CN108590889A - A kind of larynx hydrant change propulsive solid propellant rocket ground test device - Google Patents
A kind of larynx hydrant change propulsive solid propellant rocket ground test device Download PDFInfo
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- CN108590889A CN108590889A CN201810435205.0A CN201810435205A CN108590889A CN 108590889 A CN108590889 A CN 108590889A CN 201810435205 A CN201810435205 A CN 201810435205A CN 108590889 A CN108590889 A CN 108590889A
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- larynx
- bar
- bolt
- pressure sensor
- test device
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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
Abstract
A kind of larynx hydrant change propulsive solid propellant rocket ground test device disclosed by the invention, belongs to larynx bolt engines ground testing field.The present invention includes driving mechanism and emulation mechanism；Driving mechanism includes that motor fixed cover, stepping motor, sliding mark post, motor fixed cylinder, movement limitation nut, the first movement transmission plate, fastening nut, the second movement transmission plate, the first larynx tether bar, pull pressure sensor, the second larynx and tether bar sealing ring, displacement sensor, movable connecting rod；It includes front head, spring mountings, left fixed cylinder, rear head, compressed spring, screw rod, pressure sensor seat, larynx bolt to emulate mechanism.The present invention can realize that larynx hydrant change propulsive solid propellant rocket ground test, advantage are as follows：(1) verification tested under different thrusts, different pressure is realized；(2) closed-loop control to engine larynx bolt is realized；(3) testing cost is low, and acquisition data are more, and (4) are simple in structure, durability is good；(5) driving mechanism light weight.
Description
Technical field
The present invention relates to a kind of larynx hydrant change propulsive solid propellant rocket ground test devices, with belonging to larynx bolt engine
Face testing field.
Background technology
Solid propellant rocket controllability is poor, solid propellant with charge structure all storage in the combustion chamber, once
It lights, combustion face changes according to predetermined rule, can not adjust thrust size at random according to actual needs during the work time, or real
Now repeatedly start, thus greatly limit the application and development of solid propellant rocket, some weapon models also have to use
Liquid-propellant rocket engine is also had in the spacecraft of many restricted volumes as the modified power plant of missiles ' terminal
Using the liquid fuel motor or gas generator for being difficult to store for a long time and volume specific impulse is small.Therefore, advanced thrust
Regulation technology is always one of the important directions of solid propellant rocket development.
Currently, experimental test relies primarily on response time and the control essence that thermal ignition test method obtains change propulsive larynx bolt
Degree, but it is high since there are the equipment process-cycle is long, the duration of ignition is short, the restriction of material ablation, there are testing costs, error is big,
The shortcomings of data are limited is obtained, when hardware facility and technical indicator etc. cannot meet the response of larynx bolt change propulsive well
Between and control accuracy requirement.The 1960s and 1970s, foreign countries just have begun to Thrust of Solid Rocket Motor control
Technology processed has carried out a large amount of research.Due to the limitation of design conditions etc., this period adjusts Thrust of Solid Rocket Motor
Mainly based on experimental study, Aerojet, Thiokol and Advanced Ballistic Missile Defence etc. are made that greatly for the research of technology
Measure experimental study.Wherein Aerojet is the pioneer of this respect research, and beginning one's study solid propellant propulsion at first in the sixties in last century can
Control technology realizes the variation range of 22250N to 1335000N thrusts.These systems are using the medium propellant containing energy and hydraulic pressure
Driving, due to using computerized simple and reponse system, response time and control accuracy are subject to certain restrictions control system.This when
Although the phase realizes motor power by a large number of experiments, certain success is achieved, due in sealing and weight
The reason of limitation etc., these testing programs are not applied to really in practice.With machinery, electronics after the 80s and 90s
And the progress of the every profession and trades technology such as sealing technique, and the active demand to Thrust of Solid Rocket Motor control technology, make
It obtains Thrust of Solid Rocket Motor control technology and obtains further research extensively and experiment.However due to laboratory facilities and test
The limitation of technology, change propulsive larynx bolt solid propellant rocket have the following problems in terms of verification experimental verification：1) duty of engine list
One, it is difficult to realize the verification tested under different thrusts, different pressure；2) the not reproducible use of engine, larynx bolt and jet pipe material
Ablation is serious；3) domestic that open loop control mode is all used substantially to the adjusting of the inner trajectory of larynx bolt engine at present, and to realize
The STOCHASTIC CONTROL of motor power needs to realize the closed-loop control to engine larynx bolt；4) testing cost is high, and acquisition data are few,
Limited data are difficult to effectively verify to the response time of control system；5) partial engine larynx bolt drive system is using auxiliary
Hydraulic driving mode, it is complicated, it is greatly simplified using electric mechanical type of drive structure, passive quality accordingly can also be reduced.
