CN114313230B - Landing gear retraction system and method, and computer readable medium - Google Patents
Landing gear retraction system and method, and computer readable medium Download PDFInfo
- Publication number
- CN114313230B CN114313230B CN202210078301.0A CN202210078301A CN114313230B CN 114313230 B CN114313230 B CN 114313230B CN 202210078301 A CN202210078301 A CN 202210078301A CN 114313230 B CN114313230 B CN 114313230B
- Authority
- CN
- China
- Prior art keywords
- landing gear
- aircraft
- retraction
- landing
- retraction system
- 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.)
- Active
Links
- 238000000034 method Methods 0.000 title claims description 27
- 230000004044 response Effects 0.000 claims abstract description 11
- 230000005540 biological transmission Effects 0.000 claims abstract description 3
- 230000003993 interaction Effects 0.000 claims description 8
- 238000013459 approach Methods 0.000 claims description 7
- 230000002411 adverse Effects 0.000 abstract description 5
- 230000008901 benefit Effects 0.000 description 3
- 238000004590 computer program Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000000835 fiber Substances 0.000 description 2
- 230000006870 function Effects 0.000 description 2
- 230000003287 optical effect Effects 0.000 description 2
- 230000009194 climbing Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 230000002452 interceptive effect Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
Landscapes
- Traffic Control Systems (AREA)
Abstract
The invention aims to provide a civil transportation type aircraft landing gear retraction system which can improve the retraction reliability of landing gears. The landing gear retraction system for achieving the purpose comprises a control unit and an execution unit, wherein the execution unit is in transmission connection with the landing gear and is used for retracting or releasing the landing gear; wherein, in response to the first judgment condition, the control unit instructs the execution unit to retract the landing gear; in response to the second determination condition, the control unit instructs the execution unit to lower the landing gear. Through this undercarriage receive and releases system, can realize the adjustment to undercarriage receive and release state according to first judgement condition and second judgement condition to can reduce when adopting artificial operation to receive and release the undercarriage, the adverse consequence that causes because of artificial operation mistake.
Description
Technical Field
The invention relates to the field of aircrafts, in particular to a landing gear retraction system and method and a computer readable medium.
Background
Landing gear is an accessory device under the aircraft for supporting the aircraft for take-off and landing or ground taxiing and for ground movement. When the aircraft needs to move on the ground, the landing gear needs to be put down, and when the aircraft takes off, the landing gear needs to be retracted in order to ensure the flight performance.
Existing landing gear retraction systems include a control system for controlling actuation of an actuator to either retract or extend the landing gear, and an actuator assembly. Currently, landing gear systems are manually controlled by a person, i.e., by manually issuing instructions to a control system to control the actuator to either extend or retract the landing gear.
However, the inventor finds that, because the retraction and the extension of the landing gear are carried out in the process of taking off and landing of the aircraft, the working load of the unit is relatively large at this stage, errors are easy to occur, and the unit often forgets to retract or extend the landing gear, and even air-break happens. In the current aircraft, although the landing gear non-lowering alarm is set, when the unit falls into a special condition, the alarm can be ignored, and accidents are caused.
Disclosure of Invention
The invention aims to provide a landing gear retraction system which can improve the reliability of retraction of a landing gear.
The landing gear retraction system for achieving the purpose comprises a control unit and an execution unit, wherein the execution unit is in transmission connection with the landing gear and is used for retracting or retracting the landing gear; wherein, in response to a first judgment condition, the control unit instructs the execution unit to retract the landing gear; in response to a second determination, the control unit instructs the execution unit to lower the landing gear. Through this undercarriage receive and releases system, can realize the adjustment to undercarriage receive and release state according to first judgement condition and second judgement condition to can reduce when adopting artificial operation to receive and release the undercarriage, the adverse consequence that causes because of artificial operation mistake.
