CN102494867B - Force measuring apparatus of jet vane carried engine hot firing test - Google Patents
Force measuring apparatus of jet vane carried engine hot firing test Download PDFInfo
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- CN102494867B CN102494867B CN201110393624.0A CN201110393624A CN102494867B CN 102494867 B CN102494867 B CN 102494867B CN 201110393624 A CN201110393624 A CN 201110393624A CN 102494867 B CN102494867 B CN 102494867B
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Abstract
The invention relates to a force measuring apparatus of a jet vane carried engine hot firing test. The force measuring apparatus comprises a measuring assembly, a driving mechanism, a transmission mechanism, a heat proof assembly, an installation pedestal, and a connection assembly. The measuring assembly is used for measuring an air load exerting force on a jet vane and a defection angle of the jet vane as well as comprises a strain gauge balance and an angular transducer and the like. The driving mechanism, which is a driving apparatus for deflection of the jet vane, is fixed on the installation pedestal and is composed of a motor and a reducer. The transmission mechanism mainly includes a gear wheel and a pinion, wherein the pinion is connected with an output shaft of the reducer and the gear wheel is fixed with an inner bearing sleeve of a bearing pedestal. The heat proof assembly is used for protecting the force measuring apparatus to be in an environment with a temperature for normal working during the test process. The connection assembly consists of a coupling band, an angular output shaft and a shaft coupling. And the installation pedestal is used for fixing all parts including the measuring assembly, the driving mechanism, and the heat proof assembly and the like as well as is connected with an external fixed mechanism. According to the force measuring apparatus provided in the invention, a jet vane can be driven to make deflection rapidly and accurately in an engine tail jet flow; and real-time measurement is carried out on an air load exerted on the jet vane and an actual deflection angle; therefore, the force measuring apparatus has good universality and can be used repeatedly.
Description
Technical field
The present invention relates to a kind of device for measuring force of gas vane carried engine hot commissioning, belong to aerodynamics test field.
Background technology
Along with the development of Thrust Vectoring Technology, the topworks that jet vane is controlled as guided missile thrust vectoring is used more and more.Because jet cutting car flow has the singularity such as high temperature, deep-etching and height wash away, be nonsteady jet, be true stressing conditions when theory is calculated or wind tunnel test is all difficult to obtain jet vane work.Gas vane carried engine hot commissioning dynamometer check can be carried out jet vane dynamometry in actual ablation situation, measurement result has reflected the stressing conditions in jet vane practical work process, is the stressed final data of jet vane and the ultimate criterion of passing judgment on jet vane Design of Aerodynamic Configuration result.
Device for measuring force is the basic equipment of gas vane carried engine hot commissioning dynamometer check, and its function and measuring accuracy etc. have directly determined the accuracy of dynamometer check.Because jet vane application is before less, the lift-launch engine thermal test run dynamometer check that it is carried out is carried out seldom, conventionally for a set of simple and easy Special testing device of a certain specific model development, realize the dynamometry of jet vane under typicalness, its structure is conventionally simpler, be difficult to realize sophisticated testing state and accurately simulation, measuring accuracy is not high, and versatility is poor.Along with a large amount of employings of jet vane, develop and a kind ofly can accurately realize jet vane control law, and it is necessary accurately to measure jet vane device for measuring force with stronger versatility and reusability of suffered aerodynamic loading in engines tail jet flow.
Summary of the invention
Technology of the present invention is dealt with problems and is: overcome the deficiencies in the prior art, provide a kind of and can drive jet vane quick and precisely deflection in engines tail jet flow, and measure in real time the actual deflection angle of jet vane and the aerodynamic loading that bears there is stronger versatility, reusable device for measuring force.
Technical solution of the present invention is: a kind of device for measuring force of gas vane carried engine hot commissioning, is characterized in that: comprise and measure assembly, driving mechanism, gear train, solar heat protection assembly, mounting base and coupling assembling; Described measurement assembly comprises strain balance, angular transducer, and strain balance is for measuring the aerodynamic loading being applied on jet vane, and angular transducer is for measuring the deflection angle of jet vane; Described driving mechanism is the drive unit of jet vane deflection, comprises motor and speed reducer, and motor and speed reducer is fixed on T-shaped mount pad after connecting; Described gear train mainly comprises gear wheel and pinion wheel, and pinion wheel is connected with speed reducer output shaft, and the internal bearing sleeve of gear wheel and bearing base is fixed; Solar heat protection component protection device for measuring force is in process of the test in the environment temperature in normal work; Described coupling assembling comprises coupling band, angle output shaft, shaft coupling, measured jet vane is fixedly connected with coupling band, coupling band and strain balance cone match, and strain with bolt, angle output shaft is fixedly connected with bearing base, and angle output shaft is connected with angular transducer by shaft coupling; Described mounting base comprises bearing base and T-shaped mount pad, and bearing base is used for fixedly strain balance and angular transducer, and T-shaped mount pad is connected with external stability mechanism.
