CN102435410B - Test system of gas vane carried engine hot commissioning - Google Patents
Test system of gas vane carried engine hot commissioning Download PDFInfo
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- CN102435410B CN102435410B CN 201110396105 CN201110396105A CN102435410B CN 102435410 B CN102435410 B CN 102435410B CN 201110396105 CN201110396105 CN 201110396105 CN 201110396105 A CN201110396105 A CN 201110396105A CN 102435410 B CN102435410 B CN 102435410B
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Abstract
The invention relates to a test system of gas vane carried engine hot commissioning. The test system of gas vane carried engine hot commissioning comprises force measurement devices and a mounting bracket, wherein the mounting bracket is connected with a tail skirt end frame of an engine, and the force measurement devices are connected with the mounting bracket; and the number of the force measurement devices is the same as that of gas vanes, and the force measurement devices are used for fixing and driving the gas vanes to quickly and accurately deviate in a tail jet flow of the engine, and measuring the actual deviation angle and corresponding pneumatic load of the gas vanes. The test system provided by the invention can simultaneously drive one or a plurality of gas vanes to quickly and accurately deviate in the jet flow of the engine and measure the pneumatic load and the actual deviation angle of the gas vanes in real time, and has the advantages of accurate simulation, high measurement precision, stronger generality and repeated use.
Description
Technical field
The present invention relates to the pilot system that a kind of jet vane carries the engine thermal test run, belong to aerodynamics test field.
Background technology
Along with the development of Thrust Vectoring Technology, jet vane is used more and more as the topworks of guided missile thrust vectoring control.Because jet cutting car flow has singularity such as high temperature, deep-etching and height wash away, be nonsteady jet, be theoretical calculating or the true stressing conditions of wind tunnel test when all being difficult to obtain jet vane work.Jet vane carries engine thermal test run dynamometer check can carry out the jet vane dynamometry under actual ablation situation, measurement result has reflected the stressing conditions in the jet vane practical work process, is the stressed final data of jet vane and the ultimate criterion of passing judgment on jet vane aerodynamic configuration design result.
Such test is not at present popularized as yet, usually at the simple and easy special-purpose test unit of a certain specific model development one cover, realizes the dynamometry of jet vane under the typicalness.Its structure is simpler usually, is difficult to realize sophisticated testing state and accurately simulation, and measuring accuracy is not high, and versatility is poor.
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 quick in jet cutting car flow, the accurate deflection of one or more pieces jet vanes simultaneously, and measure the suffered aerodynamic loading of jet vane and actual deflection angle in real time, simulation is accurate, measuring accuracy is high, has strong versatility, reusable pilot system.
Technical solution of the present invention is: a kind of jet vane carries the pilot system of engine thermal test run, it is characterized in that: comprise device for measuring force and mounting bracket, mounting bracket is connected with the tail skirt end frame of engine, device for measuring force is connected with mounting bracket, the quantity of device for measuring force is identical with the sheet number of jet vane, be used for the fixing control jet vane that reaches in the deflection of engines tail jet flow, and measure jet vane deflection angle and suffered aerodynamic loading.
Described mounting bracket comprises position adjustments ring, mounting flange, position adjustments nut, support bar, installation end plate and support key; The position in hole is corresponding on mounting hole on the mounting flange and the engines tail skirt end frame, mounting flange is connected with support bar with installing between the end plate, support bar one end inserts the cylindrical hole that end plate is installed, and strain with nut, the other end is followed successively by external thread, cylindrical section and threaded hole, the hole of mounting flange cooperates with cylindrical section, the position adjustments nut cooperates with external thread, and withstand the rear end face of mounting flange, the position adjustments ring set is on cylindrical section, the position adjustments ring one end bolt of inserting threaded hole, the other end withstands the front end face of mounting flange, turn position adjustments ring and position adjustments nut, mounting flange moves forward and backward along support bar, and mounting flange and the distance of installing between the end plate change thereupon; The long keyway and the strip hole that are processed with on the end plate radially are installed, and the support key is put into long keyway, and can radially slide in long keyway, and the support key is used for cooperating with the T type mount pad of device for measuring force, and strip hole is used for device for measuring force is fixed on the installation end plate.
