CN104075868B - Aerodynamic load loading method used for reliability tests on aircraft flap and slat system - Google Patents
Aerodynamic load loading method used for reliability tests on aircraft flap and slat system Download PDFInfo
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- CN104075868B CN104075868B CN201410246843.XA CN201410246843A CN104075868B CN 104075868 B CN104075868 B CN 104075868B CN 201410246843 A CN201410246843 A CN 201410246843A CN 104075868 B CN104075868 B CN 104075868B
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Abstract
The invention relates to an aerodynamic load loading method used for reliability tests on an aircraft flap and slat system. The method includes the concrete steps that first, aerodynamic loads of each slat in various flight states are obtained through wind tunnel tests or simulating calculation; second, according to the aerodynamic loads of each aircraft slat in various flight states, the resultant force of the aerodynamic loads on the face of each slat in various flight states is calculated; third, the resultant force of the aerodynamic loads on the face of each aircraft slat in various flight states is decomposed into a plurality of component forces, and the magnitudes and the directions of the component forces are obtained; fourth, the component forces in the third step are evenly distributed and loaded to the face of each slat through adhesive tape and a lever system. According to the aerodynamic load loading method, the aerodynamic loads of each slat in various states during a flight period are considered; the aerodynamic loads obtained through tests or simulation can be effectively converted in the loading modes achieved in the tests, and real aerodynamic loads are guaranteed.
Description
Technical field
The present invention relates to airplane component reliability test field, more particularly, to one kind are used for the aircraft flap, slat system can
Aerodynamic loading following loading method by property test.
Background technology
The aircraft flap, slat play an important role in the flight course of civil aircraft, and its effect mainly has two：One is to prolong
Air-flow on slow wing separates, and improves the critical angle of attack of aircraft so that aircraft just can occur stall under the bigger angle of attack；Two
It is the lift coefficient increasing wing.The aircraft flap, slat motion break down and the safety of aircraft can be produced a very large impact, very
To the harsh consequence causing fatal crass.
Based on the flap, slat system to the importance of Flight Safety it is desirable to the flap, slat system have higher reliability
Degree.And be to assess the existing flap, the reliability index of slat system design, and obtain the raising flap, the reliability of slat system
The corrective measure of level, the reliability growth realizing the flap, slat system is it is necessary to Chinese-style jacket with buttons down the front, slat system carry out fail-safe analysis.Pin
Fail-safe analysis to engineering goods, is primarily present two kinds of means at present, that is, emulate and test.But the restriction due to technical merit
With the complexity of large complicated engineering goods, current Reliablility simulation can not replace reliability test completely.
In prior art, if Chinese-style jacket with buttons down the front, slat system make a flight test, it is not only with high costs, and risk is larger, and one
Denier occur the flap, slat system can not normal folding and unfolding fault it is most likely that causing the major accident of air crash.It is thus desirable to one
Kind can carry out test method and the device of reliability test in ground Chinese-style jacket with buttons down the front, slat system；And it is directed to the examination of such engineering goods
Test, existing test method does not often account for slat aerodynamic loading Chinese-style jacket with buttons down the front, the impact of slat system performance, mould in flight course
The environmental condition intended is not true.
In view of drawbacks described above, creator of the present invention passes through long research and practice obtains this creation finally.
Content of the invention
It is an object of the invention to provide a kind of aerodynamic loading loading side for the aircraft flap, slat system reliability test
Method, in order to overcome above-mentioned technological deficiency.
For achieving the above object, the present invention provides a kind of aerodynamic loading for the aircraft flap, slat system reliability test
Loading method, this detailed process is：
Step a, obtains aerodynamic loading under each state of flight for the slat by wind tunnel test or simulation calculation；
Step b, according to aerodynamic loading under different flight state for the aircraft slat, calculates the slat wing under each state of flight
Face aerodynamic loading make a concerted effort；
Step c, according to each state of flight get off the plane slat aerofoil aerodynamic loading make a concerted effort, be broken down into several points
Power, obtains size and the direction of component；
Step d, by rubberized tape and lever system, the component of above-mentioned steps c uniformly and is loaded onto slat aerofoil.
