CN1514213A - Full machine ground load on site calibration test method and its device - Google Patents

Full machine ground load on site calibration test method and its device Download PDF

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Publication number
CN1514213A
CN1514213A CNA021589593A CN02158959A CN1514213A CN 1514213 A CN1514213 A CN 1514213A CN A021589593 A CNA021589593 A CN A021589593A CN 02158959 A CN02158959 A CN 02158959A CN 1514213 A CN1514213 A CN 1514213A
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load
aircraft
wing
lever
jin
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CN1273813C (en
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阎楚良
孟繁沛
侯朝沐
张书明
何彧
王赞平
叶舸
孟祥民
张鑫
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Chinese Academy of Agricultural Mechanization Sciences
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Chinese Academy of Agricultural Mechanization Sciences
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Abstract

In the present invention, carriage and landing gear are used as pivot points to make aircraft hold in level state; at this state, load is imposed onto selected section area by strain transducer unit and to record load value, in this case aircraft wing can be calibrated on line so not only load truthfulness can be ensured but also accuracy of load calibration and precision of measurement can be ensured as mechanical basis is provided for faitigue life and analog test of aircraft wing as well as for setting up load equation of aircraft wing.

Description

Full machine landing load experimental Study on Field Calibration method and device thereof
Invention field
The present invention relates to a kind of aircraft wing load calibration test method, the invention still further relates to the isolated plant that uses this test method.
Background technology
Aircraft wing is as the vitals under the state of flight, need it should be in light weight, but it is safe in utilization again, therefore, understand that its force-bearing situation and serviceable life are the problems that people are concerned about always, but past when wing is carried out load test carries out after all wing being removed from aircraft, such test had not both guaranteed the authenticity of stand under load, did not guarantee the precision of load measurement and demarcation yet.
The present inventor is at the deficiencies in the prior art; carry out discovering with great concentration, under the condition that wing, empennage are not dismantled, carried out on-the-spot load and apply and demarcate, promptly can guarantee the safety of aircraft; can protect the authenticity of stand under load and the precision of load calibration again, so finished the present invention.
Summary of the invention
The object of the invention provides a kind of ground experimental Study on Field Calibration method of complete airborne lotus test of attaching most importance to wing, empennage, solves complete airborne lotus (comprising moment M, shearing Q and the torque T) on-line proving that present domestic aircraft attaches most importance to wing, empennage and the difficult problem of actual measurement with this.
A further object of the present invention provides a kind of device of realizing the ground experimental Study on Field Calibration method of described complete airborne lotus test.
By the result data that the test of strain transducer load calibration obtains, set up load equation, measure so that carry out aerial loading spectrum.And then measured aircraft exactly and in flight course He under the ground motion state, acted on structural external applied load time histories such as wing, empennage.
Specifically, carrying out aircraft wing load field calibration when test, aircraft is kept demarcating under the stopped status, it is characterized in that: it is to carry out according to following step under the condition that undercarriage is not dismantled:
(1), demarcate coordinate system, true origin is the fuselage construction horizontal line and the intersection point of O bit line (behind the head 1.0 meters), the X car overlaps with the fuselage construction horizontal line, backward for just, Y-axis makes progress in the aircraft plane of symmetry to just, Z axle sensing left wing and X, Y-axis formation right-handed system;
(2), wing when test with aircraft master lifting jack aircraft jack-up, with the protection carriage and the nose-gear that are added in the fuselage place is fulcrum, make the main landing gear built on stilts, central wing keeps horizontality, and aircraft system horizontal line and ground angle are determined the sectional position of load 2 ° ~ 4 ° (bowing), the load sectional tool is representative and guarantee that the installation device of sensor that can count record load is arranged, when when a wing loads, the wing will add balancing load (total outer EMx=0 that carries) in addition, and the record load value;
(3), horizontal tail when test, undercarriage lands, and is tight with the weight retaining before the gear tyre, with carriage aircraft held, and determines the load sectional position, is carried in the load section perpendicular to the horizontal tail string, connects sensor device, and the record loaded load,
(4), vertical fin when test, undercarriage lands, tight with the weight retaining before the gear tyre, the vertical fin side direction loads, and gives the device of a balance lateral loading moment of aircraft, determines to load behind the load sectional position, connects sensor device, and the record loaded load.