Described measurement assembly comprises strain balance, angular transducer, described driving mechanism comprises motor, reductor, described gear train comprises pinion wheel, gear wheel, described solar heat protection assembly comprises solar heat protection backplate, flow-stopping plate, baffle ring, heat insulation tapered sleeve, heat shield, described mounting base comprises bearing base, angular transducer mount pad, T-shaped mount pad, bearing base comprises bearing, outer bearing carrier, inner pedestal, back-up ring, and described coupling assembling comprises coupling band, angle output shaft, shaft coupling, jet vane is fixed on coupling band, coupling band and strain balance cone match, and strain with bolt, between coupling band and the strain balance conical surface, be lined with heat insulation tapered sleeve, strain balance is placed in the inner chamber of inner pedestal, by cone match, be connected with inner pedestal, and strain with nut, inner pedestal is connected with outer bearing carrier by bearing, and with back-up ring solid bearing and adjusting elasticity, inner pedestal upper end and gear wheel are fixed, lower end and angle output shaft are fixed, and keep coaxial, outer bearing carrier is fixed on T-shaped mount pad with flange, angular transducer is fixed on angular transducer mount pad, and coaxial with outer bearing carrier, angular transducer mount pad is fixed on outer bearing carrier, between angle output shaft and angular transducer, with shaft coupling, be connected, motor and reductor connect to form driving mechanism, and be fixed on T-shaped mount pad, speed reducer output shaft and pinion wheel are fixed, pinion wheel and gear wheel engagement, baffle ring is installed on coupling band, and cover the outstanding upper edge of inner pedestal, heat shield covers all devices, and be fixed on T-shaped mount pad, flow-stopping plate is installed between the spout and heat shield of engine, and be fixed on T-shaped mount pad, solar heat protection backplate is fixed on flow-stopping plate.
Described strain balance is six post girder constructions, and six post beam front ends are inner cone, have threaded hole, inner cone keyway on inner cone, and six post beam rear ends are tail cone, are processed with tail cone keyway, cable hole and external thread on tail cone.
Described angular transducer is comprised of single-turn potentiometer and two identical precision resistances of resistance, and one end of two precision resistances is connected with the power positive cathode of single-turn potentiometer respectively, and the other end of two precision resistances connects together and draws new terminals; The signal end of single-turn potentiometer be signal just, the terminals that two precision resistances are drawn are that signal is negative, add positive source, the power cathode of single-turn potentiometer, jointly form the bridge circuit of a four-wire system, as angular transducer.
The present invention's advantage is compared with prior art:
1, device for measuring force of the present invention can drive that jet vane is realized fast in engines tail jet flow, accurately deflection, realizes the accurate simulation of trystate to jet vane duty.
2, true deflection angle and the corresponding aerodynamic loading of device for measuring force energy Measurement accuracy jet vane of the present invention any time, angle measurement error≤0.05 °, strain balance measuring accuracy is better than 0.3%.
3, device for measuring force of the present invention has reliable thermal protection, and major equipment can be repeatedly used.
4, device for measuring force of the present invention can adopt multi-form fixed mechanism to realize the installation location with respect to engine, and the jet vane that can be applied to various sizes engine carries heat run dynamometer check, has stronger versatility.
By meeting above-mentioned requirements, device for measuring force can meet more polytypic test, and each test can be obtained more more accurate test figures, has improved test accuracy, has reduced experimentation cost.
