CN105547676A - Multifunctional swing-arm type rotor wing test stand - Google Patents
Multifunctional swing-arm type rotor wing test stand Download PDFInfo
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- CN105547676A CN105547676A CN201510993597.9A CN201510993597A CN105547676A CN 105547676 A CN105547676 A CN 105547676A CN 201510993597 A CN201510993597 A CN 201510993597A CN 105547676 A CN105547676 A CN 105547676A
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Abstract
The invention discloses a multifunctional swing-arm type rotor wing test stand. The test stand mainly comprises a test stand support seat, a swing arm motion mechanism, a swing arm rotation driving mechanism and an adjusting mechanism. By using the test stand, problems that a test that a new layout multi-rotor-wing helicopter uses a wind tunnel to carry out hovering and a maneuvering forward flight performance measurement test are difficult, a test period is long and test manpower and material resources are large are solved preliminarily. The invention provides a novel multifunctional swing-arm type rotor wing test stand scheme in which the wind tunnel is not needed and the scheme can be performed in a general room. Tests of hovering, non-driven forward flight, driving forward flight, lift-direction free forward flight, lift-direction constraint forward flight and the like can be performed. A plurality of layout combination of rotor wings can be performed, such as a single rotor wing, coaxial twin rotor wings, longitudinal column type twin rotor wings, traverse column type twin rotor wings, corresponding a plurality of new combined layouts and the like. The coaxial twin rotor wings are simulated by two single rotor wings which are arranged oppositely up and down. Complex driving and control systems of a coaxial twin-rotor-wing helicopter are omitted.
Description
Technical field
The present invention relates to Aviation Test field of measuring technique, particularly relate to a kind of Multifunction swing-arm type rotor model.test system.
Background technology
At present, portable rotor model.test system when general rotor model.test system flies before being mainly divided into the fixed rotor model.test system of simulation floating state, simulation according to the state of flight measuring rotor and the tilting rotor testing table of simulation tiltrotor.Various rotor model.test system feature is as follows:
(1) fixed rotor model.test system is comparatively common, as the 2m level rotor model.test system of Nanjing Aero-Space University.This testing table mainly carries out hover performance test and the flow field analysis work of rotor, be placed in wind-tunnel experiment work when also can carry out Hingeless Rotor in Forward Flight, but have following deficiency: the body supports partial volume of this type of testing table is larger on the one hand, can cause larger interference to the nearly flow field of rotor and flow field far away in wind-tunnel, and the bearing of larger front face area can cause certain blocking effect to wind-tunnel; Can relate to rotor various trim when flying before simulation on the other hand and adjust the complex process of ginseng, and the adjustment overwhelming majority of this trim and parameter is all obtain based on theory calculate in earlier stage, thus to rotor true before fly to simulate and also there is certain difference.So the test type that fixed rotor model.test system can carry out is limited, even if fly before thinking simulation, also must realizes by wind-tunnel, thus add the cost of test.
(2) portable rotor model.test system is also in blank at home, also only has " the long track " of the Princeton University of the U.S. and " railcar " of Tokyo Univ Japan abroad.Construction difficulty is large on the one hand, floor area is large, expenditure of construction is high for the maneuvering flight testing table of the type; Easily be subject to ambient weather environmental impact during test on the other hand, be difficult to find suitable test condition.
(3) special tilting rotor testing table various countries are also also few, current U.S. NASA makees the tilting rotor testing table of overtesting to tiltrotor aircrafts such as XV-15, V-22 at Langley research centre (LaRC), the more fixed rotor model.test system of testing table of the type is many complicated oil pressure actuated rotating mechanism, which increases overall structural complexity and construction weight.
Summary of the invention
In order to overcome above-mentioned the deficiencies in the prior art, the invention provides the arm-type rotor model.test system of a kind of multifunctional rotary, limited to solve existing rotor model.test system function, complicated in mechanical structure, construction weight is heavier, system complex, test needs particular surroundings as by wind-tunnel, needs the shortcomings such as complicated theory calculate preliminary work before test.
The arm-type rotor model.test system of multifunctional rotary of the present invention, comprises testing table bearing, cantilever motion mechanism, spiral arm rotary drive mechanism, governor motion.
Described testing table bearing is made up of the main stay pipe that base and base are vertically installed; Cantilever motion mechanism has spiral arm beam, and spiral arm beam is arranged on main supporting steel pipe top, makes spiral arm beam have two degree of freedom, and one degree of freedom is the rotary motion of spiral arm beam in surface level; Another degree of freedom is the small magnitude flapping action of spiral arm beam in perpendicular; The rotary motion of above-mentioned spiral arm beam in surface level is driven by spiral arm rotary drive mechanism and realizes.
Described governor motion is arranged on spiral arm beam left part, and entirety is framed structure, and the top of framework and bottom have symmetrical single rotor installation position, and the upper-lower position of single rotor installation position is adjustable, is used for installing single rotor system; There is on rear side of framework tail and push away screw propeller installation position, and tail to push away screw propeller installation position front and back position adjustable, be used for that tail is installed and push away screw propeller.
