CN109084982A - A kind of high-thrust rocket three axis force measuring device and measuring method - Google Patents
A kind of high-thrust rocket three axis force measuring device and measuring method Download PDFInfo
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- CN109084982A CN109084982A CN201810995320.3A CN201810995320A CN109084982A CN 109084982 A CN109084982 A CN 109084982A CN 201810995320 A CN201810995320 A CN 201810995320A CN 109084982 A CN109084982 A CN 109084982A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L5/00—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes
- G01L5/13—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes for measuring the tractive or propulsive power of vehicles
- G01L5/133—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes for measuring the tractive or propulsive power of vehicles for measuring thrust of propulsive devices, e.g. of propellers
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Abstract
The present invention relates to a kind of high-thrust rocket three axis force measuring device and measuring method, solve the problem of that measurement accuracy can not be effectively ensured so that measurement accuracy reduces in existing high-thrust rocket three-dimensional force measuring method.The measuring device includes that frame, the lateral thrust measurement unit in upper layer, the lateral thrust measurement unit of lower layer and axial thrust measuring unit are determined in test run moving frame, test run；Test run determines frame and includes outer layer support frame, determines ring beam on frame, determines frame lower ring, determines frame floor stringer and determine frame attachment beam；Test run moving frame includes ring beam in moving frame, moving frame lower ring, internal layer support frame；Axial thrust measuring unit is mounted on ring beam in moving frame and determines on frame between ring beam；The lateral thrust measurement unit setting of lower layer is being determined between frame floor stringer and moving frame lower ring；The lateral thrust measurement unit in upper layer is eight groups, is arranged on determining frame attachment beam and moving frame between ring beam.Meanwhile the present invention also provides a kind of three-dimensional force measuring method based on above-mentioned apparatus.
Description
Technical field
The present invention relates to high-thrust rockets to test field, and in particular to a kind of high-thrust rocket three axis force
Measuring device and measuring method.
Background technique
The test of existing high-thrust rocket only considers engine main thrust size, and to engine lateral thrust
It studies less.It is main to use the thrust measurement side based on multi-component force gauge at present when carrying out the measurement of rocket engine lateral thrust
Method and thrust test method based on unidirectional force sensor (measurement method based on six degree of freedom platform and are based on orthogonal coordinate system
Thrust test method).
Since high-thrust rocket figure is huge, thrust is high, according to the thrust test method of multi-component force gauge, then exist
Engine can not laterally install lateral pre-tightening apparatus, seriously reduce the reliability of engine test process, and then engine
It is also respectively unable to get guarantee to the measurement accuracy of thrust, so that measurement accuracy reduces.
The method that the mode that multiple groups unidirectional force sensor matches measures engine lateral thrust, has been widely used
During the three-dimensional thrust measurement of thrustor, such mode need to solve each sensor in motor power measurement process
The problem of measured value intercouples, if such method is applied in the three-dimensional thrust measurement of high-thrust rocket, high thrust
It is larger that rocket engine compared to thrustor measures each force value gap to power, due to the influence of high thrust mutual interference, compared with
Influence of the low thrust direction force value vulnerable to larger thrust direction force value, can not often be effectively ensured measurement accuracy, so that measurement
Accuracy reduces.
Summary of the invention
Present invention aim to address existing high-thrust rocket three-dimensional force measuring methods, and measurement can not be effectively ensured
Accuracy, so that the problem of measurement accuracy reduces, provides a kind of high-thrust rocket three-dimensional force measuring device and survey
Amount method can be realized the precise measurement of 1200kN high thrust oxygen kerosene engine three-dimensional thrust using this method.
The technical scheme is that
Frame is determined in a kind of high-thrust rocket three-dimensional force measuring device, including test run moving frame and test run, and test run moving frame is logical
It crosses four groups of counterweights-lever pretightning force device to be mounted on test run and determine on frame, is characterized in that, further includes upper layer lateral thrust
Measuring unit, the lateral thrust measurement unit of lower layer and axial thrust measuring unit；In X, Y, Z three-dimensional system of coordinate, test run is defined
The axial direction of moving frame is Z-direction, and radial is X, Y-direction；
The test run determines frame and includes outer layer support frame, determine ring beam on frame, determine frame lower ring, determine frame floor stringer and connect with frame is determined
Beam；It is described to determine on frame ring beam and determine the inside that frame lower ring is fixed at outer layer support frame, it is described to determine frame floor stringer and fix to set
It sets in the lower section for determining frame lower ring, it is described to determine frame attachment beam and be fixed at determine ring beam on frame, determine between frame lower ring, and along fixed
Ring beam on frame, the circumferential setting for determining frame lower ring；
The test run moving frame includes ring beam in moving frame, moving frame lower ring, internal layer support frame；Ring beam and moving frame in the moving frame
Lower ring is connected by internal layer support frame, and ring beam is located at and determines ring beam on frame and determine between frame lower ring in the moving frame, described dynamic
Frame lower ring, which is located at, to be determined below frame lower ring；
It is described to determine ring beam on frame, determine that frame lower ring, ring beam, moving frame lower ring are coaxially disposed in moving frame；
The axial thrust measuring unit is four groups, and four groups of axial thrust measuring units are mounted on ring beam in moving frame and determine frame
Between upper ring beam, and it is uniformly distributed along the circumferential direction for determining ring beam on frame, for measuring engine axial thrust；
The lateral thrust measurement unit of lower layer is two groups, and the lateral thrust measurement unit of Liang Zu lower layer is arranged in a mutually vertical manner,
And be mounted on and determine between frame floor stringer and moving frame lower ring, for measuring engine lower layer lateral force；
The lateral thrust measurement unit in upper layer is eight groups, two groups in X to being arranged in parallel, two groups in-X to being arranged in parallel,
Two groups are arranged in parallel in Y-direction, and two groups are arranged in parallel in-Y-direction；Frame attachment beam is being determined in the lateral thrust measurement unit setting in upper layer
And in moving frame between ring beam, the lateral thrust measurement unit in upper layer includes pre-tightening pull rod, third flexible connecting member, second two-way
Measurement sensor and modular support frame；The modular support frame, which is fixed at, to be determined on frame attachment beam, the preload pull rod setting
In modular support frame, the one end for pre-tightening pull rod is threadedly coupled with modular support frame, and the other end and the third for pre-tightening pull rod are flexible
The threaded one end of connector connects, and the other end of third flexible connecting member passes through ring beam on the second bidirectional measurement sensor and moving frame
It is fixedly connected.
