CN-122016105-A - Aircraft skin universe stress sensing system based on edge intelligence and digital twin

CN122016105ACN 122016105 ACN122016105 ACN 122016105ACN-122016105-A

Abstract

The application discloses an aircraft skin universe stress sensing system based on edge intelligence and digital twinning, which relates to the technical field of intelligent operation and maintenance and digital engineering of aviation equipment, and comprises a parameter optimization processing module, a parameter optimization model, a parameter analysis module and a parameter analysis module, wherein the parameter optimization processing module is used for determining the division of an aircraft monitoring area and the topology of a conductor network, constructing the parameter optimization model and determining the specification data of the conductor network of each area embedded into a composite material skin; the intelligent acquisition module is used for arranging core acquisition circuits of the acquisition sub-stations in each area and butting the sensor network, the edge processing sensing module is used for acquiring data of each acquisition sub-station based on the sensor network, carrying out on-board real-time stress alarm and feeding back the data to an aircraft manager, and the cloud processing module is used for synchronizing the data of each acquisition sub-station and the alarm data to the digital twin platform of the aircraft to form a prediction maintenance report. The hierarchical network architecture provided by the application can easily expand the number of the monitoring points to ten thousand road levels, realizes dead angle-free monitoring of the whole aircraft skin, and improves the flight safety and economy of the aircraft.

Inventors

WANG HUI
WANG ZIJIA
YE XINRU
GENG YITONG
LIANG ZIYUE
GONG YUE

Assignees

徐州干城章储能科技有限公司
徐州工程学院

Dates

Publication Date: 20260512
Application Date: 20260129

Claims (10)

1. The aircraft skin global stress sensing system based on edge intelligence and digital twinning is characterized by comprising: the parameter optimization processing module is used for determining the division of the monitoring area of the aircraft and the topology of the conductor network, constructing a parameter optimization model, and determining the specification data of the conductor network of each area of the pre-buried composite material skin based on the parameter optimization model; The intelligent acquisition module is used for arranging core acquisition circuits of acquisition substations in all areas based on the verified multichannel scheme and butting the sensing network; The edge processing sensing module is used for acquiring data of each acquisition substation based on the sensing network, carrying out on-board real-time alarm and feeding back to an aircraft manager; And the cloud processing module synchronizes the data of each acquisition substation and the alarm data to the digital twin platform of the aircraft to form a prediction maintenance report.
2. The edge intelligence and digital twinning-based aircraft skin global stress sensing system of claim 1, wherein: the method for determining aircraft monitoring zone division and conductor network topology comprises: The aircraft skin is divided into a plurality of monitoring areas, one acquisition substation is deployed in each monitoring area, and each acquisition substation manages all the sensing loops in the monitoring area.
3. The aircraft skin global stress sensing system based on edge intelligence and digital twinning according to claim 2, wherein the constructing a parametric optimization model, determining the pre-buried composite skin region conductor network specification data based on the parametric optimization model comprises: The diameter, the length and the space density of the conductors are configured differently according to the pneumatic load and the stress distribution characteristics of different parts of the aircraft; the conductor wiring density in the low stress region of the aircraft should be higher than in the high stress region.
4. The edge intelligence and digital twinning based aircraft skin global stress sensing system of claim 1, further comprising: When the conductor resistance changes, the voltage signal change quantity generated on the load is calculated, and then the quantitative relation between the induced electromotive force change quantity and the skin strain is formed.
5. The edge intelligence and digital twinning based aircraft skin global stress sensing system of claim 4, further comprising: the conductor loop is connected into a test circuit, an equivalent circuit of the conductor loop is modeled as a voltage source containing induced electromotive force V is connected with a resistor R in series, and then loop current I meets the following conditions: Wherein, the Representing the input impedance of the measuring system, when the skin strain causes the conductor resistance to change Resistance at the time Initial resistance for conductor And (3) with The current variation modulates the output voltage, specifically: Wherein, the Indicating the variation of induced electromotive force and the initial resistance of conductor Refers to the initial resistance of the conductor when unstressed.
6. The aircraft skin global stress sensing system based on edge intelligence and digital twinning as set forth in claim 5, wherein said induced electromotive force The calculation mode of (2) comprises: the conductors being regarded as being composed of several infinitesimal Composition of each infinitesimal The unique magnetic field vectors are arranged at the positions, induced electromotive force can be generated in the conductor bar according to Faraday electromagnetic induction law, and the tiny induced electromotive force dV generated on each infinitesimal is as follows: The induced electromotive force V of the entire conductor is an integral of the minute induced electromotive forces generated on all the minute elements: Wherein: Is the speed at which the conductor bars move in the magnetic field, For the magnetic induction intensity, the magnetic flux is measured, For the length of the conductor bar, Is that And Is arranged at the lower end of the cylinder, Is that And Is included in the bearing.
7. The aircraft skin global stress sensing system based on edge intelligence and digital twinning as set forth in claim 5, wherein said conductor resistance changes Strain factor with material, initial resistance of conductor And strain-related of the material, specifically expressed as: Wherein, the Representing the strain factor of the material; indicating the strain of the material.
8. The edge intelligence and digital twinning based aircraft skin global stress sensing system of claim 7, further comprising: Will be Substituting into a calculation formula of the variation of the induced electromotive force, defining a strain sensitivity coefficient of the system, expressed as In units of ; Wherein, define = ; The strain resolution of the system is equal to the ratio of the voltage resolution of the system to the strain sensitivity coefficient of the system, and the system can achieve Is used for the strain resolution of (a).
9. The edge intelligence and digital twinning based aircraft skin global stress sensing system of claim 5, further comprising: the system is provided with a current sensor on a core acquisition circuit for monitoring a current value in real time, and a current threshold judgment node is arranged on an edge processing sensing module; Current threshold value The calculation formula of (2) is as follows: Wherein: As the signal-to-noise ratio coefficient, As the standard deviation of the current noise, In order to allow for the amount of stress variation, As a coefficient of current-stress sensitivity, Is a safety margin coefficient; because each core acquisition circuit is independently connected in parallel, the position of the deformed conductor bar can be accurately positioned based on the sensing network, and an alarm signal is formed; the alarm signal comprises two signals, and the loop current I is judged to exceed the current threshold value at the current threshold value judging node And displaying the line alarm signal when the loop current data cannot be received within a time threshold, wherein the time threshold is set by the system.
10. The aircraft skin global stress sensing system based on edge intelligence and digital twinning as set forth in claim 1, wherein the cloud processing module specifically comprises: Historical test data are acquired in the digital twin platform of the aircraft, and a prediction model in the system is called to form a regional prediction maintenance report based on the historical test data, the acquired substation data and alarm data acquired in real time.