Invention content
In order to solve, existing larynx hydrant change propulsive solid propellant rocket ground test device structure function is single, structure is multiple
The problem of miscellaneous, poor durability, a kind of larynx hydrant change propulsive solid propellant rocket ground test device disclosed by the invention will solve
Certainly the technical issues of is to realize larynx hydrant change propulsive solid propellant rocket ground test, is had the following advantages that：(1) it realizes different
The verification tested under thrust, different pressure；(2) closed-loop control to engine larynx bolt is realized；(3) testing cost is low, obtains number
According to more, (4) are simple in structure, durability is good；(5) driving mechanism light weight.
The purpose of the present invention is what is be achieved through the following technical solutions.
A kind of larynx hydrant change propulsive solid propellant rocket ground test device disclosed by the invention include driving mechanism and
Emulate mechanism.The driving mechanism includes motor fixed cover, stepping motor, sliding mark post, motor fixed cylinder, movement limitation
Nut, the first movement transmission plate, fastening nut, the second movement transmission plate, the first larynx tether bar, pull pressure sensor, the second larynx
Tether bar sealing ring, displacement sensor, movable connecting rod.The emulation mechanism include front head, spring mountings, left fixed cylinder,
Rear head, compressed spring, screw rod, pressure sensor seat, larynx bolt.
Driving mechanism connection relation, which is that stepping motor is bolted, to be fixed in motor fixed cover.Stepping is electronic
Machine rotor is threaded rod, is combined into screw-nut structure by movement limitation nut and stepping motor matching, is limited by moving
Nut realizes the translation of movement limitation nut threadingly bar with the rotation of rotor, is driven to tether bar by the second larynx
Emulation mechanism or larynx bolt do linear reciprocating motion.Displacement sensor is bolted on sliding mark post, and passes through survey
Flow control one moves measurement of the displacement realization of transmission plate to emulation mechanism displacement.First larynx is tethered bar and by pull pressure sensor
Two larynxs tether bar and connect.When strong act on pull pressure sensor diaphragm, it is attached to the electricity on pull pressure sensor both sides
The resistance value of resistance foil gauge changes, and is electric signal using corresponding circuit conversion, is input in acquisition system, to realize
Measurement to emulation mechanism axially loaded.
The connection relation for emulating mechanism is that front head is hierarchic structure, and side external cylindrical surface is provided with for being fixed with motor
Cylinder is bolted threaded hole, and side is threadedly coupled with left fixed cylinder, while being connect with left fixed cylinder inner cylinder face at front head step
It touches, the deep trouth for dynamic sealing is provided on front head.Left fixed cylinder be hollow cylinder structure, both sides respectively with front head,
Rear head is threadedly coupled, and needs at least two pressure sensor seats of setting according to experiment, wherein at least includes a pressure
Input terminal is used for the combustion gas pressure of simulated engine combustion chamber for controlling input high pressure cold, also as pressure sensor seat
Including at least the pressure sensor seat for installing pressure sensor, pressure sensor is used to measure the pressure in emulation mechanism.
Second larynx tethers pole-footing and connects compressed spring according to test objective or test the larynx bolt of size.When progress cold air experimental study experiment
When the load characteristic of the larynx bolt of size, larynx tethers the larynx bolt of bar connection experiment size.Emulation mechanism, which works as, is used for analysis-driven mechanism
When response time under bringing onto load and control accuracy, the second larynx tethers bar connection compressed spring.The elastic force that compressed spring provides is used
In simulating the axially loaded in larynx bolt motion process, emulation mechanism axially loaded tethers bar, the second larynx bolt by being mounted on the first larynx
Pull pressure sensor among connecting rod measures, under analysis-driven mechanism bringing onto load response time and control accuracy.Bullet
Spring fixing piece center is provided with threaded hole, and the bolt that bar is tethered for the second larynx connects and be provided with deep trouth, is moved for compressed spring
Space is provided.It is compressed spring to emulate the spring selected by mechanism, effectively to avoid in the motion process that the second larynx tethers bar
The compressed spring flexural deformation of itself or fracture failure, compressed spring caused by due to stress is excessive or unbalance stress are sealed after being sleeved on
Head in the annular recess of spring mountings.In addition, front head, rear head are fixed together with left fixed cylinder respectively, spring is solid
Determine part bar tethered with the second larynx by screw rod to be fixed together.
Preferably, motor fixed cover side is equipped with boss, it is easy for removal and installation；Motor fixed cover is circumferentially uniformly distributed
Fixed stepping motor is bolted in threaded hole；Motor fixed cover external cylindrical surface is hierarchic structure, solid convenient for accepting motor
Safety barrel.