Further, the axial thrust measuring unit includes the first flexible connecting member, load cell and pillar；It is described
One end of pillar is connect with ring beam on frame is determined, on one end of the load cell and moving frame ring beam connect, the pillar it is another
One end is connect with the load cell other end by the first flexible connecting member.
Further, the lateral thrust measurement unit of the lower layer includes that the second flexible connecting member and the first bidirectional measurement sense
Device, one end of the first bidirectional measurement sensor, which is mounted on, determines on frame floor stringer, the other end by the second flexible connecting member with
The connection of moving frame lower ring.
Further, first flexible connecting member, the second flexible connecting member are identical with third flexible connecting member structure, packet
Cylindrical body is included, in Xr、Yr、ZrIn three-dimensional system of coordinate, the axial direction for defining cylindrical body is ZrTo radial is Xr、YrTo；Institute
Cylindrical body is stated along axial direction ZrIt is disposed with recess group I and recess group II, the recess group I is in cylindrical body XrDirection
Setting, the recess group II is in cylindrical body YrDirection setting；The recess group I include two the first recesses, two first
Recess is arranged about the axisymmetrical of cylindrical body；The recess group II includes two the second recesses, and two the second recesses close
It is arranged in the axisymmetrical of cylindrical body.When flexible connecting member can efficiently reduce three axis force measurement, respectively between power
Mutual interference improves systematic survey accuracy.
Further, from XrDirection sees, the rectangle for being projected as quadrangle chamfering of first recess, from YrDirection is seen, described
The rectangle for being projected as being connected and semicircle of first recess, the rectangle short side are tangent with semicircle respectively；Described second is recessed
Mouth is identical as the shape of the first recess.
Further, the preload pull rod includes sequentially connected first thread segment, nut and the second thread segment, and described
The rotation direction of one thread segment and the second thread segment is identical, screw pitch is different.
Further, the pitch difference of first thread segment and the second thread segment is 0.1mm.
Meanwhile the present invention also provides a kind of three-dimensional force measuring methods based on above-mentioned measuring device, comprising the following steps:
1) three axis force measurement model is established；
Rocket engine three axis force measurement model is established, X and Y-direction arrange bidirectional measurement sensors X1、X2、X3、X4、X5With
Y1、Y2、Y3、Y4、Y5, be respectively used to measurement X to Y-direction component, Z-direction arrange unidirectional force sensor Z1、Z2、Z3、Z4, for measuring Z
To thrust；
2) acquisition of correction factor；
2.1) simulation applies engine main thrust and three axis force, using measuring device, applies different directions, different size of
Power obtains the measured value size of each sensor in measuring device；
2.2) input multiple groups simulate three axis force FX′、FY′、FZ', obtain each sensor output value FX1′、FX2′、FX3′、FX4′、
FX5′、FY1′、FY2′、FY3′、FY4′、FY5′、Fz1′、Fz2′、Fz3′、Fz4', by multiple groups FX′、FY′、FZ' and each sensor output value
Introduced Malaria formula, and each correction factor a, b are determined by parameter fitting1、b2、c1、c2；
Correction formula are as follows:
3) three axis force measures；
During engine ignition, by established three-dimensional force measuring device, each measurement sensor reading F is obtainedX1、
FX2、FX3、FX4、Fx5、FY1、FY2、FY3、FY4、FY5、FZ1、FZ2、FZ3、FZ4, each measurement sensor reading is passed through into engine three-dimensional
The amendment of power correction formula, obtains the three-dimensional force value size F of actual measurementX、FY、FZ。
It further, further include pre-tightening step: the preload of the lateral thrust measurement unit in symmetrical rotary upper layer before step 1)
Pull rod, specially opposite direction rotate the preload pull rod of X and-X, and opposite direction rotates the preload pull rod of Y and-Y, realize sensor
The load of pretightning force.
