CN114313230A - Landing gear retraction system and method, computer readable medium - Google Patents
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Abstract
The invention aims to provide a civil transportation type aircraft landing gear folding and unfolding system which can improve the folding and unfolding reliability of a landing gear. The undercarriage control system comprises a control unit and an execution unit, wherein the execution unit is in transmission connection with the undercarriage and is used for retracting or putting down the undercarriage; wherein, in response to a first judgment condition, the control unit instructs the execution unit to retract the undercarriage; in response to a second determination condition, the control unit instructs the execution unit to lower the landing gear. By the undercarriage folding and unfolding system, the folding and unfolding state of the undercarriage can be adjusted according to the first judgment condition and the second judgment condition, so that adverse consequences caused by manual operation errors when the undercarriage is folded and unfolded through manual operation can be reduced.
Description
Technical Field
The invention relates to the field of airplanes, in particular to a landing gear retraction system and method and a computer readable medium.
Background
Landing gear is an attachment device for supporting an aircraft on its lower portion for takeoff and landing or for ground movement during taxiing. When the aircraft needs to move on the ground, the landing gear needs to be lowered, 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 extend or retract the landing gear, and an actuator assembly. Currently, landing gear systems are manually controlled, i.e. commands are manually sent to the control system to control the actuator to either extend or retract the landing gear.
However, the inventor finds that the retraction and the release of the landing gear are both carried out in the process of taking off and landing of the airplane, so that the unit has a large working load and is easy to make errors, the unit forgets to retract or release the landing gear often occurs, and even the air-raid shelter is caused. In the current airplane, although the alarm that the landing gear is not put down is set, when the aircraft is in a special condition, the alarm is still ignored, and an accident is caused.
Disclosure of Invention
The invention aims to provide an undercarriage folding and unfolding system, which can improve the reliability of folding and unfolding of an undercarriage.
The undercarriage control system comprises a control unit and an execution unit, wherein the execution unit is in transmission connection with the undercarriage and is used for retracting or putting down the undercarriage; wherein, in response to a first determination condition, the control unit instructs the execution unit to stow the landing gear; in response to a second determination condition, the control unit instructs the execution unit to lower the landing gear. By the undercarriage folding and unfolding system, the folding and unfolding state of the undercarriage can be adjusted according to the first judgment condition and the second judgment condition, so that adverse consequences caused by manual operation errors when the undercarriage is folded and unfolded through manual operation can be reduced.
In one or more embodiments, the first determination condition includes:
the full-wheel-borne signal of the airplane shows that the airplane is in an air state; and is
All of the landing gear is in a lowered state; and is
The control unit does not instruct the execution unit to lower the landing gear; and is
The radio altitude of the aircraft is greater than 100 feet; and is
The rate of climb of the aircraft is in excess of 10 feet per minute and the duration is in excess of 5 seconds;
the second determination condition includes:
all of the landing gear is in a stowed state; and is
The radio altitude of the aircraft is greater than 1000 feet; and is
The flaps of the aircraft are in landing approach attitude; and is
The current thrust of the aircraft engine is less than the takeoff thrust of the aircraft engine.
Through the first judgment condition and the second judgment condition, the information whether the aircraft needs to put down or retract the undercarriage can be effectively obtained, so that the undercarriage is retracted or put down according to the information, and the reliability of automatically retracting and releasing the undercarriage is guaranteed.
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 deploy the landing gear in response to the first determination condition or the second determination condition. By setting the first retraction mode, the undercarriage retraction system can retract and release the undercarriage in an automatic retraction and release mode if and only if the undercarriage retraction and release system is in the specific first retraction and release mode, so that a foundation is provided for increasing the retraction and release mode of the operating undercarriage.
In one or more embodiments, the first and second determination conditions 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 operating unit, in which the operating unit can instruct the execution unit to retract or put down the landing gear; the undercarriage control system further comprises an interaction unit, the undercarriage control system is in the first retraction mode by default, and the undercarriage control 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 undercarriage can be manually retracted 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 method for retracting and extending an undercarriage, which can improve the reliability of retracting and extending the undercarriage, comprising the steps of:
judging whether the airplane meets a first judgment condition, if so, retracting the undercarriage;
and judging whether the aircraft meets a second judgment condition, and if so, putting down the undercarriage.
In one or more embodiments, the first determination condition includes:
the full-wheel-borne signal of the airplane shows that the airplane is in an air state; and is
All of the landing gear is in a lowered state; and is
Not commanding lowering of the landing gear; and is
The radio altitude of the aircraft is greater than 100 feet; and is
The rate of climb of the aircraft is in excess of 10 feet per minute and the duration is in excess of 5 seconds;
the second determination condition includes:
the landing gear is in a stowed state; and is
The radio altitude of the aircraft is greater than 1000 feet; and is
The flaps of the aircraft are in landing approach attitude; and is
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 the undercarriage can be retracted or put down according to whether the aircraft meets the first judgment condition or the second judgment condition in the first retraction mode;
the first and second determination conditions 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 stow or lower the landing gear, the method further comprising:
switching to the second retraction mode;
operating the operating unit to stow or lower the landing gear.