Described device for measuring force comprises motor, reductor, T type mount pad, pinion wheel, gear wheel, solar heat protection backplate, coupling band, flow-stopping plate, baffle ring, heat insulation tapered sleeve, bearing, strain balance, outer bearing carrier, inner pedestal, back-up ring, angle output shaft, angular transducer mount pad, shaft coupling, angular transducer, heat shield; Jet vane is fixed on the coupling band, coupling band and strain balance cone match, and strain with bolt, be lined with heat insulation tapered sleeve between coupling band and the strain balance conical surface, strain balance is placed in the inner chamber of inner pedestal, be connected with inner pedestal with cone match, and strain with nut, inner pedestal is connected with outer bearing carrier by bearing, and with the back-up ring solid bearing and regulate degree of tightness, the inner pedestal upper end is fixed with gear wheel, lower end and angle output shaft are fixed, and keep coaxial, outer bearing carrier is fixed on the T type mount pad with flange, angular transducer is fixed on the angular transducer mount pad, and coaxial with outer bearing carrier, and the angular transducer mount pad is fixed on the outer bearing carrier, be connected with shaft coupling between angle output shaft and the angular transducer, motor and reductor connect to form driving mechanism, and are fixed on the T type mount pad, and speed reducer output shaft and pinion wheel are fixed, pinion wheel and gear wheel engagement, the baffle ring is installed on the coupling band, and covers the outstanding upper edge of inner pedestal, and heat shield covers all devices, and be fixed on the T type mount pad, flow-stopping plate is installed between the spout and heat shield of engine, and is fixed on the T type mount pad, and the solar heat protection backplate is fixed on the 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 the inner cone, and six post beam rear ends are tail cone, are processed with tail cone keyway, cable hole and external thread on the tail cone.
Described angular transducer is made up of single-turn potentiometer and two identical precision resistances of resistance, and an 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, form the bridge circuit of a four-wire system jointly, as angular transducer.
The present invention's advantage compared with prior art is:
1, pilot system of the present invention simulation accurately, the measuring accuracy height, angle measurement error≤0.05 °, the strain balance measuring accuracy is better than 0.3%.
2, quick in the engines tail jet flow, the accurately deflection of every jet vane of energy drive of pilot system of the present invention can the deflection state of true reappearance jet vane on bullet.
3, system's highly versatile, the major equipment of package unit can be repeatedly used.
By satisfying above-mentioned requirements, device can satisfy more polytypic test, and each test can be obtained more more accurate test figures, has significantly reduced experimentation cost.
Description of drawings
Fig. 1 is test system architecture of the present invention and scheme of installation.
Fig. 2 is the rear view of Fig. 1.
Fig. 3 is the mounting bracket structural representation.
Fig. 4 is that the P of Fig. 3 is to view.
Fig. 5 is the device for measuring force structural representation.
Fig. 6 is the front elevation of Fig. 5
Fig. 7 is the right view of Fig. 5
Fig. 8 is the A-A cut-open view of Fig. 5
Fig. 9 is the B-B cut-open view of Fig. 5
Figure 10 is the C-C cut-open view of Fig. 5
Figure 11 is the front elevation of T type mount pad
Figure 12 is the left view of Figure 11
Figure 13 is that the Q of Figure 11 is to view
Figure 14 is the gear set structure and cooperates synoptic diagram
Figure 15 is the bearing base structural representation
Figure 16 is the upward view of Figure 15
Figure 17 is the strain balance structural representation
Figure 18 is the A-A cut-open view of Figure 17
Figure 19 is the coupling band structural drawing
Figure 20 forms synoptic diagram for angular transducer.