Further, further include pressure increase step before step 1): Propellant Supply pipeline is pressurized, pressurization value and hair
Motivation test run required pressure value is identical, after pressurization, records each sensor initial reading, and by each biography in measurement process
The sensor initial reading subtracts, and eliminates influence of the Propellant Supply pipeline blind flange force to lateral thrust measurement.
Advantages of the present invention are as follows:
1. the present invention combines the characteristics of high-thrust rocket running support, structure of modification is carried out to running support, in not shadow
Under the premise of sound engine shaft is measured to main thrust, engine lateral thrust is measured, measurement accuracy is improved.
2. the present invention is using obtaining each measurement value sensor to different size lateral force the load of engine measuring position is each,
The thrust measurement of engine three-dimensional is corrected by data fit approach using the corresponding relationship of multiple groups input force value and measurement force value
It is dry to three-dimensional thrust precise measurement to solve omnidirectional distribution measuring unit mutual interference and architectural characteristic for each coefficient being worth in calculation formula
Measurement accuracy is effectively ensured in the problem of disturbing.
3. measuring device of the present invention is easy for installation, structure is simple, can be reliable under the strong vibration environment of engine test
Work.
Detailed description of the invention
Fig. 1 is high-thrust rocket three-dimensional force measuring device front view of the present invention；
Fig. 2 is high-thrust rocket three-dimensional force measuring device tomograph of the present invention；
Fig. 3 is high-thrust rocket three-dimensional force measuring device top view of the present invention；
Fig. 4 is axial thrust measuring unit structure chart of the present invention；
Fig. 5 is the lateral thrust measurement cellular construction figure of lower layer of the present invention；
Fig. 6 is the lateral thrust measurement cellular construction main view in upper layer of the present invention；
Fig. 7 is the lateral thrust measurement cellular construction top view in upper layer of the present invention；
Fig. 8 is that the present invention pre-tightens drawbar structure diagram；
Fig. 9 is the first flexible connecting member structural schematic diagram of the invention；
Figure 10 is the measurement model figure of inventive engine three-dimensional thrust；
Figure 11 is the schematic diagram that the present invention eliminates that blind flange force influences lateral thrust measurement；
Figure 12 is counterweight of the present invention-lever pretightning force structure drawing of device.
Appended drawing reference: frame, the lateral thrust measurement unit in the upper layer 3-, 4- lower layer lateral thrust are determined in 1- test run moving frame, 2- test run
Measuring unit, 5- axial thrust measuring unit, 6- bellows, ring beam in 11- moving frame, 12- moving frame lower ring, the support of 13- internal layer
Frame, 14- counterweight-lever pretightning force device, 21- outer layer support frame, 22- determine ring beam on frame, and 23- determines frame lower ring, and 24- determines frame
Floor stringer, 25- determine frame attachment beam, and 31- pre-tightens pull rod, 32- third flexible connecting member, 33- the second bidirectional measurement sensor, 34-
Modular support frame；The first thread segment of 311-, 312- nut, the second thread segment of 313-；The second flexible connecting member of 41-, 42- first pair
To measurement sensor；The first flexible connecting member of 51-, 52- load cell, 53- pillar；141- pull rod, 142- lever dolly,
143- lever, 144- counterweight pull rod, 145- counterweight, 611- cylindrical body, the first recess of 612-, the second recess of 613-.
Specific embodiment
Technical solution of the present invention is clearly and completely described with reference to the accompanying drawings of the specification.
The present invention has installed three-dimensional force measuring device additional on 1200kN rocket engine running support, to 1200kN high thrust
The lateral thrust of rocket engine measures.Using measuring device provided by the invention, apply not Tongfang by calibrated force source
To, different size of lateral thrust, the measured value size of sensor in each three-dimensional force measuring device is obtained, establishes and each is sensed to power
Computation model (correction formula) between device measured value and engine three axis force, and utilize the side of motor power calibrated in situ
Method, fitting obtain the size of each correction factor in computation model.It, can be by each to power in actual lateral thrust measurement process
Measurement value sensor determines the practical three axis force size of engine.
As shown in Figure 1, Figure 2, the high-thrust rocket three-dimensional force measuring device of Fig. 3, specifically includes test run moving frame 1, test run
Determine frame 2, further include the lateral thrust measurement unit 3 in upper layer, the lateral thrust measurement unit 4 of lower layer and axial thrust measuring unit 5；?
X, in Y, Z three-dimensional system of coordinate, the axial direction for defining test run moving frame 1 is Z-direction, and radial is X, Y-direction.Moving frame passes through four groups of counterweight-levers
Formula pretightning force device, which is suspended on, to be determined on frame, and provides the pretightning force of thrust level 22% or so.
