CN109974523B - Multi-nozzle rocket jet test system - Google Patents
Multi-nozzle rocket jet test system Download PDFInfo
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- CN109974523B CN109974523B CN201910229980.5A CN201910229980A CN109974523B CN 109974523 B CN109974523 B CN 109974523B CN 201910229980 A CN201910229980 A CN 201910229980A CN 109974523 B CN109974523 B CN 109974523B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F3/00—Rocket or torpedo launchers
- F41F3/04—Rocket or torpedo launchers for rockets
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B35/00—Testing or checking of ammunition
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Abstract
A multi-nozzle rocket jet test system comprising: the simulation rocket body, the test platform and the water spraying equipment for reducing noise and protecting the test platform; the overall sizes of the simulated arrow body and the test platform are designed according to the equal ratio of the actual structure size or linearly scaled, and the total water spraying flow of the water spraying equipment is k of the actual total water spraying flow 2 The water spraying speed is kept consistent with that of an actual product, the simulation arrow body is fixedly arranged on the test platform according to a preset test height and generates fuel gas during test, and the temperature, the pressure, the heat flow and the noise during the test process are collected through sensors arranged on the simulation arrow body and the test platform; and k is the ratio of the overall dimension of the simulated arrow body and the test platform to the actual structure dimension.
Description
Technical Field
The invention relates to a multi-nozzle rocket jet test system.
Background
The takeoff force thermal environment of the carrier rocket determines the safety of the carrier rocket, is also the basis of the design of a rocket system and the comprehensive protection system of each subsystem of the rocket system, and is the basis of the application of a new technology of the launch engineering of the carrier rocket.
The jet test system is a special test system which is specially used for researching the takeoff force thermal environment of the rocket before the launch of the carrier rocket. The prior jet test system only simulates jet noise in a free jet state, does not consider the disturbance effect of an actual ground emission system on the fuel flow or only adds a local obstacle, is mainly used for theoretical research, cannot reflect the noise environment of an arrow body and the ground emission system under the actual emission working condition, cannot guide the engineering design of the arrow body and the ground emission system, and has certain limitation.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the carrier rocket jet flow test system can be used for researching gas flow field distribution, noise field distribution, water spraying noise reduction effect, rocket body takeoff force thermal environment and launching system thermal protection performance in the rocket launching process.
The technical solution of the invention is as follows: a multi-nozzle rocket jet test system comprising: the simulation rocket body, the test platform and the water spraying equipment for reducing noise and protecting the test platform; the overall sizes of the simulated arrow body and the test platform are designed according to the equal ratio of the actual structure size or linearly scaled, and the total water spraying flow of the water spraying equipment is k of the actual total water spraying flow 2 The water spraying speed is kept consistent with that of an actual product, the simulation arrow body is fixedly arranged on the test platform according to a preset test height and generates fuel gas during test, and the temperature, the pressure, the heat flow and the noise during the test process are collected through sensors arranged on the simulation arrow body and the test platform; and k is the ratio of the overall dimension of the simulated arrow body and the test platform to the actual structure dimension.
Preferably, the test platform comprises a test bed base, a simulation launching platform and a test tool;
The upper surface of the test bed base is connected and fixed with the simulation launching bed and the test tool, and the load is transferred to the ground through the support legs of the test bed base; the test tool hoists the simulation rocket body at a preset height away from the fixed simulation launching platform; the test bed base is provided with a flow guide groove in advance and used for discharging and guiding high-temperature and high-pressure fuel gas generated by the engine, and the flow guide groove is linearly scaled according to the prototype size by a proportion k.
Preferably, the test tool comprises a portal frame, a spherical hinge or a flange and a steel wire rope;
one end of a symmetrical upright post combined portal frame is fixedly arranged on a base of the test bed, the upper end of a simulation arrow body is fixed by adopting a spherical hinge or a flange, and the spherical hinge or the flange is rigidly connected with the other end of the portal frame; the lower end of the simulation arrow body is fixed by an adjustable traction steel wire rope and is used for ensuring that the verticality of the simulation arrow body meets the test requirement.