Figure 21 is solar heat protection backplate example structure synoptic diagram
Figure 22 is the rear view of Figure 21
Figure 23 is the vertical view of Figure 21
Figure 24 is the internal bearing sleeve structural representation
Figure 25 is Figure 24 vertical view
Figure 26 is Figure 24 upward view
Figure 27 is angle output shaft structural representation
Figure 28 is the A-A cut-open view of Figure 27
Figure 29 is Figure 27 vertical view
Figure 30 is angular transducer mount pad structural representation
Figure 31 is Figure 30 vertical view
Among the figure:
1, engine, 2, mounting bracket, 3, device for measuring force, 4, jet vane; 21, position adjustments ring, 22, mounting flange, 23, the position adjustments nut, 24, support bar, 25, end plate is installed, 26, the support key; 31, motor, 32, reductor, 33, T type mount pad, 34, pinion wheel, 35, gear wheel, 36, the 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, the angle output shaft, 317, the angular transducer mount pad, 318, shaft coupling, 319, angular transducer, 320, heat shield; 331, heat shield fixing screw hole, 332, T type mount pad fixing screw hole, 333, support key keyway, 334, flow-stopping plate fixing screw hole, 335, the reductor fixing screw hole, 336, reductor mounting flange face, 337, bearing base mounting flange face, 338, the bearing base fixing screw hole; 3121, threaded hole, 3122, the inner cone keyway, 3123, inner cone, 3124, six post beams, 3125, the 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 cooperates the conical surface, 374, the balance fit keyway; 3191, single-turn potentiometer, 3192, precision resistance; 3141, first insert keyway, 3142, first screw hole, 3143, taper hole, 3144, second inserts keyway, 3145, second screw hole.
Embodiment
The present invention relates to the pilot system that a kind of jet vane carries the engine thermal test run, comprise mounting bracket, device for measuring force.Mounting bracket is connected with engines tail skirt end frame, be used for fixedly device for measuring force, have and regulate function axial between engine and device for measuring force, radial distance, realize the location of the relative engine jet pipe of jet vane, make jet vane flow field of living in and guided missile basically identical, device for measuring force is applicable to the engine of multiple dimensions in the certain limit.Many covers (often being quadruplet) device for measuring force is installed on the installation end frame of mounting bracket, every cover device for measuring force be used for control a slice jet vane at jet cutting car flow by setting requirement deflection, and measure the actual deflection angle of jet vane in jet cutting car flow and the aerodynamic loading that bears in real time.During test, the driving mechanisms control jet vane of being formed by AC servo motor and planet-gear speed reducer in the device for measuring force in jet cutting car flow by the rule of appointment fast, accurately deflection, and by high precision potentiometer (potentiometer independent linearity tolerance is ± 0.1%) and high-accuracy resistance (resistance always hinders tolerance 0.01%.) angular transducer formed can accurately measure the true deflection angle of jet vane in real time; Under multiple-protections such as solar heat protection backplate, flow-stopping plate, heat shield, baffle ring and heat insulation tapered sleeve, can under the engine run environment, not be heated strain influence of strain balance, accurately measure jet vane suffered aerodynamic load in jet cutting car flow, other major equipment also can be in the engine run process operate as normal, remain intact, can reuse.The present invention not only can control simultaneously the multi-disc jet vane in jet cutting car flow by default rule deflection, and measure in real time accurately 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, can realize that the device for measuring force assembly still can use by the mounting bracket assembly of changing different size.
For pilot system of the present invention, the innovative point of one of them particular importance and difficult point are exactly design and the realization of device for measuring force, and 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 used for measuring the aerodynamic loading that is applied on the jet vane, and angular transducer is fixed on the angular transducer mount pad, and angular transducer is used 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 the T type 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 of operate as normal; Coupling assembling comprises coupling band, angle output shaft, shaft coupling, measured jet vane is fixedlyed connected with coupling band, coupling band and strain balance cone match, and strain with bolt, the angle output shaft is fixedlyed connected with bearing base, and the angle output shaft is connected with angular transducer by shaft coupling; Mounting base comprises bearing base, angular transducer mount pad and T type mount pad, bearing base is used for fixedly strain balance, the angular transducer mount pad is used for the fixed angle sensor, driving mechanism, gear train, solar heat protection assembly and bearing base etc. all are fixed on the T type mount pad, and T type mount pad is fixedlyed connected with external stability mechanism.
