CN104075868A - 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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- CN104075868A CN104075868A CN201410246843.XA CN201410246843A CN104075868A CN 104075868 A CN104075868 A CN 104075868A CN 201410246843 A CN201410246843 A CN 201410246843A CN 104075868 A CN104075868 A CN 104075868A
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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 fail-test field, relate in particular to a kind of aerodynamic loading following loading method for the aircraft flap, slat System Reliability Test.
Background technology
The aircraft flap, slat play an important role in the flight course of civil aircraft, and its effect mainly contains two: the one, delay the burbling on wing, and improved the critical angle of attack of aircraft, make aircraft just stall can occur under the larger angle of attack; The 2nd, the lift coefficient of increase wing.The aircraft flap, slat motion break down and can produce a very large impact the safety of aircraft, even cause fatal crass's harsh consequence.
Based on the flap, the importance of slat system to Flight Safety, require the flap, slat system to there is higher fiduciary level.And be the reliability index of the assessment existing flap, slat system design scheme, and obtain the innovative approach of the reliability level that improves the flap, slat system, realize the reliability growth of the flap, slat system, must Chinese-style jacket with buttons down the front, slat system carries out fail-safe analysis.For the fail-safe analysis of engineering goods, mainly there is at present two kinds of means, i.e. emulation and test.But due to the restriction of technical merit and the complicacy of large complicated engineering goods, Reliablility simulation can not replace fail-test completely at present.
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, once there is the normally fault of folding and unfolding of the flap, slat system, very likely causes the major accident of air crash.Therefore need to a kind ofly can carry out in ground Chinese-style jacket with buttons down the front, slat system test method and the device of fail-test; And for the test of these type of engineering goods, existing test method is not often considered the impact of slat aerodynamic loading Chinese-style jacket with buttons down the front, slat system performance in flight course, the environmental baseline of simulation is true not.
In view of above-mentioned defect, creator of the present invention has obtained this creation finally through long research and practice.
Summary of the invention
The object of the present invention is to provide a kind of aerodynamic loading loading method for the aircraft flap, slat System Reliability Test, in order to overcome above-mentioned technological deficiency.
For achieving the above object, the invention provides a kind of aerodynamic loading loading method for the aircraft flap, slat System Reliability Test, this detailed process is:
Step a, obtains the aerodynamic loading of slat under each state of flight by wind tunnel test or simulation calculation;
Step b, the aerodynamic loading according to aircraft slat under different flight state, calculates making a concerted effort of slat aerofoil aerodynamic loading under each state of flight;
Step c, gets off the plane making a concerted effort of slat aerofoil aerodynamic loading according to each state of flight, is decomposed into several component, obtains size and the direction of component;
Steps d, by rubberized tape and lever system, the component of above-mentioned steps c is uniform and be loaded on 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 operating modes in slat airborne period;
Step a2, according to aircraft slat folding and unfolding testing requirements, establishment flight folding and unfolding operating mode;
Step a3, is used wind tunnel test or numerical evaluation to determine the aerodynamic loading of slat under each operating mode, and under each operating mode obtaining, aerodynamic loading is in the distribution situation of aerofoil;
Under each operating mode, obtain a file for storing slat aerofoil aerodynamic loading, in file, each row of data are respectively aerofoil node numbering, aerofoil node coordinate position, the component of aerofoil node aerodynamic loading in X, Y, Z direction;
Step a4, judges whether whole operating modes have been calculated, if do not complete, proceeds slat aerodynamic loading and calculates, if complete calculating, arranges slat aerodynamic loading data file under each operating mode of numbering;
Wherein, slat is defined as to Y-direction along spanwise, the thriving face direction of vertical lap seam is defined as X-direction, and vertical spanwise tangent with slat aerofoil 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, the precedence numbering slat aerodynamic loading data file according to a test period;
Step b2, according to slat aerodynamic loading data under first operating mode, makes synthetic principle firmly, lists in four component X, Y, Z direction the aerodynamic loading equation of making a concerted effort;
Step b3, according to slat aerodynamic loading data under first operating mode, using and pressing heart position moment is zero principle, lists aerodynamic loading resultant moment equation in X, Y, Z direction;
Step b4, solves the equation of the first two step, and the size of making a concerted effort that obtains respectively slat aerodynamic loading under this operating mode is with direction and make a concerted effort at the position coordinates of slat aerofoil;
Step b5, removes under each operating mode the Y-direction power of making a concerted effort, and under this operating mode of record storage, the size of making a concerted effort of slat aerodynamic loading is with direction and make a concerted effort at the position coordinates of slat aerofoil;
Step b6, judges whole operating mode occlusometers no completing at last, as unfinished, performs step b7, carries out successively next operating mode and makes a concerted effort to calculate, as complete, and performs step b8, finishes slat aerodynamic loading and makes a concerted effort to calculate.