Preferably, the water spraying equipment comprises a flow channel arranged inside the simulation launching platform and a spray head communicated with the flow channel and arranged on the upper surface of the simulation launching platform and the side surface of the diversion hole; the spray head positioned on the upper surface of the simulation launching platform ensures that the upper surface of the whole simulation launching platform is covered with water.
Preferably, the water outlet of the spray head on the upper surface of the simulated launch pad, which faces the upper surface of the launch pad, is fan-shaped and the direction of the water outlet is inclined downwards.
Preferably, the included angle between the water outlet direction and the horizontal plane is 10 +/-5 degrees.
Preferably, the included angle between the direction of the water outlet of the spray head positioned on the side surface of the flow guide hole and the horizontal plane is 27 +/-5 degrees.
Preferably, the height of the analog launching pad is adjustable.
Preferably, the test platform further comprises an upper positioning tool and a lower positioning tool; the lower positioning tool is matched with a flow guide hole in the simulation launching pad to determine the center of the simulation launching pad, the upper positioning tool is of a cylindrical structure with a certain height, and the bottom surface of the cylinder is a positioning datum plane; the upper surface of the lower positioning tool is provided with a groove with the shape consistent with that of the positioning reference surface; the simulation arrow body install the drum in, through the location reference surface with recess cooperation realizes simulation arrow body axis and simulation launching pad axis coincidence.
Preferably, the temperature, the pressure and the heat flow are acquired by a temperature sensor, a pressure sensor and a heat flow sensor which are arranged at the central position in the boundary of the core area of the gas flow of the boosting rocket engine, on the boundary of the core area of the gas flow of the core-grade rocket engine, on the wall of the core-grade diversion hole and on the wall of the boosting diversion hole.
Preferably, the boundary of the core area of the gas flow of the boosting rocket engine and the boundary of the core-level rocket engine gas flow core area are determined by a method for rapidly estimating the ablation range of the gas flow in the rocket launching process, and the method specifically comprises the following steps:
Determining the initial ablation range of the gas flow of the single-nozzle rocket in a free flight state according to the initial parameters of the single-nozzle rocket engine; the initial parameters comprise the diameter of a spray pipe, a preset expansion angle and a preset engine working pressure;
step two, according to the actual parameters of the single-nozzle rocket engine, correcting the initial ablation range in the step one to obtain a corrected ablation range;
step three, repeating the step one to the step two, and obtaining a corrected ablation range of the free-flight-state multi-nozzle rocket gas flow;
and step four, determining the boundary of the core area of the gas flow of the boosting rocket engine and the boundary of the core-level rocket engine according to the corrected ablation range and the simulated launching pad in the step two or the step three.
Preferably, the initial ablation range of the gas flow of the single-nozzle rocket in the free flight state is in a cone frustum shape; the cone angle of the truncated cone is half of the preset expansion angle, the value range of the preset expansion angle is 6-8 degrees, the diameter of the smaller end face of the truncated cone is the diameter of the spray pipe, and the height L of the truncated cone is equal to the height L of the spray pipe a The value range of (a) is 65-120 times of the diameter of the spray pipe.
Preferably, the engine parameter in the second step is an engine working pressure, and when the engine working pressure is less than or equal to a preset engine working pressure in the initial parameter in the first step, the initial ablation range is equal to the corrected ablation range; otherwise, increasing the preset expansion angle in the initial parameter in the step I to obtain a corrected ablation range;
The value range of the preset engine working pressure is 1.15-1.25 times of the engine working pressure.
Preferably, temperature sensor, pressure sensor and heat flow sensor install on a lateral wall of power and heat environment combination detecting element box, and temperature sensor, pressure sensor and heat flow sensor's sensitive end homoenergetic direct contact outside gas stream, the amplifier of temperature sensor, pressure sensor and heat flow sensor rear end all is located power and heat environment detecting element box.
