CN110949659A - Trailing edge flap control method - Google Patents
Trailing edge flap control method Download PDFInfo
- Publication number
- CN110949659A CN110949659A CN201911240126.5A CN201911240126A CN110949659A CN 110949659 A CN110949659 A CN 110949659A CN 201911240126 A CN201911240126 A CN 201911240126A CN 110949659 A CN110949659 A CN 110949659A
- Authority
- CN
- China
- Prior art keywords
- trailing edge
- edge flap
- control
- landing
- flap
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims abstract description 33
- 230000007547 defect Effects 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/02—Initiating means
- B64C13/16—Initiating means actuated automatically, e.g. responsive to gust detectors
- B64C13/22—Initiating means actuated automatically, e.g. responsive to gust detectors readily revertible to personal control
Landscapes
- Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Aviation & Aerospace Engineering (AREA)
- Traffic Control Systems (AREA)
Abstract
The invention provides a trailing edge flap control method, a trailing edge flap control switch is provided with three gears of 'retraction', 'landing' and 'automatic', when the trailing edge flap control switch is in the 'retraction' and 'landing' positions, the trailing edge flap responds to manual control, and when the trailing edge flap control switch is in the 'automatic' position, a flight control computer judges a flight stage according to an indication airspeed of an airplane, an airplane wheel bearing signal and an undercarriage retraction in-place signal, so as to control the deflection of the flap; when the flight control computer sends out a deflection instruction of the trailing edge flap, the flight control computer does not receive a signal of the trailing edge flap in place when the deflection instruction of the trailing edge flap is overtime, and the flight control computer prompts to manually control the trailing edge flap. The designed control method of the trailing edge flap can automatically control the trailing edge flap to deflect to a preset position according to the flight stage of the airplane in an automatic control mode, reduces the operation load of a pilot in the takeoff/landing stage, can realize the switching between automatic control and manual control, and ensures the safe retraction of the trailing edge flap.
Description
Technical Field
The invention belongs to the technical field of automatic control, and particularly relates to a trailing edge flap control method of an airplane.
Background
Currently, aircraft flaps are generally controlled manually. The pilot manually manipulates knobs/switches to generate flap takeoff, air or landing commands as required by the flight phase. When the use range of the flap is exceeded, the flap is not retracted, and the flap and the wing structure are damaged. Therefore, the pilot needs to pay attention to the speed of the flight meter and the flight phase at any time when performing flap control, the use limit is kept in mind, the operating load of the pilot is increased, and potential safety hazards exist.
Disclosure of Invention
In order to solve the defects of the prior art, the invention provides a trailing edge flap control method which is used for realizing automatic and manual control of the trailing edge flap meeting the requirements of different flight stages.
In order to solve the technical problem, the technical scheme adopted by the trailing edge flap control method provided by the invention is as follows: the trailing edge flap control switch is provided with three gears of retraction, landing and automatic; when the trailing edge flap control switch is in a 'retracting' position and a 'landing' position, the trailing edge flap responds to manual control; when the trailing edge flap control switch is in an 'automatic' position, the flight control computer judges a flight stage according to the relevant signals of the airplane so as to control the flap to deflect.
Further, the flight control computer carries out control logic judgment on selected aircraft related signals, specifically, an indication airspeed of the aircraft, an aircraft wheel bearing signal and an undercarriage retraction in-place signal.
Further, the control logic of the flight control computer for sending out the 'take-off' instruction is as follows: the indicated airspeed of the airplane is less than the ground medium-speed taxiing speed, the airplane wheel is in a bearing state, and the undercarriage is in a down state, namely the airplane is judged to be in a take-off stage, and the flight control computer sends a take-off command to control the trailing edge flap to deviate downwards to a take-off position.
The control logic of the flight control computer for sending out the 'air' instruction is as follows: when the undercarriage is in a retraction state, indicating that the airspeed is greater than the undercarriage extension limiting speed, judging the undercarriage is in an air stage, and sending an air command by the flight control computer to control the trailing edge flap to return to a retraction position.