Accompanying drawing explanation
Fig. 1 is device for measuring force structural representation;
Fig. 2 is the front elevation of Fig. 1;
Fig. 3 is the right view of Fig. 1;
Fig. 4 is the A-A cut-open view of Fig. 1;
Fig. 5 is the B-B cut-open view of Fig. 1;
Fig. 6 is the C-C cut-open view of Fig. 1;
Fig. 7 is the front elevation of T-shaped mount pad;
Fig. 8 is the left view of Fig. 7;
Fig. 9 is that the Q of Fig. 7 is to view;
Figure 10 is gear set structure and coordinates schematic diagram;
Figure 11 is solar heat protection backplate example structure schematic diagram;
Figure 12 is the rear view of Figure 11;
Figure 13 is the vertical view of Figure 11;
Figure 14 is bearing base structural representation;
Figure 15 is the upward view of Figure 14;
Figure 16 is internal bearing sleeve structural representation;
Figure 17 is Figure 16 vertical view;
Figure 18 is Figure 16 upward view;
Figure 19 is angle output shaft structural representation;
Figure 20 is the A-A cut-open view of Figure 19;
Figure 21 is Figure 19 vertical view;
Figure 22 is angular transducer mount pad structural representation;
Figure 23 is Figure 22 vertical view;
Figure 24 is strain balance structural representation;
Figure 25 is the A-A cut-open view of Figure 13;
Figure 26 is coupling band structural drawing;
Figure 27 is that angular transducer forms schematic diagram.
Figure 28 is a kind of external stability structural scheme of mechanism.
Figure 29 is that the P of Figure 28 is to view.
In figure:
1, engine, 4, jet vane; 21, position adjustments ring, 22, mounting flange, 23, position adjustments nut, 24, support bar, 25, end plate is installed, 26, support key; 31, motor, 32, reductor, 33, T-shaped mount pad, 34, pinion wheel, 35, gear wheel, 36, solar heat protection backplate, 37, coupling band, 38, flow-stopping plate, 39, baffle ring, 310, heat insulation tapered sleeve, 311, bearing, 312, strain balance, 313, outer bearing carrier, 314, inner pedestal, 315, back-up ring, 316, angle output shaft, 317, angular transducer mount pad, 318, shaft coupling, 319, angular transducer, 320, heat shield; 331, heat shield fixing screw hole, 332, T-shaped mount pad fixing screw hole, 333, keyway, 334, flow-stopping plate fixing screw hole, 335, reductor fixing screw hole, 336, reductor mounting flange face, 337, bearing base mounting flange face, 338, bearing base fixing screw hole; 3141, first insert keyway, the 3142, first screw hole, 3143, taper hole, 3144, second inserts keyway, the 3145, second screw hole; 3121, threaded hole, 3122, inner cone keyway, 3123, inner cone, 3124, six post beams, 3125, tail cone keyway, 3126, tail cone, 3127, cable hole, 3128, external thread; 371, jet vane fixed bolt pin-and-hole, 372, jet vane rudderpost mating surface, 373, balance coordinates the conical surface, 374, balance fit keyway; 3191, single-turn potentiometer, 3192, precision resistance.
Embodiment
The present invention relates to a kind of device for measuring force of gas vane carried engine hot commissioning, device for measuring force can directly be installed on engines tail skirt end frame by external stability mechanism, also can be installed on the independent fixed mechanism that is fixed on ground, and by the relative position between adjusting fixed mechanism and the test bay of stationary engine, realize the relative positioning of jet vane and engine tail nozzle; A set of device for measuring force can drive the deflection of a slice jet vane, and measures its true deflection angle and corresponding aerodynamic loading.During test, the driving mechanism being comprised of motor and speed reducer in device for measuring force drives quick in jet cutting car flow, the accurate deflection of jet vane, and (is always hindered tolerance and be less than 0.01% by high precision current potential device (potentiometer independent linearity tolerance is ± 0.1%) and high-accuracy resistance.) the true deflection angle of the real-time Measurement accuracy jet vane of angular transducer that forms; Under the multiple-protections such as solar heat protection backplate, flow-stopping plate, heat shield, baffle ring and heat insulation tapered sleeve, can not be heated under engine run environment strain impact of strain balance, Measurement accuracy jet vane suffered aerodynamic load in jet cutting car flow, other major equipment also can normally be worked in engine run process, remain intact, can reuse.The present invention can drive quick in jet cutting car flow, the accurate deflection of jet vane, and real-time Measurement accuracy jet vane actual deflection angle and suffered aerodynamic loading, and reusability is good, highly versatile.For size of engine specifications vary in a big way, by changing the external stability mechanism of different size, device for measuring force still can be used.When practical application, because jet vane mostly is four, so device for measuring force often adopts quadruplet to use.
