CN110550194A - cooperative turning control method and cooperative turning control system for airplane - Google Patents
cooperative turning control method and cooperative turning control system for airplane Download PDFInfo
- Publication number
- CN110550194A CN110550194A CN201910844344.3A CN201910844344A CN110550194A CN 110550194 A CN110550194 A CN 110550194A CN 201910844344 A CN201910844344 A CN 201910844344A CN 110550194 A CN110550194 A CN 110550194A
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- Prior art keywords
- airplane
- landing gear
- aircraft
- rear row
- controller
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/34—Alighting gear characterised by elements which contact the ground or similar surface wheeled type, e.g. multi-wheeled bogies
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/50—Steerable undercarriages; Shimmy-damping
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/34—Alighting gear characterised by elements which contact the ground or similar surface wheeled type, e.g. multi-wheeled bogies
- B64C2025/345—Multi-wheel bogies having one or more steering axes
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Traffic Control Systems (AREA)
Abstract
The application belongs to the technical field of airplane turning control, and particularly relates to a cooperative turning control method of an airplane, which controls a nose landing gear of the airplane to deflect towards a preset direction and controls two landing gears at the rear row of the airplane to deflect towards the opposite direction of the preset direction so as to control the airplane to turn towards the preset direction; and to a cooperative turning control system for the above cooperative turning control method.
Description
Technical Field
the application belongs to the technical field of airplane turning control, and particularly relates to a cooperative turning control method and a cooperative turning control system for an airplane.
Background
the current aircraft mainly adopts the nose wheel to turn and controls aircraft ground direction, it is in aircraft ground turn control process, only the wheel of nose landing gear participates in turn control, this kind of control mode causes the landing gear wheel easily to be worn by the side direction in the turn in-process, especially under the condition that the current aircraft is towards maximization development, the multirow aircraft that has had multirow back row to rise the landing gear has appeared, adopt above-mentioned turn control mode its last row to rise the wheel on the landing gear and by the problem of side direction wear in the aircraft turn in-process more outstanding, in addition, the turn control mode of above-mentioned aircraft needs great turning radius, has high requirement to the width of airport runway.
the present application is made in view of the above-mentioned drawbacks of the prior art.
disclosure of Invention
The present application is directed to a method and a system for controlling cooperative turning of an aircraft, so as to overcome or alleviate at least one of the disadvantages of the prior art.
The technical scheme of the application is as follows:
In one aspect, a coordinated turning control method for an aircraft is provided, which controls the aircraft to turn in a predetermined direction by controlling the nose landing gear of the aircraft to deflect in the predetermined direction and controlling the two landing gears in the rear row of the aircraft to deflect in the opposite direction of the predetermined direction.
According to at least one embodiment of the present application, the aircraft is a multi-wheeled aircraft;
The two landing gears of the rear row of the aircraft are the two landing gears of the last row of the aircraft.
according to at least one embodiment of the application, when the nose landing gear of the airplane is controlled to deflect alpha degrees towards a preset direction, the two landing gears of the rear row of the airplane are controlled to deflect beta degrees towards the opposite direction of the preset direction; wherein the content of the first and second substances,
α°＝K*β°，K∈[3,5]。
according to at least one embodiment of the present application, K-4.
According to at least one embodiment of the present application, α does not exceed 60.
another aspect provides a coordinated turn control system for an aircraft, comprising:
A nose gear control valve for mounting on a nose gear of an aircraft;
The two rear row landing gear control valves are correspondingly arranged on two landing gears of the rear row of the airplane;
The controller is electrically connected with the front undercarriage control valve and the two rear row undercarriage control valves; wherein the content of the first and second substances,
the controller controls the nose landing gear control valve to deflect the nose landing gear of the airplane to a preset direction according to the control instruction, and controls the two rear row landing gear control valves to deflect the two rear row landing gears of the airplane to the opposite direction of the preset direction so as to control the airplane to turn to the preset direction.
