CN109974523A - Multi nozzle rocket jet pilot system - Google Patents
Multi nozzle rocket jet pilot system Download PDFInfo
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- CN109974523A CN109974523A CN201910229980.5A CN201910229980A CN109974523A CN 109974523 A CN109974523 A CN 109974523A CN 201910229980 A CN201910229980 A CN 201910229980A CN 109974523 A CN109974523 A CN 109974523A
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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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- General Engineering & Computer Science (AREA)
- Testing Of Engines (AREA)
Abstract
Multi nozzle rocket jet pilot system, comprising: simulate rocket body, test platform and for reducing noise and the sprinkler of protection test platform；The contour dimension for simulating rocket body and test platform designs or carries out linear scale according to practical structures size grade ratio, and the water spray total flow of sprinkler is the k of practical water spray total flow2Times, water-jet velocity is consistent with actual product, simulation rocket body is packed on test platform according to preset test height, and generates combustion gas in test, temperature, pressure, hot-fluid, noise during being tested by the sensor acquisition being mounted on simulation rocket body and test platform；The k is the ratio for simulating the contour dimension and practical structures size of rocket body and test platform.
Description
Technical field
The present invention relates to a kind of multi nozzle rocket jet pilot systems.
Background technique
Carrier rocket power thermal environment of taking off decides that carrier rocket safety and rocket system and its each subsystem are comprehensive
The foundation of guard system design, the even more basis of carrier rocket transmitting engineering technology application.
Jet test system is taken off the special test system of power thermal environment before carrier rocket transmitting dedicated for exploration rocket
System.Previous jet test system usually only simulates the jet noise under free jet state, does not consider actual ground transmitting system
It unites to the disturbance effect of combustion gas stream or partial blockage object is only added, test data is chiefly used in theoretical research, cannot reflect reality
Emit the rocket body and ground launch system noise environment under operating condition, the engineering design of rocket body Yu ground launch system can not be instructed,
With certain limitation.
Summary of the invention
Technology of the invention solves the problems, such as: proposing a kind of carrier rocket jet test system, can be used in exploration rocket
Gas flow field distribution in emission process, noise field distribution, water spray noise reduction effect and rocket body take off power thermal environment and emission system
Thermal protective performance.
The technical solution of the invention is as follows: multi nozzle rocket jet pilot system, comprising: simulation rocket body, test platform
And for reducing noise and the sprinkler of protection test platform；The contour dimension of rocket body and test platform is simulated according to reality
Structure size etc. is the k of practical water spray total flow than designing or carrying out linear scale, the water spray total flow of sprinkler2Times,
Water-jet velocity is consistent with actual product, and simulation rocket body is packed on test platform according to preset test height, and is being tried
Combustion gas is generated when testing, temperature, pressure during testing by the sensor acquisition being mounted on simulation rocket body and test platform
Power, hot-fluid, noise；The k is the ratio for simulating the contour dimension and practical structures size of rocket body and test platform.
Preferably, the test platform includes test sewing platform base, analog transmissions platform, test tool；
The testing stand pedestal upper surface is connected and fixed analog transmissions platform and test tool, and passes through test sewing platform base
Supporting leg is by load transmission to ground；Test tool is lifted on rocket body is simulated at fixed-analog transmitting station preset height；Examination
It tests sewing platform base and presets diversion trench, for arranging the high-temperature high-pressure fuel gas for leading engine generation, the diversion trench is carried out by prototype size
The linear scale of ratio k.
Preferably, the test tool includes portal frame, flexural pivot or flange, wirerope；
Symmetrical column combination portal frame one end is packed on test sewing platform base, and simulation rocket body upper end uses flexural pivot or flange
It is fixed, the other end rigid connection of flexural pivot or flange and the portal frame；The lower end for simulating rocket body utilizes adjustable drawing steel wire
Rope is fixed, for guaranteeing that the verticality for simulating rocket body meets test requirements document.
Preferably, the sprinkler includes the runner being arranged in inside analog transmissions platform and connects with the runner
The logical sprinkler composition for being mounted on analog transmissions platform upper surface and deflector hole side；Spray head positioned at analog transmissions platform upper surface is protected
Demonstrate,prove entire analog transmissions platform upper surface covering water.
Preferably, the water outlet of the spray head face transmitting station upper surface positioned at analog transmissions platform upper surface is sector
And water outlet direction is obliquely.