When carrying out described aircraft wing load field calibration test method, all points of load are applied to rib and spar junction on the aerofoil, and its contact area is not less than 120mm * 160mm.
Preferably, when carrying out described aircraft wing load field calibration test method, utilize the main jack pair wing of aircraft to load, force transducer is placed on main lifting jack upper end, withstand in the middle of the loading lever, the two ends of lever are connected with two clamps on the wing, the section that clamp is determined at wing, three loading positions in wing front and rear beam and front and rear beam center are by change lever positions and lifting jack position and vertex position realization loading requirement.
And, equally preferably, when carrying out described aircraft wing load field calibration test method, left and right sides horizontal tail is equipped with clamp in the load cross section of determining, each clamp has three to load the hole at the front and rear beam of horizontal tail and the center of front and rear beam, each load condition is connected with the clamp of a lever and selected section, left and right sides horizontal tail connects with a lever again, ground is with a rail versatilely, press a counterweight above, do not fall to connecting sensor with jin, on connect combining leverage, down connecing versatilely, rail loads.
More preferably, when described aircraft wing load field calibration test method, left and right sides horizontal tail is equipped with clamp in the load cross section of determining, each clamp has three loadings at the front and rear beam of horizontal tail and the center of front and rear beam, and each load condition is connected with the clamp of a lever and selected section, left and right sides horizontal tail connects with a lever again, a counterweight is pressed above with a rail versatilely in ground, with jin not falling to connecting sensor, on connect combining leverage, down connecing versatilely, rail loads.
Simultaneously, when vertical fin loads, the device of giving a balance lateral loading moment of aircraft be one on airframe (43) frame right side upright side direction column, column is pressed in ground with counterweight, adorn in column upper end and the identical place of (43) frame height one with the identical wooden unit of (43) frame profile, preceding and aircraft (43) frame of test is close to.
Also can be, when vertical fin loads, the device of giving a balance lateral loading moment of aircraft be one on airframe (43) frame right side upright side direction column, column is pressed in ground with counterweight, adorn in column upper end and the identical place of (43) frame height one with the identical wooden unit of (43) frame profile, preceding and aircraft (43) frame of test is close to.
Can also be, vertical fin give when loading the device of a balance lateral loading moment of aircraft be one on airframe (43) frame right side upright side direction column, column is pressed in ground with counterweight, adorn in column upper end and the identical place of (43) frame height one with the identical wooden unit of (43) frame profile, preceding and aircraft (43) frame of test is close to.
When vertical fin loads, selected section blocks with clamp, utilize one to load the load that each situation is implemented in the lever change position, utilize the cantilever pulley of a crane, one end by wire rope and sensor with load lever and link to each other, the other end utilizes pulley guiding and jin not to fall to joining, jin the do not fall other end and crane are fixed, utilize jin not drop into row and load, and the record load value.
When vertical fin loads, selected section blocks with clamp, utilize one to load the load that each situation is implemented in the lever change position, utilize the cantilever pulley of a crane, one end by wire rope and sensor with load lever and link to each other, the other end utilizes pulley guiding and jin not to fall to joining, jin the do not fall other end and crane are fixed, utilize jin not drop into row and load, and the record load value.
When vertical fin loads, selected section blocks with clamp, utilize one to load the load that each situation is implemented in the lever change position, utilize the cantilever pulley of a crane, one end by wire rope and sensor with load lever and link to each other, the other end utilizes pulley guiding and jin not to fall to joining, jin the do not fall other end and crane are fixed, utilize jin not drop into row and load, and the record load value.
When vertical fin loads, selected section blocks with clamp, utilize one to load the load that each situation is implemented in the lever change position, utilize the cantilever pulley of a crane, one end by wire rope and sensor with load lever and link to each other, the other end utilizes pulley guiding and jin not to fall to joining, jin the do not fall other end and crane are fixed, utilize jin not drop into row and load, and the record load value.
