CN111044191A - Attitude control engine thrust measuring device - Google Patents
Attitude control engine thrust measuring device Download PDFInfo
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- CN111044191A CN111044191A CN201911191315.8A CN201911191315A CN111044191A CN 111044191 A CN111044191 A CN 111044191A CN 201911191315 A CN201911191315 A CN 201911191315A CN 111044191 A CN111044191 A CN 111044191A
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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
- G01L5/0028—Force sensors associated with force applying means
- G01L5/0038—Force sensors associated with force applying means applying a pushing force
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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
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
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Abstract
The invention relates to an attitude control engine thrust measuring device, which solves the problems that the existing attitude control engine test device has larger size and lower measurement precision and can damage a movable frame and a sensor. In the device, the center lines of the movable frame, the force source loading unit, the force measuring unit and the pre-tightening force device are coaxially arranged; the fixed frame is used for bearing the thrust of the engine; the movable frame is used for mounting the engine and transmitting the thrust generated by the engine; the force measuring unit comprises a steady-state force sensor and a bearing pressure head, the steady-state force sensor is arranged on the measuring force bearing wall and used for measuring the force transmitted by the movable frame, and the bearing pressure head transmits the force of the front flange of the movable frame to the steady-state force sensor; the force source loading unit is used for loading a standard force source of the steady-state force sensor; the pre-tightening force device is arranged between the movable frame rear flange and the measuring force bearing wall, is mainly used for eliminating a gap between the movable frame structure and the measuring force sensor, and applies a certain pre-tightening force.
Description
Technical Field
The invention relates to the field of aerospace engine tests, in particular to an attitude control engine thrust measuring device which is applied to thrust in-situ calibration and measurement in an attitude control engine high-altitude simulation test of 20kN magnitude.
Background
The 20kN belongs to a larger thrust magnitude in an attitude control engine test, and the thrust frame structure cannot be too large because a high-altitude simulation test needs to be considered, so that the deformation of the device is as small as possible while the thrust measuring device bears the 20kN thrust, and the deformation is controlled within 0.05 mm. In the existing attitude control engine test, an engine is directly connected with a measuring force sensor, or the engine is connected with a movable frame through a switching frame, and the movable frame is connected with a fixed frame through a spoke type spring piece. For the former connection, the sensor has less resistance to overturning, and is not suitable when the engine cantilever is longer or heavier; for the latter connection form, it has a larger anti-overturning capability, but if a larger force value transmission ratio is to be ensured, a spoke type spring piece with a larger structure needs to be arranged, so that the overall structure size of the thrust measuring device is increased, and the measurement precision is reduced. Meanwhile, the situation such as backfire or other dangers exist in the ignition process of the attitude control engine, the movable frame and the sensor are possibly damaged, and the test cannot be completed in time.
Disclosure of Invention
The invention aims to solve the problems that the existing attitude control engine test device is large in size, low in measurement precision and capable of damaging a movable frame and a sensor, and provides an attitude control engine thrust measurement device which achieves thrust measurement in 20 kN-magnitude attitude control engine ground and high-altitude simulation tests.
The technical scheme of the invention is as follows:
a thrust measuring device of an attitude control engine comprises a fixed frame, a movable frame, a mountain-shaped spring piece, a force source loading unit, a force measuring unit and a pre-tightening force device, wherein the center lines of the movable frame, the force source loading unit, the force measuring unit and the pre-tightening force device are coaxially arranged; the fixed frame is used for bearing the thrust of an engine and comprises a base, a front spring piece bearing wall, a measuring force bearing wall, a rear spring piece bearing wall and a standard force bearing wall, wherein the front spring piece bearing wall, the measuring force bearing wall, the rear spring piece bearing wall and the standard force bearing wall are sequentially arranged on the base; the movable frame is used for mounting an engine and transmitting thrust generated by the engine and comprises a movable frame front flange and a movable frame rear flange which are fixedly connected, the movable frame front flange is connected with the engine through a transfer frame and is connected with a front spring piece bearing wall through a mountain-shaped spring piece, and the movable frame rear flange is connected with a rear spring piece bearing wall through the mountain-shaped spring piece; the force measuring unit comprises a steady-state force sensor and a bearing pressure head, the steady-state force sensor is arranged on a measuring force bearing wall and used for measuring the force transmitted by the movable frame, and the bearing pressure head is arranged between the steady-state force sensor and the front flange of the movable frame and used for transmitting the force of the front flange of the movable frame to the steady-state force sensor; the force source loading unit is arranged on the standard force bearing wall and is used for realizing standard force loading on the steady-state force sensor; the pre-tightening force device is arranged between the movable frame rear flange and the measuring force bearing wall and comprises a pre-tightening force loading head, a pre-tightening intermediate plate, a pre-tightening frame and a plurality of pre-tightening connecting plates; the pre-tightening frame comprises a pre-tightening ring and a plurality of pre-tightening blocks, the pre-tightening ring is fixedly arranged on the rear flange of the movable frame, the pre-tightening blocks are uniformly arranged along the circumferential direction of the pre-tightening ring, one end of each pre-tightening block is vertically fixed on the end face of the pre-tightening ring, the other end of each pre-tightening block is connected with the pre-tightening intermediate plate through a pre-tightening connecting plate, one end of the pre-tightening loading head is fixedly arranged on the force-bearing measuring wall, and the other end of the pre-.
