CN106355007B - A kind of aircraft vacant lot damage determination method - Google Patents
A kind of aircraft vacant lot damage determination method Download PDFInfo
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- CN106355007B CN106355007B CN201610766355.0A CN201610766355A CN106355007B CN 106355007 B CN106355007 B CN 106355007B CN 201610766355 A CN201610766355 A CN 201610766355A CN 106355007 B CN106355007 B CN 106355007B
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Abstract
A kind of determination method of the present invention relates to aircraft vacant lot damage, belongs to fatigue life test field.Loading spectrum curve discrete is gone out into multiple data points first, secondly, determine the relationship between the accumulation frequency and stress, then the exponential equation between the fitting accumulation frequency and stress, finally determines the accumulation frequency of primary ground vacant lot flight, and stress value is calculated according to exponential equation, and then the damage of ground vacant lot can be determined according to stress value, general class aircraft proposed by the invention vacant lot damage determination method, theoretical foundation understands, step is easy, realizes that automation calculates convenient for computer programming.It can be used for quickly and accurately determining the ground vacant lot circulation damage of each key position of aircraft.It is obtained under the premise of Certification requirement meeting, with can be widely applied to various general class aircrafts the determination of vacant lot damage.
Description
Technical field
The invention belongs to fatigue life test fields, and in particular to a kind of aircraft vacant lot damage determination method.
Background technique
General-purpose aircraft is the machine that quantity is most, model is most in whole type of airplane, including baby plane, large-scale whirlpool
Wheel and propeller aeroplane etc..According to the requirement of the 571st article and 572 articles of the portion airworthiness regulation CCAR23 of civil aviaton, general class aircraft should be carried out
Fatigue strength inspection or fail safety strength checking.
The basic skills and loading spectrum that fatigue strength inspection is given in seaworthiness consultation notification AC23-13A are (containing fitful wind, machine
Move, slide and land four task segments), and propose the influence for being considered as the damage of ground vacant lot.The damage of ground vacant lot, which refers to, once to fly
Damage caused by primary load cycle occurs in row, by taking airfoil root as an example, the damage of ground vacant lot, which usually accounts for, always to be damaged
Therefore 60%-90% must determine the damage of ground vacant lot in the fatigue strength inspection to structure.
Existing seaworthiness clause and consultation notification not with regard to how from fitful wind, it is motor-driven, slide and four task segment load of landing
How definitely vacant lot damage is provided and is clearly stated in the transcendental number accumulation frequency of spectrum.In actual analysis of fatigue example, do not have
A kind of effective method for accurately determining vacant lot damage.
Summary of the invention
To solve the above-mentioned problems, The present invention gives a kind of with accurately and effectively calculating general class aircraft vacant lot damages
Determine method.
Aircraft of the present invention vacant lot damage determination method mainly comprise the steps that
S1, gust load spectral curve, maneuver load spectral curve, taxing load spectral curve and landing load set a song to music respectively
The discrete multiple data points out of line, any data point include overload increment and accumulation two parameters of the frequency；
S2, according to overload increment and minimum stress between relationship and overload increment and maximum stress between relationship it is true
Make the relationship between the accumulation frequency and minimum stress and the relationship between the accumulation frequency and maximum stress；
Exponential equation between S3, the fitting accumulation frequency and minimum stress:
Wherein, when x is minimum stress, yminFor the corresponding accumulation frequency of minimum stress, ai、bi、ciFor yminExponential equation
In coefficient, i takes the integer between 1~4, be respectively used to indicate fitful wind, it is motor-driven, slide and four y of landingminExponential equation；
Meanwhile
Exponential equation between the fitting accumulation frequency and maximum stress:
Wherein, when x is maximum stress, ymaxFor the corresponding accumulation frequency of maximum stress, aj、bj、cjFor ymaxExponential equation
In coefficient, j takes the integer between 1~4, be respectively used to indicate fitful wind, it is motor-driven, slide and four y of landingmaxExponential equation；
S4, the accumulation frequency for determining the flight of primary ground vacant lot, seek x value when y=1, and the expression formula of the y and x are
So as to acquire vacant lot minimum stress, or
So as to acquire ground vacant lot maximum stress；
S5, according to described ground vacant lot minimum stress and described ground vacant lot maximum stress, definitely vacant lot is damaged.
Preferably, in the step S1, the data point number that any loading spectrum curve discrete goes out is no less than 5.
In above scheme preferably, in the step S2, under fitful wind or maneuvering condition, the overload increment and stress
Between relationship are as follows: minimum stress=motor-driven mean stress * (1- overload increment)；Maximum stress=motor-driven mean stress * (1+ mistake
Carry increment).
In above scheme preferably, as the flat winged 1g of extension set, the motor-driven mean stress is 37.9MPa.