Further, in above-mentioned steps c, the detailed process that aircraft slat aerofoil aerodynamic loading distributes is:
Step c1 marks point of resultant force position under whole operating modes on slat aerofoil;
Step c2, draft parallelogram that load(ing) point surrounds upper below, parallel with Y-axis, and under whole operating modes the both sides of point of resultant force position, and this can not be at deep camber leading edge and the thin trailing edge place of slat to parallel edges position;
Step c3, another that draft parallelogram that load(ing) point surrounds is to parallel edges, point of resultant force is designated as to a (a < 1) to two back gauge ratios parallel with Y-axis of parallelogram, by point of resultant force to parallelogram, is designated as b (b < 1) with another opposite side distance ratio;
Step c4, all a and the b of point of resultant force obtain;
Step c5, adjusts the opposite side of the parallel Y-axis of the parallelogram that load(ing) point forms if do not meet the demands, carry out following step if meet the demands;
Step c6, adjusts another opposite side of the parallelogram that load(ing) point forms if do not meet the demands, if meet the demands, carry out 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, arrange four load(ing) points with wing flap power size and the direction in the test period.
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 that aircraft slat aerofoil rubberized tape and lever system distribute is:
Steps d 1, chooses a load(ing) point;
Steps d 2, on the straight line of the parallel Y-axis of this load(ing) point, take that this puts as mid point, and two rubberized tapes are respectively installed on both sides, and these four rubberized tape positions should be evenly in 1/4th slat airfoil area at this load(ing) point place;
Steps d 3 is installed lever system on these four rubberized tapes, uses a cable wire to connect lever system upper end, realizes aerodynamic loading and loads;
Steps d 4, judges whether the rubberized tape of four load(ing) points and lever system all install, and as not installation, perform step d5, continues to install successively, as installation, performs step d6, completes loading.
Beneficial effect of the present invention is compared with prior art: in the aircraft flap of the present invention, slat system test, considered in airborne period the aerodynamic loading under each state of slat; The aerodynamic loading that test or emulation obtain can be converted to the load mode of realizing in test effectively, and has guaranteed the true of aerodynamic loading; The aerodynamic loading that slat is subject to is distributed in the load in some regions of aerofoil by being converted to several, under each operating mode of slat motion, the direction of these several component is identical all the time, easy control and realization in test loading procedure, can be according to parameters such as the flap, the slat position aerodynamic force size that control is simulated in real time, direction, the pressure hearts in the flap, slat motion process; In test loads, by the load(ing) point distribution of rubberized tape around, guaranteed that slat structure stress is even, can not produce the excessive load not conforming to the actual conditions and the destruction that causes testpieces.
Accompanying drawing explanation
Fig. 1 is the process flow diagram of the aerodynamic loading loading method of fail-test of the present invention;
Fig. 2 a is that aircraft slat aerofoil test of the present invention or emulation obtain aerodynamic loading distribution plan;
Fig. 2 b is the aircraft slat aerofoil aerodynamic loading of the present invention distribution plan of making a concerted effort;
Fig. 2 c is the distribution plan of four loading forces of aircraft slat aerofoil of the present invention;
Fig. 2 d is rubberized tape distribution plan on aircraft slat aerofoil of the present invention;
Fig. 3 is the process flow diagram that aircraft slat aerofoil aerodynamic loading of the present invention is asked for;
Fig. 4 is the process flow diagram that aircraft slat aerofoil aerodynamic loading of the present invention makes a concerted effort to ask for;
Fig. 5 is the process flow diagram that aircraft slat aerofoil aerodynamic loading of the present invention distributes;
Fig. 6 is the process flow diagram that aircraft slat aerofoil rubberized tape of the present invention and lever system distribute.
