CN107202660B - 4-25N attitude control engine thermal vacuum environment stable state thrust calibration measuring device - Google Patents
4-25N attitude control engine thermal vacuum environment stable state thrust calibration measuring device Download PDFInfo
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- CN107202660B CN107202660B CN201710418844.1A CN201710418844A CN107202660B CN 107202660 B CN107202660 B CN 107202660B CN 201710418844 A CN201710418844 A CN 201710418844A CN 107202660 B CN107202660 B CN 107202660B
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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
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L25/00—Testing or calibrating of apparatus for measuring force, torque, work, mechanical power, or mechanical efficiency
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Abstract
The present invention relates to 4-25N attitude control engine thermal vacuum environment stable state thrust calibration measuring devices.The device includes pedestal adapter frame, damping block, determines frame, balance pinboard, one-component balance measuring device, propellant pipeline, propellant fixing device for pipe and calibrated in situ device；Pedestal adapter frame and determine that multiple damping blocks are installed between frame, and multiple damping blocks are arranged side by side；Determine frame periphery and be fixedly installed with multiple propellant fixing device for pipe, propellant pipeline is installed by propellant fixing device for pipe, and propellant pipeline one end is connected to external propellant supply system, and the other end is connected to attitude control engine propellant entrance to be measured；One-component balance measuring device is mounted on the one end for determining frame by balance pinboard, and calibrated in situ device is mounted on the other end for determining frame；Present invention accomplishes the requirement of 4-25N attitude control engine low thrust calibration measurement, it is more to solve the uncertainty introduced in measurement process due to pipeline constraint, high temperature, vibration, and is not suitable for calibrating before test run, the problems such as calibration accuracy is poor.
Description
Technical field
The present invention relates to the tests of space flight liquid engine, and in particular to 4-25N attitude control engine thermal vacuum environment stable state pushes away
Power calibrating measuring device.
Background technique
Liquid-propellant rocket engine has many unique advantages, still as presently the most mature one of propulsion system
It is main force's propulsion system that various countries make great efforts development, and all achieves many achievements in terms of high thrust and low thrust, at present beauty
Leading world still in terms of most of propulsion systems, state, it is Russian then continue keep liquid promote especially high thrust liquid fire
Leading position in terms of arrow, European Union and Japan are in the technical level for pursuing the U.S., using China as the third world countries of representative
Start to promote field to compete with tradition power in liquid.
Rocket engine is a part of rocket propulsion system.Propulsion system be by engine (solid, liquid, punching press, attitude control),
The composition such as pressure charging system, tank equipment and related equipment.No matter high thrust liquid-propellant rocket engine or low thrust liquid rocket
Engine can be described as propulsion system as long as pressure charging system, tank, propellant feed system and engine are connected together.It is more
The high thrust liquid-propellant rocket engine research institute of Nian Lai, China only develop and deliver engine, and are engaged in attitude control engine
Research institute, will not only develop Attitude rocket engine, also deliver including tank, gas cylinder and containing whole including pressure charging system
A propulsion system.
Definition about low thrust liquid-propellant rocket engine has different sayings, generally will be small in China's document and publication
Thrust is divided between 0.02-2000N (0.002-200 kilograms).A Liemasuofu is in its works " rocket engine principle "
Thrust is included into thrustor from the liquid-propellant rocket engine of 0.01-1600N in one book.No matter delivery, guided missile, satellite,
Using the engine of which kind of purposes (propellant is sunk to the bottom, end speed is corrected, orbital exponent, position holding, gesture stability etc.) on airship,
Belong to the scope of thrustor.
It is abundant with space tasks, low thrust, high specific impulse propeller more and more applied, and complete such
The thrust test of the research of the ground experiment characteristic of propulsion device, low amounts grade is the key technology that must be broken through.
The country has scholar to measure existing technological difficulties for low thrust, proposes according to the thrust pickup of application not
Together, piezoelectric transducer and strain gauge transducer two schemes can be used in testboard bay:
It is that dynamic characteristic is good using the advantages of piezoelectric transducer, high rigidity, the influence of propellant pipeline is small, the disadvantage is that
Static accuracy is lower, not can be carried out long-time stable measurement to small value force, high internal resistance is anti-, and electrical interference performance is poor, installation pretightening force
And wet temp influences greatly；
It is stable state accuracy height using the advantages of strain gauge transducer, low internal resistance output, anti-electrical interference performance is good, disadvantage
It is poor dynamic, needs subsequent additional treatments, propellant pipeline stiffness effect is big, and operating temperature range is relatively narrow.
Disclosed in measuring technology journal .Vol.18 Supp.2004 one it is entitled " realize micro-ox level dynamic thrust test
Method and experimental study " a kind of test method [8] of micro-ox level is proposed, basic thought is that micro-ox level thrust is passed through cantilever
Beam is converted into micron order displacement, then tests the micro-displacement by micro-displacement sensor, obtains microthrust size.It tests thrust
Up to 2 μ N or so.
In addition, disclosed in aerospace journal [J] .Vol.29.No 2, March 2,008 one it is entitled " micro- under vacuum environment to push away
Power surveys quantifier elimination " measurement method of microthrust under vacuum environment is proposed, the amplification principle using lever force is proposed, will be pushed away
Force value is amplified so as to accurately be detected by sensor.
But can exist when if applying to the measurement of 4-25N magnitude low thrust using above two traditional measurement method as follows
Problem:
(1) thrust moving frame and determine the influence of the supporting element, attaching means (spring leaf) between frame.
(2) influence of propellant pipeline arrangement and propellant pipeline inner pressure and fluid momentum.
