CN115221640A - Intelligent full-automatic aviation rudder wing inspection system based on infrared induction principle - Google Patents
Intelligent full-automatic aviation rudder wing inspection system based on infrared induction principle Download PDFInfo
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Abstract
The invention provides an intelligent full-automatic inspection system for an aviation rudder wing based on an infrared induction principle, which comprises the following components: the model simulation end is used for carrying out model simulation on the basis of the infrared video of the rudder wing to obtain a dynamic rudder wing model; the damage evaluation terminal is used for carrying out sub-position dynamic structure characteristic analysis and sub-position static structure characteristic analysis on the rudder wing based on the dynamic rudder wing model to obtain a structural damage value of each part in a corresponding inspection period; the rule analysis end is used for obtaining an evaluation evolution result of the corresponding part based on the structural damage values of different inspection periods and analyzing a damage evolution rule of the corresponding part based on the evaluation evolution result; the plan determining end is used for determining a total maintenance plan based on the damage evolution rule and the latest structure damage value; the method is used for carrying out dynamic model simulation and fractional structure characteristic analysis on the rudder wing by using the infrared video acquired based on the infrared induction principle, obtaining the structure damage values of different parts and making a proper maintenance plan, thereby improving the inspection and maintenance efficiency of the rudder wing.
Description
Technical Field
The invention relates to the technical field of intelligent full-automatic inspection of aviation rudder wings, in particular to an intelligent full-automatic inspection system of the aviation rudder wings based on an infrared induction principle.
Background
At present, a rudder wing refers to an aerodynamic wing surface, also called a control surface, which uses deflection to generate balance force and control force to control the flight of an airplane. The control surface is the control surface of the airplane, generally the control surface is the control surface in three directions, the horizontal direction is called elevator, namely horizontal tail, and is responsible for controlling the airplane to ascend and descend, the vertical direction is called rudder, generally the vertical tail is above, and is responsible for controlling the course of the airplane, the inclined direction is called aileron, generally the tail end of the airplane wing is responsible for controlling the airplane to incline, and the system structure characteristic of the control wing and the course control in the flight process of the aviation airplane have important influence, therefore, the system structure characteristic of the control wing needs to be checked before the airplane sails, so as to avoid the situation that the airplane generates aviation inaccuracy or is seriously influenced by jet flow interference effect in the flight process.
However, the existing rudder wing inspection methods mostly adopt a manual inspection mode, which not only needs a lot of labor cost and manual experience, but also cannot continuously ensure high-precision inspection effect, and cannot generate a rudder wing maintenance plan in a targeted manner, thereby resulting in low inspection and maintenance efficiency of the rudder wing.
Therefore, the invention provides an intelligent full-automatic inspection system for an aviation rudder wing based on an infrared induction principle.
Disclosure of Invention
The invention provides an intelligent full-automatic inspection system for an aviation rudder wing based on an infrared induction principle, which is used for carrying out dynamic model simulation on the rudder wing based on an infrared video of the rudder wing obtained based on the infrared induction principle to obtain a three-dimensional dynamic aviation wing model, then carrying out fractional dynamic structure characteristic analysis and fractional static structure characteristic analysis on the three-dimensional dynamic aviation wing model to obtain structure damage values of different parts, and making a proper maintenance plan according to a damage evolution rule obtained by the evolution analysis of the result damage values.
The invention provides an intelligent full-automatic inspection system for an aviation rudder wing based on an infrared induction principle, which comprises the following components:
the model simulation end is used for acquiring an infrared video of the rudder wing based on the inspection period and performing model simulation based on the infrared video to obtain a dynamic rudder wing model;
the damage evaluation terminal is used for carrying out sub-position dynamic structure characteristic analysis and sub-position static structure characteristic analysis on the rudder wing based on the dynamic rudder wing model to obtain a structural damage value of each part in a corresponding inspection period;
the rule analysis end is used for obtaining an evaluation evolution result of the corresponding part based on the structural damage values of different inspection periods and analyzing a damage evolution rule of the corresponding part based on the evaluation evolution result;
and the plan determining end is used for determining a total maintenance plan based on the damage evolution rule and the latest structure damage value.
Preferably, the model emulation end includes:
the video acquisition module is used for acquiring infrared local monitoring videos of the rudder wing at a plurality of monitoring angles based on the inspection period;
the alignment splicing module is used for aligning and splicing time sequences of all infrared local monitoring videos based on the spatial distribution relation of the monitoring angles to obtain the infrared video of the rudder wing;
and the module simulation module is used for carrying out model simulation on the rudder wing based on the infrared video to obtain a dynamic rudder wing model.
Preferably, the video acquisition module includes:
a cycle determination unit for acquiring an automatic inspection plan and determining an inspection cycle based on the automatic inspection plan;
and the video acquisition unit is used for controlling the plurality of infrared monitoring devices to carry out infrared monitoring on the rudder wing structure in the inspection period so as to obtain infrared local monitoring videos of a plurality of monitoring angles.