The general design idea of device for measuring force and framed structure comprise measures assembly, driving mechanism, gear train, solar heat protection assembly, mounting base and coupling assembling; Measure assembly and comprise strain balance and angular transducer, strain balance is for measuring the aerodynamic loading being applied on jet vane, and angular transducer is fixed on angular transducer mount pad, and angular transducer is for measuring the deflection angle of jet vane; Driving mechanism is the drive unit of jet vane deflection, comprises motor and speed reducer, and motor and speed reducer is fixed on T-shaped mount pad after connecting; Gear train mainly comprises gear wheel and pinion wheel, and pinion wheel is connected with speed reducer output shaft, and the internal bearing sleeve of gear wheel and bearing base is fixed; Solar heat protection component protection device for measuring force is in process of the test in the environment temperature in normal work; Coupling assembling comprises coupling band, angle output shaft, shaft coupling, measured jet vane is fixedly connected with coupling band, coupling band and strain balance cone match, and strain with bolt, angle output shaft is fixedly connected with bearing base, and angle output shaft is connected with angular transducer by shaft coupling; Mounting base comprises bearing base, angular transducer mount pad and T-shaped mount pad, bearing base is used for fixedly strain balance, angular transducer mount pad is for fixed angle sensor, driving mechanism, gear train, solar heat protection assembly and bearing base etc. are all fixed on T-shaped mount pad, and T-shaped mount pad is fixedly connected with external stability mechanism.
Below in conjunction with accompanying drawing, the present invention is elaborated:
As shown in Fig. 1-Figure 23, device for measuring force 3 comprises motor 31, reductor 32, T-shaped mount pad 33, pinion wheel 34, gear wheel 35, solar heat protection backplate 36, coupling band 37, flow-stopping plate 38, baffle ring 39, heat insulation tapered sleeve 310, bearing 311, strain balance 312, outer bearing carrier 313, inner pedestal 314, back-up ring 315, angle output shaft 316, angular transducer mount pad 317, shaft coupling 318, angular transducer 319, heat shield 320.Jet vane 4 is fixed on coupling band 37, coupling band 37 and strain balance 312 use cone match, and with bolt tension, between coupling band 37 and strain balance 312 conical surfaces, be lined with heat insulation tapered sleeve 310, in order to the heat of blocking on jet vane 4, along coupling band 37, to strain balance 312, transmit.Strain balance 312 is placed in the inner chamber of inner pedestal 314, is connected, and strains with nut by cone match with inner pedestal 314.Inner pedestal 314 is connected with outer bearing carrier 313 by bearing 311, and with back-up ring 315 solid bearing 311 and adjusting elasticities, inner pedestal 314 upper ends are fixed with gear wheel 35, and lower end and angle output shaft 316 are fixed, and maintenance coaxially.Outer bearing carrier 313 use form of flanges are fixed on T-shaped mount pad 33, and for reducing physical dimension, before and after flange face, both sides are cut off.Angular transducer mount pad 317 is fixed on outer bearing carrier 313, and angular transducer 319 is fixed on angular transducer mount pad 317, and coaxial with outer bearing carrier 313, between angle output shaft 316 and angular transducer 319, with shaft coupling 318, is connected.Motor 31 connects to form drive unit with reductor 32, and be fixed on T-shaped mount pad 33, reductor 32 output shafts and pinion wheel 34 are fixing, pinion wheel 34 and gear wheel 35 engagements, for reducing physical dimension, alleviate construction weight, gear wheel is revised, remove the part that does not need engagement, only leave the part that needs engagement in jet vane range of deflection angles.Baffle ring 39 is installed on coupling band 37, and covers the outstanding upper edge of inner pedestal 314, the gap suitable with inner pedestal 314 maintenances.Heat shield 320 covers all devices, and is fixed on T-shaped mount pad 33.Flow-stopping plate 38 is installed between the spout and heat shield 320 of engine 1, and is fixed on T-shaped mount pad 33.Solar heat protection backplate 36 is fixed on flow-stopping plate 38.The output of motor is slowed down by reductor and is amplified moment of torsion, the gear set consisting of pinion wheel and gear wheel again passes to inner pedestal by motion and moment of torsion, the strain balance, the coupling band that drive inner pedestal and be fixed on inner pedestal together rotate, and then drive jet vane to swing in jet cutting car flow.Simultaneously, angular transducer is responded to the actual rotation angle of jet vane, coupling band, strain balance and inner pedestal integral body in real time by shaft coupling, angle output shaft, the aerodynamic loading that jet vane bears passes to strain balance by coupling band, and is measured by strain balance real time record.Baffle ring 39 is installed on coupling band 37, and covers the outstanding upper edge of inner pedestal 314, and the gap suitable with inner pedestal 314 maintenances.Heat shield 320 covers all devices, and is fixed on T-shaped mount pad 33.Solar heat protection backplate 36, for stopping that engine gas jet flow is to directly the washing away and ablation of jet vane rudderpost, prevents that in test, rudderpost is blown and wash away the impact that aerodynamic force is measured in advance.Flow-stopping plate 38 is for stopping because of deflection, reflecting gas that jet vane causes in jet cutting car flow deflection, and the ablation to testing apparatus such as engine flashback, guarantees the intact of main testing apparatus and can reuse.Heat shield 320, for stopping jet cutting car flow heat radiation, makes heat shield 320 inside temperature in whole process of the test be no more than equipment normal range of operation.Baffle ring 39 is for stopping along the rudderpost hot-fluid of gap going down around, and between air, form bending channel in placing the inner pedestal inner chamber air of strain balance and heat shield, further stop heat to strain balance transmission, guarantee in the course of work that strain balance is under a substantially invariable temperature environment, prevent that strain balance from affecting measuring accuracy because of thermal strain.
