CN115030839A - Adjustable six-component test bed for small rocket engine - Google Patents
Adjustable six-component test bed for small rocket engine Download PDFInfo
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- CN115030839A CN115030839A CN202210365534.9A CN202210365534A CN115030839A CN 115030839 A CN115030839 A CN 115030839A CN 202210365534 A CN202210365534 A CN 202210365534A CN 115030839 A CN115030839 A CN 115030839A
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- 230000007246 mechanism Effects 0.000 claims abstract description 19
- 239000007921 spray Substances 0.000 claims abstract description 13
- 238000009434 installation Methods 0.000 claims abstract description 5
- 238000005259 measurement Methods 0.000 claims description 9
- 238000000034 method Methods 0.000 claims description 6
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/96—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by specially adapted arrangements for testing or measuring
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Abstract
The invention provides an adjustable six-component force test bed for a small rocket engine, which comprises an installation platform, a movable frame and a portal frame which are arranged on the installation platform, a servo mechanism arranged on the movable frame, six sensors and three sensors, wherein the six sensors bear longitudinal force; two bear the horizontal force; the last one is subjected to axial forces. After the data measured by the force transducer, a six-component model of the thrust vector is constructed, and then the vector force is calculated through a space force system balance equation group. The six-component test bed of the small solid rocket engine is convenient to disassemble and assemble, can be adjusted in size, is used for novel cold flow and heat flow tests of engines, can also complete experimental research on various thrust vector spray pipes such as sub-supersonic separation line spray pipes, submerged spray pipes, secondary injection spray pipes and the like, and is suitable for different experimental conditions and scenes such as narrow vacuum pipes for ground test and simulated high-altitude test.
Description
Technical Field
The invention relates to an adjustable six-component test bed for a small rocket engine, which is used for cold flow tests, heat flow tests and simulated high-altitude test tests of the rocket engine and can also be used for thrust vector performance tests of various advanced engine spray pipes, and belongs to the technical field of aerospace.
Background
The rocket engine experiment is a crucial step in the engine research and development process, and the thrust vector is an important performance parameter for evaluating the quality of the engine. To obtain the thrust vector performance of an engine or a nozzle, hundreds of experiments are often needed to collect data, and it is impractical to complete these tasks only by flight tests because flight tests are too costly, have high risks, have long periods, are difficult to acquire data, and consume a large amount of manpower and material resources. Therefore, a ground trial run is required to obtain data, that is, the engine is fixed on the ground, and static experiments are performed on the engine according to specific conditions and environmental requirements to obtain important data of the performance of the engine. However, the new principle, the new form of the engine and the nozzle form in the test stage are different, and the size difference of the interface is large; the advanced nozzle technology is faster, the processing period of the test bed is long, and the test bed is difficult to be matched; in addition, cold-flow and hot-flow test beds are not universal, are difficult to disassemble and assemble, are large in size, and cannot be installed in a high-modulus test run environment. The multi-component force test bed in engineering application has a complex structure and high cost, and can not meet the test requirements of high-speed alternating test engines. Therefore, in order to meet the high-frequency test requirements of various engines or advanced nozzles, the six-component test bed which is convenient to disassemble and assemble and adjustable in loading size is designed, thrust vector data are effectively measured, and the test cost and time are saved.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: in order to avoid frequent replacement of the test bed due to the size change of the engine or the spray pipe, the invention designs a novel adjustable six-component test bed which can be quickly assembled and disassembled in a narrow vacuum tank.
The purpose of the invention is realized as follows: comprises an installation platform, a movable frame, a portal frame and a servo mechanism. The mounting platform comprises a bottom plate and a rear baffle, the bottom plate is used for mounting the movable frame and the portal frame, the rear baffle is used for mounting the axial sensor baffle and bearing the axial thrust of the engine, the rear baffle is fixed on the bottom plate through bolts, and the rear baffle and the bottom plate are formed by splicing parts and are assembled and disassembled according to requirements. The movable frame comprises guide rail clamps, guide rails, box-type sliding blocks, bearing plates, an engine fixing frame, a movable frame baffle connecting piece, a sensor baffle and sensors, wherein four guide rail clamps are fixed on the bottom plate from bottom to top; along the axial, the engine fixed frame is connected with the movable frame baffle through four movable frame baffle connecting pieces, a gap reserved in the middle is used for installing a cold flow experiment air inlet, and the sensor baffle is installed on the rear baffle and is connected with the movable frame baffle through an axial sensor.