Further, the force source loading unit comprises a standard force loading head, a pull ring, a pull rod, a standard force sensor and an electric cylinder which are connected in sequence; the standard force loading head is positioned on the outer side of the movable frame rear flange and used for transmitting loading force to the movable frame rear flange, the cylinder body of the electric cylinder is fixedly arranged on a standard force bearing wall, and the output shaft of the electric cylinder is connected with the standard force sensor.
Further, the pull ring adopts a universal joint.
Furthermore, a cooling cavity is formed in the movable frame front flange, a plurality of cooling partition plates are arranged in the cooling cavity, and the cooling partition plates are used for increasing the flow area of cooling liquid.
Furthermore, the cooling device also comprises a cooling pipeline connected with the cooling cavity, wherein the cooling pipeline comprises a hard pipe section and a soft pipe section which are communicated with each other and have different diameters, the hard pipe section is arranged on the propellant pipeline and the fixed frame, and the soft pipe section is arranged on the movable frame cooling cavity and is arranged into a U-shaped bent section.
Furthermore, the inner sides of the front spring piece bearing wall and the rear spring piece bearing wall are provided with limiting blocks for limiting the movable frame.
Furthermore, a first positioning block is arranged on the front spring piece bearing wall and the rear spring piece bearing wall, a second positioning block is arranged on the movable frame front flange and the movable frame rear flange, positioning pin holes are formed in the first positioning block and the second positioning block, and the mountain-shaped spring piece is connected with the fixed frame through the first positioning block and is connected with the movable frame through the second positioning block.
Further, the outside of steady state force transducer is provided with water-cooling heat-proof device, water-cooling heat-proof device includes the water-cooling flange, is provided with the cooling chamber on the water-cooling flange, be provided with a plurality of cooling baffles in the cooling chamber.
Furthermore, the movable frame front flange and the movable frame rear flange are fixedly connected through four connecting rods.
Furthermore, the front flange of the movable frame is connected with a bearing wall of the front spring piece through four groups of mountain-shaped spring pieces, and the four groups of mountain-shaped spring pieces are uniformly arranged; the movable frame rear flange is connected with a rear spring piece bearing wall through four groups of mountain-shaped spring pieces, and the four groups of mountain-shaped spring pieces are uniformly arranged.
Compared with the prior art, the invention has the following technical effects:
1. the central lines of the fixed frame, the movable frame, the engine and the sensor of the measuring device are coaxial in a five-line mode, and the force bearing walls of the fixed frame and the movable frame adopt an integrated structure, so that the force value transmission precision is improved, and the thrust measurement precision is obviously improved.
2. In the measuring device, the connection of the movable frame and the fixed frame abandons the traditional spoke type spring leaf structure, and the front and rear mountain type spring leaf groups are connected, so that the force value transmission ratio is greatly improved from 93 percent to 99 percent while the compact structure of the whole measuring device is ensured.
3. The movable frame in the measuring device is provided with the cooling cavity, so that the movable frame and the steady-state force sensor can be effectively protected, the axial rigidity of the movable frame is enhanced, and meanwhile, a water channel formed by the cooling partition plate can isolate heat conduction from the adapter frame and radiation heat from an engine for the steady-state force sensor.
4. The water cooling pipeline of the movable frame in the measuring device adopts a flexible design and a mode of combining different drift diameters, so that the influence of pipeline constraint on force measurement is reduced while the cooling effect is ensured.
5. The measuring device is designed by a ground axis system and a unit calibration method, and the calibration equipment has the advantages of simple structure, high loading efficiency (no adjustment and reset), small repeatability error (high calibration precision) and low equipment manufacturing cost.
Drawings
FIG. 1 is a structural diagram of an attitude control engine thrust measurement device of the present invention;
FIG. 2 is a structural diagram of a fixed frame in the attitude control engine thrust measurement device of the present invention;
FIG. 3 is a structural diagram of a movable frame in the thrust measurement device of the attitude control engine of the present invention;
FIG. 4 is a schematic structural diagram of a force source loading unit in the attitude control engine thrust measurement device according to the present invention;
FIG. 5 is a schematic structural diagram of a force measuring unit in the attitude control engine thrust measuring device according to the present invention;
FIG. 6 is a schematic structural diagram of a pre-tightening force device in the attitude control engine thrust measurement device according to the present invention;
FIG. 7 is a schematic structural diagram of a cooling pipeline in the attitude control engine thrust measurement device of the present invention;
FIG. 8 is a schematic view of the installation of a limiting block in the attitude control engine thrust measurement apparatus of the present invention;
FIG. 9 is a schematic structural view of a mountain spring leaf in the thrust measurement device of the attitude control engine of the present invention;
FIG. 10 is a schematic structural diagram of a cooling cavity in the thrust measurement device of the attitude control engine according to the present invention;
FIG. 11 is a schematic diagram of the force calibration operation in the attitude control engine thrust measurement apparatus of the present invention.