In one or more embodiments, the first determination condition includes:
The all-wheel-load signal of the aircraft shows that the aircraft is in an airborne state; and
All the landing gears are in a put-down state; and
The control unit does not instruct the execution unit to lower the landing gear; and
The aircraft has a radio altitude greater than 100 feet; and
The rate of climb of the aircraft is greater than 10 feet per minute and the duration is greater than 5 seconds;
The second judgment condition includes:
All the landing gear is in a retracted state; and
The aircraft has a radio altitude greater than 1000 feet; and
The flap of the aircraft is in a landing approach attitude; and
The current thrust of the aircraft engine is less than the takeoff thrust of the aircraft engine.
Through the first judging condition and the second judging condition, information about whether the aircraft needs to put down or put up the landing gear can be effectively obtained, so that the landing gear is put up or put down according to the information, and the reliability of automatic landing gear taking up and putting down is ensured.
In one or more embodiments, the landing gear retraction system includes a first retraction mode in which the control unit may instruct the execution unit to retract or retract the landing gear in response to the first determination condition or the second determination condition. Through setting up first receipts mode for undercarriage receive and releases the system and can receive and release the undercarriage through the mode of automatic receipts and release if and only if in specific first receipts mode, thereby provides the basis for increasing the mode of operating undercarriage receive and release.
In one or more embodiments, the first judgment condition and the second judgment condition further include: the landing gear retraction system is in the first retraction mode.
In one or more embodiments, the landing gear retraction system includes a second retraction mode, the landing gear retraction system further including an operation unit, in which the execution unit may be instructed to retract or retract the landing gear by the operation unit; the landing gear retraction system further comprises an interaction unit, the landing gear retraction system is in the first retraction mode by default, and the landing gear retraction system can be switched to the second retraction mode through the interaction unit. When the automatic retraction mode fails or the manual mode is actively activated, the landing gear can be manually retracted and extended by switching to the second retraction mode, so that the safety of the retraction system is improved.
Another object of the present invention is to provide a landing gear retraction method capable of improving reliability for retraction of a landing gear, comprising the following steps:
judging whether the aircraft meets a first judging condition, and if so, retracting the landing gear;
And judging whether the aircraft meets the second judging condition, and if so, putting down the landing gear.
In one or more embodiments, the first determination condition includes:
The all-wheel-load signal of the aircraft shows that the aircraft is in an airborne state; and
All the landing gears are in a put-down state; and
Not commanding the landing gear to be lowered; and
The aircraft has a radio altitude greater than 100 feet; and
The rate of climb of the aircraft is greater than 10 feet per minute and the duration is greater than 5 seconds;
The second judgment condition includes:
the landing gear is in a retracted state; and
The aircraft has a radio altitude greater than 1000 feet; and
The flap of the aircraft is in a landing approach attitude; and
The current thrust of the aircraft engine is less than the takeoff thrust of the aircraft engine.
In one or more embodiments, the landing gear retraction method further comprises:
Configuring a first retraction mode, wherein in the first retraction mode, the landing gear can be retracted or lowered according to whether the aircraft meets the first judgment condition or the second judgment condition;
the first judgment condition and the second judgment condition respectively further include:
the landing gear retraction system is in the first retraction mode.
In one or more embodiments, the landing gear retraction method further comprises:
configuring a second retraction mode in which the operating unit is operable to retract or extend the landing gear, the method further comprising:
switching to the second retraction mode;
The operating unit is operated to retract or to lower the landing gear.
The application also provides a computer readable medium having stored thereon computer instructions which when executed by a processor implement the steps of the landing gear retraction method of any preceding claim.
The foregoing description is only an overview of the present application, and is intended to be implemented in accordance with the teachings of the present application in order that the same may be more clearly understood and to make the same and other objects, features and advantages of the present application more readily apparent.
Drawings
Various other advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The drawings are only for purposes of illustrating the preferred embodiments and are not to be construed as limiting the application. Also, like reference numerals are used to designate like parts throughout the accompanying drawings. In the drawings:
FIG. 1 illustrates a schematic view of a landing gear retraction system according to some embodiments of the present application;
FIG. 2 is a schematic view of a landing gear retraction system according to further embodiments of the present application;
FIG. 3 is a flow chart of a landing gear retraction method according to some embodiments of the present application;
FIG. 4 is a flow chart of a landing gear retraction method according to further embodiments of the present application.
