Folded wingtip alerting method, apparatus, device, and storage medium

Abstract

The application provides a folding wing tip warning method, device, equipment and storage medium, relates to the field of avionics technology, and is used for warning the abnormal state of the folding wing tip. The method mainly comprises the following steps: acquiring the current state of the folding wing tip, wherein the current state is a retracted state or an unfolded state; if it is determined that the current state is the retracted state, acquiring unfolding process information of the wing tip of the airplane, and warning the fault according to the unfolding process information; and if it is determined that the current state is the unfolded state, acquiring retraction process information of the wing tip of the airplane, and warning the fault according to the retraction process information.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of avionics, in particular to a folding wing tip warning method, device, equipment and storage medium. BACKGROUND

[0002] The folding wing technology is first applied to military aircraft. With the increasing demand for range and economy of civil aircraft, Boeing first brought this technology to the civil passenger aircraft 777X. This technology brings greater aspect ratio and wingspan to the aircraft, and solves the problems of long and thin wing design and manufacturing difficulty and runway operation caused by long wings. The aircraft using folding wing technology can meet the take-off and landing requirements of E-class airports, and the large wing can improve the lift-drag ratio, greatly improve the aerodynamic efficiency and reduce the operating cost of the aircraft.

[0003] Boeing adopts foldable wing tip design on 777X. Before take-off, the wing tip is lowered and locked, and the folding section and the fixed section form a complete large aspect ratio wing. From take-off to take-off to cruising to landing, the wing remains in this state. After landing, when the speed is lower than a certain threshold during deceleration on the runway, the wing tip is automatically folded to facilitate airport operation.

[0004] However, the folding wing state indication on the EICAS of Boeing 777X has three states under normal working conditions, namely, retracted, process state, and unfolded. However, there is no warning indication for abnormal state of the folding wing, and there is no corresponding Crew Alerting System (CAS) warning information. SUMMARY

[0005] The embodiments of the present application provide a folding wing tip warning method, device, computer equipment and storage medium, which are used to realize warning of abnormal state of the folding wing tip.

[0006] The folding wing tip warning method provided by the embodiments of the present application comprises the following steps:

[0007] Obtain the current state of the folding wing tip, wherein the current state is a retracted state or an unfolded state;

[0008] If it is determined that the current state is the retracted state, obtain the unfolding process information of the wing tip of the aircraft, and perform warning according to the unfolding process information of the fault occurred;

[0009] If it is determined that the current state is the unfolded state, obtain the retraction process information of the wing tip of the aircraft, and perform warning according to the retraction process information of the fault occurred.

[0010] The folding wing tip warning device provided by the embodiments of the present application comprises the following steps:

[0011] acquire a current state of the folding wing tip, the current state being a stowed state or a deployed state;

[0012] an alarm module, configured to acquire deployment process information of the folding wing tip of the airplane if the current state is the stowed state, and alarm a fault occurring according to the deployment process information;

[0013] an alarm module, configured to acquire stowing process information of the folding wing tip of the airplane if the current state is the deployed state, and alarm a fault occurring according to the stowing process information.

[0014] A computer program product, comprising a computer program, which, when executed by a processor, implements the folding wing tip alarm method.

[0015] The present application provides a folding wing tip alarm method, device, computer equipment and storage medium, acquire a current state of the folding wing tip, the current state being a stowed state or a deployed state, if it is determined that the current state is the stowed state, acquire the deployment process information of the folding wing tip of the airplane, and alarm a fault occurring according to the deployment process information, if it is determined that the current state is the deployed state, acquire the stowing process information of the folding wing tip of the airplane, and alarm a fault occurring according to the stowing process information. The present application is based on the analysis of the operation scene of the folding wing civil airplane, according to the analysis of the fault type of the folding wing tip in the operation scene and the alarm, so that the abnormal state of the folding wing tip can be alarmed through the present application. BRIEF DESCRIPTION OF DRAWINGS

[0016] Figure 1 A folding wing tip alarm method flow chart is provided for the present application;

[0017] Figure 2 An airplane departure scene folding wing tip alarm flow chart is provided for the present application;

[0018] Figure 3 An airplane arrival scene folding wing tip alarm flow chart is provided for the present application;

[0019] Figure 4 A structure schematic diagram of the folding wing tip alarm device provided for the present application;

[0020] Figure 5 A schematic diagram of the computer equipment provided for the present application. DETAILED DESCRIPTION

[0021] For better understanding of the above technical solutions, the technical solutions of the embodiments of the present application are described in detail below through the drawings and specific embodiments. It should be understood that the specific features in the embodiments of the present application and the embodiments are detailed descriptions of the technical solutions of the embodiments of the present application, and are not limitations of the technical solutions of the present application. In the case of no conflict, the technical features in the embodiments of the present application and the embodiments can be combined with each other.