Description

Aircraft skin universe stress sensing system based on edge intelligence and digital twin Technical Field The invention relates to the technical field of intelligent operation and maintenance and digital engineering of aviation equipment, in particular to an aircraft skin universe stress sensing system based on edge intelligence and digital twinning. Background With the development of aviation equipment to long-endurance, high-reliability and intelligent directions, the requirements for real-time, online and predictive monitoring of the health status of an aircraft structure, particularly a large-area skin, are increasingly urgent. The traditional manual inspection and regular overhaul mode cannot meet the double severe requirements of modern aviation operation on safety and economy, and the structural health monitoring technology becomes a key for guaranteeing flight safety and realizing maintenance according to conditions. At present, the structural health monitoring technology applied to the aviation field mainly has the following defects: In the optical fiber sensing technology represented by the optical fiber grating sensor, the system integration is complex, a precise light source, demodulation equipment and a large number of optical cables are needed, the cost is high, and the risk of easy breakage exists in a high-strain area; the piezoelectric sensor technology is characterized in that a piezoelectric element is fragile and needs to be coupled with a structure by an adhesive, long-term reliability is greatly influenced by environment, a driving and collecting system is complex and high in energy consumption, and a wireless sensor network technology solves the wiring problem, but a core sensor node still needs battery power supply or energy collection and faces the problems of power supply continuity, electromagnetic compatibility and communication reliability in an onboard severe environment; Meanwhile, the prior structural health monitoring technology has common defects: various sensors are usually designed aiming at specific types of damage or local areas, a large-scale and unified sensing network covering the whole engine skin is difficult to form, and the deployment mode of a point type or a small array cannot capture the space-time correlation between the stress field evolution and the damage of the whole structure; In addition, the existing structural health monitoring technology system has huge data transmission pressure and poor real-time performance on massive high-frequency data required by skin health monitoring, and data analysis is mostly limited to current state evaluation and simple threshold alarm, and lacks dynamic simulation and long-term prediction capability on damage initiation and expansion processes. Disclosure of Invention The invention aims to provide an aircraft skin universe stress sensing system based on edge intelligence and digital twinning, which is used for solving the problems of sensing fragmentation, analysis hysteresis and maintenance passivity existing in the current aircraft structure health management. The method specifically comprises the following steps: the parameter optimization processing module is used for determining the division of the monitoring area of the aircraft and the topology of the conductor network, constructing a parameter optimization model, and determining the specification data of the conductor network of each area of the pre-buried composite material skin based on the parameter optimization model; The intelligent acquisition module is used for arranging core acquisition circuits of acquisition substations in all areas based on the verified multichannel scheme and butting the sensing network; The edge processing sensing module is used for acquiring data of each acquisition substation based on the sensing network, carrying out on-board real-time alarm and feeding back to an aircraft manager; And the cloud processing module synchronizes the data of each acquisition substation and the alarm data to the digital twin platform of the aircraft to form a prediction maintenance report. According to the above technical solution, the method for determining the aircraft monitoring area division and the conductor network topology comprises: The aircraft skin is divided into a plurality of monitoring areas, one acquisition substation is deployed in each monitoring area, and each acquisition substation manages all the sensing loops in the monitoring area. According to the above technical scheme, the constructing the parameter optimization model, and determining the network specification data of each region of the pre-buried composite material skin based on the parameter optimization model includes: The diameter, the length and the space density of the conductors are configured differently according to the pneumatic load and the stress distribution characteristics of different parts of the aircraft; the choice of conductor diameter and length during a par