CN112407307A - Comprehensive display method for helicopter flight control system - Google Patents
Comprehensive display method for helicopter flight control system Download PDFInfo
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- CN112407307A CN112407307A CN202011316742.7A CN202011316742A CN112407307A CN 112407307 A CN112407307 A CN 112407307A CN 202011316742 A CN202011316742 A CN 202011316742A CN 112407307 A CN112407307 A CN 112407307A
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- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 title claims abstract description 90
- 238000000034 method Methods 0.000 title claims abstract description 33
- 238000012545 processing Methods 0.000 claims description 19
- 238000001514 detection method Methods 0.000 claims description 13
- 230000003416 augmentation Effects 0.000 claims description 6
- 238000005096 rolling process Methods 0.000 claims description 5
- 230000002159 abnormal effect Effects 0.000 claims description 3
- 230000026676 system process Effects 0.000 claims description 2
- 238000013461 design Methods 0.000 abstract description 6
- 238000005034 decoration Methods 0.000 description 2
- 230000008030 elimination Effects 0.000 description 2
- 238000003379 elimination reaction Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 230000010354 integration Effects 0.000 description 2
- 239000004973 liquid crystal related substance Substances 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012544 monitoring process Methods 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 1
- 238000012937 correction Methods 0.000 description 1
- 238000004132 cross linking Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000002452 interceptive effect Effects 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 238000013024 troubleshooting Methods 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D43/00—Arrangements or adaptations of instruments
Abstract
The invention belongs to the technical field of helicopter flight control systems, and discloses a comprehensive display method for a helicopter flight control system. The helicopter flight control system is improved on the basis of the original flight control system, the display mode of the working state of the flight control system is comprehensively changed, a control surface position indicator device is omitted, information such as control surface position indication, mode input, prompt and the like is comprehensively displayed on a multifunctional display, through the comprehensive display design method of the flight control system, display information related to the flight control system is realized on the multifunctional display, a driver can check the state of the flight control system more loosely, and the driver can pay attention to the whole flight.
Description
Technical Field
The invention belongs to the technical field of helicopter flight control systems, and particularly relates to a comprehensive display method for a helicopter flight control system.
Background
The interactive interface between the working of the helicopter flight control system and a driver is mainly a flight control console, the flight control console without a liquid crystal screen can only be connected in a mode and displayed by a code tube in a digital mode, the flight control console with the liquid crystal screen is represented by a certain type of the helicopter flight control console, and can display information such as the working state, fault declaration and the like of the flight control system, but the installation position of the flight control console has a common problem that the flight control console is not directly in front of the driver, and the driver needs to lower the head when looking up the state of the flight control system, so that the flight safety is influenced to a certain extent.
Disclosure of Invention
In order to solve the problems, the invention comprehensively changes the display mode of the working state of the flight control system on the basis of the design of the flight control system of a certain helicopter, cancels a control surface position indicator device, and comprehensively displays information such as control surface position indication, system working state, autopilot modal input, system prompt and the like on a multifunctional display.
The technical scheme of the invention is as follows:
a comprehensive display method for a helicopter flight control system comprises the following steps: the output data of the pitching steering engine, the rolling steering engine and the course steering engine in series are transmitted to a comprehensive task processing system through a bus, and the comprehensive task processing system processes the output data of the three steering engines in series and displays the data on a multifunctional display in a pointer deflection mode.
Further, the method further comprises: and outputting the working state of the flight control system and the function mode of the autopilot to the comprehensive task processing system in a bus form, and displaying the working state and the function mode of the autopilot on the multifunctional display after the working state and the function mode of the autopilot are processed by the comprehensive task processing system.
Furthermore, the comprehensive task processing system also displays the function mode of the autopilot according to the longitudinal axis, the heading and the total distance.
Further, the method further comprises: if the flight control system does not meet the self-detection or function mode connection condition when the flight control system performs self-detection or connects the function mode of the automatic pilot, the reason why the condition is not met is sent to the comprehensive task processing system, and the reason is displayed on the multifunctional display after being processed by the comprehensive task processing system.