[0022] Please refer to Figure 1 A folding wing tip warning method is provided for the embodiments of the present application, which specifically includes steps S1-S3:

[0023] Step s1, the current state of the folding wing tip is obtained, which is a stowed state or a deployed state.

[0024] Step s2, if it is determined that the current state is the stowed state, the deployment process information of the aircraft wing tip is obtained, and the occurring failure is warned according to the deployment process information.

[0025] Specifically, when the current state of the folding wing tip is the stowed state, the flowchart shown in Figure 2 is executed. That is, the warning of the occurring failure according to the deployment process information includes:

[0026] Step s21, if the folding wing tip is in the stowed state, it is confirmed whether the pilot controls the wing tip to deploy.

[0027] Step s22, if the pilot does not control the wing tip to deploy, the aircraft is warned according to whether it enters the runway.

[0028] Among them, the warning according to whether the aircraft enters the runway includes: if the aircraft enters the runway, outputting the CAS warning information that the aircraft enters the runway but the wing tip is not deployed; if the aircraft does not enter the runway, jumping to step s21 to confirm whether the pilot controls the wing tip to deploy and continuing to execute.

[0029] Step s23, if the pilot controls the wing tip to deploy, it is determined whether the aircraft wing tip has a failure.

[0030] Step s24, if the aircraft wing tip has a failure, outputting the wing tip image warning information and the wing tip state civil aircraft crew warning system CAS alert information, the wing tip image warning information being used to indicate the position of the wing tip with a failure.

[0031] Specifically as Figure 2As shown, if the aircraft wing tip does not fail, if it is determined that the left wing tip is stuck and the right wing tip is normal, the output wing tip image warning information is that the left wing tip image warning information becomes amber X, and the right side is dynamically displayed; if the right wing tip is stuck and the left wing tip is normal, the output wing tip image warning information is that the right wing tip becomes amber X, and the left side is dynamically displayed; if the left and right wing tips are stuck, the output wing tip warning image is that the left and right wing tips become amber X.

[0032] The wing tip image warning information in the present application fully follows the design style of the civil aircraft EICAS fault flag graphic symbol, and the folding wing graphic symbol warning scheme is designed according to the fault type, as shown in Table 1.

[0033] Table 1

[0034]

[0035]

[0036] The CAS warning indication designed according to the civil aircraft crew alarm system (CAS) window interaction design specification in the present application has five kinds, which are CONFIG WINGTIPS, WINGTIPS DRIVE, CHKL INCOMPLETE NORM, WINGTIPS DRIVE, and WINGTIPS SYS, and the CAS information warning scheme is shown in Table 2. Among them, the wing tip state civil aircraft crew alarm system CAS warning information in the present embodiment is WINGTIPS DRIVE in Table 2.

[0037] Table 2

[0038]

[0039] Step s25, if the aircraft wing tip does not fail and the wing tip is in the unfolded state, it is determined whether the pilot opens the check sheet to check the wing tip state.

[0040] Step s26, if the pilot does not open the check sheet to check the wing tip state, the CAS warning information that the pilot does not open the check sheet according to the procedure to confirm the folding wing tip state is output.

[0041] In the present embodiment, if the pilot opens the check sheet to check the wing tip state, the process ends.

[0042] Step s3, if it is determined that the current state is the unfolded state, the folding process information of the aircraft wing tip is obtained, and the fault occurring is warned according to the folding process information.

[0043] Specifically, when the current state of the folding wing tip is the unfolded state, the folding process information of the aircraft wing tip is obtained according to the folding process information of the aircraft wing tip, and the fault occurring is warned according to the folding process information. Figure 3The flowchart shown is executed. That is, in the step of warning about the occurrence of a failure according to the stowing process information, the following steps are included:

[0044] In step s31, if the folding wing tip is in the unfolded state, it is determined whether the system has received a stowing failure signal.

