CN102494867A - 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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- CN102494867A CN102494867A CN2011103936240A CN201110393624A CN102494867A CN 102494867 A CN102494867 A CN 102494867A CN 2011103936240 A CN2011103936240 A CN 2011103936240A CN 201110393624 A CN201110393624 A CN 201110393624A CN 102494867 A CN102494867 A CN 102494867A
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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 the device for measuring force 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 as the topworks of guided missile thrust vectoring control more and more.Because jet cutting car flow has singularity such as high temperature, deep-etching and height wash away, be nonsteady jet, be Theoretical Calculation or the wind tunnel test true stressing conditions 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 stressed final data of jet vane and the ultimate criterion of passing judgment on jet vane aerodynamic configuration design result.
Device for measuring force is the basic equipment that jet vane carries engine thermal test run dynamometer check, and its function and measuring accuracy etc. have directly determined the accuracy of dynamometer check.Because jet vane is used less before; Its lift-launch engine thermal test run dynamometer check of carrying out is carried out seldom,, realized the dynamometry of jet vane under the typicalness usually to the simple and easy special-purpose test unit of a certain model development one cover; Its structure is simpler usually; 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 the jet vane control law, and it is necessary accurately to measure jet vane device for measuring force with strong versatility and reusable property of suffered aerodynamic loading in the engines tail jet flow.
Summary of the invention
Technology of the present invention is dealt with problems and is: the deficiency that overcomes prior art; Provide a kind of and can drive jet vane deflection quick and precisely in the engines tail jet flow, and measure the actual deflection angle of jet vane in real time and the aerodynamic loading that bears have strong versatility, a reusable device for measuring force.
Technical solution of the present invention is: a kind of jet vane carries the device for measuring force of engine thermal test run, it is characterized in that: comprise and measure assembly, driving mechanism, gear train, solar heat protection assembly, mounting base and coupling assembling; Said measurement assembly comprises strain balance, angular transducer, and strain balance is used to measure the aerodynamic loading that affacts on the jet vane, and angular transducer is used to measure the deflection angle of jet vane; Said 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; Said 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; 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 are used cone match; And with the bolt tension, the angle output shaft is fixedly connected with bearing base, and the angle output shaft is connected with angular transducer through shaft coupling; Said mounting base comprises bearing base and T type mount pad, and bearing base is used for fixing strain balance and angular transducer, and T type mount pad is connected with external stability mechanism.
Said measurement assembly comprises strain balance, angular transducer; Said driving mechanism comprises motor, reductor; Described gear train comprises pinion wheel, gear wheel; Said solar heat protection assembly comprises solar heat protection backplate, flow-stopping plate, baffle ring, heat insulation tapered sleeve, heat shield; Said mounting base comprises bearing base, angular transducer mount pad, T type mount pad, and 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 the coupling band, and coupling band and strain balance are used cone match, and with the bolt tension, is lined with heat insulation tapered sleeve between the 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 with the nut tension, inner pedestal is connected with outer bearing carrier through bearing; And with back-up ring solid bearing and adjusting degree of tightness, the inner pedestal upper end is fixed with gear wheel, and lower end and angle output shaft are fixed, and keep coaxial; Outer bearing carrier is fixed on the T type mount pad with flange, and 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; Speed reducer output shaft and pinion wheel are fixed, pinion wheel and gear wheel engagement, and the baffle ring is installed on the coupling band; And covering the outstanding upper edge of inner pedestal, heat shield covers all devices, and is 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.
Said 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.
Said 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, device for measuring force of the present invention can drive that jet vane is realized fast, accurately deflection in the engines tail jet flow, realizes the accurate simulation of trystate to the jet vane duty.
2, device for measuring force of the present invention can accurately be measured true deflection angle and the corresponding aerodynamic loading of jet vane any time, angle measurement error≤0.05 °, and the strain balance measuring accuracy is superior to 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 installing and locating with respect to engine, and the jet vane that can be applied to the various sizes engine carries the heat run dynamometer check, has stronger versatility.
Through satisfying above-mentioned requirements, device for measuring force can satisfy more polytypic test, and each test can be obtained more more accurately test figures, has improved test accuracy, has reduced experimentation cost.