The portal frame comprises portal frame sliding rails, portal frame sliding blocks, portal frame fixing parts, a first portal frame, a second portal frame and a cross beam, the two portal frame sliding rails are fixed on the bottom plate in parallel, and the four portal frame sliding blocks can slide on the sliding rails and can also be locked by screws, so that the movement of the portal frame is limited. The four portal frame fixing parts are fixed on the sliding block and used for fixing a first portal frame and a second portal frame, and the first portal frame and the second portal frame are connected through two cross beams.
The servo mechanism comprises a servo mechanism fixing piece and an electric push rod, the servo mechanism fixing piece is fixed on the engine fixing frame, and the electric push rod is connected with the servo mechanism fixing piece through a hinge.
Furthermore, the rear baffle and the bottom plate are formed by splicing parts, threaded holes are drilled in the bottom plate and used for mounting a guide rail clamp of the movable frame, a portal frame guide rail and the like, and large holes are formed in the periphery of the bottom plate and used for fixing experiments.
Further, the engine fixing frame is formed by splicing square pipes through angle irons, the size of the engine fixing frame is configured according to the size of an engine, the square pipes are divided into an inner layer and an outer layer, the inner layer square pipes can stretch out and draw back in the outer layer square pipes, the engine fixing frame can be adjusted according to the size of the engine, the engine fixing frame is connected with two bearing plates through three sensors, the head of the engine fixing frame is one, and the tail of the engine fixing frame is two.
Furthermore, the first portal frame and the second portal frame are formed by splicing square pipes through angle irons and are axially fixed on four portal frame fixing pieces, the two portal frames are connected through a cross beam, the length of the cross beam can be adjusted, and the engine size is configured.
Furthermore, the engine fixing frame is connected with the portal frame through two transverse sensors and respectively positioned between the front side of the engine fixing frame and the first portal frame and between the rear side of the engine fixing frame and the second portal frame.
Furthermore, the movable frame baffle and the sensor baffle are connected by the axial sensor and fixed by bolts.
Furthermore, four servo mechanisms are respectively arranged at four corners of the engine fixing frame and used for controlling the swinging of the spray pipe.
Further, all sensors are tension-compression bidirectional force sensors.
The method for measuring the thrust vector by using the adjustable six-component test bed of the small solid rocket engine comprises the following steps:
s1), constructing a six-component force model; an O-XYZ rectangular coordinate system is constructed, an intersection point of an engine axis and a plane where a rear end face sensor is located is taken as a coordinate system origin O, the engine axis is taken as an X axis, a Y axis passes through the origin O to be vertically intersected with the X axis and to be parallel to a horizontal plane, and a Z axis passes through the origin O to be vertically intersected with the X axis and to be vertically directed to the ground; axial force F in X direction 6 In the Y direction with a transverse force F 4 、F 5 In the Z direction with a longitudinal force F 1 、F 2 、F 3 (ii) a The method comprises the following steps of (1) setting the pressure of a sensor to be positive and the tension to be negative;
s2), according to the six-component model, calculating the thrust vector of the engine through a space force system balance equation set; the space force system balance equation system is as follows:
in the formula F 1 、F 2 The unit is N for the force measurement value of a sensor connecting the tail end of the engine fixing frame and the bearing plate; f 3 The unit of the force measurement value of a sensor for connecting the front end of the engine fixing frame with the bearing plate is N; f 4 、F 5 The unit is N for the force measurement value of a sensor for connecting an engine fixing frame and a portal frame; f 6 The unit is N for the force measurement value of a sensor connecting the movable frame baffle and the sensor baffle;
F x 、F y and F z The components of vector thrust in X, Y, Z coordinate directions are respectively, and the unit of the quantity value is N; m x 、M y And M z The components of the resultant moment in X, Y, Z coordinate directions are respectively, the unit of the quantity value is N.m, and the positive direction is determined according to the right-hand spiral rule;
furthermore, the sensor needs to be calibrated before testing, and the weight is added and subtracted circularly by a quintile method to calibrate the sensor.
Furthermore, the first-order natural frequency of the engine obtained through simulation analysis is 150Hz, and the test run requirement of the engine is met.