Preferably, the lesion evaluation tip includes:
the first analysis module is used for carrying out sub-position dynamic structure characteristic analysis on the rudder wing based on the dynamic rudder wing model to obtain a first structure damage value corresponding to each position in each inspection period;
the second analysis module is used for performing sub-position static structure analysis on the rudder wing based on the dynamic rudder wing model to obtain a second structure damage value corresponding to each part in each inspection period;
and the result summarizing module is used for taking the average value of the first structural damage value and the second structural damage value of the corresponding part in the corresponding inspection period as the structural damage value of the corresponding part in the corresponding inspection period.
Preferably, the first analysis module comprises:
the decomposition unit is used for carrying out part decomposition on the dynamic structure frame corresponding to the dynamic rudder wing model based on each structure unit contained in the structure unit gradient list to obtain a plurality of linkage part frames corresponding to each structure unit;
the analysis unit is used for generating basic motion vectors of corresponding parts based on the motion amplitude and the motion direction of the parts corresponding to the minimum structure units contained in the linkage part frame in the dynamic process, and taking the mean value of the basic motion vectors of all the parts contained in the linkage part frame as the corresponding linkage motion vector;
the calculating unit is used for calculating a first deviation value of the corresponding part based on a rate characteristic value curve of the corresponding part in a dynamic process and a corresponding standard rate characteristic value curve;
and an evaluation unit for calculating a second deviation value between each of the interlocking motion vectors and the standard interlocking motion vector of the corresponding interlocking part frame, and calculating a first structural damage value of the corresponding part in the corresponding inspection cycle based on the first deviation value of the corresponding part and the second deviation values of all interlocking part frames including the corresponding part.
Preferably, the second analysis module comprises:
the frame extraction unit is used for acquiring a standard static posture of each part in a standard inspection state, and acquiring a static local frame of the corresponding part and a complete rudder wing static frame corresponding to the static local frame in the dynamic rudder wing model based on the standard static posture;
the coordinate determination unit is used for unifying the complete rudder wing static frame under a preset coordinate system to obtain a coordinate unification result, and determining the current coordinate representation of the static local frame based on the coordinate unification result;
and the damage determining unit is used for acquiring the standard coordinate representation of the corresponding standard static posture, and taking a third deviation value of the current coordinate representation and the standard coordinate representation as a second structural damage value of the corresponding part in the corresponding inspection period.
Preferably, the rule analysis end includes:
the result sorting module is used for sorting the structural damage values of the corresponding parts based on the inspection period corresponding to the corresponding dynamic rudder wing model to obtain the evaluation evolution result of the corresponding parts;
and the evolution analysis module is used for analyzing the damage evolution rule of the corresponding part based on the evaluation evolution result.
Preferably, the evolution analysis module comprises:
the curve generation unit is used for generating a corresponding structural damage value change curve based on the structural damage value sequence contained in the evaluation evolution result;
and the rule determining unit is used for determining a corresponding structural damage value change function based on the structural damage value change curve and taking the structural damage value change function as a corresponding damage evolution rule.
Preferably, the plan determination end includes:
the first determining module is used for determining a maintenance plan of the corresponding part based on the corresponding damage evolution rule when the latest structure damage value accords with the damage evolution rule of the corresponding part;
the second determining module is used for determining a maintenance plan of the corresponding part based on the latest structure damage value and the damage evolution rule of the corresponding part when the latest structure damage value does not accord with the damage evolution rule of the corresponding part;
and the comprehensive generation module is used for generating a total maintenance plan based on the maintenance plan of each part.
Preferably, the first determining module includes:
the maintenance determining unit is used for determining a maintenance period and a corresponding maintenance item of the corresponding part based on the corresponding damage evolution rule when the latest structure damage value accords with the damage evolution rule of the corresponding part;
and a plan determination unit for determining a maintenance plan of the corresponding portion based on the maintenance cycle of the corresponding portion and the corresponding maintenance item.
Additional features and advantages of the invention will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. The objectives and other advantages of the invention will be realized and attained by the structure particularly pointed out in the written description and claims hereof as well as the appended drawings.
The technical solution of the present invention is further described in detail by the accompanying drawings and embodiments.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention and not to limit the invention. In the drawings:
fig. 1 is a schematic diagram of an intelligent full-automatic inspection system for an aviation rudder wing based on an infrared induction principle in an embodiment of the invention;
FIG. 2 is a schematic diagram of a model simulation end according to an embodiment of the present invention;
FIG. 3 is a schematic diagram of a video capture module according to an embodiment of the present invention;
FIG. 4 is a schematic diagram of a damage-assessment end according to an embodiment of the present invention;
FIG. 5 is a diagram of a first analysis module according to an embodiment of the present invention;
FIG. 6 is a diagram of a second analysis module according to an embodiment of the present invention;
FIG. 7 is a schematic diagram of a rule analysis end according to an embodiment of the present invention;
FIG. 8 is a schematic diagram of an evolution analysis module according to an embodiment of the present invention;
FIG. 9 is a schematic diagram of a schedule determination end in an embodiment of the present invention;
fig. 10 is a schematic diagram of a first determining module according to an embodiment of the present invention.