according to at least one embodiment of the present application, further comprising:
The nose landing gear position sensor is used for being installed on a nose landing gear of the airplane and electrically connected with the controller so as to feed back the deflection angle of the nose landing gear of the airplane to the controller;
and the two rear row landing gear position sensors are correspondingly arranged on the two landing gears of the rear row of the airplane, and are electrically connected with the controller so as to feed back the deflection angles of the two landing gears of the rear row of the airplane to the controller.
according to at least one embodiment of the application, the pedal turning mechanism further comprises a command sensor, wherein the command sensor is used for being installed on the pedal turning mechanism of the airplane and electrically connected with the controller, and the command sensor is used for sending control commands to the controller.
drawings
FIG. 1 is a schematic structural diagram of a cooperative turn control system of an aircraft provided by an embodiment of the present application;
FIG. 2 is a schematic structural diagram of wheels of an aircraft turning to the right according to an embodiment of the present application;
FIG. 3 is a schematic structural diagram of a wheel when an aircraft turns to the left according to an embodiment of the present application;
Wherein:
1-a nose landing gear control valve; 2-a rear-row lifting and falling frame control valve; 3-a controller; 4-a nose gear position sensor; 5-rear row lifting and falling frame position sensor; 6-a command sensor; 7-nose landing gear; 8-last row landing gear.
Detailed Description
The present application will be described in further detail with reference to the following drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the relevant application and are not limiting of the application. It should be noted that, for convenience of description, only the portions related to the present application are shown in the drawings.
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.
It should be noted that in the description of the present application, the terms of direction or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the directions or positional relationships shown in the drawings, which are merely for convenience of description, and do not indicate or imply that the device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present application. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
Furthermore, it should be noted that, in the description of the present application, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as being fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood by those skilled in the art as the case may be.
the present application is described in further detail below with reference to fig. 1 to 3.
On one hand, the method for controlling the cooperative turning of the airplane is provided, and the method is characterized in that the method controls the nose landing gear 7 of the airplane to deflect towards a preset direction and controls the two landing gears of the rear row of the airplane to deflect towards the opposite direction of the preset direction so as to control the airplane to turn towards the preset direction; the predetermined directions include a left direction and a right direction when the aircraft is taxiing on the ground.
As for the cooperative turning control method of the aircraft disclosed in the above embodiments, it is easily understood by those skilled in the art that the turning of the aircraft in the corresponding direction is realized by simultaneously controlling the front landing gear 7 and the two landing gears in the rear row to deflect in opposite directions, that is, the wheels on the front landing gear 7 and the wheels on the two landing gears in the rear row to deflect in opposite directions, and the control method of the turning of the aircraft makes the front landing gear and the two landing gears in the rear row cooperate, so that the side wear of the wheels on the landing gears of the aircraft during the turning of the aircraft can be reduced, and the turning radius of the aircraft can be reduced.
In some alternative embodiments, the aircraft is a multi-wheeled aircraft;
the two landing gears in the rear row of the aircraft are the two landing gears 8 in the last row of the aircraft, i.e. the two landing gears in the last row located at the tail of the aircraft.
In some alternative embodiments, when the nose landing gear 7 of the aircraft is controlled to deflect by α ° in a predetermined direction, the two landing gears of the rear row of the aircraft are controlled to deflect by β ° in the opposite direction to the predetermined direction; wherein the content of the first and second substances,
α°＝K*β°，K∈[3,5]。
with respect to the cooperative turning control method of the aircraft disclosed in the above embodiment, it will be readily understood by those skilled in the art that the deflection angle of the nose landing gear 7 of the aircraft is linearly related to the deflection angle of the two landing gears of the rear row of the aircraft.
in some alternative embodiments, K-4.
In some alternative embodiments, α does not exceed 60.
In another aspect, there is provided a cooperative turning control system for an aircraft, the cooperative turning control system including:
A nose landing gear control valve 1 for mounting on a nose landing gear 7 of an aircraft;
Two rear row landing gear control valves 2, which are correspondingly arranged on two landing gears of the rear row of the airplane;
the controller 3 is electrically connected with the nose landing gear control valve 1 and the two rear row landing gear control valves 2; wherein the content of the first and second substances,
The controller 3 controls the nose landing gear 7 of the airplane to deflect towards a preset direction by controlling the nose landing gear control valve 1 and controls the two rear row landing gear control valves 2 to deflect the two rear row landing gears of the airplane towards the opposite direction of the preset direction according to the control command so as to control the airplane to turn towards the preset direction.