In addition, the present invention also provides a kind of isolated plant of realizing described aircraft wing load field calibration test method, it is characterized in that: the sensor device of aircraft is that force transducer is placed on the lifting jack upper end, withstand on and load in the middle of the lever, the two ends of lever are connected with two clamps on the wing, and clamp is stuck in the definite section of wing, three loading positions of wing front and rear beam and front and rear beam center by change lever positions and lifting jack position and vertex position realization loading requirement.
Preferably, the horizontal tail charger is that left and right sides horizontal tail is equipped with clamp in the load cross section of determining, each clamp has three each load condition of loading hole to be connected with the clamp of a lever and selected section at the front and rear beam of horizontal tail and the center of front and rear beam, left and right sides horizontal tail connects ground with a rail versatilely with lever again, press a counterweight above, do not fall to connecting sensor with jin, on connect combining leverage, down connecing versatilely, rail loads.
Equally preferably, the vertical fin charger is to block with clamp at selected section, utilize one to load the load that each situation is implemented in the lever change position, utilize the cantilever pulley of a crane, one end by wire rope and sensor with load lever and link to each other, the other end utilizes pulley guiding and jin not to fall to joining, jin the do not fall other end and crane are fixed, utilize jin not drop into row and load, and the record load value.
Because the present invention carries out under the condition that wing is not dismantled, both guaranteed the safety of aircraft, the authenticity of wing stand under load and the precision of load calibration have been guaranteed again, set up load equation by the test of strain transducer load calibration, also just can measure aircraft acts on wing under state of flight external applied load time history exactly, decide the mechanics basis of longevity and simulation test loading as fatigue.
Description of drawings
Fig. 1 is the load(ing) point location drawing.
Fig. 2 is a horizontal tail load(ing) point synoptic diagram.
Fig. 3 is a vertical fin load(ing) point synoptic diagram.
Fig. 4 is the aircraft floor status of support.
Fig. 5 is that wing is demarcated the loading synoptic diagram.
Fig. 6 is that horizontal tail is demarcated the loading synoptic diagram.
Fig. 7 is that vertical fin is demarcated the loading synoptic diagram.
Embodiment
The present invention is described in further detail below in conjunction with drawings and Examples:
At first selected coordinate system, coordinate is that full machine coordinate system true origin is the intersection point of fuselage construction horizontal line and O bit line (behind the head 1.0 meters), and the X car overlaps with the fuselage construction horizontal line, backward for just, upwards for just, the Z axle points to left wing and X, Y-axis formation right-handed system to Y-axis in the aircraft plane of symmetry.
1 wing load calibration
1.1 load measurement tangent plane
The I tangent plane is right flank 12 ribs outer 400; The II tangent plane is right flank 7 ribs outer 250;
The III tangent plane is right flank 2 ribs outer 400; The IV tangent plane is left wing's 2 ribs outer 400.
1.2 aircraft state
Main landing gear built on stilts during the wing test, central wing keeps horizontality, and aircraft system horizontal line and ground angle are approximately 3 °.
1.3 test situation and load
Fig. 1 is seen in the load(ing) point position, and test situation and magnitude of load see Table 1.
The table 1 wing test load and the pressure heart
Load type Sequence number I tangent plane (12 ribs are outer) II, III, IV tangent plane (outside 7 ribs, 2 ribs are outer)
??X(m) ??Z(m) ??P(kN) ??X(m) ??Z(m) ??P(kN)
Mark ??1 ??9.868 ??-11.00 ??25 ??9.565 ??-8.76 ????40
Decide load ????2 ????9.929 ????-11.45 ????30 ????9.620 ??-9.16 ????50
????3 ????9.989 ????-11.90 ????20 ????9.687 ??-9.66 ????35
????4 ????10.577 ????-11.00 ????25 ????10.456 ??-8.76 ????40
????5 ????10.602 ????-11.45 ????30 ????10.478 ??-9.16 ????50
????6 ????10.626 ????-11.90 ????20 ????10.505 ??-9.66 ????35
????7 ????10.223 ????-11.00 ????40 ????10.011 ??-8.76 ????60
????8 ????10.265 ????-11.45 ????40 ????10.049 ??-9.16 ????60
????9 ????10.308 ????-11.90 ????40 ????10.096 ??-9.66 ????60
Check load ????1 ????10.171 ????-11.417 ????40 ????9.918 ??-9.075 ????60
????2 ????10.353 ????-11.417 ????40 ????10.164 ??-9.075 ????60
????3 ????10.214 ????-12.210 ????30 ????9.960 ??-9.850 ????50
????4 ????10.460 ????-12.210 ????30 ????10.269 ??-9.850 ????50
2 empennage load calibrations
2.1 load measurement tangent plane
Horizontal tail: the V tangent plane is right horizontal tail and fuselage interface outer 350;
Horizontal tail: the VI tangent plane is left horizontal tail and fuselage interface outer 350;
Vertical fin: the VII tangent plane is on vertical fin 1 rib 50.