Preferably, sliding mark post side is helicitic texture, the other side is uniformly distributed for fixture installation and displacement sensing
The fixed threaded hole of device.
Preferably, motor fixed cylinder is cylindrical shell, and is useful for the circumferential recess of disassembly and installation in wall surface milling,
Both sides are bolted with motor fixed cover and front head respectively.
Preferably, the first movement transmission plate is circular plate structure, center is uniformly distributed circular through hole, surrounding with circumferential
Circular arc wall face is symmetrical, easy for removal and installation.
Preferably, the second larynx bolt connecting rod two end has threaded hole, and uniformly it is provided with deep trouth in external cylindrical surface and is moved for axis
Sealing.
A kind of working method of larynx hydrant change propulsive solid propellant rocket ground test device disclosed by the invention, including
Following steps：
Step 1：Left fixed cylinder gas pressure intensity, larynx bolt displacement regulated quantity, control accuracy are determined according to test objective；
Step 2：Selection meets displacement sensor, the pull pressure sensor of test objective range；
Step 3：According to a kind of larynx hydrant change propulsive solid propellant rocket ground test device connection relation group
Fill ground test device；
Step 4：Check a kind of larynx hydrant change propulsive solid propellant rocket ground test device reasonability and
The stability of assembly；
Step 5：By accessing high pressure gas on pressure sensor seat, the second larynx is driven to tether using stepping motor
Bar moves back and forth, the air-tightness of check device；
Step 6：If a kind of larynx hydrant change propulsive solid propellant rocket ground test device gas leakage, repeat to walk
Rapid five reach expected requirement until ground test device；
Step 7：It is selected to execute step 8 or step 9 according to test objective, carries out corresponding ground testing experiment；
Step 8：Mechanism is emulated when carrying out the load characteristic for the larynx bolt that size is tested in cold air experimental study, the second larynx bolt
The larynx bolt of connecting rod connection experiment size.It pushes larynx to tether the reciprocating motion of bar by stepper motor, realizes the displacement tune to larynx bolt
Section acquires the larynx bolt load data of experiment size by pull pressure sensor.Change input cold air pressure in experiment, realizes different
The research of pressure lower larynx bolt load characteristic.
Step 9：Emulate mechanism when under analysis-driven mechanism bringing onto load response time and when control accuracy, second
Larynx tethers bar connection compressed spring.Compressed spring provide elastic force be used for simulate the second larynx tether in bar motion process axial direction by
Power emulates mechanism axially loaded by being measured mounted on the pull pressure sensor that the first larynx tethers bar, the second larynx tethers among bar, and
Driving mechanisms control system is passed to by Real-time Feedback, when for the analysis load-carrying response of closed-loop control lower drive mechanism
Between and control accuracy.By changing compressed spring rigidity in experiment, when realizing the load-carrying response of different thrust lower drive mechanisms
Between and control accuracy verification experimental verification.
Advantageous effect
1. a kind of larynx hydrant change propulsive solid propellant rocket ground test device disclosed by the invention, when progress cold air examination
When testing the load characteristic of larynx bolt of research experiment size, the second larynx tethers the larynx bolt of bar connection experiment size；It is electronic by stepping
Machine pushes the first larynx to tether the reciprocating motion of bar, realizes that the displacement to larynx bolt is adjusted, and experiment ruler is acquired by pull pressure sensor
The load data of very little larynx bolt；Change input cold air pressure in experiment, realizes the research of different pressure lower larynx bolt load characteristics.
2, a kind of larynx hydrant change propulsive solid propellant rocket ground test device disclosed by the invention drives when for analyzing
When the response time of motivation structure and control accuracy, the second larynx tethers bar connection compressed spring；The elastic force that compressed spring provides is used for
The axially loaded in larynx bolt motion process is simulated, the first larynx tethers bar to emulation mechanism axially loaded, the second larynx tethers by being mounted on
Pull pressure sensor among bar measures, and passes to driving mechanisms control system by Real-time Feedback, for analyzing closed loop
Control response time and the control accuracy of lower drive mechanism；By changing compressed spring rigidity in experiment, realize under different thrusts
The verification experimental verification of driving mechanism load-carrying response time and control accuracy.
3, a kind of larynx hydrant change propulsive solid propellant rocket ground test device disclosed by the invention is tested compared to hot-fluid
Condition lower larynx bolt and jet pipe material ablation are serious, and the deformation of cold air experimental condition lower larynx bolt is small, and material is reusable without ablation,
Material serviceability ratio is high.