Detailed Description
Embodiments of the technical scheme of the present application will be described in detail below with reference to the accompanying drawings. The following examples are only for more clearly illustrating the technical aspects of the present application, and thus are merely examples, and are not intended to limit the scope of the present application.
Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs; the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the application; the terms "comprising" and "having" and any variations thereof in the description of the application and the claims and the description of the drawings above are intended to cover a non-exclusive inclusion.
At present, the landing gear is controlled manually by a machine set to the landing gear system, so that the energy of the machine set is consumed, and once the machine set makes mistakes, adverse effects are easy to occur.
After the research of the applicant, the retraction of the landing gear can be controlled through a reasonable-design automatic control system, so that adverse effects caused by human operation errors are reduced.
In one aspect, according to some embodiments of the present application, a landing gear retraction system is provided, referring to fig. 1, with fig. 1 showing a schematic view of a landing gear retraction system according to some embodiments of the present application. The landing gear retraction system comprises a control unit 1 and an execution unit 2. The actuator unit 2 is in driving connection with the landing gear 3 for retracting or extending the landing gear 3. Wherein, in response to the first judgment condition, the control unit 1 instructs the execution unit 2 to retract the landing gear 3; in response to the second judgment condition, the control unit 1 instructs the execution unit 2 to lower the landing gear 3.
Reference herein to "an embodiment" means that a particular feature, structure, or characteristic described in connection with the embodiment may be included in at least one embodiment of the application. The appearances of such phrases in various places in the specification are not necessarily all referring to the same embodiment, nor are separate or alternative embodiments mutually exclusive of other embodiments. Those of skill in the art will explicitly and implicitly appreciate that the embodiments described herein may be combined with other embodiments.
The actuating unit 2 is used for driving/driving the landing gear 3 to retract or to be put down, alternatively, in some embodiments, the actuating unit 2 comprises an actuator cylinder, a connecting rod and other components, and the actuating cylinder can drive the connecting rod to communicate with the landing gear 3 in driving connection with the connecting rod to follow, so as to put down or retract the landing gear.
Through this undercarriage receive and releases system, can realize the adjustment to undercarriage 3 receive and release state according to first judgement condition and second judgement condition to can reduce when adopting the artificial operation to receive and release the undercarriage, the adverse consequence that causes because of the artificial operation mistake.
According to some embodiments of the application, the first judgment condition includes: the all-wheel-load signal of the aircraft shows that the aircraft is in an airborne state; and landing gear 3 is in the lowered state; and the control unit 1 does not instruct the execution unit 2 to lower the landing gear 3; and the radio altitude of the aircraft is greater than 100 feet; and the rate of climb of the aircraft exceeds 10 feet per minute and the duration exceeds 5 seconds;
The second judgment condition includes: the landing gear 3 is in a stowed state; and the radio altitude of the aircraft is greater than 1000 feet; and the flap of the aircraft is in a landing approach attitude; and the current thrust of the aircraft engine is less than the takeoff thrust of the aircraft engine.
The wheel load signal is a key signal in the landing gear system of the aircraft, and can be obtained according to a landing gear system wheel load sensor for judging the air-ground state of the aircraft. After the comprehensive judgment of the three landing gear wheel load signals of the aircraft, the all-wheel load signal can be obtained, and whether the aircraft is in an in-air state or not can be obtained.
To determine whether the landing gear 3 is in the down state or the up state, alternatively, a sensor may be provided on the landing gear 3, and the position and attitude information of the landing gear 3 may be determined based on the signal of the sensor. Alternatively, the position and attitude information of the landing gear 3 may also be obtained by an image acquisition unit such as a camera.
The radio altitude of the aircraft and the climbing rate of the aircraft are basic state information of the aircraft in a flight state.
Whether the flap of the aircraft is in a landing approach attitude can be obtained from the catch of the flap.
In the first judgment condition, the additional judgment control unit 1 does not instruct the execution unit 2 to release the landing gear 3, so that the instruction for releasing the landing gear 3 has higher priority than the instruction for retracting the landing gear 3, thereby preventing the landing gear 3 from being retracted by mistake due to system failure and further causing accidents.