Motor 31 is AC servo motor, utilize that its rotating speed is fast, positioning precision is high and the advantage such as overload capacity is strong, make device for measuring force can drive jet vane within the of short duration engine thermal test run time fast, accurately deflection, and the impact of aerodynamic loading can bear engine ignition time and in the quick deflection of jet vane; Described reductor 32 is planet-gear speed reducer, utilizes the feature that its reduction gear ratio is large, precision is high and volume is little, makes device for measuring force can control jet vane accurately deflection under high pulling torque.Heat insulation tapered sleeve 310 is formed by the boron phenolic fiberglass reinforced plastics materials processing with heat insulating function, in order to blocking-up, by the heat on the jet vane of jet flow ablation, along coupling band, to strain balance, is transmitted.Bearing 311 is taper roll bearing, and load-bearing capacity is large, can bear engine ignition huge shock load of moment.Solar heat protection backplate 36 can select the compound substance of resistance to ablation to make, and adopts the true solar heat protection backplate using on guided missile, to examine the resistance to ablation ability of solar heat protection backplate and the protection effect to rudderpost more.Between solar heat protection backplate and rudderpost, process appropriate gap, guarantee not because jet vane rudderpost contacts the measurement that affects jet vane aerodynamic loading with backplate, prevent that excesssive gap from causing gas-flow along gap going down, to increase the burden of flow-stopping plate, heat shield and baffle ring etc. simultaneously.Flow-stopping plate 38 can be made by steel plate, be arranged between engine jet pipe and heat shield, be fixed on T-shaped mount pad, become L-type, block top panel and the front panel of heat shield simultaneously, to stop because of the jet vane deflection that deflection causes in jet cutting car flow or reflecting gas, and the ablation of engine flashback to testing apparatus, guarantee the intact of main testing apparatus and can reuse.Perforate on flow-stopping plate, guarantees to keep suitable gap between flow-stopping plate and rudderpost, coupling band, prevents the measurement of Contact Effect aerodynamic force.The optional use of heat shield 320 has the glass epoxy riveted joint of heat insulating function, becomes frame type, be fixed on T-shaped mount pad, and perforate on plate in the above, and between coupling band, keep appropriate clearance, prevent the measurement of Contact Effect aerodynamic force.
As shown in Fig. 7,8,9,33 one-tenth " T " fonts of T-shaped mount pad, be processed with T-shaped mount pad fixing screw hole 332, keyway 333 and lightening grooves above, screw hole 332 can be connected with external agency for T-shaped mount pad, keyway 333 is externally to move the position in mechanism for realizing T-shaped mount pad, to realize device for measuring force with respect to the change of engine radial distance.A kind of schematic diagram of external agency is as shown in Figure 28-29, and external agency comprises position adjustments ring 21, mounting flange 22, position adjustments nut 23, support bar 24, end plate 25 and support key 26 are installed.Mounting flange 22 is for being connected with engine apron end frame, end plate 25 is installed for fixedly device for measuring force is installed, mounting flange 22 is connected with support bar 24 with installing between end plate 25, support bar 24 one end are fixed with end plate 25 use nuts and cylinder are installed, and the other end is followed successively by external thread, cylindrical section and threaded hole.The hole of mounting flange 22 coordinates with cylindrical section, and position adjustments nut 23 coordinates with external thread, and withstands the rear end face of mounting flange 22, and position adjustments ring 21 is enclosed within on cylindrical section, and one end is fixed with the bolt that inserts threaded hole, and the front end face of mounting flange 22 is withstood in one end.By turning position adjustments ring 21 and position adjustments nut 23, can make mounting flange 22 move forward and backward along support bar 24, thereby realize mounting flange 22 and the distance adjustment between end plate 25 is installed.Install on end plate 25 and be processed with long keyway and strip hole radially, in device for measuring force, the support key keyway 333 of T-shaped mount pad 33 coordinates with support key 26, device for measuring force can installed radially slip on end plate 25, with bolt by the fixing device for measuring force 3 of strip hole, strip hole with bolt through T-shaped mount pad fixing screw hole 332 and installation end plate 25, after tighting a bolt, device for measuring force 3 is fixed on and installs on end plate 25, and after loosering a bolt, device for measuring force 3 can installed radially slip on end plate 25.Looser a bolt and can radially regulate the position of device for measuring force.External agency is directly fixed on engine apron end frame, package