In some optional embodiments, further comprising:
a nose landing gear position sensor 4, which is used for being mounted on a nose landing gear 7 of the airplane and is electrically connected with the controller 3 so as to feed back the deflection angle of the nose landing gear 7 of the airplane to the controller 3;
Two rear row landing gear position sensors 5, for corresponding mounting on two landing gears of the rear row of the aircraft, are electrically connected to the controller 3, so as to feed back to the controller 3 the deflection angle of the two landing gears of the rear row of the aircraft.
with regard to the cooperative turning control method for an aircraft disclosed in the above embodiment, it is easily understood by those skilled in the art that the controller 3 can determine whether the nose landing gear 7 and the two landing gears in the rear row of the aircraft are deflected in place according to the deflection angle of the nose landing gear 7 of the aircraft and the deflection angles of the two landing gears in the rear row of the aircraft fed back by the nose landing gear position sensor 4 and the two rear row landing gear position sensors 5.
In some optional embodiments, the control system further comprises a command sensor 6, which is used for being installed on a pedal turning mechanism of the airplane and is electrically connected with the controller 3 so as to send a control command to the controller 3.
For the cooperative turning control method for the aircraft disclosed in the above embodiment, as those skilled in the art can easily understand, the command sensor 6 is installed on a pedal turning mechanism of the aircraft, an operator operates the pedal turning mechanism according to actual conditions, so that the command sensor 6 installed on the pedal turning mechanism sends a corresponding control command to the controller 3, and the controller 3 controls the nose landing gear control valve 1 and the two rear row landing gear control valves 2 according to the control command, so that the nose landing gear 7 and the two rear row landing gears of the aircraft deflect by corresponding angles, thereby realizing cooperative control of the aircraft turning.
So far, the technical solutions of the present application have been described in connection with the preferred embodiments shown in the drawings, but it is easily understood by those skilled in the art that the scope of the present application is obviously not limited to these specific embodiments. Equivalent changes or substitutions of related technical features can be made by those skilled in the art without departing from the principle of the present application, and the technical scheme after the changes or substitutions will fall into the protection scope of the present application.
Claims (8)
1. A cooperative turning control method of an aircraft is characterized in that,
the airplane is controlled to turn in a predetermined direction by controlling the nose landing gear (7) of the airplane to deflect in the predetermined direction and controlling the two landing gears in the rear row of the airplane to deflect in the opposite direction of the predetermined direction.
2. The cooperative turn control method according to claim 1, characterized in that,
The aircraft is a multi-wheeled aircraft;
the two landing gears of the rear row of the aircraft are the two landing gears (8) of the last row of the aircraft.
3. The cooperative turn control method according to claim 1, characterized in that,
Controlling the two landing gears in the rear row of the airplane to deflect beta degrees in the opposite direction of a preset direction when the nose landing gear (7) of the airplane is controlled to deflect alpha degrees in the preset direction; wherein the content of the first and second substances,
α°＝K*β°，K∈[3,5]。
4. the cooperative turn control method according to claim 3, characterized in that,
K＝4。
5. The cooperative turn control method according to claim 2, characterized in that,
alpha is not more than 60.
6. A coordinated turn control system for an aircraft, comprising:
A nose landing gear control valve (1) for mounting on a nose landing gear (7) of an aircraft;
Two rear row landing gear control valves (2) for corresponding mounting on two landing gears of the rear row of the aircraft;
the controller (3) is electrically connected with the nose landing gear control valve (1) and the two rear row landing gear control valves (2); wherein the content of the first and second substances,
And the controller (3) controls the nose landing gear control valve (1) to deflect a nose landing gear (7) of the airplane to a preset direction according to a control instruction, and controls the two rear row landing gear control valves (2) to deflect the two rear row landing gears of the airplane to the opposite direction of the preset direction so as to control the airplane to turn to the preset direction.