Preferably, a jet flow noise test array is arranged at the to-be-detected part of the carrier rocket, and jet flow noise of the simulated rocket body is detected by a noise sensor on the array in a near field mode; the part to be detected comprises an arrow body and/or a transmitting system.
Preferably, the part to be detected further comprises a launching field plateau high-altitude area which takes the arrow body as the center, is positioned outside the gas impact range and is higher than the arrow body; and a plurality of groups of linear arrays are arranged in the area, and the number of noise sensors on each group of linear arrays is not less than 6.
Preferably, the jet noise test array arranged on the arrow body comprises an axial linear array arranged along the height direction of the arrow body and/or an annular array arranged along the circumferential direction of the arrow body fairing; the jet flow noise test array arranged on the launching system comprises a linear array or a matrix array arranged along the height direction of an umbilical tower or a service tower of the launching system and/or an array arranged at the position of a peripheral water spray nozzle of the launching platform.
Compared with the prior art, the invention has the beneficial effects that:
the prior art generally only simulates jet flow noise in a free jet flow state, does not consider the disturbance effect of a ground emission system on emitted gas flow, and cannot accurately simulate a gas flow field, a noise field and a thermodynamic environment condition under an actual emission working condition. Compared with the prior art, the invention fully considers the influence of the actual ground launching system, ensures the full similarity between the jet flow test system and the original carrier rocket system, can research the gas flow field distribution, the noise field distribution, the water spraying noise reduction effect, the rocket body takeoff force thermal environment and the launching system thermal protection performance in the actual launching process of the carrier rocket, and can provide full support for the engineering design of subsequent products.
The jet flow test system comprises a simulation rocket body, a simulation launching platform, a diversion trench and water spraying noise reduction equipment, and sufficient similarity is kept, so that the similarity of a gas flow field and a noise field is ensured, and the accuracy and credibility of test data are ensured;
the invention can ensure the impact angle of the gas flow through corresponding adjustment links, further ensure the similarity of the gas flow field, and ensure the safety of the test through fixing the tail section of the rocket body.
The test system has the function of water spraying and noise reduction, simultaneously the water spraying flow, the water spraying speed, the water spraying angle and the water curtain shape are similar to those of the original product, and the influence of the factors such as the water spraying flow, the water spraying speed and the like on the emission noise can be researched.
The relative positions of all components of the test system are adjustable, and the impact height of the gas flow and the position of the rocket body relative to the core-level diversion hole can be further ensured through adjustment of the assembly link, so that the similarity of the gas flow field is ensured.
According to the invention, by reasonably arranging the pressure, temperature and heat flow detection areas, the arrangement positions and the arrangement number of the array sensors can be greatly reduced, and the field construction workload and the protection workload are reduced; meanwhile, the sound vibration coupling damage of the strong noise of the gas flow to the detection sensor and the electric components of the front-end amplifier is reduced.
Drawings
FIG. 1 is a schematic diagram of the system of the present invention;
FIG. 2 is a schematic view of the installation and fixation of a simulated rocket according to the present invention;
FIG. 3 is a schematic view of different takeoff heights of the simulated rocket body according to the invention;
FIG. 4 is a schematic view of the flow channel in the upper stage body of the simulation launching stage according to the present invention;
FIG. 5 is a schematic view of an arrow body positioning arrangement of the present invention;
FIG. 6 is a schematic diagram of an exemplary positioning scheme for an analog launch pad;
FIG. 7 is a schematic view of a simulated rocket test sensor mount according to the present invention;
in the figure, 1-the test stand base; 2-simulating a launching pad; 3-water spraying equipment; 4-simulating arrow body; 5-testing the tool; 6-gantry column; 7-a portal frame; 8-spherical hinge; 9-adjustable drawing of the steel wire rope; 10-upper table body; 11-a support arm; 12-an inner flow passage; 13-a water supply inlet; 14-mounting a positioning tool; 15-lower positioning tool 16-upper surface of the test bed base; 17-simulation launching platform supporting legs 18-annular mounting rack; 19-longitudinal mounting.