Detailed Description
The preferred embodiments of the present invention will be described in conjunction with the accompanying drawings, and it should be understood that they are presented herein only to illustrate and explain the present invention and not to limit the present invention.
Example 1:
the invention provides an intelligent full-automatic inspection system of an aviation rudder wing based on an infrared induction principle, which comprises the following components with reference to a figure 1:
the model simulation end is used for acquiring an infrared video of the rudder wing based on the inspection period and performing model simulation based on the infrared video to obtain a dynamic rudder wing model;
the damage evaluation terminal is used for carrying out sub-position dynamic structure characteristic analysis and sub-position static structure characteristic analysis on the rudder wing based on the dynamic rudder wing model to obtain a structural damage value of each part in a corresponding inspection period;
the rule analysis end is used for obtaining an evaluation evolution result of the corresponding part based on the structural damage values of different inspection periods and analyzing a damage evolution rule of the corresponding part based on the evaluation evolution result;
and the plan determining end is used for determining a total maintenance plan based on the damage evolution rule and the latest structure damage value.
In this embodiment, the verification period is a period for automatically verifying the rudder wing.
In this embodiment, the infrared video is a monitoring video obtained based on the infrared sensing principle and including the test action performed by the rudder wing when being inspected.
In this embodiment, the three-dimensional dynamic wing model is a three-dimensional dynamic model representing a dynamic process of a test action performed when the rudder wing is inspected, which is obtained by performing model simulation on the rudder wing based on an infrared video.
In this embodiment, the structural damage value is a numerical value representing the current structural damage degree of the corresponding portion in the rudder wing, which is obtained after performing the analysis of the dynamic structural characteristics and the static structural characteristics of the sub-portions on the rudder wing.
In this embodiment, the evaluation and evolution result is a result of a historical evolution process of the structural damage value representing the corresponding portion in the rudder wing, which is obtained based on the structural damage values of different inspection periods.
In this embodiment, the damage evolution law is a historical evolution law of the structural damage value of the corresponding portion in the rudder wing obtained after analyzing the evaluation evolution result.
In this embodiment, the total maintenance plan is a maintenance plan that is determined based on the damage evolution rule and the latest structural damage value and includes a maintenance cycle and a maintenance project for each part of the rudder wing.
The beneficial effects of the above technology are: the method comprises the steps of carrying out dynamic model simulation on a rudder wing based on an infrared video of the rudder wing obtained by an infrared induction principle to obtain a three-dimensional dynamic wing model, carrying out sub-position dynamic structure characteristic analysis and sub-position static structure characteristic analysis on the three-dimensional dynamic wing model to obtain structural damage values of different positions, making a proper maintenance plan according to a damage evolution rule obtained by the evolution analysis of the result damage values, achieving high-precision and high-efficiency automatic inspection of the aviation rudder wing without a large amount of labor cost and manual experience, automatically generating a reasonable maintenance plan, and improving inspection and maintenance efficiency of the rudder wing.
Example 2:
on the basis of the embodiment 1, the model simulation end, referring to fig. 2, includes:
the video acquisition module is used for acquiring infrared local monitoring videos of the rudder wing at a plurality of monitoring angles based on the inspection period;
the alignment splicing module is used for aligning and splicing time sequences of all infrared local monitoring videos based on the spatial distribution relation of the monitoring angles to obtain the infrared video of the rudder wing;
and the module simulation module is used for carrying out model simulation on the rudder wing based on the infrared video to obtain a dynamic rudder wing model.
In this embodiment, the monitoring angle is a preset angle for acquiring an infrared local monitoring video of the rudder wing.
In this embodiment, the infrared local monitoring video is the local monitoring video of the rudder wing acquired at the corresponding monitoring angle based on the infrared sensing principle.
In this embodiment, the infrared video is a monitoring video that is obtained by aligning and splicing all infrared local monitoring videos in time sequence based on the spatial distribution relationship of the monitoring angles and that can monitor all structures of the rudder wing.
The beneficial effects of the above technology are: the method comprises the steps of splicing infrared local monitoring videos for monitoring the local structure of the rudder wing, which are obtained based on a detection period and an infrared induction principle, based on the spatial distribution relation of monitoring angles to obtain the infrared videos capable of monitoring all structures of the rudder wing, and performing three-dimensional modeling based on the infrared videos, so that the comprehensive monitoring and accurate modeling of the rudder wing structure are realized.
Example 3:
on the basis of embodiment 2, the video acquisition module, referring to fig. 3, includes:
a cycle determination unit for acquiring an automatic inspection plan and determining an inspection cycle based on the automatic inspection plan;
and the video acquisition unit is used for controlling the plurality of infrared monitoring devices to perform infrared monitoring on the rudder wing structure in the inspection period so as to obtain infrared local monitoring videos of a plurality of monitoring angles.