Reference numerals: 1-fixed frame, 2-movable frame, 3-mountain spring leaf, 4-force source loading unit, 5-force measuring unit, 6-pretightening force device, 7-cooling pipeline, 8-switching frame, 9-engine, 10-limiting block, 11-base, 12-front spring leaf bearing wall, 13-measuring force bearing wall, 14-rear spring leaf bearing wall, 15-standard force bearing wall, 16-first locating block, 21-movable frame front flange, 22-movable frame rear flange, 23-cooling cavity, 231-cooling partition plate, 24-connecting rod, 25-second locating block, 41-standard force loading head, 42-pull ring, 43-pull rod, 44-standard force sensor, 45-electric cylinder, 51-steady state force sensor, 52-bearing pressure head, 61-pretightening force loading head, 62-pretightening intermediate plate, 63-pretightening frame, 64-pretightening connecting plate, 631-pretightening ring, 632-pretightening block, 71-hard pipe section and 72-soft pipe section.
Detailed Description
The invention is described in further detail below with reference to the figures and specific embodiments.
The invention provides a thrust measuring device of an attitude control engine, which aims to realize thrust measurement in ground and high-altitude simulation tests of a 20 kN-magnitude high-room pressure attitude control engine. The measuring device adopts a single-point force bearing structure for measuring thrust by a single sensor, a front and back mountain-shaped spring leaf structure is adopted for connecting a movable frame and a fixed frame, an automatic thrust in-situ calibration system consisting of a standard force sensor and an electric cylinder is adopted, the rear part of a driven frame is subjected to stress application calibration, a transmission path of a calibration force value is consistent with a test run working condition, the influence of a propellant supply pipeline, a cooling pipeline, a measuring cable and the like on thrust measurement can be effectively eliminated through in-situ calibration, the force value transmission ratio can reach more than 99%, and the thrust measurement precision of a 20 kN-magnitude high-chamber pressure attitude control engine is greatly improved.
As shown in fig. 1, the attitude control engine thrust measuring device includes a fixed frame 1 (including a thrust bearing foundation, a standard force bearing foundation, a spring piece base and a base), a movable frame 2, a mountain-shaped spring piece 3 (including a front mountain-shaped spring piece group and a rear mountain-shaped spring piece group), a force source loading unit 4, a force measuring unit 5 and a pre-tightening force device 6, and the center lines of the movable frame 2, the force source loading unit 4, the force measuring unit 5 and the pre-tightening force device 6 are coaxially arranged.
As shown in fig. 2, the fixed frame 1 is used for bearing the thrust of the attitude control engine 9, and includes a base 11, and a front spring piece bearing wall 12, a measurement force bearing wall 13, a rear spring piece bearing wall 14, and a standard force bearing wall 15 which are sequentially arranged on the base 11. The material of the fixed frame 1 is selected 304, and in order to ensure the stability of the device, the front spring leaf bearing wall 12 and the rear spring leaf bearing wall 14 can be arranged into an integral structure. The base 11 is provided with positioning holes which are distributed along the thrust axis and used for ensuring the relative positions of the bearing walls during longitudinal installation, the positioning holes are welded on the fixed frame 1, and the positioning holes are machined after structural stress is removed.
During measurement, the fixed frame 1 ensures that five central lines of an engine central line, a movable frame central line, a steady-state force sensor central line, a standard force sensor central line and a force source central line are coaxial, so that a thrust transmission axis is ensured to be coaxial with a standard force transmission path in an in-situ calibration process in the working process of the engine, and the maximum deformation of the movable frame is less than 0.05mm when the movable frame bears the 20kN thrust of an external engine through the position distribution design and the local reinforcement optimization design of each bearing wall.
As shown in fig. 3, the movable frame 2 is used for mounting the engine 9 and transmitting thrust generated by the engine 9, and includes a movable frame front flange 21 and a movable frame rear flange 22 which are fixedly connected, and the movable frame front flange 21 and the movable frame rear flange 22 may be connected by four connecting rods 24, or may be connected by other methods. The movable frame front flange 21 is connected with the engine 9 through the adapter 8, and is connected with the front spring piece bearing wall 12 through the mountain-shaped spring piece 3, and the movable frame rear flange 22 is connected with the rear spring piece bearing wall 14 through the mountain-shaped spring piece 3. During the hot test, the engine thrust is transmitted from the front flange 21 of the movable frame to the steady-state force sensor 51, and during the in-situ calibration, the standard force is transmitted from the rear flange 22 of the movable frame to the front flange 21 of the movable frame and then to the steady-state force sensor 51, so as to ensure that the states of the two are equal, the movable frame 2 is ensured to have enough rigidity, generally not more than 0.1 mm.
As shown in fig. 8, the inner sides of the front spring piece bearing wall 12 and the rear spring piece bearing wall 14 are provided with a limiting block 10, and the limiting block has the functions of: when automatic normal position calibration is carried out, the phenomenon that the movable frame is excessively displaced due to misoperation to cause unrecoverable plastic deformation to the mountain-shaped spring piece is prevented, or in the preparation process of a trial run product, when an engine is installed or an inlet pipeline is configured, the phenomenon that the movable frame is excessively displaced to cause damage to the mountain-shaped spring piece is prevented, and the gap between the movable frame and the mountain-shaped spring piece is about 1mm by adjusting the limiting screw on the limiting block, so that the mountain-shaped spring piece is always in the elastic deformation range of the mountain-shaped spring piece while thrust measurement is not influenced.
