CN114995225A - A controller based on a canopy operating device - Google Patents

Abstract

The invention provides a controller based on a cockpit cover manipulation device, comprising an MCU, a switch 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 control device is realized, and the safe, stable and reliable opening and closing of the aircraft canopy can be realized, and the pilots and ground staff can easily grasp the life, fault state and working state of the aircraft canopy control device.

Description

A controller based on a canopy operating device

technical field

The invention relates to the technical field of aircraft canopy manipulation, in particular to a controller based on a canopy manipulation device.

Background technique

With the development of avionics, the control device of the aircraft canopy is changing from the traditional hydraulic control to the electric drive control.

The motor drive control of the aircraft canopy control device requires high reliability, small size, 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 an aircraft canopy operating device, a controller for an aircraft canopy operating device is required.

SUMMARY OF THE INVENTION

The invention provides a controller based on a cockpit cover operating device, which has the characteristics of high reliability, small size, light weight (high power density) and high intelligence.

The present invention provides a controller based on a cockpit cover operating device, comprising: 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: an MCU control circuit , clutch control circuit and electromagnet control circuit; among them,

A first aviation socket 1 is installed on the front panel of the controller to be cross-linked with the aircraft, which is used for the aircraft to supply power to the controller, the pilot to send commands to open and close the hatch cover to the controller by manipulating the switch, and The host computer performs RS422 bus communication;

A second aviation socket 2 is installed on the front panel of the controller to be cross-linked with the cockpit cover operating device, and control the operation of the clutch and the motor in the cockpit cover operating device by means of power supply;

The MCU control circuit is used to complete the collection of input signals, hatch cover positions, bus currents, etc., generate PWM waves and F/R signals according to corresponding logic to the brushless motor driver 10, and output clutch control signals to the clutch control circuit. The circuit controls the hatch control device to open or close the hatch; output the electromagnet control signal to the electromagnet control circuit to control the on-board electromagnet;

The clutch control circuit is used to control the power supply of the clutch in the cockpit cover operating device on and off through a MOS tube;

The electromagnet control circuit is used to control the on-off of the power supply of the electromagnet on the aircraft through a relay whose wire package voltage is 5V. The control circuit supplies power to the on-board electromagnet, and the electromagnet automatically resets the on-board control switch and automatically cancels the command to open or close the hatch without the need for the pilot to manually reset the control switch.

Optionally, it also includes: a filter component 4;

The filter assembly 4 is used to convert the two input DC28V from the aircraft into two DC28V with different working currents and one DC15V;

Among them, the maximum current of one DC28V is 50A, which is used to power the motor driver in the canopy control device; the maximum current of one DC28V is 3.5A, which is used to supply power to the electromagnet on the plane, and the maximum current of one DC15V is 2A, which is used for the secondary control of the control board. The power processing circuit supplies power.

Optionally, the control board assembly 5 further includes: an input signal processing circuit;

The input signal processing circuit uses the optocoupler to electrically isolate the command signal from the aircraft and the limit position signal in the canopy control device, and sends it to the MCU control circuit after performing the electrical isolation and 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 the interface circuit for RS422 communication with the host computer; reports the working current, life, feedback related position signals, and fault status in the form of RS422 bus;

The fault storage circuit uses EEPROM as a storage chip, and uses an IIC bus to communicate with the MCU control circuit;

After the MCU control circuit detects the fault, the fault information is stored in the EEPROM, which facilitates the maintenance of the controller.

Optionally, it also includes: a collection board assembly 6;

The collection board assembly 6 includes a supporting capacitor circuit and a busbar current sensor;

The supporting capacitor circuit is used for supplying power to the brushless motor driver 10 from one channel of DC28V output from the filter assembly 4;

The busbar current sensor converts the current generated on one line of DC28V output by the filter assembly 4 into a 0.5-4.5V voltage analog signal to complete the busbar current acquisition.

Optionally, the control board assembly 5 further includes: a position detection circuit and a busbar current detection circuit;

The position detection circuit is used to convert the hatch position signal output from the cockpit lid operating device into a 0-3.19V signal through an operational amplifier and act on the MCU control circuit to collect the hatch position in real time to achieve accurate position protection. ; The position signal of the hatch cover is 0～15V potentiometer signal;

The bus current detection circuit is used to convert the 0.5-4.5V voltage analog signal collected by the bus current sensor in the acquisition board component 6 into a 0.33-3V voltage through an operational amplifier and then send it to the MCU control circuit. The MCU control circuit collects the bus voltage in real time. Realize overcurrent protection of canopy operating device.

