Adaptive intelligent monitoring system for shape of flexible composite skin of morphing aircraft

Abstract

The invention discloses an adaptive intelligent monitoring system for the shape of a flexible composite skin of a morphing aircraft, and aims to solve the problems of insufficient monitoring precision and slow response speed of a traditional monitoring system. The system integrates an intelligent skin material, a sensor grid, a central processing unit and a self-adaptive control system, and realizes real-time monitoring of the skin shape change of the morphing aircraft by adopting an advanced flexible composite material and a shape memory alloy and combining a fiber bragg grating sensor technology. The sensor grid can accurately measure parameters such as stress, strain, displacement and temperature, and transmits data to the central processing unit for analysis. The adaptive control system adjusts the skin shape in real time according to the analysis result and a preset strategy, and the flight performance is optimized. According to the invention, the flight performance and safety of the variant aircraft are improved, and high-dynamic and high-precision monitoring and adjustment are realized.

Description

Technical Field

[0001] The present invention relates to a method capable of inverting the load state of a variable wing in a short time, belonging to the field of aerospace technology. Background Art

[0002] During the flight of traditional aircraft, their aerodynamic shapes remain unchanged, making it difficult to adapt to complex and changing flight environments. As a new type of aircraft, variable aircraft can change their aerodynamic shapes during flight, such as wing area, aspect ratio, and sweep angle, etc., to optimize flight performance. However, the monitoring and control of the skin shape change of variable aircraft is one of the key technologies to achieve its performance optimization. Existing monitoring systems often have problems such as insufficient monitoring accuracy and slow response speed, making it difficult to meet the high-dynamic and high-precision monitoring requirements of variable aircraft.

[0003] In summary, there is an urgent need to develop a monitoring method that is adaptive, intelligent, and applicable to the skin shape of variable aircraft to improve the real-time performance of monitoring and adjustment. Summary of the Invention

[0004] The technical problem to be solved by the present invention is: overcoming the deficiencies of the prior art, providing an adaptive intelligent monitoring system for the shape of the flexible composite skin of a variable aircraft, which realizes the real-time monitoring and adaptive adjustment of the skin shape change of the variable aircraft by integrating intelligent materials and sensing technologies.

[0005] The technical solution of the present invention is:

[0006] An adaptive intelligent monitoring system for the shape of the flexible composite skin of a variable aircraft, comprising: a composite skin, a central processing unit, and an adaptive control system; a sensor grid is arranged inside the composite skin;

[0007] The composite skin deforms adaptively with the change of the aerodynamic shape of the aircraft, and the sensor grid monitors the stress, strain, displacement, and temperature parameters of the composite skin during the deformation process in real time and transmits the data to the central processing unit;

[0008] The central processing unit analyzes the shape change law of the composite skin and issues adjustment instructions according to the control strategy. The adjustment instructions are transmitted to the composite skin through the adaptive control system to drive it to perform shape adjustment; the adaptive control system adaptively adjusts the shape of the skin of the variable aircraft according to the adjustment instructions.

[0009] Further, the composite skin is of a sandwich structure, including a shape memory alloy layer, a sensor network layer, and a matrix material layer.

[0010] Further, the shape memory alloy layer has the ability of deformation and recovery, and can deform with the change of the aerodynamic shape of the aircraft.

[0011] Further, the sensor network layer includes fiber Bragg grating sensors and a silica gel thin layer, and the fiber Bragg grating sensors are implanted into the silica gel thin layer to form the sensor network layer.

[0012] Further, the matrix material layer is made of polyvinyl chloride material.