Through the first judging condition and the second judging condition, information about whether the aircraft needs to put down or put up the landing gear can be effectively obtained, so that the landing gear is put up or put down according to the information, and the reliability of automatic landing gear taking up and putting down is ensured.
According to some embodiments of the application, the landing gear retraction system comprises a first retraction mode in which the control unit 1 may instruct the execution unit 2 to retract or to extend the landing gear 3 in response to a first determination condition or a second determination condition.
By setting the first retraction mode, the landing gear retraction system can retract and retract the landing gear 3 in an automatic retraction mode if and only if the landing gear retraction system is in the specific first retraction mode, thereby providing a basis for increasing the retraction mode of the operation landing gear.
Optionally, in some embodiments, the landing gear retraction system only uses an automatic retraction manner to retract the landing gear 3, and at this time, the first retraction mode is not required to be additionally set.
Further, on the basis of the foregoing embodiment, the first judgment condition and the second judgment condition further include: the landing gear retraction system is in a first retraction mode.
Only when the landing gear retraction system is in the first retraction mode, the control unit 1 may be caused to retract or to extend the landing gear 3 according to the first determination condition and the second determination condition.
Referring to fig. 2, fig. 2 is a schematic view of a landing gear retraction system according to other embodiments of the present application, the landing gear retraction system including a second retraction mode, and the landing gear retraction system further including an operation unit 4, in which the operation unit 4 can instruct the execution unit 2 to retract or to retract the landing gear 3; the landing gear retraction system further comprises an interaction unit 5, the landing gear retraction system is in the first retraction mode by default, and the landing gear retraction system can be switched to the second retraction mode through the interaction unit 5.
In the description of embodiments of the present application, the technical terms "first," "second," and the like are used merely to distinguish between different objects and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated, a particular order or a primary or secondary relationship.
The operating unit 4 is optionally an operating lever, by which the position or the actuation posture of the executing unit 2 can be controlled manually, so that the landing gear 3 is brought up or down.
The interaction unit 5 is optionally a screen panel with an interactive interface in the screen panel, and the retractable mode can be switched by touching a corresponding key in the interface, optionally with information in the screen panel for indicating the landing gear status.
When the automatic retraction mode fails or the manual mode is actively activated, the landing gear can be manually retracted and extended by switching to the second retraction mode, so that the safety of the retraction system is improved.
On the other hand, according to some embodiments of the present application, a landing gear retraction method is provided, please refer to fig. 3, fig. 3 is a flow chart of the landing gear retraction method according to some embodiments of the present application; the landing gear retraction method comprises the following steps:
S101: judging whether the aircraft meets the first judging condition, if so, executing step S102: stowing the landing gear;
S103: judging whether the aircraft meets the second judging condition, if so, executing step S104: and (5) lowering the landing gear.
The step S101 and the step S102 may be performed synchronously, i.e. whether the aircraft meets the first determination condition or whether the aircraft meets the second determination condition is continuously determined, and if the conditions are met, the step S102 or the step S104 is performed. If the condition is not satisfied, continuing to judge.
According to some embodiments of the application, the first judgment condition includes: the all-wheel-load signal of the aircraft shows that the aircraft is in an airborne state; and landing gear 3 is in the lowered state; and the control unit 1 does not instruct the execution unit 2 to lower the landing gear 3; and the radio altitude of the aircraft is greater than 100 feet; and the rate of climb of the aircraft exceeds 10 feet per minute and the duration exceeds 5 seconds; the second judgment condition includes: the landing gear 3 is in a stowed state; and the radio altitude of the aircraft is greater than 1000 feet; and the flap of the aircraft is in a landing approach attitude; and the current thrust of the aircraft engine is less than the takeoff thrust of the aircraft engine.
The conditions in the first or second judging conditions need to be all satisfied, so that the judging result in step S101 or S103 is yes.
According to some embodiments of the application, the landing gear retraction method further comprises: a first retraction mode is configured, and under the first retraction mode, the landing gear 3 can be retracted or lowered according to whether the aircraft meets a first judgment condition or a second judgment condition;
the first judgment condition and the second judgment condition respectively further include: the landing gear retraction system is in a first retraction mode.
