CN220164162U - Electric vertical take-off and landing aircraft flap control system based on DSP control - Google Patents
Electric vertical take-off and landing aircraft flap control system based on DSP control Download PDFInfo
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- CN220164162U CN220164162U CN202223595866.0U CN202223595866U CN220164162U CN 220164162 U CN220164162 U CN 220164162U CN 202223595866 U CN202223595866 U CN 202223595866U CN 220164162 U CN220164162 U CN 220164162U
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Abstract
The utility model provides an electric vertical take-off and landing aircraft flap control system based on DSP control, which comprises: a flight control computer; a steering engine controller; a DC brushless motor; a transmission device; pushing the bar; a flap; linear displacement sensor and normally closed brake. The electric vertical take-off and landing aircraft flap control system based on the DSP control solves the problems of instability, inaccuracy, insufficient response and the like of the aircraft flap control in the field of electric vertical take-off and landing aircraft flap control systems, is used on electric vertical take-off and landing aircraft equipment, is efficient and low in cost, has high reliability, and can ensure effective and rapid retraction and landing of the electric vertical take-off and landing aircraft flaps.
Description
Technical Field
The utility model belongs to the technical field of airplane flaps, and particularly relates to an electric vertical take-off and landing airplane flap control system based on DSP control.
Background
The flap control system of the airplane is used as important onboard equipment, and whether the flap control system can work normally or not seriously affects the safety of the airplane. Aircraft flap control systems of the prior art suffer from instability, inaccuracy, and not rapid response.
Accordingly, there is a need to provide a control system that ensures efficient and rapid retraction and lowering of the flaps of an electric vertical takeoff and landing aircraft.
Disclosure of Invention
In order to solve the problems, the utility model provides an electric vertical take-off and landing aircraft flap control system based on DSP control, which is used in the fields of high control precision, control of electric vertical take-off and landing aircraft flaps and the like.
The utility model aims to provide an electric vertical take-off and landing aircraft flap control system based on DSP control, which comprises:
the flight control computer is used for issuing a flap action instruction and processing and responding a signal and a fault mode of the flap action fed back by the flap controller through the CAN bus;
the steering engine controller is communicated with the flight control computer through a CAN bus, receives CAN bus control signals of the upper computer, calculates a control law, controls the driving module to drive the direct current brushless motor to work, realizes driving amplification and braking functions through the driving control module, and feeds back working information and self-checking information of the working state of the flight control computer;
the direct-current brushless motor is responsible for realizing power output after receiving PWM control signals, F/R signals and HALL signals of the motor of the control module;
the transmission device is used for transmitting power;
the pushing bar is used for acting the driving force generated by the driving device on the wing surface of the flap so as to retract or put down the flap;
the flap receives a driving force from the pushing bar and changes the change of the current airfoil angle, so that the changed state of the airfoil of the electric vertical take-off and landing aircraft;
the linear displacement sensor is driven by the push rod and feeds back the real-time position of the push rod to the steering engine controller;
the normally closed brake is arranged at the rear end of the motor, and is used for locking a motor shaft to keep the steering engine at the current position when the steering engine does not output.
The electric vertical take-off and landing aircraft flap control system based on DSP control provided by the utility model also has the characteristics that the flight control computer receives and sends the position instruction of the flap, and displays the state information of the fault and monitoring quantity of the flap.
The DSP control-based electric vertical take-off and landing aircraft flap control system provided by the utility model also has the characteristics that the working information comprises the current position, current information and voltage information on a steering engine controller.
The flap control system of the electric vertical take-off and landing aircraft based on DSP control provided by the utility model has the characteristics that the transmission device adopts a transmission mode of matching a two-stage involute spur gear with a ball screw.
The DSP control-based electric vertical take-off and landing aircraft flap control system provided by the utility model also has the characteristics that the spur gear is made of stainless steel materials, and the ball screw is preloaded to eliminate axial gaps.
The electric vertical take-off and landing aircraft flap control system based on DSP control also has the characteristic that the push rod converts the force transmitted by the transmission device into position variation to push the change of the flap position.
The electric vertical take-off and landing aircraft flap control system based on DSP control provided by the utility model has the characteristics that the linear displacement sensor feeds back the real-time position of the push rod to the steering engine controller in an analog form through the real-time change value of the potentiometer.
The electric vertical take-off and landing aircraft flap control system based on DSP control provided by the utility model also has the characteristics that the linear displacement sensor adopts a high-precision linear potentiometer, and the nonlinearity degree of the linear displacement sensor is as follows: less than or equal to +/-0.3 percent, and the output smoothness is as follows: less than or equal to 0.1 percent, effective electric stroke: 80mm.
