CN107831015B - A kind of high thrust solid propellant rocket piezoelectric tester - Google Patents
A kind of high thrust solid propellant rocket piezoelectric tester Download PDFInfo
- Publication number
- CN107831015B CN107831015B CN201710999601.1A CN201710999601A CN107831015B CN 107831015 B CN107831015 B CN 107831015B CN 201710999601 A CN201710999601 A CN 201710999601A CN 107831015 B CN107831015 B CN 107831015B
- Authority
- CN
- China
- Prior art keywords
- plate
- rotary table
- dynamometer
- pull rod
- cylinder
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Testing Of Engines (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The invention belongs to sense, observation and control technology field, provide a kind of high thrust solid propellant rocket piezoelectric tester.The present invention realizes the requirement of the six-dimensional force on-line proving of solid propellant rocket, and devises corresponding verifying structure to calibration result, increases the reliability of the present apparatus.Apparatus of the present invention are made of support frame, castor, support rotary table, lateral loading device, adapter frame, dynamometer, standard force snesor, connecting cylinder, hydraulic power system.The device range is big, and processability of product structure is good, and precision is high, can carry out the test of non-coplanar force and torque simultaneously, can more comprehensively, accurate test engine thrust vectoring characteristic.
Description
Technical field
The invention belongs to sense, observation and control technology field, be related to a kind of high thrust solid propellant rocket piezoelectric tester,
It is significant in the thrust vectoring test of the fields such as aerospace, defence and military engine, it is specifically for use in solid-rocket
The thrust vectoring of engine is tested.
Background technique
Higher and higher to the reliability requirement of propulsion system with the fast development of modern aerospace industry, engine pushes away
The accurate control of power is of great significance to control aircraft operation posture, raising targeting precision etc..By solid propellant propulsion
The chemical energy of agent is referred to as solid propellant rocket as the rocket engine of the energy, has been widely used as rocket, guided missile, universe
The power device of the various aircraft such as airship and space shuttle.Thrust vectoring is the critical performance parameters of rocket engine, in order to
Ensure to succeed in sending up using engine as the aircraft of power device, engine must try its performance before being delivered for use
Test examination, testing rear up to standard can be used as the power device of rocket.
For testing, the device of Thrust of Solid Rocket Motor vector can be divided into multicomponent balance and multi dimension pushes away both at home and abroad
Two class of force vector test bay, wherein six square phase thrust vectoring test bay is current most commonly used test device, but there are still
Such as the problems such as engine installation and debugging are complicated and the time is long, Test Rig intrinsic frequency is lower.
The six degree of freedom Solid Rocket Engine Test platform of Polytechnics, Florida design is at present for finding
Relatively advanced thrust vectoring test device can carry out the test of rocket engine six-dimensional force, main to test 10000 to power
The power of pound (about 44482N), but this force value is actually needed surveyed force value for solid propellant rocket and still differs greatly.
Also, this test device can not have corresponding verification to test result after test, and the reliability of test result is still
There are problems.
Therefore, for the test of Thrust of Solid Rocket Motor vector, one kind is needed to can be convenient, reliably measurement pushes away greatly
The test device of power Thrust of Solid Rocket Motor vector.The present invention is designed corresponding on the basis of using piezoelectric transducer
Structure test Thrust of Solid Rocket Motor vector.
Summary of the invention
Present invention aims at the on-line testings for realizing Thrust of Solid Rocket Motor vector, start meeting solid-rocket
Machine is convenient, reliably installation and debugging while, can be realized the requirement of solid propellant rocket high thrust test.