[0045] In step s32, if the system has received a stowing failure signal, wing tip image warning information and CAS prompt information that the folding wing system detected a failure before landing and the folding wing tip cannot be stowed are output.

[0046] In step s33, if the system has not received a stowing failure signal, it is determined whether a determination condition for automatic stowing of the wing tip is reached.

[0047] Specifically, the determination condition can be that the automatic folding control panel is in an AUTO state, the aircraft is on the ground, and the ground speed is less than 50 knots.

[0048] In step s34, if the determination condition for automatic stowing of the wing tip is not reached, it is determined whether the pilot has implemented manual control to stow the wing tip.

[0049] In step s35, if the pilot has not implemented manual control to stow the wing tip, wing tip image warning information and CAS alert information that the automatic folding control panel is in an automatic state and the folding wing tip meets the automatic folding condition but the folding wing cannot be automatically stowed are output.

[0050] In step s36, if the determination condition for automatic stowing of the wing tip is reached or the pilot has implemented manual control to stow the wing tip, it is determined whether a failure occurs in the aircraft wing tip according to the stowing process information.

[0051] In step s37, if a failure occurs in the aircraft wing tip, wing tip image warning information and wing tip state CAS alert information are output, and the wing tip image warning information is used to indicate the position of the wing tip with a failure.

[0052] If a failure does not occur in the aircraft wing tip, if it is determined whether the left wing tip is stuck and the right wing tip is normal, the wing tip image warning information output specifically is that the left wing tip image warning information becomes amber X and the right wing tip is dynamically displayed; if the right wing tip is stuck and the left wing tip is normal, the wing tip image warning information output specifically is that the right wing tip becomes amber X and the left wing tip is dynamically displayed; and if both the left and right wing tips are stuck, the wing tip warning image output specifically is that both the left and right wing tips become amber X.

[0053] In this embodiment, if a failure does not occur in the aircraft wing tip, it is determined that the folding wing tip is in a stowed state.

[0054] It should be noted that the alarm logic involved in this application all occurs in the operational scenarios of folding-wing aircraft entering and leaving the airport, and the types of faults involved include, but are limited to, the following 10 types: left wingtip deployment jam, right wingtip deployment jam, both wingtip deployment jam, pilot not opening the checklist to confirm the folding wingtip status according to procedure, aircraft entering the runway but wingtips not deployed, left wingtip retracted jam, right wingtip retracted jam, both wingtips retracted jam, folding wingtips failing to retract automatically according to the predetermined logic, and a certain fault detected before landing causing the folding wingtips to fail to retract.

[0055] This invention provides a method for alarming folding wingtips. The method acquires the current state of the folding wingtips, which can be either retracted or deployed. If the current state is determined to be retracted, the method acquires deployment process information of the aircraft wingtips and issues an alarm for any malfunctions based on this information. If the current state is determined to be deployed, the method acquires retraction process information of the aircraft wingtips and issues an alarm for any malfunctions based on this information. This invention is based on an analysis of the operating scenarios of folding-wing civil aircraft, analyzing and issuing alarms based on the possible types of malfunctions that may occur with the folding wingtips in these scenarios. Therefore, this invention can achieve alarming for abnormal states of the folding wingtips.

[0056] It should be understood that the sequence number of each step in the above embodiments does not imply the order of execution. The execution order of each process should be determined by its function and internal logic, and should not constitute any limitation on the implementation process of the embodiments of the present invention.

[0057] In one embodiment, a folding wingtip alarm device is provided, which corresponds one-to-one with the folding wingtip alarm method described in the above embodiments. For example... Figure 4 As shown, the functional modules of the folding wingtip alarm device are described in detail below:

[0058] The acquisition module 41 is used to acquire the current state of the folding wingtip, which is either a retracted state or an unfolded state.

[0059] The alarm module 42 is used to obtain the deployment process information of the aircraft wingtip if the current state is the retracted state, and to issue an alarm for the fault that occurs based on the deployment process information.

[0060] The alarm module 42 is used to obtain the wingtip retraction process information of the aircraft if the current state is the deployed state, and to issue an alarm for any faults that occur based on the retraction process information.