Referring to fig. 4, fig. 4 is a schematic flow chart of a landing gear retraction method according to other embodiments of the present application; the landing gear retraction method further comprises the following steps:
the method further includes configuring a second retraction mode in which the operating unit is operable to retract or extend the landing gear, the method further comprising:
step S105: switching to a second retraction mode;
step S106: the operating unit is operated to retract or to lower the landing gear.
The landing gear retraction method according to one or more embodiments described above may be implemented by using the landing gear retraction system according to one or more embodiments described above, which is not described herein.
The present disclosure provides the above computer-readable storage medium having stored thereon computer instructions. When the computer instructions are executed by the processor, the landing gear retraction method provided by any one of the embodiments can be implemented, so that the landing gear can be automatically retracted and extended, and the reliability of the retraction and extension of the landing gear is improved.
The steps of a method or algorithm described in connection with the embodiments disclosed herein may be embodied directly in hardware, in a software module executed by a processor, or in a combination of the two. A software module may reside in RAM memory, flash memory, ROM memory, EPROM memory, EEPROM memory, registers, hard disk, a removable disk, a CD-ROM, or any other form of storage medium known in the art. An exemplary storage medium is coupled to the processor such the processor can read information from, and write information to, the storage medium. In the alternative, the storage medium may be integral to the processor. The processor and the storage medium may reside in an ASIC. The ASIC may reside in a user terminal. In the alternative, the processor and the storage medium may reside as discrete components in a user terminal.
In one or more exemplary embodiments, the functions described may be implemented in hardware, software, firmware, or any combination thereof. If implemented in software as a computer program product, the functions may be stored on or transmitted over as one or more instructions or code on a computer-readable medium. Computer-readable media includes both computer storage media and communication media including any medium that facilitates transfer of a computer program from one place to another. A storage media may be any available media that can be accessed by a computer. By way of example, and not limitation, such computer-readable media can comprise RAM, ROM, EEPROM, CD-ROM or other optical disk storage, magnetic disk storage or other magnetic storage devices, or any other medium that can be used to carry or store desired program code in the form of instructions or data structures and that can be accessed by a computer. Any connection is properly termed a computer-readable medium. For example, if the software is transmitted from a web site, server, or other remote source using a coaxial cable, fiber optic cable, twisted pair, digital Subscriber Line (DSL), or wireless technologies such as infrared, radio, and microwave, then the coaxial cable, fiber optic cable, twisted pair, DSL, or wireless technologies such as infrared, radio, and microwave are included in the definition of medium. Disk (disk) and disc (disk) as used herein include Compact Disc (CD), laser disc, optical disc, digital Versatile Disc (DVD), floppy disk and blu-ray disc where disks (disk) usually reproduce data magnetically, while discs (disk) reproduce data optically with lasers. Combinations of the above should also be included within the scope of computer-readable media.
In the description of the embodiments of the present application, unless explicitly specified and limited otherwise, the terms "mounted," "connected," "secured" and the like should be construed broadly and may be, for example, fixedly connected, detachably connected, or integrally formed; or may be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communicated with the inside of two elements or the interaction relationship of the two elements. The specific meaning of the above terms in the embodiments of the present application will be understood by those of ordinary skill in the art according to specific circumstances.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present application, and not for limiting the same; although the application has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some or all of the technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit of the application, and are intended to be included within the scope of the appended claims and description. In particular, the technical features mentioned in the respective embodiments may be combined in any manner as long as there is no structural conflict. The present application is not limited to the specific embodiments disclosed herein, but encompasses all technical solutions falling within the scope of the claims.
