Aircraft structure load monitoring method

Abstract

The invention discloses an aircraft structure load monitoring method. The method comprises the following steps: S1, polishing a bonding surface on the surface of a refitted key structure of an aircraft fuselage; s2, bonding a strain sensor on the bonding surface; s3, a strain / stress monitoring device is installed in a luggage compartment of the airplane; and S4, an optical fiber lead and a power supply and signal line are laid, the optical fiber lead is connected between the strain sensor and the strain / stress monitoring device and used for transmitting strain and stress data of the surface of the refitted key structure in real time, and the power supply and signal line is used for providing a power source for the strain / stress monitoring device and conducting communication. According to the invention, the stress data of the refitted key part of the aircraft fuselage can be accurately collected in real time, and long-term tracking analysis and maintenance decision are facilitated.

Description

Technical Field

[0001] This invention relates to a method for monitoring the structural load of an aircraft. Background Technology

[0002] With the rapid development of China's aviation manufacturing industry, the localization of foreign civil aircraft has gradually become a trend. However, despite rigorous verification and approval processes, the lack of original aircraft design and manufacturing data makes it impossible to accurately calculate the stress level of the modified aircraft structure, posing a potential risk to its safe operation. To ensure the structural safety of the modified aircraft, it is necessary to collect and monitor the stress levels of key modified components in real time for structural health testing and fatigue life assessment. Traditional methods for aircraft structural health testing mainly rely on periodic manual inspections, which suffer from low efficiency, high cost, and poor real-time performance, making it difficult to meet the safety and economic requirements of modern civil aircraft. Summary of the Invention

[0003] The purpose of this invention is to provide a method for monitoring the structural load of an aircraft, which can collect stress data of key parts of the aircraft fuselage in real time and accurately, facilitating long-term tracking analysis and maintenance decisions.

[0004] The technical solution adopted in this invention is as follows:

[0005] A method for monitoring aircraft structural loads includes the following steps:

[0006] S1. Grind the bonding surfaces on the key structural surfaces of the aircraft fuselage during modification;

[0007] S2. Adhere the strain sensor to the bonding surface;

[0008] S3. Install strain / stress monitoring equipment in the aircraft's baggage compartment;

[0009] S4. Lay optical fiber leads, power supply and signal lines. The optical fiber leads are connected between the strain sensor and the strain / stress monitoring device for real-time transmission of strain and stress data on the modified key structural surface. The power supply and signal lines are used to provide power to the strain / stress monitoring device and for communication.

[0010] This invention involves installing strain sensors in key areas of the aircraft fuselage during modification. The collected data is transmitted to strain / stress monitoring equipment installed in the aircraft's baggage compartment for processing and storage. This provides data support for the safe operation of the aircraft and can be widely applied to the domestic modification and routine maintenance of aircraft.

[0011] The present invention also has the following preferred designs:

[0012] The luggage compartment of the present invention is equipped with a base plate, and a mounting bracket is provided on the base plate, on which the strain / stress monitoring device is fixedly mounted.

[0013] The strain / stress monitoring device is grounded via a grounding wire, which is connected to an aircraft grounding post installed on the aircraft fuselage.

[0014] As a feasible implementation, the optical fiber lead and the power supply and signal lines of the present invention enter the interior of the luggage compartment through the cable entry port on the luggage compartment, and the optical fiber lead and the power supply and signal lines are fitted with cable conduits.

[0015] As a feasible implementation, the bottom plate of the luggage compartment of the present invention is further provided with an optical fiber flange and a relay bracket. The optical fiber flange and the relay bracket are used to guide and fix the optical fiber lead and fix the relay. The relay is connected to the power supply line of the strain / stress device. The bottom plate of the luggage compartment is also provided with a protective baffle, which is located outside the optical fiber flange and the relay bracket.

[0016] As a feasible implementation method, the strain / strain monitoring device of the present invention remotely transmits and stores the strain and stress data monitored by the strain sensor in the cloud through the power supply and signal lines, which facilitates remote data analysis.

[0017] The present invention has the following beneficial effects:

[0018] 1. This invention can collect data in real time and accurately, facilitating long-term tracking, analysis, and maintenance decisions. It provides data support for the safe operation of aircraft and can be widely applied to the domestic modification and routine maintenance of aircraft. It is of great significance for improving aircraft safety and reducing operating costs.

[0019] 2. The installation structure adopted in this invention meets the special requirements of the aviation environment, has good anti-interference ability and reliability, and can meet the strength requirements of relevant airworthiness regulations, making it stable and reliable. Attached Figure Description

[0020] The present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments:

[0021] Figure 1 This is a structural diagram of a device used for monitoring aircraft structural loads in an embodiment.

[0022] Figure 2 This is a diagram showing the installation structure inside the aircraft's baggage compartment.

[0023] Figure 3 An exploded view of the installation structure for strain / stress monitoring equipment.

[0024] Explanation of reference numerals in the attached figures:

[0025] 1. Aircraft fuselage; 2. Fiber optic cable; 2a. Fiber optic cable start point; 3. Power supply and signal lines; 4. Conduit; 5. Strain / stress monitoring equipment; 6. Baggage compartment; 7. Base plate; 8. Fiber optic flange and relay bracket; 9. Protective baffle; 10. Mounting bracket; 11. Screw; 12. Nut; 13. Grounding wire. Detailed Implementation

[0026] To make the objectives, technical solutions, and advantages of the present invention more apparent, exemplary embodiments according to the present invention will be described in detail below with reference to the accompanying drawings. Obviously, the described embodiments are merely a part of the embodiments of the present invention, and not all of the embodiments of the present invention. It should be understood that the present invention is not limited to the exemplary embodiments described herein. Based on the embodiments of the present invention described herein, all other embodiments obtained by those skilled in the art without inventive effort should fall within the protection scope of the present invention.