When carrying out rotor system test, single rotor system is arranged on the single rotor installation position on lower rotor lengthwise position adjuster bar, lower rotor lengthwise position adjuster bar by high precision pull/moment of torsion integrative sensor; Single rotor is also provided with speed probe; Tail pushes away screw propeller and is arranged on tail by pressure transducer and pushes away on screw propeller installation position.Single rotor installation position is also used for auxiliary large wing governor motion is installed, realizes the installation of auxiliary large wing.
Single rotary wing performance, single rotor+wing combined type layout performance, the performance of single rotor+wing+thrust screw propeller combined type layout, coaxial double-rotary wing performance, the test of coaxial double-rotary wing+wing combined type layout performance, coaxial double-rotary wing+wing+thrust screw propeller combined type layout performance test can be realized by the arm-type rotor model.test system of above-mentioned multifunctional rotary.
A, single rotary wing performance are tested;
Apply a set of single rotor system, be arranged on single rotor installation position of below;
B, single rotor+wing combined type layout performance test;
On the basis of a, single rotor installation position of below installs auxiliary large wing additional;
C, single rotor+wing+thrust screw propeller combined type layout performance test;
On the basis of b, install afterbody thrust propeller set additional;
D, coaxial double-rotary wing performance test;
On the basis of a, single rotor system of same size is installed in single rotor installation position up;
The test of e, coaxial double-rotary wing+wing combined type layout performance;
On the basis of d, single rotor installation position of below is installed auxiliary large wing;
F, coaxial double-rotary wing+wing+thrust screw propeller combined type layout performance test;
On the basis of e, install afterbody thrust propeller set additional.
The testing table of above-mentioned often kind of layout type all can complete separately hovering test and fly test before simulating, and when carrying out hovering test, not being worked by the power-off of spiral arm drive motor, making the rotation condition of spiral arm beam in surface level dead.And spiral arm drive motor energising work when flying before doing to test, rotate with constant angular velocity according to testing requirements, the rotation condition of spiral arm beam in surface level is removed, thus single rotor system is in constant incoming flow environment all the time.Can carry out thus external force drive with without outer power-actuated before fly simulated experiment.Meanwhile, when flying simulated experiment before carrying out, also retrain by spacer pin in the rotation of spiral arm beam in perpendicular, thus may carry out complete freely and semi-free before fly simulation test.Semi-free is the motion retrained in rotary course by rotor system on lift direction, and is freely full the rippling that rotary motion in the existing surface level of rotor system has on lift direction.When various layout is tested, pass through installed high precision pull/moment of torsion integrative sensor to measure the moment of torsion of rotor and pulling force, measured by the rotating speed of speed probe to rotor, by pressure transducer, the thrust that tail pushes away screw propeller is measured; The measurement data signals of three sensors arrives ground data processing end by each signal data transmission line and carries out analog to digital conversion, and multiple amplifies, Noise reducing of data, the process such as Data Integration, finally obtains the measured value needed.
The invention has the advantages that:
1, the arm-type rotor model.test system of multifunctional rotary of the present invention, the function singleness solving existing rotor model.test system is limited, complicated in mechanical structure, construction weight is heavier, system complex, and part test platform needs the cooperation of wind-tunnel just can complete test, needs complicated theory calculate preliminary work before test, the shortcomings such as use cost is high, and time cost is large;
2, the arm-type rotor model.test system of multifunctional rotary of the present invention, solve existing rotor model.test system function limited, complicated in mechanical structure, construction weight is heavier, and test needs particular surroundings as by shortcomings such as wind-tunnel.
Accompanying drawing explanation
Fig. 1 is multifunctional rotary of the present invention arm-type rotor model.test system one-piece construction schematic diagram;
Fig. 2 tests table mount and spiral arm rotary drive mechanism structural representation in the arm-type rotor model.test system of multifunctional rotary of the present invention;
Fig. 3 is spiral arm motion 2 structural representation in the arm-type rotor model.test system of multifunctional rotary of the present invention;
Fig. 4 is governor motion structural representation in the arm-type rotor model.test system of multifunctional rotary of the present invention;
Fig. 5 is test rotor system of the present invention composition and mounting means schematic diagram;
Fig. 6 is that single rotary wing performance is test bed;
Fig. 7 is single rotor+wing combined type layout property test platform;
Fig. 8 is single rotor+wing+afterbody thrust screw propeller combined type layout property test platform;
Fig. 9 is coaxial double-rotary wing property test platform;
Figure 10 is coaxial double-rotary wing+wing combined type layout property test platform;
Figure 11 is coaxial double-rotary wing+wing+afterbody thrust screw propeller combined type layout property test platform.
In figure:
1-testing table bearing 2-spiral arm motion 3-spiral arm rotary drive mechanism
4-governor motion 5-power module 6-rotor system
The main supporting steel pipe of 7-collector ring 101-base 102-
103-diagonal brace angle steel 104-assists angle steel 201-spiral arm beam
The horizontal hinged-support of the horizontal hinge cover 203-horizontal hinge 204-of 202-spiral arm motion
205-short turning axle 206-location-plate 207-locating sleeve
208-register pin 301-long turning axle 302-reduction gear box
303-spiral arm drive motor 401-governor motion erecting frame 402-rotor spacing regulating sleeve
Under 403-upper rotor lengthwise position adjuster bar 404-, rotor lengthwise position adjuster bar 405-tail pushes away screw propeller lengthwise position adjuster bar
406-tail pushes away propeller shaft and pushes away screw propeller lengthwise position regulating sleeve 408-tail to position adjustments bar 407-tail and push away propeller shaft to position adjustments cover
409-locating sleeve 410-backstay 411-backstay B
The mono-rotor system of 412-backstay C413-backstay D501-
502-assists large wing 503-afterbody thrust screw propeller
Embodiment
Below in conjunction with drawings and Examples, the invention will be further described.
