CN102095577A - Load control method for aircraft flap experiment - Google Patents
Load control method for aircraft flap experiment Download PDFInfo
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- CN102095577A CN102095577A CN2011100005891A CN201110000589A CN102095577A CN 102095577 A CN102095577 A CN 102095577A CN 2011100005891 A CN2011100005891 A CN 2011100005891A CN 201110000589 A CN201110000589 A CN 201110000589A CN 102095577 A CN102095577 A CN 102095577A
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Abstract
The invention relates to a load control method for an aircraft experiment, in particular to a load control method for an aircraft flap experiment. In the method, a mode that a flap movement angle and the turning pulse signal of a driving mechanism output shaft correspond is adopted, and the pulse signal serves as the reference to carry out follow-up load. The method mainly comprises three-aspect contents, i.e. a segmented linear simulation non-linear control mode, an in-segment speed-regulation compensation mode and an in-segment pulse counting point-by-point load mode. With the method, a passive and precise follow-up non-linear load is realized, the operation response speed and the control precision of a loading system are improved, system stability is enhanced, and the load control method can be used for aircraft flap experiments for driving mechanism output shafts with a pulse output signal.
Description
Technical field
The present invention relates to a kind of aircraft testing loading control method, particularly relate to a kind of aircraft flap test loading control method.
Background technology
At present, in aircraft flap folding and unfolding test, Loading Control all adopts the simplification loading method, comprise fixed load, fixing pressure heart position, relax three kinds of simplified ways of the scope of accepting of load attitude, and adopt angle and the corresponded manners of time by the load majority that the wing flap movement angle is applied, can not be accurately corresponding in real time, and also can produce error aspect the measurement wing flap movement angle.In addition, wing flap movement angle metering system can be divided into two kinds, and first kind of anglec of rotation that is to use the displacement sensor wing flap, defective are that displacement transducer is prone to fault when long term repeatability is worked.Second kind of anglec of rotation that is to use angular transducer to measure wing flap, defective is that the angular transducer feedback signal is prone to hysteresis.
Summary of the invention
The objective of the invention is: design a kind of wing flap test loading control method, solve the problem of feedback signal lags, load can accurately be changed with the wing flap movement locus apply, and keep loading direction vertical with the wing flap aerofoil all the time.Simultaneously, make loading system accurately operation steady in a long-term.
Technical scheme of the present invention: wing flap test loading control method of the present invention uses wing flap driving mechanism output shaft rotational pulse signal as the Loading Control command reference, loading system receives that whenever a rotational pulse signal just sends a control command, and this method may further comprise the steps:
(1) sets up wing flap movement angle-driving mechanism output shaft rotational pulse counting curve, carry out sectional linear fitting according to knee point;
(2) according to the segmentation situation to specified load in the charter and press the position of heart position actuator to carry out by the end points of section linear distribution again;
(3) static state of being undertaken under this state by the wing flap angle of the end points correspondence of section loads, and measures the corresponding bid value that actuator is adjusted in the position, and the physics flex point when adjusting the actuator motion according to the position is carried out the segmentation adjustment;
(4) carry out the segmentation dynamic load, according to the Total tune situation that load applies, speed governing is compensated for as the broken line load mode with acceleration, deceleration function to this section.
Described wing flap test loading control method is used speed governing compensation Loading Control mode in the piecewise linearity simulation nonlinear way adapter section.
Beneficial effect of the present invention: adopt piecewise linearity simulation nonlinear way, pulse signal pointwise load mode according to the output of wing flap driving mechanism, speed governing compensation method in the adapter section, realized the non-linear loading of the accurate servo-actuated of passive type, improve the travelling speed and the control accuracy of loading system, strengthened the stability of system.
Description of drawings
Fig. 1 is an aircraft flap test servo-actuated loading structure synoptic diagram.
Fig. 2 is wing flap movement angle and rotational pulse signal relation figure.
Speed governing compensation method synoptic diagram in Fig. 3 section of being.
Fig. 4 normal load feedback profile and theoretical loading curve figure.
Fig. 5 speed governing compensation loads feedback and theoretical loading curve curve map.
Fig. 6 is an actual loaded feedback profile design sketch.