7. the cooperative turn control system according to claim 6,
Further comprising:
a nose landing gear position sensor (4) which is used for being installed on a nose landing gear (7) of the airplane and is electrically connected with the controller (3) so as to feed back the deflection angle of the nose landing gear (7) of the airplane to the controller (3);
And the two rear row landing gear position sensors (5) are correspondingly arranged on the two landing gears of the rear row of the airplane and are electrically connected with the controller (3) so as to feed back the deflection angles of the two landing gears of the rear row of the airplane to the controller (3).
8. the cooperative turn control system according to claim 7,
the control device is characterized by further comprising an instruction sensor (6) which is used for being installed on a pedal turning mechanism of the airplane and electrically connected with the controller (3) so as to send the control instruction to the controller (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910844344.3A CN110550194A (en) | 2019-09-06 | 2019-09-06 | cooperative turning control method and cooperative turning control system for airplane |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910844344.3A CN110550194A (en) | 2019-09-06 | 2019-09-06 | cooperative turning control method and cooperative turning control system for airplane |
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| Publication Number | Publication Date |
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| CN110550194A true CN110550194A (en) | 2019-12-10 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201910844344.3A Pending CN110550194A (en) | 2019-09-06 | 2019-09-06 | cooperative turning control method and cooperative turning control system for airplane |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112357065A (en) * | 2020-11-25 | 2021-02-12 | 同济大学 | Ground turning control method of multi-wheel multi-support airplane |
| CN112810805A (en) * | 2021-01-20 | 2021-05-18 | 同济大学 | Multi-wheel multi-support wide-body airplane main wheel cooperative turning asymmetric control system |
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| US3488020A (en) * | 1967-07-25 | 1970-01-06 | Boeing Co | Steerable four truck main landing gear for heavy aircraft |
| US5242131A (en) * | 1992-04-08 | 1993-09-07 | The Boeing Company | Steerable landing gear |
| CN201329894Y (en) * | 2008-12-10 | 2009-10-21 | 威海广泰空港设备股份有限公司 | Steering gear for wheels of aircraft tractor |
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| CN202987262U (en) * | 2012-10-11 | 2013-06-12 | 吉林大学 | Four-wheel independent steering-by-wire system with multiple-steering modal |
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| US20150329202A1 (en) * | 2012-12-19 | 2015-11-19 | Borealis Technical Limited | Control of ground travel and steering in an aircraft with powered main gear drive wheels |
| CN105564639A (en) * | 2014-10-11 | 2016-05-11 | 中国航空工业集团公司西安飞机设计研究所 | Dual-redundancy nose-wheel steering and shimmy-damping system |
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Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3488020A (en) * | 1967-07-25 | 1970-01-06 | Boeing Co | Steerable four truck main landing gear for heavy aircraft |
| US5242131A (en) * | 1992-04-08 | 1993-09-07 | The Boeing Company | Steerable landing gear |
| CN201329894Y (en) * | 2008-12-10 | 2009-10-21 | 威海广泰空港设备股份有限公司 | Steering gear for wheels of aircraft tractor |
| CN101638052A (en) * | 2009-08-21 | 2010-02-03 | 山东大学 | Wheel assembly with integration of independent driving, steering, suspending and braking |
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| US20150329202A1 (en) * | 2012-12-19 | 2015-11-19 | Borealis Technical Limited | Control of ground travel and steering in an aircraft with powered main gear drive wheels |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112357065A (en) * | 2020-11-25 | 2021-02-12 | 同济大学 | Ground turning control method of multi-wheel multi-support airplane |
| CN112357065B (en) * | 2020-11-25 | 2021-12-31 | 同济大学 | Ground turning control method of multi-wheel multi-support airplane |
| CN112810805A (en) * | 2021-01-20 | 2021-05-18 | 同济大学 | Multi-wheel multi-support wide-body airplane main wheel cooperative turning asymmetric control system |
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Application publication date: 20191210 |
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