The arm-type rotor model.test system of multifunctional rotary of the present invention comprises testing table bearing 1, spiral arm motion 2, spiral arm rotary drive mechanism 3 and governor motion 4, as shown in Figure 1, for testing rotor system 5 performance.
Described testing table bearing 1 comprises base 101, main supporting steel pipe 102, diagonal brace angle steel 103 and auxiliary angle steel 104, as shown in Figure 2.Wherein, base 101 circumference 4 uniform positions and diagonal brace angle steel 103 one end are fixed, and all circumferential uniform with main supporting steel pipe sidewall 4 positions of diagonal brace angle steel 103 other end are fixed.For reinforcement experiment table mount 1 bottom structure, by 4 auxiliary angle steel 104,4 positions uniform with main supporting steel pipe 102 sidewall circumference in the middle part of 4 bearing diagonal angle steel are fixed.Main supporting steel pipe 102 top is used for installing spiral arm motion 2.
Described spiral arm motion 2 comprises spiral arm beam 201, spiral arm moves horizontal hinge cover 202, horizontal hinge 203, horizontal hinged-support 204 and short turning axle 205, as shown in Figure 3.Wherein, the spiral arm horizontal hinge cover 202 that moves is socketed on spiral arm beam 201, and is arranged in the horizontal hinged-support 204 of U-shaped structure, and be connected with horizontal hinge 203 by deep groove ball bearing, horizontal hinge 203 two ends and horizontal hinged-support 204 two ends are fixed.Dynamic stability factor during owing to considering the static stability of spiral arm beam 201 and rotating, therefore the move link position of horizontal hinge cover 202 and horizontal hinged-support 204 of horizontal hinge 203 and spiral arm is positioned at spiral arm and moves the top of horizontal hinge cover 202.Short turning axle 205 is vertically arranged, and one end and spiral arm horizontal hinge cover 202 bottom surface of moving is fixed, and the other end is used for connecting spiral arm rotary drive mechanism 3.Short turning axle 205 is connected with the main supporting steel pipe 102 in testing table bearing 1 by bearing seat, and concrete mode is: bearing seat is fixedly installed in the top end of main supporting steel pipe 102, is connected with short turning axle 205 upper end bearing by the bearing arranged in bearing seat; And then the location realized between spiral arm motion 2 and testing table bearing 1.Thus, make spiral arm beam 201 have two degree of freedom, one degree of freedom be spiral arm beam 201 around the rotary motion of short turning axle 205 in surface level, radius of turn is 4m, is driven by spiral arm rotary drive mechanism 3; Second is optional degree of freedom is that spiral arm beam 201 is around the small magnitude flapping action of horizontal hinge 203 in vertical plane, comprehensive aerodynamic force according to the rotor system performance of simulated flight state and aerodynamic interference mutually drives, thus the mutual superposition of two degree of freedom can realize the rotor system of simulated flight state complete freely simulate before fly.
Above-mentioned spiral arm beam 201 retrains by positioning component around the small magnitude flapping action of horizontal hinge 203; Positioning component comprises location-plate 206, locating sleeve 207 and register pin 208, as shown in Figure 3; Location-plate 206 is two, and stiff end is fixedly mounted on horizontal hinged-support 204 both sides respectively.Locating sleeve 207 is fixedly sleeved on spiral arm beam 201, between the positioning end being positioned at two location-plates 206.On locating sleeve 207 both sides and two location-plate 206 stiff ends, correspondence position has pilot hole, by register pin 208 through fixing after homonymy location-plate 206 and the pilot hole on locating sleeve 207, and then realize spacing around the flapping action of horizontal hinge 203 small magnitude of spiral arm beam 201; After being extracted by register pin 208, the small magnitude flapping action of spiral arm beam 201 around horizontal hinge 203 can be realized, so reach simulated flight state rotor system semi-free simulation before fly.
Above-mentioned spiral arm rotary drive mechanism 3 comprises long turning axle 301, reduction gear box 302 and spiral arm drive motor 303, as shown in Figure 2.Wherein, spiral arm drive motor 303 adopts 220V direct current permanent magnet motor, power 750w, speed adjustable range 10-1800rpm; Spiral arm drive motor 303 is fixedly mounted on the base 101 of testing table bearing 1 by electric machine support.Spiral arm drive motor 303 output shaft is provided with reduction gear box 302, and reduction gear box 302 adopts the worm speed-down case of 30:1 high reduction gear ratio.Long turning axle 301 is vertically arranged, and top is coaxially fixed by flexible clutch and short turning axle 205, and bottom is coaxially fixed by the output shaft of flexible clutch and reduction gear box 302.Long turning axle 301 is connected with the main supporting steel pipe 102 in testing table bearing 1 by bearing seat, and concrete mode is: bearing seat is fixedly installed in the top of main supporting steel pipe 102, is connected with long turning axle 301 upper end bearing by the bearing arranged in bearing seat; And then the location realized between long turning axle 301 and testing table bearing 1.After being slowed down by the output of reduction gear box 302 pairs of spiral arm drive motor 303, drive long turning axle 301 to rotate by motor, and then drive short turning axle 205 to rotate, realize the rotary motion of spiral arm beam 201 around short turning axle 205.