[0013] Further, the central processing unit analyzes the shape change law of the composite skin, which specifically includes the following steps:

[0014] (1) Data acquisition and preprocessing: The central processing unit first receives real-time data from the sensor grid, including curvature (κ), stress (б), strain (ε), displacement (s), and temperature (T) parameters; subsequently, preprocess these raw data, including denoising, calibration, and normalization, to ensure the accuracy and reliability of the data;

[0015] (2) Key feature extraction: Extract key features from the preprocessed data. The key features can reflect the change trend and law of the skin shape, including strain rate displacement (Δs), and temperature gradient (ΔT);

[0016] (3) Shape change modeling: Based on the extracted key features, use machine learning or numerical analysis methods to establish a mathematical model of the skin shape change. This mathematical model is used to predict the shape state of the skin at future time points;

[0017] (4) Shape change law analysis: Conduct in-depth analysis on the prediction results output by the mathematical model, including statistical analysis, spectral analysis, or pattern recognition of time series data, to identify periodic changes, mutation points, or long-term trends, and obtain the shape change law. The shape change law refers to the deformation patterns experienced by the composite skin under different flight conditions (different speeds (v), altitudes (h), attitudes (h), etc.), including deformation rate curvature change strain distribution

[0018] (5) Control strategy formulation: According to the shape change law and flight performance optimization objectives, formulate an adaptive adjustment control strategy to maximize the lift-to-drag ratio (K).

[0019] Further, the central processing unit issues adjustment instructions according to the control strategy, which specifically includes the following steps:

[0020] (1) Adjustment instruction generation: After formulating the control strategy, the central processing unit generates adjustment instructions according to the specific requirements of the control strategy. The adjustment instructions include the specific area to be adjusted, the adjustment amplitude, and the adjustment speed;

[0021] (2) Instruction Sending and Execution: The central processing unit sends the generated adjustment instructions to the adaptive control system to drive the composite skin to perform shape adjustment and ensure the accurate execution of the instructions.

[0022] Furthermore, the adaptive control system includes: a global deformation controller, multiple distributed drivers, multiple local deformation controllers, and multiple distributed sensors; the adaptive control system adaptively adjusts the shape of the skin of the morphing aircraft according to the adjustment instructions, and the specific implementation process is as follows:

[0023] (1) Receiving Adjustment Instructions: The global deformation controller, as the core of the adaptive control system, first receives the adjustment instructions from the central processing unit;

[0024] (2) Instruction Parsing and Allocation: The global deformation controller parses the received adjustment instructions to obtain the specific area to be adjusted, the adjustment amplitude, and the adjustment speed, and the global deformation controller distributes the parsing results to the corresponding local deformation controllers;

[0025] (3) Local Deformation Control: The local deformation controller controls its corresponding distributed driver to generate the corresponding driving force according to the received task instructions; at the same time, the distributed sensors continuously monitor the deformation of the skin and feedback the real-time data to the local deformation controller and the global deformation controller to form a closed-loop control;

[0026] (4) Feedback and Adjustment: Monitor the shape adjustment effect through the distributed sensors. If the predetermined shape is not reached, it will return to the central processing unit and continue to execute the task in a loop until the predetermined shape is reached or the stop condition is met.

[0027] The beneficial effects of the present invention compared with the prior art are:

[0028] (1) Significantly improving the monitoring accuracy and response speed: By integrating an advanced fiber Bragg grating sensor network, high-precision and multi-point real-time monitoring of the skin shape change is achieved, significantly improving the monitoring accuracy. At the same time, the introduction of the adaptive control system enables the system to quickly respond to the monitoring data and timely adjust the skin shape, meeting the high-dynamic and high-precision monitoring requirements of the morphing aircraft.

[0029] (2) Enhancing the adaptability of the aircraft and optimizing the performance: The intelligent skin material uses shape memory alloy, which has good deformation ability and recoverability, and can adaptively deform with the change of the aerodynamic shape of the aircraft. Combining with the real-time adjustment function of the adaptive control system, the aircraft can flexibly adjust the aerodynamic shape, such as wing area, aspect ratio, and sweep angle, according to the flight environment, flight profile, etc. during the flight process, so as to optimize the flight performance and improve the flight efficiency.

[0030] (3) Improve flight safety and reliability: The combination of real-time monitoring and adaptive adjustment functions enables the system to detect and correct changes in the skin shape in a timely manner, avoiding flight instability or safety hazards caused by shape changes. At the same time, the introduction of intelligent skin materials also improves the damage resistance and durability of the aircraft, further enhancing flight safety and reliability.