In this embodiment, the autoverification plan is a plan prepared in advance and including a period for autoverifying the rudder wing.
In this embodiment, the infrared monitoring device is a device that uses the infrared sensing principle to realize video monitoring of an object.
The beneficial effects of the above technology are: the inspection period of the rudder wing is determined based on the automatic inspection plan, and the infrared monitoring is carried out on the rudder wing structure based on the inspection period and the infrared monitoring device, so that the rudder wing is locally monitored according to the automatic inspection plan.
Example 4:
on the basis of example 1, the injury evaluation terminal, referring to fig. 4, includes:
the first analysis module is used for carrying out sub-position dynamic structure characteristic analysis on the rudder wing based on the dynamic rudder wing model to obtain a first structure damage value corresponding to each part in each inspection period;
the second analysis module is used for performing sub-position static structure analysis on the rudder wing based on the dynamic rudder wing model to obtain a second structure damage value corresponding to each position in each inspection period;
and the result summarizing module is used for taking the average value of the first structural damage value and the second structural damage value of the corresponding part in the corresponding inspection period as the structural damage value of the corresponding part in the corresponding inspection period.
In this embodiment, the first structural damage value is a numerical value representing a structural damage degree of a corresponding part in the rudder wing in a current dynamic process, which is obtained after performing sub-position dynamic structural characteristic analysis on the rudder wing based on the dynamic rudder wing model.
In this embodiment, the second structural damage value is a numerical value representing a structural damage degree of a corresponding part in the rudder wing in a current static process, which is obtained after performing sub-part static structural characteristic analysis on the rudder wing based on the dynamic rudder wing model.
In this embodiment, the structural damage value is an average value of the first structural damage value and the second structural damage value of the corresponding portion in the corresponding inspection period.
The beneficial effects of the above technology are: based on a dynamic rudder wing model, averaging a first structural damage value and a second structural damage value obtained after carrying out sub-position dynamic structural characteristic analysis and sub-position static structural analysis on the rudder wing to obtain a structural damage value of a corresponding part in a corresponding inspection period, and carrying out sub-position and sub-assembly platform structural characteristic analysis on the rudder wing, so that the estimated numerical value representing the structural damage degree of the corresponding part in the rudder wing is accurate enough, and the high precision of automatic inspection on the rudder wing is further ensured.
Example 5:
on the basis of embodiment 4, a first analysis module, with reference to fig. 5, comprises:
the decomposition unit is used for carrying out part decomposition on the dynamic structure frame corresponding to the dynamic rudder wing model based on each structural unit contained in the structural unit gradient list to obtain a plurality of linkage part frames corresponding to each structural unit;
the analysis unit is used for generating basic motion vectors of corresponding parts based on the motion amplitude and the motion direction of the parts corresponding to the minimum structure units contained in the linkage part frame in the dynamic process, and taking the mean value of the basic motion vectors of all the parts contained in the linkage part frame as the corresponding linkage motion vector;
the calculating unit is used for calculating a first deviation value of the corresponding part based on a rate characteristic value curve of the corresponding part in a dynamic process and a corresponding standard rate characteristic value curve;
and the evaluation unit is used for calculating a second deviation value between each linkage motion vector and the standard linkage motion vector of the corresponding linkage part frame, and calculating a first structural damage value of the corresponding part in the corresponding inspection period based on the first deviation value of the corresponding part and the second deviation values of all linkage part frames including the corresponding part.
In this embodiment, the gradient list of structural units is a list including a plurality of structural units distributed according to gradients, for example: a minimum structural unit (which is a structural unit corresponding to each part in the rudder wing), a second small structural unit (which is a structural unit formed by assembling two parts in the rudder wing), a third small structural unit (which is a structural unit formed by assembling three parts in the rudder wing), and the like.
In this embodiment, the structural unit is the total number of sites included in a single structure.
In this embodiment, based on each structural unit included in the structural unit gradient list, a dynamic structural frame corresponding to the dynamic rudder wing model is subjected to part decomposition, and a plurality of linkage part frames corresponding to each structural unit are obtained, that is:
performing part decomposition on a dynamic structure frame corresponding to the dynamic rudder wing model based on the minimum structure unit to obtain a plurality of linkage part frames corresponding to the minimum structure unit (wherein each linkage part frame only comprises one part in the rudder wing);
performing part decomposition on the dynamic structure frame corresponding to the dynamic rudder wing model based on a second small structure unit to obtain a plurality of linkage part frames corresponding to the second small structure unit (wherein each linkage part frame only comprises two parts in the rudder wing);
performing part decomposition on the dynamic structure frame corresponding to the dynamic rudder wing model based on the third small structure unit to obtain a plurality of linkage part frames corresponding to the third small structure unit (wherein each linkage part frame only comprises three parts in the rudder wing)
And so on.