Further, in above-mentioned steps a, the detailed process that aircraft slat aerofoil aerodynamic loading is asked for is：
Step a1, obtains all of operating mode in slat airborne period；
Step a2, according to aircraft slat folding and unfolding test requirements document, works out flight folding and unfolding operating mode；
Step a3, determines the aerodynamic loading of slat under each operating mode, each obtaining using wind tunnel test or numerical computations
Under operating mode, aerodynamic loading is in the distribution situation of aerofoil；
Obtain a file under each operating mode to be used for storing slat aerofoil aerodynamic loading, in file, each row of data are respectively the wing
Face node numbering, aerofoil node coordinate position, aerofoil node aerodynamic loading component in the X, Y, Z direction；
Step a4, judges whether whole operating modes calculate and completes, if not completing, proceeds slat aerodynamic loading meter
Calculate, if completing to calculate, arranging and numbering slat aerodynamic loading data file under each operating mode；
Wherein, slat is defined as Y-direction along spanwise, vertical lap seam thriving face direction is defined as X to slat aerofoil phase
Cut and vertical spanwise is defined as Z-direction.
Further, in above-mentioned steps b, the detailed process that aircraft slat aerofoil aerodynamic loading makes a concerted effort to ask for is：
Step b1, numbers slat aerodynamic loading data file according to the precedence of a test period；
Step b2, according to slat aerodynamic loading data under first operating mode, using the synthesis principle of power, lists four component
In X, Y, Z-direction, aerodynamic loading is made a concerted effort equation；
Step b3, according to slat aerodynamic loading data under first operating mode, is zero principle using pressure heart position moment, lists
In X, Y, Z-direction, aerodynamic loading is made a concerted effort moment equation；
Step b4, solves the equation of the first two steps, obtain respectively slat aerodynamic loading under this operating mode make a concerted effort size with
Direction and make a concerted effort slat aerofoil position coordinates；
Step b5, removes Y-direction power of making a concerted effort under each operating mode, the size of making a concerted effort of slat aerodynamic loading under this operating mode of record storage
With direction and make a concerted effort slat aerofoil position coordinates；
Step b6, judges that whole operating mode occlusometers are no at last and completes, as unfinished, then execution step b7, under carrying out successively
One operating mode makes a concerted effort to calculate, and such as completes, then execution step b8, terminates slat aerodynamic loading and makes a concerted effort to calculate.
Further, in above-mentioned steps c, the detailed process of aircraft slat aerofoil aerodynamic loading distribution is：
Step c1, marks point of resultant force position under whole operating modes on slat aerofoil；
Step c2, drafts the upper following of the parallelogram that load(ing) point surrounds, parallel with Y-axis, and closes under whole operating modes
The both sides of trail force load position, and this can not be at the deep camber leading edge of slat and thin trailing edge to parallel edges position；
Step c3, draft the parallelogram that load(ing) point surrounds another to parallel edges, by point of resultant force to parallel four
Two parallel with the Y-axis back gauge ratio of side shape is designated as a (a ＜ 1), and point of resultant force to parallelogram is right with another
Back gauge ratio is designated as b (b ＜ 1)；
Step c4, obtains a and b of whole point of resultant force；
Step c5, if being unsatisfactory for requiring, adjusts the opposite side of the parallel Y-axis of parallelogram of load(ing) point composition, if meeting
Require then to execute following step；
Step c6, if being unsatisfactory for requiring, adjusts another opposite side of the parallelogram of load(ing) point composition, if meet requiring,
Then execute following step；
Step c7, carries out the distribution that whole aerodynamic loadings are made a concerted effort；
Step c8, obtains four loaded load；
Step c9, arranges four load(ing) points with the power size in the wing flap test period and direction.