(3) propulsion in pipeline, thrust chamber head, jet pipe cooling jacket during heat run, after engine main valve
The variation of the ablation amount of agent loading and ablation jet pipe, can cause the variation of engine gravity, therefore will affect thrust measurement
Accuracy.
(4) low-thrust rocket quality itself and thrust are smaller, are easy in test non-linear and all by horse structure
The influence in collarette border, while engine body temperature in heat run is higher, has not to component connected to it and sensor etc.
Uniform heat conduction and heat radiation can bring structural nonlinear and Sensor temperature drift etc. to adversely affect, and high temperature can introduce biggish
Uncertainty of measurement.This requires racks and sensor to have good dynamic characteristic, higher static accuracy, anti-interference ability
By force, while it being able to carry out long-time stable measurement, but general voltage-type and strain gauge transducer application characteristic are stronger, are difficult same
When meet requirements above.
It (5) is the mechanical equipments such as a large amount of mechanical pumps of vacuum degree needed for guarantee test run, ejection system inevitably to survey
Amount process has some impact on, and vibration can introduce corresponding uncertainty of measurement.
According to 4-25N attitude control engine thermal vacuum environment stable state thrust measurement technical requirements, use at present as shown in Figure 1
Device realize low thrust measurement, specifically engine 003 is directly hung on sensor, engine is born by engine
Weight, then carries out thrust measurement, and sensor uses spoke type elastic element 001, is pasted with foil gauge on elastic element 001
002, as shown in Figure 1, but currently used device has the following problems:
(1) during 4-25N attitude control engine stable state thrust measurement, engine, which is horizontally mounted, to be fixed on sensor,
Under the weight effect of engine, the effect of sensor bending moment can generate certain deformation in vertical direction, in heat run process
In the engine quality due to caused by thrust chamber ablation variation to sensor will also result in measurement interference, and these influence before examination
It can not carry out accurate Theory and calculate analysis, these states are different from laboratory's calibration environment；
(2) during 4-25N attitude control engine stable state thrust measurement, atmospheric pressure, environment temperature and laboratory are calibrated
Environment is different, its precision reduces when application test room calibration factor being caused to calculate motor power；
(3) during thrust measurement, the installation of Propellant Supply pipeline there are pipeline constraint, will necessarily generate it is certain just
Beginning force value needs to repeat installation pipeline when carrying out test of many times, this causes initial force value also incomplete in each test process
Identical, these states can not also be simulated in laboratory；
(4) during engine thermal test run, Propellant Supply pipeline can generate one with the thrust variation of engine
Setting becomes, to generate extra binding, this results in the thrust transmission efficiency of engine to reduce, therefore, by balance sensor
The force value measured is less than the true thrust of engine.
There is also defect, current calibrating mode is mostly manual calibration for the calibration of current measuring system simultaneously, i.e., by pair
High-precision standard force snesor suspension counterweight carries out proof force load, and power to be loaded is remembered after stablizing by Pacific Ocean acquisition system
Measuring force and proof force are recorded, to measure system calibration, this mode is suitble to be calibrated before test run, not only time-consuming consumption
Power, calibration accuracy are also not high enough.
Summary of the invention
In order to realize 4-25N attitude control engine low thrust calibration measurement requirement, pipeline constraint, height in measurement process are solved
The uncertainty that temperature, vibration introduce is more, and be not suitable for before test run calibration, the problems such as calibration accuracy is poor, proposes a kind of 4-25N
Attitude control engine thermal vacuum environment stable state thrust calibration measuring device.
Basic functional principle of the invention:
Power source controls computer and drives servomechanism to drive electric cylinder by PLC controller according to the calibration procedure set
Proof force load is applied to standard force snesor, and by load function of wire in one-component balance measuring device, while should
Standard force value is transferred to data acquisition unit；Under this force, the voltage signal exported in one-component balance measuring device
It is acquired by data acquisition unit, returns to power source control computer through bus.Power source control computer stores calibration process in real time
The practical force value that Plays power source and one-component balance measuring device are exported in each calibration gear, then by data processing, obtain
Take the calibration factor of one-component balance measuring device.