In this embodiment, the linkage part frame is a part frame that includes the total number of parts included in the corresponding structural unit and corresponds to each structural unit obtained by performing part decomposition on the dynamic structural frame corresponding to the dynamic rudder wing model based on each structural unit included in the structural unit gradient list.
In this embodiment, the motion amplitude is the motion displacement of the middle part of the rudder wing in the dynamic process.
In this embodiment, the moving direction is the moving direction of the middle part of the rudder wing in the dynamic process.
In this embodiment, the basic motion vector is determined by taking the motion amplitude of the corresponding portion in the dynamic process as a mode of the vector and taking the corresponding motion direction as the direction of the vector.
In this embodiment, the linkage motion vector is the mean of the basic motion vectors of all the positions included in the linkage position frame.
In this embodiment, calculating a first deviation value of the corresponding portion based on the rate characteristic curve of the corresponding portion in the dynamic process and the corresponding standard rate characteristic curve includes:
determining the real-time movement rate of each part in the dynamic process, generating a corresponding real-time rate curve based on the real-time movement rate, aligning the real-time rate curves of each part contained in all linkage part frames containing the corresponding part, and obtaining a first alignment result;
based on the first alignment result, carrying out alignment addition and averaging processing on the real-time speed curve of each part contained in all the linkage part frames containing the corresponding part to obtain a speed characteristic value curve of the corresponding part;
acquiring a standard rate characteristic value curve of a corresponding part, and calculating a first deviation value between the rate characteristic value curve of the corresponding part and the corresponding standard rate characteristic value curve, wherein the method comprises the following steps:
aligning the rate characteristic value curve and the standard rate characteristic value curve to obtain a second alignment result;
aligning the linear function curve of the rate characteristic value curve with the linear function curve of the standard rate characteristic value curve to obtain a third alignment result;
calculating a first deviation value between the rate characteristic value curve of the corresponding position and the corresponding standard rate characteristic value curve based on the second alignment result and the third alignment result, and the method comprises the following steps:
in the formula (I), the compound is shown in the specification,
a first deviation value between the rate characterizing value curve of the corresponding site and the corresponding standard rate characterizing value curve,
is a logarithmic function with a base 10,
the total number of points contained in the rate indicator curve for the corresponding site or the corresponding standard rate indicator curve,
for the rate characterizing value curve of the corresponding site or the second contained in the corresponding standard rate characterizing value curve
The point of the light beam is the point,
the first included in the rate characterizing value curve for the corresponding site
The magnitude of the point(s) is,
for the corresponding standard rate characterizing value curve
The magnitude of the point(s) is,
a first order function curve included in the rate characteristic value curve for the corresponding site
The magnitude of the point(s) is,
first order function curve of corresponding standard rate characteristic value curve
The amplitude of the points;
for example,
is a number of 3, and the number of the carbon atoms is 3,
sequentially comprises 9 parts, 18 parts and 27 parts,
the number of the components is 10, 20 and 30,
sequentially comprises 9, 9 and 9 in turn,
10, 10 and 10 in sequence, then
Is 0.04139.
In this embodiment, the second deviation value is a deviation value between the linked motion vector of the corresponding linked part frame and the corresponding standard linked motion vector, which is:
in the formula (I), the compound is shown in the specification,
a second deviation value between the interlocking motion vector of the corresponding interlocking part frame and the corresponding standard interlocking motion vector,
is a linkage motion vector of the corresponding linkage part frame,
is a standard linkage motion vector corresponding to the linkage part frame,
is the Euclidean distance between the linkage motion vector of the corresponding linkage part frame and the standard linkage motion vector,
a model of a standard linkage motion vector corresponding to the linkage position frame;
for example,
is a number of 10 and is provided with,
is 20, then
Is 0.5.
The ratio of the difference between the corresponding linkage motion vector and the standard linkage motion vector of the corresponding linkage position frame to the standard linkage motion vector.
In this embodiment, the standard linkage motion vector is a linkage motion vector corresponding to the linkage portion frame in a state without structural damage.
In this embodiment, the first structural damage value of the corresponding portion in the corresponding inspection cycle is calculated based on the first deviation value of the corresponding portion and the second deviation values of all the interlocking portion frames including the corresponding portion, and is:
and taking the average value of the first deviation value of the corresponding part and the second deviation values of all the linkage part frames containing the corresponding part as the first structural damage value of the corresponding part in the corresponding test period.