Below in conjunction with accompanying drawing the present invention is elaborated:
As Fig. 1, shown in Figure 2, the pilot system that a kind of jet vane carries the engine thermal test run comprises mounting bracket 2, device for measuring force 3, the number of device for measuring force 3 is identical with the sheet number of jet vane, the number of diagram device for measuring force 3 is 4, mounting bracket 2 is connected with the tail skirt end frame of engine 1 by its mounting flange 22, in that being installed, 33 of end plate 25 and T type mount pads cooperate with support key 26, device for measuring force 3 can only be radially slided in that end plate 25 upper edges are installed, again with bolt by install on the end plate 25 strip hole fixedly device for measuring force 3. jet vanes 4 be fixed on the coupling band 37 of device for measuring force 3.
As shown in Figure 3, Figure 4, mounting bracket 2 comprises position adjustments ring 21, mounting flange 22, position adjustments nut 23, support bar 24, end plate 25 and support key 26 is installed.Mounting flange 22 is used for being connected with engine apron end frame, end plate 25 is installed is used for installing and fixing device for measuring force, mounting flange 22 is connected with support bar 24 with installing between the end plate 25, support bar 24 1 ends cooperate fixing with installation end plate 25 usefulness nuts and cylinder, the other end is followed successively by external thread, cylindrical section and threaded hole.The hole of mounting flange 22 cooperates with cylindrical section, and position adjustments nut 23 cooperates with external thread, and withstands the rear end face of mounting flange 22, and position adjustments ring 21 is enclosed within on the cylindrical section, the end bolt of inserting threaded hole, and an end withstands the front end face of mounting flange 22.By turning position adjustments ring 21 and position adjustments nut 23, mounting flange 22 is moved forward and backward along support bar 24, thereby realize the distance adjustment between mounting flange 22 and the installation end plate 25.The long keyway and the strip hole that are processed with on the end plate 25 radially are installed, the support key keyway 333 of T type mount pad 33 cooperates with support key 26 in the device for measuring force 3, support key 26 can only radially slide device for measuring force 3 in installation end plate 25 upper edges, with bolt by the fixing device for measuring force 3 of strip hole, pass the strip hole of T type mount pad fixing screw hole 332 and installation end plate 25 with bolt, the back device for measuring force 3 that tights a bolt is fixed on to be installed on the end plate 25, and the back device for measuring force 3 that loosers a bolt can radially slide in installation end plate 25 upper edges.Looser a bolt and radially to regulate the position of device for measuring force.Use support bar connection flange and end plate is installed, can when guaranteeing the whole erection stiffness of support, alleviate construction weight, alleviate package unit to the burden of engine apron end frame.Mounting bracket directly is fixed on the engine apron end frame, package unit in commissioning process with engine synchronous vibration, need not to preventing that jet vane and engine jet pipe are because vibrating the inconsistent installation site of adjusting jet vane that causes colliding in commissioning process, measured jet vane can be installed by missile-borne actual position, its flow field of living in is consistent with the real work flow field, and measurement result is more true and reliable.
By the mounting flange 22 of adjusting mounting bracket 2 and the distance of installation end frame 25, can regulate device for measuring force 3 with respect to the axial location of the nozzle of engine 1, move radially by the installation end frame 25 of device for measuring force 3 along mounting bracket 2, can regulate device for measuring force 3 with respect to the radial position of the nozzle of engine 1.By above-mentioned adjusting, can accurately locate jet vane 4 with respect to the position of engine 1 nozzle, jet vane 1 can be installed by missile-borne actual position, its flow field of living in is consistent with the real work flow field, guarantees that simultaneously single unit system can be common to the engine 1 of multiple jet size specification in the certain limit.For size of engine specifications vary in a big way, can realize that device for measuring force 3 still can be general by the mounting bracket 2 of changing different size.
As Fig. 5-shown in Figure 31, device for measuring force 3 comprises motor 31, reductor 32, T type 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 the coupling band 37, coupling band 37 is used cone match with strain balance 312, and with the bolt tension, be lined with heat insulation tapered sleeve 310 between coupling band 37 and strain balance 312 conical surfaces, in order to block heat 312 transmission along coupling band 37 to strain balance on the jet vane 4.Strain balance 312 is placed in the inner chamber of inner pedestal 314, is connected with inner pedestal 314 with cone match, and strains with nut.Inner pedestal 314 is connected with outer bearing carrier 313 by bearing 311, and with back-up ring 315 solid bearings 311 and adjusting degree of tightness, inner pedestal 314 upper ends and gear wheel 35 are fixed, and lower end and angle output shaft 316 are fixed, and keep coaxial.Outer bearing carrier 313 usefulness form of flanges are fixed on the T type mount pad 33.Angular transducer mount pad 317 is fixed on the outer bearing carrier 313, and angular transducer 319 is fixed on the angular transducer mount pad 317, and coaxial with outer bearing carrier 313, is connected with shaft coupling 318 between angle output shaft 316 and the angular transducer 319.Motor 31 connects to form drive unit with reductor 32, and be fixed on the T type 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, removing does not need the part that meshes, and only staying needs the part that meshes in the jet vane range of deflection angles.Baffle ring 39 is installed on the 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 the T type mount pad 33.Flow-stopping plate 38 is installed between the spout and heat shield 320 of engine 1, and is fixed on the T type mount pad 33.Solar heat protection backplate 36 is fixed on the flow-stopping plate 38.The output of motor is slowed down by reductor and is amplified moment of torsion, the gear set of forming by pinion wheel and gear wheel will move and pass to inner pedestal with moment of torsion again, the strain balance, the coupling band that drive inner pedestal and be fixed on the inner pedestal together rotate, and then the drive jet vane is swung 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 the strain balance real time record.Baffle ring 39 is installed on the coupling band 37, and covers inner pedestal 314 outstanding upper edges, and the gap suitable with inner pedestal 314 maintenances.Heat shield 320 covers all devices, and is fixed on the T type mount pad 33.Solar heat protection backplate 36 is used for stopping the engine gas jet flow to directly the washing away and ablates of jet vane rudderpost, and rudderpost is blown and wash away the influence to the aerodynamic force measurement in advance in preventing from testing.Flow-stopping plate 38 is used for stopping because of deflection, reflecting gas that jet vane causes in jet cutting car flow deflection, and engine flashback etc. is to the ablation of testing apparatus, guarantees the intact of main testing apparatus and can reuse.Heat shield 320 is used for stopping the jet cutting car flow heat radiation, makes heat shield 320 inside temperature in entire test be no more than the equipment normal range of operation.Baffle ring 39 is used for stopping the hot-fluid along the rudderpost downward transmission in slit on every side, and in the inner pedestal inner chamber air of placing strain balance and heat shield, form bending channel between the air, further stop heat to the strain balance transmission, guarantee that strain balance is under the substantially invariable temperature environment in the course of work, prevent that strain balance from influencing measuring accuracy because of thermal strain.
Motor 31 is AC servo motor, utilize that its rotating speed is fast, bearing accuracy is high and advantage such as overload capacity is strong, make device for measuring force can control jet vane and in of short duration engine thermal time installation, realize the quick deflection of complicated rule, and the impact of aerodynamic loading can bear engine ignition the time and in the quick deflection of jet vane; Described reductor 32 is planet-gear speed reducer, utilizes the characteristics that its reduction gear ratio is big, 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, the heat on the jet vane of being ablated by jet flow in order to blocking-up along coupling band to the strain balance transmission.Bearing 311 is taper roll bearing, and load-bearing capacity is big, can bear engine ignition moment huge impact load.Solar heat protection backplate 36 can select for use the compound substance of anti-ablation to make, and also can use on the guided missile the true solar heat protection backplate that uses, with the anti-ablation ability of examination solar heat protection backplate and to the protection effect of rudderpost.Process appropriate gap between solar heat protection backplate and the rudderpost, guarantee not because the jet vane rudderpost contacts the measurement that influences the jet vane aerodynamic loading with backplate, prevent that simultaneously excesssive gap from causing gas-flow to transmit and the burden of increase flow-stopping plate, heat shield and baffle ring etc. along the gap downwards.Flow-stopping plate 38 can be made by steel plate, be arranged between engine jet pipe and the heat shield, be fixed on the T type mount pad, become the L type, block top panel and the front panel of heat shield simultaneously, stopping because of the jet vane deflection that deflection causes in jet cutting car flow or reflecting gas, and engine flashback is to the ablation of testing apparatus, guarantees the intact of main testing apparatus and can reuse.Perforate on the flow-stopping plate guarantees to keep suitable gap between flow-stopping plate and rudderpost, the coupling band, prevents that contact from influencing aerodynamic force and measuring.Heat shield 320 optional usefulness have the glass epoxy riveted joint of heat insulating function, become frame type, are fixed on the T type mount pad, and perforate on the plate in the above makes between itself and coupling band to keep appropriate clearance, prevents that contact from influence the aerodynamic force measurement.
Shown in Figure 17,18, strain balance 312 is five component strain balances, and five components are respectively: My, Mz, Y, Mx, Q do not contain along the power Z of 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 such as Figure 17, left and right sides surface measurement Y with left and right sides post beam, upper and lower sides planar survey My, use the upper and lower surface of lower prop beam and measure Q, Mx and Mz are measured in the left and right side.Strain balance 312 front ends are inner cone 3123, on have threaded hole 3121, inner cone keyway 3122, cooperates with coupling band 37 with the conical surface, with keyway 3122 location lift-over, strain with bolt and to bore.The rear end is tail cone 3126, is processed with tail cone keyway 3125, cable hole 3127 and external thread 3128 on the tail cone.Signal wire passes from cable hole 3127, cooperates with inner pedestal 314 with the conical surface, locatees lift-over with keyway 3125, and strains with nut.Can reach each component output coordinating by the coordination of each post beam size and the selection of strainometer paste position, with the measuring accuracy of assurance power and moment, satisfy the accurate measurement of the bigger aerodynamic loading of suffered each the component value gap of jet vane.Adopt awl to cooperate before and after the balance, realize the lift-over location with key, realize the tension of awl with threaded engagement.Inner cone is connected with coupling band with heat insulation tapered sleeve, and the back awl is connected with inner pedestal.Awl is combined with to be beneficial to and guarantees the structure installation accuracy, is not prone to because cooperating the bad balance mechanical creep that causes to the influence of balance calibration precision and experimental measurement precision.
As Figure 11,12, shown in 13,33 one-tenth " T " fonts of T type mount pad, left surface is fitted with the installation end face, be processed with T type mount pad fixing screw hole 332 above, keyway 333 and loss of weight groove, externally process along engine long keyway and strip hole radially on the installation end face of fixed mechanism, insert keyway 333 and long keyway with key, device for measuring force can only be moved along the keyway direction, pass T type mount pad fixing screw hole 332 and external stability mechanism with bolt strip hole on the end face is installed, the back device for measuring force 3 that tights a bolt is fixed in the external stability mechanism, and the back device for measuring force 3 that loosers a bolt can radially slide along engine; Reductor is with after reductor mounting flange face 336 cooperates, and is fixing by reductor fixing screw hole 335 with bolt; Bearing base is with after bearing base mounting flange face 337 cooperates, and is fixing by bearing base fixing screw hole 338 with bolt; At heat shield 320 two sides processing screw hole, 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 19, the rudderpost of jet vane 4 cooperates with the jet vane rudderpost mating surface 372 of coupling band 37, processes column pin hole at rudderpost, fixes with the stud pin that passes jet vane fixed bolt pin-and-hole 371; The inner cone 3123 of strain balance 312 puts heat insulation tapered sleeve 310, cooperates the conical surface 373 to cooperate again with balance, and inserts balance fit keyway 374 with key and carry out the lift-over location, again with bolt tension awl.
As shown in figure 20, angular transducer 319 is made up of high precision single-turn potentiometer 3191 and high-accuracy resistance 3192.One end of the high-accuracy resistance 3192 that two resistances are identical just is connected (namely just being connected the high-accuracy resistance that resistance is identical with two terminals of power-at the power supply of potentiometer respectively) 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.With the signal end of high precision single-turn potentiometer 3191 as signal just, terminals between the 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.The high precision single-turn potentiometer has adaptive capacity to environment preferably, can bear bigger impact, vibrations and temperature variation, and this circuit can improve output signal, and energy angles of display output directly perceived is positive and negative.
Shown in Figure 24,25,26, gear wheel 35 usefulness bolt and are transmitted moment of torsion with first key that inserts keyway 3141 to first screw hole 3142 of inner pedestal 314; The tail cone of strain balance 312 cooperates with taper hole 3143, realizes the lift-over location with second key that inserts keyway 3144, strains with nut again; Back-up ring 315 usefulness screws are fixing by second screw hole 3145.
Shown in Figure 27,28,29, angle output shaft 316 1 ends are and inner pedestal 314 flange connecting that one end is the cylinder that is connected with shaft coupling 318; For the signal wire that makes strain balance 312 therefrom passes, and alleviate construction weight as far as possible, the coupling part is cut into a narrow beam between flange and the cylinder.
Shown in Figure 30,31, angular transducer mount pad 317 1 ends are and outer bearing carrier 313 flange connecting, one end is the installation end face of angular transducer 319, for the signal wire that makes strain balance 312 therefrom passes, and in the jet vane deflection, do not blocked by the angular transducer mount pad, flange is cut off with the both sides, coupling part that end face is installed.
In the process of the test, the gaseous jet that solar heat protection backplate 36 stops engine 1 is directly washed away and is ablated the rudderpost of jet vane 4, and rudderpost is blown and wash away the influence that aerodynamic force is measured in advance in preventing from testing.Flow-stopping plate 38 is used for stopping jet flow gas deflector, the reflection that causes in the jet flow deflection of engine 1 because of jet vane 4, and the tempering of engine 1 etc. is to the ablation of testing apparatus, 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 entire test be no more than the equipment normal range of operation.Baffle ring 39 stops along the hot-fluid of the rudderpost downward transmission in slit on every side, and forms bending channel between the air in the inner pedestal 314 inner chamber air of placing strain balance 312 and heat shield 320.Further stop heat to the transmission of strain balance 312, guarantee that strain balance 312 is under the substantially invariable temperature environment in the course of work, prevent that strain balance 312 from influencing measuring accuracy because of thermal strain.
After engine 1 ignition signal sends, AC servo motor 31 begins by specifying rule to rotate, its output is slowed down by planet-gear speed reducer 32 and is amplified moment of torsion, the gear set of forming by pinion wheel 34 and gear wheel 35 will move and pass to inner pedestal 314 with moment of torsion again, the strain balance 312, the coupling band 37 that drive inner pedestal 314 rotations and be fixed on the inner pedestal 314 together rotate, and then drive jet vane 4 is swung rapidly and accurately by the appointment rule 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 is accurately measured in real time by strain balance 312.
The content that is not described in detail in the instructions of the present invention belongs to those skilled in the art's known technology.
Claims (4)
1. a jet vane carries the pilot system of engine thermal test run, it is characterized in that: comprise device for measuring force (3) and mounting bracket (2), mounting bracket (2) is connected with the tail skirt end frame of engine (1), device for measuring force (3) is connected with mounting bracket (2), the quantity of device for measuring force (3) is identical with the sheet number of jet vane (4), be used for the fixing control jet vane (4) that reaches in the deflection of engines tail jet flow, and measure jet vane (4) deflection angle and suffered aerodynamic loading; Described mounting bracket (2) comprises position adjustments ring (21), mounting flange (22), position adjustments nut (23), support bar (24), end plate (25) and support key (26) is installed; The position in hole is corresponding on mounting hole on the mounting flange (22) and engine (1) the tail skirt end frame, mounting flange (22) is connected with support bar (24) with installing between the end plate (25), support bar (24) one ends insert the cylindrical hole that end plate (25) is installed, and strain with nut, the other end is followed successively by external thread, cylindrical section and threaded hole, the hole of mounting flange (22) cooperates with cylindrical section, position adjustments nut (23) cooperates with external thread, and withstand the rear end face of mounting flange (22), position adjustments ring (21) is enclosed within on the cylindrical section, position adjustments ring (21) the one ends bolt of inserting threaded hole, the other end withstands the front end face of mounting flange (22), turn position adjustments ring (21) and position adjustments nut (23), mounting flange (22) moves forward and backward along support bar (24), and mounting flange (22) and the distance of installing between the end plate (25) change thereupon; The long keyway and the strip hole that are processed with on the end plate (25) radially are installed, support key (26) is put into long keyway, and can in long keyway, radially slide, support key (26) is used for cooperating with the T type mount pad (33) of device for measuring force (3), and strip hole is used for device for measuring force (3) is fixed on installation end plate (25).
2. a kind of jet vane according to claim 1 carries the pilot system of engine thermal test run, and it is characterized in that: described device for measuring force (3) comprises motor (31), reductor (32), T type 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 the coupling band (37), coupling band (37) is used cone match with strain balance (312), and strain with bolt, be lined with heat insulation tapered sleeve (310) between coupling band (37) and strain balance (312) conical surface, strain balance (312) is placed in the inner chamber of inner pedestal (314), be connected with inner pedestal (314) with cone match, 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 regulate degree of tightness, inner pedestal (314) upper end is fixing with gear wheel (35), lower end and angle output shaft (316) are fixing, and keep coaxial, outer bearing carrier (313) is fixed on the T type mount pad (33) with flange, angular transducer (319) is fixed on the angular transducer mount pad (317), and it is coaxial with outer bearing carrier (313), angular transducer mount pad (317) is fixed on the outer bearing carrier (313), be connected with shaft coupling (318) between angle output shaft (316) and the angular transducer (319), motor (31) connects to form driving mechanism with reductor (32), and be fixed on the T type 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 the coupling band (37), and cover the outstanding upper edge of inner pedestal (314), heat shield (320) covers all devices, and be fixed on the T type mount pad (33), flow-stopping plate (38) is installed between the spout and heat shield (320) of engine (1), and be fixed on the T type mount pad (33), solar heat protection backplate (36) is fixed on the flow-stopping plate (38).
3. a kind of jet vane according to claim 2 carries the pilot system of engine thermal test run, it is characterized in that: described strain balance (312) is six post beam (3124) structures, six post beam front ends are inner cone (3123), have threaded hole (3121), inner cone keyway (3122) on the inner cone (3123), six post beam rear ends are tail cone (3126), are processed with tail cone keyway (3125), cable hole (3127) and external thread (3128) on the tail cone (3126).
4. a kind of jet vane according to claim 3 carries the pilot system of engine thermal test run, it is characterized in that: described angular transducer (319) is made up 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), form the bridge circuit of a four-wire system jointly, as angular transducer (319).
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| CN 201110396105 CN102435410B (en) | 2011-12-01 | 2011-12-01 | Test system of gas vane carried engine hot commissioning |
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| CN 201110396105 CN102435410B (en) | 2011-12-01 | 2011-12-01 | Test system of gas vane carried engine hot commissioning |
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| CN103954389B (en) * | 2014-05-09 | 2016-01-06 | 中国航天空气动力技术研究院 | Jet vane dynamometer check device |
| CN104568464A (en) * | 2014-12-29 | 2015-04-29 | 广电计量检测（天津）有限公司 | Thermal radiation test bench for engine armor and controlling method thereof |
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| CN114486243B (en) * | 2021-12-16 | 2024-04-09 | 航天科工防御技术研究试验中心 | Device and method for testing friction torque of rudder shaft rotating mechanism |
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