The specific technical solution of the present invention is:
The present invention provides a kind of 4-25N attitude control engine thermal vacuum environment stable state thrust calibration measuring devices, including base
Seat adapter frame, damping block are determined frame, balance pinboard, one-component balance measuring device, propellant pipeline, propellant pipeline and are fixed
Device and calibrated in situ device；
Pedestal adapter frame and determine that multiple damping blocks are installed between frame, and multiple damping blocks are arranged side by side；Determine frame periphery to fix
Multiple propellant fixing device for pipe are installed, propellant pipeline is installed by propellant fixing device for pipe, propellant pipeline
One end is connected to external propellant supply system, and the other end is connected to attitude control engine propellant entrance to be measured；Single component day
Flat measuring device is mounted on the one end for determining frame by balance pinboard, and calibrated in situ device is mounted on the other end for determining frame；
One-component balance measuring device includes balance bracket, balance weight assembly and balance safety protection bracket；
Balance bracket includes vertical beam and horizontal strain beam；Attitude control engine to be measured is installed at the top of vertical beam, to
The thrust direction of attitude control engine is measured perpendicular to vertical beam；Balance weight assembly is mounted in the middle part of vertical beam；The bottom of vertical beam with
Horizontal strain beam upper surface is connected, and the lower end surface of horizontal strain beam is provided with front end gusset, intermediate gusset and rear end gusset；Water
Flat strain beam is passed through front end gusset, intermediate gusset respectively and is fixedly connected with, rear end gusset with balance pinboard；On horizontal strain beam
Foil gauge is covered with by full-bridge mode；
Balance weight assembly includes balanced lever and clump weight；Balanced lever is perpendicular in the middle part of vertical beam, balanced lever packet
Include fixing end and free end；Fixing end is to opening up strip hole between free end；It is fixedly connected in the middle part of fixing end and vertical beam, counterweight
Block is fixed on strip hole by bolt and nut；
Balance safety device includes balance safety protection bracket and stop screw；The one of balance safety protection bracket
End is fixedly mounted on and determines on frame, and the other end is provided with two pieces of parallel fixed plates, in the middle part of vertical beam between two fixed plates,
The distance between two fixed plates are greater than the thickness in the middle part of vertical beam, and stop screw is installed in one of fixed plate, limit spiral shell
The thread segment of nail passes through the fixed plate and contacts with the vertical beam；
Calibrated in situ device includes standard force source, standard force source control system and L-type support；
The bottom of L-type support is fixedly connected with frame is determined；Attitude control to be measured is installed with the vertical beam at the top of L-type support to start
Machine contour position is installed by standard force source；Standard force source includes electric cylinder, mounting flange, adapting rod, standard force snesor, switching
Ring and load steel wire；
Electric cylinder is vertically fixedly installed in L-type support by mounting flange, the output end of electric cylinder by adapting rod with
The connection of standard force snesor；The output end of standard force snesor installs adapter ring；Load steel wire one end is connect with adapter ring, another
End is connect with the central axes of attitude control engine to be measured；
Standard force source control system include power source control computer, bus, data acquisition unit, servo-driver and
PLC controller；
Power source controls computer transmission objectives force value to PLC controller, and PLC controller passes through described in servo-driver control
Electric cylinder movement, the practical force value that electric cylinder movement generates act in one-component balance measuring device and by data acquisition unit
Power source is returned by bus transfer after reception and controls computer；Power source control computer compares practical force value and standard force value
Compared with the calibration factor of acquisition one-component balance measuring device.
One-component balance measuring device further includes balance active thermostat；Balance active thermostat includes being fixedly mounted
Water-cooling jacket structure on determining frame and positioned at vertical beam two sides；What water-cooling jacket structure composition one was isolated with free surrounding space
Cavity；Horizontal strain beam position is in the cavity；
The side wall of water-cooling jacket structure is hollow mechanism, is equipped with the first water supply connector in water-cooling jacket structure and goes out with first
Water swivel；First water supply connector is arranged close to water-cooling jacket structure bottom, and the first water outlet connector is close to water-cooling jacket structure upper
Setting.
Calibrated in situ device further includes the cylindrical housings being fixedly mounted in L-type support, and standard force snesor is located at circle
In cylindrical shell；The outer wall of cylindrical housings is hollow structure, be equipped on the outer wall of cylindrical housings the second water supply connector with
Second water outlet connector；Second water supply connector is arranged close to cylindrical housings central lower, and the second water outlet connector is close to circular cylindrical shell
The setting of body central upper.
Specifically, above-mentioned to determine frame upper surface and be provided with equidistant multiple T-slots, balance pinboard is along the multiple T-type
U-type groove is offered in slot orientation；The center of adjacent T-slot is away from the relational expression with the length of U-type groove satisfaction are as follows: Lu >=2Lt,
Wherein, U-type groove length is Lu, and adjacent T-slot center is away from for Lt.
Specifically, propellant fixing device for pipe be include lower bracket and front band, the bottom surface of the lower bracket
Threaded hole is offered, the upper end of lower bracket is lower catch hoop compatible with the front band.
It is respectively provided between attitude control engine to be measured between above-mentioned horizontal strain beam and balance pinboard, at the top of vertical beam
Vacuum insulation panel.
Relationship is as follows between maximum strain ε and attitude control engine thrust F to be measured on above-mentioned horizontal strain beam:
Wherein, A is horizontal strain beam cross-sectional area, and E is the elasticity modulus of horizontal strain beam, WzIt is cut for the bending resistance of vertical beam
Face coefficient, y are engine to be measured between the position that the installation site of vertical beam intersects to vertical beam with horizontal strain beam
Vertical height；
Above-mentioned calibrated in situ device further includes the electric cylinder protective cover being fixed in L-type support, and electric cylinder is located at electronic guarantor
In shield.
Above-mentioned damping block is 6 BE-40 dampers, and intrinsic frequency is less than 15Hz.
The material of above-mentioned propellant pipeline is 1Cr18Ni9Ti, is arranged using " Z " type structure.
Advantage for present invention:
1, present invention employs one-component balance devices, and are equipped with damper and propellant fixing device for pipe, solve
The problems such as uncertainty introduced when attitude control engine thrust measurement due to pipeline constraint, vibration is more, calibrated in situ can be with mould
Static demarcating and the check of measuring system are completed in quasi- actual condition, scene, and the automatic in-situ calibrating installation in the present apparatus is compared to biography
It unites for calibrating mode, thrust calibration can be carried out with remote auto, to demarcate before realizing test run, in test run, after test run, together
When by computer record standard force value and measurement force value simultaneously, stated accuracy is higher, closer to actual condition.
2, one-component balance dress of the present invention centers balance weight assembly, can be in examination forward horizontal stand due to caused by engine suspension
Amount of unbalance, while design has balance safety device, it is ensured that balance will not overload under the conditions of maloperation, and protection passes
Sensor measurement accuracy.
3, the present invention uses balance active thermostat and power source active thermostat, makes foil gauge and standard force snesor
It is in constant suitable temperature environment always during heat run, solves horizontal strain beam Zona transformans under thermal vacuum environment
The foil gauge and proof force sensor accuracy class come reduces, the problem of zero drift.