unit vibrates with engine synchronization in commissioning process, without for preventing that jet vane and engine jet pipe are because vibrating the inconsistent installation site that causes collision to adjust jet vane in commissioning process, measured jet vane can be installed by missile-borne actual position, its flow field of living in is consistent with real work flow field, and measurement result is more true and reliable.By regulating the distance of mounting flange 22 and installation end frame 25, can regulate device for measuring force with respect to the axial location of the nozzle of engine 1, by device for measuring force, along installation end frame 25, move radially, adjustable device for measuring force is with respect to the radial position of the nozzle of engine 1.By above-mentioned adjusting, can locate jet vane 4 with respect to the position of engine 1 nozzle, jet vane 1 can be installed by missile-borne actual position, and its flow field of living in is consistent with real work flow field, guarantees that single unit system can be common to the engine 1 of multiple jet size specification in certain limit simultaneously.For size of engine specifications vary in a big way, can realize by changing the mounting bracket 2 of different size, device for measuring force 3 still can be general.External agency shown in Figure 28-29 is only a kind of preferred performance.In fact, as long as externally the upper processing of fixed mechanism is along engine long keyway and strip hole radially, can realizes the fixing of device for measuring force and move radially.
After reductor coordinates with reductor mounting flange face 336, fixing by reductor fixing screw hole 335 with bolt; After bearing base coordinates with bearing base mounting flange face 337, fixing by bearing base fixing screw hole 338 with bolt; At heat shield 320 two sides processing screw holes, fixing by heat shield fixing screw hole 331 with screw; Flow-stopping plate 38 is fixing by flow-stopping plate fixing screw hole 334.
As shown in Figure 16,17,18, gear wheel 35 use are bolted on the screw hole 3142 of inner pedestal 314, and with the key transmitting torque that inserts keyway 3141; The tail cone of strain balance 312 coordinates with taper hole 3143, realizes rolling location, then strain with nut with the key that inserts keyway 3144; Back-up ring 315 use screws are fixing by screw hole 3145.
As shown in Figure 19,20,21, angle output shaft 316 one end are the flange being connected with inner pedestal 314, and one end is the cylinder being connected with shaft coupling 318; For the signal wire of strain balance 312 is therefrom passed, and alleviate construction weight as far as possible, between flange and cylinder, coupling part is cut into a narrow beam.
As shown in Figure 22,23, angular transducer mount pad 317 one end are the flange being connected with outer bearing carrier 313, one end is the installation end face of angular transducer 319, for the signal wire of strain balance 312 is therefrom passed, and by angular transducer mount pad, do not blocked in jet vane deflection, flange is cut off with the both sides, coupling part that end face is installed.
As shown in Figure 24,25, strain balance 312 is five component strain balances, and five components are respectively: My, Mz, Y, Mx, Q, and not containing the power Z along rudderpost axis.Strain balance is for being symmetrical in the ginseng heart (reference center of balance design, application point for design load) six post beams 3124, the arrangement form of six post beams 3124 is as Figure 17, left and right surface measurement Y with left and right post beam, upper and lower side is measured My, use the upper and lower surface of lower prop beam and measure Q, Mx and Mz are measured in left and right side.Strain balance 312 front ends are inner cone 3123, above have threaded hole 3121, inner cone keyway 3122, coordinate, with the 3122 location rollings of inner cone keyway, with bolt tension cone with the conical surface with coupling band 37.Rear end is tail cone 3126, is processed with tail cone keyway 3125, cable hole 3127 and external thread 3128 on tail cone.Signal wire passes from cable hole 3127, with the conical surface, coordinates with inner pedestal 314, with the 3125 location rollings of tail cone keyway, and strains with nut.By the coordination of each post beam size and the selection of strainometer paste position, can reach each component output coordinating, to guarantee the measuring accuracy of force and moment, meet the Measurement accuracy of the aerodynamic loading that suffered each component value gap of jet vane is larger.Before and after balance, adopt cone to coordinate, with key, realize rolling location, by threaded engagement, realize the tension of cone.Inner cone is connected with coupling band with heat insulation tapered sleeve, and rear cone is connected with inner pedestal.Cone is combined with to be beneficial to and guarantees structure installation accuracy, is not prone to because coordinating the bad impact of balance mechanical creep on balance calibration precision and experimental measurement precision that cause.
