CN111997786A - Portable measurement and control system box of rocket engine - Google Patents
Portable measurement and control system box of rocket engine Download PDFInfo
- Publication number
- CN111997786A CN111997786A CN202010689941.6A CN202010689941A CN111997786A CN 111997786 A CN111997786 A CN 111997786A CN 202010689941 A CN202010689941 A CN 202010689941A CN 111997786 A CN111997786 A CN 111997786A
- Authority
- CN
- China
- Prior art keywords
- box body
- measurement
- control system
- rocket engine
- lower box
- 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.)
- Pending
Links
- 238000005259 measurement Methods 0.000 title claims abstract description 42
- 230000003750 conditioning effect Effects 0.000 claims description 8
- 238000002955 isolation Methods 0.000 claims description 8
- 239000004973 liquid crystal related substance Substances 0.000 claims description 6
- 238000012360 testing method Methods 0.000 abstract description 13
- 238000012545 processing Methods 0.000 abstract description 4
- 238000004458 analytical method Methods 0.000 abstract description 3
- 238000004364 calculation method Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 239000003380 propellant Substances 0.000 description 2
- 230000004044 response Effects 0.000 description 2
- 239000007787 solid Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000000605 extraction Methods 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 230000036316 preload Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000005070 sampling Methods 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
Images
Classifications
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Testing Or Calibration Of Command Recording Devices (AREA)
Abstract
The invention discloses a portable measurement and control system box of a rocket engine, which comprises a box body part and a measurement and control system part, wherein the box body part comprises an upper box body, a lower box body, a hinge and a pull rod, the upper box body is connected with the lower box body through the hinge, and the upper end of the main plate surface of the lower box body is sequentially provided with a pressure signal input end, a temperature signal output end, a pulse output end and a power switch; the keyboard is arranged on the left side of the lower end of the keyboard, and the USB bus port is arranged on the right side of the lower end of the keyboard; the lower box body is internally provided with a measurement and control system part. The system can realize real-time recording and analysis of multiple test parameters, and can realize measurement and control of variable duty ratio through reasonable use of software and hardware. The processing of the subsequent data is convenient and labor-saving, the working efficiency is improved, and the working intensity of workers is reduced.
Description
Technical Field
The invention relates to the technical field of rocket engine measurement and control systems, in particular to a portable rocket engine measurement and control system box.
Background
The rocket engine test is various tests performed on the rocket engine from the beginning to the point before the rocket engine is put into service. In order to ensure that the rocket engine runs well in actual use, various performances of the rocket engine need to be tested on the ground. The rocket engine works under the harsh conditions of high temperature, high pressure, strong vibration and the like, and in order to check whether the engine reaches the design index, a series of strict tests are required to evaluate the structural reliability, performance parameters, service life, adaptability and the like before delivery and use.
The method is used for testing the research on a new structure, a new system, a new propellant, a new process and the like of the engine. A complete measurement and control system is needed to collect relevant data, so that solid support is provided for subsequent calculation. The existing related measurement and control equipment has the characteristics of single test parameter, low response speed, huge equipment, old calculation method and the like.
Disclosure of Invention
Aiming at the defects of the prior art, the invention provides a portable measurement and control system box of a rocket engine.
The technical scheme adopted by the invention is that the portable measurement and control system box of the rocket engine comprises a box body part and a measurement and control system part, wherein the box body part comprises an upper box body, a lower box body, a hinge and a pull rod, the upper box body is connected with the lower box body through the hinge, and the upper end of the main plate surface of the lower box body is sequentially provided with a pressure signal input end, a temperature signal output end, a pulse output end and a power switch; the keyboard is arranged on the left side of the lower end of the keyboard, and the USB bus port is arranged on the right side of the lower end of the keyboard; the lower box body is internally provided with a measurement and control system part, the measurement and control system part comprises a collection and measurement system and a control output system, the collection and measurement system is used for collecting signals of terminal equipment, and the control output system is used for outputting pulse signals.
Furthermore, the pull rod is installed on the back face of the lower box body, and a liquid crystal display screen is arranged on the main plate face of the upper box body after the upper box body is opened.
Furthermore, go up box edge be provided with wheel and hasp, the hasp is used for closed upper and lower box.
Furthermore, the edge of the lower box body is provided with a power supply external interface and a fan.