4, the balance pinboard setting U-type groove that the present invention uses, is in after guarantee balance bracket installation and determines frame intermediate symmetry
Face position determines to open up T-slot on frame, and (U-type groove length) Lu >=2Lt (adjacent T-slot center away from), and balance branch may be implemented
Frame moving in stepless way is fixed, and the installation of different model engine is facilitated to fix.
5, between horizontal strain beam and balance pinboard of the invention, at the top of vertical beam between attitude control engine to be measured
It is respectively provided with vacuum insulation panel, vacuum insulation panel is combined by filling core material and vacuum protection surface layer, can effectively avoid air pair
Heat transmitting, thermal coefficient caused by stream can be greatly lowered, conduct so as to avoid engine gas heat during heat run
To foil gauge, causes foil gauge precision to reduce and even damage.
6, damping block of the invention is 6 BE-40 dampers, and intrinsic frequency is less than 15Hz, and each vibration isolation block can carry
40kg, vibration isolation block are placed in basic connecting plate and determine between frame, reduce the extraneous vibration passed over by vacuum chamber basis.
7, the arrangement of propellant pipeline of the invention uses " Z " type structure, guarantees that intake section is vertical with engine axis,
Entrance rigidity is reduced, reduces pipeline constraint, further increases the measurement accuracy of one-component balance.
Detailed description of the invention
The structure diagram of the existing measuring device of Fig. 1；
Fig. 2 is three-dimensional structure sketch of the invention；
Fig. 3 is structure diagram of the invention；
Fig. 4 is the structure diagram of one-component balance measuring device；
Fig. 5 is the structure diagram of standard force source；
Fig. 6 is the cross-sectional view of balance active thermostat
Fig. 7 is the main view for determining frame；
Fig. 8 is the A of Fig. 7 to cross-sectional view；
Fig. 9 is the main view of propellant fixing device for pipe；
Figure 10 is the side view of propellant fixing device for pipe；
Figure 11 present invention uses one-component balance lever principle schematic diagram；
Figure 12 is the schematic diagram of standard force source control system.
Appended drawing reference is as follows:
1- pedestal adapter frame, 2- damping block, 3- determine frame, 4- balance pinboard, 5- one-component balance measuring device, 51- days
Flat bracket, 511- vertical beam, 512- horizontal strain beam, the front end 5121- gusset, gusset among 5122-, the rear end 5123- gusset,
52- balance weight assembly, 521- balanced lever, 522- clump weight, 53- balance safety device, 531- balance safety protection bracket,
532- stop screw, 6- propellant pipeline, 7- propellant fixing device for pipe, 71- lower bracket, blocks on 72- at 533- fixed plate
Hoop, 73- threaded hole, 74- lower catch hoop, 8- calibrated in situ device, 81- standard force source, 811- electric cylinder, 812- mounting flange,
813- adapting rod, 814- standard force snesor, 815- adapter ring, 816- load steel wire, 83-L type bracket, 84- cylindrical housings,
The second water supply connector of 841-, the second water outlet connector of 842-, 85- electric cylinder protective cover, 9- attitude control engine to be measured, 10- strain
Piece, 11- balance active thermostat, 111- water-cooling jacket structure, the first water supply connector of 112-, the first water outlet connector of 113-.
Specific embodiment
Thrust calibration measuring device proposed by the present invention includes pedestal adapter frame 1, damping block 2, determines frame 3, balance pinboard
4, one-component balance measuring device 5, propellant pipeline 6, propellant fixing device for pipe 7 and calibrated in situ device 8；
The concrete function of above several components is:
Pedestal adapter frame 1 is used for and vacuum chamber basis is docked, and docking location is provided with U-shaped hole, is easily installed position tune
Section, material selection carbon steel, structure use hollow design, under the premise of being proof strength and rigidity, reduce its quality, Vacancy
Meter is installed in carrying minimum position, basic connecting plate upper surface is provided with damping block connection screw thread blind hole, uses bolt with damping block
Connection.
Frame 3 and balance pinboard 4 are determined for installing one-component balance measuring device, propellant fixing device for pipe, are realized
The axial thrust measurement that the 4-25N attitude control engine course of work generates is used for and supports each component, and related active force is transmitted
To test bay basis.
Damping block 2 uses 6 dampers using BE-40 damper, design, and each damper can carry 40kg, every
Vibration block is placed in basic connecting plate and determines between frame, reduces the extraneous vibration passed over by vacuum chamber basis.
One-component balance measuring device 5 realizes the measurement of attitude control engine low thrust, converts voltage signal for thrust input
Output, after being computed, can obtain attitude control engine axial thrust to be measured.
Propellant pipeline 6 is used to provide propellant to attitude control engine to be measured.
Propellant fixing device for pipe 7 be used for propellant pipeline is neat, rationally, be reliably mounted at and determine frame.
Calibrated in situ device 8 calibrates one-component balance measuring device for providing standard force source, obtains calibration system
Number.