Further, the method further comprises: the comprehensive task processing system also displays the control surface position indication information, the working state of the flight control system, the function mode of the automatic pilot and the prompt information of the flight control system in the same area on the multifunctional display in a centralized way.
Further, the control surface position indication information includes: pitch, roll, and heading information.
Further, the operating state information of the flight control system includes: no power-on, power-on waiting, stability augmentation and stability augmentation control.
Further, flight control system prompt information includes: self-detection steps and results of the flight control system, reasons why the autopilot functional mode cannot be connected, abnormal exit of the autopilot functional mode and prompt information for turning off the flight control system.
Further, the system further comprises: and displaying the fault information of the flight control system on the multifunctional display system in Chinese within the cross.
The invention relates to a design method for comprehensive display of a helicopter flight control system, which is used for monitoring the working state of the flight control system by a driver in the flight process and also can be used for providing state display for ground self-detection and fault elimination.
During final assembly and test flight of the helicopter, various faults caused by ground self-detection are solved by using the method, the ground service maintenance time is shortened, and the 'fool' operation prompt can enable a driver to quickly know the use of the flight control system.
Drawings
Fig. 1 is a schematic view of a comprehensive display window of a flight control system.
Detailed Description
The design method according to the present invention will be described in further detail with reference to the accompanying drawings.
A design method for the comprehensive display of a helicopter flight control system is mainly used for monitoring the working state of the flight control system by a driver in the flight process, can also be used for ground self-detection and fault elimination to provide state display, and can quickly locate the fault reason, and referring to figure 1, the comprehensive display of the helicopter flight control system is realized by the following modes and steps:
1) the function of indicating the position of the control surface is realized in a multifunctional device
The helicopter flight control system is characterized in that the prototype flight control system is provided with a pitching, rolling and course control surface position indicator, the control surface position indicator is arranged on an instrument and used for displaying the output quantity of a series-connection steering engine of the flight control system, signals are transmitted through a simulation cable, the system architecture is optimized, the helicopter flight control system is provided with three control surface position indicators, the output quantities of the pitching, rolling and course series-connection steering engine are transmitted to a comprehensive task processing system in a GJB289A bus form, and the output quantities are displayed on a multifunctional display according to a prototype physical model of the control surface position indicator.
2) Digital tube for canceling flight control console panel
The helicopter flight control system cancels the display of the nixie tube, and displays the fault information of the flight control system on a multifunctional display through Chinese within a cross.
3) Increasing flight control modal investment information display
After the relevant modes of the flight control system are input, the relevant mode buttons and the like on the flight control console can be lighted, but due to the fact that the view of the installation position of the flight control console is poor, the button switches of the flight control console panel are distributed, and the current working state of the flight control system is difficult to directly read, the helicopter flight control system transmits the information to the comprehensive task processing system through a GJB289A bus form to be comprehensively displayed on the multifunctional display, and the modes are classified according to the longitudinal axis, the heading and the total distance.
4) Increasing flight control system prompt information display
The flight control system carries out self-detection or puts in a functional mode in the air, certain conditions are required to be met, the flight control system has complex structure and cross-linking, and the reasons which do not meet the conditions are multiple, so great difficulty is brought to ground troubleshooting and air adjustment, the helicopter flight control system integrates various reasons which do not meet the conditions, the various reasons are transmitted to the integrated task processing system through a G289 JB289A bus form to be comprehensively displayed on the multifunctional display, and in the process of self-detection or putting in the mode, prompt information can be popped up as long as obstacles appear, and ground service or air service correction and adjustment are guided.