Description of drawings
Fig. 1 is the 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 type 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 the gear set structure and cooperates synoptic diagram;
Figure 11 is a solar heat protection backplate example structure synoptic diagram;
Figure 12 is the rear view of Figure 11;
Figure 13 is the vertical view of Figure 11;
Figure 14 is the bearing base structural representation;
Figure 15 is the upward view of Figure 14;
Figure 16 is the internal bearing sleeve structural representation;
Figure 17 is Figure 16 vertical view;
Figure 18 is Figure 16 upward view;
Figure 19 is an 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 an angular transducer mount pad structural representation;
Figure 23 is Figure 22 vertical view;
Figure 24 is the strain balance structural representation;
Figure 25 is the A-A cut-open view of Figure 13;
Figure 26 is the coupling band structural drawing;
Figure 27 forms synoptic diagram for angular transducer.
Figure 28 is a kind of external stability structural scheme of mechanism.
Figure 29 is that the P of Figure 28 is to view.
Among the figure:
1, engine, 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, solar heat protection backplate, 37, coupling band, 38, flow-stopping plate, 39, the 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, 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, 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; 3141, first insert keyway, 3142, first screw hole, 3143, taper hole, 3144, second inserts keyway, 3145, second 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.
Embodiment
The present invention relates to the device for measuring force that a kind of jet vane carries the engine thermal test run; Device for measuring force can directly be installed on the engines tail skirt end frame through external stability mechanism; Also can be installed in the independent stationary mechanism of being fixed in ground, and realize the relative positioning of jet vane and engine tail nozzle through the relative position between the test bay of regulating fixed mechanism and stationary engine; One cover 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 drive mechanism jet vane of being made up of motor and speed reducer in the device for measuring force is quick in jet cutting car flow, accurately deflection, and (always hinders tolerance less than 0.01% through high precision potentiometer (potentiometer independent linearity tolerance is ± 0.1%) and high-accuracy resistance.) angular transducer formed accurately measures 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 can drive quick in jet cutting car flow, the accurate deflection of jet vane, and accurately measures jet vane actual deflection angle and suffered aerodynamic loading in real time, and reusability is good, highly versatile.For size of engine specifications vary in a big way, through changing the external stability mechanism of different size, device for measuring force still can use.When practical application, because mostly jet vane 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 used to measure the aerodynamic loading that affacts on the jet vane, and angular transducer is fixed on the angular transducer mount pad, and angular transducer is used to measure 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 fixedly connected with coupling band, and coupling band and strain balance are used cone match, and strain with bolt; The angle output shaft is fixedly connected with bearing base, and the angle output shaft is connected with angular transducer through shaft coupling; Mounting base comprises bearing base, angular transducer mount pad and T type mount pad; Bearing base is used for fixing strain balance; The angular transducer mount pad is used for fixing angular transducer; 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 fixedly connected with external stability mechanism.
Below in conjunction with accompanying drawing the present invention is elaborated:
Like Fig. 1-shown in Figure 23, 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, be lined with heat insulation tapered sleeve 310 between the coupling band 37 and strain balance 312 conical surfaces with the bolt tension, transmit to strain balance 312 along coupling band 37 in order to the heat on the blocking-up 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 through 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 fixing, and lower end and angle output shaft 316 are fixing, and keep coaxial.Outer bearing carrier 313 usefulness flange form fix are to T type mount pad 33, and for reducing physical dimension, both sides are cut off before and after the flange face.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 is fixed on the T type mount pad 33, and 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 need not mesh, only stay the part that needs engagement 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, keeps suitable gap with inner pedestal 314.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 through reductor and is amplified moment of torsion; The gear set of forming through pinion wheel and gear wheel again will move and moment of torsion passes to inner pedestal; 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 whole actual rotation angle of jet vane, coupling band, strain balance and inner pedestal in real time through shaft coupling, angle output shaft; The aerodynamic loading that jet vane bears passes to strain balance through 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 keeps suitable gap with inner pedestal 314.Heat shield 320 covers all devices, and is fixed on the T type mount pad 33.Solar heat protection backplate 36 is used to stop the engine gas jet flow to directly the washing away and ablate of jet vane rudderpost, and rudderpost is blown and wash away the influence that aerodynamic force is measured in advance in preventing to test.Flow-stopping plate 38 is used for stopping deflection, the reflecting gas because of 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 to stop 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 to stop 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 an 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 drive jet vane in of short duration engine thermal time installation fast, accurately deflection, and the impact of aerodynamic loading can bear engine ignition the time and in the quick deflection of jet vane; Described reductor 32 is a 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 accurate 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 a 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 process, and adopts the true solar heat protection backplate that uses on the guided missile more, reaches the protection effect to rudderpost with the anti-ablation ability of examination solar heat protection backplate.Process appropriate gap between solar heat protection backplate and the rudderpost; Guarantee not because of 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 processed 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 the top panel and the front panel of heat shield simultaneously; Stopping because of 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 the measurement of contact and influence aerodynamic force.Heat shield 320 optional usefulness have the glass epoxy riveted joint of heat insulating function, become frame type, be fixed on the T type mount pad, and perforate on the plate in the above, and keep appropriate clearance between coupling band, prevent the measurement of contact and influence aerodynamic force.