As shown in fig. 4, the force source loading unit 4 is arranged on the standard force bearing wall 15 and is used for performing standard force source on the steady-state force sensor 51, and comprises a standard force loading head 41, a pull ring 42, a pull rod 43, a standard force sensor 44 and an electric cylinder 45 which are connected in sequence; the standard force loading head 41 is positioned at the outer side of the movable frame rear flange 22 and is used for transmitting the loading force of the force source loading unit 4 to the movable frame rear flange 22, the cylinder body of the electric cylinder 45 is fixedly arranged on the standard force bearing wall 15, and the output shaft is connected with the standard force sensor 44. The force source loading unit 4 is used for loading a standard force source of the steady-state force sensor 51 by the electric cylinder 45, the force source loading unit 4 is loaded through a single point of the rear flange 22 of the movable frame, a force value acts on the steady-state force sensor 51 through the four connecting rods 24, in order to reduce the mass of the movable frame 2 and ensure the rigidity of the movable frame, the connecting rods 24 are of a hollow cylindrical structure, and the material is made of modulated 45 steel. Because pull rod 43 and standard force loading head 41 are the rigid connection, prevent that the loading mechanism load that leads to because machining error or installation error from excessively deviating, the pull ring 42 of connecting standard force loading head 41 and pull rod 43 adopts "fisheye" structure, and when standard force loading head 41 and pull rod 43 disalignment, the "fisheye" structure of pull ring inside can carry out the self-adaptation, guarantees the effective transmission of power value. The fisheye structure is a universal joint structure, and when the pull rod 43 is in hard connection, the fisheye connection part can rotate automatically, so that the connection of the pull rod 43 is not restrained additionally.
The force source loading unit 4 is one of the key links of the thrust in-situ calibration system, and in order to reduce the uncertainty introduced in the in-situ calibration process, the force source loading unit 4 can stably output in the vacuum, high-temperature and vibration environments. The 20kN thrust measuring device selects a high-precision electric cylinder as a force loading actuating mechanism, and converts the rotary motion of a servo motor into linear motion through a product with the servo motor and a lead screw integrally designed. The whole set of force value loading device comprises a servo motor, a slide rail, a ball screw, a force sensor, a mounting base, a real-time controller and the like, and is mounted with the base of the thrust measurement calibration device through the mounting base. The real-time controller integrates a measurement and control function, wherein the servo motor controller is used for controlling the rotation angle of the motor, the angle encoder is used for detecting the rotation angle of the motor, the limit switch is used for limiting the displacement stroke of the ball screw, the force sensor is used for detecting the output force value of the force loading mechanism, and the closed-loop control of the standard force loading process is realized through the fusion and judgment of key parameter information.
As shown in fig. 5, the force measuring unit 5 includes a steady-state force sensor 51 and a force-bearing ram 52, the steady-state force sensor 51 is disposed on the measuring force-bearing wall 13 and is used for measuring the force transmitted by the movable frame 2, and the force-bearing ram 52 is disposed between the steady-state force sensor 51 and the movable frame front flange 21 and transmits the force of the movable frame front flange 21 to the steady-state force sensor 51. The steady state force sensor is a calibrated object, the thrust data of the engine 9 can be converted into voltage signals to be output, a water-cooling heat insulation device is arranged on the outer side of the steady state force sensor 51 and comprises a water-cooling flange, a cooling cavity is formed in the water-cooling flange, a plurality of cooling partition plates are arranged in the cooling cavity, and the structure of the cooling cavity is the same as that of the cooling cavity arranged on the movable frame front flange.
As shown in fig. 6, the pre-tightening force device 6 is arranged between the movable frame rear flange 22 and the measurement force bearing wall 13, and includes a pre-tightening force loading head 61, a pre-tightening middle plate 62, a pre-tightening frame 63 and a plurality of pre-tightening connection plates 64; the pre-tightening frame 63 comprises a pre-tightening ring 631 and a plurality of pre-tightening blocks 632, the pre-tightening ring 631 is fixedly arranged on the movable frame rear flange 22, the pre-tightening blocks 632 are uniformly arranged along the circumferential direction of the pre-tightening ring 631, one end of each pre-tightening block 632 is vertically fixed on the end face of the pre-tightening ring 631, the other end of each pre-tightening block is connected with the pre-tightening intermediate plate 62 through the pre-tightening connecting plate 64, one end of the pre-tightening force loading head 61 is fixedly arranged on the measuring force bearing wall 13, and the other end of the pre-tightening. The pretightening force device 6 is mainly used for eliminating a gap between the movable frame 2 and the steady-state force sensor, and simultaneously can ensure that the actual use range of the steady-state force sensor is within the most suitable measurement range by applying a certain pretightening force, thereby ensuring the measurement accuracy.