Described governor motion 4 is arranged on the installation end of spiral arm beam 201, as shown in Figure 4, comprise governor motion erecting frame 401, rotor spacing regulating sleeve 402, upper rotor lengthwise position adjuster bar 403, lower rotor lengthwise position adjuster bar 404, tail push away screw propeller lengthwise position adjuster bar 405, tail pushes away propeller shaft and push away screw propeller lengthwise position regulating sleeve 407 to position adjustments bar 406, tail and push away propeller shaft with tail and overlap 408 to position adjustments.
Wherein, tail pushes away propeller shaft and is arranged on the stiff end of spiral arm beam 201 to the stiff end of position adjustments cover 408; Tail pushes away propeller shaft and is designed with tail and pushes away propeller shaft to position adjustments hole on position adjustments cover 408, and governor motion 4 mounting hole.Governor motion erecting frame 401 is the U-shaped structural framing be made up of two erecting frame cross bars and an erecting frame vertical pole; Erecting frame vertical pole pushes away propeller shaft after governor motion 4 mounting hole on position adjustments cover 408 through tail, and fix by holding out against screw, fixed position is positioned in the middle part of erecting frame vertical pole, and makes erecting frame vertical pole perpendicular to spiral arm beam 201, and vertically arranges.Two rotor spacing regulating sleeves 402 are fixedly mounted on the end of two erecting frame cross bars respectively; Two rotor spacing regulating sleeves 402 are designed with rotor position adjustments hole.Upper rotor lengthwise position adjuster bar 403, lower rotor lengthwise position adjuster bar 404 are each passed through the rotor position adjustments hole on two rotor spacing regulating sleeves 402, fixed by rotor set screw, make rotor adjuster bar and lower rotor adjuster bar vertical with two erecting frame cross bars respectively, and vertically arrange.Upper rotor adjuster bar and lower rotor adjuster bar opposite side are used for installing a set of single rotor system respectively; After unclamping rotor set screw, rotor adjuster bar and lower rotor adjuster bar can be made in fact in lengthwise movement, and then realize the adjustment of upper and lower two cover rotor system spacing.It is the L-type structure be made up of adjuster bar A and mounting rod A to position adjustments bar 406 that tail pushes away propeller shaft, adjuster bar A pushes away propeller shaft after governor motion 4 mounting hole on position adjustments cover 408 through tail, push away propeller shaft by tail to fix to set screw, make adjuster bar A and governor motion erecting frame 401 place plane orthogonal, and mounting rod A is parallel with erecting frame cross bar.Described mounting rod A end winding support is installed tail and is pushed away screw propeller lengthwise position regulating sleeve 407; Tail pushes away and screw propeller lengthwise position regulating sleeve 407 is designed with tail pushes away screw propeller lengthwise position adjustment hole.It is the L-type structure be made up of adjuster bar B and mounting rod B that tail pushes away screw propeller lengthwise position adjuster bar 405, after adjuster bar B pushes away screw propeller lengthwise position adjustment hole through tail, push away the longitudinal set screw of screw propeller by tail to fix, make adjuster bar B vertical with adjuster bar A, mounting rod B and adjuster bar A be arranged in parallel.Mounting rod B end, towards governor motion erecting frame 401 place plane, is used for installing.Pushing away propeller shaft to set screw by unclamping tail thus, making tail push away propeller shaft to position adjustments bar 406 along the axially-movable of afterbody thrust screw propeller 503, and then the axial location realizing afterbody thrust screw propeller 503 regulates; Pushing away the longitudinal set screw of screw propeller by unclamping tail, make tail push away screw propeller lengthwise position adjuster bar 405 and longitudinally move, and then the lengthwise position realizing afterbody thrust screw propeller 503 regulating.
Be positioned at the erecting frame cross bar of top in governor motion 4 of the present invention, overlap on position fixed ends and have locating sleeve 409 above mounting rod vertical pole with on spiral arm two, by pin, the locating sleeve 409 above the erecting frame cross bar of backstay A410 and top, erecting frame vertical pole and on spiral arm beam on close position fixed ends is fixed.On below the erecting frame cross bar, erecting frame vertical pole of below, cover has locating sleeve 409, is fixed by the locating sleeve 409 below the erecting frame cross bar of backstay B411 and below, erecting frame vertical pole and on spiral arm beam on close position fixed ends by pin.Push away propeller shaft at tail to overlap on the mounting rod A in adjuster bar and have locating sleeve 409, on adjuster bar A, also cover has two locating sleeves 409, a locating sleeve 409 on backstay C412 and mounting rod A and the locating sleeve 409 above mounting rod vertical pole is fixed by pin; By pin, another locating sleeve 409 on backstay D413 and mounting rod B and the locating sleeve 409 on adjuster bar A are fixed; Thus, the relative position realized between each rod member is fixed, and forms three-legged structure between each bar in each backstay and governor motion 4, and then reinforces whole governor motion 4, strengthens the rigidity of governor motion 4; And pin is unloaded the position adjustments between can realizing in governor motion 4 between each bar.