As shown in figure 12, counterweight-lever pretightning force device 14 be existing apparatus, including pull rod 141, lever dolly 142,
One end of counterweight pull rod 144, counterweight pull rod 144 are arranged by screw thread for lever 143, counterweight pull rod 144 and counterweight 145, counterweight 145
The other end and lever 143 one end it is hinged, the other end of lever 143 and lever dolly 142 are hinged, and 142 bottom of lever dolly
Portion is equipped with through-hole, and the other end that one end of pull rod 141 passes through through-hole and lever 143 is hinged, on the other end and moving frame of pull rod 141
Ring beam 11 is connected, while lever dolly 142 is fixed at and determines on frame on ring beam 22, compact-sized to make, and determines the support of frame outer layer
The column of frame 21 is hollow structure, can be arranged counterweight 145 is directly hanging in column, and counterweight is hanging, not with determine bridge joint touching.Often
Group counterweight weight 500kg, lever dolly fulcrum is away from pull rod vertical range and lever dolly fulcrum away from counterweight pull rod vertical range
Than for 1:19.Counterweight-lever pretightning force device is amplified counterweight weight by lever ratio, and the power of amplification is loaded in test run
In frame moving frame, preload of the running support moving frame on device for measuring force is realized.
Test run determines frame 2 and includes outer layer support frame 21, determine ring beam 22 on frame, determine frame lower ring 23, determine frame floor stringer 24 and determine
Frame attachment beam 25；Determine ring beam 22 on frame and determines the inside that frame lower ring 23 is fixed at outer layer support frame 21, to determine frame floor stringer
24 are fixed at the lower section for determining frame lower ring 23, determine frame attachment beam 25 and be fixed at determine ring beam 22 on frame, determine frame lower ring
Between 23, and along the circumferential setting determined ring beam 22 on frame, determine frame lower ring 23, i.e., circumferentially determines ring beam 22 on frame, determines ring under frame
The outer surface of beam 23.
Test run moving frame 1 includes ring beam 11, moving frame lower ring 12, internal layer support frame 13 in moving frame；Ring beam 11 and dynamic in moving frame
Frame lower ring 12 is connected by internal layer support frame 13, in moving frame ring beam 11 be located at determine on frame ring beam 22 with determine frame lower ring 23 it
Between, moving frame lower ring 12, which is located at, determine the lower section of frame lower ring 23, determines ring beam 22 on frame, determines frame lower ring 23, ring beam 11 in moving frame, moves
Frame lower ring 12 is coaxially disposed.
As shown in figure 4, axial thrust measuring unit 5 is four groups, four groups of axial thrust measuring units 5 are mounted on ring in moving frame
Beam 11 and determine on frame between ring beam 22, four groups of axial thrust measuring units 5 are circumferentially uniformly distributed along 22 axis of ring beam on frame is determined, with X-axis
For 45 degree of phase angles, for measuring engine axial thrust, while reducing between axial thrust measurement and lateral thrust measurement
It influences each other.Axial thrust measuring unit 5 includes the first flexible connecting member 51, load cell 52 and pillar 53；Pillar 53
One end is connect with ring beam 22 on frame is determined, on one end of load cell 52 and moving frame ring beam 11 connect, the other end of pillar 53 with
52 other end of load cell is connected by the first flexible connecting member 51, and arrangement form is as shown in Figure 1.
As shown in figure 5, the lateral thrust measurement unit 4 of lower layer is two groups, the lateral thrust measurement unit 4 of Liang Zu lower layer mutually hangs down
Directly, and setting is being determined between frame floor stringer 24 and moving frame lower ring 12, for measuring engine lower layer lateral force, while reducing side
To influencing each other between thrust measurement and axial thrust measurement.The lateral thrust measurement unit 4 of lower layer includes the second flexible connection
Part 41 and the first bidirectional measurement sensor 42, one end of the first bidirectional measurement sensor 42, which is mounted on, determines on frame floor stringer 24, separately
One end is connect by the second flexible connecting member 41 with moving frame lower ring 12, the second flexible connecting member 41 and the first bidirectional measurement sensing
Device 42 concretely 10t flexible connecting member, 10t bidirectional propulsion measurement sensor.Specific connection type are as follows: moving frame lower ring 12
It is connected with the second flexible connecting member 41 by screw thread, the second flexible connecting member 41 passes through screw thread and the first bidirectional measurement sensor 42
It is connected, the first bidirectional measurement sensor 42, which is mounted on, to be determined on frame floor stringer 24.
As shown in Figure 6, Figure 7, the lateral thrust measurement unit 3 in upper layer be eight groups, two groups in X to being arranged in parallel, two groups in-X
To being arranged in parallel, two groups are arranged in parallel in Y-direction, and two groups are arranged in parallel in-Y-direction.The lateral setting of thrust measurement unit 3 in upper layer is fixed
On frame attachment beam 25 and moving frame between ring beam 11, for measuring engine upper layer lateral force, while reduce lateral thrust measurement with
Influencing each other between axial thrust measurement.The lateral thrust measurement unit 3 in upper layer includes pre-tightening pull rod 31, third flexible connecting member
32, the second bidirectional measurement sensor 33 and modular support frame 34；Modular support frame 34, which is fixed at, to be determined on frame attachment beam 25, in advance
It strains at bar 31 to be arranged in modular support frame 34, the one end for pre-tightening pull rod 31 is threadedly coupled with modular support frame 34, pre-tightens pull rod
31 other end is connect with the threaded one end of third flexible connecting member 32, and the other end of third flexible connecting member 32 passes through second pair
It is fixedly connected to measurement sensor 33 with ring beam 11 in moving frame.