Detailed Description
The invention is described in detail below with reference to the figures and examples.
1) The outline of the jet flow test system is similar to that of the original carrier rocket and launching support system
In order to ensure that the gas flow field, the take-off force thermal environment and even the noise field distribution, the water spraying noise reduction effect and the thermal protection performance of the launching system are consistent with those of an actual carrier rocket and a launching support system, the outline of the jet flow test system is required to keep sufficient similarity with that of an actual product. Meanwhile, the water spraying flow and the water spraying speed of the water spraying noise reduction system are matched with those of the test system. In order to reduce the jet flow test scale, on the premise of meeting the similarity of a gas flow field and a take-off force thermal environment, the structural size of the test system can be subjected to linear scaling (the scaling coefficient is k), the total water spray flow of the test system is subjected to linear proportional square scaling, and the water spray speed is consistent with that of a prototype. Of course, under some test environments, the test system structure size can also be linearly scaled.
2) The test platform has the functions of platform body support and gas discharge and guide
The test platform comprises a test bed base 1, a simulation launching platform 2 and a test tool 5; referring to the attached drawing 1, the upper surface of a test bed base 1 is fixedly connected with a simulation launching platform 2 and a test tool 5 through bolts, and loads are transmitted to the ground through four support legs of the test bed base 1; the test tool hoists the simulation rocket body at a preset height away from the fixed simulation launching platform; the test bed base is provided with a flow guide groove in advance and used for discharging and guiding high-temperature and high-pressure fuel gas generated by the engine. And the diversion trench is linearly scaled according to the prototype size by the proportion k.
3) Simulation rocket body is reliably installed fixedly
Referring to the attached figure 2, the simulation rocket body 4 is fixedly installed through a three-column combined portal frame (a portal frame column 6; a portal frame 7). The upper end of the simulation rocket body 4 is fixed by a spherical hinge 8 or a flange, the lower end of the simulation rocket body is fixed by an adjustable traction steel wire rope 9, and the phenomenon that the tail of the rocket body shakes greatly due to the fact that the thrust of an engine is eccentric is avoided.
In addition, in order to ensure that the verticality of the simulated rocket body 4 meets the test requirements, the spatial position of the tail of the rocket body can be accurately adjusted by adjusting the length of the adjustable traction steel wire rope 9, so that the verticality of the simulated rocket body 4 is adjusted.
4) Simulation arrow body height is adjustable
Referring to fig. 3, gantry columns 6 of different heights are preset. According to the test requirements, the portal frame upright post 6 with the corresponding height is replaced for different working conditions of the rocket body takeoff height so as to simulate the rocket gas flow field, the power-heat environment and the noise field under different takeoff heights.
5) Built-in runner of upper table body of analog launching table
Referring to fig. 4, a flow passage 12 is arranged in the upper table body of the simulation launching table, water is introduced from a water supply inlet 13 and is sprayed out by spray heads distributed on the upper surface of the upper table body and on the side surfaces of the diversion holes.
The spray head on the upper surface of the table body is used for protecting the upper surface structure of the simulation launching table 2, and the included angle between the water outlet direction and the horizontal plane is 10 +/-5 degrees; the spray heads at the side surfaces of the flow guide holes are used for protecting the side wall structure of the flow guide hole 2 of the simulation launching pad, and the included angle between the water outlet direction of the spray head at the side surface of the flow guide hole and the horizontal plane is 27 +/-5 degrees.
6) Accurate positioning of rocket body relative to simulation launching platform
Referring to fig. 5, the positioning tool is used to complete the precise positioning of the simulated rocket body 4 relative to the simulated launching platform 2. The positioning tool is divided into two parts: an upper positioning tool 14 and a lower positioning tool 15. The upper positioning tool 14 is arranged at the tail end of the arrow body and is tightly matched with the outer surface of the arrow body; the lower positioning tool 15 is arranged in a core-level diversion hole of the upper table body 10 of the simulation launching platform and is tightly matched with the inner surface of the core-level diversion hole.