Invention is further explained with reference to the accompanying drawing:
As shown in Figures 2 and 3, pedestal adapter frame 1 and determine that multiple damping blocks 2 are installed between frame 3, and multiple damping blocks 2 are simultaneously
Row's setting；；Determine 3 periphery of frame and be fixedly installed with multiple propellant fixing device for pipe 6, propellant pipeline 5 passes through propellant pipeline 6
Fixed device installation, 5 one end of propellant pipeline are connected to external propellant supply system, the other end and attitude control engine to be measured
The connection of 9 propellant entrances；One-component balance measuring device 5 is mounted on the one end for determining frame 3, calibrated in situ by balance pinboard 4
Device 8 is mounted on the other end for determining frame 3；
As shown in figure 4, one-component balance measuring device 5 includes that balance bracket 51, balance weight assembly 52 and balance are anti-safely
Protection unit 53；
Balance bracket 51 includes vertical beam 511 and horizontal strain beam 512；The top of vertical beam 511 is installed by appearance to be measured
Engine 9 is controlled, the thrust direction of attitude control engine 9 to be measured is perpendicular to vertical beam 511；Balance weight assembly 52 is mounted on vertical beam
511 middle parts；The bottom and 512 upper surface of horizontal strain beam of vertical beam 511 are connected, and the lower end surface of horizontal strain beam 512 is provided with
Front end gusset, intermediate gusset and rear end gusset；Horizontal strain beam passes through front end gusset, intermediate gusset respectively with, rear end gusset
It is fixedly connected with balance pinboard 4；Foil gauge 10 is covered with by full-bridge mode on horizontal strain beam 512；
As shown in FIG. 7 and 8,3 material of frame selection 1Cr18Ni9Ti is determined, for realizing 5 grade portions of one-component balance measuring device
The connection of part, surface is provided with equidistant T-slot, and is provided with high-precision positioning hole, accurately installs for one-component balance；It
For flat turn fishplate bar 4 for realizing one-component balance measuring device 5 and the flexible connection for determining frame 3, connection type is to be bolted, and is turned
It is provided with U-type groove and corresponding high-precision positioning hole on fishplate bar, guarantees after installing in frame intermediate symmetry face position is determined, if U-type groove
Length is Lu, and Lu >=2Lt, then when moving along engine axis direction, any position are designed away from for Lt in adjacent T-slot center
It is all at least intersecting therewith there are two T-slot, so as to realize that one-component balance moving in stepless way is fixed, different model is facilitated to start
The installation of machine is fixed.
As shown in figure 4, balance weight assembly 52 includes balanced lever 521 and clump weight 522；Balanced lever 521 perpendicular to
511 middle part of vertical beam, balanced lever 521 include fixing end and free end；Fixing end is to opening up strip hole between free end；It is fixed
It holds and is fixedly connected in the middle part of vertical beam 5111, clump weight 522 is bolted on strip hole；It is arranged on balanced lever 521
There is graduation mark.Clump weight 522 can move adjustment on balanced lever 521, determine its equilbrium position, design on balanced lever
There is graduation mark, guarantees to be in identical trystate when same product test of many times.
Balance safety device 53 includes balance safety protection bracket 531 and stop screw 532；Balance security protection
One end of bracket 531, which is fixedly mounted on, determines on frame 3, and the other end is provided with two pieces of parallel fixed plates 533,511 middle part of vertical beam
Between two fixed plates 533, the distance between two fixed plates 533 are greater than the thickness at 511 middle part of vertical beam, one of
Stop screw 532 is installed, the thread segment of stop screw 532 passes through the fixed plate 533 and the vertical beam in fixed plate 533
511 contacts.Stop screw is held out against into vertical beam in actual use, then can guarantee and absorbed beyond load by fixing bracket, from
And protect the sensor from damage.
As shown in fig. 6, calibrating measuring device of the invention further includes so that foil gauge 10 is begun using Forced water cooling convection type
Eventually in 22 ± 1 DEG C of isoperibol, the balance active thermostat 11 of the measurement accuracy of guarantee；Balance active thermostat
11 include being fixedly mounted on the water-cooling jacket structure 111 determined on frame and be located at 511 two sides of vertical beam；Water-cooling jacket structure 111
Constitute a cavity being isolated with free surrounding space；512, the horizontal strain beam is in the cavity；
The side wall of water-cooling jacket structure 111 is hollow structure, is equipped with the first water supply connector in water-cooling jacket structure 111
112 and first water outlet connector 113；First water supply connector 112 is arranged close to 111 lower part of water-cooling jacket structure, the first water outlet connector
113 are arranged close to 111 top of water-cooling jacket structure.111 material of water-cooling jacket structure is stainless steel, surface polishing treatment, right
While carrying out water cooling heat exchange inside device, extraneous radiation heat reflection can also be increased and surveyed to guarantee during heat run
Force snesor may be at 22 ± 1 DEG C of isoperibol, guarantee its measurement accuracy, while the joint arrangement of upper entering and lower leaving, can be with
Guarantee that cooling water is more as far as possible in the hollow structure of water-cooling jacket structure, it is ensured that constant temperature effect.
As shown in Figures 9 and 10, propellant fixing device for pipe 7 includes lower bracket 71 and front band 72, the lower part branch
The bottom surface of frame 71 offers threaded hole 73, and the upper end of lower bracket 71 is lower catch hoop 74 compatible with the front band 72, on
Clip 72 and lower catch hoop 74 are bolted, to realize the fastening of propellant pipeline.
In addition, between horizontal strain beam 512 and balance pinboard 4, the top of vertical beam 511 and attitude control engine 9 to be measured
Between be respectively provided with vacuum insulation panel 12, in order to effectively avoid heat caused by cross-ventilation transmitting, thermal coefficient can be substantially
Degree reduces, and conducts so as to avoid engine gas heat during heat run to foil gauge, and foil gauge precision is caused to reduce very
To damage.