[0031] (4) Reduce system complexity and maintenance costs: Through an integrated design, intelligent materials, sensor layouts, adaptive control systems, etc. are organically combined to form an efficient and collaborative working mechanism. This not only reduces the system complexity but also decreases the number and types of components, thus reducing maintenance costs and maintenance difficulties. Brief Description of the Drawings

[0032] Figure 1 Schematic diagram of the adaptive intelligent monitoring system for the skin shape of the variant aircraft of the present invention;

[0033] Figure 2 Structural diagram of the combined deformable skin;

[0034] Figure 3 Layout diagram of the sensor network;

[0035] Figure 4 Flowchart of the adaptive control system. Detailed Implementation Manner

[0036] The following further describes in detail the specific implementation manner of the present invention in conjunction with the drawings.

[0037] As Figure 1 shown, the present invention proposes an adaptive intelligent monitoring system for the shape of the flexible composite skin of a variant aircraft, which system includes: a composite skin, a central processing unit, and an adaptive control system; a sensor grid is arranged inside the composite skin;

[0038] The composite skin adapts to deform with the change of the aerodynamic shape of the aircraft. The sensor grid real-time monitors the curvature (κ), stress (б), strain (ε), displacement (s), and temperature (T) parameters of the composite skin during the deformation process, and transmits the data to the central processing unit;

[0039] The central processing unit analyzes the shape change law of the composite skin and issues adjustment instructions according to the control strategy. The adjustment instructions are transmitted to the composite skin through the adaptive control system to drive it to perform shape adjustment; the adaptive control system adaptively adjusts the shape of the skin of the variant aircraft according to the adjustment instructions.

[0040] As Figure 2The figure shows the structure diagram of a combined deformable skin. It shows a flexible composite skin structure embedded with shape memory alloy. The shape memory alloy layer, fiber Bragg grating sensor layer, and matrix material layer are stacked in sequence. Materials with different properties are combined together through a multi-layer composite method to form a composite skin with excellent comprehensive properties. By introducing shape memory alloy into this material, it has good deformation ability and recoverability, and can adaptively deform with the change of the aerodynamic shape of the aircraft. That is: the composite skin is a sandwich structure, including a memory alloy layer, a sensor network layer, and a matrix material layer.

[0041] Preferably, the memory alloy layer has deformation ability and recoverability, and can deform with the change of the aerodynamic shape of the aircraft.

[0042] Preferably, the sensor network layer includes fiber Bragg grating sensors and a silicone thin layer. The fiber Bragg grating sensors are implanted into the silicone thin layer to form the sensor network layer. As Figure 3 The figure shows the layout diagram of the sensor network, which shows the positions and densities of strain sensors, displacement sensors, and temperature sensors arranged on the skin surface.

[0043] Fiber Bragg Grating (FBG) is a fiber optic sensor based on fiber grating technology. By connecting multiple FBGs in series on a single optical fiber and using multiplexing technology, multi-point measurement can be achieved, improving the utilization rate and flexibility of the sensors. These sensors can real-time monitor parameters such as stress, strain, displacement, and temperature of the skin during the deformation process, and transmit the data to the central processing unit.

[0044] Preferably, the matrix material layer uses polyvinyl chloride material.

[0045] In the present invention, the central processing unit analyzes the shape change law of the composite skin, specifically including the following steps:

[0046] (1) Data acquisition and preprocessing: The central processing unit first receives real-time data from the sensor network, including curvature (κ), stress (б), strain (ε), displacement (s), and temperature (T) parameters; subsequently, preprocess these raw data, including denoising, calibration, and normalization, to ensure the accuracy and reliability of the data;

[0047] (2) Key feature extraction: Extract key features from the preprocessed data. The key features can reflect the change trend and law of the skin shape, including strain rate displacement amount (Δs), temperature gradient (ΔT);