Claims (8)
1. A landing gear retraction system, comprising:
A control unit; and
The execution unit is in transmission connection with the landing gear and is used for retracting or releasing the landing gear;
wherein, in response to a first judgment condition, the control unit instructs the execution unit to retract the landing gear; in response to a second determination condition, the control unit instructs the execution unit to lower the landing gear;
the first judgment condition includes:
The all-wheel-load signal of the aircraft shows that the aircraft is in an airborne state; and
All the landing gears are in a put-down state; and
The control unit does not instruct the execution unit to lower the landing gear; and
The aircraft has a radio altitude greater than 100 feet; and
The rate of climb of the aircraft is greater than 10 feet per minute and the duration is greater than 5 seconds; and
The instruction priority of the landing gear is higher than that of the landing gear;
The second judgment condition includes:
the landing gear is in a retracted state; and
The aircraft has a radio altitude greater than 1000 feet; and
The flap of the aircraft is in a landing approach attitude; and
The current thrust of the aircraft engine is less than the takeoff thrust of the aircraft engine.
2. A landing gear retraction system according to claim 1 wherein the landing gear retraction system includes a first retraction mode in which the control unit is operable to instruct the execution unit to retract or retract the landing gear in response to the first or second determination.
3. The landing gear retraction system according to claim 2 wherein the first determination condition and the second determination condition each further include:
the landing gear retraction system is in the first retraction mode.
4. The landing gear retraction system according to claim 2 wherein the landing gear retraction system includes a second retraction mode, the landing gear retraction system further including an operating unit, in the second retraction mode the actuating unit being instructed to retract or retract the landing gear by the operating unit;
The landing gear retraction system further comprises an interaction unit, the landing gear retraction system is in the first retraction mode by default, and the landing gear retraction system can be switched to the second retraction mode through the interaction unit.
5. The landing gear retraction method is characterized by comprising the following steps of:
judging whether the aircraft meets a first judging condition, and if so, retracting the landing gear;
judging whether the aircraft meets a second judging condition, and if so, putting down the landing gear;
the first judgment condition includes:
The all-wheel-load signal of the aircraft shows that the aircraft is in an airborne state; and
All the landing gears are in a put-down state; and
Not commanding the landing gear to be lowered; and
The aircraft has a radio altitude greater than 100 feet; and
The rate of climb of the aircraft is greater than 10 feet per minute and the duration is greater than 5 seconds; and
The instruction priority of the landing gear is higher than that of the landing gear;
The second judgment condition includes:
the landing gear is in a retracted state; and
The aircraft has a radio altitude greater than 1000 feet; and
The flap of the aircraft is in a landing approach attitude; and
The current thrust of the aircraft engine is less than the takeoff thrust of the aircraft engine.
6. The landing gear retraction method according to claim 5 further comprising:
configuring a first retraction mode in which the landing gear can be retracted or lowered according to whether the aircraft meets the first or second determination conditions;
the first judgment condition and the second judgment condition respectively further include:
the landing gear retraction system is in the first retraction mode.
7. The landing gear retraction method according to claim 6 further comprising:
configuring a second retraction mode in which the operating unit is operable to retract or extend the landing gear, the method further comprising:
switching to the second retraction mode;
The operating unit is operated to retract or to lower the landing gear.