4, a kind of larynx hydrant change propulsive solid propellant rocket ground test device disclosed by the invention is tested compared to hot-fluid
Under the conditions of, igniting is of high cost, and experimental condition is limited by place, it is difficult to carry out the verification experimental verification of a large amount of repeatability；Cold air experiment is surveyed
It tries at low cost, is not limited by space enrironment, test of many times is facilitated to verify, obtain that data are more, and a large amount of data are to control system
The research of response time and larynx bolt load characteristic have deeper understanding.
5, auxiliary hydraulic pressure type of drive, a kind of larynx disclosed by the invention are used compared to partial engine larynx bolt drive system
Hydrant change propulsive solid propellant rocket ground test device can simplify structure using electric mechanical type of drive, reduce phase
Answer passive quality.
Description of the drawings
Fig. 1 be a kind of larynx hydrant change propulsive solid propellant rocket ground test device structural schematic diagram (emulation mechanism into
The larynx bolt load characteristic of size is tested in row cold air experimental study)
Fig. 2 is that (emulation mechanism uses a kind of larynx hydrant change propulsive solid propellant rocket ground test device structural schematic diagram
In verifying response time under driving mechanism bringing onto load and control accuracy)
Wherein：1- driving mechanisms, 2- emulation mechanism, 1.1- motor fixed covers, 1.2- stepping motors, 1.3- sliding marks
Bar, 1.4- motors fixed cylinder, 1.5- movement limitations nut, 1.6 first movement transmission plates, 1.7- fastening nuts, 1.8- second are transported
Dynamic transmission plate, the first larynxs of 1.9- tether bar, 1.10- pull pressure sensor, the second larynxs of 1.11- tether bar, 1.12- sealing rings,
It is sealed after 1.13- displacement sensors, 1.14- movable connecting rods, 2.1- front heads, 2.2- spring mountings, the left fixed cylinders of 2.3-, 2.4-
Head, 2.5- compressed springs, 2.6- screw rods, 2.7- pressure sensors seat, 2.8- larynx bolts.
Specific implementation mode
In order to better illustrate objects and advantages of the present invention, invention content is done further with example below in conjunction with the accompanying drawings
Explanation.
Embodiment 1：
A kind of larynx hydrant change propulsive solid propellant rocket ground test device disclosed in the present embodiment includes driving mechanism 1
With emulation mechanism 2.The driving mechanism 1 includes motor fixed cover 1.1, (87000 series of straight lines drive stepping motor 1.2
Device), sliding mark post 1.3, motor fixed cylinder 1.4, movement limitation nut 1.5, first move transmission plate 1.6, fastening nut 1.7
(M8), the second movement transmission plate 1.8, the first larynx tether bar 1.9, pull pressure sensor 1.10 (20kg), the second larynx and tether bar
1.11, sealing ring 1.12, displacement sensor 1.13 (10mm), movable connecting rod 1.14.The emulation mechanism 2 include front head 2.1,
Spring mountings 2.2, left fixed cylinder 2.3, rear head 2.4, compressed spring 2.5, screw rod 2.6, pressure sensor seat 2.7 (M20 ×
1.5), larynx bolt 2.8.
1 connection relation of driving mechanism, which is that stepping motor 1.2 is bolted, to be fixed in motor fixed cover 1.1.Step
It is threaded rod into 1.2 rotor of motor, feed screw nut knot is combined by movement limitation nut 1.5 and the matching of stepping motor 1.2
Structure limits rotation of the nut 1.5 with rotor by movement, realizes the translation of movement limitation nut 1.5 threadingly bar, to
Tethering bar 1.11 by the second larynx drives emulation mechanism 2 or larynx bolt 2.8 to do linear reciprocating motion.Displacement sensor 1.13 passes through spiral shell
It tethers and connects on sliding mark post 1.3, and the displacement by measuring the first movement transmission plate 1.6 is realized to emulating 2, mechanism
The measurement of shifting.First larynx is tethered bar 1.9 to pull pressure sensor 1.10 and the second larynx tethers bar 1.11 and connects.When there is masterpiece
When on pull pressure sensor diaphragm, the resistance value for being attached to the resistance strain gage on pull pressure sensor both sides changes, then passes through
It is electric signal to cross corresponding circuit conversion, is input in acquisition system, to realize the measurement to 2 axially loaded of emulation mechanism.