The arm-type rotor model.test system of multifunctional rotary of the present invention adopts two kinds of form power supplys to power, and comprises direct supply (DC) and AC power (AC).AC power adopts civil power 220V alternating current, and direct supply is the lithium battery group of 12S48V, and two kinds of power supply mounting interface positions are all placed in testing table bearing 1 place.The 220v alternating current of the output of AC power turns DC Module by interchange, and to transfer direct current to be that spiral arm drive motor 303 is powered.Due to when testing, single rotor system installation site is positioned at the termination of spiral arm beam 201, therefore the circuit trace of direct supply is: the power lead output terminal of direct supply accesses the electron speed regulator ESC DC terminal of single rotor system, and then to adjust ESC direct current to be changed into alternating current by electricity be that the drive motor of single rotor system is powered.The input end of direct supply power lead is along on adjuster bar in governor motion 4 and governor motion erecting frame 401 to spiral arm beam 201, then along spiral arm beam 201 to horizontal free bearing, enter in short turning axle 205 by the perforate on horizontal hinged-support 204, the end of incoming cables of overhanging collector ring 7 inner ring with being installed on short turning axle 205 of the elliptical opening again on short turning axle 205 sidewall is connected, collector ring inner ring is fixedly mounted on short turning axle 205, the leading-out terminal of collector ring 7 outer shroud is connected to direct supply along main supporting steel pipe 102, avoid when testing by collector ring 7, due to the rotation of spiral arm beam 201, cause the winding of DC power supply circuit.
By the arm-type rotor model.test system of above-mentioned multifunctional rotary, can carry out single rotary wing performance, single rotor+wing combined type layout performance, the performance of single rotor+wing+thrust screw propeller combined type layout, coaxial double-rotary wing performance, the test of coaxial double-rotary wing+wing combined type layout performance, coaxial double-rotary wing+wing+thrust screw propeller combined type layout performance test, concrete mode is as follows:
Test rotor system 5 comprises two cover list rotor systems 501, auxiliary large wing 502, afterbody thrust screw propeller 503, as shown in Figure 5.Wherein, single rotor system 501 has the JR700 magnitude electronic model plane main rotor part of standard, and complete total distance and cyclic pitch control system, rotor diameter D=1.6m, NACA0012 symmetrical airfoil turns blade without negative twist.When testing, in test rotor system 5, each several part is installed in the following way: the integral installation of single rotor system 501, on high precision pull/moment of torsion integrative sensor 504, is installed on the end of upper rotor lengthwise position adjuster bar 403 or lower rotor lengthwise position adjuster bar 404 by high precision pull/moment of torsion integrative sensor 504.Single rotor system 501 is also provided with speed probe, speed probe adopts hall sensing formula sensor, its induction small magnet is arranged on the deceleration gear wheel in single rotor system, and hall sensing end installation site is positioned to drive immediately below gear wheel and is right against induction small magnet, and the spacing between strict adjustment hall sensing end and induction small magnet.Afterbody thrust screw propeller 503 is arranged on pressure transducer 505, is arranged on tail pushes away on screw propeller lengthwise position adjuster bar 405 by pressure transducer 505.Above-mentioned high precision pull/moment of torsion integrative sensor 504, speed probe are identical with the cabling mode of direct supply with the cabling mode of the signal data line of pressure transducer 505.Assist the wing of both sides in large wing 502 to form by the rigid foam engraving of external application glass-fiber-fabric, be arranged on lower rotor adjuster bar by auxiliary large wing governor motion 506; Described auxiliary large wing regulates 506 whole mechanism to be framed structure, and the flange that the wing of both sides is designed by end is connected with framework two sides respectively; And perforate flange is designed with along wing fore-and-aft direction, be also designed with perforate along the vertical direction at frame facet, thus by screw through after flange and the perforate on framework, tighten with nut screw connection, realize fixing between wing and installation frame; And unclamp nut, wing can be realized move forward and backward along the perforate on flange, and move up and down along the perforate on frame side wall, simultaneously, wing also can own rotation, and then can regulate according to the position of concrete testing requirements to wing, change the auxiliary relatively single upper-lower position of rotor system of large wing, the adjustment of front and back position, and change the angle of attack of auxiliary large wing; In whole auxiliary large wing adjustment process, both sides wing should synchronously regulate, the symmetry of both sides wing.
1, single rotary wing performance test;
As shown in Figure 6, apply a set of single rotor system 501, be arranged on lower rotor lengthwise position adjuster bar 404 end, form single rotary wing performance test bed, carry out single rotary wing performance test.
2, single rotor+wing combined type layout performance test;
As shown in Figure 7, forming on the test bed basis of single rotor, install auxiliary large wing 502 additional, regulate the upper and lower of the auxiliary relatively single rotor system 501 of large wing 502 and front and back position by auxiliary large wing governor motion 506, form single rotor+wing combined type layout test bed.Thus on the basis that single rotary wing performance is tested, carry out different wing position and the impact of single rotor overall performance is tested.