[0061] In an optional embodiment provided by the present invention, the alarm module 42 is specifically used for:

[0062] Determine whether there is a malfunction at the wingtip of the aircraft based on the deployment process information;

[0063] if the wing tip of the airplane fails, outputting a wing tip image warning information and a wing tip state CAS alert information, the wing tip image warning information being used for indicating the position of the failed wing tip;

[0064] if the wing tip of the airplane does not fail, confirming whether the pilot opens a check list to check the wing tip state;

[0065] if the pilot does not open the check list to check the wing tip state, outputting a CAS alert information that the pilot does not open the check list to confirm the folded wing tip state according to the procedure.

[0066] In an optional embodiment provided by the present application, the warning module 42 is specifically used for:

[0067] confirming whether the pilot controls the wing tip to be unfolded;

[0068] if the pilot does not control the wing tip to be unfolded, warning according to whether the airplane enters a runway;

[0069] if the pilot controls the wing tip to be unfolded, acquiring unfolding process information of the wing tip of the airplane, and warning according to the unfolding process information.

[0070] In an optional embodiment provided by the present application, the warning module 42 is specifically used for:

[0071] if the airplane enters the runway, outputting a CAS warning information that the airplane enters the runway but the wing tip is not unfolded;

[0072] if the airplane does not enter the runway, jumping to step of confirming whether the pilot controls the wing tip to be unfolded and continuing to execute.

[0073] In an optional embodiment provided by the present application, the warning module 42 is specifically used for:

[0074] determining whether the wing tip of the airplane fails according to the folding process information;

[0075] if the wing tip of the airplane fails, outputting a wing tip image warning information and a wing tip state CAS alert information, the wing tip image warning information being used for indicating the position of the failed wing tip;

[0076] if the wing tip of the airplane does not fail, determining that the folded wing tip is in a folding state.

[0077] In an optional embodiment provided by the present application, the warning module 42 is specifically used for:

[0078] determining whether the system receives a folding failure signal;

[0079] If the system receives the signal that the wing tip cannot be retracted, the wing tip image warning information and the CAS prompt information that the folding wing system detects some failure before landing to cause the folding wing tip to be unable to be retracted are outputted.

[0080] If the system does not receive the signal that the wing tip cannot be retracted, the wing tip is automatically retracted according to whether the determination condition is reached.

[0081] In an optional embodiment provided by the present application, the warning module 42 is specifically used for:

[0082] If the wing tip is not automatically retracted according to the determination condition, it is determined whether the pilot realizes manual control to retract the wing tip.

[0083] If the pilot cannot realize manual control to retract the wing tip, the wing tip image warning information and the CAS standby information that the automatic folding control panel is in an automatic state, the folding wing tip meets the automatic folding condition, but the folding wing fails to be automatically retracted are outputted.

[0084] If the wing tip is automatically retracted according to the determination condition or the pilot realizes manual control to retract the wing tip, the step of determining whether the aircraft wing tip fails according to the retraction process information is continued to be executed.

[0085] The specific limitation of the folding wing tip warning device can refer to the limitation of the folding wing tip warning method in the above, which will not be described here. Each module in the above device can be realized by software, hardware and a combination thereof in whole or in part. Each module can be embedded in or independent of the processor in the computer device in the form of hardware, or can be stored in the memory in the computer device in the form of software, so as to be called and executed by the processor to execute the operation corresponding to each module.

[0086] In an embodiment, a computer device is provided, which can be a server, and an internal structure diagram thereof can be as shown in Figure 5 The computer device includes a processor, a memory, a network interface and a database connected through a system bus. The processor of the computer device is used to provide computing and control capabilities. The memory of the computer device includes a non-volatile storage medium and an internal memory. The non-volatile storage medium stores an operating system, a computer program and a database. The internal memory provides an environment for the operating system and the computer program in the non-volatile storage medium to run. The network interface of the computer device is used to communicate with an external terminal through a network connection. The computer program is executed by the processor to implement a folding wing tip warning method.

[0087] In an embodiment, a computer device is provided, which includes a memory, a processor and a computer program stored in the memory and executable on the processor, and the processor implements the following steps when executing the computer program:

[0088] obtaining a current state of the folding wingtip, the current state being a stowed state or a deployed state;

[0089] if it is determined that the current state is the stowed state, obtaining deployment process information of the wingtip of the aircraft, and warning of a fault occurring according to the deployment process information;

[0090] if it is determined that the current state is the deployed state, obtaining stowing process information of the wingtip of the aircraft, and warning of a fault occurring according to the stowing process information.