The control logic of the flight control computer for sending the landing command is as follows: and (4) judging the landing stage that the undercarriage is converted from the retraction state to the extension state and the indicated airspeed is less than the landing limiting speed of the undercarriage, and sending a landing command to control the trailing edge flap to return to the landing position by the flight control computer.
Further, in the landing stage of the airplane, when the airplane wheel is changed from a non-bearing state to a bearing state, a takeoff command is sent out to control the trailing edge flap to be retracted to a takeoff position.
Similarly, in the landing phase of the aircraft, when the aircraft incidence angle is smaller than α (the stop angle is multiplied by 1.2), a 'stow' command is sent to control the flap to be stowed to the 'stow' position.
Further, the logic for handling a trailing edge flap control anomaly is: when the flight control computer sends out a deflection instruction t (the time from the 'retraction' position to the 'landing' position is multiplied by 1.2) of the trailing edge flap for a second, the flight control computer does not receive a signal of the trailing edge flap in place, declares an 'automatic flap fault' and sends out a voice alarm to prompt the manual control of the trailing edge flap.
In the technical scheme, the designed automatic and manual control modes of the trailing edge flap can automatically control the trailing edge flap to deflect to a preset position according to the flight phase of the airplane, so that the control load of a pilot in the takeoff/landing phase is reduced, the automatic and manual control switching can be realized, and the safe retraction and release of the trailing edge flap are ensured.
Drawings
FIG. 1 is a flow chart of the logic for automatic control of a trailing edge flap according to the invention.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to fig. 1, and it is obvious that the described embodiments are only a specific embodiment of the present invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
A trailing edge flap control method is used for realizing automatic and manual control of trailing edge flaps meeting requirements of different flight phases.
The control switch of the trailing edge flap (flap) is provided with three gears of 'retraction', 'landing' and 'automatic'.
When the flap control switch is in the 'retraction' position and the 'landing' position, the trailing edge flap responds to manual control.
When the flap control switch is in an 'automatic' gear, the flight control computer judges the automatic deflection of the flap in the flight stage according to the indicated airspeed of the airplane, the airplane wheel bearing signal and the undercarriage signal, and the specific control logic is as follows, as shown in the attached figure 1:
the automatic control needs to meet the following conditions:
□ flap control switch signal is normal;
□ flap is not faulty;
□ the signal of the load switch of the main wheel is normal;
□ the signal of the switch for the main landing gear retracting to the right position is normal;
□ the communication between the flight control computer and the flap drive system is normal;
□ the flight control system is in the digital master mode.
After the airplane is powered on, when the flight control computer detects that the indicated airspeed is less than or equal to the ground medium-speed sliding speed, the main wheel bearing switch is in a bearing state and the main undercarriage retraction in-place switch is in an uncollapsed state, the airplane is judged to be in a take-off stage, and a take-off command is sent to control the flap to deflect downwards to a take-off position;
when the flight control computer detects that the retraction in-place switch of the main landing gear is in a retraction state or indicates that the airspeed is greater than the landing gear extension limiting speed, the flight control computer judges that the flight control computer is in an air stage and sends an 'air' instruction to control the flap to return to the retraction position;
when the flight control computer detects that the retraction in-place switch of the main landing gear is converted from retraction to non-retraction and the indicated airspeed is less than or equal to the landing gear extension limiting speed, the landing stage is judged, and a landing command is sent to control the flap to return to the landing position;
in the landing stage, when the main wheel bearing switch is changed from a non-bearing state to a bearing state, a take-off command is sent to control the flap to be retracted to a take-off position;
in the landing stage, when the aircraft incidence angle is smaller than α, a 'retracting' command is sent out to control the flap to retract to a 'retracting' position.
When the flight control computer sends out a flap deflection instruction for t seconds, the flap deflection in-place signal is not received, an automatic flap fault is declared, and a voice alarm prompt is sent out to manually control the flap.
When the flap is under automatic control, the flap is retracted to a 'stowed' position, requiring manual control of the flap.