The beneficial effects of the above technology are: calculating a vector of a linkage operation process of linkage part frames of different structural units containing corresponding parts based on a mean value of basic motion vectors of all parts contained in the linkage part frames of different structural units containing the corresponding parts in the rudder wing, determining deviation values of the corresponding parts in the dynamic process of the rudder wing in a motion direction and a motion amplitude caused by self structural damage and structural damage of other linkage parts connected with the self structural damage based on a difference value between the linkage motion vectors and corresponding standard linkage vectors, and determining a rate deviation of the corresponding parts in the dynamic process by calculating a difference value of a rate characteristic value curve of the corresponding parts in the dynamic process and a corresponding standard rate characteristic value curve; the dynamic analysis of the structure characteristics of the rudder wing is realized according to the motion direction, the motion amplitude and the motion speed angle of different parts in the rudder wing in the dynamic process, the influence of the linkage structure between different parts in the rudder wing on the evaluation of the structure damage value of the corresponding part is also considered through the analysis of the linkage part frames of different structural units, and the high precision of the evaluation result of the structure characteristic damage of the rudder wing is further ensured to a greater extent.
Example 6:
on the basis of embodiment 4, the second analysis module, with reference to fig. 6, comprises:
the frame extraction unit is used for acquiring a standard static posture of each part in a standard inspection state, and acquiring a static local frame of the corresponding part and a complete rudder wing static frame corresponding to the static local frame in the dynamic rudder wing model based on the standard static posture;
the coordinate determination unit is used for unifying the complete rudder wing static frame under a preset coordinate system to obtain a coordinate unification result, and determining the current coordinate representation of the static local frame based on the coordinate unification result;
and the damage determining unit is used for acquiring the standard coordinate representation of the corresponding standard static posture, and taking a third deviation value of the current coordinate representation and the standard coordinate representation as a second structural damage value of the corresponding part in the corresponding inspection period.
In this embodiment, the standard inspection state is a standard state corresponding to the position included in the rudder wing which needs to be automatically inspected in a static state.
In this embodiment, the standard static posture is a posture corresponding to the corresponding part in the standard verification state.
In this embodiment, the static local frame is a local frame corresponding to a position of the rudder wing acquired from the dynamic rudder wing model when the corresponding position is in a corresponding standard static attitude.
In this embodiment, the complete rudder wing static frame is a complete structural frame corresponding to the rudder wing when the corresponding portion corresponds to the standard static attitude.
In this embodiment, the coordinate unification result is a result obtained after unifying the complete rudder wing static frame in the preset coordinate system, and the result includes coordinate values of each point in the complete rudder wing static frame in the preset coordinate system.
In this embodiment, the current coordinate representation is a coordinate value of each point in the static local frame in the preset coordinate system.
In this embodiment, the standard coordinate representation is a coordinate value of each point in the static local frame corresponding to the corresponding portion in the non-structural-damage state in the corresponding standard static posture in the preset coordinate system.
In this embodiment, the third deviation value is a deviation value between the current coordinate representation and the standard coordinate representation, that is, a ratio of a difference between a coordinate value of each point in the current coordinate representation and a corresponding coordinate value of the corresponding point in the standard coordinate representation to a corresponding coordinate value of the corresponding point in the standard coordinate representation.
The beneficial effects of the above technology are: and determining the structural damage degree of each part in the rudder wing evaluated in the static state by calculating the deviation value of the current coordinate representation of the static local frame corresponding to each part in the standard inspection state and the corresponding standard coordinate representation.
Example 7:
on the basis of the embodiment 1, the rule analysis end, referring to fig. 7, includes:
the result sorting module is used for sorting the structural damage values of the corresponding parts based on the inspection period corresponding to the corresponding dynamic rudder wing model to obtain the evaluation evolution result of the corresponding parts;
and the evolution analysis module is used for analyzing the damage evolution rule of the corresponding part based on the evaluation evolution result.
In this embodiment, the evaluation and evolution result is a sequencing sequence of the structural damage values obtained by sequencing the structural damage values of the corresponding portions based on the inspection period corresponding to the corresponding dynamic rudder wing model.
The beneficial effects of the above technology are: the structure damage values of the corresponding parts are sequenced based on the corresponding test periods of the corresponding dynamic rudder wing models to obtain evaluation evolution results of the corresponding parts, the evaluation evolution results are analyzed to obtain damage evolution rules of the corresponding parts, a basis is provided for subsequently determining test conditions of the corresponding parts in the rudder wing, the test conditions are determined for the parts of the rudder wing, and then the automatic test precision of the rudder wing is further improved.
Example 8:
on the basis of embodiment 7, the evolution analysis module, with reference to fig. 8, comprises:
the curve generation unit is used for generating a corresponding structural damage value change curve based on the structural damage value sequence contained in the evaluation evolution result;
and the rule determining unit is used for determining a corresponding structural damage value change function based on the structural damage value change curve and taking the structural damage value change function as a corresponding damage evolution rule.
In this embodiment, the structural damage value sequence is a sequence obtained by sorting the structural damage values of the corresponding portions based on the inspection period corresponding to the corresponding dynamic rudder wing model included in the evaluation evolution result.
In this embodiment, the structural damage value change curve is a curve that is generated based on the structural damage value sequence and guarantees the change of the structural damage value with time.
In this embodiment, the structural damage value change function is a function describing a structural damage value change curve.