Furthermore, the measurement and control system comprises a switching terminal, a first voltage-stabilizing direct-current switch power supply, a second voltage-stabilizing direct-current switch power supply, a thermocouple isolation conditioning module, a sensor, a current isolation conditioning module, a collection card and a signal amplifier, and the voltage-stabilizing direct-current power supply is adopted to supply power to the equipment and supply power to the equipment in a pulse mode.
The invention has the beneficial effects that: the system can realize real-time recording and analysis of multiple test parameters, and can realize measurement and control of variable duty ratio through reasonable use of software and hardware. The system has the advantages that the subsequent data can be conveniently processed in a labor-saving manner, the working efficiency is improved, the working intensity of workers is reduced, the response speed of the signals is improved by adopting the solid-state signal amplifier, the accuracy of data acquisition is improved, and the thrust of the engine, the propellant consumption and the engine efficiency can be determined through the subsequent analysis of the data. The man-machine interaction display control interface is convenient for monitoring data and processing subsequent data in time, and is compact in structure, convenient to disassemble and convenient to carry and transport.
Drawings
FIG. 1 is a schematic diagram of a discrete integrated system.
FIG. 2 is a schematic structural diagram of a portable measurement and control system box of a rocket engine.
FIG. 3 is a schematic view of the front structure of the portable rocket engine measurement and control system box of the present invention.
FIG. 4 is a schematic view of a back structure of a rocket engine portable measurement and control system box.
FIG. 5 is a schematic view of a panel structure of a rocket engine portable measurement and control system case.
FIG. 6 is a partially exploded view of a rocket engine portable measurement and control system box according to the present invention.
The labels in the figure are: 1, putting the box body; 2-wheels; 3, locking and buckling; 4-liquid crystal display screen; 5-external interface of power supply; 6-a fan; 7-lower box body; 8-a transfer terminal; 9-voltage-stabilizing direct-current switching power supply 1; 10-voltage-stabilizing direct-current switching power supply 2; 11-a thermocouple isolation conditioning module; 12-a sensor; 13-a galvanic isolation conditioning module; 14-acquisition card; 15-a signal amplifier; 16-a guide rail; 17-a hinge; 18-a tie rod; 19-pressure signal input; 20-temperature signal output end; 21-a pulse output end; 22-power switch; 23-USB bus port; 24-keyboard.
Detailed Description
The invention will be further described with reference to fig. 1 to 6, wherein the ground single-machine test stand control system of the invention is a miniaturized control duplication system mainly established for completing a single-machine engine test, and the control system mainly completes high-precision time sequence control of a single engine. Meanwhile, the system has the functions of starting, emergency shutdown, program recognization, valve current collection and the like. The engine parameter measuring system is used for measuring, acquiring and processing data of parameters such as temperature, pressure, flow and the like in the engine test engineering.
The rocket engine measurement and control system box is divided into two parts, the control box is divided into a box body part and a measurement and control system part, the box body comprises an upper box body 1 and a lower box body 7, and the box body part comprises wheels 2, a liquid crystal display screen 4, a pull rod 18, a hinge 17, a lock catch 3, the liquid crystal display screen 4 and a keyboard 24. The hinge 17 is used for connecting and fixing the upper box body and the lower box body through screws, and a box lock catch 3 is arranged outside the closed box bodies of the two box bodies; an external pull rod 18 is mounted on the back of the lower box body through screws; wheels 2 are arranged outside the box body for convenient movement; the liquid crystal display 4 and the keyboard 24 are arranged for convenient display and operation.
The measurement and control system comprises a switching terminal 8, a first voltage-stabilizing direct-current switching power supply 9, a first voltage-stabilizing direct-current switching power supply 10, a thermocouple isolation conditioning module 11, a Hall sensor 12, a current isolation conditioning module 13, an acquisition card 14, an ART-USB2861 acquisition card and a signal amplifier 15. The power supply of the voltage-stabilizing direct-current power supply is adopted to ensure that the power is supplied to the equipment and simultaneously the pulse power supply is carried out. The control output system comprises a pressure signal input end 19, a temperature signal output end 20, a pulse output end and a USB bus port 23.
The acquisition control system realizes a measurement and control system which integrates multiple functions of signal acquisition, record storage and the like into a whole by utilizing a data acquisition and control system based on a virtual instrument according to test requirements and combining with the current advanced computer measurement and control technology.