Like Fig. 7,8, shown in 9; 33 one-tenth " T " fonts of T type mount pad; Be processed with T type mount pad fixing screw hole 332, keyway 333 and loss of weight groove above; Screw hole 332 can be used for T type mount pad and be connected with external agency, and keyway 333 is to be used to realize that T type mount pad externally moves the position in the mechanism, to realize the change of device for measuring force with respect to the engine radial distance.A kind of synoptic diagram of external agency is 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 used for being connected with engine apron end frame; End plate 25 is installed is used to install and fix 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 and installation end plate 25 usefulness nuts and cylinder matching and fixing, 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, and an end is with the bolt of inserting threaded hole, and an end withstands the front end face of mounting flange 22.Through turning position adjustments ring 21 and position adjustments nut 23, mounting flange 22 is moved forward and backward along support bar 24, thereby realize mounting flange 22 and the distance adjustment between the end plate 25 is installed.Install on the end plate 25 and be processed with long keyway and strip hole radially; The support key keyway 333 of T type mount pad 33 cooperates with support key 26 in the device for measuring force; Device for measuring force can radially slide in installation end plate 25 upper edges, passes through fixedly device for measuring force 3 of strip hole with bolt, passes 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.External agency 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 of 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, and its flow field of living in is consistent with the real work flow field, and measurement result is more true and reliable.Through regulating the distance of mounting flange 22 and installation end frame 25; Can regulate the axial location of device for measuring force with respect to the nozzle of engine 1; Move radially along installation end frame 25 through device for measuring force, the scalable device for measuring force is with respect to the radial position of the nozzle of engine 1.Through above-mentioned adjusting; Can locate the position of jet vane 4 with respect to engine 1 nozzle; Jet vane 1 can be installed by missile-borne actual position, and 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 through the mounting bracket 2 of changing different size.External agency shown in Figure 28-29 is merely a kind of preferred performance.In fact, as long as externally going up of fixed mechanism processed along engine long keyway and strip hole radially, can realize the fixing of device for measuring force and move radially getting final product.
Reductor is with after reductor mounting flange face 336 cooperates, and is fixing through reductor fixing screw hole 335 with bolt; Bearing base is with after bearing base mounting flange face 337 cooperates, and is fixing through bearing base fixing screw hole 338 with bolt; The processing screw hole in heat shield 320 two sides, fixing with screw through heat shield fixing screw hole 331; Flow-stopping plate 38 is fixing through flow-stopping plate fixing screw hole 334.
Like Figure 16,17, shown in 18, gear wheel 35 usefulness bolt and are transmitted moment of torsion with the key that inserts keyway 3141 to the 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 the key that inserts keyway 3144, strains with nut again; Back-up ring 315 usefulness screws are fixing through screw hole 3145.
Like Figure 19,20, shown in 21, 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.
Like Figure 22, shown in 23; 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.
Like Figure 24, shown in 25, 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 are with the left and right sides surface measurement Y of left and right sides post beam, upper and lower sides planar survey My; Use the upper and lower surfaces 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, cooperate with coupling band 37 with the conical surface, with inner cone keyway 3122 location lift-over, with bolt tension awl.The rear end is a 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 tail cone keyway 3125, and strains with nut.Can reach each component output coordinating through the coordination of each post beam size and the selection of strainometer paste position,, satisfy the accurate measurement of the bigger aerodynamic loading of suffered each the component value gap of jet vane with the measuring accuracy of assurance power and moment.Adopt awl to cooperate before and after the balance, realize the lift-over location, realize the tension of awl with threaded engagement with key.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 of cooperating the bad influence that causes the balance mechanical creep to balance calibration precision and experimental measurement precision.