One-component balance measuring device uses lever principle, and the thrust that engine is generated passes through lever+elastic rotation shaft
Motor power is converted to torque, then horizontal strain beam is designed at the lesser position of the arm of force, horizontal strain beam by design method
On by full-bridge mode post foil gauge, can compared to conventional springs formula force measuring machine thus under the magnitude of the identical thrust of engine
The deflection of horizontal strain beam is greatly increased, to improve its sensitivity, schematic illustration is as shown in figure 11, horizontal strain beam
On maximum strain ε and motor power F have following relationship；
Wherein, A is horizontal strain beam cross-sectional area, and E is the elasticity modulus of horizontal strain beam, WzIt is cut for the bending resistance of vertical beam
Face coefficient, y are engine to be measured between the position that the installation site of vertical beam intersects to vertical beam with horizontal strain beam
Vertical height
Motor inlet section pipeline uses hard tube when test.Since the propellant in pipeline can be when entering motor inlet
Flow direction changes, so that additional force value is introduced in thrust measurement, according to liquid propellant rocket engine test requirement, entrance
Pipeline should axially be moved towards perpendicular to thrust, and oxidant and fuel channel is made to be symmetrical with thrust axis, then can make fluid pressure
Minimize value with " negative thrust " caused by liquid flowing, in order to reduce pipeline rigidity, the arrangement of propellant pipeline 6 uses " Z "
Type structure, fuel and oxidant pipeline are fixed on determining frame by fixing device for pipe.
Referring to fig. 2, calibrated in situ device 8 includes standard force source 81, standard force source control system and L-type support 83；
The bottom of L-type support 83 is fixedly connected with frame 3 is determined；Installed with the vertical beam 511 to be measured in 83 top of L-type support
Attitude control engine contour position is installed by standard force source 81；As shown in figure 4, standard force source 81 includes electric cylinder 811, mounting flange
812, adapting rod 813, standard force snesor 814, adapter ring 815 and load steel wire 816；
Referring to Fig. 5, electric cylinder 811 is vertically fixedly installed in (actually electronic in L-type support 83 by mounting flange 812
Cylinder 811 is fixed with mounting flange 812 by 4 bolts, and design is machined with positioning convex platform on mounting flange 812, for connecting electricity
Accurate positioning when dynamic cylinder 811 and support frame, guarantees the concentricity of electric cylinder installation), the output end of electric cylinder 811 passes through switching
Bar 813 is connect with standard force snesor 814；The output end of standard force snesor 814 installs adapter ring 815；Load steel wire 816 1
End is connect with adapter ring 815, and the other end is connect with the central axes of attitude control engine 9 to be measured；In order to avoid hot environment is to mark
The influence of quasi- force snesor, calibrated in situ device further include the cylindrical housings 84 being fixedly mounted in L-type support 83, proof force
Sensor 814 is located in cylindrical housings 84；The outer wall of cylindrical housings 84 is hollow structure, on the outer wall of cylindrical housings 84
Second water supply connector 841 and the second water outlet connector 842 are installed；Second water supply connector 841 is under 84 center of cylindrical housings
Portion's setting, the second water outlet connector 842 are arranged close to 84 central upper of cylindrical housings.It is former in order to be protected to electric cylinder 811
Position calibrating installation 8 further includes the electric cylinder protective cover 85 being fixed in L-type support, and electric cylinder 811 is located in electronic protective cover 85.
Standard force snesor 814 selects HBM S2 standard force snesor, range 50N, measurement accuracy 0.05%.Switching
Ring 815 is used to load the connection of steel wire 816 and standard force snesor 814, and one end is machined with to be matched with standard force snesor 814
External screw thread, other end is provided with the through-hole of φ 0.2, and fixed for loading steel wire 816, load 816 one end of steel wire passes through φ 0.2
Through-hole takes soldering pouring type to carry out connected, guarantees steel wire bonding strength and concentricity.It loads steel wire and uses low elasticity, height
The alloy-steel wire of intensity, Low rigidity, it is ensured that it is sluggish without pulling force in loading procedure, it is interfered in uninstall process without internal force.In order to reduce
The weight of loading device, electric cylinder adapting rod, proof force adapter ring, mounting flange are all made of light material LV12 production.
As shown in figure 12, standard force source control system includes power source control computer, CAN bus, MP30 data acquisition list
Member, HBM standard force snesor, SMC electric cylinder, servo-driver, PLC controller, cable；
Power source controls the calibrating procedure that computer executes setting, after some gear has determined the standard force value of load, leads to
PLC controller control servo driver drives electric cylinder movement is crossed, the practical force value that electric cylinder generates acts on one-component balance
Measuring device, and acquired by MP30 data acquisition unit, then practical force value real-time Transmission is controlled to power source by CAN bus and is counted
Calculation machine, power source control the software in computer for practical force value with standard force value compared with, form closed-loop control, when practical force value and
When standard force value is within the scope of allowable error, the load of stopping criterion power, and power source control computer is transmitted the data to, then
Execute the motion control of next gear.
The specific implementation process of the calibrating measuring device is as follows:
1, status checkout
By showing current bridge for bridge pressure, and by pressure time examining system to the foil gauge in one-component balance measuring device
Pressure, data acquisition unit can be realized foil gauge signal and acquire in real time, apply force value to balance bracket along engine shaft, corresponding
Become the output of piece bridge to be checked, confirmation bridge output is correct, and data acquisition unit can carry out the pressure of standard force snesor
Adjustment, and the output voltage values of standard force snesor are acquired in real time.
2, low thrust attitude control engine is installed
Before product installation, balance safety device in measuring device should be locked, prevent foil gauge mistake in installation process
Failure is carried, the thrust during confirmation engine thermal test run, will be to be measured by balance pinboard within foil gauge range ability
It measures attitude control engine and balance bracket is installed.