Further, in above-mentioned steps c8,
The load of lower four load(ing) points of each operating mode is respectively
Further, in above-mentioned steps d, the detailed process of aircraft slat aerofoil rubberized tape and lever system distribution is：
Step d1, chooses a load(ing) point；
Step d2, on the straight line of the parallel Y-axis of this load(ing) point, with this point as midpoint, two rubberized tapes are respectively installed on both sides,
This four rubberized tape positions should be uniformly in a quarter slat airfoil area that this load(ing) point is located；
Step d3, four rubberized tapes of here is installed lever system, connects lever system upper end using a cable wire, realize
Aerodynamic loading loads；
Step d4, judges whether the rubberized tape of four load(ing) points and lever system all install, such as non-installation,
Then execution step d5, continues to install successively, such as installation, then execution step d6, completes to load.
Compared with prior art the beneficial effects of the present invention is：In the aircraft flap of the present invention, slat system are tested, examine
Consider in airborne period, the aerodynamic loading under each state of slat；The aerodynamic loading of test or emulation acquisition can turn effectively
It is changed to the load mode realized in test, and ensure that the true of aerodynamic loading；The aerodynamic loading that slat is subject to passes through conversion
It is distributed in the load in some pieces of regions of aerofoil for several, under each operating mode of slat motion, the side of this several component
To identical all the time, it is easily controlled in test loading procedure and realizes, can be according to the flap, flap position in the flap, slat motion process
The parameters such as aerodynamic force size that real-time control is simulated, direction, the pressure heart；In test loads, by rubberized tape around load(ing) point
Distribution it is ensured that slat structure stress uniformly, the destruction that the excessive load not conformed to the actual conditions will not be produced and lead to testpieces.
Brief description
Fig. 1 is the flow chart of the aerodynamic loading loading method of reliability test of the present invention；
Fig. 2 a is aircraft slat aerofoil test of the present invention or emulation obtains aerodynamic loading distribution map；
Fig. 2 b makes a concerted effort distribution map for aircraft slat aerofoil aerodynamic loading of the present invention；
Fig. 2 c is the distribution map of aircraft four loading forces of slat aerofoil of the present invention；
Fig. 2 d is rubberized tape distribution map on aircraft slat aerofoil of the present invention；
The flow chart that Fig. 3 asks for for aircraft slat aerofoil aerodynamic loading of the present invention；
Fig. 4 makes a concerted effort the flow chart asked for for aircraft slat aerofoil aerodynamic loading of the present invention；
Fig. 5 is the flow chart of aircraft slat aerofoil aerodynamic loading distribution of the present invention；
The flow chart that Fig. 6 is aircraft slat aerofoil rubberized tape of the present invention and lever system distribution.
Specific embodiment
Below in conjunction with accompanying drawing, the above-mentioned He other technical characteristic of the present invention and advantage are described in more detail.
Refer to shown in Fig. 1, it is the flow chart of the aerodynamic loading loading method of reliability test of the present invention, this concrete mistake
Cheng Wei：
Step a, obtains aerodynamic loading under each state of flight for the slat by wind tunnel test or simulation calculation；
Step b, according to aerodynamic loading under different flight state for the aircraft slat, calculates the slat wing under each state of flight
Face aerodynamic loading make a concerted effort；
Step c, according to each state of flight get off the plane slat aerofoil aerodynamic loading make a concerted effort, be broken down into several points
Power, obtains size and the direction of component；
Step d, by rubberized tape and lever system, the component of above-mentioned steps c uniformly and is loaded onto slat aerofoil.
The embodiment of the present invention, slat is defined as Y-direction along spanwise, and vertical lap seam thriving face direction is defined as X to seam
Cautiously face is tangent and vertical spanwise is defined as Z-direction.
Aerodynamic loading is made a concerted effort to be divided into four component, the position of four component constitutes a parallelogram, will make with joint efforts
It is designated as a (a ＜ 1) with point to parallelogram two back gauge ratios parallel with Y-axis, by point of resultant force to parallel four sides
Shape be designated as b (b ＜ 1) with another opposite side distance ratio.