The beneficial effects of the above technology are: the function corresponding to the structural damage value change curve generated based on the structural damage value sequence contained in the evaluation evolution result is determined, so that the damage evolution rule of the corresponding part is accurately represented by the function, and a basis is further provided for the subsequent generation of the inspection conditions of different parts in the rudder wing and the automatic inspection of the inspection conditions.
Example 9:
on the basis of embodiment 1, the plan determination end, referring to fig. 9, includes:
the first determining module is used for determining a maintenance plan of the corresponding part based on the corresponding damage evolution rule when the latest structure damage value accords with the damage evolution rule of the corresponding part;
the second determination module is used for determining a maintenance plan of the corresponding part based on the latest structure damage value and the damage evolution rule of the corresponding part when the latest structure damage value does not accord with the damage evolution rule of the corresponding part;
and the comprehensive generation module is used for generating a total maintenance plan based on the maintenance plan of each part.
In this embodiment, when the latest structural damage value conforms to the damage evolution law of the corresponding portion, it is:
determining a standard structure damage value corresponding to the current inspection period based on a structure damage value change function corresponding to the damage evolution rule, judging whether the difference value between the latest structure damage value and the standard structure damage value is smaller than a difference threshold value, and if so, judging that the latest structure damage value accords with the damage evolution rule of the corresponding part;
otherwise, judging that the latest structural damage value does not accord with the damage evolution rule of the corresponding part.
In this embodiment, the maintenance plan is a plan that determines a maintenance cycle and a maintenance project including a corresponding portion based on the corresponding damage evolution law.
In this embodiment, determining the maintenance plan of the corresponding portion based on the latest structural damage value and the damage evolution rule of the corresponding portion includes:
taking the latest maintenance cycle as the maintenance cycle of the corresponding part;
determining maintenance items of the corresponding parts based on the latest structural damage values of the corresponding parts and the latest structural damage value-maintenance item list;
and determining a maintenance plan of the corresponding part based on the corresponding maintenance period and the maintenance project.
In this embodiment, the overall maintenance plan is an overall plan including maintenance plans for each portion of the rudder wing.
The beneficial effects of the above technology are: whether the latest structural damage value of the corresponding part accords with the damage evolution rule of the corresponding part or not can be judged, whether the structural damage of the corresponding part in the normal aging range occurs or not can be judged, if yes, the initial maintenance plan of the corresponding part is adjusted based on the latest structural damage value, otherwise, the initial maintenance plan of the corresponding part determined based on the damage evolution rule is kept, the maintenance plan of different parts in the rudder wing is adjusted in real time according to the structural damage assessment result, and the maintenance efficiency and the maintenance effect are improved.
Example 10:
on the basis of embodiment 9, the first determining module, referring to fig. 10, includes:
the maintenance determining unit is used for determining a maintenance period and a corresponding maintenance item of the corresponding part based on the corresponding damage evolution rule when the latest structure damage value accords with the damage evolution rule of the corresponding part;
and a plan determining unit for determining a maintenance plan of the corresponding part based on the maintenance period of the corresponding part and the corresponding maintenance item.
In this embodiment, determining the maintenance cycle and the corresponding maintenance item of the corresponding portion based on the corresponding damage evolution law includes:
determining maintenance items to be executed when the corresponding parts reach different preset structural damage values based on the preset structural damage value-maintenance item list;
and determining the time when the corresponding part reaches different preset structure damage values based on the damage evolution rule, taking the event as a corresponding maintenance period, and taking the maintenance item corresponding to the preset structure damage value as the maintenance item to be executed in the corresponding maintenance period.
The beneficial effects of the above technology are: when the latest structural damage value of the corresponding part accords with the corresponding damage evolution rule, the maintenance period and the corresponding maintenance project of the corresponding part are determined based on the damage evolution rule, so that the maintenance plans of different parts in the rudder wing are made in a targeted manner according to the structural damage evaluation result, and the maintenance efficiency and the maintenance effect are improved.
It will be apparent to those skilled in the art that various changes and modifications may be made in the present invention without departing from the spirit and scope of the invention. Thus, if such modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is also intended to include such modifications and variations.
Claims (10)
1. The utility model provides a full automatic check system of aviation rudder wing intelligence based on infrared induction principle which characterized in that includes:
the model simulation end is used for carrying out model simulation based on the infrared video of the rudder wing to obtain a dynamic rudder wing model;
the damage evaluation terminal is used for carrying out sub-position dynamic structure characteristic analysis and sub-position static structure characteristic analysis on the rudder wing based on the dynamic rudder wing model to obtain a structural damage value of each part in a corresponding inspection period;
the rule analysis end is used for obtaining an evaluation evolution result of the corresponding part based on the structural damage values of different inspection periods and analyzing a damage evolution rule of the corresponding part based on the evaluation evolution result;
and the plan determining end is used for determining a total maintenance plan based on the damage evolution rule and the latest structure damage value.