In above scheme preferably, in the step S2, under sliding state, between overload increment and the stress
Relationship are as follows: minimum stress=slide mean stress -35.5* overload increment；Maximum stress=slide mean stress+35.5* overload
Increment.
In above scheme preferably, the mean stress that slides is 5.86MPa.
In above scheme preferably, in the step S2, under landing state, between overload increment and the stress
Relationship are as follows: when aircraft sinks or the rate of climb is not less than 1 foot/s, minimum stress=landing recycles mean stress -8.27* (1
+ sinking or the rate of climb), maximum stress=landing circulation mean stress+8.27* (1+ sinks or the rate of climb) is otherwise, minimum
Stress=landing recycles mean stress -16.5MPa, and maximum stress=landing recycles mean stress+16.5MPa.
In above scheme preferably, the landing circulation mean stress is 19.0MPa.
General class aircraft proposed by the invention vacant lot damage determination method, theoretical foundation understands, step is easy, just
Realize that automation calculates in computer programming.It can be used for quickly and accurately determining the ground vacant lot circulation damage of each key position of aircraft
Wound.
General class aircraft proposed by the invention vacant lot damage determination method, be before meeting Certification requirement
It puts, with can be widely applied to various general class aircrafts the determination of vacant lot damage.
Detailed description of the invention
The flow chart of one preferred embodiment of the determination method of Fig. 1 for aircraft of the present invention vacant lot damage.
Fig. 2 is that the gust load of embodiment illustrated in fig. 1 of the present invention composes discrete data point minimum stress, maximum stress and accumulation
Frequency relation schematic diagram.
Fig. 3 is that the taxing load of embodiment illustrated in fig. 1 of the present invention composes discrete data point minimum stress, maximum stress and accumulation
Frequency relation schematic diagram.
Fig. 4 be fitful wind, it is motor-driven, slide, land each loading spectrum corresponding to minimum stress at different levels per hour, maximum stress
Accumulate each coefficient for being fitted to exponential equation of the frequency.
Specific embodiment
To keep the purposes, technical schemes and advantages of the invention implemented clearer, below in conjunction in the embodiment of the present invention
Attached drawing, technical solution in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label indicate same or similar element or element with the same or similar functions.Described embodiment is the present invention
A part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to use
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiments of the present invention, ordinary skill people
Member's every other embodiment obtained without creative efforts, shall fall within the protection scope of the present invention.Under
Face is described in detail the embodiment of the present invention in conjunction with attached drawing.
In the description of the present invention, it is to be understood that, term " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom" "inner", "outside" is based on attached drawing institute
The orientation or positional relationship shown, is merely for convenience of description of the present invention and simplification of the description, rather than the dress of indication or suggestion meaning
It sets or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as protecting the present invention
The limitation of range.
As shown in Figure 1, aircraft of the present invention vacant lot damage determination method mainly comprise the steps that
S1, gust load spectral curve, maneuver load spectral curve, taxing load spectral curve and landing load set a song to music respectively
The discrete multiple data points out of line, any data point include overload increment and accumulation two parameters of the frequency；
S2, according to overload increment and minimum stress between relationship and overload increment and maximum stress between relationship it is true
Make the relationship between the accumulation frequency and minimum stress and the relationship between the accumulation frequency and maximum stress；
Exponential equation between S3, the fitting accumulation frequency and minimum stress:
Wherein, when x is minimum stress, yminFor the corresponding accumulation frequency of minimum stress, ai、bi、ciFor yminExponential equation
In coefficient, i takes the integer between 1~4, be respectively used to indicate fitful wind, it is motor-driven, slide and four y of landingminExponential equation；
Meanwhile
Exponential equation between the fitting accumulation frequency and maximum stress:
Wherein, when x is maximum stress, ymaxFor the corresponding accumulation frequency of maximum stress, aj、bj、cjFor ymaxExponential equation
In coefficient, j takes the integer between 1~4, be respectively used to indicate fitful wind, it is motor-driven, slide and four y of landingmaxExponential equation；
S4, the accumulation frequency for determining the flight of primary ground vacant lot, the accumulation frequency of the primary ground vacant lot flight are as follows: work as y=1
When x value, the expression formula of the y and x is
So as to acquire vacant lot minimum stress, or
So as to acquire ground vacant lot maximum stress；
S5, according to described ground vacant lot minimum stress and described ground vacant lot maximum stress, definitely vacant lot is damaged.
In the present embodiment step S1, such as by annex one provides in seaworthiness consultation notification AC23-13A fitful wind, motor-driven, sliding
Row, landing load spectral curve difference it is discrete go out several points, by taking fitful wind as an example, from attached drawing along abscissa interval it is identical away from
It is worth from taking out 10, and corresponding coordinate is converted into the accumulation frequency corresponding to overload increments at different levels per hour, first two columns in Fig. 2
Give corresponding data.