The 1st, load string of a musical instrument face, the 2nd, wing flap, the 3rd, load frock, 4, the 10th, guide rail, 5, the 8th, coaster, 6, the 9th, actuator is adjusted in the position, the 7th, load actuator, the 10th, sectional linear fitting curve, the 11st, actual relationship curve, the 12nd, knee point, the 13rd, quicken the broken line loading curve, the 15th, deceleration broken line loading curve, 17, the 18th, the speed governing broken line loads flex point, the 14th, certain section original directive curve, the 16th, certain section original directive control End of Curve, the 19th, certain section original directive control spring of curve, 20, the 22nd, theoretical loading curve, the 21st, normal load feedback profile, the 23rd, the speed governing compensation loads feedback profile, the 24th, the error upper limit, the 25th, feedback profile, the 26th, error lower limit.
Embodiment
Below with reference to accompanying drawing technical solution of the present invention is further described.
(1) takes measurement of an angle-the step-by-step counting corresponding relation
Use the counter and the obliquity sensor of DEWETRON measuring equipment, actual measurement goes out the corresponding curve of wing flap movement angle-step-by-step counting, shown in the actual relationship curve among Fig. 1.
(2) linear segmented
Utilize curve linear match mode with wing flap movement angle-step-by-step counting corresponding relation curve segmentation (see figure 2).
According to charter given load and pressure heart position, carry out dynamic load according to the curve fitting segmentation, determine the physics flex point (reversal point) the when motion of actuator (see figure 1) is adjusted in the position, carry out the secondary segmenting of curve.
According to test mission book specified load value, by the end points bid value of every section of linear relationship calculating.Corresponding load value sees Table 1 after the segmentation.
| The sectional |
0 | 1 | 2 | 3 | 4 | 5 | 6 | 7 | 8 |
| Angle (°) | 0 | 5 | 6.4 | 7.5 | 10 | 15.3 | 20 | 25.3 | 30 |
| Step-by-step counting (individual) | 0 | 613 | 670 | 702 | 755 | 846 | 905 | 968 | 1015 |
| Load (daN) | 202 | 299 | 328 | 349 | 418 | 579 | 771 | 893 | 1046 |
Corresponding load value after table 1 segmentation
(3) revise section inner control curve
Movement characteristic according to every section, utilize the correction of the speed governing compensation way section of carrying out inner control curve in the section, set the speed governing penalty coefficient (variable slope multiple and variable slope flex point) of every section each passage, strengthen the coordinated movement of various economic factors of total system, improve the response speed of control system, eliminate system start-up slow excessively, stop overshooting problem.
The speed governing compensation way mainly is the linear gradient that loads by changing in the section, realizes that single step sends the change of order load, thereby changes the operation response speed of loading system.Its synoptic diagram is seen Fig. 3, and the design sketch that finally reaches is seen Fig. 4, Fig. 5.
(4) load by the pointwise of pulse counting
Utilize the step-by-step counting in the table 1 and the corresponding relation of load, the speed governing compensation way carries out the calculating of the corresponding load of each step-by-step counting in the adapter section, and computing formula sees Table 2.
Table 2 bid value computing formula
As benchmark, the pairing load order of current step-by-step counting is sent in pulse of every reception with wing flap driving mechanism output shaft rotational pulse signal.
The feedback signal of final control curve as shown in Figure 6, value of feedback all in the specification error scope and good with the wing flap motion state, does not load hysteresis phenomenon and takes place.
Claims (2)
1. an aircraft flap is tested loading control method, it is characterized in that described method use wing flap driving mechanism output shaft rotational pulse signal is as the Loading Control command reference, loading system receives that whenever a rotational pulse signal just sends a control command, and this method may further comprise the steps:
(1) sets up wing flap movement angle-driving mechanism output shaft rotational pulse counting curve, carry out sectional linear fitting according to knee point;
(2) according to the segmentation situation to specified load in the charter and press the position of heart position actuator to carry out by the end points of section linear distribution again;
(3) static state of being undertaken under this state by the wing flap angle of the end points correspondence of section loads, and measures the corresponding bid value that actuator is adjusted in the position, and the physics flex point when adjusting the actuator motion according to the position is carried out the segmentation adjustment;
(4) carry out the segmentation dynamic load, according to the Total tune situation that load applies, speed governing is compensated for as the broken line load mode with acceleration, deceleration function to this section.
2. a kind of aircraft flap test loading control method according to claim 1 is characterized in that described loading method uses speed governing compensation Loading Control mode in the piecewise linearity simulation nonlinear way adapter section.