3, single rotor+wing+thrust screw propeller combined type layout performance test;
As shown in Figure 8, on the basis that single rotor+wing combined type layout is test bed, install afterbody thrust screw propeller 503 additional, form single rotor+wing+thrust screw propeller combined type layout test bed, tail is coordinated to push away the adjustment of screw propeller lengthwise position adjuster bar 405 pairs of afterbody thrust screw propellers about 503 and front and back position, on the basis of single rotor+wing combined type layout performance test, carry out the performance impact test of different afterbody thrust screw propeller 503 position to the multiple this combined type layout entirety of single rotor+wing.
4, coaxial double-rotary wing performance test;
As shown in Figure 9, on the basis of single rotor test experimental bed, single rotor system 501 of same size is added in upper rotor lengthwise position adjuster bar 403 end, i.e. two single rotor systems 501, be installed on upper rotor lengthwise position adjuster bar 403 with on lower rotor lengthwise position adjuster bar 404 respectively by high precision pull/moment of torsion integrative sensor 504, form coaxial double-rotary wing test bed.Thus, on the basis that single rotary wing performance is tested, by upper rotor lengthwise position adjuster bar 403 with lower rotor lengthwise position adjuster bar 404 to the adjustment of two single rotor system 501 spacing, carry out the coaxial double-rotary wing performance test of different rotor spacing.
The test of 5, coaxial double-rotary wing+wing combined type layout performance;
As shown in Figure 10, on the basis that coaxial double-rotary wing is test bed, install auxiliary large wing 502 additional, form coaxial double-rotary wing+wing combined type layout test bed.Thus, on the basis of coaxial double-rotary wing performance test, change auxiliary large wing 502 relative to the upper and lower of two single rotor systems 501 and front and back position by auxiliary large wing governor motion 506, carry out auxiliary large wing 502 and the impact of the performance of coaxial double-rotary wing is tested.
6, coaxial double-rotary wing+wing+thrust screw propeller combined type layout performance test;
As shown in figure 11, on the basis that coaxial double-rotary wing+wing combined type layout is test bed, install afterbody thrust screw propeller 503 additional, form coaxial double-rotary wing+wing+thrust screw propeller combined type layout property test platform, tie tail thrust screw propeller 503 lengthwise position adjuster bar 405 changes afterbody thrust screw propeller 503 and regulates relative to the upper and lower of two single rotor systems 501 and front and back position, on the basis of coaxial double-rotary wing+wing combined type layout performance test, carry out the coaxial double-rotary wing+wing this combined type layout overall performance impact test of different afterbody thrust screw propeller 503 position on combined type layout.
And when carrying out above-mentioned various layout and installing, by governor motion 4, with the parts in used test rotor system, incoherent rod member can be installed and remove weight reduction; As: when carrying out the test of single rotary wing performance, the upper cross bar in upper rotor adjuster bar, adjusting frame and tail can be pushed away screw propeller lengthwise position adjuster bar 405, tail pushes away propeller shaft and remove to position adjustments bar 406.
The testing table of above-mentioned often kind of layout type all can complete separately hovering test and fly test before simulating, and when carrying out hovering test, not being worked by spiral arm drive motor 303 power-off, making the rotation condition of spiral arm beam 201 in surface level dead.And spiral arm drive motor 303 is energized work when flying test before doing, rotates with constant angular velocity according to testing requirements, the rotation condition of spiral arm beam 201 in surface level is removed, thus single rotor system 501 is in constant incoming flow environment all the time.Can carry out thus external force drive with without outer power-actuated before fly simulated experiment.Meanwhile, when flying simulated experiment before carrying out, also retrain by spacer pin in the rotation of spiral arm beam 201 in perpendicular, thus may carry out complete freely and semi-free before fly simulation test.Semi-free is the motion retrained in rotary course by rotor system 5 on lift direction, and is freely full the rippling that rotary motion in the existing surface level of rotor system 5 has on lift direction.When various layout is tested, the moment of torsion and the pulling force that pass through installed high precision pull/moment of torsion integrative sensor 504 pairs of rotors are measured, measured by the rotating speed of speed probe to rotor, measured by the thrust of pressure transducer 505 pairs of afterbody thrust screw propellers 503; The measurement data signals of three sensors arrives ground data processing end by each signal data transmission line and carries out analog to digital conversion, and multiple amplifies, Noise reducing of data, the process such as Data Integration, finally obtains the measured value needed.
Claims (8)
1. the arm-type rotor model.test system of multifunctional rotary, is characterized in that: comprise testing table bearing, cantilever motion mechanism, spiral arm rotary drive mechanism, governor motion;
Described testing table bearing is made up of the main stay pipe that base and base are vertically installed; Cantilever motion mechanism has spiral arm beam, and spiral arm beam is arranged on main supporting steel pipe top, makes spiral arm beam have two degree of freedom, and one degree of freedom is the rotary motion of spiral arm beam in surface level; Another degree of freedom is the small magnitude flapping action of spiral arm beam in perpendicular; The rotary motion of above-mentioned spiral arm beam in surface level is driven by spiral arm rotary drive mechanism and realizes;
Described governor motion is arranged on spiral arm beam left part, and entirety is framed structure, and the top of framework and bottom have symmetrical single rotor installation position, and the upper-lower position of single rotor installation position is adjustable, is used for installing single rotor system; There is on rear side of framework tail and push away screw propeller installation position, and tail to push away screw propeller installation position front and back position adjustable, be used for that tail is installed and push away screw propeller.