As shown in figure 8, pre-tightening pull rod 31 includes sequentially connected first thread segment 311, nut 312 and the two the first screw threads
Section 311.The lateral thrust measurement unit 3 in upper layer can using adjustable preloads pull rod 31 realization in moving frame at 11 height of ring beam to dynamometry
The lateral pretightning force of structure application 1t.The adjustable principle for pre-tightening pull rod 31 is to rotate adjustable preload pull rod 31 by hexagon
When, it is micro- using the pretightning force under the conditions of pitch difference progress sensor Light deformation since pitch difference is 0.1mm before and after pull rod
It adjusts.
As shown in figure 9,32 structure phase of the first flexible connecting member 51, the second flexible connecting member 41 and third flexible connecting member
Together comprising cylindrical body 611, in Xr、Yr、ZrIn three-dimensional system of coordinate, the axial direction for defining cylindrical body 611 is ZrTo diameter
To for Xr、YrTo；Cylindrical body is along axial direction ZrIt is disposed with recess group I and recess group II, recess group I is in cylindrical body
XrDirection setting, recess group II is in cylindrical body YrDirection setting；Recess group I include two the first recesses 612, two first
Recess 612 is arranged about the axisymmetrical of cylindrical body；Recess group II includes two the second recesses 613, two the second recesses
The 613 axisymmetrical setting about cylindrical body.From XrDirection sees, the rectangle for being projected as quadrangle chamfering of the first recess 612,
From YrDirection sees, the rectangle for being projected as being connected and semicircle of the first recess 612, and rectangle short side is tangent with semicircle respectively；
Second recess 613 is identical as the shape of the first recess 612.(in terms of X-direction, the square for being projected as quadrangle chamfering of the first recess 612
Shape；In terms of Y-direction, the first recess 612 is projected as semicircle, and respectively there is a straight line at semicircular both ends, straight line perpendicular to X to
And Z-direction.) when can efficiently reduce three axis force measurement, respectively to the mutual interference between power, it is accurate to improve systematic survey flexible connecting member
Property.
A kind of high-thrust rocket three-dimensional force measuring method provided by the invention, specifically includes the following steps:
1. installing measuring device；
Fig. 1, Fig. 2, Fig. 3 are the structure chart of 1200kN high-thrust rocket three-dimensional force measuring device, mainly by test run
Moving frame 1, test run determine frame 2, the lateral thrust measurement unit 3 in upper layer, the lateral thrust measurement unit 4 of lower layer and axial thrust measuring unit
5 compositions, may be implemented accurately to measure axial thrust and radial thrust.
In running support moving frame ring beam 11, on moving frame lower ring 12, install side force measurement unit additional respectively, wherein upper layer side
Uniformly distributed along running support axis to power measuring unit, there are two lower layer's lateral force measuring units, is arranged in upper layer side force measurement list
Immediately below first, determine between frame floor stringer and moving frame lower ring.By engine shaft between thrust measurement sensor and support construction
120t flexible connecting member is installed additional, to eliminate the measurement production that axial thrust is excessive to cause supporting surface frictional force excessive, to lateral thrust
It is raw to influence.
2. the preparation before measurement；
2.1) before being measured to engine lateral thrust, upper layer measurement structure need to be pre-tightened, the method for preload
It is that the rotation connected on each load cell of symmetrical rotary pre-tightens pull rod, the specially lateral thrust measurement unit 3 in symmetrical rotary upper layer
Preload pull rod, be specially rotated in a clockwise direction preload pull rod (the specially opposite direction rotation X and-X of X and-X respectively
Preload pull rod), be rotated in a clockwise direction the preload pull rod (the preload pull rod of opposite direction rotation Y and-Y) of Y and-Y respectively,
Since the screw pitch that rotation pre-tightens pull rod rear and front end is respectively 2mm and 1.9mm, when rotating the screw rod, screw rod is for each revolution
The displacement difference that 0.1mm can be generated can be realized the fine tuning and load of sensor pretightning force using deformation caused by the displacement.
Pre- next, should ensure that has the pulling force of 1t on each load cell, is less than 3t due to estimating engine three axis force, respectively
Only zero-bit during bilateral transducer dynamometry, improves the precision of thrust measurement.