As shown in fig. 10, during the test, the temperature change may cause the temperature of the measuring device and the sensor to rise, resulting in thermal deformation of the measuring device and temperature drift of the sensor, and thermal radiation protection measures need to be applied to the measuring device. In the measurement of the invention, the steady-state force sensor 51 is close to the engine 9, the main heat transfer modes are heat conduction and radiation, and the high-temperature radiation and the conduction in the ignition process of the attitude control engine 9 can cause great influence and even damage to the steady-state force sensor 51. The cooling cavity 23 is added on the basis of the traditional single movable frame 2 structure, the cooling cavity 23 is arranged on the movable frame front flange 21, a plurality of cooling partition plates 231 are arranged in the cooling cavity 23, and the plurality of cooling partition plates 231 are used for increasing the flow area of cooling liquid. The cavity of the cooling cavity 23 is internally provided with a stainless steel cooling partition plate 231 to form a cooling water channel, circulating cooling water is enabled to flow through a heat radiation high-temperature position along the trend of the water channel, heat conduction from the adapter rack 8 and radiation heat from the engine 9 are isolated, meanwhile, the cooling partition plate 231 greatly increases the strength and rigidity of the movable rack 2 structure, and when the movable rack 2 structure bears a 20kN calibration force value, the deformation is smaller than 0.5mm, so that the consistency of the calibration process and the thermal ignition process is ensured, and the calibration precision is improved.
As shown in fig. 7, the water-cooled moving frame 2 has good strength, rigidity and thermal protection effect, but water inlet and outlet pipelines need to be arranged, if a hose structure is used, a large error is brought to thrust measurement due to poor repeatability, if a hard pipe is used, a large constraint force is introduced, in order to solve the contradiction, the invention designs cooling pipeline structures with different diameters and 'rigidity and flexibility', and the cooling pipeline 7 is connected with the cooling cavity 23. The cooling pipeline 7 is divided into two sections, including a hard pipe section 71 and a soft pipe section 72 which are communicated with each other, and stainless steel pipes with different outer diameters are selected. Selection of rigid pipe sections 71 to be mounted on propellant lines and fixed shelves
Stainless steel pipe for increasing rigidity of fixing, and a hose section 72 provided at an inlet portion of the moving frame cooling chamber 23
Stainless steel pipe to design U type bending segment, reduce the restraint of pipeline substitution.
As shown in fig. 9, the space between the movable frame 2 and the fixed frame 1 of the 20kN thrust measuring device is small, and when the spoke type spring piece is adopted, the axial rigidity of the spring piece is difficult to meet the design requirement, so the mountain-shaped spring plate is adopted in the device of the invention, and the material of the mountain-shaped spring plate is 60Si2Mn (the allowable stress is 1177 MPa). The mountain-shaped spring piece 33 is used for connecting the movable frame 2 with the fixed frame 1, so that the movable frame 2 is accurately positioned and is used as constraint on a force interface between the movable frame 2 and the fixed frame 1, and the movable frame 2 can not transversely move and can only slightly move along the direction of a thrust axis. The movable frame front flange 21 is connected with the front spring piece bearing wall 12 through four groups of mountain-shaped spring pieces 3, and the four groups of mountain-shaped spring pieces 3 are uniformly arranged; the movable frame rear flange 22 is connected with the rear spring piece bearing wall 14 through four groups of mountain-shaped spring pieces 3, and the four groups of mountain-shaped spring pieces 3 are uniformly arranged. Each plane of the mountain-shaped spring piece 3 can ensure good flatness, and the mountain-shaped spring piece is applied to a posture control engine 9 measuring device with a small thrust magnitude. The mountain-shaped spring piece 3 connects the movable frame 2 and the fixed frame 1, so that the movable frame is ensured to have smaller rigidity along the axial direction and have larger rigidity in other directions, and meanwhile, the mountain-shaped spring piece has stronger capability of resisting the lateral force of the engine 9, so that the movable frame 2 can do small movement along the direction of the thrust axis, the movable frame 2 is limited to move in other directions, and the whole size of the thrust measuring device is more compact. The front of the mountain-shaped spring piece 3 is divided into three parts, the middle part is a fixed section, the two ends are displacement sections, when the movable frame 2 is subjected to external force, the displacement sections at the two ends can make small displacement along the axial direction, the longitudinal section is divided into five sections, the large section is a structural reinforcement section, the small section is an elastic displacement section, the structure can ensure that the mountain-shaped spring piece 3 has great longitudinal rigidity on the premise of having enough strength, the axial rigidity is smaller, and the effectiveness of force value transmission is ensured.
The mountain-shaped spring pieces 3 in the device of the invention are 8 pieces in total, and the front group and the rear group are two groups, and each group is 4 pieces. The key point of the chevron-shaped spring pieces 33 is that the planes of each group of chevron-shaped spring pieces 3 can be flush after installation. In order to solve the problem, a first positioning block 16 is arranged on a front spring piece bearing wall 12 and a rear spring piece bearing wall 14, second positioning blocks 25 are arranged on a front flange 21 and a rear flange 22 of a movable frame, a mountain-shaped spring piece 3 is connected with a fixed frame 1 through the first positioning block 16 and is connected with a movable frame 2 through the second positioning block 25, each group of first positioning blocks 16 is processed by an integral body of the fixed frame 1, each group of second positioning blocks 25 is processed by an integral body of the movable frame 2, sufficient flatness is guaranteed, meanwhile, positioning pin holes are formed in the first positioning block 16 and the second positioning block 25, when the mountain-shaped spring piece 3 is installed with the first positioning block 16 and the second positioning block 25, position alignment is firstly carried out through the positioning pins, then the mountain-shaped spring piece is fixedly installed, and after the installation is finished, the flatness of each plane of the mountain-shaped spring piece 3 is guaranteed to be within 0.01 in a free state.