Technical solution of the present invention:
A kind of high thrust solid propellant rocket piezoelectric tester, including support frame 6, caster device 7, adapter frame 1, branch
Hold round platform 4, lateral loading device 3, dynamometer 2, standard force snesor 10, it is main to hydraulic power system 5, back-end central pull rod 8,
Front end center pull rod 11, connecting cylinder 9, scaling board 12 and load nut 13；
The support frame 6 is welded by square substrate, 4 reinforcement studs and 8 reinforcement transverse bars, reinforces stud difference
It is vertically welded on four angles of square substrate；Two groups of caster devices 7 are separately mounted to 6 two sides of support frame；
The support rotary table 4 is made of upper plate, lower plate, loaded cylinder and reinforcing rib, is mounted on 6 upper end of support frame；
Wherein, upper plate is connected with lower plate by loaded cylinder, and loaded cylinder is cylinder；The reinforcing rib is divided into two kinds, and one kind is square plate,
It is installed between upper plate and lower plate, and is fixed on loaded cylinder；Another kind is T-type plate, and T-type plate is installed between upper plate and lower plate, T-type
The transverse slat of plate is located at outside, at the keyway of upper surface；Square plate and T-type plate are uniform, are alternately mounted on upper plate and lower plate
Centre forms an entirety；
The upper surface of the support rotary table 4 is equipped with 8 uniformly distributed keyways, and key is fixed in keyway by pin and bolt,
As 8 stations；The identical threaded hole of 5 groups of spacing is arranged on each station in upper surface of the support rotary table 4, it is any alternate
Two groups of threaded holes realize positioning, realize the transformation of 3 positions；When Y-direction two opposite lateral loading devices 3 occupy phase respectively
When anti-two extreme positions, i.e. realization torque MXSimulation loading；
The lateral loading device 3 totally 8, the outer of the upper surface of support rotary table 4 is uniformly mounted on by key and bolt
Circumference is slided each along its corresponding key；
The dynamometer 2 includes dynamometer top plate, dynamometer bottom plate and sensor, is fixedly installed on support rotary table 4
Surface；Wherein, dynamometer top plate and dynamometer bottom plate are the square plate equipped with centre bore, sensor be connected to top plate and bottom plate it
Between, form an entirety；
Rotary table with holes, is fixed on dynamometer top plate centered on the scaling board 12, passes through rotary table and dynamometer top
The centre bore of plate realizes positioning；
1 lower end of adapter frame is by being threadably mounted at 12 upper surface of scaling board, 1 upper end of adapter frame and rocket engine
Connection；
9 upper end of connecting cylinder is fixed on the lower surface of support 4 lower plate of rotary table, coaxial with loaded cylinder；
It is described it is main to hydraulic power system 5 include hydraulic cylinder, back-end central pull rod 8, standard force snesor 10 and front end
Center pull rod 11, front end center pull rod 11 and back-end central pull rod 8 are both connected on standard force snesor 10, front end center pull rod
11 pass through dynamometer 2 and scaling board 12, fixed by load nut 13；Back-end central pull rod 8 is connect with hydraulic cylinder；It is main to hydraulic
Dynamical system 5 is bolted on 9 lower end of connecting cylinder；
The caster device 7 freely can rise and fall.
The lateral loading device 3 removes the lateral loading device 3 of side, and heightening device is fixed on branch and is held round
4 upper surface of platform, then lateral loading device 3 is fixed on heightening device by key and bolt, to realize moment M y, M respectivelyZ
Simulation loading.
While meeting stiffness by itself, solve that hydraulic cylinder in assembling process is difficult to install is asked for the design of support frame
Topic；The use of castor may be implemented the free-moving demand of test device, when test, castor be risen, substrate and ground face contact,
And device is fixed on by designated position by foundation bolt.Adapter frame is used for connecting test device and solid propellant rocket, root
According to the size of engine the adjustment adapter frame and rocket engine connecting pin of different model, engine installation process simple and convenient；
Support rotary table by 16, two kinds of (8 every kind) shapes, reinforcing rib of different sizes form.When test, main Xiang Li, lateral force are all
Correspondingly act on rotary table, in addition, other parts and components such as adapter frame, dynamometer are also directly or indirectly mounted on rotary table,
Therefore it is required that rotary table has very high intensity, rigidity to bear the power generated in gravity and loading procedure；8 lateral loading devices with
And dynamometer is directly connected with rotary table upper surface, in order to guarantee that lateral loading device is vertically mounted on support rotary table surface, needs
There is very high machining accuracy on rotary table surface.It supports rotary table as entire test macro most important components, needs very high
Intensity, rigidity and intrinsic frequency.