2.2) influence of the propellant pipeline blind flange force to thrust measurement in pressurization is eliminated.In commissioning process, propellant
After supply line pressurization, since the presence of pipeline bellows 6 can generate blind flange force, the direction of blind flange force and the side of motor power
To as shown in figure 11, in order to eliminate influence of the blind flange force to thrust measurement, after being pressurized in advance to Propellant Supply pipeline,
Remember the mode of zero-bit again to sensor, eliminates influence of the blind flange force to thrust measurement.If do not remembered zero-bit to sensor, then surveyed
The measured value F of the motor power of amountMAre as follows:
FM=FT-(Ff+FN)
Wherein, kerosene pipeline blind flange force Ff, liquid oxygen pipeline blind flange force FN, engine actual thrust FT；
Propellant Supply pipeline is pressurized using the process gas on test bay, is required when pressurization value is with engine test
Pressure value it is identical, after pressurization, record each sensor reading, and the initial reading subtracts by each sensor during the test
It goes, eliminates influence of the Propellant Supply pipeline blind flange force to lateral thrust measurement, propellant can effectively eliminate using this method
Influence of the pipeline blind flange force to thrust measurement improves the accuracy that engine is respectively measured to power.
Step 2.2) can also carry out before step 2.1).
3) engine three axis force measurement model is established；
3.1) three axis force measurement as shown in Figure 10, is carried out using the force snesor of 14 omnidirectional distributions, X and Y-direction arrangement pass
Sensor X1、X2、X3、X4、X5And Y1、Y2、Y3、Y4、Y5, it is respectively used to measurement X and Y-direction component, Z-direction arranges force snesor Z1、Z2、
Z3、Z4, for measuring Z-direction thrust；
Axial main thrust (Z-direction) measurement:
The measurement of engine axial thrust 4 sensors used by the measurement of test bay axial thrust, Z1、Z2、Z3、Z4
The power output of this four groups of sensors is Fz1、Fz2、Fz3、Fz4, due to being pre-tightened by running support moving frame weight, engine weight, running support
Above four groups of sensor registrations are remembered 0 before engine ignition by the influence of power and loine pressure etc., to eliminate pretightning force and
Influence of the gravity to thrust measurement, axial main thrust can theoretically be calculated by following formula:
Fz=A (FZ1+FZ2+FZ3+FZ4) (1)
Coefficient A is the influence coefficient that three axis force measures that elastic constraint used measures main thrust in formula, can pass through scene
Calibration method measures；
Field calibration method is existing method, and specific visible [1] Zhang Xuecheng, Jing Fenglin appoint quick equal rocket engine thrust
Automatic calibration [J] aerospace measurement technology .1998 in situ of measurement, 18 (2): 60-64. Zhu Qing, Xu Jianyang .CS-01 HIGHER ALTITUDE TEST FACILITY pushes away
Power measurement and the test of calibrating installation development [J] gas turbine and research .2002,15 (3): 38-42.
The specific method of field calibration is that four standard force snesors are connected in Thrust Measuring System, utilize four
The identical hydraulic cylinder of output force value in parallel exerts a force to standard force snesor respectively, and is passed the power by standard force snesor
Running support moving frame is passed, which is measured by thrust measurement sensor, at this point, the power that four standard force snesors measure
The sum of value is FMark, the sum of force value that four load cells measure is FIt surveys, coefficient A is calculate by the following formula:
A=FMark/FIt surveys
The measurement of engine lateral thrust:
The direction of engine lateral thrust and the direction of main thrust are spatially mutually orthogonal relationship, and measurement structure is total
It is divided into two layers, three axis force measurement structure cooperates two-direction pull press by 8 preload force loading devices, 2t flexible connecting member at the middle and upper levels
The mode of sensor series realizes, is loaded with the prefastening force of 1t on each sensor, each X to the output force value of sensor be FX1、
FX2、FX3、FX4；The output force value of each Y-direction sensor is FY1、FY2、FY3、FY4。
Lower layer's three axis force measurement structure by the tension compression bidirectional sensor of two Orthogonally arrangements cooperate 10t flexible connecting member into
The measurement of row three axis force.Tension compression bidirectional sensor is connect by flex link with moving frame, X to the output force value of sensor be FX5；
The output force value of each Y-direction sensor is FY5。
In the three axis force measurement structure of upper layer, lateral thrust sensors X1、X2、X3、X4、Y1、Y2、Y3、Y4It is respectively arranged in former bullet
The neutral gear of spring plate hold-down support two sides, in moving frame at collar tie beam height, X5And Y5It is respectively arranged in X1、X2Underface, ring under moving frame
At depth of beam, installation site is as shown in Figure 1, 2.
The calculation method of theoretical lateral thrust is, X is to force snesor X1、X2、X3、X4、X5Power output be FX1、FX2、FX3、
FX4、FX5, engine X can be denoted as F to thrustX, then:
FX=FX1+FX2+FX3+FX4+FX5 (2)
Y-direction force snesor Y1、Y2、Y3、Y4、Y5Power output be FY1、FY2、FY3、FY4、FY5, engine Y-direction thrust can be denoted as
FY, then:
FY=FY1+FY2+FY3+FY4+FY5 (3)
3.2) amendment of motor power calculated with actual values formula
Power source device is set in engine jet pipe position, which can generate the lateral thrust of certain orientation in the position
And axial thrust, apply the thrust magnitude of different directions and size in power source position, and be recorded in the corresponding measured value of each sensor,
Under the conditions of can get multiple groups difference thrust, the data sample of each measurement value sensor, using the data sample to engine reality
Each correction factor a, b in thrust computing formula1、b2、c1、c2It is fitted.