Incorporated by reference to shown in Fig. 2 a, 2b, 2c and 2d, it is respectively the test of aircraft slat aerofoil or emulation obtains aerodynamic loading and divides
Butut；Aircraft slat aerofoil aerodynamic loading is made a concerted effort distribution map；The distribution map of aircraft four loading forces of slat aerofoil；The aircraft slat wing
Rubberized tape distribution map on face.
Refer to shown in Fig. 3, its flow chart asked for for aircraft slat aerofoil aerodynamic loading of the present invention, this detailed process
For：
Step a1, obtains all of operating mode in slat airborne period；
Step a2, according to aircraft slat folding and unfolding test requirements document, works out flight folding and unfolding operating mode；
Step a3, determines the aerodynamic loading of slat under each operating mode, each obtaining using wind tunnel test or numerical computations
Under operating mode aerodynamic loading aerofoil distribution situation as shown in Figure 2 a, obtain under each operating mode a .dat file for storage stitch
Cautiously face aerodynamic loading, in file, each row of data respectively aerofoil node numbering, aerofoil node coordinate position, aerofoil node is pneumatic
Load component in the X, Y, Z direction；
Step a4, judges whether whole operating modes calculate and completes, if not completing, proceeds slat aerodynamic loading meter
Calculate, if completing to calculate, arranging and numbering slat aerodynamic loading .dat data file under each operating mode.
Refer to shown in Fig. 4, it is made a concerted effort the flow chart asked for for aircraft slat aerofoil aerodynamic loading of the present invention, this concrete mistake
Cheng Wei：
Step b1, numbers slat aerodynamic loading .dat data file according to the precedence of a test period；
Step b2, according to slat aerodynamic loading data under first operating mode, using the synthesis principle of power, lists four component
In X, Y, Z-direction, aerodynamic loading is made a concerted effort equation；
Step b3, according to slat aerodynamic loading data under first operating mode, is zero principle using pressure heart position moment, lists
In X, Y, Z-direction, aerodynamic loading is made a concerted effort moment equation；
Step b4, solves the equation of the first two steps, obtain respectively slat aerodynamic loading under this operating mode make a concerted effort size with
Direction and make a concerted effort slat aerofoil position coordinates；
Step b5, remove under this operating mode make a concerted effort Y-direction power, under this operating mode of record storage slat aerodynamic loading make a concerted effort size with
Direction and make a concerted effort slat aerofoil position coordinates；
Due to Y-direction power with respect to X and Z-direction power from the point of view of, very little, negligible.
Step b6, judges that whole operating mode occlusometers are no at last and completes, as unfinished, then execution step b7, under carrying out successively
One operating mode makes a concerted effort to calculate, and such as completes, then execution step b8, terminates slat aerodynamic loading and makes a concerted effort to calculate；All operating mode makes a concerted effort to divide
Cloth is referring to Fig. 2 b.
Refer to shown in Fig. 5, it is the flow chart of aircraft slat aerofoil aerodynamic loading distribution of the present invention, this detailed process
For：
Step c1, marks point of resultant force position under whole operating modes on slat aerofoil；
Step c2, drafts the upper following of the parallelogram that load(ing) point surrounds, parallel with Y-axis, and closes under whole operating modes
The both sides of trail force load position, and this can not be at the deep camber leading edge of slat and thin trailing edge to parallel edges position；
Step c3, draft the parallelogram that load(ing) point surrounds another to parallel edges；
Step c4, obtains a and b of whole point of resultant force；
Step c5, if being unsatisfactory for requiring, the opposite side of the parallel Y-axis of parallelogram that adjustment load(ing) point is constituted, if full
Foot requires then to execute following step；
Step c6, if being unsatisfactory for requiring, adjusts another opposite side of the parallelogram of load(ing) point composition, if meet requiring,
Then execute following step；
Step c7, carries out the distribution that whole aerodynamic loadings are made a concerted effort；
Step c8, obtains four loaded load；
The load of lower four load(ing) points of each operating mode is respectively
Step c9, arranges four load(ing) points with the power size in the wing flap test period and direction；Component position after distribution
Referring to shown in Fig. 2 c.