The sizes of h, L, L and b1 in the structure of the mountain-shaped spring plate 3 are reasonably designed, and the strength and rigidity of the two groups of spring plate groups in the thrust measuring device are considered by the system, so that the constraint force value introduced by the spring plate groups is ensured to be less than 1%. Finally, the mountain-shaped spring piece 3 in the device of the invention is as follows: the mountain-shaped spring piece 33 designed by 60Si2Mn has an axial rigidity of 241N/mm and a vertical rigidity of 250000N/mm, and can realize the function of preventing the carrier 2 from moving transversely and only slightly in the direction of the thrust axis. In the ignition process of the 20kN engine, the deformation amount of the nozzle in the vertical direction is 0.04mm (the un-ignition displacement is minus 0.05mm, and the deformation amount is minus 0.09mm in the ignition process), the maximum stress of the spring leaf set is 66MPa, and the spring leaf set has the capability of resisting the lateral force of the engine 9.
As shown in fig. 11, the force source loading unit 4 of the system of the present invention calibrates the steady state force sensor 51 under inlet line pressurization conditions prior to testing. During thrust calibration, the force source loading unit 4 is controlled by the control system to apply a force value, signals of the steady-state force sensor 51 amplified by the signal amplifier are collected in real time, the output value of the steady-state force sensor 51 is constantly compared with a target value, when the difference value between the output value and the target value is stable in a certain interval, the calibration computer sends an instruction to the data collection computer, the output values of the standard force sensor 44 and the output value of the steady-state force sensor are simultaneously recorded by the calibration computer, and the collected standard force value is transmitted to the collection computer by the calibration computer, so that automatic calibration is realized, namely the standard force sensor is used for calibrating the constrained measuring force sensor. The control system of the device adopts PLC automatic control, so that the device can be automatically calibrated in a remote way before and after the ignition of the engine. The measuring system is composed of a data transmission system and a data acquisition system, the data transmission system can realize the transmission of voltage signals among all components, the acquisition system can realize the acquisition of voltage signals output by the steady-state thrust sensor, can independently provide excitation for a strain bridge of the steady-state thrust sensor, and can perform retesting on the excitation; the collecting computer can synchronously record the standard force value output by the standard force source and the voltage signal output by the steady-state thrust sensor in the calibration process.
Claims (10)
1. The utility model provides an appearance accuse engine thrust measuring device which characterized in that: the force source device comprises a fixed frame (1), a movable frame (2), a mountain-shaped spring piece (3), a force source loading unit (4), a force measuring unit (5) and a pre-tightening force device (6), wherein the center lines of the movable frame (2), the force source loading unit (4), the force measuring unit (5) and the pre-tightening force device (6) are coaxially arranged;
the fixed frame (1) is used for bearing the thrust of an engine (9) and comprises a base (11), and a front spring piece bearing wall (12), a measuring force bearing wall (13), a rear spring piece bearing wall (14) and a standard force bearing wall (15) which are sequentially arranged on the base (11);
the movable frame (2) is used for mounting an engine (9) and transmitting thrust generated by the engine (9), and comprises a movable frame front flange (21) and a movable frame rear flange (22) which are fixedly connected, the movable frame front flange (21) is connected with the engine (9) through a transfer frame (8) and is connected with a front spring piece bearing wall (12) through a mountain-shaped spring piece (3), and the movable frame rear flange (22) is connected with a rear spring piece bearing wall (14) through the mountain-shaped spring piece (3);
the force measuring unit (5) comprises a steady-state force sensor (51) and a force bearing pressure head (52), the steady-state force sensor (51) is arranged on the force bearing wall (13) for measuring the force transmitted by the movable frame (2), and the force bearing pressure head (52) is arranged between the steady-state force sensor (51) and the front flange (21) of the movable frame and transmits the force of the front flange (21) of the movable frame to the steady-state force sensor (51);
the force source loading unit (4) is arranged on the standard force bearing wall (15) and is used for realizing standard force loading on the steady-state force sensor (51);
the pre-tightening force device (6) is arranged between the movable frame rear flange (22) and the measuring force bearing wall (13), and comprises a pre-tightening force loading head (61), a pre-tightening middle plate (62), a pre-tightening frame (63) and a plurality of pre-tightening connecting plates (64); the pre-tightening frame (63) comprises a pre-tightening ring (631) and a plurality of pre-tightening blocks (632), the pre-tightening ring (631) is fixedly arranged on the movable frame rear flange (22), the pre-tightening blocks (632) are uniformly arranged along the circumferential direction of the pre-tightening ring (631), one end of each pre-tightening block is vertically fixed on the end face of the pre-tightening ring (631), the other end of each pre-tightening block is connected with a pre-tightening middle plate (62) through a pre-tightening connecting plate (64), one end of a pre-tightening loading head (61) is fixedly arranged on the measuring force bearing wall (13), and the other end of each pre-tightening loading head is in contact with the pre-tightening middle plate.
2. The attitude control engine thrust measurement device according to claim 1, characterized in that: the force source loading unit (4) comprises a standard force loading head (41), a pull ring (42), a pull rod (43), a standard force sensor (44) and an electric cylinder (45) which are connected in sequence; the standard force loading head (41) is located on the outer side of the movable frame rear flange (22) and used for transmitting loading force to the movable frame rear flange (22), a cylinder body of the electric cylinder (45) is fixedly arranged on a standard force bearing wall (15), and an output shaft of the electric cylinder is connected with a standard force sensor (44).