[0091] In one embodiment, a computer readable storage medium is provided, having stored thereon a computer program, the computer program being executed by a processor to implement the following steps:

[0092] obtaining a current state of the folding wingtip, the current state being a stowed state or a deployed state;

[0093] if it is determined that the current state is the stowed state, obtaining deployment process information of the wingtip of the aircraft, and warning of a fault occurring according to the deployment process information;

[0094] if it is determined that the current state is the deployed state, obtaining stowing process information of the wingtip of the aircraft, and warning of a fault occurring according to the stowing process information.

[0095] In one embodiment, a computer program product is provided, the computer program product comprising a computer program, the computer program being executed by a processor to implement the following steps:

[0096] obtaining a current state of the folding wingtip, the current state being a stowed state or a deployed state;

[0097] if it is determined that the current state is the stowed state, obtaining deployment process information of the wingtip of the aircraft, and warning of a fault occurring according to the deployment process information;

[0098] if it is determined that the current state is the deployed state, obtaining stowing process information of the wingtip of the aircraft, and warning of a fault occurring according to the stowing process information.

[0099] Those skilled in the art can understand that all or part of the processes in the above-mentioned embodiment methods can be completed by instructing the relevant hardware through a computer program. The computer program can be stored in a non-volatile computer readable storage medium, and when executed, can include the processes of the above-mentioned embodiment methods. Any reference to memory, storage, database or other medium used in the embodiments provided by the present application can include non-volatile and / or volatile memory. Non-volatile memory can include read-only memory (ROM), programmable ROM (PROM), electrically programmable ROM (EPROM), electrically erasable programmable ROM (EEPROM) or flash memory. Volatile memory can include random access memory (RAM) or external cache memory. As an illustration but not limitation, RAM is available in various forms, such as static RAM (SRAM), dynamic RAM (DRAM), synchronous DRAM (SDRAM), double data rate SDRAM (DDR SDRAM), enhanced SDRAM (ESDRAM), synchronous link (Synchlink) DRAM (SLDRAM), memory bus (Rambus) direct RAM (RDRAM), direct memory bus dynamic RAM (DRDRAM), and memory bus dynamic RAM (RDRAM), etc.

[0100] Those skilled in the art can clearly understand that, for the convenience and brevity of description, only the division of the above-mentioned functional units and modules is exemplified, and in actual application, the above-mentioned functions can be completed by different functional units and modules according to needs, that is, the internal structure of the device is divided into different functional units or modules to complete all or part of the functions described above.

[0101] The above embodiments are only used to illustrate the technical solutions of the present application, but not limit it. Although the present application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that they can modify the technical solutions recorded in the foregoing embodiments, or make equivalent replacement for part of the technical features. The modification or replacement does not make the essence of the corresponding technical solution deviate from the spirit and scope of the technical solutions of the embodiments of the present application, and should be included in the protection scope of the present application.

Claims

1. A folded wingtip warning method, characterized by, The method comprises: acquiring a current state of the folding wing tip, the current state being a stowed state or an unfolded state; if it is determined that the current state is the stowed state, acquiring unfolding process information of the aircraft wing tip, and alarming a fault occurring according to the unfolding process information; if it is determined that the current state is the unfolded state, acquiring a stowing process information of the aircraft wing tip, and alarming a fault occurring according to the stowing process information; wherein the alarming occurs in the operation scene of the folding wing aircraft entering and leaving the runway, and the fault types involved include but are not limited to the following 10 types: left wing tip unfolding jam, right wing tip unfolding jam, both wing tips unfolding jam, pilot not opening the checklist to confirm the folding wing tip state according to the procedure, the aircraft entering the runway but the wing tip not unfolded, left wing tip stowing jam, right wing tip stowing jam, both wing tips stowing jam, the folding wing tip failing to be automatically stowed according to the predetermined logic, and the folding wing tip failing to be stowed due to a certain fault detected before landing.