5) Flight control system integrated display area is concentrated
The position indication (pitching, rolling and course) of a control surface, flight control mode input information (control stability augmentation/stability augmentation and the like, airspeed maintenance/automatic hovering and the like), and prompt information display (flight control system self-detection steps and results, information such as reasons for mode input failure, abnormal mode exit, flight control disconnection prompt and the like) of the flight control system are all information needing attention at any moment in the normal flight process, and the multifunctional display is provided with a special display area for the flight control system to carry out comprehensive display, so that the load of a driver is reduced.
The technology has the advantages that:
1) direct view and clarity
The failure information declaration designed by the method does not need the driver to memorize hard backs, carries out guidance prompt information given by self-detection before flight and modal investment, can quickly position the reason that the flight control system does not meet the conditions, realizes 'fool' use of the flight control system, and reduces the workload of air ground personnel.
2) Display integration
The method displays the position indication, the mode input and the prompt information of the control surface on the multifunctional display, optimizes the system architecture, has high integration level with an avionic system, and is greatly convenient for the operation and the use of crew members in a comprehensive display mode.
3) Wide application range
The comprehensive display design method of the flight control system is suitable for all digital configuration flight control systems, electric flight control systems and future light transmission flight control systems.
The foregoing is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, several modifications and decorations can be made without departing from the original scope of the invention, and these modifications and decorations should also be regarded as the protection scope of the present invention.
Claims (9)
1. A helicopter flight control system comprehensive display method is characterized by comprising the following steps: the method comprises the following steps: the output data of the pitching steering engine, the rolling steering engine and the course steering engine in series are transmitted to a comprehensive task processing system through a bus, and the comprehensive task processing system processes the output data of the three steering engines in series and displays the data on a multifunctional display in a pointer deflection mode.
2. The comprehensive display method of the helicopter flight control system according to claim 1, characterized in that: the method further comprises the following steps: and outputting the working state of the flight control system and the function mode of the autopilot to the comprehensive task processing system in a bus form, and displaying the working state and the function mode of the autopilot on the multifunctional display after the working state and the function mode of the autopilot are processed by the comprehensive task processing system.
3. The comprehensive display method of the helicopter flight control system according to claim 2, characterized in that: and the comprehensive task processing system also displays the functional modes of the autopilot according to the longitudinal axis, the course and the total distance.
4. The comprehensive display method of the helicopter flight control system according to claim 3, characterized in that: the method further comprises the following steps: if the flight control system does not meet the self-detection or function mode connection condition when the flight control system performs self-detection or connects the function mode of the automatic pilot, the reason why the condition is not met is sent to the comprehensive task processing system, and the reason is displayed on the multifunctional display after being processed by the comprehensive task processing system.
5. The comprehensive display method of the helicopter flight control system according to claim 4, characterized in that: the method further comprises the following steps: the comprehensive task processing system also displays the control surface position indication information, the working state of the flight control system, the function mode of the automatic pilot and the prompt information of the flight control system in the same area on the multifunctional display in a centralized way.
6. The comprehensive display method of the helicopter flight control system according to claim 5, characterized in that: the control surface position indication information includes: pitch, roll, and heading information.
7. The comprehensive display method of the helicopter flight control system according to claim 5, characterized in that: the working state information of the flight control system comprises: no power-on, power-on waiting, stability augmentation and stability augmentation control.
8. The comprehensive display method of the helicopter flight control system according to claim 5, characterized in that: flight control system prompt message includes: self-detection steps and results of the flight control system, reasons why the autopilot functional mode cannot be connected, abnormal exit of the autopilot functional mode and prompt information for turning off the flight control system.
9. The comprehensive display method of the helicopter flight control system according to claim 1, characterized in that: the system further comprises: and displaying the fault information of the flight control system on the multifunctional display system in Chinese within the cross.
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| CN202011316742.7A CN112407307A (en) | 2020-11-20 | 2020-11-20 | Comprehensive display method for helicopter flight control system |
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| CN202011316742.7A CN112407307A (en) | 2020-11-20 | 2020-11-20 | Comprehensive display method for helicopter flight control system |
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Application publication date: 20210226 |