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| CN2011100005891A CN102095577A (en) | 2011-01-05 | 2011-01-05 | Load control method for aircraft flap experiment |
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| CN2011100005891A CN102095577A (en) | 2011-01-05 | 2011-01-05 | Load control method for aircraft flap experiment |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103558019A (en) * | 2013-11-05 | 2014-02-05 | 中国航空工业集团公司西安飞机设计研究所 | Three-slideway wing flap test method for simulating deformation of wings |
| CN104048874A (en) * | 2014-06-24 | 2014-09-17 | 西北工业大学 | Load follow-up loading system for plane flap reliability test |
| CN104697761A (en) * | 2013-12-06 | 2015-06-10 | 中国飞机强度研究所 | Follow-up loading method of movable airfoil |
| CN104890898A (en) * | 2015-06-23 | 2015-09-09 | 中国航空工业集团公司西安飞机设计研究所 | High lift device movement performance test method and system, and load spectrum measurement method |
| CN104897355A (en) * | 2015-06-23 | 2015-09-09 | 中国航空工业集团公司西安飞机设计研究所 | Folded wing non-linear flutter test device |
| CN105758629A (en) * | 2014-12-19 | 2016-07-13 | 成都飞机设计研究所 | Servo loading method in aircraft strength test |
| CN107264836A (en) * | 2017-07-28 | 2017-10-20 | 中国航空工业集团公司西安飞机设计研究所 | The a wide range of following loading experimental rig of hatch door and test method |
| CN109335021A (en) * | 2018-11-21 | 2019-02-15 | 中国航发西安动力控制科技有限公司 | A kind of test oil door rod self-adaptation control method |
| CN109515748A (en) * | 2018-12-07 | 2019-03-26 | 江西洪都航空工业集团有限责任公司 | A kind of aircraft flap non-linear force loading method |
| CN110310543A (en) * | 2019-05-30 | 2019-10-08 | 福建科德电子科技有限公司 | A kind of simulated flight device flap runners |
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2011
- 2011-01-05 CN CN2011100005891A patent/CN102095577A/en active Pending
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103558019B (en) * | 2013-11-05 | 2016-03-09 | 中国航空工业集团公司西安飞机设计研究所 | A kind of three slide rail wing flap test methods simulating wing distortion |
| CN103558019A (en) * | 2013-11-05 | 2014-02-05 | 中国航空工业集团公司西安飞机设计研究所 | Three-slideway wing flap test method for simulating deformation of wings |
| CN104697761A (en) * | 2013-12-06 | 2015-06-10 | 中国飞机强度研究所 | Follow-up loading method of movable airfoil |
| CN104048874A (en) * | 2014-06-24 | 2014-09-17 | 西北工业大学 | Load follow-up loading system for plane flap reliability test |
| CN105758629B (en) * | 2014-12-19 | 2018-04-03 | 成都飞机设计研究所 | A kind of following loading method in aircraft strength test |
| CN105758629A (en) * | 2014-12-19 | 2016-07-13 | 成都飞机设计研究所 | Servo loading method in aircraft strength test |
| CN104890898A (en) * | 2015-06-23 | 2015-09-09 | 中国航空工业集团公司西安飞机设计研究所 | High lift device movement performance test method and system, and load spectrum measurement method |
| CN104897355A (en) * | 2015-06-23 | 2015-09-09 | 中国航空工业集团公司西安飞机设计研究所 | Folded wing non-linear flutter test device |
| CN104897355B (en) * | 2015-06-23 | 2017-05-17 | 中国航空工业集团公司西安飞机设计研究所 | Folded wing non-linear flutter test device |
| CN107264836A (en) * | 2017-07-28 | 2017-10-20 | 中国航空工业集团公司西安飞机设计研究所 | The a wide range of following loading experimental rig of hatch door and test method |
| CN107264836B (en) * | 2017-07-28 | 2020-04-14 | 中国航空工业集团公司西安飞机设计研究所 | Cabin door large-range follow-up loading test device and test method |
| CN109335021A (en) * | 2018-11-21 | 2019-02-15 | 中国航发西安动力控制科技有限公司 | A kind of test oil door rod self-adaptation control method |
| CN109335021B (en) * | 2018-11-21 | 2022-03-25 | 中国航发西安动力控制科技有限公司 | Adaptive control method for accelerator rod for test |
| CN109515748A (en) * | 2018-12-07 | 2019-03-26 | 江西洪都航空工业集团有限责任公司 | A kind of aircraft flap non-linear force loading method |
| CN109515748B (en) * | 2018-12-07 | 2022-03-29 | 江西洪都航空工业集团有限责任公司 | Nonlinear force loading method for airplane flap |
| CN110310543A (en) * | 2019-05-30 | 2019-10-08 | 福建科德电子科技有限公司 | A kind of simulated flight device flap runners |
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Application publication date: 20110615 |