The upper surface of the lower positioning tool 15 is finely processed into a convex round surface or a concave round table with the same size as the bottom surface of the upper positioning tool 14. When the convex round surface is superposed with the bottom surface of the upper positioning tool 14, the simulated rocket body 4 and the core-level diversion hole of the simulated launching platform 2 are proved to finish centering adjustment; when the positions are not overlapped, the position of the simulation launching platform 2 is correspondingly adjusted until the convex circular surface is overlapped with the bottom surface of the upper positioning tool 4.
7) Accurate positioning of platform body relative to diversion trench
Referring to the attached figure 6, four raised flanges are preset on the upper surface 16 of the base of the test bed, and the relative positions and sizes of the raised flanges are consistent with those of the flanges on the bottom surfaces of the supporting legs 17 of the launching pad. When the simulation launching pad 2 is installed, the position of the simulation launching pad is adjusted to ensure that the flange on the bottom surface of the landing leg 17 of the launching pad coincides with the flange on the upper surface 16 of the base of the test bed.
8) Test sensor mounting rack is reserved to arrow body outside
Referring to fig. 7, two types of test sensor mounting brackets are mounted on the outer side of the arrow body: a circumferential mounting 18, a longitudinal mounting 19. The annular mounting rack 18 is arranged at the position of the simulation rocket body fairing, and the longitudinal mounting rack 19 is axially fixed along the simulation rocket body. The position of the sensor mounting frame can be adjusted according to the test requirement.
9) Test system device, test and height adjustment
Referring to fig. 1-7, the test system was assembled.
Firstly, a test bed base 1 is installed and fixed on a preset test terrace, and base supporting legs are connected and fastened with terrace foundation bolts; then hoisting the simulation launching pad 2 to the test bed base 1 to ensure that the bottom flange of the launching pad supporting leg 17 is superposed and aligned with the flange of the upper surface 16 of the test bed base; then three portal frame columns 6 are installed to finish the rough alignment of the portal frame columns and the upper surface of the test bed base; then, connecting the simulated arrow body 4 with a spherical hinge 8 of a portal frame 7; then integrally hoisting the portal frame 7 and the simulated rocket body 4 combination above the portal frame upright 6 to complete connection and fixation; and finally, an adjustable traction steel wire rope 9 is installed at the tail of the simulation arrow body, the length of the steel wire rope is adjusted, and the self-perpendicularity adjustment and fixation of the arrow body are completed.
And (3) carrying out a jet flow test, wherein the test system sends a water spraying signal and an ignition signal according to a preset time sequence, the simulated rocket body 4 engine starts to ignite, and gas flow is continuously generated until the explosive column is completely combusted.
And replacing the portal frame stand columns with different heights according to subsequent test requirements, and completing jet flow test simulation under different takeoff heights.
10) Pressure, temperature, heat flow and noise measurement in test process
Pressure, temperature, heat flow measurements
The temperature, the pressure and the heat flow are acquired by a temperature sensor, a pressure sensor and a heat flow sensor which are arranged at the central position in the boundary of the core area of the gas flow of the boosting rocket engine, on the boundary of the core-level rocket engine gas flow core area, on the wall of the core-level diversion hole and on the wall of the boosting diversion hole. In order to increase the integrity and reliability of data, a sensor can be arranged in a gas flow spreading area on the surface of the simulated launching pad. The gas flow spreading area of the launching platform table top is a gas flow impact area in which gas splashes outwards after being disturbed by relevant structures of the simulated launching table and the diversion trench or spreads along the diversion trench wall of the simulated launching table top, and ablation removal strength is greatly reduced compared with that of a core area.