2.2 aircraft state
Rise before the aircraft, led and land.Horizontal tail loads in horizontal tail string plane (outside 9 °) downward vertically, and the vertical fin side direction loads.
2.3 test situation and load
Test situation and magnitude of load see Table 2.
Fig. 2, Fig. 3 are seen in the load(ing) point position.
The table 2 empennage test load and the pressure heart
Load type Sequence number Tailplane (left side) Vertical tail
????X(m) ??Z(m) ??P(kN) ??X(m) ??Y(m) ??P(kN)
Demarcate load ????1 ????21.890 ??1.948 ????-9 ??20.803 ??3.390 ????10
????2 ????22.009 ??2.343 ????-9 ??21.974 ??3.790 ????10
????3 ????22.128 ??2.739 ????-7 ??21.145 ??4.190 ????7
????4 ????22.705 ??1.948 ????-9 ??21.902 ??3.390 ????10
????5 ????22.770 ??2.343 ????-9 ??22.003 ??3.790 ????10
????6 ????22.836 ??2.739 ????-7 ??22.103 ??4.190 ????7
????7 ????22.298 ??1.948 ??-12 ??21.353 ??3.390 ????14
????8 ????22.390 ??2.343 ??-12 ??21.488 ??3.790 ????14
????9 ????22.482 ??2.739 ??-12 ??21.624 ??4.190 ????14
Check load ????1 ????22.230 ??2.091 ??-12 ??21.276 ??3.600 ????14
????2 ????22.433 ??2.091 ??-12 ??21.572 ??3.600 ????14
????3 ????22.347 ??2.798 ??-9 ??21.402 ??4.100 ????10
????4 ????22.644 ??2.798 ??-9 ??21.785 ??4.100 ????10
2.4 aerofoil load position and restriction
Its contact area of intersection point place that all points of load must be applied to rib and spar on the aerofoil is not less than 120 * 160.
The each point load limit is as follows:
Wing 21 ribs-5kN
19 ribs-10kN
17 ribs-12kN
14 ribs-20kN
9,11 ribs-35kN
7 ribs-50kN
Horizontal tail 9 ribs are with interior each point 6kN, in addition to 12 rib each point 3kN.
Vertical fin 10 ribs are with interior each point 7kN, in addition to 13 rib each point 4kN.
5 test methods
5.1 wing is demarcated loading method
5.1.1 aircraft floor status of support
Aircraft jack-up, is fulcrum with 20 frame carriages and preceding with aircraft master lifting jack, makes the main landing gear built on stilts, makes central wing keep horizontality, and adds the protection carriage at fuselage 31 frame places, and aircraft can not roll when guaranteeing to load.Before play the most following of pillar and live with the column pad, and block in front with the assurance aircraft with block (or weight) and can not move forward.The angle on aircraft system horizontal line and ground is approximately 3 ° (bowing) and sees Fig. 4.
5.1.2 wing is demarcated loading method
Starboard wing with three secondary clamps (11 ribs, 15 ribs, 20 ribs) port wing second mate clamps (11 ribs, 15 ribs) when left and right sides wing loads with 11 ribs, 15 ribs, left-right symmetric loads, when starboard wing 15 ribs, when 20 ribs load, port wing adds balancing load (total outer ∑ MX=0 that carries).
Utilize the main jack pair wing of aircraft to load, force transducer is placed on main lifting jack upper end, withstands on to load in the middle of the lever, and the two ends of lever are connected with two clamps on the wing.Clamp by change lever positions and lifting jack position and vertex position realization loading requirement, is seen Fig. 1, Fig. 5 at three loading positions of wing front and rear beam and front and rear beam center.