2. the arm-type rotor model.test system of multifunctional rotary as claimed in claim 1, is characterized in that: also have horizontal hinge cover, horizontal hinge, horizontal hinged-support and turning axle in cantilever motion mechanism; Realize two degree of freedom of spiral arm beam; Wherein, horizontal hinge cover is socketed on spiral arm beam, is connected by bearing between horizontal hinge with horizontal hinged-support; Horizontal hinge cover is fixedly mounted on the turning axle top vertically arranged, and turning axle bottom connects rotary drive mechanism.
3. the arm-type rotor model.test system of multifunctional rotary as claimed in claim 1, is characterized in that: cantilever motion mechanism also has positioning component, is used for the small magnitude flapping action of constraint spiral arm beam in vertical plane.
4. the arm-type rotor model.test system of multifunctional rotary as claimed in claim 3, is characterized in that: positioning component comprises location-plate, locating sleeve and register pin; Location-plate is arranged at spiral arm beam both sides, and locating sleeve is fixedly sleeved on spiral arm beam, between the positioning end being positioned at two location-plates; On locating sleeve both sides and two location-plate stiff ends, correspondence position has pilot hole, is fixed, realize the constraint of the small magnitude flapping action of spiral arm beam in vertical plane by register pin through after homonymy location-plate and the pilot hole on locating sleeve.
5. the arm-type rotor model.test system of multifunctional rotary as claimed in claim 1, is characterized in that: governor motion comprises governor motion erecting frame, rotor spacing regulating sleeve, upper rotor lengthwise position adjuster bar, lower rotor lengthwise position adjuster bar, tail push away screw propeller lengthwise position adjuster bar, tail push away propeller shaft to position adjustments bar, tail pushes away screw propeller lengthwise position regulating sleeve and tail pushes away propeller shaft to position adjustments cover;
Wherein, tail pushes away propeller shaft and is arranged on spiral arm beam end to the stiff end that position adjustments is overlapped; Tail pushes away propeller shaft and puts to position adjustments and be designed with tail and push away propeller shaft to position adjustments hole, and governor motion mounting hole; Governor motion erecting frame is the U-shaped structural framing be made up of two erecting frame cross bars and an erecting frame vertical pole; After erecting frame vertical pole pushes away through tail the governor motion mounting hole that propeller shaft puts to position adjustments, fix by holding out against screw, fixed position is positioned in the middle part of erecting frame vertical pole, and makes erecting frame vertical pole perpendicular to spiral arm beam, and vertically arranges; Two rotor spacing regulating sleeves are fixedly mounted on the end of two erecting frame cross bars respectively; Two rotor spacing regulating sleeves are designed with rotor position adjustments hole; Upper rotor lengthwise position adjuster bar, lower rotor lengthwise position adjuster bar are each passed through the rotor position adjustments hole on two rotor spacing regulating sleeves, fixed by rotor set screw, make rotor adjuster bar and lower rotor adjuster bar vertical with two erecting frame cross bars respectively, and vertically arrange; Upper rotor adjuster bar and lower rotor adjuster bar opposite side are used for installing a set of single rotor system respectively; After unclamping rotor set screw, rotor adjuster bar and lower rotor adjuster bar can be made in fact in lengthwise movement, and then realize the adjustment of upper and lower two cover rotor system spacing; It is the L-type structure be made up of adjuster bar A and mounting rod A to position adjustments bar that tail pushes away propeller shaft, after adjuster bar A pushes away through tail the governor motion mounting hole that propeller shaft puts to position adjustments, push away propeller shaft by tail to fix to set screw, make adjuster bar A and governor motion erecting frame place plane orthogonal, and mounting rod A is parallel with erecting frame cross bar.Described mounting rod A end winding support is installed tail and is pushed away screw propeller lengthwise position regulating sleeve; Tail pushes away and screw propeller lengthwise position regulating sleeve is designed with tail pushes away screw propeller lengthwise position adjustment hole; It is the L-type structure be made up of adjuster bar B and mounting rod B that tail pushes away screw propeller lengthwise position adjuster bar, after adjuster bar B pushes away screw propeller lengthwise position adjustment hole through tail, push away the longitudinal set screw of screw propeller by tail to fix, make adjuster bar B vertical with adjuster bar A, mounting rod B and adjuster bar A be arranged in parallel; Mounting rod B end, towards governor motion erecting frame place plane, is used for installing tail and pushes away screw propeller.
6. the arm-type rotor model.test system of multifunctional rotary as claimed in claim 1, is characterized in that: single rotor system is arranged on the single rotor installation position on lower rotor lengthwise position adjuster bar, lower rotor lengthwise position adjuster bar by high precision pull/moment of torsion integrative sensor 11; Single rotor is also provided with speed probe; Tail pushes away screw propeller and is arranged on tail by pressure transducer and pushes away on screw propeller installation position.
7. the arm-type rotor model.test system of multifunctional rotary as claimed in claim 1, is characterized in that: single rotor installation position is also used for install auxiliary large wing governor motion, realizes the installation of auxiliary large wing; Auxiliary large wing governor motion entirety is framed structure, is arranged on single rotor installation position; The flange that in auxiliary large wing, the wing of both sides is designed by end is connected with framework two sides respectively; And perforate flange is designed with along wing fore-and-aft direction, be also designed with perforate along the vertical direction at frame facet, thus by screw through after flange and the perforate on framework, tighten with nut screw connection, realize fixing between wing and installation frame; And the relatively single upper-lower position of rotor system of auxiliary large wing, the adjustment of front and back position can be realized, and change the angle of attack of auxiliary large wing.