The boundary of the core area of the gas flow of the boosting rocket engine and the boundary of the core-level rocket engine gas flow core area are determined by a method for rapidly estimating the ablation range of the gas flow in the rocket launching process, and the method specifically comprises the following steps:
step 101, according to initial parameters of a single-nozzle rocket engine, including the diameter of a nozzle, a preset expansion angle and a preset engine working pressure; determining the initial ablation range of the gas flow of the single-nozzle rocket in the free flight state; the initial ablation range of the gas flow of the single-nozzle rocket in the free flight state is in a cone frustum shape. The cone angle of the truncated cone is half of the preset expansion angle, the value range of the preset expansion angle is 6-8 degrees, the diameter of the smaller end face of the truncated cone is the diameter of the spray pipe, and the height L of the truncated cone is equal to the height L of the spray pipe a The value range of (a) is 65-120 times of the diameter of the spray pipe.
102, according to parameters of a single-nozzle rocket engine, including the working pressure of the engine; the initial ablation range described in the correction step 101 results in a corrected ablation range. When the working pressure of the engine is less than or equal to the preset working pressure of the engine in the initial parameter in the step one, the initial ablation range is equal to the correction ablation range; otherwise, adjusting the preset expansion angle in the initial parameters in the step one to obtain a corrected ablation range;
the value range of the preset engine working pressure is 1.15-1.25 times of the engine working pressure.
103, repeating the steps 101 to 102, and geometrically superposing the corrected ablation ranges of the multiple free-flight-state single-nozzle rocket gas flows to obtain the corrected ablation range of the free-flight-state multi-nozzle rocket gas flows.
And step 104, determining the boundary of the core area of the gas flow of the boosting rocket engine and the boundary of the core-level rocket engine gas flow core area through the geometric relationship according to the corrected ablation range, the structural size and the position of the launching platform 5 and the structural size and the position of the diversion trench 8 in the step 102 or the step 103.
Temperature sensor, pressure sensor and heat flow sensor install on a lateral wall of power and heat environment combination detecting element box, and temperature sensor, pressure sensor and heat flow sensor's sensitive end homoenergetic direct contact outside gas stream, the amplifier of temperature sensor, pressure sensor and heat flow sensor rear end all is located power and heat environment detecting element box is interior. Of course, the acceleration and the strain can also be measured through experiments according to different measurement requirements. And an acceleration sensor and a strain sensor are additionally arranged on one side wall of the force-heat environment combined detection unit box, and the sensitive ends and the rear end amplifiers of the acceleration sensor and the strain sensor are positioned in the force-heat environment combined detection unit box. The number of any sensors in the combined force and heat environment detection unit box is optimally more than or equal to 2.
Noise detection
The jet flow noise test array is arranged on the to-be-detected part of the carrier rocket, and the jet flow noise of the simulated rocket body is detected by a noise sensor on the array in a near field mode; the part to be detected comprises an arrow body and/or a transmitting system. In order to increase the detection accuracy, the part to be detected also comprises an emitting field plateau high-altitude area which takes the arrow body as the center, is positioned outside the gas impact range and is higher than the arrow body; and a plurality of groups of linear arrays are arranged in the area, and the number of noise sensors on each group of linear arrays is not less than 6.
The jet flow noise test array arranged on the arrow body comprises an axial linear array arranged along the height direction of the arrow body and/or an annular array arranged along the circumferential direction of the arrow body fairing; the sensor sensitive heads on the axial linear array are on the same straight line and are parallel to the axis of the arrow body. At least 4 groups of axial linear arrays are arranged along the circumference of the arrow body, and the number of each group of noise sensors is not less than 6. The sensor sensitive heads of the annular array are positioned on the same reference circle, and the circular surface is vertical to the axis of the arrow body. The annular array is arranged along the axial direction of the arrow body for at least 2 groups, and the number of each group of noise sensors is not less than 4. The jet flow noise test array arranged on the arrow body is distributed on the surface of the arrow body or distributed outside the arrow body. When the jet flow noise test array is distributed outside the arrow body, the radial clearance from the arrow body is not less than 0.25 times of the diameter of the nozzle.
The jet flow noise test array arranged on the launching system comprises a linear array or a matrix array arranged along the height direction of an umbilical tower or a service tower of the launching system and/or an array arranged at the peripheral water spray nozzle position of the launching platform. When the array is arranged at the position of the water spraying nozzles on the periphery of the launching platform, the array also comprises an array which is circumferentially arranged on the launching platform, and the sensor sensitive heads on the array which is circumferentially arranged on the launching platform are symmetrically distributed along the center of the launching platform and are parallel to the upper surface of the launching platform.
The umbilical tower or the service tower is arranged on the tower surface or outside the tower along a linear array or a matrix array arranged in the height direction. The radial clearance between the noise test array arranged outside the tower and the tower body is not less than 0.25 times of the diameter of the nozzle. The sensitive heads of the noise sensors on the linear array or the matrix array arranged in the height direction of the umbilical tower or the service tower are on the same plane and are parallel to the axis of the arrow body, and the sensitive heads face the arrow body.
The invention has not been described in detail in part of its common general knowledge to those skilled in the art.
Claims (12)
1. Many spray tubes rocket jet test system, its characterized in that includes: the simulation rocket body, the test platform and the water spraying equipment for reducing noise and protecting the test platform; the overall sizes of the simulated arrow body and the test platform are linearly scaled according to the actual structure size, and the total water spraying flow of the water spraying equipment is k of the actual total water spraying flow 2 The water spraying speed is kept consistent with that of an actual product, the simulation arrow body is fixedly arranged on the test platform according to a preset test height and generates fuel gas during test, and the temperature, the pressure, the heat flow and the noise during the test process are collected through sensors arranged on the simulation arrow body and the test platform; k is the ratio of the overall dimensions of the simulated arrow body and the test platform to the actual structural dimension;
the test platform comprises a test bed base, a simulation launching platform and a test tool; the upper surface of the test bed base is connected and fixed with the simulation launching bed and the test tool, and the load is transferred to the ground through the support legs of the test bed base; the test tool hoists the simulation rocket body at a preset height away from the fixed simulation launching platform; the test bed base is provided with a diversion trench for discharging high-temperature and high-pressure fuel gas generated by an engine, and the diversion trench is linearly scaled according to the prototype size by a proportion k;
the test tool comprises a portal frame, a spherical hinge or a flange and a steel wire rope; one end of a symmetrical upright post combined portal frame is fixedly arranged on a base of the test bed, the upper end of a simulation arrow body is fixed by adopting a spherical hinge or a flange, and the spherical hinge or the flange is rigidly connected with the other end of the portal frame; the lower end of the simulation arrow body is fixed by an adjustable traction steel wire rope and is used for ensuring that the verticality of the simulation arrow body meets the test requirement;
Two types of test sensor mounting racks are installed on the outer side of the simulation rocket body: the annular mounting frame and the longitudinal mounting frame are arranged; the annular mounting rack is mounted at the position of the simulated rocket body fairing, and the longitudinal mounting rack is axially fixed along the simulated rocket body.
2. The system of claim 1, wherein: the water spraying equipment comprises a flow channel arranged in the simulation launching platform and a spray head which is communicated with the flow channel and is arranged on the upper surface of the simulation launching platform and the side surface of the diversion hole; the spray head positioned on the upper surface of the simulation launching platform ensures that the upper surface of the whole simulation launching platform is covered with water.
3. The system of claim 2, wherein: the spray head positioned on the upper surface of the simulation launching platform is in a fan shape facing a water outlet on the upper surface of the launching platform, and the direction of the water outlet is inclined downwards.
4. The system of claim 3, wherein: the included angle between the water outlet direction and the horizontal plane is 10 +/-5 degrees.
5. The system of claim 2, wherein: the included angle between the direction of the water outlet of the spray head on the side surface of the flow guide hole and the horizontal plane is 27 +/-5 degrees.
6. The system of claim 1, wherein: the height of the simulation launching pad is adjustable.
7. The system according to claim 1 or 6, characterized in that: the test platform further comprises an upper positioning tool and a lower positioning tool; the lower positioning tool is matched with a flow guide hole in the simulation launching pad to determine the center of the simulation launching pad, the upper positioning tool is of a cylindrical structure with a certain height, and the bottom surface of the cylinder is a positioning datum plane; the upper surface of the lower positioning tool is provided with a groove with the shape consistent with that of the positioning reference surface; the simulation arrow body install the drum in, through the location reference surface with recess cooperation realizes simulation arrow body axis and simulation launching pad axis coincidence.
8. The system of claim 1, wherein: the temperature, the pressure and the heat flow are acquired by temperature sensors, pressure sensors and heat flow sensors which are arranged at the central position in the boundary of the core area of the gas flow of the boosting rocket engine, on the boundary of the core-level rocket engine gas flow core area, on the wall of the core-level flow guide hole and on the wall of the boosting flow guide hole.
9. The system of claim 8, wherein: temperature sensor, pressure sensor and heat flow sensor install on a lateral wall of power and heat environment combination detecting element box, and temperature sensor, pressure sensor and heat flow sensor's sensitive end homoenergetic direct contact outside gas stream, the amplifier of temperature sensor, pressure sensor and heat flow sensor rear end all is located power and heat environment combination detecting element box is interior.
10. The system of claim 1, wherein: a jet flow noise test array is arranged on a to-be-detected part of the rocket, and jet flow noise of a simulated rocket body is detected by a noise sensor on the array in a near field mode; the part to be detected comprises an arrow body and/or a transmitting system.
11. The system of claim 10, wherein: the part to be detected also comprises an upper air area of the launching field level, the upper air area takes the arrow body as the center, is positioned outside the gas impact range and is higher than the arrow body; and a plurality of groups of linear arrays are arranged in the area, and the number of noise sensors on each group of linear arrays is not less than 6.
12. The system of claim 10, wherein: the jet flow noise test array arranged on the arrow body comprises an axial linear array arranged along the height direction of the arrow body and/or an annular array arranged along the circumferential direction of the arrow body fairing; the jet flow noise test array arranged on the launching system comprises a linear array or a matrix array arranged along the height direction of an umbilical tower or a service tower of the launching system and/or an array arranged at the position of a peripheral water spraying nozzle of the launching platform.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201910229980.5A CN109974523B (en) | 2019-03-26 | 2019-03-26 | Multi-nozzle rocket jet test system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910229980.5A CN109974523B (en) | 2019-03-26 | 2019-03-26 | Multi-nozzle rocket jet test system |
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| CN111562189B (en) * | 2020-05-31 | 2022-06-28 | 太原理工大学 | Ultrahigh-temperature gas jet erosion test device for diversion trench material |
| CN111795828B (en) * | 2020-06-05 | 2022-06-03 | 湖北航天技术研究院总体设计所 | Horizontal simulation launch test device and method |
| CN112326868A (en) * | 2020-11-09 | 2021-02-05 | 北京航天发射技术研究所 | Temperature measurement method and temperature measurement device based on integral metal structure |
| CN113074065B (en) * | 2021-04-06 | 2022-04-01 | 北京航天发射技术研究所 | Power system for comprehensive research of heat transfer multiphase flow noise |
| CN113188819B (en) * | 2021-04-12 | 2022-08-23 | 北京航天发射技术研究所 | Rocket launching water spraying noise reduction effect evaluation method |
| CN113482800B (en) * | 2021-07-19 | 2022-03-11 | 西安航天动力试验技术研究所 | Fuel gas guide plate based on film vaporization cooling principle and use method thereof |
| CN113804818B (en) * | 2021-08-26 | 2023-10-20 | 西安近代化学研究所 | Rapid baking and burning test device for warhead and use method |
| CN114543583B (en) * | 2022-04-28 | 2022-07-15 | 成都航天万欣科技有限公司 | Precision adjusting device and method for storage and transportation launching box |
| CN116629028B (en) * | 2023-07-19 | 2023-09-22 | 东方空间技术(山东)有限公司 | Method and device for determining parameters of flow guide groove of petal-shaped launching pad |
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