5.1.2.1 demarcating, wing I tangent plane loads
Starboard wing 15 ribs, 20 ribs load, port wing 11 ribs, 15 ribs add balancing load, and port wing uses the hole 11 that loads lever to link to each other with 11 rib clamp center pits, and hole 12 links to each other with 15 rib clamp center pits, hole 14 links to each other with very heavy summit, and the starboard wing lever connects and load sees Table 4.
Table 4 wing I tangent plane nominal data (in the table data unreceipted be the starboard wing data)
Test situation Position, 15 rib clamp hole Load lever hole number Position, 20 rib clamp hole Load lever hole number Hole, lifting jack position number Thousand Ns of right flank load Right load is pressed heart X Right load is pressed heart Z Thousand Ns of left wing's load
????1 Before ????28 Before ????29 ????30 ????25 ????9.868 ???11.000 ???30.02
????2 Before ????28 Before ????29 ????31 ????30 ????9.929 ???11.450 ???37.50
????3 Before ????28 Before ????29 ????32 ????20 ????9.989 ???11.900 ???25.98
????4 After ????33 After ????34 ????35 ????25 ????10.577 ???11.000 ???30.02
????5 After ????33 After ????34 ????36 ????30 ????10.602 ???11.450 ???37.50
????6 After ????33 After ????34 ????37 ????20 ????10.626 ???11.900 ???25.98
????7 In ????38 In ????39 ????40 ????40 ????10.223 ???11.000 ???48.03
????8 In ????38 In ????39 ????41 ????40 ????10.265 ???11.450 ???50.00
????9 In ????38 In ????39 ????42 ????40 ????10.308 ???11.900 ???51.97
????10 In ????43 Before ????44 ????45 ????40 ????10.171 ???11.417 ???49.85
????11 In ????46 After ????47 ????48 ????40 ????10.353 ???11.417 ???49.85
????12 Before ????49 In ????50 ????51 ????30 ????10.214 ???12.210 ???39.98
????13 After ????52 In ????53 ????54 ????30 ????10.460 ???12.210 ???39.98
5.1.2.2 wing II, III, IV tangent plane are demarcated and are loaded
Left and right sides wing loads in 11 ribs, 15 ribs symmetry, and lever connects and load sees Table 5.
Table 5: wing II, III, IV tangent plane nominal data
Test situation Position, 11 rib clamp hole Load lever hole number Position, 15 rib clamp hole Load lever hole number Hole, lifting jack position number Thousand Ns of right flank load Right load is pressed heart X Right load is pressed heart Z
????1 Before ????1 Before ????2 ????3 ????40 ??9.565 ??8.760
????2 Before ????1 Before ????2 ????4 ????50 ??9.620 ??9.160
????3 Before ????1 Before ????2 ????5 ????35 ??9.687 ??9.660
????4 After ????6 After ????7 ????8 ????40 ??10.456 ??8.760
????5 After ????6 After ????7 ????9 ????50 ??10.478 ??9.160
????6 After ????6 After ????7 ????10 ????35 ???10.505 ??9.660
????7 In ????11 In ????12 ????13 ????60 ???10.011 ??8.760
????8 In ????11 In ????12 ????14 ????60 ???10.049 ??9.160
????9 In ????11 In ????12 ????15 ????60 ???10.096 ??9.660
????10 In ????16 Before ????17 ????18 ????60 ???9.918 ??9.075
????11 In ????19 After ????20 ????21 ????60 ???10.164 ??9.075
????12 Before ????22 In ????23 ????24 ????50 ???9.960 ??9.850
????13 After ????25 In ????26 ????27 ????50 ???10.269 ??9.850
5.1.3 tailplane is demarcated loading method
5.1.3.1 aircraft state
Aircraft keeps stopped status, nose-gear, and main landing gear is tight with the catch retaining, with 20 frame carriages aircraft is held, and adds counterweight (or with fuselage 31 frame carriages) at the fuselage front deck and comes balance Z to moment
5.1.3.2 demarcation loading method
Left and right sides horizontal tail is equipped with clamp at 3 ribs, 10 rib places, each clamp has three to load the hole at the front and rear beam of horizontal tail and the center of front and rear beam, each load condition is connected with 3 ribs, 10 rib clamps with a lever, left and right sides horizontal tail connects with a lever again, ground is with a rail versatilely, press 4~5 tons of counterweights above, do not fall to connecting sensor with jin, on connect combining leverage, down connect versatilely that rail loads, Fig. 2 is seen in the load(ing) point position, load sees Table 2, installation form is seen Fig. 6, and 9 ° at the tailplane upper counterangle guarantees during loading that loading direction is vertical with horizontal tail string plane.