The electric vertical take-off and landing aircraft flap control system based on DSP control provided by the utility model also has the characteristics that the normally closed brake is a normally closed power-off brake, and the steering engine controller controls the DSP to control the on-off of a normally closed brake power supply through discrete quantity output signals after the power-off brake reaches a designated position according to an action instruction sent by the flight control computer.
The DSP control-based electric vertical take-off and landing aircraft flap control system provided by the utility model also has the characteristics that the normally closed power-off brake allows the maximum rotation speed to be: 14000rmp, brake torque 0.15Nm.
The beneficial effects are that:
the DSP control-based electric vertical take-off and landing aircraft flap control system solves the problems of instability, inaccuracy, inaccurate response and the like of the aircraft flap control in the field of electric vertical take-off and landing aircraft flap control systems, is used on electric vertical take-off and landing aircraft equipment, is efficient and low in cost, has high reliability, and can ensure that the electric vertical take-off and landing aircraft flaps are effectively and quickly retracted and put down.
Drawings
In order to more clearly illustrate the technical solutions of the present utility model, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present utility model, and that other drawings can be obtained according to these drawings without inventive effort for a person skilled in the art.
Fig. 1 is a schematic block diagram of an electric vertical take-off and landing aircraft flap control system based on DSP control according to an embodiment of the present utility model.
Detailed Description
In order to make the technical means, creation characteristics, achievement purposes and effects achieved by the utility model easy to understand, the following embodiments specifically describe the electric vertical take-off and landing aircraft flap control system based on DSP control provided by the utility model with reference to the accompanying drawings.
In the description of the embodiments of the present utility model, it should be understood that the terms "center", "longitudinal", "lateral", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on the drawings, are merely for convenience in describing the present utility model and simplify the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the utility model.
Furthermore, the terms "first," "second," "third," and the like are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first", "a second", etc. may explicitly or implicitly include one or more such feature. In the description of the utility model, unless otherwise indicated, the meaning of "a plurality" is two or more.
The terms "mounted," "connected," "coupled," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the creation of the present utility model can be understood by those of ordinary skill in the art in a specific case.
As shown in fig. 1, there is provided an electric vertical take-off and landing aircraft flap control system based on DSP control, the control system comprising:
the flight control computer is used for issuing a flap action instruction and processing and responding a signal and a fault mode of the flap action fed back by the flap controller through the CAN bus;
the steering engine controller is communicated with the flight control computer through a CAN bus, receives CAN bus control signals of the upper computer, calculates a control law, controls the driving module to drive the direct current brushless motor to work, realizes driving amplification and braking functions through the driving control module, and feeds back working information and self-checking information of the working state of the flight control computer;
the direct-current brushless motor is responsible for realizing power output after receiving PWM control signals, F/R signals and HALL signals of the motor of the control module;
the transmission device is used for transmitting power;
the pushing bar is used for acting the driving force generated by the driving device on the wing surface of the flap so as to retract or put down the flap;
the flap receives a driving force from the pushing bar and changes the change of the current airfoil angle, so that the changed state of the airfoil of the electric vertical take-off and landing aircraft;
the linear displacement sensor is driven by the push rod and feeds back the real-time position of the push rod to the steering engine controller;
the normally closed brake is arranged at the rear end of the motor, and is used for locking a motor shaft to keep the steering engine at the current position when the steering engine does not output.
In some embodiments, the flight control computer receives and transmits position instructions for the flap, displaying status information for the failure and the monitored amount of the flap.
In some embodiments, the operating information includes a current position, current information, and voltage information on the steering engine controller.
In some embodiments, the transmission device adopts a transmission mode of matching a two-stage involute spur gear with a ball screw. The transmission device adopts a transmission mode with higher efficiency, the transmission ratio is larger, and finally, a transmission mode of two-stage involute straight teeth and a ball screw is adopted, so that the straight teeth gear transmission efficiency is high, and the movement is stable and flexible.
In some embodiments, the spur gear is made of stainless steel material, and the ball screw is preloaded to eliminate axial play. The axial clearance of the ball screw can be basically eliminated after the ball screw is pre-tensioned, the rolling friction efficiency is high, and the maximum output force is 2000N according to the rated output force of 1000N.
In some embodiments, the push rod converts the force transmitted by the transmission device into a position change amount to push the flap to change.
In some embodiments, the linear displacement sensor feeds back the real-time position of the push rod to the steering engine controller in the form of analog quantity through the real-time change value of the potentiometer. The steering engine controller is subjected to DSP operation processing, so that closed-loop control of the position of the electric steering engine can be formed.
In some embodiments, the linear displacement sensor is a high-precision linear potentiometer, and the nonlinearity degree of the linear potentiometer is: less than or equal to +/-0.3 percent, and the output smoothness is as follows: less than or equal to 0.1 percent, effective electric stroke: 80mm.