The present application also provides a computer readable medium having stored thereon computer instructions which, when executed by a processor, carry out the steps of the landing gear retraction method according to any of the preceding claims.
The foregoing description is only an overview of the technical solutions of the present application, and the present application can be implemented according to the content of the description in order to make the technical means of the present application more clearly understood, and the following detailed description of the present application is given in order to make the above and other objects, features, and advantages of the present application more clearly understandable.
Drawings
Various additional 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. Moreover, like reference numerals are used to refer to like elements throughout. 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 other embodiments of the present application;
FIG. 3 is a schematic flow diagram of a method of retracting and extending landing gears according to some embodiments of the present application;
FIG. 4 is a flow chart illustrating a method of retracting and extending landing gears according to further embodiments of the present application.
Detailed Description
Embodiments of the present invention will be described in detail below with reference to the accompanying drawings. The following examples are merely used to more clearly illustrate the technical solutions of the present application, and therefore are only examples, and the protection scope of the present application is not limited thereby.
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 "including" and "having," and any variations thereof, in the description and claims of this application and the description of the above figures are intended to cover non-exclusive inclusions.
At present, the control of the undercarriage is realized by manually controlling an undercarriage system by a unit, the energy of the unit is consumed, and once the unit makes a mistake, adverse results are easy to occur.
After research, the applicant finds that the retraction and the release of the landing gear can be controlled through an automatic control system with reasonable design, so that adverse effects caused by manual operation errors are reduced.
In one aspect, according to some embodiments of the present application, a landing gear retraction system is provided, and referring to fig. 1, fig. 1 shows 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 actuating unit 2 is in driving connection with the undercarriage 3 for retracting or lowering the undercarriage 3. Wherein, in response to a first judgment condition, the control unit 1 instructs the execution unit 2 to retract the undercarriage 3; in response to the second judgment condition, the control unit 1 instructs the execution unit 2 to lower the undercarriage 3.
Reference herein to "an embodiment" means that a particular feature, structure, or characteristic described in connection with the embodiment can be included in at least one embodiment of the application. The appearances of the phrase 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. It is explicitly and implicitly understood by one skilled in the art that the embodiments described herein can be combined with other embodiments.
The execution unit 2 is used for driving/driving the landing gear 3 to retract or put down, and optionally, in some embodiments, the execution unit 2 includes a cylinder, a connecting rod, and the like, and the actuating of the cylinder can drive the connecting rod to communicate with the landing gear 3 in transmission connection with the connecting rod to follow up, so as to put down or put up the landing gear.
By the undercarriage control system, the adjustment of the retraction state of the undercarriage 3 can be realized according to the first judgment condition and the second judgment condition, so that adverse consequences caused by manual operation errors when the undercarriage is retracted and extended by manual operation can be reduced.
According to some embodiments of the application, the first determination condition comprises: the full-wheel-borne signal of the airplane shows that the airplane is in an air state; and the undercarriage 3 is in the lowered condition; and the control unit 1 does not instruct the execution unit 2 to lower the undercarriage 3; and the radio altitude of the aircraft is greater than 100 feet; and the rate of climb of the aircraft is in excess of 10 feet per minute and the duration is in excess of 5 seconds;
the second determination condition includes: the landing gear 3 is in a stowed condition; and the radio altitude of the aircraft is greater than 1000 feet; and the flaps of the aircraft are 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 an aircraft landing gear system, can be obtained according to a landing gear system wheel load sensor and is used for judging the air-ground state of the aircraft. After comprehensive judgment is carried out on the wheel load signals of the three undercarriages of the airplane, the full wheel load signals can be obtained, and whether the airplane is in the air or not can be obtained.
In order to determine whether the undercarriage 3 is in the down state or the retracted state, a sensor may be optionally provided on the undercarriage 3, and the position and attitude information of the undercarriage 3 may be determined according to a signal of the sensor. Alternatively, the position and attitude information of the undercarriage 3 may be obtained by an image acquisition unit such as a camera.
The radio altitude of the airplane and the climbing rate of the airplane are basic state information of the airplane in a flying state.
Whether the flap of the aircraft is in the landing approach attitude can be obtained according to the blocking position of the flap.
In the first judgment condition, the control unit 1 is additionally judged not to instruct the execution unit 2 to put down the undercarriage 3, so that the priority of the undercarriage 3 putting down instruction is higher than that of the undercarriage 3 retracting instruction, and the undercarriage 3 is prevented from being retracted by mistake due to system failure, and further accidents are caused.