5.1.3.3 lever connects and magnitude of load
The horizontal tail lever connects and magnitude of load sees Table 6
The lever of table 6 horizontal tail: V, VI tangent plane connects and load data
Test situation Position, 3 rib clamp hole Load lever hole number Position, 10 rib clamp hole Load lever hole number Lever center pit number Combining leverage hole number The lever web member is long Load coordinate X value Always add thousand Ns of load
??1 Before ??1 Before ??2 ??3 ??1 ??989 ?21.890 ??17.78
??2 Before ??1 Before ??2 ??4 ??2 ??1052 ?22.009 ??17.78
??3 Before ??1 Before ??2 ??5 ??3 ??1115 ?22.128 ??13.83
??4 After ??11 After ??12 ??13 ??1 ??989 ?22.705 ??17.78
??5 After ??11 After ??12 ??14 ??2 ??1052 ?22.770 ??17.78
??6 After ??11 After ??12 ??15 ??3 ??1115 ?22.836 ??13.83
??7 In ??6 In ??7 ??8 ??1 ??989 ?22.298 ??23.70
??8 In ????6 In ????7 ????9 ????2 ????1052 ?22.390 ??23.70
??9 In ????6 In ????7 ????10 ????3 ????1115 ?22.482 ??23.70
?10 In ????6 Before ????16 ????17 ????4 ????1011 ?22.230 ??23.70
?11 In ????6 After ????18 ????19 ????4 ????1011 ?22.433 ??23.79
?12 Before ????6 In ????20 ????21 ????5 ????1125 ?22.347 ??17.78
?13 After ????22 In ????23 ????24 ????5 ????1125 ?22.644 ??17.78
Annotate: tangent plane web member length counts 3 ribs, 390,10 ribs, 430 unit millimeters.
5.1.4 vertical tail is demarcated loading method
5.1.4.1 aircraft state
Aircraft state is identical when demarcating loading with tailplane
5.1.4.2 the side direction support of aircraft
What the vertical fin demarcation added is that Z is to load, thereby to aircraft can produce Y to X to moment, must give the certain constraint of aircraft, upright side direction column that 3m is high on airframe 43 frame right sides, column is pressed in ground with counterweight, adorn in column upper end and the identical place of 43 frame height one with the identical wooden unit of 43 frame profiles, preceding and aircraft 43 frames of test are close to.
5.1.4.3 demarcation loading method
Vertical fin 5 ribs, 10 ribs block with the loading clamp, utilize one to load the load that each situation is implemented in the lever change position, magnitude of load sees Table 2, and Fig. 3 is seen in the load(ing) point position, utilize the cantilever pulley of 15 tons of cranes, an end links to each other with the loading lever with sensor by wire rope.The other end utilizes pulley guiding and jin not to fall to joining, and the do not fall other end and crane of jin fixed, and utilizes jin not drop into row and loads, and sees Fig. 7.
5.1.4.4 lever connects and magnitude of load
The vertical fin lever connects and magnitude of load sees Table 7
Table 7: vertical fin: the lever of VII tangent plane connects and load data
Test situation Position, 5 rib clamp hole Load lever hole number Position, 10 rib clamp hole Load lever hole number Lever center pit number Thousand Ns of side loads Side load is pressed heart X Side load is pressed heart Y
????1 Before ????1 Before ????2 ????3 ????10 ??20.803 ??3.390
????2 Before ????1 Before ????2 ????4 ????10 ??20.974 ??3.790
????3 Before ????1 Before ????2 ????5 ????7 ??21.145 ??4.190
????4 After ????6 After ????7 ????8 ????10 ??21.902 ??3.390
????5 After ????6 After ????7 ????9 ????10 ??22.003 ??3.790
????6 After ????6 After ????7 ????10 ????7 ??22.103 ??4.190
????7 In ????11 In ????12 ????13 ????14 ??21.353 ??3.390
??8 In ????11 In ????12 ????14 ????14 ??21.488 ??3.790
??9 In ????11 In ????12 ????15 ????14 ??21.624 ??4.190
??10 In ????11 Before ????16 ????17 ????14 ??21.276 ??3.600
??11 In ????11 After ????18 ????19 ????14 ??21.572 ??3.600
??12 Before ????1 In ????20 ????21 ????10 ??21.402 ??4.100
??13 After ????11 In ????22 ????23 ????10 ??21.785 ??4.100
In addition, the present invention is not only applicable to aircraft wing, for the structure of other similar wing, so long as under the condition of not dismantling, with sensor device test machine wing load, all belong to protection scope of the present invention.