Compared with the prior art, the invention has the beneficial effects that: the adjustable six-component test bed for the small rocket engine is convenient to assemble and disassemble, and can meet the experimental requirements of cold flow tests, heat flow tests, high-altitude test run simulation and other engine vector thrust performances. According to the adjustable six-component force test bed for the small rocket engine, the size of the engine fixing frame can be adjusted within a certain range, the experimental requirements of engines with different diameters and different spring lengths are met, and the cost is saved. According to the adjustable six-component force test bed for the small rocket engine, the gantry frame slides on the guide rail and can also be locked, and meanwhile, the cross beam can also be adjusted to be matched with the engine fixing frame. The adjustable six-component force test bed for the small solid rocket engine is provided with a servo device and is used for cold flow experiments and hot test of various swinging spray pipes.
Drawings
Fig. 1 is a schematic structural view of a six-component force test bed of a small rocket engine.
Fig. 2 is a schematic structural view of a mounting platform of a six-component force test bed of a small rocket engine.
Fig. 3 is a schematic structural view of the test bed moving frame of the present invention.
Fig. 4 is a schematic structural view of the test bed fixing frame of the present invention.
Fig. 5 is a schematic structural view of the test bed portal frame of the present invention.
Fig. 6 is a schematic structural diagram of a test bed servo mechanism of the present invention.
Fig. 7 is a schematic diagram of the six-component measurement vector thrust of the present invention.
Detailed Description
The invention is described in further detail below with reference to the drawings and the detailed description.
The present invention will be described in further detail with reference to the accompanying drawings and specific embodiments. It should be noted that, in the description of the present invention, except for the contact manner between each slider and the guide rail and between the electric push rod and the hinge, the other connections are all fixed connections.
A six-component test bed of a small solid rocket engine is shown in figure 1 in the whole structure and is used for measuring the vector force of the small solid rocket engine and comprises a mounting platform 100, a movable frame 200, a portal frame 300 and a servo mechanism 400.
The mounting platform 100 is used for mounting the movable frame 200 and the portal frame 300 and specifically comprises rear baffles 101 and 102 and two bottom plates 103 and 104, the rear baffles and the bottom plates are spliced by bolts, and the rear baffles 101 and 102 are fixed on the bottom plates 103 and 104 by bolts. The rear baffle is used for bearing axial thrust and is connected with the sensor baffle through bolts, and the movable frame 200 and the portal frame 300 are fixed on the bottom plates 103 and 104 through bolts.
The movable frame 200 is used for fixing a small solid rocket engine for experiments and specifically comprises a guide rail clamp 201, a guide rail 202, a box type sliding block 203, a bearing plate 204, a sensor 205, an engine fixing frame 206, a movable frame baffle connecting piece 207, a movable frame baffle 208 and a sensor baffle 209. Four guide rail clamps 201 are fixed on the bottom plates 103 and 104 by bolts; the number of the guide rails 202 is two, and the guide rails are fixed by a guide rail clamp 201; the number of the box-type sliding blocks 203 is four, two guide rails are respectively arranged on each guide rail, and the box-type sliding blocks 203 can freely slide on the guide rails 202; the two bearing plates 204 are fixed on the box-type sliding block 203 by bolts and are mainly used for fixing the sensor 205 and bearing longitudinal force; the number of the sensors 205 is six, three of the sensors are used for connecting the bearing plates 204 and the engine fixing frame 206 and bearing longitudinal force, wherein one end bearing plate is used, two tail bearing plates are used, two of the sensors are used for connecting the engine fixing frame and the portal frame 300 and bearing transverse force, the front and the back of each sensor are respectively used, and the last sensor is arranged between the movable frame baffle 208 and the sensor baffle 209 and bears axial force; the engine fixing frame 206 is used for fixing an engine required by an experiment; the four movable frame baffle connecting pieces 207 are used for connecting the engine fixing frame 206 and the movable frame baffle 208, and the reserved space in the middle is used for installing an air inlet of a cold flow experiment; the movable frame baffle 208 is connected to the movable frame baffle connecting piece through bolts; the sensor baffle 209 is connected to the moving frame baffle 208 by the sensor 205, and is fixed to the back baffle 110 by bolts to receive the axial thrust.
The gantry 300 is used for installing a side sensor, and the stability and safety of the structure are enhanced, and specifically comprises a gantry guide rail 301, a gantry slider 302, a gantry fixing member 303, a first gantry 304, a second gantry 305 and a beam 306. The two gantry guide rails 301 are fixed on the bottom plates 103 and 104 by bolts; the number of the gantry sliding blocks 302 is four, and two gantry guide rails are arranged on each gantry guide rail and can slide on the gantry guide rails 301; four gantry fixing pieces 303 are respectively fixed on the four gantry sliding blocks 302; the first gantry 304 is mounted on two gantry mounts near the tailgate, the second gantry 305 is mounted on two gantry mounts far from the tailgate, and the gantries 304 and 305 are used to mount side sensors; the two beams 306 are used for connecting the first gantry 304 and the second gantry 305.