Embodiment
Below in conjunction with accompanying drawing, to the present invention is above-mentioned, be described in more detail with other technical characterictic and advantage.
Refer to shown in Fig. 1, the process flow diagram of its aerodynamic loading loading method that is fail-test of the present invention, this detailed process is:
Step a, obtains the aerodynamic loading of slat under each state of flight by wind tunnel test or simulation calculation;
Step b, the aerodynamic loading according to aircraft slat under different flight state, calculates making a concerted effort of slat aerofoil aerodynamic loading under each state of flight;
Step c, gets off the plane making a concerted effort of slat aerofoil aerodynamic loading according to each state of flight, is decomposed into several component, obtains size and the direction of component;
Steps d, by rubberized tape and lever system, the component of above-mentioned steps c is uniform and be loaded on slat aerofoil.
The embodiment of the present invention, is defined as Y-direction by slat along spanwise, and the thriving face direction of vertical lap seam is defined as X-direction, and vertical spanwise tangent with slat aerofoil is defined as Z-direction.
Aerodynamic loading is made a concerted effort to be divided into four component, the position of four component forms a parallelogram, point of resultant force is designated as to a (a < 1) to two back gauge ratios parallel with Y-axis of parallelogram, by point of resultant force to parallelogram, is designated as b (b < 1) with another opposite side distance ratio.
Shown in Fig. 2 a, 2b, 2c and 2d, it is respectively the test of aircraft slat aerofoil or emulation obtains aerodynamic loading distribution plan; The aircraft slat aerofoil aerodynamic loading distribution plan of making a concerted effort; The distribution plan of four loading forces of aircraft slat aerofoil; Rubberized tape distribution plan on aircraft slat aerofoil.
Refer to shown in Fig. 3, the process flow diagram that it is asked for for aircraft slat aerofoil aerodynamic loading of the present invention, this detailed process is:
Step a1, obtains all operating modes in slat airborne period;
Step a2, according to aircraft slat folding and unfolding testing requirements, establishment flight folding and unfolding operating mode;
Step a3, use wind tunnel test or numerical evaluation to determine the aerodynamic loading of slat under each operating mode, under each operating mode obtaining, aerodynamic loading in the distribution situation of aerofoil as shown in Figure 2 a, under each operating mode, obtain a .dat file for storing slat aerofoil aerodynamic loading, in file, each row of data are respectively aerofoil node numbering, aerofoil node coordinate position, the component of aerofoil node aerodynamic loading in X, Y, Z direction;
Step a4, judges whether whole operating modes have been calculated, if do not complete, proceeds slat aerodynamic loading and calculates, if complete calculating, arranges slat aerodynamic loading .dat data file under each operating mode of numbering.
Refer to shown in Fig. 4, it is the process flow diagram that aircraft slat aerofoil aerodynamic loading of the present invention makes a concerted effort to ask for, and this detailed process is:
Step b1, the precedence numbering slat aerodynamic loading .dat data file according to a test period;
Step b2, according to slat aerodynamic loading data under first operating mode, makes synthetic principle firmly, lists in four component X, Y, Z direction the aerodynamic loading equation of making a concerted effort;
Step b3, according to slat aerodynamic loading data under first operating mode, using and pressing heart position moment is zero principle, lists aerodynamic loading resultant moment equation in X, Y, Z direction;
Step b4, solves the equation of the first two step, and the size of making a concerted effort that obtains respectively slat aerodynamic loading under this operating mode is with direction and make a concerted effort at the position coordinates of slat aerofoil;
Step b5, removes under this operating mode the Y-direction power of making a concerted effort, and under this operating mode of record storage, the size of making a concerted effort of slat aerodynamic loading is with direction and make a concerted effort at the position coordinates of slat aerofoil;
Because Y-direction power is with respect to X and Z-direction power, very little, can ignore.
Step b6, judges whole operating mode occlusometers no completing at last, as unfinished, performs step b7, carries out successively next operating mode and makes a concerted effort to calculate, as complete, and performs step b8, finishes slat aerodynamic loading and makes a concerted effort to calculate; All operating mode makes a concerted effort to distribute referring to Fig. 2 b.