Claims (8)
1. A trailing edge flap control method is characterized in that: the trailing edge flap control switch is provided with three gears of retraction, landing and automatic; when the trailing edge flap control switch is in a 'retracting' position and a 'landing' position, the trailing edge flap responds to manual control; when the trailing edge flap control switch is in an 'automatic' position, the flight control computer judges a flight stage according to the relevant signals of the airplane so as to control the flap to deflect.
2. The trailing edge flap control method according to claim 1, characterized in that: the flight control computer carries out control logic judgment on selected aircraft related signals, specifically, the selected aircraft related signals are an indication airspeed of the aircraft, an aircraft wheel bearing signal and an undercarriage retraction in-place signal.
3. The trailing edge flap control method according to claim 2, characterized in that: the control logic of the flight control computer for sending the 'take-off' instruction is as follows:
the indicated airspeed of the airplane is less than the ground medium-speed taxiing speed, the airplane wheel is in a bearing state, the undercarriage is in a down state, and the judgment is in a take-off stage, and the flight control computer sends a take-off command to control the trailing edge flap to deviate downwards to a take-off position.
4. The trailing edge flap control method according to claim 2, characterized in that: the control logic of the flight control computer for sending out the 'air' instruction is as follows:
when the undercarriage is in a retraction state, | | indicates that the airspeed is greater than the undercarriage down limiting speed = and is judged to be in an air stage, the flight control computer sends an "air" command to control the trailing edge flap to return to the retraction position.
5. The trailing edge flap control method according to claim 2, characterized in that: the control logic of the flight control computer for sending the landing command is as follows:
and (4) judging that the landing gear is in a landing stage when the retraction of the landing gear is changed into a down state and the indication airspeed is less than the down limiting speed of the landing gear = and sending a landing command to control the trailing edge flap to return to the landing position by the flight control computer.
6. The trailing edge flap control method according to claim 5, characterized in that: in the landing stage of the airplane, when the airplane wheel is changed from a non-bearing state to a bearing state, a takeoff command is sent out to control the trailing edge flap to be retracted to a takeoff position.
7. The trailing edge flap control method of claim 5, wherein during a landing phase of the aircraft, when the aircraft angle of attack is less than α (stop angle x 1.2), a "stow" command is issued to control the flap to stow to a "stow" position.
8. The trailing edge flap control method according to any one of claims 1 to 7, characterized in that: the logic for handling the trailing edge flap control anomaly is:
when the flight control computer sends out a deflection instruction t (the time from the 'retraction' position to the 'landing' position is multiplied by 1.2) of the trailing edge flap for a second, the flight control computer does not receive a signal of the trailing edge flap in place, declares an 'automatic flap fault' and sends out a voice alarm to prompt the manual control of the trailing edge flap.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911240126.5A CN110949659A (en) | 2019-12-06 | 2019-12-06 | Trailing edge flap control method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911240126.5A CN110949659A (en) | 2019-12-06 | 2019-12-06 | Trailing edge flap control method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110949659A true CN110949659A (en) | 2020-04-03 |
Family
ID=69979981
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911240126.5A Pending CN110949659A (en) | 2019-12-06 | 2019-12-06 | Trailing edge flap control method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110949659A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113998095A (en) * | 2021-11-08 | 2022-02-01 | 陕西千山航空电子有限责任公司 | Control method of trainer trailing edge flap control system |