The servo mechanism 400 is used for controlling the swinging of the nozzle and comprises a servo mechanism fixing part 401 and an electric push rod 402, wherein the servo mechanism fixing part 401 is fixed on the engine fixing frame 206, and the electric push rod is connected with the servo mechanism fixing part through a hinge.
Preferably, threaded holes are drilled in the bottom plates 103 and 104 for mounting a rear baffle, a guide rail clamp of a movable frame, a portal frame guide rail and the like, and large holes are formed in the periphery for fixing in an outdoor experiment.
Preferably, the engine fixing frame 206 is formed by splicing a square tube by angle iron, the square tube is divided into an inner layer and an outer layer, the inner layer square tube can be stretched in the outer layer square tube, and therefore the engine fixing frame can be adjusted according to the size of the engine, as shown in fig. 4. The engine fixing frame is connected with two bearing plates by three sensors, wherein the head part is one, and the tail part is two.
Preferably, the first portal frame 304 and the second portal frame 305 are formed by splicing square pipes through angle irons, are fixed on four portal frame fixing pieces 303 along the axial direction, are connected through a cross beam 306, and the cross beam 306 is formed by splicing an inner square pipe and an outer square pipe and can adjust the length according to requirements. The two portal frames can slide on the portal frame guide rail 301 through the sliding block 302 and can also be locked. Preferably, the servo mechanisms 400 are fixed at four corners of the engine fixing frame 206, and can control the movable section of the nozzle to realize full-axis swing.
Preferably, all sensors are tension-compression bidirectional force sensors, and the experiment requirements can be met.
In summary, the present invention provides a six component force test bed for small solid, liquid or hybrid rocket engine experiments. The test bed structurally comprises a mounting platform, a movable frame, a portal frame and a servo mechanism. The mounting platform comprises a rear baffle plate and a bottom plate; the movable frame comprises a guide rail clamp, a guide rail, a box-type sliding block, a bearing plate, a sensor, an engine fixing frame, a baffle plate connecting piece, a movable frame baffle plate and a sensor baffle plate; the portal frame comprises a slide rail, a portal frame slide block, a portal frame fixing piece, a first portal frame, a second portal frame and a cross beam; the servo mechanism comprises a servo mechanism fixing piece and an electric push rod. After the data measured by the force transducer is measured, a six-component model of a thrust vector is constructed, and then the vector force is calculated through a space force system balance equation set. The traditional six-component test bed only matches engines with fixed diameters and fixed bullet lengths, the size of a new rocket engine prototype with a new principle and a new form is faster to change, a fixing device of the engine and even the test bed are required to be changed, the experiment cost is increased, and the changing speed of the novel engine is reduced. The six-component test bed of the small solid rocket engine is convenient to disassemble and assemble, can be adjusted in size, is used for testing cold flow and heat flow of a novel engine, can also complete experimental research on various thrust vectoring spray pipes such as sub-supersonic separation line spray pipes, submerged spray pipes, secondary injection spray pipes and the like, and is suitable for different experimental conditions and scenes such as ground test and narrow vacuum pipes for simulating high-altitude test.
Claims (8)
1. The utility model provides a small-size rocket engine six component test-beds with adjustable which characterized in that: the device comprises an installation platform, a movable frame and a portal frame which are arranged on the installation platform, a servo mechanism arranged on the movable frame, and six sensors, wherein three sensors bear longitudinal force; two bear the horizontal force; the last one is subjected to axial forces.
2. An adjustable six-component force test bed for a small rocket engine according to claim 1, wherein: the mounting platform comprises a bottom plate and a rear baffle plate vertically arranged on the bottom plate.
3. An adjustable six-component test bed for small rocket engines, according to claim 2, wherein: the movable frame comprises guide rail clamps arranged on the bottom plate in pairs, a guide rail arranged between each pair of guide rail clamps, box type sliding blocks arranged on the guide rail, two force bearing plates arranged on the adjacent box type sliding blocks respectively, a first sensor and a second sensor arranged on the front end force bearing plate, a third sensor arranged on the rear end force bearing plate, an engine fixing frame arranged at the upper ends of the first sensor to the third sensor, a movable frame baffle arranged on the end face of the engine fixing frame through a movable frame baffle connecting piece, and a sensor baffle arranged on the rear baffle.