Refer to shown in Fig. 5, it is the process flow diagram that aircraft slat aerofoil aerodynamic loading of the present invention distributes, and this detailed process is:
Step c1 marks point of resultant force position under whole operating modes on slat aerofoil;
Step c2, draft parallelogram that load(ing) point surrounds upper below, parallel with Y-axis, and under whole operating modes the both sides of point of resultant force position, and this can not be at deep camber leading edge and the thin trailing edge place of slat to parallel edges position;
Step c3, another that draft parallelogram that load(ing) point surrounds is to parallel edges;
Step c4, all a and the b of point of resultant force obtain;
Step c5, if do not meet the demands, adjusts the opposite side of the parallel Y-axis of the parallelogram that load(ing) point forms, and carries out following step if meet the demands;
Step c6, adjusts another opposite side of the parallelogram that load(ing) point forms if do not meet the demands, if meet the demands, carry out 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, arrange four load(ing) points with wing flap power size and the direction in the test period; Component position after distribution is referring to shown in Fig. 2 c.
Refer to shown in Fig. 6, it is the process flow diagram of aircraft slat aerofoil rubberized tape of the present invention and lever system distribution; This detailed process is:
Steps d 1, chooses a load(ing) point;
Steps d 2, on the straight line of the parallel Y-axis of this load(ing) point, take that this puts as mid point, two two rubberized tapes is respectively installed, and these four rubberized tape positions should be evenly in 1/4th slat airfoil area at this load(ing) point place;
Steps d 3 is installed lever system on these four rubberized tapes, uses a cable wire to connect lever system upper end, realizes aerodynamic loading and loads;
Steps d 4, judges whether the rubberized tape of four load(ing) points and lever system all install, and as not installation, perform step d5, continues to install successively, as installation, performs step d6, completes loading; Rubberized tape is installed and is distributed referring to Fig. 2 d.
In the aircraft flap of the present invention, slat system test, considered in airborne period the aerodynamic loading under each state of slat; The aerodynamic loading that test or emulation obtain can be converted to the load mode of realizing in test effectively, and has guaranteed the true of aerodynamic loading; The aerodynamic loading that slat is subject to is distributed in the load in some regions of aerofoil by being converted to several, under each operating mode of slat motion, the direction of these several component is identical all the time, easy control and realization in test loading procedure, can be according to parameters such as the flap, the slat position aerodynamic force size that control is simulated in real time, direction, the pressure hearts in the flap, slat motion process; In test loads, by the load(ing) point distribution of rubberized tape around, guaranteed that slat structure stress is even, can not produce the excessive load not conforming to the actual conditions and the destruction that causes testpieces.
The foregoing is only preferred embodiment of the present invention, is only illustrative for invention, and nonrestrictive.Those skilled in the art is understood, and in the spirit and scope that limit, can carry out many changes to it in invention claim, revise, and even equivalence, but all will fall within the scope of protection of the present invention.
Claims (6)
1. for an aerodynamic loading loading method for the aircraft flap, slat System Reliability Test, it is characterized in that, this detailed process is:
Step a, obtains the aerodynamic loading of slat under each state of flight by wind tunnel test or simulation calculation;
Step b, the aerodynamic loading according to aircraft slat under different flight state, calculates making a concerted effort of slat aerofoil aerodynamic loading under each state of flight;
Step c, gets off the plane making a concerted effort of slat aerofoil aerodynamic loading according to each state of flight, is decomposed into several component, obtains size and the direction of component;
Steps d, by rubberized tape and lever system, the component of above-mentioned steps c is uniform and be loaded on slat aerofoil.
2. the aerodynamic loading loading method for the aircraft flap, slat System Reliability Test according to claim 1, is characterized in that, in above-mentioned steps a, the detailed process that aircraft slat aerofoil aerodynamic loading is asked for is:
Step a1, obtains all operating modes in slat airborne period;
Step a2, according to aircraft slat folding and unfolding testing requirements, establishment flight folding and unfolding operating mode;
Step a3, is used wind tunnel test or numerical evaluation to determine the aerodynamic loading of slat under each operating mode, and under each operating mode obtaining, aerodynamic loading is in the distribution situation of aerofoil;
Under each operating mode, obtain a file for storing slat aerofoil aerodynamic loading, in file, each row of data are respectively aerofoil node numbering, aerofoil node coordinate position, the component of aerofoil node aerodynamic loading in X, Y, Z direction;
Step a4, judges whether whole operating modes have been calculated, if do not complete, proceeds slat aerodynamic loading and calculates, if complete calculating, step a5, arranges slat aerodynamic loading data file under each operating mode of numbering;
Wherein, slat is defined as to Y-direction along spanwise, the thriving face direction of vertical lap seam is defined as X-direction, and vertical spanwise tangent with slat aerofoil is defined as Z-direction.