3, restraint system is installed
According to measuring device design requirement installation propellant pipeline, attitude control engine control air pipe and pressure, temperature vibration
Dynamic measurement cable, connects the circulation waterway of balance active thermostat and standard force snesor thermostat, and start circulation
Water, by various pipelines and cable fixation.Ensure various pipelines, cable is without interference phenomenon.Counterweight position is adjusted, until
Data acquisition unit shows that one-component balance measuring device output signal is zero, and balance is in equilibrium state at this time.
4, calibrated in situ
It reviews and validate engine and has been in heat examination car state, propellant pipeline is pressurized to test rated pressure.It preloads
Force value is the 120% of normal thrust, and load no less than three times, is added by zero to 120% rated load thrust point, 6 gears
It carries, does lift load and backhaul unloading, while the calibration data of recording balance load cell signal respectively every time.
5, one-component balance measuring device coefficient calculates
According to process (4) calibrated in situ the data obtained, its linearly dependent coefficient, standard deviation are calculated using least square method
Difference, and by above-mentioned two parameter setting into power source control computer.Circular is as follows:
Least square method is fitted the linear equation (y=bx+a) between one group of variable, for calibrated in situ measuring system
Speech, x are the standard force value of a certain gear, and y is collected measurement force value while the gear corresponds to.Meeting during actual alignment
The liter backhaul standard force value and measurement force value of different stalls are collected, and is repeated 3 times, to obtain one group of nominal data [xi,
yi], the correlation between two variables is indicated with related coefficient (R).
The calculation formula of slope b is formula
The calculation formula of intercept a is formula:
Related coefficient is the parameter for measuring one group of measurement data xi, yi linear correlation degree, is defined as:
R value 0 < | r | in≤1.| r | the good linearity between 1, x, y；R is positive, and straight slope is positive, referred to as just
It is related；R is negative, and straight slope is negative, referred to as negatively correlated.| r | it is then non-between measurement data points dispersion or xi, yi close to 0
Linearly.
In least square method, it is assumed that independent variable error can be ignored, and be to derive regression equation for convenience.Operation
The error that the error of middle function is greater than independent variable assumes it is believed that meeting.Actually it is both variable, there is error, thus
Cause the standard deviation (n >=6) of result y, a, b as follows:
(denominator of radical is n-2, is because there are two variables)
The standard deviation obtained in this calibration system is σy
6, coefficient inspection
Axial proof force is applied to balance bracket, and by the output signal of acquisition equipment record foil gauge, with calibration gained
Data processing of the coefficient to acquisition checks that the output force value of foil gauge in one-component balance measuring device is consistent with standard force value
Property, and a liter backhaul load is repeatedly carried out, check its repeatability.(note: repeatability here passes through primarily directed to measuring system
Backhaul load is risen several times, sees whether it is consistent in the measurement output of each power load gear, if consistency is fine, shows to measure
System stability it is fine namely its repeatability is good)
7, prepare heat run
After examination load verification is errorless, electric cylinder zero, load steel wire no longer stress, integrated apparatus has been in heat examination at this time
Car state.
Claims (10)
1. a kind of 4-25N attitude control engine thermal vacuum environment stable state thrust calibration measuring device, it is characterised in that: turn including pedestal
Connect frame (1), damping block (2), determine frame (3), balance pinboard (4), one-component balance measuring device (5), propellant pipeline (6),
Propellant fixing device for pipe (7) and calibrated in situ device (8)；
Pedestal adapter frame (1) and determine to install between frame (3) multiple damping blocks (2), and multiple damping blocks (2) are arranged side by side；Determine frame
(3) periphery is fixedly installed with multiple propellant fixing device for pipe (7), and propellant pipeline (6) passes through the fixed dress of propellant pipeline
Installation is set, propellant pipeline (6) one end is connected to external propellant supply system, the other end and attitude control engine to be measured (9)
The connection of propellant entrance；One-component balance measuring device (5) is mounted on the one end for determining frame (3) by balance pinboard (4), in situ
Calibrating installation (8) is mounted on the other end for determining frame (3)；
One-component balance measuring device (5) includes balance bracket (51), balance weight assembly (52) and balance safety device
(53)；
Balance bracket (51) includes vertical beam (511) and horizontal strain beam (512)；The top installation of vertical beam (511) is to be measured
It measures attitude control engine (9), the thrust direction of attitude control engine to be measured is perpendicular to vertical beam (511)；Balance weight assembly (52) installation
In the middle part of vertical beam (511)；The bottom and horizontal strain beam (512) upper surface of vertical beam (511) are connected, horizontal strain beam
(512) lower end surface is provided with front end gusset (5121), intermediate gusset (5122) and rear end gusset (5123)；Horizontal strain beam
(512) it is fixedly connected respectively by front end gusset (5121), intermediate gusset (5122), rear end gusset with balance pinboard (4)；Water
Foil gauge (10) are covered with by full-bridge mode on flat strain beam (512)；
Balance weight assembly (52) includes balanced lever (521) and clump weight (522)；Balanced lever (521) is perpendicular in vertical beam
(511) middle part, balanced lever (521) includes fixing end and free end；Fixing end is to opening up strip hole between free end；Fixing end
It is fixedly connected with vertical beam (511) middle part, clump weight (522) is fixed on strip hole by bolt and nut；
Balance safety device (53) includes balance safety protection bracket (531) and stop screw (532)；Balance is anti-safely
One end of shield bracket (531), which is fixedly mounted on, determines on frame (3),
The other end is provided with two pieces of parallel fixed plates (533), in the middle part of vertical beam (511) between two fixed plates (533),
The distance between two fixed plates (533) are greater than the thickness in the middle part of vertical beam (511), install on one of fixed plate (533)
Stop screw (532), the thread segment of stop screw (532) pass through the fixed plate (533) and contact with the vertical beam (511)；
Calibrated in situ device (8) includes standard force source (81), standard force source control system and L-type support (83)；
The bottom of L-type support (83) is fixedly connected with frame (3) is determined；At the top of L-type support (83) with the vertical beam (511) installation to
It measures attitude control engine contour position and standard force source is installed；Standard force source (81) includes electric cylinder (811), mounting flange
(812), adapting rod (813), standard force snesor (814), adapter ring (815) and load steel wire (816)；
Electric cylinder (811) is vertically fixedly installed in L-type support by mounting flange (812), and the output end of electric cylinder (811) is logical
Adapting rod (813) is crossed to connect with standard force snesor (814)；The output end of standard force snesor (814) installs adapter ring
(815)；Load steel wire (816) one end is connect with adapter ring (815), and the central axes of the other end and attitude control engine to be measured connect
It connects；
Standard force source control system includes power source control computer, bus, data acquisition unit, servo-driver and PLC control
Device processed；
Power source controls computer transmission objectives force value to PLC controller, and PLC controller is controlled described electronic by servo-driver
Cylinder (811) movement, the practical force value that electric cylinder (811) movement generates are acted on one-component balance measuring device (5) and are counted
Power source is returned by bus transfer after receiving according to acquisition unit and controls computer；Power source controls computer to practical force value and proof force
Value is compared, and obtains the calibration factor of one-component balance measuring device (5).