3. The attitude control engine thrust measurement device according to claim 2, characterized in that: the pull ring (42) adopts a universal joint.
4. An attitude control engine thrust measurement apparatus according to claim 1, 2 or 3, characterized in that: a cooling cavity (23) is formed in the movable frame front flange (21), a plurality of cooling partition plates (231) are arranged in the cooling cavity (23), and the plurality of cooling partition plates (231) are used for increasing the flow area of cooling liquid.
5. The attitude control engine thrust measurement device according to claim 4, characterized in that: the cooling device is characterized by further comprising a cooling pipeline (7) connected with the cooling cavity (23), wherein the cooling pipeline (7) comprises a hard pipe section (71) and a hose section (72), the hard pipe section (71) and the hose section (72) are communicated and have different diameters, the hard pipe section (71) is arranged on the propellant pipeline and the fixed frame (1), and the hose section (72) is arranged on the movable frame cooling cavity (23) and is set to be a U-shaped bending section.
6. The attitude control engine thrust measurement device according to claim 5, characterized in that: and the inner sides of the front spring piece bearing wall (12) and the rear spring piece bearing wall (14) are provided with limiting blocks (10) for limiting the movable frame (2).
7. The attitude control engine thrust measurement device according to claim 6, characterized in that: the spring support is characterized in that a first positioning block (16) is arranged on the front spring piece bearing wall (12) and the rear spring piece bearing wall (14), a second positioning block (25) is arranged on the movable support front flange (21) and the movable support rear flange (22), positioning pin holes are formed in the first positioning block (16) and the second positioning block (25), and the mountain-shaped spring piece (3) is connected with the fixed support (1) through the first positioning block (16) and is connected with the movable support (2) through the second positioning block (25).
8. The attitude control engine thrust measurement device according to claim 7, characterized in that: the outside of steady state force transducer (51) is provided with water-cooling heat-proof device, water-cooling heat-proof device includes the water-cooling flange, is provided with the cooling chamber on the water-cooling flange, be provided with a plurality of cooling baffles in the cooling chamber.
9. The attitude control engine thrust measurement device according to claim 8, characterized in that: the movable frame front flange (21) and the movable frame rear flange (22) are fixedly connected through four connecting rods (24).
10. The attitude control engine thrust measurement device according to claim 9, characterized in that: the movable frame front flange (21) is connected with a front spring piece bearing wall (12) through four groups of mountain-shaped spring pieces (3), and the four groups of mountain-shaped spring pieces (3) are uniformly arranged; the movable frame rear flange (22) is connected with a rear spring piece bearing wall (14) through four groups of mountain-shaped spring pieces (3), and the four groups of mountain-shaped spring pieces (3) are uniformly arranged.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112378561A (en) * | 2020-11-25 | 2021-02-19 | 西安航天动力试验技术研究所 | Integrated equipment and method for attitude control engine thrust measurement and in-situ calibration |
| CN114509271A (en) * | 2021-12-31 | 2022-05-17 | 北京航天益森风洞工程技术有限公司 | Engine thrust measuring rack and thrust measuring method |
Citations (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2041728U (en) * | 1987-09-10 | 1989-07-26 | 上海实用电子研究所 | Heat-sink fan temperature unloading device for automobile |
| CN1312183A (en) * | 2000-02-29 | 2001-09-12 | 巴鲁法蒂股份公司 | Motion-transfering device of motor-vehicle fan co-axially operated with connection system |
| CN101435728A (en) * | 2008-12-18 | 2009-05-20 | 中国科学院力学研究所 | Apparatus and method for measuring small rocket engine thrust force vector in vacuum |
| CN102818671A (en) * | 2012-08-16 | 2012-12-12 | 北京航空航天大学 | High-precision liquid or gas rocket engine thrust rack |
| CN102818676A (en) * | 2012-08-16 | 2012-12-12 | 北京航空航天大学 | Thrust rack in-situ calibration system |
| CN202707241U (en) * | 2012-07-17 | 2013-01-30 | 天津雷沃重工集团股份有限公司 | Fan driving structure of engine |
| CN103091111A (en) * | 2013-01-25 | 2013-05-08 | 南京理工大学 | Side direction hydraulic pressure calibration adjustable support of vertical type six-component test bed |
| CN203490076U (en) * | 2013-09-12 | 2014-03-19 | 沈阳黎明航空发动机(集团)有限责任公司 | Aeroengine ground indoor stand air intake heating device |