2. The intelligent full-automatic inspection system for aviation rudder wings based on the infrared induction principle as claimed in claim 1, wherein the model simulation terminal comprises:
the video acquisition module is used for acquiring infrared local monitoring videos of the rudder wing at a plurality of monitoring angles based on the inspection period;
the alignment splicing module is used for aligning and splicing time sequences of all infrared local monitoring videos based on the spatial distribution relation of the monitoring angles to obtain the infrared video of the rudder wing;
and the module simulation module is used for carrying out model simulation on the rudder wing based on the infrared video to obtain a dynamic rudder wing model.
3. The intelligent full-automatic inspection system for aviation rudder wings based on the infrared induction principle as claimed in claim 2, wherein the video acquisition module comprises:
a cycle determination unit for acquiring an automatic inspection plan and determining an inspection cycle based on the automatic inspection plan;
and the video acquisition unit is used for controlling the plurality of infrared monitoring devices to carry out infrared monitoring on the rudder wing structure in the inspection period so as to obtain infrared local monitoring videos of a plurality of monitoring angles.
4. The intelligent automatic inspection system for aviation rudder wings based on the infrared induction principle as claimed in claim 1, wherein the damage evaluation terminal comprises:
the first analysis module is used for carrying out sub-position dynamic structure characteristic analysis on the rudder wing based on the dynamic rudder wing model to obtain a first structure damage value corresponding to each position in each inspection period;
the second analysis module is used for performing sub-position static structure analysis on the rudder wing based on the dynamic rudder wing model to obtain a second structure damage value corresponding to each position in each inspection period;
and the result summarizing module is used for taking the average value of the first structural damage value and the second structural damage value of the corresponding part in the corresponding inspection period as the structural damage value of the corresponding part in the corresponding inspection period.
5. The intelligent full-automatic inspection system for aviation rudder wings based on the infrared induction principle as claimed in claim 4, wherein the first analysis module comprises:
the decomposition unit is used for carrying out part decomposition on the dynamic structure frame corresponding to the dynamic rudder wing model based on each structure unit contained in the structure unit gradient list to obtain a plurality of linkage part frames corresponding to each structure unit;
and the calculating unit is used for calculating a first structural damage value of the corresponding part in the corresponding inspection period based on the speed characteristic value curve of the corresponding part in the dynamic process and the linkage motion vector of each linkage part frame containing the corresponding part.
6. The intelligent full-automatic inspection system for aviation rudder wings based on the infrared induction principle as claimed in claim 4, wherein the second analysis module comprises:
the frame extraction unit is used for acquiring a static local frame of a corresponding part in the dynamic rudder wing model based on the standard static posture of each part in the standard inspection state and determining the current coordinate representation of the static local frame;
and the damage determining unit is used for acquiring the standard coordinate representation of the corresponding standard static posture, and taking a third deviation value of the current coordinate representation and the standard coordinate representation as a second structural damage value of the corresponding part in the corresponding inspection period.
7. The intelligent full-automatic inspection system for aviation rudder wings based on the infrared induction principle as claimed in claim 1, wherein the law analysis terminal comprises:
the result sorting module is used for sorting the structural damage values of the corresponding parts based on the inspection period corresponding to the corresponding dynamic rudder wing model to obtain the evaluation evolution result of the corresponding parts;
and the evolution analysis module is used for analyzing the damage evolution rule of the corresponding part based on the evaluation evolution result.
8. The intelligent full-automatic aviation rudder wing inspection system based on the infrared induction principle as claimed in claim 7, wherein the evolution analysis module comprises:
the curve generation unit is used for generating a corresponding structural damage value change curve based on the structural damage value sequence contained in the evaluation evolution result;
and the rule determining unit is used for determining a corresponding structural damage value change function based on the structural damage value change curve and taking the structural damage value change function as a corresponding damage evolution rule.
9. The intelligent full-automatic inspection system for the aviation rudder wing based on the infrared induction principle as claimed in claim 1, wherein the plan determination end comprises:
the first determining module is used for determining a maintenance plan of the corresponding part based on the corresponding damage evolution rule when the latest structure damage value accords with the damage evolution rule of the corresponding part;
the second determination module is used for determining a maintenance plan of the corresponding part based on the latest structure damage value and the damage evolution rule of the corresponding part when the latest structure damage value does not accord with the damage evolution rule of the corresponding part;
and the comprehensive generation module is used for generating a total maintenance plan based on the maintenance plan of each part.
10. The intelligent full-automatic inspection system for the aviation rudder wing based on the infrared induction principle as claimed in claim 9, wherein the first determination module comprises:
the maintenance determining unit is used for determining a maintenance period and a corresponding maintenance item of the corresponding part based on the corresponding damage evolution rule when the latest structure damage value accords with the damage evolution rule of the corresponding part;
and a plan determining unit for determining a maintenance plan of the corresponding part based on the maintenance period of the corresponding part and the corresponding maintenance item.
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