Claims (15)

1, a kind of aircraft wing load field calibration test method, it keeps demarcating under the stopped status at aircraft, and it is characterized in that: it is to carry out according to following step under the condition that undercarriage is not dismantled:
(1), demarcate coordinate system, true origin is the fuselage construction horizontal line and the intersection point of O bit line (behind the head 1.0 meters), the X car overlaps with the fuselage construction horizontal line, backward for just, Y-axis makes progress in the aircraft plane of symmetry to just, Z axle sensing left wing and X, Y-axis formation right-handed system;
(2), wing when test with aircraft master lifting jack aircraft jack-up, with the protection carriage and the nose-gear that are added in the fuselage place is fulcrum, make the main landing gear built on stilts, central wing keeps horizontality, and aircraft system horizontal line and ground angle are determined the sectional position of load 2 °~4 ° (bowing), the load sectional tool is representative and guarantee that the installation device of sensor that can count record load is arranged, when when a wing loads, the wing will add balancing load (total outer EMx=0 that carries) in addition, and the record load value;
(3), horizontal tail when test, undercarriage lands, and is tight with the weight retaining before the gear tyre, with carriage aircraft held, and determines the load sectional position, is carried in the load section perpendicular to the horizontal tail string, connects sensor device, and the record loaded load,
(4), vertical fin when test, undercarriage lands, tight with the weight retaining before the gear tyre, the vertical fin side direction loads, and gives the device of a balance lateral loading moment of aircraft, determines to load behind the load sectional position, connects sensor device, and the record loaded load.
2, aircraft wing load field calibration test method according to claim 1, it is characterized in that: all points of load are applied to rib and spar junction on the aerofoil, and its contact area is not less than 120mm * 160mm.
3, aircraft wing load field calibration test method according to claim 1 and 2, it is characterized in that: utilize the main jack pair wing of aircraft to load, force transducer is placed on main lifting jack upper end, withstand on and load in the middle of the lever, the two ends of lever are connected with two clamps on the wing, the section that clamp is determined at wing, three loading positions in wing front and rear beam and front and rear beam center are by change lever positions and lifting jack position and vertex position realization loading requirement.
4, aircraft wing load field calibration test method according to claim 1 and 2, it is characterized in that: left and right sides horizontal tail is equipped with clamp in the load cross section of determining, each clamp has three to load the hole at the front and rear beam of horizontal tail and the center of front and rear beam, each load condition is connected with the clamp of a lever and selected section, left and right sides horizontal tail connects with a lever again, ground is with a rail versatilely, press a counterweight above, do not fall to connecting sensor with jin, on connect combining leverage, down connecing versatilely, rail loads.
5, aircraft wing load field calibration test method according to claim 3, it is characterized in that: left and right sides horizontal tail is equipped with clamp in the load cross section of determining, each clamp has three loadings at the front and rear beam of horizontal tail and the center of front and rear beam, each load condition is connected with the clamp of a lever and selected section, left and right sides horizontal tail connects with a lever again, ground is with a rail versatilely, press a counterweight above, do not fall to connecting sensor with jin, on connect combining leverage, down connecing versatilely, rail loads.
6, aircraft wing load field calibration test method according to claim 1 and 2, it is characterized in that: when vertical fin loads, the device of giving a balance lateral loading moment of aircraft be one on airframe (43) frame right side upright side direction column, column is pressed in ground with counterweight, adorn in column upper end and the identical place of (43) frame height one with the identical wooden unit of (43) frame profile, preceding and aircraft (43) frame of test is close to.