4. An adjustable six-component force test bed for a small rocket engine according to claim 3, wherein: the portal frame comprises a pair of portal frame guide rails arranged on the bottom plate, two portal frame sliding blocks arranged on each portal frame, and a square frame arranged on the portal frame sliding blocks, wherein the square frame is positioned outside the engine fixing frame, and two sensors bearing transverse force are positioned between the square frame and the engine fixing frame.
5. An adjustable six-component force test bed for small rocket engines according to claim 3 or 4, wherein: four servo mechanisms respectively arranged at four corners of the engine fixing frame for controlling the swinging of the spray pipe
6. An adjustable six-component force test bed for small rocket engines according to any of claims 1-4, wherein: all sensors are tension-compression bidirectional load cells.
7. An adjustable six-component test bed for small rocket engines according to any one of claim 5, wherein: all sensors are tension-compression bidirectional load cells.
8. The method for measuring the thrust vector of the adjustable small rocket engine six-component test bed is applied to any one of the claims 1 to 5, and is characterized in that:
s1, constructing a six-component force model; an O-XYZ rectangular coordinate system is constructed, the intersection point of the engine axis and the plane where the rear end face sensor is located is taken as a coordinate system origin O, the engine axis is taken as an X axis, a Y axis passes through the origin O and is perpendicularly intersected with the X axis and is parallel to the horizontal plane, and a Z axis passes through the origin O and is perpendicularly intersected with the X axis and is parallel to the horizontal planeThe passing origin O is vertically intersected with the X axis and vertically points to the ground; axial force F in X direction 6 In the Y direction with a transverse force F 4 、F 5 In the Z direction with a longitudinal force F 1 、F 2 、F 3 (ii) a The method comprises the following steps of (1) setting the pressure of a sensor to be positive and the tension to be negative;
s2, solving and calculating the thrust vector of the engine through a space force system balance equation set according to the six-component model; the space force system balance equation set is as follows:
in the formula F 1 、F 2 The unit is N for the force measurement value of a sensor connecting the tail end of the engine fixing frame and the bearing plate; f 3 The unit is N for the force measurement value of a sensor connecting the front end of the engine fixing frame and the bearing plate; f 4 、F 5 The unit of the force measurement value of a sensor for connecting the engine fixing frame and the portal frame is N; f 6 The unit is N for the force measurement value of a sensor connecting the movable frame baffle and the sensor baffle; f x 、F y And F z The components of vector thrust in X, Y, Z coordinate directions are respectively, and the unit of the quantity value is N; m x 、M y And M z The components of resultant moment in X, Y, Z coordinate directions are respectively, the unit of the quantity value is N.m, and the 'positive' direction is determined according to the right-hand spiral rule.
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| CN202210365534.9A CN115030839A (en) | 2022-04-07 | 2022-04-07 | Adjustable six-component test bed for small rocket engine |
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| CN202210365534.9A CN115030839A (en) | 2022-04-07 | 2022-04-07 | Adjustable six-component test bed for small rocket engine |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| KR101422259B1 (en) * | 2013-08-27 | 2014-07-28 | 아틱스엔지니어링(주) | Engine test equipment |
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| CN208537176U (en) * | 2018-08-01 | 2019-02-22 | 中发天信(北京)航空发动机科技股份有限公司 | Aircraft engine test stand frame |
| CN110220712A (en) * | 2019-06-24 | 2019-09-10 | 西北工业大学 | A kind of rocket engine propulsion test device |
| CN213274857U (en) * | 2020-10-28 | 2021-05-25 | 江西中发天信航空发动机科技有限公司 | Aeroengine test run rack |
-
2022
- 2022-04-07 CN CN202210365534.9A patent/CN115030839A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR101422259B1 (en) * | 2013-08-27 | 2014-07-28 | 아틱스엔지니어링(주) | Engine test equipment |
| CN208537176U (en) * | 2018-08-01 | 2019-02-22 | 中发天信(北京)航空发动机科技股份有限公司 | Aircraft engine test stand frame |
| 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 |
| CN110220712A (en) * | 2019-06-24 | 2019-09-10 | 西北工业大学 | A kind of rocket engine propulsion test device |
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