3. the aerodynamic loading loading method for the aircraft flap, slat System Reliability Test according to claim 2, is characterized in that, in above-mentioned steps b, the detailed process that aircraft slat aerofoil aerodynamic loading makes a concerted effort to ask for is:
Step b1, the precedence numbering slat aerodynamic loading data file according to a test period;
Step b2, according to slat aerodynamic loading data under first operating mode, makes synthetic principle firmly, lists in four component X, Y, Z direction the aerodynamic loading equation of making a concerted effort;
Step b3, according to slat aerodynamic loading data under first operating mode, using and pressing heart position moment is zero principle, lists aerodynamic loading resultant moment equation in X, Y, Z direction;
Step b4, solves the equation of the first two step, and the size of making a concerted effort that obtains respectively slat aerodynamic loading under this operating mode is with direction and make a concerted effort at the position coordinates of slat aerofoil;
Step b5, removes under each operating mode the Y-direction power of making a concerted effort, and under this operating mode of record storage, the size of making a concerted effort of slat aerodynamic loading is with direction and make a concerted effort at the position coordinates of slat aerofoil;
Step b6, judges whole operating mode occlusometers no completing at last, as unfinished, performs step b7, carries out successively next operating mode and makes a concerted effort to calculate, as complete, and performs step b8, finishes slat aerodynamic loading and makes a concerted effort to calculate.
4. according to the aerodynamic loading loading method for the aircraft flap, slat System Reliability Test described in claim 2 or 3, it is characterized in that, in above-mentioned steps c, the detailed process that aircraft slat aerofoil aerodynamic loading distributes is:
Step c1 marks point of resultant force position under whole operating modes on slat aerofoil;
Step c2, draft parallelogram that load(ing) point surrounds upper below, parallel with Y-axis, and under whole operating modes the both sides of point of resultant force position, and this can not be at deep camber leading edge and the thin trailing edge place of slat to parallel edges position;
Step c3, another that draft parallelogram that load(ing) point surrounds is to parallel edges, point of resultant force is designated as to a (a < 1) to two back gauge ratios parallel with Y-axis of parallelogram, by point of resultant force to parallelogram, is designated as b (b < 1) with another opposite side distance ratio;
Step c4, all a and the b of point of resultant force obtain;
Step c5, adjusts the opposite side of the parallel Y-axis of the parallelogram that load(ing) point forms if do not meet the demands, carry out following step if meet the demands;
Step c6, adjusts another opposite side of the parallelogram that load(ing) point forms if do not meet the demands, if meet the demands, carry out 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, arrange four load(ing) points with wing flap power size and the direction in the test period.
5. the aerodynamic loading loading method for the aircraft flap, slat System Reliability Test according to claim 4, is characterized in that, in above-mentioned steps c8,
The load of lower four load(ing) points of each operating mode is respectively
6. according to the aerodynamic loading loading method for the aircraft flap, slat System Reliability Test described in claim 2 or 3, it is characterized in that, in above-mentioned steps d, the detailed process that aircraft slat aerofoil rubberized tape and lever system distribute is:
Steps d 1, chooses a load(ing) point;
Steps d 2, on the straight line of the parallel Y-axis of this load(ing) point, take that this puts as mid point, and two rubberized tapes are respectively installed on both sides, and these four rubberized tape positions should be evenly in 1/4th slat airfoil area at this load(ing) point place;
Steps d 3 is installed lever system on these four rubberized tapes, uses a cable wire to connect lever system upper end, realizes aerodynamic loading and loads;
Steps d 4, judges whether the rubberized tape of four load(ing) points and lever system all install, and as not installation, perform step d5, continues to install successively, as installation, performs step d6, completes loading.
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| CN113063570A (en) * | 2019-12-27 | 2021-07-02 | 中国航空工业集团公司西安飞机设计研究所 | Slat load loading method in full-size fatigue test of airplane |
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