8. A computer readable medium having stored thereon computer instructions which, when executed by a processor, implement the steps of the landing gear retraction method according to claim 5 or 6.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210078301.0A CN114313230B (en) | 2022-01-24 | 2022-01-24 | Landing gear retraction system and method, and computer readable medium |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210078301.0A CN114313230B (en) | 2022-01-24 | 2022-01-24 | Landing gear retraction system and method, and computer readable medium |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114313230A CN114313230A (en) | 2022-04-12 |
| CN114313230B true CN114313230B (en) | 2024-06-14 |
Family
ID=81029165
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210078301.0A Active CN114313230B (en) | 2022-01-24 | 2022-01-24 | Landing gear retraction system and method, and computer readable medium |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114313230B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116176832B (en) * | 2023-05-04 | 2023-10-24 | 成都凯天电子股份有限公司 | Method for controlling retraction, extension and extension based on complex undercarriage configuration |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110466745A (en) * | 2019-09-24 | 2019-11-19 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of unmanned plane undercarriage control control method |
| CN111619790A (en) * | 2019-02-28 | 2020-09-04 | 空中客车营运有限公司 | Landing gear system, aircraft, method and storage medium |
Family Cites Families (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR818936A (en) * | 1937-03-08 | 1937-10-06 | Renault Aviat | Landing Gear Improvements |
| US6854689B1 (en) * | 2004-02-09 | 2005-02-15 | The Boeing Company | Methods and systems for operating aircraft landing gears |
| CN206265292U (en) * | 2016-11-18 | 2017-06-20 | 捷西迪（广州）光学科技有限公司 | A kind of unmanned aerial vehicle with retractable landing gear device |
| GB2563851B (en) * | 2017-06-27 | 2020-04-01 | Airbus Operations Ltd | Aircraft steering |
| GB2571708A (en) * | 2018-02-28 | 2019-09-11 | Airbus Operations Ltd | Landing gear system control |
| CN111661315B (en) * | 2019-03-07 | 2023-07-11 | 海鹰航空通用装备有限责任公司 | Unmanned aerial vehicle landing gear autonomous-lowering management method and control system |
| CN111661314B (en) * | 2019-03-07 | 2023-07-14 | 海鹰航空通用装备有限责任公司 | Unmanned aerial vehicle undercarriage autonomous stowing management method and control system |
| GB2583464A (en) * | 2019-04-18 | 2020-11-04 | Airbus Operations Ltd | System and method for landing gear retraction |
| CN113753223A (en) * | 2020-06-02 | 2021-12-07 | 北京航天易联科技发展有限公司 | Undercarriage control method and device, electronic equipment and storage medium |
| CN113723561A (en) * | 2021-09-10 | 2021-11-30 | 中国航空工业集团公司西安飞行自动控制研究所 | Method for judging flight phase of airplane ground proximity warning system based on data driving |
-
2022
- 2022-01-24 CN CN202210078301.0A patent/CN114313230B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111619790A (en) * | 2019-02-28 | 2020-09-04 | 空中客车营运有限公司 | Landing gear system, aircraft, method and storage medium |
| CN110466745A (en) * | 2019-09-24 | 2019-11-19 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of unmanned plane undercarriage control control method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114313230A (en) | 2022-04-12 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| RU2478520C2 (en) | Device for automatic control over aircraft lift increase system | |
| CN114313230B (en) | Landing gear retraction system and method, and computer readable medium | |
| US11001390B2 (en) | Helicopter hybrid engine system | |
| RU2449153C1 (en) | Method and device to apply thrust reversers of aircraft | |
| US8255098B2 (en) | Variably manned aircraft | |
| EP2086837B1 (en) | System and method for transferring airplanes | |
| US9944384B2 (en) | Method and a device for controlling at least two subsystems of an aircraft | |
| JP6267945B2 (en) | Aircraft engine control computer and aircraft | |
| EP2033059B1 (en) | Surface contact override landing scheme for a fbw rotary-wing aircraft | |
| US20200407047A1 (en) | Landing gear system control | |
| CN109552649B (en) | Telescopic refueling arm control system and method | |
| CN111824396A (en) | System and method for landing gear retraction | |
| CN110949659A (en) | Trailing edge flap control method | |
| CN110667826B (en) | High-lift distributed telex control system | |
| CN111619790A (en) | Landing gear system, aircraft, method and storage medium | |
| EP3112260A1 (en) | A method of controlling aerodynamic means of an aircraft, an associated control system, and an aircraft provided with such a control system | |
| CN111846250B (en) | Method and system for controlling speed and attitude modes of an aircraft | |
| CN113998095A (en) | Control method of trainer trailing edge flap control system | |
| US20220412287A1 (en) | System for controlling an aircraft thrust reversal means | |
| CN113859529B (en) | Retractable rudder control system and control method | |
| KR102671496B1 (en) | Communication relay streamlined unmanned aerial vehicle system | |
| CN212989954U (en) | Unmanned aerial vehicle with simplified operation | |
| CN116088564A (en) | Indoor intelligent agricultural operation unmanned aerial vehicle flight control method | |
| JPH04314696A (en) | Helicopter | |
| CN113975697A (en) | Fire-fighting aircraft water-drawing takeoff alarming method |
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 | ||
| GR01 | Patent grant |