Through the first judgment condition and the second judgment condition, the information whether the aircraft needs to put down or retract the undercarriage can be effectively obtained, so that the undercarriage is retracted or put down according to the information, and the reliability of automatically retracting and releasing the undercarriage is guaranteed.
According to some embodiments of the present application, the landing gear retraction system comprises a first retraction mode in which the control unit 1 can instruct the execution unit 2 to retract or put down the landing gear 3 in response to a first or second determination condition.
By setting the first retraction mode, the undercarriage retraction system can retract and retract the undercarriage 3 in an automatic retraction mode if and only if the undercarriage retraction system is in the specific first retraction mode, so that a foundation is provided for increasing the retraction mode of operating the undercarriage.
Optionally, in some embodiments, the undercarriage retracting system only retracts the undercarriage 3 in an automatic retracting manner, and at this time, the first retracting mode does not need to be additionally set.
Further, on the basis of the foregoing embodiment, the first and second determination conditions 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 can the control unit 1 be caused to retract or to put down the landing gear 3 according to the first and second determination conditions.
According to some embodiments of the present application, please refer 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 comprising a second retraction mode, the landing gear retraction system further comprising an operating unit 4, in which the operating unit 4 can instruct the execution unit 2 to retract or put down the landing gear 3; the undercarriage control system further comprises an interaction unit 5, the undercarriage control system is in a first control mode by default, and the undercarriage control system can be switched to a second control mode through the interaction unit 5.
In the description of the embodiments of the present application, the technical terms "first", "second", and the like are used only for distinguishing different objects, and are not to be construed as indicating or implying relative importance or implicitly indicating the number, specific order, or primary-secondary relationship of the technical features indicated.
The operating unit 4 is optionally a lever, by means of which the position or the actuation position of the actuating unit 2 can be manually controlled, so that the undercarriage 3 is retracted or lowered.
The interaction unit 5 is optionally a screen panel, the screen panel has an interactive interface, the retractable mode can be switched by touching a corresponding key in the interface, and optionally, the screen panel has information for indicating the landing gear state.
When the automatic retraction mode fails or the manual mode is actively activated, the undercarriage can be manually retracted by switching to the second retraction mode, so that the safety of the retraction system is improved.
In another aspect, a method of retracting and extending landing gear is provided according to some embodiments of the present application, and referring to fig. 3, fig. 3 is a schematic flow chart of a method of retracting and extending landing gear according to some embodiments of the present application; the undercarriage retraction and extension method comprises the following steps:
s101: judging whether the airplane meets a first judgment condition, if so, executing a step S102: retracting the undercarriage;
s103: judging whether the aircraft meets a second judgment condition, if so, executing the step S104: and (5) lowering the landing gear.
Step S101 and step S102 may be performed synchronously, that is, it is determined whether the aircraft satisfies the first determination condition or whether the aircraft satisfies the second determination condition, and if the conditions are satisfied, step S102 or step S104 is executed. If the condition is not satisfied, the judgment is continued.
According to some embodiments of the present application, the first determination condition includes: the full-wheel-borne signal of the airplane shows that the airplane is in an air state; and the undercarriage 3 is in the lowered condition; and the control unit 1 does not instruct the execution unit 2 to lower the undercarriage 3; and the radio altitude of the aircraft is greater than 100 feet; and the rate of climb of the aircraft is in excess of 10 feet per minute and the duration is in excess of 5 seconds; the second determination condition includes: the landing gear 3 is in a stowed condition; and the radio altitude of the aircraft is greater than 1000 feet; and the flaps of the aircraft are 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 judgment condition or the second judgment condition need to be all satisfied, so that the judgment result in step S101 or S103 is yes.
According to some embodiments of the present application, the landing gear retraction method further comprises: a first retraction mode is configured, and the undercarriage 3 can be retracted or put down according to whether the aircraft meets the first judgment condition or the second judgment condition in the first retraction mode;
the first and second determination conditions further include: the landing gear retraction system is in a first retraction mode.
Referring to fig. 4, according to some embodiments of the present application, fig. 4 is a schematic flow chart of a method of retracting a landing gear according to other embodiments of the present application; the landing gear retracting method further comprises the following steps:
configuring a second retraction mode in which the operating unit is operable to retract or put down 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 put down the landing gear.
According to the undercarriage retracting method described in the foregoing one or more embodiments, the undercarriage retracting system described in the foregoing one or more embodiments may be used to implement the undercarriage retracting method, and details are not repeated herein.