| CN104265444A (en) * | 2014-09-29 | 2015-01-07 | 日立汽车系统(苏州）有限公司 | Windward collection device, engine with windward collection device, and windward distribution method |
| CN105547585A (en) * | 2015-12-31 | 2016-05-04 | 西安航天动力试验技术研究所 | Attitude control engine vector thrust original position calibration apparatus |
| CN107202660A (en) * | 2017-06-06 | 2017-09-26 | 西安航天动力试验技术研究所 | 4 25N attitude control engine thermal vacuum environment stable state thrust calibration measurement apparatus |
| CN107238457A (en) * | 2017-06-28 | 2017-10-10 | 北京航空航天大学 | A kind of low thrust measurement apparatus |
| CN107389240A (en) * | 2017-06-06 | 2017-11-24 | 西安航天动力试验技术研究所 | 4 25N attitude control engine thermal vacuum environment stable state thrust-measuring devices |
| FR3044093B1 (en) * | 2015-11-19 | 2017-12-15 | Snecma | TEST BENCH FOR TURBOJET ENGINE |
| CN107907342A (en) * | 2017-12-18 | 2018-04-13 | 西安航天动力测控技术研究所 | The thrust calibrated in situ device that a kind of canted nozzle axially reinforces |
| CN108953004A (en) * | 2018-03-23 | 2018-12-07 | 西安航天动力试验技术研究所 | A kind of high-thrust rocket lateral force test predictor method |
| CN109141905A (en) * | 2018-10-01 | 2019-01-04 | 北京航天三发高科技有限公司 | A kind of six square phase test bay and its method for measuring vectored thrust |
| CN109632171A (en) * | 2019-01-08 | 2019-04-16 | 陕西航天西诺美灵电气有限公司 | A kind of rocket engine micro-force measuring apparatus |
-
2019
- 2019-11-28 CN CN201911191315.8A patent/CN111044191B/en active Active
Patent Citations (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2041728U (en) * | 1987-09-10 | 1989-07-26 | 上海实用电子研究所 | Heat-sink fan temperature unloading device for automobile |
| CN1312183A (en) * | 2000-02-29 | 2001-09-12 | 巴鲁法蒂股份公司 | Motion-transfering device of motor-vehicle fan co-axially operated with connection system |
| CN101435728A (en) * | 2008-12-18 | 2009-05-20 | 中国科学院力学研究所 | Apparatus and method for measuring small rocket engine thrust force vector in vacuum |
| CN202707241U (en) * | 2012-07-17 | 2013-01-30 | 天津雷沃重工集团股份有限公司 | Fan driving structure of engine |
| CN102818671A (en) * | 2012-08-16 | 2012-12-12 | 北京航空航天大学 | High-precision liquid or gas rocket engine thrust rack |
| CN102818676A (en) * | 2012-08-16 | 2012-12-12 | 北京航空航天大学 | Thrust rack in-situ calibration system |
| CN103091111A (en) * | 2013-01-25 | 2013-05-08 | 南京理工大学 | Side direction hydraulic pressure calibration adjustable support of vertical type six-component test bed |
| CN203490076U (en) * | 2013-09-12 | 2014-03-19 | 沈阳黎明航空发动机(集团)有限责任公司 | Aeroengine ground indoor stand air intake heating device |
| CN104265444A (en) * | 2014-09-29 | 2015-01-07 | 日立汽车系统(苏州）有限公司 | Windward collection device, engine with windward collection device, and windward distribution method |
| FR3044093B1 (en) * | 2015-11-19 | 2017-12-15 | Snecma | TEST BENCH FOR TURBOJET ENGINE |
| CN105547585A (en) * | 2015-12-31 | 2016-05-04 | 西安航天动力试验技术研究所 | Attitude control engine vector thrust original position calibration apparatus |
| CN107202660A (en) * | 2017-06-06 | 2017-09-26 | 西安航天动力试验技术研究所 | 4 25N attitude control engine thermal vacuum environment stable state thrust calibration measurement apparatus |
| CN107389240A (en) * | 2017-06-06 | 2017-11-24 | 西安航天动力试验技术研究所 | 4 25N attitude control engine thermal vacuum environment stable state thrust-measuring devices |
| CN107202660B (en) * | 2017-06-06 | 2019-07-16 | 西安航天动力试验技术研究所 | 4-25N attitude control engine thermal vacuum environment stable state thrust calibration measuring device |
| CN107238457A (en) * | 2017-06-28 | 2017-10-10 | 北京航空航天大学 | A kind of low thrust measurement apparatus |
| CN107907342A (en) * | 2017-12-18 | 2018-04-13 | 西安航天动力测控技术研究所 | The thrust calibrated in situ device that a kind of canted nozzle axially reinforces |
| CN108953004A (en) * | 2018-03-23 | 2018-12-07 | 西安航天动力试验技术研究所 | A kind of high-thrust rocket lateral force test predictor method |
| CN109141905A (en) * | 2018-10-01 | 2019-01-04 | 北京航天三发高科技有限公司 | A kind of six square phase test bay and its method for measuring vectored thrust |
| CN109632171A (en) * | 2019-01-08 | 2019-04-16 | 陕西航天西诺美灵电气有限公司 | A kind of rocket engine micro-force measuring apparatus |
Non-Patent Citations (3)
| Title |
|---|
| 丁佳伟等: "大推力液体火箭发动机试车台推力架结构强度分析", 《学术论文》 * |
| 宋江涛等: "通用飞机发动机一体化试验平台的设计与应用", 《燃气涡轮试验与研究》 * |
| 朱子环等: "氢氧火箭发动机高空模拟试验推力测量装置研制", 《宇航计测技术》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112378561A (en) * | 2020-11-25 | 2021-02-19 | 西安航天动力试验技术研究所 | Integrated equipment and method for attitude control engine thrust measurement and in-situ calibration |
| CN114509271A (en) * | 2021-12-31 | 2022-05-17 | 北京航天益森风洞工程技术有限公司 | Engine thrust measuring rack and thrust measuring method |
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