7, aircraft wing load field calibration test method according to claim 3, it is characterized in that: vertical fin give when loading the device of a balance lateral loading moment of aircraft be one on airframe (43) frame right side upright side direction column, column is pressed in ground with counterweight, adorn in column upper end and the identical place of (43) frame height one with the identical wooden unit of (43) frame profile, preceding and aircraft (43) frame of test is close to.
8, aircraft wing load field calibration test method according to claim 5, it is characterized in that: vertical fin give when loading the device of a balance lateral loading moment of aircraft be one on airframe (43) frame right side upright side direction column, column is pressed in ground with counterweight, adorn in column upper end and the identical place of (43) frame height one with the identical wooden unit of (43) frame profile, preceding and aircraft (43) frame of test is close to.
9, aircraft wing load field calibration test method according to claim 1 and 2, it is characterized in that: when vertical fin loads, selected section blocks with clamp, utilize one to load the load that each situation is implemented in the lever change position, utilize the cantilever pulley of a crane, an end links to each other with the loading lever with sensor by wire rope, the other end utilizes pulley guiding and jin not to fall to joining, the do not fall other end and crane of jin fixed, and utilize jin not drop into row and load, and the record load value.
10, aircraft wing load field calibration test method according to claim 3, it is characterized in that: when vertical fin loads, selected section blocks with clamp, utilize one to load the load that each situation is implemented in the lever change position, utilize the cantilever pulley of a crane, an end links to each other with the loading lever with sensor by wire rope, the other end utilizes pulley guiding and jin not to fall to joining, the do not fall other end and crane of jin fixed, and utilize jin not drop into row and load, and the record load value.
11, aircraft wing load field calibration test method according to claim 5, it is characterized in that: when vertical fin loads, selected section blocks with clamp, utilize one to load the load that each situation is implemented in the lever change position, utilize the cantilever pulley of a crane, an end links to each other with the loading lever with sensor by wire rope, the other end utilizes pulley guiding and jin not to fall to joining, the do not fall other end and crane of jin fixed, and utilize jin not drop into row and load, and the record load value.
12, aircraft wing load field calibration test method according to claim 8, it is characterized in that: when vertical fin loads, selected section blocks with clamp, utilize one to load the load that each situation is implemented in the lever change position, utilize the cantilever pulley of a crane, an end links to each other with the loading lever with sensor by wire rope, the other end utilizes pulley guiding and jin not to fall to joining, the do not fall other end and crane of jin fixed, and utilize jin not drop into row and load, and the record load value.
13, realize the isolated plant of claim 1 or 2 described aircraft wing load field calibration test methods, it is characterized in that: the sensor device of aircraft is that force transducer is placed on the lifting jack upper end, withstand on and load in the middle of the lever, the two ends of lever are connected with two clamps on the wing, and clamp is stuck in the definite section of wing, three loading positions of wing front and rear beam and front and rear beam center by change lever positions and lifting jack position and vertex position realization loading requirement.
14, realize the isolated plant of claim 1 or 2 described aircraft wing load field calibration test methods, it is characterized in that: the horizontal tail charger is that left and right sides horizontal tail is equipped with clamp in the load cross section of determining, each clamp has three to load the hole at the front and rear beam of horizontal tail and the center of front and rear beam, each load condition is connected with the clamp of a lever and selected section, left and right sides horizontal tail connects ground with a lever again and presses a counterweight versatilely above the rail with one, do not fall to connecting sensor with jin, on connect combining leverage, down connecing versatilely, rail loads.
15, realize the isolated plant of claim 1 or 2, it is characterized in that: the vertical fin charger is to block with clamp at selected section, utilize one to load the load that each situation is implemented in the lever change position, utilize the cantilever pulley of a crane, one end by wire rope and sensor with load lever and link to each other, the other end utilizes pulley guiding and jin not to fall to joining, jin the do not fall other end and crane are fixed, utilize jin not drop into row and load, and the record load value.
CN 02158959 2002-12-31 2002-12-31 Full machine ground load on site calibration test method and its device Expired - Fee Related CN1273813C (en)

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