Refer to shown in Fig. 6, its flow chart being aircraft slat aerofoil rubberized tape of the present invention and lever system distribution；This tool
Body process is：
Step d1, chooses a load(ing) point；
Step d2, on the straight line of the parallel Y-axis of this load(ing) point, with this point as midpoint, two rubberized tapes are respectively installed on both sides,
This four rubberized tape positions should be uniformly in a quarter slat airfoil area that this load(ing) point is located；
Step d3, four rubberized tapes of here is installed lever system, connects lever system upper end using a cable wire, realize
Aerodynamic loading loads；
Step d4, judges whether the rubberized tape of four load(ing) points and lever system all install, such as non-installation,
Then execution step d5, continues to install successively, such as installation, then execution step d6, completes to load；Rubberized tape install distribution referring to
Fig. 2 d.
Pneumatic load in the aircraft flap of the present invention, slat system test it is contemplated that in airborne period, under each state of slat
Lotus；The aerodynamic loading of test or emulation acquisition can be effectively converted into the load mode realized in test, and ensure that gas
Dynamic loading true；The aerodynamic loading that slat is subject to by being converted to the load that several are distributed in some pieces of regions of aerofoil,
Under each operating mode of slat motion, the direction of this several component is identical all the time, is easily controlled and real in test loading procedure
Existing, the aerodynamic force size that can be simulated according to the flap, flap position real-time control in the flap, slat motion process, direction, pressure heart etc.
Parameter；In test loads, by the distribution of rubberized tape around load(ing) point it is ensured that slat structure stress uniformly, will not produce
The excessive load not conformed to the actual conditions and the destruction leading to testpieces.
The foregoing is only presently preferred embodiments of the present invention, be merely illustrative for invention, and nonrestrictive.
Those skilled in the art understands, it can be carried out in the spirit and scope that invention claim is limited with many changes, change,
Even equivalent, but fall within protection scope of the present invention.
Claims (4)
1. a kind of for the aircraft flap, slat system reliability test aerodynamic loading loading method it is characterised in that detailed process
For：
Step a, obtains aerodynamic loading under each state of flight for the slat by wind tunnel test or simulation calculation；
Step b, according to aerodynamic loading under different flight state for the aircraft slat, calculates slat aerofoil gas under each state of flight
Dynamic loading make a concerted effort；
Step c, according to each state of flight get off the plane slat aerofoil aerodynamic loading make a concerted effort, be broken down into several component,
Obtain size and the direction of component；
Step d, by rubberized tape and lever system, the component of above-mentioned steps c uniformly and is loaded onto slat aerofoil；
Wherein, in step a, the detailed process that aircraft slat aerofoil aerodynamic loading is asked for is：
Step a1, obtains all of operating mode in slat airborne period；
Step a2, according to aircraft slat folding and unfolding test requirements document, works out flight folding and unfolding operating mode；
Step a3, determines the aerodynamic loading of slat under each operating mode using wind tunnel test or numerical computations, each operating mode obtaining
Lower aerodynamic loading is in the distribution situation of aerofoil；
Obtain a file under each operating mode to be used for storing slat aerofoil aerodynamic loading, in file, each row of data are respectively aerofoil knot
Point numbering, aerofoil node coordinate position, aerofoil node aerodynamic loading component in the X, Y, Z direction；
Step a4, judges whether whole operating modes calculate and completes, if not completing, proceeding slat aerodynamic loading and calculating, if
Complete to calculate, then step a5, arrange and number slat aerodynamic loading data file under each operating mode；
Wherein, slat is defined as Y-direction along spanwise, vertical lap seam thriving face direction be defined as X to, tangent with slat aerofoil simultaneously
Vertical spanwise is defined as Z-direction；
Wherein, in step b, the detailed process that aircraft slat aerofoil aerodynamic loading makes a concerted effort to ask for is：