8. the arm-type rotor model.test system of multifunctional rotary as claimed in claim 1, is characterized in that: for the performance of single rotary wing performance, single rotor+wing combined type layout performance, single rotor+wing+thrust screw propeller combined type layout, coaxial double-rotary wing performance, the test of coaxial double-rotary wing+wing combined type layout performance, coaxial double-rotary wing+wing+thrust screw propeller combined type layout performance test;
A, single rotary wing performance are tested;
Apply a set of single rotor system, be arranged on single rotor installation position of below;
B, single rotor+wing combined type layout performance test;
On the basis of a, single rotor installation position of below installs auxiliary large wing additional;
C, single rotor+wing+thrust screw propeller combined type layout performance test;
On the basis of b, install afterbody thrust screw propeller additional;
D, coaxial double-rotary wing performance test;
On the basis of a, single rotor system of same size is installed in single rotor installation position up;
The test of e, coaxial double-rotary wing+wing combined type layout performance;
On the basis of d, single rotor installation position of below is installed auxiliary large wing;
F, coaxial double-rotary wing+wing+thrust screw propeller combined type layout performance test;
On the basis of e, install afterbody thrust screw propeller additional.
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| CN107063622A (en) * | 2017-03-30 | 2017-08-18 | 福州大学 | Coaxial tilting type rotor aeroperformance test platform and its method |
| CN107063622B (en) * | 2017-03-30 | 2023-06-16 | 福州大学 | Coaxial tilting rotor wing pneumatic performance test platform and method thereof |
| CN107651213A (en) * | 2017-04-26 | 2018-02-02 | 天津中德应用技术大学 | Dynamic equilibrium machinery arm |
| CN107588922A (en) * | 2017-08-31 | 2018-01-16 | 北京电子工程总体研究所 | The analogue measurement device of the direction aerodynamic force of unmanned plane three and three direction aerodynamic moments |
| CN107719696A (en) * | 2017-09-12 | 2018-02-23 | 北京航空航天大学 | A kind of dynamic characteristics synchronous testing device of axially compact type aircraft propeller |
| CN108639379A (en) * | 2018-06-29 | 2018-10-12 | 长沙市云智航科技有限公司 | A kind of aircraft rotor component test device |
| CN110006591A (en) * | 2019-04-23 | 2019-07-12 | 河南三和航空工业有限公司 | Large-scale rotor dynamic balancing commissioning device |
| CN110470454A (en) * | 2019-09-16 | 2019-11-19 | 中国空气动力研究与发展中心低速空气动力研究所 | A kind of double propeller hub synchronization backing propeller test devices |
| CN110562483A (en) * | 2019-09-24 | 2019-12-13 | 哈尔滨工业大学 | lift-drag characteristic measuring device for vertical Mars aircraft coaxial rotor system |
| CN110562484A (en) * | 2019-09-24 | 2019-12-13 | 哈尔滨工业大学 | Hovering characteristic testing device for testing single-shaft rotor system of Mars aircraft |
| CN110562483B (en) * | 2019-09-24 | 2022-07-15 | 哈尔滨工业大学 | Lift-drag characteristic measuring device for vertical Mars aircraft coaxial rotor system |
| CN110901951A (en) * | 2019-11-15 | 2020-03-24 | 哈尔滨飞机工业集团有限责任公司 | Multifunctional tail rotor test system |
| CN113008531A (en) * | 2019-12-20 | 2021-06-22 | 海鹰航空通用装备有限责任公司 | Measuring device for propeller tension and torque |
| CN113008532B (en) * | 2019-12-20 | 2022-07-15 | 海鹰航空通用装备有限责任公司 | Method for measuring tension and torque of propeller |
| CN113008532A (en) * | 2019-12-20 | 2021-06-22 | 海鹰航空通用装备有限责任公司 | Method for measuring tension and torque of propeller |
| CN113008531B (en) * | 2019-12-20 | 2022-07-15 | 海鹰航空通用装备有限责任公司 | Measuring device for propeller tension and torque |
| CN111999031A (en) * | 2020-09-11 | 2020-11-27 | 中国航空工业集团公司哈尔滨空气动力研究所 | Sudden change ground effect ground simulation device based on rotary test bed |
| CN114415710A (en) * | 2021-12-02 | 2022-04-29 | 北京电子工程总体研究所 | Tilting path optimization method of tilting rotor aircraft and readable storage medium |
| WO2024099122A1 (en) * | 2022-11-10 | 2024-05-16 | 浙大城市学院 | Composite propeller blade tiltrotor powertrain test device and test method |
| CN116558766A (en) * | 2023-07-10 | 2023-08-08 | 中国空气动力研究与发展中心低速空气动力研究所 | Ground simulation method for tail rotor aerodynamic characteristic test in aerodynamic interference environment |
| CN116558766B (en) * | 2023-07-10 | 2023-09-01 | 中国空气动力研究与发展中心低速空气动力研究所 | Ground simulation method for tail rotor aerodynamic characteristic test in aerodynamic interference environment |
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