As shown in figure 26, the rudderpost of jet vane 4 coordinates with the jet vane rudderpost mating surface 372 of coupling band 37, processes column pin hole on rudderpost, uses through the stud pin of jet vane fixed bolt pin-and-hole 371 and fixes; The inner cone 3123 of strain balance 312 puts heat insulation tapered sleeve 310, then coordinates the conical surface 373 to coordinate with balance, and with key, inserts balance fit keyway 374 and carry out rolling location, then bores with bolt tension.
As shown in figure 27, angular transducer 319 is comprised of high precision single-turn potentiometer 3191 and precision resistance 3192.One end that two resistances differ the high-accuracy resistance 3192 that is less than 0.01% is just connected respectively (at the power supply of potentiometer, being just connected the high-accuracy resistance that resistance is identical with two terminals of power-respectively) with two terminals of power-with the power supply of high precision single-turn potentiometer 3191, the other end connects together, and draws new terminals.Using the signal end of high precision single-turn potentiometer 3191 as signal just, terminals between high-accuracy resistance 3192 are that signal is negative, the power supply that adds high precision single-turn potentiometer 3191 just, power-, form the bridge circuit of a four-wire system, as angular transducer 319.High precision single-turn potentiometer has good adaptive capacity to environment, can bear larger impact, vibrations and temperature variation, and this circuit can improve output signal, and energy angles of display output directly perceived is positive and negative.
In process of the test, the gaseous jet that solar heat protection backplate 36 stops engine 1 is directly washed away and ablation the rudderpost of jet vane 4, prevents that in test, rudderpost is blown and wash away the impact that aerodynamic force is measured in advance.Flow-stopping plate 38 is for stopping jet flow gas deflector, the reflection causing in the jet flow deflection of engine 1 because of jet vane 4, and the ablation to testing apparatus such as the tempering of engine 1, guarantees the intact of main testing apparatus and can reuse.Heat shield 320 stops the jet flow heat radiation of engine 1, makes its inside temperature in whole process of the test be no more than equipment normal range of operation.Baffle ring 39 stops along the rudderpost hot-fluid of gap going down around, and form bending channel placing between the inner pedestal 314 inner chamber air of strain balance 312 and the interior air of heat shield 320, further stop heat to the transmission of strain balance 312, guarantee in the course of work that strain balance 312 is under a substantially invariable temperature environment, prevent that strain balance 312 from affecting measuring accuracy because of thermal strain.
After engine 1 ignition signal sends, AC servo motor 31 starts to rotate, its output is slowed down and is amplified moment of torsion by planet-gear speed reducer 32, the gear set consisting of pinion wheel 34 and gear wheel 35 again passes to inner pedestal 314 by motion and moment of torsion, the strain balance 312, the coupling band 37 that drive inner pedestal 314 to rotate and be fixed on inner pedestal 314 together rotate, and then drive jet vane 4 by appointment rule, to swing rapidly and accurately in the jet flow of engine 1.Simultaneously, angular transducer 318 is responded to the actual rotation angle of jet vane 4, coupling band 37, strain balance 312 and inner pedestal 314 integral body in real time by shaft coupling 318, angle output shaft 316, the aerodynamic loading that jet vane 4 bears passes to strain balance 312 by coupling band 37, and by the real-time Measurement accuracy of strain balance 312.
The content not being described in detail in instructions of the present invention belongs to those skilled in the art's known technology.