2. 4-25N attitude control engine thermal vacuum environment stable state thrust calibration measuring device according to claim 1, feature
Be: the one-component balance measuring device (5) further includes balance active thermostat (11)；Balance active thermostat (11)
Water-cooling jacket structure (111) including determining on frame (3) and being located at the setting of vertical beam (511) two sides；Water-cooling jacket
Structure (111) constitutes a cavity being isolated with free surrounding space；Horizontal strain beam (512) position is in the cavity；
The side wall of water-cooling jacket structure (111) is hollow mechanism, be equipped in water-cooling jacket structure the first water supply connector (112) with
First water outlet connector (113)；First water supply connector (112) is arranged close to water-cooling jacket structure (111) lower part, the first water outlet connector
(113) it is arranged close to water-cooling jacket structure (111) top.
3. 4-25N attitude control engine thermal vacuum environment stable state thrust calibration measuring device according to claim 1, feature
Be: the calibrated in situ device (8) further includes the cylindrical housings (84) being fixedly mounted on L-type support (83)；Proof force
Sensor (814) is located in cylindrical housings (84)；The outer wall of cylindrical housings (84) is hollow structure, cylindrical housings 84
Second water supply connector (841) and the second water outlet connector (842) are installed on outer wall；Second water supply connector (841) is close to cylindrical
The setting of shell (84) central lower, the second water outlet connector (842) are arranged close to cylindrical housings (84) central upper.
4. 4-25N attitude control engine thermal vacuum environment stable state thrust calibration measuring device according to claim 1 or 2 or 3,
It is characterized by:
Described to determine frame (3) upper surface and be provided with equidistant multiple T-slots, balance pinboard (4) is along the multiple T-slot arrangement side
U-type groove is offered upwards；The center of adjacent T-slot is away from the relational expression with the length of U-type groove satisfaction are as follows: Lu >=2Lt,
Wherein, U-type groove length is Lu, and adjacent T-slot center is away from for Lt.
5. 4-25N attitude control engine thermal vacuum environment stable state thrust calibration measuring device according to claim 4, feature
Be: the propellant fixing device for pipe (7) includes lower bracket (71) and front band (72), the bottom surface of the lower bracket
It offers threaded hole (73), the upper end of lower bracket (71) is compatible lower catch hoop (74) with the front band (72).
6. 4-25N attitude control engine thermal vacuum environment stable state thrust calibration measuring device according to claim 5, feature
Be: between the horizontal strain beam (512) and balance pinboard (4), at the top of vertical beam (511) with attitude control engine to be measured
(9) vacuum insulation panel is respectively provided between.
7. 4-25N attitude control engine thermal vacuum environment stable state thrust calibration measuring device according to claim 6, feature
Be: relationship is as follows between the maximum strain ε and attitude control engine thrust F to be measured on the horizontal strain beam (512):
Wherein, A is horizontal strain beam (512) cross-sectional area, and E is the elasticity modulus of horizontal strain beam (512), WzFor vertical beam
(511) bending resistant section coefficient, y be engine to be measured vertical beam (511) installation site to vertical beam (511) with level
Vertical height between the position of strain beam (512) intersection.
8. 4-25N attitude control engine thermal vacuum environment stable state thrust calibration measuring device according to claim 7, feature
Be: the calibrated in situ device (8) further includes the electric cylinder protective cover being fixed in L-type support, and electric cylinder is located at electronic guarantor
In shield.
9. 4-25N attitude control engine thermal vacuum environment stable state thrust calibration measuring device according to claim 8, feature
Be: the damping block (2) is 6 BE-40 dampers, and intrinsic frequency is less than 15Hz.
10. 4-25N attitude control engine thermal vacuum environment stable state thrust calibration measuring device according to claim 9, special
Sign is: the material of the propellant pipeline is 1Cr18Ni9Ti, is arranged using " Z " type structure.
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| CN111044191A (en) * | 2019-11-28 | 2020-04-21 | 西安航天动力试验技术研究所 | Attitude control engine thrust measuring device |
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