The connection relation of emulation mechanism 2 is that front head 2.1 is hierarchic structure, and side external cylindrical surface, which is provided with, to be used for and motor
Fixed cylinder 1.4 is bolted threaded hole, and side is threadedly coupled with left fixed cylinder 2.3, at the same at 2.1 step of front head with left fixation
Cylinder 2.3 inner cylinder faces contact, is provided with the deep trouth for dynamic sealing on front head 2.1.Left fixed cylinder 2.3 is hollow cylinder knot
Structure, both sides are threadedly coupled with front head 2.1, rear head 2.4 respectively, and need at least two pressure sensings of setting according to experiment
Device seat 2.7 wherein at least includes a pressure input as pressure sensor seat 2.7, is used for controlling input high pressure cold
Carry out the combustion gas pressure of simulated engine combustion chamber, also includes at least the pressure sensor seat 2.7 for installing pressure sensor, pressure
Force snesor is used to measure the pressure in emulation mechanism 2.Second larynx tethers bar 1.11 and connects compressed spring 2.5 according to test objective
Or the larynx bolt 2.8 of experiment size.When carrying out the load characteristic for the larynx bolt 2.8 that size is tested in cold air experimental study, the second larynx
Tether the larynx bolt 2.8 of the connection experiment size of bar 1.11.Mechanism 2 is emulated when for response under 1 bringing onto load of analysis-driven mechanism
Between and when control accuracy, the second larynx tethers bar 1.11 and connects compressed spring 2.5.The elastic force that compressed spring 2.5 provides is for simulating
Axially loaded in larynx bolt motion process, by being mounted on, the first larynx tethers bar 1.9 to emulation 2 axially loaded of mechanism, the second larynx tethers
Pull pressure sensor 1.10 among bar 1.11 measures, under 1 bringing onto load of analysis-driven mechanism response time and control
Precision.2.2 center of spring mountings is provided with threaded hole, and the bolt that bar 1.11 is tethered for the second larynx connects and be provided with deep trouth,
Space is provided for the movement of compressed spring 2.5.It is compressed spring 2.5 to emulate the spring selected by mechanism 2, effectively to avoid second
Larynx tethers the flexural deformation of itself caused by due to stress is excessive or unbalance stress of compressed spring 2.5 in the motion process of bar 1.11
Or fracture failure, compressed spring 2.5 are sleeved in the annular recess of rear head and spring mountings 2.2.In addition, front head 2.1, after
End socket 2.4 is fixed together with left fixed cylinder 2.3 respectively, and spring mountings 2.2 tether bar 1.11 by screw rod 2.6 and the second larynx
It is fixed together.
1.1 side of motor fixed cover is equipped with boss, easy for removal and installation；Motor fixed cover 1.1 is circumferential to be uniformly distributed spiral shell
Fixed stepping motor 1.2 is bolted in pit；1.1 external cylindrical surface of motor fixed cover is hierarchic structure, convenient for accepting electricity
Machine fixed cylinder 1.4.
It is helicitic texture to slide 1.3 side of mark post, and the other side is uniformly distributed for fixture installation and displacement sensor 1.13
Fixed threaded hole.
Motor fixed cylinder 1.4 is cylindrical shell, and is useful for the circumferential recess of disassembly and installation, both sides point in wall surface milling
It is not bolted with motor fixed cover 1.1 and front head 2.1.
First movement transmission plate 1.6 is circular plate structure, and center is uniformly distributed circular through hole, surrounding circular arc wall with circumferential
Face is symmetrical, easy for removal and installation.
Second larynx, which tethers 1.11 both ends of bar, threaded hole, and is uniformly provided with deep trouth for axis dynamic sealing in external cylindrical surface.
A kind of working method of larynx hydrant change propulsive solid propellant rocket ground test device disclosed in the present embodiment, packet
Include following steps：
Step 1：According to test objective determine left 2.3 gas pressure intensities of fixed cylinder of 10Mpa, 2.8 displacement regulated quantity of 5mm larynxs bolt,
0.2kg control accuracies；
Step 2：Selection meets test objective 10mm displacement sensors 1.13,20kg pull pressure sensor 1.10；
Step 3：According to a kind of larynx hydrant change propulsive solid propellant rocket ground test device connection relation group
Fill ground test device；
Step 4：Check a kind of larynx hydrant change propulsive solid propellant rocket ground test device reasonability and
The stability of assembly；
Step 5：By accessing 5Mpa high pressure gas on pressure sensor seat 2.7, driven using stepping motor 1.2
Second larynx tethers the reciprocating motion of bar 1.11, checks that threaded connection and the second larynx tether bar 1.11 and front head in emulation mechanism 2
The air-tightness of 2.1 dynamic sealings；
Step 6：If a kind of larynx hydrant change propulsive solid propellant rocket ground test device gas leakage, repeat to walk
Rapid five reach expected requirement until ground test device；
Step 7：It is selected to execute step 8 or step 9 according to test objective, carries out corresponding ground testing experiment；
Step 8：Mechanism 2 is emulated when carrying out the load characteristic for the larynx bolt 2.8 that size is tested in cold air experimental study, second
Larynx tethers bar 1.11 and connects larynx bolt 2.8.Two pressure sensor seats 2.7 are set in left fixed cylinder 2.3, and a pressure input is made
For pressure sensor seat 2.7, it is used for the combustion gas pressure of simulated engine combustion chamber for controlling input 10Mpa high pressure colds, separately
The pressure sensor seat 2.7 of one installation 20Mpa range pressure sensor, 20Mpa range pressure sensors are emulated for measuring
Pressure in mechanism 2.It pushes the first larynx to tether the reciprocating motion of bar 1.9 by stepper motor 1.2, realizes that overall length be 90.2mm
The displacement of larynx bolt 2.8 adjust, pass through pull pressure sensor 1.10 and acquire 2.8 load data of larynx bolt.It is cold to change input in experiment
Air pressure strong 5Mpa, 10Mpa, 15Mpa realize the research of different 2.8 load characteristics of pressure lower larynx bolt.
Step 9：Emulate mechanism 2 when under 1 bringing onto load of analysis-driven mechanism response time and when control accuracy, the
Two larynxs tether bar 1.11 and connect compressed spring 2.5.The elastic force that compressed spring 2.5 provides tethers the fortune of bar 1.11 for simulating the second larynx
Axially loaded during dynamic, by being mounted on, the first larynx tethers bar 1.9 to emulation 2 axially loaded of mechanism, the second larynx tethers bar 1.11
The pull pressure sensor 1.10 of intermediate 20kg ranges measures, and passes to 1 control system of driving mechanism by Real-time Feedback, with
In analyzing response time and control accuracy under 1 bringing onto load of closed-loop control lower drive mechanism.By changing compressed spring in experiment
2.5 rigidity, realize verification experimental verification of the driving mechanism 1 with 5kg, 10kg, 15kg response time and control accuracy loaded.
Above-described specific descriptions have carried out further specifically the purpose, technical solution and advantageous effect of invention
It is bright, it should be understood that the above is only a specific embodiment of the present invention, the protection model being not intended to limit the present invention
It encloses, all within the spirits and principles of the present invention, any modification, equivalent substitution, improvement and etc. done should be included in the present invention
Protection domain within.
Claims (7)
1. a kind of larynx hydrant change propulsive solid propellant rocket ground test device, it is characterised in that：Including driving mechanism (1) and
Emulate mechanism (2)；The driving mechanism (1) includes motor fixed cover (1.1), stepping motor (1.2), sliding mark post
(1.3), motor fixed cylinder (1.4), movement limitation nut (1.5), the first movement transmission plate (1.6), fastening nut (1.7), the
Two movement transmission plates (1.8), the first larynx tether bar (1.9), pull pressure sensor (1.10), the second larynx and tether bar (1.11) sealing
Enclose (1.12), displacement sensor (1.13), movable connecting rod (1.14)；The emulation mechanism (2) includes front head (2.1), spring
Fixing piece (2.2), left fixed cylinder (2.3), rear head (2.4), compressed spring (2.5), screw rod (2.6), pressure sensor seat
(2.7), larynx bolt (2.8)；
Driving mechanism (1) connection relation, which is that stepping motor (1.2) is bolted, to be fixed in motor fixed cover (1.1)；
Stepping motor (1.2) rotor is threaded rod, and silk is combined by movement limitation nut (1.5) and stepping motor (1.2) matching
Thick stick nut structure limits rotation of the nut (1.5) with rotor by movement, realizes movement limitation nut (1.5) threadingly
The translation of bar drives emulation mechanism (2) or larynx bolt (2.8) to do linear reciprocating motion to tether bar (1.11) by the second larynx；
Displacement sensor (1.13) is bolted on sliding mark post (1.3), and by measuring the first movement transmission plate
(1.6) measurement to emulating mechanism (2) displacement is realized in displacement；First larynx is tethered bar (1.9) by pull pressure sensor (1.10)
Bar (1.11) is tethered with the second larynx to connect；When strong act on pull pressure sensor (1.10) diaphragm, it is attached to tension and compression
The resistance value of the resistance strain gage on force snesor (1.10) both sides changes, and is electric signal using corresponding circuit conversion, defeated
Enter into acquisition system, to realize the measurement to emulating mechanism (2) axially loaded；
The connection relation of emulation mechanism (2) is that front head (2.1) is hierarchic structure, and side external cylindrical surface, which is provided with, to be used for and motor
Fixed cylinder (1.4) is bolted threaded hole, and side is threadedly coupled with left fixed cylinder (2.3), at the same at front head (2.1) step with
Left fixed cylinder (2.3) inner cylinder face contact, is provided with the deep trouth for dynamic sealing on front head (2.1)；Left fixed cylinder (2.3) is
Hollow cylinder structure, both sides are threadedly coupled with front head (2.1), rear head (2.4) respectively, and need to be arranged according to experiment
At least two pressure sensor seats (2.7) wherein at least include a pressure input as pressure sensor seat (2.7), are used
It is used for the combustion gas pressure of simulated engine combustion chamber in control input high pressure cold, also includes at least for installing pressure sensor
Pressure sensor seat (2.7), pressure sensor be used for measures emulate mechanism in pressure；Second larynx tethers bar (1.11) basis
Test objective connects compressed spring (2.5) or tests the larynx bolt (2.8) of size；Size is tested when carrying out cold air experimental study
When the load characteristic of larynx bolt (2.8), larynx tethers the larynx bolt (3) of bar connection experiment size；Mechanism (2) is emulated when for analysis-driven
When response time under mechanism (1) bringing onto load and control accuracy, the second larynx tethers bar (1.11) connection compressed spring (2.5)；Pressure
The elastic force that contracting spring (2.5) provides is used to simulate axially loaded in larynx bolt (2.8) motion process, emulation mechanism (2) it is axial by
Power tethers bar (1.9) by being mounted on the first larynx, the second larynx tethers the intermediate pull pressure sensor (1.10) of bar (1.11) and measures, with
For under analysis-driven mechanism (1) bringing onto load response time and control accuracy；Spring mountings (2.2) center is provided with screw thread
Hole, the bolt that bar (1.11) is tethered for the second larynx connect and are provided with deep trouth, and space is provided for compressed spring (2.5) movement；
It is compressed spring (2.5) to emulate the spring selected by mechanism (2), effectively the second larynx to be avoided to tether being moved through for bar (1.11)
Compressed spring (2.5) flexural deformation of itself or fracture failure caused by due to stress is excessive or unbalance stress in journey compresses bullet
Spring (2.5) is sleeved in the annular recess of rear head (2.4) and spring mountings (2.2)；In addition, front head (2.1), rear head
(2.4) it is fixed together respectively with left fixed cylinder (2.3), spring mountings (2.2) tether bar by screw rod (2.6) and the second larynx
(1.11) it is fixed together.
2. a kind of larynx hydrant change propulsive solid propellant rocket ground test device as described in claim 1, it is characterised in that：
Motor fixed cover (1.1) side is equipped with boss, easy for removal and installation；Motor fixed cover (1.1) is circumferentially uniformly distributed threaded hole,
Fixed stepping motor (1.2) is bolted；Motor fixed cover (1.1) external cylindrical surface is hierarchic structure, convenient for accepting electricity
Machine fixed cylinder (1.4).
3. a kind of larynx hydrant change propulsive solid propellant rocket ground test device as described in claim 1, it is characterised in that：
Sliding mark post (1.3) side is helicitic texture, and the other side is uniformly distributed fixed for fixture installation and displacement sensor (1.13)
Threaded hole.
4. a kind of larynx hydrant change propulsive solid propellant rocket ground test device as described in claim 1, it is characterised in that：
Motor fixed cylinder (1.4) be cylindrical shell, and wall surface milling be useful for disassembly and installation circumferential recess, both sides respectively with electricity
Machine fixed cover (1.1) and front head (2.1) are bolted.
5. a kind of larynx hydrant change propulsive solid propellant rocket ground test device as described in claim 1, it is characterised in that：
First movement transmission plate (1.6) is circular plate structure, and center is uniformly distributed circular through hole with circumferential, and surrounding circular arc wall face is symmetrical
Distribution, it is easy for removal and installation.
6. a kind of larynx hydrant change propulsive solid propellant rocket ground test device as described in claim 1, it is characterised in that：
Second larynx, which tethers bar (1.11) both ends, threaded hole, and is uniformly provided with deep trouth for axis dynamic sealing in external cylindrical surface.