Claims (4)
1. a device for measuring force for gas vane carried engine hot commissioning, comprises and measures assembly, driving mechanism, gear train, solar heat protection assembly, mounting base and coupling assembling; It is characterized in that: described measurement assembly comprises strain balance, angular transducer, strain balance is for measuring the aerodynamic loading being applied on jet vane, and angular transducer is for measuring the deflection angle of jet vane; Described driving mechanism is the drive unit of jet vane deflection, comprises motor and speed reducer, and motor and speed reducer is fixed on T-shaped mount pad after connecting; Described gear train mainly comprises gear wheel and pinion wheel, and pinion wheel is connected with speed reducer output shaft, and the internal bearing sleeve of gear wheel and bearing base is fixed; Solar heat protection component protection device for measuring force is in process of the test in the environment temperature in normal work; Described coupling assembling comprises coupling band, angle output shaft, shaft coupling, measured jet vane is fixedly connected with coupling band, coupling band and strain balance cone match, and strain with bolt, angle output shaft is fixedly connected with bearing base, and angle output shaft is connected with angular transducer by shaft coupling; Described mounting base comprises bearing base, angular transducer mount pad and T-shaped mount pad, and bearing base is used for fixedly strain balance and angular transducer, and angular transducer mount pad is for fixed angle sensor, and T-shaped mount pad is connected with external stability mechanism.
2. the device for measuring force of a kind of gas vane carried engine hot commissioning according to claim 1, it is characterized in that: described measurement assembly comprises strain balance (312), angular transducer (319), described driving mechanism comprises motor (31), reductor (32), described gear train comprises pinion wheel (34), gear wheel (35), described solar heat protection assembly comprises solar heat protection backplate (36), flow-stopping plate (38), baffle ring (39), heat insulation tapered sleeve (310), heat shield (320), described mounting base comprises bearing base, angular transducer mount pad (317), T-shaped mount pad (33), bearing base comprises bearing (311), outer bearing carrier (313), inner pedestal (314), back-up ring (315), described coupling assembling comprises coupling band (37), angle output shaft (316), shaft coupling (318), jet vane (4) is fixed on coupling band (37), coupling band (37) and cone match for strain balance (312), and strain with bolt, between coupling band (37) and strain balance (312) conical surface, be lined with heat insulation tapered sleeve (310), strain balance (312) is placed in the inner chamber of inner pedestal (314), by cone match, be connected with inner pedestal (314), and strain with nut, inner pedestal (314) is connected with outer bearing carrier (313) by bearing (311), and with back-up ring (315) solid bearing (311) and adjusting elasticity, inner pedestal (314) upper end and gear wheel (35) are fixing, lower end and angle output shaft (316) are fixing, and keep coaxial, outer bearing carrier (313) is fixed on T-shaped mount pad (33) with flange, angular transducer (319) is fixed on angular transducer mount pad (317), and coaxial with outer bearing carrier (313), angular transducer mount pad (317) is fixed on outer bearing carrier (313), between angle output shaft (316) and angular transducer (319), with shaft coupling (318), be connected, motor (31) connects to form driving mechanism with reductor (32), and be fixed on T-shaped mount pad (33), reductor (32) output shaft and pinion wheel (34) are fixing, pinion wheel (34) and gear wheel (35) engagement, baffle ring (39) is installed on coupling band (37), and cover the outstanding upper edge of inner pedestal (314), heat shield (320) covers all devices, and be fixed on T-shaped mount pad (33), flow-stopping plate (38) is installed between the spout and heat shield (320) of engine (1), and be fixed on T-shaped mount pad (33), solar heat protection backplate (36) is fixed on flow-stopping plate (38).
3. the device for measuring force of a kind of gas vane carried engine hot commissioning according to claim 1, it is characterized in that: described strain balance (312) is six post beam (3124) structures, six post beam front ends are inner cone (3123), on inner cone (3123), have threaded hole (3121), inner cone keyway (3122), six post beam rear ends are tail cone (3126), are processed with tail cone keyway (3125), cable hole (3127) and external thread (3128) on tail cone (3126).
4. the device for measuring force of a kind of gas vane carried engine hot commissioning according to claim 1, it is characterized in that: described angular transducer (319) is comprised of single-turn potentiometer (3191) and two identical precision resistances (3192) of resistance, one end of two precision resistances (3192) is connected with the power positive cathode of single-turn potentiometer (3191) respectively, and the other end of two precision resistances (3192) connects together and draws new terminals; The signal end of single-turn potentiometer (3191) be signal just, the terminals that two precision resistances (3192) are drawn are that signal is negative, add positive source, the power cathode of single-turn potentiometer (3191), the common bridge circuit that forms a four-wire system, as angular transducer (319).
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| CN201110393624.0A CN102494867B (en) | 2011-12-01 | 2011-12-01 | Force measuring apparatus of jet vane carried engine hot firing test |
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| CN201110393624.0A CN102494867B (en) | 2011-12-01 | 2011-12-01 | Force measuring apparatus of jet vane carried engine hot firing test |
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