In some embodiments, the normally closed brake is a normally closed power-off brake, and the steering engine controller controls the DSP to control the on-off of the normally closed brake power supply through a discrete output signal after the normally closed brake reaches a designated position according to an action instruction sent by the flight control computer. 2500N static braking can be achieved.
In some embodiments, the normally closed power-off brake allows a maximum rotational speed of: 14000rmp, brake torque 0.15Nm.
The foregoing description of the preferred embodiments of the utility model is not intended to be limiting, but rather is intended to cover all modifications, equivalents, and alternatives falling within the spirit and principles of the utility model. The foregoing is merely a preferred embodiment of the present utility model, and it should be noted that it will be apparent to those skilled in the art that modifications and variations can be made without departing from the technical principles of the present utility model, and these modifications and variations should also be regarded as the scope of the utility model.
Claims (10)
1. An electric vertical take-off and landing aircraft flap control system based on DSP control, the control system comprising:
the flight control computer is used for issuing a flap action instruction and processing and responding a signal and a fault mode of the flap action fed back by the flap controller through the CAN bus;
the steering engine controller is communicated with the flight control computer through a CAN bus, receives CAN bus control signals of the upper computer, calculates a control law, controls the driving module to drive the direct current brushless motor to work, realizes driving amplification and braking functions through the driving control module, and feeds back working information and self-checking information of the working state of the flight control computer;
the direct-current brushless motor is responsible for realizing power output after receiving PWM control signals, F/R signals and HALL signals of the motor of the control module;
the transmission device is used for transmitting power;
the pushing bar is used for acting the driving force generated by the driving device on the wing surface of the flap so as to retract or put down the flap;
the flap receives a driving force from the pushing bar and changes the change of the current airfoil angle, so that the changed state of the airfoil of the electric vertical take-off and landing aircraft;
the linear displacement sensor is driven by the push rod and feeds back the real-time position of the push rod to the steering engine controller;
the normally closed brake is arranged at the rear end of the motor, and is used for locking a motor shaft to keep the steering engine at the current position when the steering engine does not output.
2. The DSP-control-based electric vertical take-off and landing aircraft flap control system according to claim 1, wherein the flight control computer receives and transmits a flap position command and displays status information of a flap fault and a monitoring amount.
3. The DSP-control-based electric vertical take-off and landing aircraft flap control system of claim 1 wherein said operational information includes current position, current information, and voltage information on a steering engine controller.
4. The electric vertical take-off and landing aircraft flap control system based on DSP control as claimed in claim 1, wherein the transmission device adopts a transmission mode of two-stage involute spur gear and ball screw in a matching way.
5. The DSP-control-based electric vertical take-off and landing aircraft flap control system of claim 4 wherein said spur gear is made of stainless steel material and said ball screw is preloaded to eliminate axial play.
6. The DSP-control-based electric vertical take-off and landing aircraft flap control system according to claim 1, wherein the push rod converts the force transmitted by the transmission device into a position change amount to push the change of the flap position.
7. The DSP-control-based electric vertical take-off and landing aircraft flap control system according to claim 1, wherein the linear displacement sensor feeds back the real-time position of the push rod to the steering engine controller in the form of analog quantity through the real-time change value of the potentiometer.
8. The DSP-control-based electric vertical take-off and landing aircraft flap control system of claim 7, wherein the linear displacement sensor is a high-precision linear potentiometer, and the nonlinearity is as follows: less than or equal to +/-0.3 percent, and the output smoothness is as follows: less than or equal to 0.1 percent, effective electric stroke: 80mm.
9. The electric vertical take-off and landing aircraft flap control system based on DSP control of claim 1, wherein the normally closed brake is a normally closed power-off brake, and the steering engine controller controls the DSP to control the on-off of a normally closed brake power supply through discrete output signals after the power-off brake reaches a designated position according to an action instruction sent by the flight control computer.
10. The DSP-control-based electric vertical take-off and landing aircraft flap control system of claim 9 wherein said normally closed power-off brake allows a maximum rotational speed of: 14000rmp, brake torque 0.15Nm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202223595866.0U CN220164162U (en) | 2022-12-29 | 2022-12-29 | Electric vertical take-off and landing aircraft flap control system based on DSP control |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202223595866.0U CN220164162U (en) | 2022-12-29 | 2022-12-29 | Electric vertical take-off and landing aircraft flap control system based on DSP control |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220164162U true CN220164162U (en) | 2023-12-12 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202223595866.0U Active CN220164162U (en) | 2022-12-29 | 2022-12-29 | Electric vertical take-off and landing aircraft flap control system based on DSP control |
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| Country | Link |
|---|---|
| CN (1) | CN220164162U (en) |
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- 2022-12-29 CN CN202223595866.0U patent/CN220164162U/en active Active
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