[0027] It should be understood that the invention can be embodied in various forms and should not be construed as being limited to the embodiments set forth herein. Rather, providing these embodiments will make the disclosure thorough and complete, and will fully convey the scope of the invention to those skilled in the art.

[0028] The terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the invention. When used herein, the singular forms “a,” “an,” and “the” are also intended to include the plural forms, unless the context clearly indicates otherwise.

[0029] A method for monitoring aircraft structural loads, using monitoring devices such as... Figures 1 to 3 As shown, it includes the following steps:

[0030] S1. Grind the bonding surface on the key structural surface of the aircraft fuselage 1 for modification;

[0031] S2. Adhere the strain sensor to the bonding surface;

[0032] S3. Install strain / stress monitoring equipment 5 in the aircraft's baggage compartment 6;

[0033] S4. Lay the fiber optic lead 2 and the power supply and signal line 3. The fiber optic lead 2 is connected between the strain sensor and the strain / stress monitoring device 5 to transmit strain and stress data of the modified key structure surface in real time. The power supply and signal line 3 is used to provide power to the strain / stress monitoring device 5 and to communicate. The fiber optic lead 2a of the fiber optic lead 2 is connected to the strain sensor. The strain and stress data of the modified key structure during aircraft operation are monitored by the high-precision fiber optic sensor. The fiber optic lead 2 and the power supply and signal line 3 can be fixedly attached to the structure of the aircraft fuselage 1 with tape.

[0034] In one embodiment, see Figure 2 and Figure 3 The luggage compartment 6 is equipped with a base plate 7, and a mounting bracket 10 is provided on the base plate 7. The strain / stress monitoring device 5 is fixedly installed on the mounting bracket 10. The strain / stress monitoring device 5 can be connected to the mounting bracket 10 by fasteners consisting of a screw 11 and a nut 12.

[0035] The strain / stress monitoring device 5 is grounded through grounding wire 13, which is connected to the aircraft grounding post on the aircraft fuselage. The connection end of the grounding wire 13 and the strain / stress monitoring device 5 can be pressed onto the strain / stress monitoring device 5 by screw 11 to achieve electrical contact.

[0036] In one embodiment, the optical fiber lead 2 and the power supply and signal line 3 enter the interior of the luggage compartment 6 through the wiring port on the luggage compartment 6, and the optical fiber lead 2 and the power supply and signal line 3 are fitted with wiring conduits 4.

[0037] In one embodiment, the bottom plate 7 of the luggage compartment 6 is also provided with an optical fiber flange and a relay bracket 8. The optical fiber flange and relay bracket 8 are used to guide and fix the optical fiber lead 2 and fix the relay. The relay is connected to the power supply line of the strain / stress device 5. The bottom plate 7 of the luggage compartment 6 is also provided with a protective baffle 9, which is located outside the optical fiber flange and relay bracket.

[0038] In one embodiment, the strain / strain monitoring device 5 remotely transmits and stores the strain and stress data monitored by the strain sensor in the cloud via power supply and signal lines 3, facilitating remote data analysis.

[0039] The above embodiments of the present invention are not intended to limit the scope of protection of the present invention. The implementation of the present invention is not limited thereto. All other modifications, substitutions or alterations made to the above structure of the present invention based on the above content of the present invention, in accordance with ordinary technical knowledge and common practice in the field, without departing from the basic technical idea of ​​the present invention, shall fall within the scope of protection of the present invention.

Claims

1. A method for monitoring aircraft structural loads, characterized in that, Includes the following steps: S1. Grind the bonding surfaces on the key structural surfaces of the aircraft fuselage during modification; S2. Adhere the strain sensor to the bonding surface; S3. Install strain / stress monitoring equipment in the aircraft's baggage compartment; S4. Lay optical fiber leads, power supply and signal lines. The optical fiber leads are connected between the strain sensor and the strain / stress monitoring device for real-time transmission of strain and stress data on the modified key structural surface. The power supply and signal lines are used to provide power to the strain / stress monitoring device and for communication.

2. The aircraft structural load monitoring method according to claim 1, characterized in that: The luggage compartment is equipped with a base plate, and a mounting bracket is provided on the base plate. The strain / stress monitoring equipment is fixedly mounted on the mounting bracket.

3. The aircraft structural load monitoring method according to claim 2, characterized in that: The strain / stress monitoring equipment is grounded via a grounding wire.

4. The aircraft structural load monitoring method according to claim 3, characterized in that: The optical fiber lead and the power supply and signal lines enter the interior of the luggage compartment through the cable entry port on the luggage compartment, and the optical fiber lead and the power supply and signal lines are fitted with cable conduits.

5. The aircraft structural load monitoring method according to claim 4, characterized in that: The bottom plate of the luggage compartment is also provided with an optical fiber flange and a relay bracket. The optical fiber flange and relay bracket are used to guide and fix the optical fiber lead and fix the relay. The relay is connected to the power supply line of the strain / stress device. The bottom plate of the luggage compartment is also provided with a protective baffle, which is located outside the optical fiber flange and relay bracket.

6. The aircraft structural load monitoring method according to claim 1, characterized in that: The strain / strain monitoring device remotely transmits and stores the strain and stress data monitored by the strain sensor in the cloud via the power supply and signal lines.

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