Beneficial effects of the present invention: the present invention realizes the thrust vectoring measurement of solid propellant rocket, and by vertical
The design of structure eliminates influence of the engine gravity to lateral force measurement result, and solves traditional test device rocket motor
The problems such as machine installation is complicated, testing range range is small.Meanwhile the lateral force loading device of the present invention has 8 stations, in orthogonal test
After the completion, diagonal plays the role of verifying, ensure that the reliability of device experiment result.The device range is big (main
The simulation loading of Xiang Like realization 300000N), processability of product structure is good, and precision is high, and installation and debugging are simple, can carry out sky simultaneously
Between power and torque test, can more comprehensively, accurate test engine thrust vectoring characteristic.
Detailed description of the invention
Fig. 1 is the sectional view of apparatus of the present invention.
Fig. 2 is the overall structure diagram of apparatus of the present invention.
Fig. 3 is heightening device schematic diagram.
Fig. 4 is support rotary table schematic diagram.
In figure: 1 adapter frame；2 dynamometers；3 sides are to loading device；4 support rotary tables；
5 is main to hydraulic power system；6 support frames；7 caster devices；8 back-end central pull rods；
9 connecting cylinder, 10 standard force snesor；11 front end center pull rods；12 scaling boards；13 load nuts.
Specific embodiment
Below in conjunction with attached drawing and technical solution, a specific embodiment of the invention is further illustrated.
It is main to hydraulic power system 5 after connecting hydraulic oil, back-end central pull rod 8 under the driving of hydraulic oil by drive mark
Quasi- force snesor 10 is pulled down with front end center pull rod 11, and the load nut 13 by connecting with front end center pull rod 11 is final
Power is acted on scaling board 12, the main simulation loading to power X-direction is realized；Y-direction lateral force be laterally connect it is hydraulic
After oil, power is respectively acting on to realize the simulation loading of Y-direction by scaling board side by lateral loading device 3.Z-direction is same
Reason.It is identical that 5 groups of spacing are arranged on the support each station in 4 upper surface of rotary table, equirotal threaded hole, lateral loading device 3
It can be slided along key, and realize positioning by any two groups alternate threaded holes, finally realize the transformation of 3 stations.Work as Y-direction
When two opposite lateral loading devices 3 occupy two opposite extreme positions respectively, torque M can be realizedXSimulation loading.
The lateral loading device 3 in Y-direction side is removed, heightening device is fixed on support 4 upper surface of rotary table, the connection type of heightening device
(being fixed by bolt and key) identical as the connection type of lateral loading device 3, and it is fixed in three of corresponding station
Middle position in position, then lateral loading device 3 is fixed on heightening device by key and bolt, so as to real respectively
Existing moment MZSimulation loading.Similarly, moment M may be implementedYSimulation loading.Three-dimensional orthogonal calibration (i.e. FX、FY、FZ) tested
Cheng Hou can verify lateral force calibration result by the lateral loading device 3 of diagonal positions, increase the device pair
The reliability of thrust vectoring test.In addition, in order to simulate the test mode of vectorial force, the present apparatus, which devises, to be able to achieve 2 ° of deflections and adds
The hydraulic power system of load can carry out the load of 8 stations, and test obtained vectorial force out by respective formula reverse, lead to
Measurement of comparison value and theoretical value are crossed to verify the measurement accuracy of the present apparatus, also improves the reliability of test macro.
