell is provided with a weight reduction groove for effective weight reduction and heat dissipation treatment.
9. A controller according to claim 2, characterized in that the brushless motor driver (10) is adapted to receive PWM waves and F/R signals from the control panel assembly (5) to control the electric motor of the canopy actuator to perform clockwise and counterclockwise rotation to open and close the canopy.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210579375.2A CN114995225A (en) | 2022-05-25 | 2022-05-25 | Controller based on cockpit cover operating device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210579375.2A CN114995225A (en) | 2022-05-25 | 2022-05-25 | Controller based on cockpit cover operating device |
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| Publication Number | Publication Date |
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| CN114995225A true CN114995225A (en) | 2022-09-02 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210579375.2A Pending CN114995225A (en) | 2022-05-25 | 2022-05-25 | Controller based on cockpit cover operating device |
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| 仝宇: "航空机电作动器用三环少齿差减速器多体动力学研究", 中国优秀硕士学位论文全文数据库 工程科技Ⅱ辑 * |
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