The system comprises an upper computer system (Labview) depending on a Windows system, a signal acquisition card, an FPGA digital controller and an SSR relay drive circuit. The system comprises an acquisition and measurement part and a control output part. The working principle is as shown in the attached figure 1: the acquisition and measurement part mainly has the functions of acquiring a weak current signal (4-20mA) of the terminal equipment, converting the signal into actual pressure, current and the like, and displaying the actual pressure, current and the like on an upper computer interface (LabVIEW). The user can observe data, select a channel, store data and the like by having an upper computer interface. The sensor 12 (Hall pressure sensor) converts signals such as pressure and the like into 4-20mA current or 1-5V voltage, and transmits the current or the voltage to the acquisition board card. The acquisition card 14 converts the obtained analog signals into digital signals and transmits the digital signals to an upper computer system. The upper computer is driven by the DAQmx to restore the digital signals to obtain data types required by the user, such as pressure (MPa), extraction current (A) and the like.
In the control output system, a Labview upper computer pre-loads a test run pulse time sequence into an FPGA cache queue, and outputs a pulse signal according to a test run instruction. The FPGA outputs a high-level signal as 5V voltage, and 24V/36V pulse signal output is realized through a Solid State Relay (SSR) drive board.
The parameters of the acquisition and measurement system are as follows:
the signal type: 4-20mA/2-10V analog signals;
the number of channels: 24AI (difference);
resolution ratio: 16 bits;
and (3) measuring precision: 0.1% FS;
sampling rate: not less than 2 KS/s;
and (3) saving a data format: TDMS;
data processing: the supporting software can play back the intercepted data to generate an Excel file;
controlling and outputting system parameters:
the number of channels: 8 DO;
minimum step size: 1ms (the minimum period of high and low levels is 2ms in an ideal state);
and (3) control precision: 0.2 ms;
the power supply mode comprises the following steps: DC 5V/24V;
output voltage: DC 24V/36V.
Claims (5)
1. The portable measurement and control system box of the rocket engine is characterized in that: the temperature and pulse measuring and controlling box comprises a box body part and a measuring and controlling system part, wherein the box body part comprises an upper box body, a lower box body, a hinge and a pull rod, the upper box body is connected with the lower box body through the hinge, and a pressure signal input end, a temperature signal output end, a pulse output end and a power switch are sequentially arranged at the upper end of the main plate surface of the lower box body; the keyboard is arranged on the left side of the lower end of the keyboard, and the USB bus port is arranged on the right side of the lower end of the keyboard; the lower box body is internally provided with a measurement and control system part, the measurement and control system part comprises a collection and measurement system and a control output system, the collection and measurement system is used for collecting signals of terminal equipment, and the control output system is used for outputting pulse signals.
2. A rocket engine portable measurement and control system case according to claim 1, characterized in that: the back of the lower box body is provided with a pull rod, and after the upper box body is opened, a liquid crystal display screen is arranged on the main board surface of the upper box body.
3. A rocket engine portable measurement and control system case according to claim 1, characterized in that: the edge of the upper box body is provided with wheels and a lock catch, and the lock catch is used for closing the upper box body and the lower box body.
4. A rocket engine portable measurement and control system case according to claim 1, characterized in that: and the edge of the lower box body is provided with a power supply external interface and a fan.