It should be noted that for the accuracy for guaranteeing subsequent step curve matching, the number of any loading spectrum curve discrete out
Strong point number should be no less than 5.The present embodiment except taxing load spectrum in it is discrete go out 5 points in addition to, excess-three curve from
Shed 10 data points.
In the present embodiment, step S2 is used to determine the accumulation frequency and stress according to the relationship between overload increment and stress
Between relationship, overloading the relationship between increment and stress is minimum stress=mean stress-stress amplitude；Maximum stress=flat
Equal stress+stress amplitude, mainly according to the limited of four load spectral curves of general class aircraft and aircraft any structure
First stress analysis result determines.Four states are illustrated respectively below.
Relationship in the step S2, under fitful wind or maneuvering condition, between the overload increment and stress are as follows: minimum is answered
Power=motor-driven mean stress * (1- overloads increment)；Maximum stress=motor-driven mean stress * (1+ overloads increment).
The stress analysis result at the undercarriage position of, single-shot general according to certain, nonpressurized cabin aircraft: when aircraft puts down winged 1g,
Corresponding average flight stress is 37.9MPa, and fitful wind and motor-driven stress amplitude are 1g × Δ g；Δ g is to overload increment.
The minimum stress and maximum stress being calculated are as shown in next two columns in attached drawing 2.It is understood that aircraft is in Y direction
Overload, the ratio being equal between airplane ascensional force (Y) and aircraft gravity (G), i.e. ny=Y/G, when often claiming flat fly, ny=1 flies to be flat
1g。
Relationship under sliding state, between the overload increment and stress are as follows: minimum stress=slide mean stress-
35.5* overloading increment；Maximum stress=slide mean stress+35.5* overload increment.It is stress that wherein 35.5*, which overloads increment,
Amplitude.
The above-mentioned mean stress that slides is 5.86MPa.5 discrete data points of sliding state and corresponding minimum stress and most
Big stress is as shown in Figure 3.
In the step S2, under landing state, it is described overload increment and stress between relationship are as follows: when aircraft sink or
When the rate of climb is not less than 1 foot/s, minimum stress=landing circulation mean stress -8.27* (1+ sinks or the rate of climb), most
Big stress=landing circulation mean stress+8.27* (1+ sinks or the rate of climb), otherwise, minimum stress=landing circulation is average
Stress -16.5MPa, maximum stress=landing recycle mean stress+16.5MPa.Subsidence velocity unit is foot/s.
Above-mentioned landing circulation mean stress is 19.0MPa.
Using minimum stress as x coordinate, to accumulate the frequency as y-coordinate, be fitted respectively fitful wind, it is motor-driven, slide and land every
The exponential equation of hour minimum stresses at different levels and the accumulation frequency:
Wherein, when x is minimum stress, yminFor the corresponding accumulation frequency of minimum stress, ai、bi、ciFor yminExponential equation
In coefficient, i takes the integer between 1~4, be respectively used to indicate fitful wind, it is motor-driven, slide and four y of landingminExponential equation；
Meanwhile using maximum stress as x coordinate, to accumulate the frequency as y-coordinate, be fitted respectively fitful wind, it is motor-driven, slide and land per hour
The exponential relationship of maximum stresses at different levels and the accumulation frequency:
Wherein, when x is maximum stress, ymaxFor the corresponding accumulation frequency of maximum stress, aj、bj、cjFor ymaxExponential equation
In coefficient, j takes the integer between 1~4, be respectively used to indicate fitful wind, it is motor-driven, slide and four y of landingmaxExponential equation.
Fig. 4 gives after over-fitting, obtained fitful wind, it is motor-driven, slide, each loading spectrum that lands is with minimums at different levels per hour
The each coefficient for being fitted to exponential equation of the accumulation frequency corresponding to stress, maximum stress.To obtain four yminIndex side
Journey and four ymaxExponential equation.
Finally, determine the accumulation frequency of primary ground vacant lot flight, definition (the flight hair every time of base area vacant lot stress damage
Damage caused by raw primary Cyclic Stress), seek x value when y=1, the expression formula of the y and x are
So as to acquire vacant lot minimum stress, or
So as to acquire ground vacant lot maximum stress.
In the present embodiment, it is -9.1MPa that using Matlab software, reverse, which obtains ground vacant lot minimum stress, respectively, and ground vacant lot is maximum
Stress is 71.5MPa.
It, can be according to the annex of seaworthiness consultation notification AC23-13A after definitely vacant lot minimum stress and maximum stress
Definitely vacant lot damage is 2.0533 × 10 to S-N Curve in 2-6/ hour.
General class aircraft proposed by the invention vacant lot damage determination method, theoretical foundation understands, step is easy, just
Realize that automation calculates in computer programming.It can be used for quickly and accurately determining the ground vacant lot circulation damage of each key position of aircraft
Wound.
General class aircraft proposed by the invention vacant lot damage determination method, be before meeting Certification requirement
It puts, with can be widely applied to various general class aircrafts the determination of vacant lot damage.
Finally it is noted that the above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations.To the greatest extent
Present invention has been described in detail with reference to the aforementioned embodiments for pipe, those skilled in the art should understand that: it is still
It is possible to modify the technical solutions described in the foregoing embodiments, or part of technical characteristic is equally replaced
It changes；And these are modified or replaceed, the essence for technical solution of various embodiments of the present invention that it does not separate the essence of the corresponding technical solution
Mind and range.
Claims (8)
1. a kind of aircraft vacant lot damage determination method characterized by comprising
S1, respectively by gust load spectral curve, maneuver load spectral curve, taxing load spectral curve and landing load spectral curve from
Shed multiple data points, and any data point includes overload increment and accumulation two parameters of the frequency；
S2, it is determined according to the relationship between overload increment and minimum stress and the relationship between overload increment and maximum stress
Accumulate the relationship between the relationship between the frequency and minimum stress and the accumulation frequency and maximum stress；
Exponential equation between S3, the fitting accumulation frequency and minimum stress:
Wherein, when x is minimum stress, yminFor the corresponding accumulation frequency of minimum stress, ai、bi、ciFor yminIn exponential equation
Coefficient, i take the integer between 1~4, be respectively used to indicate fitful wind, it is motor-driven, slide and four y of landingminExponential equation；Together
When,
Exponential equation between the fitting accumulation frequency and maximum stress:
Wherein, when x is maximum stress, ymaxFor the corresponding accumulation frequency of maximum stress, aj、bj、cjFor ymaxIn exponential equation
Coefficient, j take the integer between 1~4, be respectively used to indicate fitful wind, it is motor-driven, slide and four y of landingmaxExponential equation；
S4, the accumulation frequency for determining the flight of primary ground vacant lot, seek x value when y=1, and the expression formula of the y and x are
So as to acquire vacant lot minimum stress, or
So as to acquire ground vacant lot maximum stress；
S5, according to described ground vacant lot minimum stress and described ground vacant lot maximum stress, definitely vacant lot is damaged.
2. aircraft as described in claim 1 vacant lot damage determination method, it is characterised in that: it is any in the step S1
The data point number that loading spectrum curve discrete goes out is no less than 5.
3. aircraft as described in claim 1 vacant lot damage determination method, it is characterised in that: in the step S2, in battle array
Relationship under wind or maneuvering condition, between the overload increment and stress are as follows: minimum stress=motor-driven mean stress * (1- overload
Increment)；Maximum stress=motor-driven mean stress * (1+ overloads increment).
4. aircraft as claimed in claim 3 vacant lot damage determination method, it is characterised in that: as the flat winged 1g of extension set, institute
Stating motor-driven mean stress is 37.9MPa.
5. aircraft as described in claim 1 vacant lot damage determination method, it is characterised in that: in the step S2, in cunning
Relationship under row state, between the overload increment and stress are as follows: minimum stress=slide mean stress -35.5* overload increment；
Maximum stress=slide mean stress+35.5* overload increment.
6. aircraft as claimed in claim 5 vacant lot damage determination method, it is characterised in that: the mean stress that slides is
5.86MPa。
7. aircraft as described in claim 1 vacant lot damage determination method, it is characterised in that: in the step S2, rise
Relationship under drop state, between the overload increment and stress are as follows: when aircraft sinks or the rate of climb is not less than 1 foot/s,
Minimum stress=landing circulation mean stress -8.27* (1+ sinks or the rate of climb), maximum stress=landing recycles mean stress
+ 8.27* (1+ sinks or the rate of climb), otherwise, minimum stress=landing circulation mean stress -16.5MPa, maximum stress=
Lu Xunhuan mean stress+16.5MPa.
8. aircraft as claimed in claim 7 vacant lot damage determination method, it is characterised in that: landings is recycled and is averagely answered
Power is 19.0MPa.
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| CN112528478B (en) * | 2020-12-04 | 2022-07-12 | 中国航空工业集团公司成都飞机设计研究所 | Rapid compilation method for gust load spectrum of unmanned aerial vehicle |
| CN114428026A (en) * | 2021-12-30 | 2022-05-03 | 中国航空工业集团公司西安飞机设计研究所 | Fatigue analysis method for aircraft fuselage skin circumferential butt seam band plate connecting structure |
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