[0048] (3) Shape change modeling: Based on the extracted key features, use machine learning or numerical analysis methods to establish a mathematical model of the skin shape change. This mathematical model is used to predict the shape state of the skin at future time points;

[0049] (4) Shape change law analysis: Deeply analyze the prediction results output by the mathematical model, including statistical analysis, spectral analysis or pattern recognition of time series data, to identify periodic changes, mutation points or long-term trends, and obtain the shape change law. The shape change law refers to the deformation patterns experienced by the composite skin under different flight conditions (different speeds (v), altitudes (h), attitudes (h), etc.), including the deformation rate Curvature change Strain distribution

[0050] (5) Control strategy formulation: According to the shape change law and the flight performance optimization goal, formulate an adaptive adjustment control strategy to maximize the lift-to-drag ratio (K).

[0051] The central processing unit issues adjustment instructions according to the control strategy, which specifically includes the following steps:

[0052] (1) Adjustment instruction generation: After formulating the control strategy, the central processing unit generates adjustment instructions according to the specific requirements of the control strategy. The adjustment instructions include the specific areas to be adjusted, the adjustment amplitude, and the adjustment speed;

[0053] (2) Instruction sending and execution: The central processing unit sends the generated adjustment instructions to the adaptive control system to drive the composite skin to perform shape adjustment and ensure that the instructions are accurately executed.

[0054] As Figure 1 shown, the adaptive control system includes: a global deformation controller, multiple distributed drivers, multiple local deformation controllers, and multiple distributed sensors; the adaptive control system adaptively adjusts the shape of the skin of the variable aircraft according to the adjustment instructions, and the specific implementation process is as Figure 4 shown:

[0055] (1) Receive adjustment instructions: The global deformation controller, as the core of the adaptive control system, first receives the adjustment instructions from the central processing unit;

[0056] (2) Instruction parsing and distribution: The global deformation controller parses the received adjustment instructions to obtain the specific areas to be adjusted, the adjustment amplitude, and the adjustment speed, and the global deformation controller distributes the parsing results to the corresponding local deformation controllers;

[0057] (3) Local deformation control: The local deformation controller controls its corresponding distributed driver to generate the corresponding driving force according to the received task instructions; at the same time, the distributed sensors continuously monitor the deformation of the skin and feedback the real-time data to the local deformation controller and the global deformation controller to form a closed-loop control;

[0058] (4) Feedback and adjustment: Monitor the shape adjustment effect through distributed sensors. If the predetermined shape is not achieved, it will return to the central processing unit and continue to execute the task in a loop until the predetermined shape is achieved or the stop condition is met.

[0059] The present invention solves the problems of insufficient monitoring accuracy and slow response speed of traditional monitoring systems. It improves the flight performance and safety of variable aircraft, and realizes high-dynamic and high-precision monitoring and adjustment.

[0060] The parts not detailed in the present invention belong to the common general knowledge of those skilled in the art.

Claims

1. A flexible composite skin shape adaptive intelligent monitoring system for a variant aircraft, characterized in that Comprising: A composite skin, a central processing unit, and an adaptive control system; a sensor grid is provided inside the composite skin; The composite skin adapts and deforms according to the change of the aerodynamic shape of the aircraft, and the sensor grid real-time monitors the stress, strain, displacement, and temperature parameters of the composite skin during the deformation process, and transmits the data to the central processing unit; The central processing unit analyzes the shape change law of the composite skin, and issues an adjustment instruction according to the control strategy. The adjustment instruction is transmitted to the composite skin through the adaptive control system to drive it to perform shape adjustment; the adaptive control system adaptively adjusts the shape of the skin of the morphing aircraft according to the adjustment instruction.

2. The shape self-adaptive intelligent monitoring system for the flexible composite skin of a variant aircraft according to claim 1, characterized in that: The composite skin is of a sandwich structure, including a shape memory alloy layer, a sensor network layer, and a matrix material layer.