2. The method of claim 1, wherein, The alarming of the fault occurring according to the unfolding process information comprises: determining whether the aircraft wing tip has a fault according to the unfolding process information; if the aircraft wing tip has a fault, outputting wing tip image alarm information and wing tip state CAS alert information, the wing tip image alarm information being used to indicate the position of the wing tip having the fault; if the aircraft wing tip has no fault, confirming whether the pilot opens the checklist to check the wing tip state; if the pilot does not open the checklist to check the wing tip state, outputting CAS alert information that the pilot does not open the checklist to confirm the folding wing tip state according to the procedure.

3. The method of claim 2, wherein, Before the acquiring of the unfolding process information of the aircraft wing tip and the alarming of the fault occurring according to the unfolding process information, the method further comprises: confirming whether the pilot controls the unfolding of the wing tip; if the pilot does not control the unfolding of the wing tip, alarming according to whether the aircraft enters the runway; The acquiring of the unfolding process information of the aircraft wing tip and the alarming of the fault occurring according to the unfolding process information comprise: if the pilot controls the unfolding of the wing tip, acquiring the unfolding process information of the aircraft wing tip and alarming the fault occurring according to the unfolding process information.

4. The method of claim 3, wherein, The alarming according to whether the aircraft enters the runway comprises: if the aircraft enters the runway, outputting CAS warning information that the aircraft enters the runway but the wing tip is not unfolded; if the aircraft does not enter the runway, jumping to the step of confirming whether the pilot controls the unfolding of the wing tip for continuous execution.

5. The method of claim 1, wherein, The alarming of the fault occurring according to the stowing process information comprises: determining whether the aircraft wing tip has a fault according to the stowing process information; if the aircraft wing tip has a fault, outputting wing tip image alarm information and wing tip state CAS alert information, the wing tip image alarm information being used to indicate the position of the wing tip having the fault; if the aircraft wing tip has no fault, determining that the folding wing tip is in the stowed state.

6. The method of claim 5, wherein, Before the determining of whether the aircraft wing tip has a fault according to the stowing process information, the method further comprises: determining whether the system receives a stowing failure signal; If the system receives the signal that the wingtip cannot be retracted, the wingtip image warning information and CAS prompt information that the folding wing system detects some failure before landing to cause the folding wingtip to be unable to be retracted are outputted. If the system does not receive the signal that the wingtip cannot be retracted, the wingtip automatic retraction is performed according to whether the determination condition is reached.

7. The method of claim 6, wherein, The wingtip automatic retraction according to whether the determination condition is reached includes: If the wingtip automatic retraction is not reached, it is determined whether the pilot realizes manual control retraction of the wingtip. If the pilot cannot realize manual control retraction of the wingtip, the wingtip image warning information and CAS alert information that the automatic folding control panel is in an automatic state, the folding wingtip meets the automatic folding condition, but the folding wing fails to be automatically retracted are outputted. If the wingtip automatic retraction is reached or the pilot realizes manual control retraction of the wingtip, the step of determining whether the aircraft wingtip fails according to the retraction process information is continued.

8. A folding wingtip warning device, characterized in that The device includes: An acquisition module is configured to acquire a current state of the folding wingtip, the current state being a retracted state or an unfolded state. An alarm module is configured to, if the current state is the retracted state, acquire unfolding process information of the aircraft wingtip, and alarm a failure according to the unfolding process information. An alarm module is configured to, if the current state is the unfolded state, acquire retraction process information of the aircraft wingtip, and alarm a failure according to the retraction process information. The alarms occur in the operation scenarios of the folding wing aircraft entering and leaving the field, and the failure types include but are not limited to the following 10 types: left wingtip unfolding jamming, right wingtip unfolding jamming, both wingtips unfolding jamming, the pilot not opening the check sheet to confirm the folding wingtip state according to the procedure, the aircraft entering the runway but the wingtip not unfolding, left wingtip retraction jamming, right wingtip retraction jamming, both wingtips retraction jamming, the folding wingtip failing to be automatically retracted according to the predetermined logic, and detecting some failure before landing to cause the folding wingtip to be unable to be retracted.

9. A computer device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, characterized in that, The processor executes the computer program to realize the folding wingtip alarm method in any one of claims 1 to 7.

10. A computer-readable storage medium storing a computer program, the computer program comprising instructions that, when executed by a computer, cause the computer to perform the method of any one of claims 1 to 9. The computer program is executed by the processor to realize the folding wingtip alarm method in any one of claims 1 to 7.

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