7. a kind of larynx hydrant change propulsive solid propellant rocket ground test device as described in claim 1,2,3,4,5 or 6,
It is characterized in that：Working method includes the following steps：
Step 1：Left fixed cylinder (2.3) gas pressure intensity, larynx bolt (2.8) displacement regulated quantity, control essence are determined according to test objective
Degree；
Step 2：Selection meets displacement sensor (1.13), the pull pressure sensor of test objective range
(1.10)；
Step 3：Assemble ground according to a kind of larynx hydrant change propulsive solid propellant rocket ground test device connection relation
Face test device；
Step 4：Check reasonability and the assembly of a kind of larynx hydrant change propulsive solid propellant rocket ground test device
Stability；
Step 5：By accessing high pressure gas on pressure sensor seat (2.7), second is driven using stepping motor (1.2)
Larynx tethers bar (1.11) reciprocating motion, the air-tightness of check device；
Step 6：If a kind of larynx hydrant change propulsive solid propellant rocket ground test device gas leakage, step 5 is repeated
Until ground test device reaches expected requirement；
Step 7：It is selected to execute step 8 or step 9 according to test objective, carries out corresponding ground testing experiment；
Step 8：Mechanism (2) is emulated when carrying out the load characteristic for the larynx bolt (2.8) that size is tested in cold air experimental study, second
Larynx tethers the larynx bolt (2.8) of bar (1.11) connection experiment size；The reciprocal fortune of bar is tethered by stepping motor (1.2) promotion larynx
It is dynamic, realize that the displacement to larynx bolt (2.8) is adjusted, the larynx bolt (2.8) that experiment size is acquired by pull pressure sensor (1.10) is negative
Carry data；Change input cold air pressure in experiment, realizes the research of different pressure lower larynx bolt (2.8) load characteristics；
Step 9：Emulate mechanism (2) when under analysis-driven mechanism (1) bringing onto load response time and when control accuracy, the
Two larynxs tether bar (1.11) connection compressed spring (2.5)；The elastic force that compressed spring (2.5) provides tethers bar for simulating the second larynx
(1.11) axially loaded in motion process, emulation mechanism (2) axially loaded tether bar (1.9), second by being mounted on the first larynx
Larynx tethers the intermediate pull pressure sensor (1.10) of bar (1.11) and measures, and passes to driving mechanism (1) control by Real-time Feedback
System processed, for analysis closed-loop control lower drive mechanism (1) load-carrying response time and control accuracy；By changing in experiment
Variable compression spring (2.5) rigidity, realizes the experiment of different thrust lower drive mechanism (1) load-carrying response times and control accuracy
Verification.
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| CN201810435205.0A CN108590889B (en) | 2018-05-09 | 2018-05-09 | Throat bolt type variable thrust solid rocket engine ground testing device |
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| CN201810435205.0A CN108590889B (en) | 2018-05-09 | 2018-05-09 | Throat bolt type variable thrust solid rocket engine ground testing device |
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| CN109632171A (en) * | 2019-01-08 | 2019-04-16 | 陕西航天西诺美灵电气有限公司 | A kind of rocket engine micro-force measuring apparatus |
| CN110109374A (en) * | 2019-05-13 | 2019-08-09 | 九州云箭(北京)空间科技有限公司 | The Hardware In The Loop Simulation Method and device of liquid-propellant rocket engine thrust regulating system |
| CN110344966A (en) * | 2019-07-16 | 2019-10-18 | 北京强度环境研究所 | A kind of construction device and method of solid-rocket ground experiment free boundary |
| CN111766073A (en) * | 2020-07-09 | 2020-10-13 | 北京理工大学 | Solid rocket engine high-speed spin test holding device |
| CN113255145A (en) * | 2021-06-03 | 2021-08-13 | 中国人民解放军国防科技大学 | Attitude and orbit control engine throat plug motion time sequence experimental design method, device and equipment |
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| CN110344966B (en) * | 2019-07-16 | 2021-01-05 | 北京强度环境研究所 | Device and method for constructing free boundary of solid rocket ground test |
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| CN111766073A (en) * | 2020-07-09 | 2020-10-13 | 北京理工大学 | Solid rocket engine high-speed spin test holding device |
| WO2022068703A1 (en) * | 2020-10-04 | 2022-04-07 | 西安航天动力测控技术研究所 | Thrust transfer apparatus for ignition test of solid rocket engine in form of rear skirt connection |
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| CN113255145A (en) * | 2021-06-03 | 2021-08-13 | 中国人民解放军国防科技大学 | Attitude and orbit control engine throat plug motion time sequence experimental design method, device and equipment |
| CN113255145B (en) * | 2021-06-03 | 2021-09-24 | 中国人民解放军国防科技大学 | Attitude and orbit control engine throat plug motion time sequence experimental design method, device and equipment |
| CN113638823A (en) * | 2021-08-10 | 2021-11-12 | 北京理工大学 | Needle valve type flow-adjustable gas generator ground test device |
| CN113638823B (en) * | 2021-08-10 | 2022-06-17 | 北京理工大学 | Needle valve type flow-adjustable gas generator ground test device |
| CN113933044A (en) * | 2021-12-09 | 2022-01-14 | 星河动力(北京)空间科技有限公司 | Test method, device and platform for flexible joint assembly of rocket engine spray pipe |
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