Claims (2)
1. a kind of high thrust solid propellant rocket piezoelectric tester, which is characterized in that the high thrust solid-rocket hair
Motivation piezoelectric tester includes support frame (6), caster device (7), adapter frame (1), support rotary table (4), lateral loading device
(3), dynamometer (2), it is main to hydraulic power system (5), connecting cylinder (9), scaling board (12) and load nut (13)；
The support frame (6) is welded by square substrate, 4 reinforcement studs and 8 reinforcement transverse bars, is reinforced stud and is hung down respectively
Directly it is welded on four angles of square substrate；Two groups of caster devices (7) are separately mounted to support frame (6) two sides；
The support rotary table (4) is made of upper plate, lower plate, loaded cylinder and reinforcing rib, is mounted on support frame (6) upper end；
Wherein, upper plate is connected with lower plate by loaded cylinder, and loaded cylinder is cylinder；The reinforcing rib is divided into two kinds, and one kind is square plate,
It is installed between upper plate and lower plate, and is fixed on loaded cylinder；Another kind is T-type plate, and T-type plate is installed between upper plate and lower plate, T-type
The transverse slat of plate is located at outside, at the keyway of upper surface；Square plate and T-type plate are uniform, are alternately mounted on upper plate and lower plate
Centre forms an entirety；
The upper surface of the support rotary table (4) is equipped with 8 uniformly distributed keyways, and key is fixed in keyway by pin and bolt, i.e.,
For 8 stations；The identical threaded hole of 5 groups of spacing is arranged on each station in upper surface of the support rotary table (4), it is any alternate
Two groups of threaded holes realize positioning, realize the transformation of 3 positions；When Y-direction two opposite lateral loading devices (3) occupy respectively
When opposite two extreme positions, i.e. realization torque MXSimulation loading；
The lateral loading device (3) totally 8 is uniformly mounted on the outer of the upper surface of support rotary table (4) by key and bolt
Circumference is slided each along its corresponding key；
The dynamometer (2) includes dynamometer top plate, dynamometer bottom plate and sensor, is fixedly installed in support rotary table (4)
Surface；Wherein, dynamometer top plate and dynamometer bottom plate are the square plate equipped with centre bore, sensor be connected to top plate and bottom plate it
Between, form an entirety；
Rotary table with holes, is fixed on dynamometer top plate, passes through rotary table and dynamometer top plate centered on the scaling board (12)
Centre bore realize positioning；
Adapter frame (1) lower end is by being threadably mounted at scaling board (12) upper surface, adapter frame (1) upper end and rocket motor
Machine connection；
Described connecting cylinder (9) upper end is fixed on the lower surface of support rotary table (4) lower plate, coaxial with loaded cylinder；
It is described it is main to hydraulic power system (5) include hydraulic cylinder, back-end central pull rod (8), standard force snesor (10) and before
It holds center pull rod (11), front end center pull rod (11) and back-end central pull rod (8) are both connected on standard force snesor (10), preceding
Center pull rod (11) are held to pass through dynamometer (2) and scaling board (12), it is fixed by load nut (13)；Back-end central pull rod (8)
It is connect with hydraulic cylinder；It is main to be bolted on connecting cylinder (9) lower end to hydraulic power system (5)；
The caster device (7) freely can rise and fall.
2. high thrust solid propellant rocket piezoelectric tester according to claim 1, which is characterized in that by side
Lateral loading device (3) removes, and heightening device is fixed on support rotary table (4) upper surface, then lateral loading device (3) is passed through
Key and bolt are fixed on heightening device, to realize moment M y, M respectivelyZSimulation loading.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710999601.1A CN107831015B (en) | 2017-10-24 | 2017-10-24 | A kind of high thrust solid propellant rocket piezoelectric tester |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710999601.1A CN107831015B (en) | 2017-10-24 | 2017-10-24 | A kind of high thrust solid propellant rocket piezoelectric tester |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107831015A CN107831015A (en) | 2018-03-23 |
| CN107831015B true CN107831015B (en) | 2019-06-07 |
Family
ID=61648930
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710999601.1A Active CN107831015B (en) | 2017-10-24 | 2017-10-24 | A kind of high thrust solid propellant rocket piezoelectric tester |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107831015B (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109323834B (en) * | 2018-11-22 | 2020-04-28 | 大连理工大学 | Six-dimensional dynamic force generating device |