3. The shape self-adaptive intelligent monitoring system for the flexible composite skin of a variant aircraft according to claim 2, characterized in that: The shape memory alloy layer has the ability to deform and recover, and can deform according to the change of the aerodynamic shape of the aircraft.

4. A shape self - adaptive intelligent monitoring system for the flexible composite skin of a variant aircraft, according to claim 2, characterized in that: The sensor network layer includes fiber Bragg grating sensors and a silica gel thin layer, and the fiber Bragg grating sensors are implanted into the silica gel thin layer to form the sensor network layer.

5. The shape self - adaptive intelligent monitoring system for the flexible composite skin of a variant aircraft according to claim 2, characterized in that: The matrix material layer uses polyvinyl chloride material.

6. The shape self - adaptive intelligent monitoring system for the flexible composite skin of a variant aircraft according to claim 1, characterized in that: The central processing unit analyzes the shape change law of the composite skin, specifically including the following steps: (1) Data acquisition and preprocessing: The central processing unit first receives the real-time data from the sensor grid, including curvature κ, stress б, strain ε, displacement s, and temperature T parameters; Subsequently, preprocess these raw data, including denoising, calibration, and normalization, to ensure the accuracy and reliability of the data; (2) Key feature extraction: Extract key features from the preprocessed data. The key features can reflect the change trends and rules of the skin shape, including strain rate displacement Δs, and temperature gradient ΔT; (3) Shape change modeling: Based on the extracted key features, use machine learning or numerical analysis methods to establish a mathematical model of the skin shape change; this mathematical model is used to predict the shape state of the skin at future time points; (4) Analysis of shape change patterns: Conduct in-depth analysis of the prediction results output by the mathematical model, including statistical analysis, spectral analysis, or pattern recognition of time series data, to identify periodic changes, mutation points, or long-term trends, and obtain the shape change patterns; the shape change patterns refer to the deformation patterns experienced by the composite skin under different flight conditions, i.e., different speeds v, altitudes h, and attitudes h, including the deformation rate Curvature change Strain distribution (5) Control strategy formulation: According to the shape change law and the flight performance optimization goal, formulate an adaptive adjustment control strategy to maximize the lift-to-drag ratio K.

7. The shape adaptive intelligent monitoring system for the flexible composite skin of a variant aircraft according to claim 6, characterized in that: The central processing unit issues an adjustment instruction according to the control strategy, specifically including the following steps: (1) Adjustment instruction generation: After formulating the control strategy, the central processing unit generates an adjustment instruction according to the specific requirements of the control strategy. The adjustment instruction includes the specific area to be adjusted, the adjustment amplitude, and the adjustment speed; (2) Instruction sending and execution: The central processing unit sends the generated adjustment instruction to the adaptive control system to drive the composite skin to perform shape adjustment to ensure that the instruction is accurately executed.

8. A shape adaptive intelligent monitoring system for the flexible composite skin of a morphing aircraft according to claim 7, characterized in that: The adaptive control system includes: a global deformation controller, a plurality of distributed drivers, a plurality of local deformation controllers, and a plurality of distributed sensors; the adaptive control system adaptively adjusts the shape of the skin of the morphing aircraft according to the adjustment instruction. The specific implementation process is as follows: (1) Receiving the adjustment instruction: The global deformation controller, as the core of the adaptive control system, first receives the adjustment instruction from the central processing unit; (2) Instruction parsing and distribution: The global deformation controller parses the received adjustment instructions to obtain the specific area to be adjusted, the adjustment amplitude, and the adjustment speed, and the global deformation controller distributes the parsing results to the corresponding local deformation controllers; (3) Local deformation control: The local deformation controller controls the corresponding distributed drivers to generate corresponding driving forces according to the received task instructions; at the same time, the distributed sensors continuously monitor the deformation of the skin and feedback the real-time data to the local deformation controller and the global deformation controller to form a closed-loop control; (4) Feedback and adjustment: Monitor the shape adjustment effect through the distributed sensors. If the predetermined shape is not reached, it will return to the central processing unit and continue to execute the task in a loop until the predetermined shape is reached or the stop condition is met.

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