Shown in figure 26, the rudderpost of jet vane 4 cooperates with the jet vane rudderpost mating surface 372 of coupling band 37, on rudderpost, processes column pin hole, 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.
Shown in figure 27, angular transducer 319 is made up of high precision single-turn potentiometer 3191 and precision resistance 3192.Two resistances differ a end less than 0.01% high-accuracy resistance 3192 and just are connected (promptly 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 the power supply of high precision single-turn potentiometer 3191 with two terminals of power-; The other end connects together, and draws new terminals.With the signal end of high precision single-turn potentiometer 3191 just as signal; 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 the output signal, and ability angles of display output directly perceived is positive and negative.
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 to test.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 in the inner pedestal 314 inner chamber air of placing strain balance 312 and heat shield 320, form bending channel between the air; Further stop the transmission of heat to 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 to rotate; Its output is slowed down through planet-gear speed reducer 32 and is amplified moment of torsion; The gear set of forming through pinion wheel 34 and gear wheel 35 again will move and moment of torsion passes to inner pedestal 314, drives that inner pedestal 314 rotates and the strain balance 312, the coupling band 37 that are fixed on the inner pedestal 314 together rotate, and then drive jet vane 4 is swung by the appointment rule in the jet flow of engine 1 rapidly and accurately.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 through shaft coupling 318, angle output shaft 316; The aerodynamic loading that jet vane 4 bears passes to strain balance 312 through coupling band 37, and is accurately measured in real time by strain balance 312.
The content of not doing to describe 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 device for measuring force of engine thermal test run, it is characterized in that: comprise and measure assembly, driving mechanism, gear train, solar heat protection assembly, mounting base and coupling assembling; Said measurement assembly comprises strain balance, angular transducer, and strain balance is used to measure the aerodynamic loading that affacts on the jet vane, and angular transducer is used to measure the deflection angle of jet vane; Said 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; Said 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; 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 are used cone match; And with the bolt tension, the angle output shaft is fixedly connected with bearing base, and the angle output shaft is connected with angular transducer through shaft coupling; Said mounting base comprises bearing base, angular transducer mount pad and T type mount pad, and bearing base is used for fixing strain balance and angular transducer, and the angular transducer mount pad is used for fixing angular transducer, and T type mount pad is connected with external stability mechanism.
2. a kind of jet vane according to claim 1 carries the device for measuring force of engine thermal test run; It is characterized in that: said measurement assembly comprises strain balance (312), angular transducer (319); Said driving mechanism comprises motor (31), reductor (32); Described gear train comprises pinion wheel (34), gear wheel (35); Said 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); Said mounting base comprises bearing base, angular transducer mount pad (317), T type mount pad (33), and bearing base comprises bearing (311), outer bearing carrier (313), inner pedestal (314), back-up ring (315), and described coupling assembling comprises coupling band (37), angle output shaft (316), shaft coupling (318); Jet vane (4) is fixed on the coupling band (37), and coupling band (37) is used cone match with strain balance (312), and strains with bolt; Be lined with heat insulation tapered sleeve (310) between the coupling band (37) and strain balance (312) conical surface, strain balance (312) is placed in the inner chamber of inner pedestal (314), is connected with inner pedestal (314) with cone match; And with the nut tension, inner pedestal (314) is connected with outer bearing carrier (313) through bearing (311), and with back-up ring (315) solid bearing (311) and adjusting degree of tightness; Inner pedestal (314) upper end is fixing with gear wheel (35), and 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, and angular transducer (319) is fixed on the angular transducer mount pad (317), and coaxial with outer bearing carrier (313); Angular transducer mount pad (317) is fixed on the outer bearing carrier (313), is connected with shaft coupling (318) between angle output shaft (316) and the angular transducer (319), and 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, and 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 is fixed on the T type mount pad (33), and 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 1 carries the device for measuring force of engine thermal test run; It is characterized in that: said 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 1 carries the device for measuring force of engine thermal test run; It is characterized in that: said 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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| 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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| CN102494867B CN102494867B (en) | 2014-03-19 |
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| CN102840962A (en) * | 2012-08-17 | 2012-12-26 | 中国航天空气动力技术研究院 | Half-module window rotating mechanism applied to supersonic wind tunnel |
| CN103615938A (en) * | 2013-12-09 | 2014-03-05 | 中国航天空气动力技术研究院 | Guided-missile folding wing unfolding testing apparatus |
| CN103954389A (en) * | 2014-05-09 | 2014-07-30 | 中国航天空气动力技术研究院 | Gas vane force measuring test device |
| CN104677638A (en) * | 2013-11-27 | 2015-06-03 | 中国舰船研究设计中心 | Blade tip jet test device |
| CN107416213A (en) * | 2017-05-16 | 2017-12-01 | 上海航天控制技术研究所 | A kind of aircraft tail end fire proof construction with jet vane |
| CN107884153A (en) * | 2017-10-24 | 2018-04-06 | 中国运载火箭技术研究院 | A kind of structure for simulating high speed pneumatic denudation |
| CN109632234A (en) * | 2018-12-25 | 2019-04-16 | 中国航天空气动力技术研究院 | A kind of gas vane carried engine hot commissioning test rudderpost protective device |
| CN110987399A (en) * | 2019-12-19 | 2020-04-10 | 武汉天拓宇航智能装备有限公司 | Gas rudder testing device |
| CN112284679A (en) * | 2020-09-10 | 2021-01-29 | 湖北航天飞行器研究所 | Five-component balance for gas vane force measurement and component force calculation method |
| CN112284750A (en) * | 2020-09-10 | 2021-01-29 | 湖北航天飞行器研究所 | Method for testing performance of gas rudder of solid rocket engine |
| CN113932966A (en) * | 2021-09-15 | 2022-01-14 | 航天科工防御技术研究试验中心 | Gas rudder force measuring device, system and application method |
| CN113933044A (en) * | 2021-12-09 | 2022-01-14 | 星河动力(北京)空间科技有限公司 | Test method, device and platform for flexible joint assembly of rocket engine spray pipe |
| CN114235321A (en) * | 2022-02-25 | 2022-03-25 | 中国空气动力研究与发展中心高速空气动力研究所 | Wind tunnel force measurement experimental device integrating gas rudder and spray pipe |
| CN115575079A (en) * | 2022-12-08 | 2023-01-06 | 中国空气动力研究与发展中心低速空气动力研究所 | Connecting piece for strain balance, temperature control system and temperature control method |
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| CN102840962B (en) * | 2012-08-17 | 2015-02-25 | 中国航天空气动力技术研究院 | Half-module window rotating mechanism applied to supersonic wind tunnel |
| CN104677638A (en) * | 2013-11-27 | 2015-06-03 | 中国舰船研究设计中心 | Blade tip jet test device |
| CN103615938A (en) * | 2013-12-09 | 2014-03-05 | 中国航天空气动力技术研究院 | Guided-missile folding wing unfolding testing apparatus |
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| CN110987399A (en) * | 2019-12-19 | 2020-04-10 | 武汉天拓宇航智能装备有限公司 | Gas rudder testing device |
| CN110987399B (en) * | 2019-12-19 | 2021-11-23 | 武汉天拓宇航智能装备有限公司 | Gas rudder testing device |
| CN112284679A (en) * | 2020-09-10 | 2021-01-29 | 湖北航天飞行器研究所 | Five-component balance for gas vane force measurement and component force calculation method |
| CN112284750A (en) * | 2020-09-10 | 2021-01-29 | 湖北航天飞行器研究所 | Method for testing performance of gas rudder of solid rocket engine |
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| CN113932966B (en) * | 2021-09-15 | 2023-12-12 | 航天科工防御技术研究试验中心 | Force measuring device, system and application method of gas rudder |
| CN113933044A (en) * | 2021-12-09 | 2022-01-14 | 星河动力(北京)空间科技有限公司 | Test method, device and platform for flexible joint assembly of rocket engine spray pipe |
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| CN115575079A (en) * | 2022-12-08 | 2023-01-06 | 中国空气动力研究与发展中心低速空气动力研究所 | Connecting piece for strain balance, temperature control system and temperature control method |
| CN115575079B (en) * | 2022-12-08 | 2023-03-21 | 中国空气动力研究与发展中心低速空气动力研究所 | Connecting piece for strain balance, temperature control system and temperature control method |
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