Optionally, the control board assembly 5 further includes: a secondary power supply processing circuit;

The secondary power supply processing circuit converts a DC15V voltage output from the filter assembly 4 into DC5V and DC3.3V, wherein DC5V is used for the power supply of the electromagnet control circuit, and DC3.3V is used for the fault storage circuit, RS422 The communication circuit, the input signal processing circuit and the MCU control circuit are powered.

Optionally, it further includes: a controller housing 3;

The controller housing 3 adopts a standard case design, and a weight-reducing groove is designed on the surface to perform effective weight-reduction and heat-dissipation treatment.

Optionally, the brushless motor driver 10 is used to receive the PWM wave and the F/R signal from the control board assembly 5 to control the motor in the canopy cover operating device to complete clockwise and counterclockwise rotation to drive the cabin. Opening and closing of the cover.

The invention provides a controller based on a cockpit cover manipulation device, comprising an MCU, a switch 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 control device is realized, and the safe, stable and reliable opening and closing of the aircraft canopy can be realized, and the pilots and ground staff can easily grasp the life, fault state and working state of the aircraft canopy control device.

Description of drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the accompanying drawings that need to be used in the description of the embodiments or the prior art. Obviously, the accompanying drawings in the following description These are some embodiments of the present invention, and for those of ordinary skill in the art, other drawings can also be obtained from these drawings without any creative effort.

Fig. 1 is the front view structure schematic diagram of the present invention;

Fig. 2 is the internal arrangement schematic diagram of the present invention;

Fig. 3 is the internal arrangement schematic diagram of the present invention;

Fig. 4 is the structural block diagram of the controller based on the canopy operating device of the present invention;

Description of reference numbers:

The first aviation socket 1 , the second aviation socket 2 , the controller housing 3 , the filter assembly 4 , the control board assembly 5 , the collection board assembly 6 , the wires 7 , the wires 8 , the binding wires 9 , and the brushless motor driver 10 .

Detailed ways

The controller based on the aircraft canopy operating device provided by the present invention will be explained below with reference to the accompanying drawings.

As shown in FIG. 1 , the present invention provides a controller based on an aircraft canopy control device, which has the characteristics of high reliability, small size, light weight (high power density), and high intelligence. It can not only meet the functions of unlocking and opening the canopy and locking and closing the canopy of the aircraft canopy control device, but also can quickly realize the fault detection and location of the canopy control device and itself, and can timely report the working current of the product in the form of RS422 bus, life, feedback relevant position signals, fault status, and at the same time can realize the online upgrade function of the software.

As shown in FIG. 2 and FIG. 3 , the present invention provides a controller based on an aircraft cockpit cover operating device, including: a first aviation socket 1 , a second aviation socket 2 , a controller housing 3 , a filter assembly 4 , a control The board assembly 5 , the collection board assembly 6 , the wire 7 , the wire 8 , the binding wire 9 and the brushless motor driver 10 .

Further, a first aviation socket 1 is installed on the front panel of the controller to be cross-linked with the aircraft, for the aircraft to supply power to the controller, and the pilot sends the controller to open and close the hatch cover by manipulating the switch. command, and communicate with the host computer via RS422 bus.

Further, a second aviation socket 2 is installed on the front panel of the controller to be cross-linked with the canopy operating device, and control the operation of the clutch and the motor in the canopy operating device by means of power supply.

Further, the controller casing 3 adopts a standard chassis design, and the controller casing 3 is designed with a weight reduction slot for effective weight reduction and heat dissipation.

Further, as shown in FIG. 4 , the filter assembly 4 enables the controller to meet the power supply characteristics and electromagnetic compatibility requirements of the whole machine. At the same time, the two input DC28V from the aircraft (the two are redundant power supply, the controller can work normally when either power supply is valid) is converted into two DC28V with different working currents (the maximum current of one DC28V is 50A, which is used in the cockpit Power supply for the motor driver in the cover control device; one DC28V with a maximum current of 3.5A, used to supply power to the electromagnet on the machine), and one DC15V (with a maximum current of 2A, used for the secondary power processing circuit of the control board and the position detection circuit and busbar current sense circuit power supply).

Further, as shown in FIG. 4 , the collection board assembly 6 includes a supporting capacitor circuit and a busbar current sensor. One channel of DC28V output from the filter assembly 4 supplies power to the brushless motor driver 10 after passing through the supporting capacitor circuit. The bus current sensor converts the current generated on one line of DC28V output by the filter assembly 4 into a 0.5-4.5V voltage analog signal (corresponding to -100A-100A of the bus current) and sends it to the control board assembly 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 busbar current detection circuit, an MCU control circuit, an RS422 communication circuit, a fault storage circuit, and a clutch control circuit. and electromagnet control circuit.

The secondary power supply processing circuit in the control board assembly 5 converts a DC15V voltage not output from the filter assembly 4 into DC5V (for the power supply of the electromagnet control circuit) and DC3.3V (for the fault storage circuit). , RS422 communication circuit, input signal processing circuit and MCU control circuit power supply).

The MCU in the control board assembly 5 completes the collection of the input signal, the position of the hatch cover, the bus current, etc., according to the corresponding logic PWM wave and F/R signal to the brushless motor driver 10, and outputs the clutch control signal to the clutch control circuit. Control the hatch cover to open or close the hatch cover; output the electromagnet control signal to the electromagnet control circuit to control the on-board electromagnet.

The input signal processing circuit in the control board assembly 5 uses an optocoupler to electrically isolate the command signal from the aircraft and the limit position signal in the canopy control device and process the redundancy, and then the MCU control circuit collects it.

The position detection circuit in the control board assembly 5 converts the hatch position signal (0~15V analog voltage) from the cockpit cover operating device into a 0~3.19V voltage through an operational amplifier and then enters the AD acquisition port that comes with the MCU. , MCU real-time acquisition of hatch cover position to achieve accurate position protection function.

The busbar current detection circuit in the control board assembly 5 converts the 0.5-4.5V voltage analog signal output from the busbar current sensor in the acquisition board assembly 6 into a 0.33-3V voltage through an operational amplifier and then enters the AD acquisition port that comes with the MCU. , the MCU collects the bus voltage in real time to realize the overcurrent protection of the canopy control device.

The RS422 communication circuit in the control board assembly 5 uses SM3490 as the interface circuit for RS422 communication with the host computer. The controller reports the working current, life, feedback related position signals and fault status of the product in the form of RS422 bus. The data of the online upgrade of the controller software is also sent to the MCU through the RS422 communication circuit. The fault storage circuit in the control board assembly 5 uses the EEPROM as the memory chip, and uses the IIC bus to communicate with the MCU. After the MCU detects the fault, the fault information is stored in the EEPROM, which is convenient for the maintenance of the controller.

The clutch control circuit in the control board assembly 5 controls the power supply of the clutch in the cockpit cover operating device on and off through a MOS tube.

The electromagnet control circuit in the control board assembly 5 controls the on-off of the power supply of the electromagnet on the machine through a relay with a wire package voltage of 5V. When the controller controls the hatch control device to open or close the hatch according to the pilot's instructions, the controller supplies power to the on-board electromagnet through the electromagnet control circuit, and the electromagnet automatically resets the on-board control switch and automatically cancels opening or closing the hatch. The cover command does not require the pilot 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 sent from the MCU control circuit in the control board assembly 5 to control the motor in the canopy control device to complete the clockwise rotation. And turn counterclockwise to drive the hatch cover to open and close.

Exemplarily, the wire 7 is used for signal cross-linking between the acquisition board assembly 6 and the control board assembly 5; the wire 8 is used for the signal cross-linking between the control board assembly 5 and the brushless motor driver 10 and the second aviation socket 2 ;

One embodiment of the present invention is an aircraft cockpit cover operating device controller, which basically includes MCU, switch signal acquisition circuit, clutch control circuit, motor drive circuit, clutch control circuit, and motor drive circuit. The driving control of the aircraft canopy control device is realized, and the safe, stable and reliable opening and closing of the aircraft canopy can be realized, and the pilots and ground staff can easily grasp the life, fault state and working state of the aircraft canopy control device.

Claims (9)

1. A controller based on an aircraft cockpit cover operating device, characterized in that it 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: MCU control circuit, clutch control circuit and electromagnet control circuit; wherein, A first aviation socket (1) is installed on the front panel of the controller to be cross-linked with the aircraft, for the aircraft to supply power to the controller, and the pilot sends commands to open and close the hatch cover to the controller by manipulating the switch , RS422 bus communication with the host computer; A second aviation socket (2) is installed on the front panel of the controller to be cross-linked with the cockpit cover operating device, and control the operation of the clutch and the motor in the cockpit cover operating device by means of power supply; The MCU control circuit is used to complete the collection of input signals, hatch cover positions, bus currents, etc., generate PWM waves and F/R signals according to corresponding logic to the brushless motor driver (10), and output clutch control signals to the The clutch control circuit controls the hatch cover operating device to open or close the hatch cover; output the electromagnet control signal to the electromagnet control circuit to control the on-board electromagnet; The clutch control circuit is used to control the power supply of the clutch in the cockpit cover operating device on and off through a MOS tube; The electromagnet control circuit is used to control the on-off of the power supply of the electromagnet on the aircraft through a relay whose wire package voltage is 5V. The control circuit supplies power to the on-board electromagnet, and the electromagnet automatically resets the on-board control switch and automatically cancels the command to open or close the hatch without the need for the pilot to manually reset the control switch. 2. The controller according to claim 1, characterized in that, further comprising: a filter assembly (4); The filter assembly (4) is used to convert the two input DC28V from the aircraft into two DC28V with different working currents and one DC15V; Among them, the maximum current of one DC28V is 50A, which is used to power the motor driver in the canopy control device; the maximum current of one DC28V is 3.5A, which is used to supply power to the electromagnet on the plane, and the maximum current of one DC15V is 2A, which is used for the secondary control of the control board. The power processing circuit supplies power. 3. The controller according to claim 2, wherein the control board assembly (5) further comprises: an input signal processing circuit; The input signal processing circuit uses the optocoupler to electrically isolate the command signal from the aircraft and the limit position signal in the canopy control device, and sends it to the MCU control circuit after performing the electrical isolation and redundancy processing. 4. The controller according to claim 3, wherein the control board assembly (5) further comprises: a fault storage circuit and an RS422 communication circuit; The RS422 communication circuit uses SM3490 as the interface circuit for RS422 communication with the host computer; reports the working current, life, feedback related position signals, and fault status in the form of RS422 bus; The fault storage circuit uses EEPROM as a storage chip, and uses an IIC bus to communicate with the MCU control circuit; After the MCU control circuit detects the fault, the fault information is stored in the EEPROM, which facilitates the maintenance of the controller. 5. The controller according to claim 4, characterized in that, further comprising: a collection board assembly (6); The collection board assembly (6) includes a support capacitor circuit and a busbar current sensor; The supporting capacitor circuit is used for supplying power to the brushless motor driver (10) from one channel of DC28V output from the filter assembly (4); The busbar current sensor converts the current generated on one line of DC28V output by the filter assembly 4 into a 0.5-4.5V voltage analog signal to complete the busbar current acquisition. 6. The controller according to claim 5, wherein the control board assembly (5) further comprises: a position detection circuit and a busbar current detection circuit; The position detection circuit is used to convert the hatch position signal output from the cockpit lid operating device into a 0-3.19V signal through an operational amplifier and act on the MCU control circuit to collect the hatch position in real time to achieve accurate position protection. ; The position signal of the hatch cover is 0～15V potentiometer signal; The busbar current detection circuit is used to convert the 0.5-4.5V voltage analog signal collected by the busbar current sensor in the acquisition board assembly (6) into a 0.33-3V voltage through an operational amplifier and then send it to the MCU control circuit, and the MCU control circuit collects in real time. The bus voltage realizes the overcurrent protection of the canopy operating device. 7. The controller according to claim 6, wherein the control board assembly (5) further comprises: a secondary power supply processing circuit; The secondary power processing circuit converts a DC15V voltage output from the filter assembly (4) into DC5V and DC3.3V, wherein DC5V is used for power supply of the electromagnet control circuit, and DC3.3V is used for the fault storage circuit , RS422 communication circuit, input signal processing circuit and MCU control circuit power supply. 8. The controller according to claim 1, characterized in that, further comprising: a controller housing (3); The controller housing (3) adopts a standard chassis design, and a weight-reducing groove is designed on the surface to perform effective weight-reducing and heat-dissipating treatment. 9 . The controller according to claim 2 , wherein the brushless motor driver ( 10 ) is used to control the cabin by receiving PWM waves and F/R signals from the control board assembly ( 5 ). 10 . The electric motor in the cover operating device completes clockwise and counterclockwise rotation to drive the opening and closing of the hatch.

Images