The present disclosure provides the above-mentioned computer-readable storage medium having stored thereon computer instructions. When the computer instruction is executed by the processor, the undercarriage folding and unfolding method provided by any one of the embodiments can be implemented, so that the undercarriage can be automatically folded and unfolded, and the reliability of folding and unfolding of the undercarriage 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 (disc), as used herein, includes Compact Disc (CD), laser disc, optical disc, Digital Versatile Disc (DVD), floppy disk and blu-ray disc where disks (disks) usually reproduce data magnetically, while discs (discs) 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 otherwise explicitly stated or limited, the terms "mounted," "connected," "fixed," and the like are used in a broad sense, and for example, may be fixedly connected, detachably connected, or integrated; mechanical connection or electrical connection is also possible; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meanings of the above terms in the embodiments of the present application can be understood by those of ordinary skill in the art according to specific situations.
Finally, it should be noted that: the above embodiments are only used for illustrating the technical solutions of the present application, and not for limiting the same; although the present application has been described in detail with reference to the foregoing embodiments, it should be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; such modifications and substitutions do not depart from the spirit and scope of the present disclosure, and the present disclosure should be construed as being covered by the claims and the specification. In particular, the technical features mentioned in the embodiments can be combined in any way as long as there is no structural conflict. The present application is not intended to be limited to the particular embodiments disclosed herein but is to cover all embodiments that may fall within the scope of the appended claims.
Claims (10)
1. A landing gear retraction system, comprising:
a control unit; and
the execution unit is in transmission connection with the undercarriage and is used for retracting or putting down the undercarriage;
wherein, in response to a first determination condition, the control unit instructs the execution unit to stow the landing gear; in response to a second determination condition, the control unit instructs the execution unit to lower the landing gear.
2. The landing gear retraction system according to claim 1,
the first judgment condition includes:
the full-wheel-borne signal of the airplane shows that the airplane is in an air state; and is
All of the landing gear is in a lowered state; and is
The control unit does not instruct the execution unit to lower the landing gear; and is
The radio altitude of the aircraft is greater than 100 feet; and is
The rate of climb of the aircraft is in excess of 10 feet per minute and the duration is in excess of 5 seconds;
the second determination condition includes:
the landing gear is in a stowed state; and is
The radio altitude of the aircraft is greater than 1000 feet; and is
The flaps of the aircraft are in landing approach attitude; and is
The current thrust of the aircraft engine is less than the takeoff thrust of the aircraft engine.
3. 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 actuation unit to retract or lower the landing gear in response to either the first or second determining conditions.
4. The landing gear retraction system according to claim 3, wherein said first and second determining conditions each further comprise:
the landing gear retraction system is in the first retraction mode.
5. A landing gear retraction system according to claim 3, wherein the landing gear retraction system includes a second retraction mode, the landing gear retraction system further including an operating unit, in which the operating unit can be used to instruct the actuator unit to retract or extend the landing gear;
the undercarriage control system further comprises an interaction unit, the undercarriage control system is in the first retraction mode by default, and the undercarriage control system can be switched to the second retraction mode through the interaction unit.
6. A method of deploying and retracting a landing gear, comprising the steps of:
judging whether the airplane meets a first judgment condition, if so, retracting the undercarriage;
and judging whether the aircraft meets a second judgment condition, and if so, putting down the undercarriage.
7. A method of retracting and releasing a landing gear according to claim 6,
the first judgment condition includes:
the full-wheel-borne signal of the airplane shows that the airplane is in an air state; and is
All of the landing gear is in a lowered state; and is
Not commanding lowering of the landing gear; and is
The radio altitude of the aircraft is greater than 100 feet; and is
The rate of climb of the aircraft is in excess of 10 feet per minute and the duration is in excess of 5 seconds;
the second determination condition includes:
the landing gear is in a stowed state; and is
The radio altitude of the aircraft is greater than 1000 feet; and is
The flaps of the aircraft are in landing approach attitude; and is
The current thrust of the aircraft engine is less than the takeoff thrust of the aircraft engine.
8. The landing gear stowing and releasing method according to claim 6, further comprising:
configuring a first retraction mode, wherein the undercarriage can be retracted or put down according to whether the aircraft meets the first judgment condition or the second judgment condition in the first retraction mode;
the first and second determination conditions further include:
the landing gear retraction system is in the first retraction mode.
9. The landing gear stowing and releasing method according to claim 8, further comprising:
configuring a second retraction mode in which the operating unit is operable to stow or lower the landing gear, the method further comprising:
switching to the second retraction mode;
operating the operating unit to stow or lower the landing gear.
10. A computer readable medium having stored thereon computer instructions which, when executed by a processor, carry out the steps of the landing gear retraction method according to any of claims 6 to 8.
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| CN202210078301.0A CN114313230B (en) | 2022-01-24 | 2022-01-24 | Landing gear retraction system and method, and computer readable medium |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116176832A (en) * | 2023-05-04 | 2023-05-30 | 成都凯天电子股份有限公司 | Method for controlling retraction, extension and extension based on complex undercarriage configuration |
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| CN114313230B (en) | 2024-06-14 |
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