| CN110836743B (en) * | 2019-10-31 | 2021-09-03 | 南京理工大学 | Thrust vector test bench for main side thrust decoupling |
| CN110836744B (en) * | 2019-10-31 | 2021-06-11 | 南京理工大学 | Small-size vertical thrust vector testboard |
| CN113959621B (en) * | 2021-10-31 | 2023-06-16 | 西安航天动力测控技术研究所 | Test method for measuring multi-component force of solid rocket engine by five components |
| CN113959622B (en) * | 2021-10-31 | 2023-08-29 | 西安航天动力测控技术研究所 | Test device for five-component measurement of multi-component force of solid rocket engine |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101464215A (en) * | 2009-01-15 | 2009-06-24 | 大连理工大学 | Propulsion test device of piezo-electricity type rocket motor |
| CN102680238A (en) * | 2012-05-29 | 2012-09-19 | 西北工业大学 | Non-contact engine thrust testing method and device |
| CN103278281A (en) * | 2013-04-25 | 2013-09-04 | 北京航天试验技术研究所 | Turntable-method thrust vector measuring system |
| CN105043633A (en) * | 2015-07-13 | 2015-11-11 | 大连理工大学 | Vertical type integrated thrust vector testing device |
| CN107152980A (en) * | 2017-05-16 | 2017-09-12 | 大连理工大学 | A kind of piezoelectric type becomes force value and compares caliberating device |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20130019587A1 (en) * | 2011-07-21 | 2013-01-24 | Isaac Hoffman | Thruster devices and methods of making thruster devices for use with thrust vector control systems |
-
2017
- 2017-10-24 CN CN201710999601.1A patent/CN107831015B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101464215A (en) * | 2009-01-15 | 2009-06-24 | 大连理工大学 | Propulsion test device of piezo-electricity type rocket motor |
| CN102680238A (en) * | 2012-05-29 | 2012-09-19 | 西北工业大学 | Non-contact engine thrust testing method and device |
| CN103278281A (en) * | 2013-04-25 | 2013-09-04 | 北京航天试验技术研究所 | Turntable-method thrust vector measuring system |
| CN105043633A (en) * | 2015-07-13 | 2015-11-11 | 大连理工大学 | Vertical type integrated thrust vector testing device |
| CN107152980A (en) * | 2017-05-16 | 2017-09-12 | 大连理工大学 | A kind of piezoelectric type becomes force value and compares caliberating device |
Non-Patent Citations (2)
| Title |
|---|
| 对火箭发动机推力矢量测试系统的标定;王志勇等;《传感器与微系统》;20070120;全文 |
| 火箭发动机推力矢量测量平台的原理与结构;高长银等;《压电与声光》;20100615;全文 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107831015A (en) | 2018-03-23 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107831015B (en) | A kind of high thrust solid propellant rocket piezoelectric tester | |
| CN104111138A (en) | Large-scale missile engine six-component dynamometry and calibrating device | |
| CN103471751B (en) | High-precision strain type torque sensor | |
| CN111551328B (en) | Six-degree-of-freedom vibration excitation system with parallel configuration of three-stage Stewart mechanism | |
| CN109115510B (en) | Six-component force test bed and error determination method thereof | |
| CN103645455B (en) | Probe correcting device | |
| CN104535335A (en) | Multi-axial loading axle assembly endurance test bed | |
| CN204359539U (en) | A kind of Multi-axial Loading axle assembly long duration test stand | |
| CN106840644B (en) | Reliability test bed for electromagnetic and electric push rod mixed loading tool rest | |
| CN102564685A (en) | Multi-dimensional force sensor dynamic experiment device based on stable-state sine exciting force | |
| CN206710057U (en) | A kind of six component measurement balances and model for wind tunnel experiment | |
| CN104458303B (en) | Heavy numerical control vertical lathe reliability test system | |
| CN107179242B (en) | A kind of manual simplified true triaxil tester | |
| CN102183893B (en) | Low-frequency large-deflection adjustable inertia load analog piece | |
| US20210116342A1 (en) | Mechanical performance testing device and hydraulic control system thereof | |
| CN111948077A (en) | High-temperature high-pressure composite fretting wear test device | |
| CN107806950B (en) | A kind of high thrust vector vertical device for testing structure | |
| CN110501114A (en) | Three-dimensional force sensor Calibration of Dynamic device and method | |
| CN103698073A (en) | Device and method for testing fastening pressure of shape memory alloy pipe joint | |
| CN203298928U (en) | Multi-component sensor calibration apparatus | |
| CN109323834B (en) | Six-dimensional dynamic force generating device | |
| CN109115512B (en) | Test bed for realizing six-component force model construction method and method for measuring vector thrust | |
| CN202002774U (en) | Three-dimensional measuring mechanism for realizing quality characteristic of flying object with wings | |
| CN216815843U (en) | Comparison type multi-component force sensor calibration device | |
| CN207742044U (en) | A kind of experimental rig of test electric vehicle charge interface bending property |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |