CN109357874A - A kind of engine test parameter measurement system for solid propellant rocket ground whirling test stand - Google Patents
A kind of engine test parameter measurement system for solid propellant rocket ground whirling test stand Download PDFInfo
- Publication number
- CN109357874A CN109357874A CN201811428615.9A CN201811428615A CN109357874A CN 109357874 A CN109357874 A CN 109357874A CN 201811428615 A CN201811428615 A CN 201811428615A CN 109357874 A CN109357874 A CN 109357874A
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- China
- Prior art keywords
- optical
- acquisition
- port
- record system
- photoelectric conversion
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Classifications
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- 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
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01D—MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
- G01D21/00—Measuring or testing not otherwise provided for
- G01D21/02—Measuring two or more variables by means not covered by a single other subclass
-
- G—PHYSICS
- G08—SIGNALLING
- G08C—TRANSMISSION SYSTEMS FOR MEASURED VALUES, CONTROL OR SIMILAR SIGNALS
- G08C17/00—Arrangements for transmitting signals characterised by the use of a wireless electrical link
- G08C17/02—Arrangements for transmitting signals characterised by the use of a wireless electrical link using a radio link
Abstract
The present invention proposes that a kind of engine test parameter measurement system for solid propellant rocket ground whirling test stand, including sensor, local acquisition and record system, light collecting ring and long-range test run number adopt center；Local acquisition and record system are mounted in the equipment box on ground whirling test stand shaft top, the local acquisition of signal access of sensor acquisition and record system；Also there is network communication photoelectric conversion module and D.C. regulated power supply, local acquisition and record system are connect with the electric port of network communication photoelectric conversion module by twisted pair cable in equipment box；The optical port of network communication photoelectric conversion module is connect with ring interface in light collecting ring by being located at the optical fiber of interior of rotating shaft optical-fibre channel；The outer ring interface of light collecting ring is connected to the host computer optical-electric module optical port that long-range test run number adopts center by the optical fiber being located in outdoor cable pipeline, and the host computer network port is accessed by twisted pair cable in the electric port of host computer optical-electric module.The present invention substantially increases the reliability for obtaining data.
Description
Technical field
The present invention relates to solid propellant rocket ground rotation test technical fields, specially a kind of to send out for solid-rocket
The engine test parameter measurement system of motivation ground whirling test stand.
Background technique
Solid propellant rocket (abbreviation solid engines) ground experiment (abbreviation test run) be solid engines from develop, examination
An important stage for testing production is the important channel of verifying, examination solid engines various requirement index.
In solid engines commissioning process, need the major parameter for measuring and recording to have: the pressure of combustion chamber is big
Small, motor body surface deflection and temperature change etc..
In commissioning process, extremely severe vibration, noise circumstance can be generated, especially in the rotation using heavy-duty motor
In testing stand environment, intense electromagnetic interference problem is also had, brings huge challenge to parameter test system.Therefore, development meets
The test method and measuring system of solid engines measuring trial run parameter demand have importance.
At present in solid engines commissioning process, the composition of measuring trial run parameter system be it is such, i.e., measurement combustion chamber
The pressure transducer of pressure, the foil gauge for measuring shell surface deformation amount and the thermocouple for measuring casing surface temperature, are all logical
The connection of conducting wire cable is crossed, then is drawn by the collecting ring of rotary shaft, signal acquisition is accessed finally by conducting wire cable and data is remembered
The input terminal of recording system.
The deficiency of the measuring system composition of the prior art has at 4 points, first is that signal poor anti jamming capability, entire channel environment
All uncertainty may be brought to measuring signal；Second is that channel is at high cost, because one sensor signal of every increase will be put into
One complete cable passage；Third is that, once coming into operation because system is built up, being almost impossible to change without scalability
The channel number of afflux ring interface；Fourth is that Information Security is poor, especially for solid engines test run it is this have it is irreversible,
Even more so for high-cost test process, once measurement route goes wrong, data are just lost completely, even if using bilateral
It is also inevitable that road backs up this high cost way.
Summary of the invention
In order to solve the problems existing in the prior art, the present invention proposes a kind of for the rotation test of solid propellant rocket ground
The engine test parameter measurement system of platform, by realizing pressure transducer, foil gauge and thermocouple etc. on whirling test stand
The local acquisition of sensor signal and data record, then data are transferred in remote testing data by TCP/IP network protocol
The heart realizes that data show, interact and store again at test data center, eliminates the channel signal of former measuring system appearance not
Deterministic disturbance reduces a large amount of channel and drains and disturbs work, shortens the test run preparatory period, while also substantially increasing acquisition number
According to reliability.
The technical solution of the present invention is as follows:
A kind of engine test parameter measurement system for solid propellant rocket ground whirling test stand, including
Combustion chamber pressure sensor, foil gauge and thermocouple；Combustion chamber pressure sensor is installed to Solid Rocket Motor combustion chamber pressure
On power measured hole, foil gauge and thermocouple are respectively adhered on the specified position of solid rocket motor case, it is characterised in that:
It further include that local acquisition and record system, light collecting ring and long-range test run number adopt center；
The equipment that the local acquisition and record system are mounted on the swing boom configuration shaft top of ground whirling test stand
In case, combustion chamber pressure sensor, the local acquisition of signal access and note of foil gauge and thermocouple by conducting wire cable by acquisition
Recording system；
Also there is network communication photoelectric conversion module and D.C. regulated power supply, D.C. regulated power supply is this in the equipment box
Ground acquisition and record system and the power supply of network communication photoelectric conversion module；Local acquisition and record system and network communication photoelectricity turn
The electric port of mold changing block is connected by twisted pair cable；
The smooth collecting ring is arranged in the whirling test stand of ground in the rotary shaft of stage body basement, the rotary shaft
Inside has optical-fibre channel, and ring interface is by being located at rotary shaft in the optical port and light collecting ring of network communication photoelectric conversion module
The optical fiber of internal Fibre Channel connects；
The outer ring interface of light collecting ring is connected to long-range test run number by the optical fiber being located in outdoor cable pipeline and adopts center
Host computer optical-electric module optical port, host computer network-side is accessed by twisted pair cable in the electric port of host computer optical-electric module
Mouthful.
Further preferred embodiment, a kind of engine test for solid propellant rocket ground whirling test stand
Parameter measurement system, it is characterised in that: adopt in locally acquisition and record system and long-range test run number and all have data in center
Memory module, by combustion chamber pressure sensor, foil gauge is synchronize stored in local acquisition and records with the acquisition signal of thermocouple
System and long-range test run number are adopted in center.
Beneficial effect
This invention removes the channel signal uncertainty interference that former measuring system occurs, and reduce a large amount of channel and drain
Work is disturbed, the test run preparatory period is shortened, while also substantially increasing the reliability for obtaining data.The invention avoids increases
One sensor signal will be laid with the trouble of cable passage over long distances again, and the system expandability greatly enhances.Using this
After invention, Information Security is obtained preferably backing up and be ensured, local data actuation and long-range firing test data center are right in real time simultaneously
Parameter measurement data is saved, and local data actuation additionally uses data black box safeguard measure.
Additional aspect and advantage of the invention will be set forth in part in the description, and will partially become from the following description
Obviously, or practice through the invention is recognized.
Detailed description of the invention
Above-mentioned and/or additional aspect of the invention and advantage will become from the description of the embodiment in conjunction with the following figures
Obviously and it is readily appreciated that, in which:
Fig. 1: engine test parameter measurement system composition schematic diagram.
Specific embodiment
The embodiment of the present invention is described below in detail, the examples of the embodiments are exemplary, it is intended to for explaining this
Invention, and be not considered as limiting the invention.
As shown in Figure 1, being mounted on the rotating arm of whirling test stand by the solid propellant rocket of test run, in commissioning process
In rotate with rotary shaft.And it is used for the engine test parameter measurement system packet of solid propellant rocket ground whirling test stand
Include combustion chamber pressure sensor, foil gauge and thermocouple；Combustion chamber pressure sensor is installed to Solid Rocket Motor combustion chamber
On pick-up hole, foil gauge and thermocouple are respectively adhered on the specified position of solid rocket motor case, are additionally wrapped
It includes local acquisition and record system, light collecting ring and long-range test run number adopts center.
The equipment that the local acquisition and record system are mounted on the swing boom configuration shaft top of ground whirling test stand
In case, combustion chamber pressure sensor, the local acquisition of signal access and note of foil gauge and thermocouple by conducting wire cable by acquisition
Recording system, in the present embodiment, local acquisition and record system are by NI cDAQ-9137 cabinet and corresponding function data collecting card group
At.
Also there is TCP/IP network communication photoelectric conversion module and D.C. regulated power supply, DC voltage-stabilizing electricity in the equipment box
Source is local acquisition and record system and the power supply of network communication photoelectric conversion module；Local acquisition and record system and TCP/IP net
The electric port of network communication photoelectric conversion module is connected by twisted pair cable.
The smooth collecting ring is arranged in the whirling test stand of ground in the rotary shaft of stage body basement, the rotary shaft
Inside has optical-fibre channel, and the optical port of TCP/IP network communication photoelectric conversion module is with ring interface in light collecting ring by being located at
The optical fiber of interior of rotating shaft optical-fibre channel connects.
The outer ring interface of light collecting ring is connected to long-range test run number by the optical fiber being located in outdoor cable pipeline and adopts center
Host computer optical-electric module optical port, the electric port of host computer optical-electric module accesses the network-side of host computer by twisted pair cable
Mouthful.
This invention removes the channel signal uncertainty interference that former measuring system occurs, and reduce a large amount of channel and drain
Work is disturbed, the test run preparatory period is shortened, while also substantially increasing the reliability for obtaining data.The invention avoids increases
One sensor signal will be laid with the trouble of cable passage over long distances again, and the system expandability greatly enhances.Using this
After invention, Information Security is obtained preferably backing up and be ensured, local data actuation and long-range firing test data center are right in real time simultaneously
Parameter measurement data is saved, and local data actuation additionally uses data black box safeguard measure.
Although the embodiments of the present invention has been shown and described above, it is to be understood that above-described embodiment is example
Property, it is not considered as limiting the invention, those skilled in the art are not departing from the principle of the present invention and objective
In the case where can make changes, modifications, alterations, and variations to the above described embodiments within the scope of the invention.
Claims (2)
1. a kind of engine test parameter measurement system for solid propellant rocket ground whirling test stand, including combustion chamber
Pressure transducer, foil gauge and thermocouple；Combustion chamber pressure sensor is installed to Solid Rocket Motor combustion chamber pressure measurement
Kong Shang, foil gauge and thermocouple are respectively adhered on the specified position of solid rocket motor case, it is characterised in that: further include
Local acquisition and record system, light collecting ring and long-range test run number adopt center；
The local acquisition and record system are mounted in the equipment box on swing boom configuration shaft top of ground whirling test stand,
By the signal access of acquisition, locally acquisition and record are by conducting wire cable for combustion chamber pressure sensor, foil gauge and thermocouple
System；
Also there is network communication photoelectric conversion module and D.C. regulated power supply, D.C. regulated power supply is local adopts in the equipment box
Collection and record system and the power supply of network communication photoelectric conversion module；Local acquisition and record system and network communication photoelectric conversion mould
The electric port of block is connected by twisted pair cable；
The smooth collecting ring is arranged in the whirling test stand of ground in the rotary shaft of stage body basement, the interior of rotating shaft
With optical-fibre channel, ring interface passes through positioned at interior of rotating shaft in the optical port and light collecting ring of network communication photoelectric conversion module
The optical fiber of optical-fibre channel connects；
The outer ring interface of light collecting ring is connected to long-range test run number by the optical fiber being located in outdoor cable pipeline and adopts the upper of center
The host computer network port is accessed by twisted pair cable in the electric port of position machine optical-electric module optical port, host computer optical-electric module.
2. a kind of engine test parameter for solid propellant rocket ground whirling test stand is surveyed according to claim 1
Amount system, it is characterised in that: adopted in locally acquisition and record system and long-range test run number and all have data storage mould in center
Block, by combustion chamber pressure sensor, foil gauge and the acquisition signal of thermocouple synchronize be stored in local acquisition and record system with
And long-range test run number is adopted in center.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811428615.9A CN109357874A (en) | 2018-11-27 | 2018-11-27 | A kind of engine test parameter measurement system for solid propellant rocket ground whirling test stand |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811428615.9A CN109357874A (en) | 2018-11-27 | 2018-11-27 | A kind of engine test parameter measurement system for solid propellant rocket ground whirling test stand |
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| CN109357874A true CN109357874A (en) | 2019-02-19 |
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| CN201811428615.9A Pending CN109357874A (en) | 2018-11-27 | 2018-11-27 | A kind of engine test parameter measurement system for solid propellant rocket ground whirling test stand |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110017992A (en) * | 2019-05-16 | 2019-07-16 | 九州云箭(北京)空间科技有限公司 | A kind of liquid rocket dynamical system test run method and its device |
| CN111766073A (en) * | 2020-07-09 | 2020-10-13 | 北京理工大学 | Solid rocket engine high-speed spin test holding device |
| CN112177805A (en) * | 2020-09-07 | 2021-01-05 | 湖北三江航天江河化工科技有限公司 | Engine ground test remote test system and test method |
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| US20020177978A1 (en) * | 2001-04-16 | 2002-11-28 | Obenhoff Ryan E. | Digital data acquisition system for manitoring and remote testing of gas and steam turbine performance parameters |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110017992A (en) * | 2019-05-16 | 2019-07-16 | 九州云箭(北京)空间科技有限公司 | A kind of liquid rocket dynamical system test run method and its device |
| CN111766073A (en) * | 2020-07-09 | 2020-10-13 | 北京理工大学 | Solid rocket engine high-speed spin test holding device |
| CN111766073B (en) * | 2020-07-09 | 2021-08-03 | 北京理工大学 | Solid rocket engine high-speed spin test holding device |
| CN112177805A (en) * | 2020-09-07 | 2021-01-05 | 湖北三江航天江河化工科技有限公司 | Engine ground test remote test system and test method |
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Application publication date: 20190219 |