Step b1, numbers slat aerodynamic loading data file according to the precedence of a test period；
Step b2, according to slat aerodynamic loading data under first operating mode, using the synthesis principle of power, list four component X, Y,
In Z-direction, aerodynamic loading is made a concerted effort equation；
Step b3, according to slat aerodynamic loading data under first operating mode, is zero principle using pressure heart position moment, list X, Y,
In Z-direction, aerodynamic loading is made a concerted effort moment equation；
Step b4, solves the equation of the first two steps, obtains make a concerted effort size and the direction of slat aerodynamic loading under this operating mode respectively
And make a concerted effort in the position coordinates of slat aerofoil；
Step b5, removes Y-direction power of making a concerted effort under each operating mode, make a concerted effort size and the side of slat aerodynamic loading under this operating mode of record storage
To and make a concerted effort slat aerofoil position coordinates；
Step b6, judges that whole operating mode occlusometers are no at last and completes, as unfinished, then execution step b7, carry out the next one successively
Operating mode makes a concerted effort to calculate, and such as completes, then execution step b8, terminates slat aerodynamic loading and makes a concerted effort to calculate.
2. the aerodynamic loading loading method for the aircraft flap, slat system reliability test according to claim 1, it is special
Levy and be, in above-mentioned steps c, the detailed process of aircraft slat aerofoil aerodynamic loading distribution is：
Step c1, marks point of resultant force position under whole operating modes on slat aerofoil；
Step c2, drafts the upper following of the parallelogram that load(ing) point surrounds, parallel with Y-axis, and makes a concerted effort to make under whole operating modes
With the both sides of a position, and this can not be at the deep camber leading edge of slat and thin trailing edge to parallel edges position；
Step c3, draft the parallelogram that load(ing) point surrounds another to parallel edges, by point of resultant force to parallelogram
Two parallel with Y-axis back gauge ratio be designated as a, and a ＜ 1；By point of resultant force to parallelogram and another opposite side
Distance ratio is designated as b, and b ＜ 1；
Step c4, obtains a and b of whole point of resultant force；
Step c5, if being unsatisfactory for a ＞ 1/2, the opposite side of the parallel Y-axis of parallelogram that adjustment load(ing) point is constituted, if meet a
＞ 1/2, then execute following step；
Step c6, if being unsatisfactory for b ＞ 1/2, another opposite side of the parallelogram that adjustment load(ing) point is constituted, if meet b ＞ 1/
2, then execute following step；
Step c7, carries out the distribution that whole aerodynamic loadings are made a concerted effort；
Step c8, obtains four loaded load；
Step c9, arranges four load(ing) points with the power size in the wing flap test period and direction.
3. the aerodynamic loading loading method for the aircraft flap, slat system reliability test according to claim 2, it is special
Levy and be, in above-mentioned steps c8,
The load of lower four load(ing) points of each operating mode is respectively
Wherein, FiFor described aircraft under i-th state of flight slat aerofoil aerodynamic loading make a concerted effort.
4. the aerodynamic loading loading method for the aircraft flap, slat system reliability test according to claim 1, it is special
Levy and be, in above-mentioned steps d, the process of aircraft slat aerofoil rubberized tape and lever system distribution is：
Step d1, chooses a load(ing) point；
Step d2, on the straight line of the parallel Y-axis of this load(ing) point, with this point as midpoint, two rubberized tapes are respectively installed on both sides, and this four
Individual rubberized tape position should be uniformly in a quarter slat airfoil area that this load(ing) point is located；
Step d3, four rubberized tapes of here is installed lever system, connects lever system upper end using a cable wire, realize pneumatic
Load loads；
Step d4, judges whether the rubberized tape of four load(ing) points and lever system all install, such as non-installation, then hold
Row step d5, continues to install successively, such as installation, then execution step d6, completes to load.
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