| CN114013628A (en) * | 2021-09-27 | 2022-02-08 | 广东空天科技研究院 | Wing folding control method and device |
| CN114180092A (en) * | 2021-10-18 | 2022-03-15 | 中国航空工业集团公司沈阳飞机设计研究所 | Launching control system of catapult plane |
| CN113998095B (en) * | 2021-11-08 | 2024-07-02 | 陕西千山航空电子有限责任公司 | Control method of trailing edge flap control system of trainer |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101808896A (en) * | 2007-09-24 | 2010-08-18 | 空中客车营运有限公司 | Automatic control of a high lift system of an aircraft |
| CN103287574A (en) * | 2013-01-05 | 2013-09-11 | 中国航空工业集团公司西安飞机设计研究所 | Control method of high-lift device of airplane |
| CN105109671A (en) * | 2015-09-25 | 2015-12-02 | 江西洪都航空工业集团有限责任公司 | Leading-edge flap control method |
| US20160139597A1 (en) * | 2013-06-14 | 2016-05-19 | Bombardier Inc. | Aircraft ground lift dump flight control function |
| CN106061842A (en) * | 2014-03-18 | 2016-10-26 | 波音公司 | Short landing warning |
-
2019
- 2019-12-06 CN CN201911240126.5A patent/CN110949659A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101808896A (en) * | 2007-09-24 | 2010-08-18 | 空中客车营运有限公司 | Automatic control of a high lift system of an aircraft |
| CN103287574A (en) * | 2013-01-05 | 2013-09-11 | 中国航空工业集团公司西安飞机设计研究所 | Control method of high-lift device of airplane |
| US20160139597A1 (en) * | 2013-06-14 | 2016-05-19 | Bombardier Inc. | Aircraft ground lift dump flight control function |
| CN106061842A (en) * | 2014-03-18 | 2016-10-26 | 波音公司 | Short landing warning |
| CN105109671A (en) * | 2015-09-25 | 2015-12-02 | 江西洪都航空工业集团有限责任公司 | Leading-edge flap control method |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114013628A (en) * | 2021-09-27 | 2022-02-08 | 广东空天科技研究院 | Wing folding control method and device |
| CN114180092A (en) * | 2021-10-18 | 2022-03-15 | 中国航空工业集团公司沈阳飞机设计研究所 | Launching control system of catapult plane |
| CN114180092B (en) * | 2021-10-18 | 2024-06-11 | 中国航空工业集团公司沈阳飞机设计研究所 | Catapult aircraft take-off control system |
| CN113998095A (en) * | 2021-11-08 | 2022-02-01 | 陕西千山航空电子有限责任公司 | Control method of trainer trailing edge flap control system |
| CN113998095B (en) * | 2021-11-08 | 2024-07-02 | 陕西千山航空电子有限责任公司 | Control method of trailing edge flap control system of trainer |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US8356776B2 (en) | Automatic control of a high lift system of an aircraft | |
| EP3415419B1 (en) | Landing gear controller | |
| CN105644800B (en) | One kind is taken off warning system | |
| US20090118874A1 (en) | Systems and methods for controlling aircraft electrical power | |
| US9771141B2 (en) | Leading edge system and method for approach noise reduction | |
| CA2913979C (en) | Aircraft ground lift dump flight control function | |
| CN110949659A (en) | Trailing edge flap control method | |
| US9254909B2 (en) | Optimized flap positioning for go-around operations | |
| WO2019166461A1 (en) | Landing gear system control | |
| US9630705B2 (en) | Drive system for ground spoiler, and aircraft | |
| Yetter | Why do airlines want and use thrust reversers? A compilation of airline industry responses to a survey regarding the use of thrust reversers on commercial transport airplanes | |
| US20020099479A1 (en) | System for automatically controlling lift-augmentation devices of an aircraft during take-off | |
| CN108016604B (en) | Control method for overriding mode in flap control system | |
| US11541992B2 (en) | Landing gear retraction | |
| US7850125B2 (en) | Method and device for reducing the wake vortices of an aircraft in the approach/landing phase | |
| CN105109671A (en) | Leading-edge flap control method | |
| US3224713A (en) | Landing gear system | |
| CN113998095B (en) | Control method of trailing edge flap control system of trainer | |
| CN113815869B (en) | Icing aircraft attack angle protection control method | |
| CN115657526A (en) | Flap automatic control method and device | |
| RU2774010C1 (en) | Method for controlling a gas turbine engine in case of spontaneous opening of a reversing device | |
| CN113998095A (en) | Control method of trainer trailing edge flap control system | |
| CN115556922A (en) | Flap automatic control method and device based on state flow graph | |
| CN117602067A (en) | Light programmable landing gear system and control method thereof | |
| CN113550947A (en) | Stamping turbine control system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20200403 |
|
| RJ01 | Rejection of invention patent application after publication |