Preferably, 10 ± 5 ° of angle of the water outlet direction and horizontal plane.
Preferably, described positioned at the nozzle delivery port direction of deflector hole side and 27 ± 5 ° of of angle of horizontal plane
Preferably, the analog transmissions platform height is adjustable.
Preferably, the test platform further includes upper positioning tool, lower positioning tool；Lower positioning tool and analog transmissions
Deflector hole cooperation on platform, determines the center of analog transmissions platform, and upper positioning tool is the cylindrical structure with certain altitude, cylinder
Bottom surface be positioning reference plane；The lower positioning tool upper surface setting and the consistent groove of positioning reference plane shape；
Simulation rocket body is mounted in the cylinder, realizes simulation rocket body axis by positioning reference plane and the groove cooperation
It is overlapped with analog transmissions platform axis.
Preferably, the temperature, pressure, hot-fluid are by being laid in booster rocket engine combustion gas stream core space boundary
Center, on core grade rocket engine combustion gas stream core space boundary, on core grade water conservancy diversion hole wall, the temperature on boosting water conservancy diversion hole wall
Degree sensor, pressure sensor and heat flow transducer collect.
Preferably, the booster rocket engine combustion gas stream core space boundary, core grade rocket engine combustion gas stream core
Area boundary is determined using rocket launching process combustion gas stream ablation range rapid Estimation method, is specifically comprised the following steps:
Step 1: determining free flight state single spraying pipe rocket combustion gas according to the initial parameter of single spraying pipe rocket engine
Flow initial ablation range；The initial parameter includes jet size, default divergence cone angle, default engine operation pressure；
Step 2: according to the actual parameter of single spraying pipe rocket engine, initial ablation range described in amendment step one
Obtain amendment ablation range；
Step 3: repeatedly step 1 is to step 2, the amendment ablation of the state of flight that gains freedom multi nozzle rocket combustion gas stream
Range；
Step 4: amendment ablation range, analog transmissions platform according to step 2 or step 3 determine booster rocket
Engine gas stream core space boundary and core grade rocket engine combustion gas stream core space boundary.
Preferably, the free flight state single spraying pipe rocket combustion gas stream initial ablation range is truncated cone；The circle
The cone angle of frustum is the half of the default divergence cone angle, and the value range of the default divergence cone angle is 6 °~8 °, the frustum of a cone
Lesser end face diameter is jet size, the height L of the frustum of a coneaValue range be 65~120 times of jet size.
Preferably, engine parameter described in step 2 is engine operation pressure, when the engine operation pressure
When less than or equal to default engine operation pressure in initial parameter described in step 1, initial ablation range is equal to amendment ablation
Range；Otherwise increase the default divergence cone angle in initial parameter described in step 1, obtain amendment ablation range；
The engine operation pressure that the value range of the default engine operation pressure is 1.15~1.25 times.
Preferably, the temperature sensor, pressure sensor and heat flow transducer are mounted on the combination inspection of power thermal environment
It surveys in the one side wall of unit box, and the sensitive end of temperature sensor, pressure sensor and heat flow transducer can directly connect
Outer combustion gas stream is touched, the amplifier of temperature sensor, pressure sensor and heat flow transducer rear end is respectively positioned on the hot ring of the power
In the detection unit box of border.
Preferably, by installing jet noise hot-wire array at carrier rocket position to be detected, pass through the noise on array
Sensor detects the jet noise of simulation rocket body by way of near field；The position to be detected includes rocket body and/or transmitting system
System.
Preferably, the position to be detected further includes the high empty region of launching level ground, and the region is centered on rocket body, and position
Except combustion gas impact range, highly it is higher than rocket body；Multiple groups linear array, making an uproar in every group of linear array are set in the area
Sonic transducer is no less than 6.
Preferably, the jet noise hot-wire array installed on the rocket body includes the axial direction that rocket body is arranged along short transverse
The annular array that linear array and/or rocket body radome fairing are circumferentially arranged；The jet noise hot-wire array packet installed in emission system
Include the linear array or matrix array and/or flat pad periphery that emission system umbilical tower or service tower are arranged in the height direction
The array of spray nozzle location arrangements.
The present invention has the beneficial effect that compared with prior art
The prior art generally only simulates the jet noise under free jet state, does not consider that ground launch system fires transmitting
The disturbance effect of air-flow, cannot gas flow field, noise field and power thermal environment condition under accurate simulation actual transmission operating condition.This
Compared with prior art, the influence to actual ground emission system is fully considered for invention, guarantee jet test system with
Abundant similitude between former booster system can study the gas flow field distribution during carrier rocket actual transmission, make an uproar
Sound-filed simulation, water spray noise reduction effect and rocket body take off power thermal environment and emission system thermal protective performance, can be subsequent product
Engineering design provide adequately support.
Jet test system of the present invention includes simulation rocket body, analog transmissions platform, diversion trench and water spray noise reducing apparatus, and is protected
Sufficient similitude is held, to guarantee the similitude of gas flow field, noise field, it is ensured that the accuracy and credibility of test data；
The present invention can be further ensured that combustion gas stream by corresponding adjustment link to guarantee the angle of attack of combustion gas stream
The similitude of field, furthermore passes through the fixation to rocket body endpiece, the safety of guarantee test.
Pilot system of the present invention has water spray decrease of noise functions, while spray flow, water-jet velocity, water spray angle, water curtain shape
Shape is similar to original product holding, can study influence of the factors such as spray flow, speed to shot noise.
Each component relative position of pilot system of the present invention is adjustable, can be further ensured that combustion by the adjustment of assembling link
The shock height and rocket body of air-flow with respect to core grade deflector hole position, to guarantee the similitude of gas flow field.
The present invention can drastically reduce sensor array arrangement by reasonable Arrangement pressure and temp hot-fluid detection zone
Position and arrangement quantity, have simplified site operation workload and protected working amount；Combustion gas stream very noisy is reduced simultaneously to pass detection
Sensor, front-end amplifier appliance component coupled vibro-acoustic destroy.
Detailed description of the invention
Fig. 1 is present system schematic diagram；
Fig. 2 is that simulated rocket of the present invention installs fixed schematic diagram；
Fig. 3 is that present invention simulation rocket body difference is taken off high-level schematic；
Fig. 4 is analog transmissions platform upper platform body inner flow passage schematic diagram of the present invention；
Fig. 5 is rocket body locating scheme schematic diagram of the present invention；
Fig. 6 is analog transmissions platform locating scheme schematic diagram of the present invention；
Fig. 7 is that present invention simulation rocket body tests sensor mount schematic diagram；
In figure, 1- tests sewing platform base；2- analog transmissions platform；3- sprinkler；4- simulates rocket body；5- test tool；6- dragon
Door frame column；7- portal frame；8- flexural pivot；9- is adjustable drawing wirerope；10- upper platform body；11- support arm；12- inner flow passage；13- is supplied
Water inlet；The upper positioning tool of 14-；Positioning tool 16- testing stand pedestal upper surface under 15-；17- analog transmissions platform supporting leg 18- ring
To mounting rack；The longitudinally mounted frame of 19-.
Specific embodiment
With reference to the accompanying drawing and example elaborates to the present invention.
1) jet test system gabarit and former carrier rocket are similar to transmitting support system holding
To guarantee gas flow field, power of taking off thermal environment or even noise field distribution, water spray noise reduction effect, emission system thermal protection
Performance is consistent with practical carrier rocket, transmitting support system, and jet test system gabarit should keep abundant with actual product
Similitude.At the same time, spray flow, the water-jet velocity for noise reduction system of spraying water should be matched with pilot system.It certainly is reduction
Jet test scale can be with to test system architecture size under the premise of meeting gas flow field, power of taking off thermal environment similitude
Linearly contracting is carried out than (proportionality coefficient k), pilot system water spray total flow carry out linear scale square contracting ratio, water-jet velocity and original
Type is consistent.Certainly, under certain experimental enviroments, linear scale processing can also be carried out to test system architecture size.
2) test platform has stage body support and jet exhaust function
The test platform includes test sewing platform base 1, analog transmissions platform 2, test tool 5；With reference to attached drawing 1, testing stand
Fixed-analog transmitting station 2 and test tool 5 is bolted in 1 upper surface of pedestal, and passes through four supporting legs of test sewing platform base 1
By load transmission to ground；Test tool is lifted on rocket body is simulated at fixed-analog transmitting station preset height；Testing stand
Pedestal presets diversion trench, for arranging the high-temperature high-pressure fuel gas for leading engine generation.The diversion trench carries out ratio k in prototype size
Linear scale.
3) simulation rocket body reliably installs fixation
With reference to attached drawing 2, portal frame (gantry pillar 6 is combined by three columns；Portal frame 7) installation fixed-analog rocket body 4.
Simulation 4 upper end of rocket body is fixed using flexural pivot 8 or flange, and simulation rocket body lower end is fixed using adjustable drawing wirerope 9, prevents from starting
The thrust eccentric of machine causes rocket body tail portion that larger shaking occurs.
In addition, to guarantee that the verticality of simulation rocket body 4 meets test requirements document, it can be long by adjusting adjustable drawing wirerope 9
Degree accurately adjusts the spatial position of rocket body tail portion, to adjust the verticality of simulation rocket body 4.
4) simulation rocket body is height-adjustable
With reference to attached drawing 3, the gantry pillar 6 of preset different height.According to test demand, take off highly to different rocket bodies
Operating condition replaces the gantry pillar 6 of corresponding height, for simulating the different rocket jet flow fields and the hot ring of power to take off under height
Border, noise field.
5) runner built in analog transmissions platform upper platform body
With reference to attached drawing 4, runner 12 built in analog transmissions platform upper platform body, water is introduced by water feed inlet 13, is appeared on the stage by being distributed in
The spray head of body upper surface and deflector hole side everywhere sprays.
The spray head of stage body upper surface is for protecting 2 surface structure of analog transmissions platform, the folder in water outlet direction and horizontal plane
10 ± 5 ° of angle；The spray head of deflector hole side everywhere is located at deflector hole side for protecting 2 side wall construction of analog transmissions platform deflector hole
Nozzle delivery port direction and 27 ± 5 ° of angle of horizontal plane.
6) rocket body relative analog transmitting station is accurately positioned
With reference to attached drawing 5, the accurate positioning of simulation 4 relative analog transmitting station 2 of rocket body is completed using positioning tool.Positioning tool
It is divided into two parts composition: upper positioning tool 14 and lower positioning tool 15.Upper positioning tool 14 is mounted on rocket body tail end, outside rocket body
Surfaces mate；Lower positioning tool 15 is mounted in 10 core grade deflector hole of analog transmissions platform upper platform body, in core grade deflector hole
Surfaces mate.
The upper surface of lower positioning tool 15 finish one with upper 14 bottom surface of positioning tool raised disc of the same size or
Be recessed rotary table.When the protrusion disc is overlapped with upper 14 bottom surface of positioning tool, it was demonstrated that simulation rocket body 4 and 2 core grade of analog transmissions platform
Deflector hole is completed centering and is adjusted；When not being overlapped, the position of analog transmissions platform 2 is adjusted accordingly, until raised disc with it is upper
4 bottom surface of positioning tool is overlapped.
7) stage body opposite flow slot is accurately positioned
With reference to attached drawing 6, in testing stand pedestal upper surface 16 preset four raised flanges, raised flanges relative position and sizes
It is consistent with 17 bottom side flanges of transmitting station supporting leg.When analog transmissions platform 2 is installed, its position should be adjusted and guarantee 17 bottom surface of transmitting station supporting leg
Flange is overlapped with 16 flange of testing stand pedestal upper surface.
8) reserved test sensor mount on the outside of rocket body
With reference to attached drawing 7, two class testing sensor mounts are installed on the outside of rocket body: circumferential mounting rack 18, longitudinally mounted frame
19.Circumferential mounting rack 18 is installed on simulation rocket body fairing position, and longitudinally mounted frame 19 is along simulation rocket body axial restraint.Sensor
Installation rack position can be adjusted according to testing requirement.
9) testing system apparatus, test and height adjustment
With reference to 1~attached drawing of attached drawing 7, pilot system is assembled.
Test sewing platform base 1 is fixed on the default test piece of smooth land first, pedestal supporting leg is connect with piece of smooth land foundation bolt
Fastening；It then will be in the lifting of analog transmissions platform 2 to test sewing platform base 1, it is ensured that 17 bottom side flanges of transmitting station supporting leg and test stylobate
Seat 16 flange of upper surface is overlapped alignment；Then three gantry pillars 6 are installed, table on gantry pillar and test sewing platform base is completed
The coarse adjustment in face is straight；Simulation rocket body 4 is then carried out to connect with the flexural pivot 8 of portal frame 7；Then it combines portal frame 7 with simulation rocket body 4
Body is integrally lifted into 6 top of gantry pillar, completes to be connected and fixed；Adjustable drawing wirerope finally is installed in simulation rocket body tail portion
9, rope capacity is adjusted, the vertical adjustment and fixation of rocket body itself are completed.
Carry out jet test, pilot system issues water spray signal, ignition signal by scheduled timing, simulates 4 engine of rocket body
Start to light a fire, persistently generate combustion gas stream, until powder column burning is complete.
According to follow-up test demand, the gantry pillar of different height is replaced, completes the jet flow examination that difference is taken off under height
Test simulation.
10) pressure, temperature, hot-fluid, noise testing during testing
Pressure, temperature, heat-flow measurement
Temperature, pressure, hot-fluid pass through the center that is laid in booster rocket engine combustion gas stream core space boundary, core
On grade rocket engine combustion gas stream core space boundary, on core grade water conservancy diversion hole wall, the temperature sensor on boosting water conservancy diversion hole wall, pressure
Sensor and heat flow transducer collect.It, can also be in analog transmissions platform in order to increase the Integrity And Reliability of data
Table top combustion gas stream, which is stretched, installs sensor in area.The flat pad table top combustion gas stream stretch area be combustion gas through analog transmissions platform, lead
It splashes outward after the disturbance of chute dependency structure or along the combustion gas stream impact zone that analog transmissions platform table top water conservancy diversion cell wall is stretched, this goes to burn
Erosion intensity can decline much compared to core space.
The booster rocket engine combustion gas stream core space boundary, core grade rocket engine combustion gas stream core space boundary are adopted
It is determined, is specifically comprised the following steps: with rocket launching process combustion gas stream ablation range rapid Estimation method
Step 101, according to the initial parameter of single spraying pipe rocket engine, including jet size, default divergence cone angle, default hair
Motivation operating pressure；Determine free flight state single spraying pipe rocket combustion gas stream initial ablation range；The free flight state list
Jet pipe rocket combustion gas stream initial ablation range is truncated cone.The cone angle of the frustum of a cone is the half of the default divergence cone angle,
The value range of the default divergence cone angle is 6 °~8 °, and the lesser end face diameter of the frustum of a cone is jet size, the circular cone
The height L of platformaValue range be 65~120 times of jet size.
Step 102, according to single spraying pipe rocket engine parameter, including engine operation pressure；Described in amendment step 101
Initial ablation range obtain amendment ablation range.When the engine operation pressure is less than or equal to initially join described in step 1
When default engine operation pressure in number, initial ablation range is equal to amendment ablation range；Otherwise described in set-up procedure one just
Default divergence cone angle in beginning parameter obtains amendment ablation range；
The engine operation pressure that the value range of the default engine operation pressure is 1.15~1.25 times.
Step 103 repeats step 101 to step 102, by the amendment of multiple free flight state single spraying pipe rocket combustion gas streams
Ablation range carries out geometric superposition, the amendment ablation range of the state of flight that gains freedom multi nozzle rocket combustion gas stream.
Step 104 corrects ablation range, the structure size of flat pad 5 according to step 102 or step 103
With position, the structure size of diversion trench 8 and position, booster rocket engine combustion gas stream core space boundary is determined by geometrical relationship
With core grade rocket engine combustion gas stream core space boundary.
Temperature sensor, pressure sensor and the heat flow transducer is mounted on power thermal environment combine detection unit box
One side wall on, and the sensitive end of temperature sensor, pressure sensor and heat flow transducer can directly contact external combustion
Air-flow, it is single that the amplifier of temperature sensor, pressure sensor and heat flow transducer rear end is respectively positioned on the power thermal environment detection
In first box.Certainly according to different measurement requests, test measurement acceleration and strain can also be passed through.Equally in the hot ring of above-mentioned power
Increase acceleration transducer, strain transducer, acceleration transducer, strain transducer in the one side wall of border combine detection unit box
Sensitive end and backend amplifier be respectively positioned in power thermal environment combine detection unit box.In power thermal environment combine detection unit box
The quantity of any sensor is optimal to be more than or equal to 2.
Noise measuring
It is logical by the noise transducer on array by installing jet noise hot-wire array at carrier rocket position to be detected
The mode for crossing near field detects the jet noise of simulation rocket body；The position to be detected includes rocket body and/or emission system.In order to
Increase the accuracy of detection, the position to be detected further includes the high empty region of launching level ground, the region centered on rocket body, and
Except combustion gas impact range, highly it is higher than rocket body；Multiple groups linear array is set in the area, in every group of linear array
Noise transducer is no less than 6.
Wherein, the jet noise hot-wire array installed on rocket body includes the axial linear array that rocket body is arranged along short transverse
And/or the annular array that rocket body radome fairing is circumferentially arranged；Sensor sensing head in the axial linear array is the same as always
On line, and it is parallel with rocket body axis.Axial linear array is along circumferentially at least 4 groups of rocket body, the quantity of every group of noise transducer
No less than 6.The sensor sensing head of the annular array is on identical graduation circle, and disc is vertical with rocket body axis.Ring
Shape array axially arranges at least 2 groups along rocket body, and the quantity of every group of noise transducer is no less than 4.The jet flow installed on rocket body is made an uproar
Sound test array is distributed in rocket body surface, or is distributed in outside rocket body.Diameter when jet noise hot-wire array is distributed in outside rocket body, from rocket body
It is not less than 0.25 times of nozzle diameter to gap.
The jet noise hot-wire array installed in emission system includes emission system umbilical tower or service tower along short transverse
The linear array or matrix array of upper arrangement and/or the array of flat pad periphery spray nozzle location arrangements.Work as flat pad
It when the array of peripheral spray nozzle location arrangements, further include the array of flat pad circumferentially, flat pad is circumferentially
Sensor sensing head on array should be distributed along flat pad central symmetry, and parallel with flat pad upper surface.
In linear array or the matrix array arrangement and tower surface that umbilical tower or service tower are arranged in the height direction, or
Outside tower.Radial clearance of the noise testing array installed outside tower from tower body is not less than 0.25 times of nozzle diameter.Umbilical tower or duty
The sensing head of the linear array arranged in the height direction of business tower or the noise transducer on matrix array in the same plane, and
Parallel and sensing head is towards rocket body with rocket body axis.
Unspecified part of the present invention belongs to common sense well known to those skilled in the art.
Claims (17)
1. multi nozzle rocket jet pilot system, characterized by comprising: simulate rocket body, test platform and for reducing noise
And the sprinkler of protection test platform；The contour dimension for simulating rocket body and test platform is designed according to practical structures size grade ratio
Or linear scale is carried out, the water spray total flow of sprinkler is the k of practical water spray total flow2Times, water-jet velocity and practical production
Product are consistent, and simulation rocket body is packed on test platform according to preset test height, and generate combustion gas in test, are passed through
Temperature, the pressure, hot-fluid, noise being mounted on during the sensor on simulation rocket body and test platform acquires test；It is described
K be the ratio for simulating the contour dimension and practical structures size of rocket body and test platform.
2. system according to claim 1, it is characterised in that: the test platform includes test sewing platform base, simulation hair
Penetrate platform, test tool；
The testing stand pedestal upper surface is connected and fixed analog transmissions platform and test tool, and passes through the supporting leg of test sewing platform base
By load transmission to ground；Test tool is lifted on rocket body is simulated at fixed-analog transmitting station preset height；Testing stand
Pedestal presets diversion trench, and for arranging the high-temperature high-pressure fuel gas for leading engine generation, the diversion trench carries out ratio k in prototype size
Linear scale.
3. system according to claim 2, it is characterised in that: the test tool include portal frame, flexural pivot or flange,
Wirerope；
Symmetrical column combination portal frame one end is packed on test sewing platform base, and simulation rocket body upper end is solid using flexural pivot or flange
It is fixed, the other end rigid connection of flexural pivot or flange and the portal frame；The lower end for simulating rocket body utilizes adjustable drawing wirerope
It is fixed, for guaranteeing that the verticality for simulating rocket body meets test requirements document.
4. system according to claim 1, it is characterised in that: the sprinkler includes being arranged in analog transmissions platform
The runner in portion and the sprinkler composition for being mounted on analog transmissions platform upper surface and deflector hole side is connected to the runner；Position
Spray head in analog transmissions platform upper surface guarantees that entire analog transmissions platform upper surface covers water.
5. system according to claim 4, it is characterised in that: the spray head face positioned at analog transmissions platform upper surface
The water outlet of transmitting station upper surface be fan-shaped and water outlet direction obliquely.
6. system according to claim 5, it is characterised in that: the angle 10 in the water outlet direction and horizontal plane ±
5°。
7. system according to claim 4, it is characterised in that: the nozzle delivery port direction positioned at deflector hole side
With 27 ± 5 ° of angle of horizontal plane.
8. system according to claim 1, it is characterised in that: the analog transmissions platform height is adjustable.
9. the system according to claim 2 or 8, it is characterised in that: the test platform further include upper positioning tool, under
Positioning tool；Deflector hole on lower positioning tool and analog transmissions platform cooperates, and determines the center of analog transmissions platform, upper positioning tool
For the cylindrical structure with certain altitude, the bottom surface of cylinder is positioning reference plane；The described lower positioning tool upper surface setting with
The consistent groove of positioning reference plane shape；Simulation rocket body is mounted in the cylinder, passes through the positioning reference plane
Cooperate with the groove and realizes that simulation rocket body axis is overlapped with analog transmissions platform axis.
10. system according to claim 1, it is characterised in that: the temperature, pressure, hot-fluid are by being laid in boosting
On center, core grade rocket engine combustion gas stream core space boundary in rocket engine combustion gas stream core space boundary, core grade
Temperature sensor, pressure sensor and heat flow transducer on water conservancy diversion hole wall, on boosting water conservancy diversion hole wall collect.
11. system according to claim 10, it is characterised in that: the booster rocket engine combustion gas stream core space side
Boundary, core grade rocket engine combustion gas stream core space boundary are true using rocket launching process combustion gas stream ablation range rapid Estimation method
It is fixed, specifically comprise the following steps:
Step 1: according to the initial parameter of single spraying pipe rocket engine, at the beginning of determining free flight state single spraying pipe rocket combustion gas stream
Beginning ablation range；The initial parameter includes jet size, default divergence cone angle, default engine operation pressure；
Step 2: initial ablation range described in amendment step one obtains according to the actual parameter of single spraying pipe rocket engine
Correct ablation range；
Step 3: repeatedly step 1 is to step 2, the amendment ablation range of the state of flight that gains freedom multi nozzle rocket combustion gas stream；
Step 4: amendment ablation range, analog transmissions platform according to step 2 or step 3 determine that booster rocket starts
Machine combustion gas stream core space boundary and core grade rocket engine combustion gas stream core space boundary.
12. system according to claim 11, it is characterised in that: at the beginning of the free flight state single spraying pipe rocket combustion gas stream
Beginning ablation range is truncated cone；The cone angle of the frustum of a cone is the half of the default divergence cone angle, the default divergence cone angle
Value range is 6 °~8 °, and the lesser end face diameter of the frustum of a cone is jet size, the height L of the frustum of a coneaValue
The jet size that range is 65~120 times.
13. system according to claim 11, it is characterised in that: engine parameter described in step 2 is engine work
Make pressure, when the engine operation pressure is less than or equal to the default engine operation pressure in initial parameter described in step 1
When, initial ablation range is equal to amendment ablation range；Otherwise increase the default divergence cone angle in initial parameter described in step 1, obtain
Correct ablation range；
The engine operation pressure that the value range of the default engine operation pressure is 1.15~1.25 times.
14. system according to claim 10, it is characterised in that: temperature sensor, pressure sensor and the heat
Flow sensor is mounted in the one side wall of power thermal environment combine detection unit box, and temperature sensor, pressure sensor and heat
The sensitive end of flow sensor can directly contact outer combustion gas stream, temperature sensor, pressure sensor and heat flow transducer
The amplifier of rear end is respectively positioned in the power thermal environment detection unit box.
15. system according to claim 1, it is characterised in that: made an uproar by installing jet flow at carrier rocket position to be detected
Sound test array detects the jet noise of simulation rocket body in such a way that the noise transducer on array is by near field；Described
Position to be detected includes rocket body and/or emission system.
16. system according to claim 15, it is characterised in that: the position to be detected further includes launching level ground high-altitude
Region, the region are located at except combustion gas impact range centered on rocket body, are highly higher than rocket body；It is arranged in the area more
Linear array is organized, the noise transducer in every group of linear array is no less than 6.
17. system according to claim 15, it is characterised in that: the jet noise hot-wire array installed on the rocket body
The annular array that the axial linear array and/or rocket body radome fairing being arranged including rocket body along short transverse are circumferentially arranged；Transmitting system
The jet noise hot-wire array installed on system includes the line array that emission system umbilical tower or service tower are arranged in the height direction
The array of column or matrix array and/or flat pad periphery spray nozzle location arrangements.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910229980.5A CN109974523B (en) | 2019-03-26 | 2019-03-26 | Multi-nozzle rocket jet test system |
Applications Claiming Priority (1)
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111562189A (en) * | 2020-05-31 | 2020-08-21 | 太原理工大学 | Ultrahigh-temperature gas jet erosion test device for diversion trench material |
| CN111795828A (en) * | 2020-06-05 | 2020-10-20 | 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 |
| CN113074065A (en) * | 2021-04-06 | 2021-07-06 | 北京航天发射技术研究所 | Power system for comprehensive research of heat transfer multiphase flow noise |
| CN113188819A (en) * | 2021-04-12 | 2021-07-30 | 北京航天发射技术研究所 | Rocket launching water spraying noise reduction effect evaluation method |
| CN113482800A (en) * | 2021-07-19 | 2021-10-08 | 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 |
| CN113804818A (en) * | 2021-08-26 | 2021-12-17 | 西安近代化学研究所 | Rapid fire-baking test device for warhead and using method |
| CN114543583A (en) * | 2022-04-28 | 2022-05-27 | 成都航天万欣科技有限公司 | Precision adjusting device and method for storage and transportation launching box |
| CN116629028A (en) * | 2023-07-19 | 2023-08-22 | 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 |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4344592A (en) * | 1977-11-10 | 1982-08-17 | Spiridon Constantinescu | Launching tower for heavy rockets |
| CN103090723A (en) * | 2011-10-27 | 2013-05-08 | 北京航天发射技术研究所 | Water injection, cooling and denoising system for rocket launching |
| CN103712522A (en) * | 2012-09-29 | 2014-04-09 | 北京航天发射技术研究所 | Rocket launching system with water spraying, cooling and denoising functions |
| CN103712808A (en) * | 2012-09-29 | 2014-04-09 | 北京航天发射技术研究所 | Detection system for single-jet-pipe rocket launch water-spray cooling noise-reduction effect |
| CN207181068U (en) * | 2017-08-14 | 2018-04-03 | 北京强度环境研究所 | 8 freedom suspension devices of carrier rocket full modal test |
| CN109099765A (en) * | 2018-08-23 | 2018-12-28 | 北京航天发射技术研究所 | Speed reducing recovery device is tested based on the rocket launching for blocking pulling force |
-
2019
- 2019-03-26 CN CN201910229980.5A patent/CN109974523B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4344592A (en) * | 1977-11-10 | 1982-08-17 | Spiridon Constantinescu | Launching tower for heavy rockets |
| CN103090723A (en) * | 2011-10-27 | 2013-05-08 | 北京航天发射技术研究所 | Water injection, cooling and denoising system for rocket launching |
| CN103712522A (en) * | 2012-09-29 | 2014-04-09 | 北京航天发射技术研究所 | Rocket launching system with water spraying, cooling and denoising functions |
| CN103712808A (en) * | 2012-09-29 | 2014-04-09 | 北京航天发射技术研究所 | Detection system for single-jet-pipe rocket launch water-spray cooling noise-reduction effect |
| CN207181068U (en) * | 2017-08-14 | 2018-04-03 | 北京强度环境研究所 | 8 freedom suspension devices of carrier rocket full modal test |
| CN109099765A (en) * | 2018-08-23 | 2018-12-28 | 北京航天发射技术研究所 | Speed reducing recovery device is tested based on the rocket launching for blocking pulling force |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111562189A (en) * | 2020-05-31 | 2020-08-21 | 太原理工大学 | Ultrahigh-temperature gas jet erosion test device for diversion trench material |
| 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 |
| CN111795828A (en) * | 2020-06-05 | 2020-10-20 | 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 |
| CN113074065A (en) * | 2021-04-06 | 2021-07-06 | 北京航天发射技术研究所 | Power system for comprehensive research of heat transfer multiphase flow noise |
| CN113188819A (en) * | 2021-04-12 | 2021-07-30 | 北京航天发射技术研究所 | Rocket launching water spraying noise reduction effect evaluation method |
| CN113482800A (en) * | 2021-07-19 | 2021-10-08 | 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 |
| CN113804818A (en) * | 2021-08-26 | 2021-12-17 | 西安近代化学研究所 | Rapid fire-baking test device for warhead and using method |
| 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 |
| CN114543583A (en) * | 2022-04-28 | 2022-05-27 | 成都航天万欣科技有限公司 | Precision adjusting device and method for storage and transportation launching box |
| CN116629028A (en) * | 2023-07-19 | 2023-08-22 | 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 |
| 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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