Multiple groups FX′、FY′、FZUnder conditions of ' input, each sensor output value F is obtainedX1′、FX2′、FX3′、FX4′、FX5′、
FY1′、FY2′、FY3′、FY4′、FY5′、Fz1′、Fz2′、Fz3′、Fz4', by multiple groups FX′、FY′、FZ' and the input of each sensor output value
Correction formula, and each correction factor a, b are determined by parameter fitting1、b2、c1、c2；
It is simulated in engine jet pipe position and applies engine main thrust and three axis force, by running support practical structures and respectively to survey
The influence that amount structure intercouples, motor power calculated with actual values formula need to be modified, and correction formula is as follows:
In the above semiempirical formula, engine is mainly considered respectively to the mutual interference relationship of power, wherein coefficient a is X, Y-direction
The rigidity of lateral force constraint original part, the influence coefficient to Z-direction axial thrust；Coefficient b1For engine shaft to constraint original part it is rigid
Property, to the influence coefficient of lateral force Fx measurement；Coefficient b2For the lateral force constraint original part rigidity of Y-direction, lateral force Fx is measured
Influence coefficient；Coefficient c1For engine shaft to constraint original part rigidity, to the influence coefficient of lateral force Fz measurement；Coefficient c2For the side Y
To lateral force constraint original part rigidity, to the influence coefficient of lateral force Fx measurement.
3.3) measurement of engine lateral thrust:
During engine ignition, by established three-dimensional force measuring device, each measurement sensor can be obtained and read
Number FX1、FX2、FX3、FX4、Fx5、FY1、FY2、FY3、FY4、FY5、FZ1、FZ2、FZ3、FZ4, and carry it into motor power actual value meter
Formula is calculated, it is final to determine three-dimensional force value size FX、FY、FZ。
Claims (10)
1. a kind of high-thrust rocket three-dimensional force measuring device, including frame (2) is determined in test run moving frame (1) and test run, test run is moved
Frame (1), which is mounted on test run by four groups of counterweights-lever pretightning force device, to be determined on frame (2), it is characterised in that: further includes upper layer side
To thrust measurement unit (3), the lateral thrust measurement unit (4) of lower layer and axial thrust measuring unit (5)；It is sat in X, Y, Z three-dimensional
In mark system, the axial direction for defining test run moving frame (1) is Z-direction, and radial is X, Y-direction；
The test run determines frame (2) and includes outer layer support frame (21), determine ring beam on frame (22), determine frame lower ring (23), determine frame auxiliary
Beam (24) and determine frame attachment beam (25)；It is described to determine ring beam on frame (22) and determine frame lower ring (23) to be fixed at outer layer support frame
(21) inside, it is described to determine frame floor stringer (24) and be fixed at the lower section for determining frame lower ring (23), it is described to determine frame attachment beam
(25) it is fixed at and determines ring beam on frame (22), determines between frame lower ring (23), and along determining ring beam on frame (22), determine frame lower ring
(23) circumferential setting；
The test run moving frame (1) includes ring beam in moving frame (11), moving frame lower ring (12), internal layer support frame (13)；The moving frame
Upper ring beam (11) and moving frame lower ring (12) are connected by internal layer support frame (13), and ring beam (11) is located at and determines on frame in the moving frame
Ring beam (22) and determine between frame lower ring (23), the moving frame lower ring (12), which is located at, determine frame lower ring (23) lower section；
It is described to determine ring beam on frame (22), determine that frame lower ring (23), ring beam (11), moving frame lower ring (12) are coaxially set in moving frame
It sets；
The axial thrust measuring unit (5) is four groups, and four groups of axial thrust measuring units (5) are mounted on ring beam in moving frame (11)
With determine between ring beam on frame (22), and it is uniformly distributed along the circumferential direction for determining ring beam on frame (22), for measuring engine axial thrust；
The lateral thrust measurement unit (4) of lower layer is two groups, and the lateral thrust measurement unit (4) of Liang Zu lower layer is mutually perpendicular to set
It sets, and is mounted on and determines between frame floor stringer (24) and moving frame lower ring (12), for measuring engine lower layer lateral force；
The lateral thrust measurement unit (3) in upper layer is eight groups, two groups in X to being arranged in parallel, two groups in-X to being arranged in parallel, two
Group is arranged in parallel in Y-direction, and two groups are arranged in parallel in-Y-direction；
The lateral thrust measurement unit (3) in upper layer is arranged on determining frame attachment beam (25) and moving frame between ring beam (11), described
The lateral thrust measurement unit (3) in upper layer includes pre-tightening pull rod (31), third flexible connecting member (32), the second bidirectional measurement sensor
(33) and modular support frame (34)；The modular support frame (34), which is fixed at, determines on frame attachment beam (25), described pre- to strain at
In modular support frame (34), the one end for pre-tightening pull rod (31) is threadedly coupled with modular support frame (34) for bar (31) setting, is pre-tightened
The other end of pull rod (31) is connect with the threaded one end of third flexible connecting member (32), the other end of third flexible connecting member (32)
It is fixedly connected by the second bidirectional measurement sensor (33) with ring beam in moving frame (11).
2. high-thrust rocket three-dimensional force measuring device according to claim 1, it is characterised in that: the axial direction pushes away
Power measuring unit (5) includes the first flexible connecting member (51), load cell (52) and pillar (53)；The one of the pillar (53)
End with determine ring beam on frame (22) and connect, ring beam (11) connection, the pillar on one end of the load cell (52) and moving frame
(53) the other end is connect with load cell (52) other end by the first flexible connecting member (51).
3. high-thrust rocket three-dimensional force measuring device according to claim 2, it is characterised in that: the lower layer side
It include the second flexible connecting member (41) and the first bidirectional measurement sensor (42) to thrust measurement unit (4), described first is two-way
One end of measurement sensor (42), which is mounted on, determines on frame floor stringer (24), and the other end passes through the second flexible connecting member (41) and moving frame
Lower ring (12) connection.
4. high-thrust rocket three-dimensional force measuring device according to claim 3, it is characterised in that: described first is soft
Property connector (51), the second flexible connecting member (41) are identical with third flexible connecting member (32) structure, including cylindrical body
(611), in Xr、Yr、ZrIn three-dimensional system of coordinate, the axial direction for defining cylindrical body (611) is ZrTo radial is Xr、YrTo；
The cylindrical body (611) is along axial ZrIt is disposed with recess group I and recess group II, the recess group I is cylindric
Ontology XrDirection setting, the recess group II is in cylindrical body YrDirection setting；The recess group I includes two the first recesses
(612), two the first recesses (612) are arranged about the axisymmetrical of cylindrical body (611)；The recess group II includes two
Second recess (613), two the second recesses (613) are arranged about the axisymmetrical of cylindrical body (611).
5. high-thrust rocket three-dimensional force measuring device according to claim 4, it is characterised in that: from XrDirection sees,
The rectangle for being projected as quadrangle chamfering of first recess (612), from YrDirection sees that the first recess (612) are projected as
The rectangle and semicircle being connected, the rectangle short side are tangent with semicircle respectively；
Second recess (613) is identical as the shape of the first recess (612).
6. high-thrust rocket three-dimensional force measuring device according to any one of claims 1 to 5, it is characterised in that: institute
Stating and pre-tightening pull rod (31) includes sequentially connected first thread segment (311), nut (312) and the second thread segment (313), and described the
One thread segment (311) is identical with the rotation direction of the second thread segment (313), screw pitch is different.
7. high-thrust rocket three-dimensional force measuring device according to claim 6, it is characterised in that: first spiral shell
The pitch difference of line section (311) and the second thread segment (313) is 0.1mm.
8. the three axis force measurement side based on any high-thrust rocket three-dimensional force measuring device of claim 1 to 7
Method, which comprises the following steps:
1) three axis force measurement model is established；
Rocket engine three axis force measurement model is established, X and Y-direction arrange bidirectional measurement sensors X1、X2、X3、X4、X5And Y1、Y2、
Y3、Y4、Y5, be respectively used to measurement X to Y-direction component, Z-direction arrange unidirectional force sensor Z1、Z2、Z3、Z4, pushed away for measuring Z-direction
Power；
2) acquisition of correction factor；
2.1) simulation applies engine main thrust and three axis force, using measuring device, applies different directions, different size of power,
Obtain the measured value size of each sensor in measuring device；
2.2) input multiple groups simulate three axis force FX′、FY′、FZ', obtain each sensor output value FX1′、FX2′、FX3′、FX4′、FX5′、
FY1′、FY2′、FY3′、FY4′、FY5′、Fz1′、Fz2′、Fz3′、Fz4', by multiple groups FX′、FY′、FZ' and the input of each sensor output value
Correction formula, and each correction factor a, b are determined by parameter fitting1、b2、c1、c2；
Correction formula are as follows:
3) three axis force measures；
During engine ignition, by established three-dimensional force measuring device, each measurement sensor reading F is obtainedX1、FX2、
FX3、FX4、Fx5、FY1、FY2、FY3、FY4、FY5、FZ1、FZ2、FZ3、FZ4, each measurement sensor is read and is repaired by engine three axis force
Positive formula amendment, obtains the three-dimensional force value size F of actual measurementX、FY、FZ。
9. high-thrust rocket three-dimensional force measuring method according to claim 8, which is characterized in that before step 1)
Further include pre-tightening step: the preload pull rod of the lateral thrust measurement unit in symmetrical rotary upper layer, specially opposite direction rotate X and-X
Preload pull rod, opposite direction rotate Y and-Y preload pull rod, realization sensor pretightning force load.
10. high-thrust rocket three-dimensional force measuring method according to claim 8, which is characterized in that step 1) it
Before further include pressure increase step: Propellant Supply pipeline is pressurized, pressurization value is identical as engine test required pressure value,
After pressurization, each sensor initial reading is recorded, and the initial reading subtracts by each sensor in measurement process, elimination pushes away
Influence into agent supply line blind flange force to lateral thrust measurement.
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