5. A rocket engine portable measurement and control system case according to claim 1, characterized in that: the measurement and control system comprises a switching terminal, a first voltage-stabilizing direct-current switching power supply, a second voltage-stabilizing direct-current switching power supply, a thermocouple isolation conditioning module, a sensor, a current isolation conditioning module, a collection card and a signal amplifier, and the voltage-stabilizing direct-current power supply is adopted to supply power to equipment and supply power to the equipment in a pulse mode.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010689941.6A CN111997786A (en) | 2020-07-17 | 2020-07-17 | Portable measurement and control system box of rocket engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010689941.6A CN111997786A (en) | 2020-07-17 | 2020-07-17 | Portable measurement and control system box of rocket engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111997786A true CN111997786A (en) | 2020-11-27 |
Family
ID=73466962
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010689941.6A Pending CN111997786A (en) | 2020-07-17 | 2020-07-17 | Portable measurement and control system box of rocket engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111997786A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0783114A (en) * | 1993-09-17 | 1995-03-28 | Mitsubishi Electric Corp | Rocket motor |
| CN102042122A (en) * | 2011-01-05 | 2011-05-04 | 北京航空航天大学 | Portable measuring and controlling system for rocket engine ground tests |
| CN104898502A (en) * | 2015-04-27 | 2015-09-09 | 中国直升机设计研究所 | Unmanned helicopter portable measurement and control system and measurement and control method |
| CN204646453U (en) * | 2015-05-08 | 2015-09-16 | 宋明明 | Portable missile rocket motor the cannot-harm-detection device |
| CN104991483A (en) * | 2015-05-19 | 2015-10-21 | 北京宇航系统工程研究所 | Test-launch-control remote monitoring platform based on virtualization technology |
| CN205449503U (en) * | 2015-12-21 | 2016-08-10 | 中国航天空气动力技术研究院 | Aeroengine measurement and control device |
-
2020
- 2020-07-17 CN CN202010689941.6A patent/CN111997786A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0783114A (en) * | 1993-09-17 | 1995-03-28 | Mitsubishi Electric Corp | Rocket motor |
| CN102042122A (en) * | 2011-01-05 | 2011-05-04 | 北京航空航天大学 | Portable measuring and controlling system for rocket engine ground tests |
| CN104898502A (en) * | 2015-04-27 | 2015-09-09 | 中国直升机设计研究所 | Unmanned helicopter portable measurement and control system and measurement and control method |
| CN204646453U (en) * | 2015-05-08 | 2015-09-16 | 宋明明 | Portable missile rocket motor the cannot-harm-detection device |
| CN104991483A (en) * | 2015-05-19 | 2015-10-21 | 北京宇航系统工程研究所 | Test-launch-control remote monitoring platform based on virtualization technology |
| CN205449503U (en) * | 2015-12-21 | 2016-08-10 | 中国航天空气动力技术研究院 | Aeroengine measurement and control device |
Non-Patent Citations (1)
| Title |
|---|
| 邵焕杰: "《便携式发射动力学参数测试系统设计方法研究》", 《中国优秀博硕士学位论文全文数据库(硕士)》 * |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN207675890U (en) | A kind of steering engine simulation TT＆C system | |
| CN101699284A (en) | Frozen-soil experiment system capable of applying dynamic load | |
| CN208833299U (en) | A kind of electric pushrod test device | |
| CN102478033A (en) | Measuring and controlling system of electro-hydraulic servo valve | |
| CN109632171B (en) | Rocket engine micro-force measuring device | |
| CN101221422A (en) | Portable vibration data collector and method based on embedded technology | |
| CN102830695B (en) | Based on the subway gate cell failure detection system of semi-true object emulation technology | |
| CN101435842A (en) | Multifunctional integrated test system | |
| CN109885026A (en) | A kind of test macro for aviation piston engine boost controller | |
| CN111997786A (en) | Portable measurement and control system box of rocket engine | |
| CN201548682U (en) | Three-phase impact performance load power signal source device | |
| CN105004463A (en) | Piston type propeller engine thrust measuring method and piston type propeller engine thrust measuring device | |
| CN201142137Y (en) | Portable single-channel vibration data collector based on embedded technology | |
| CN209117817U (en) | A kind of circuit board testing tooling of PLC control | |
| CN111008118A (en) | Servo system energy consumption evaluation system and evaluation method | |
| CN205483517U (en) | It shows servovalve static performance tester to have characteristic curve and performance parameter | |
| CN111075607A (en) | Test system and method for space propellant autonomous replenishment process | |
| CN206458669U (en) | A kind of hydraulic system of engineering vehicle combined training platform | |
| CN212482889U (en) | Test device for testing characteristics of foot brake valve | |
| CN209069348U (en) | A kind of measurement and control signal equivalent system | |
| CN203785891U (en) | Measurement and control system used for tractor clutch assembly integrated test stand | |
| CN201210260Y (en) | Special laboratory temperature and humidity monitoring and control apparatus | |
| CN116907789B (en) | Multi-system synchronous identification method and device based on pressure measurement | |
| CN217034187U (en) | Circuit for testing cycle life of small lithium iron phosphate battery | |
| CN111336158A (en) | Hydraulic mechanism pressure characteristic test device and test method thereof |
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 | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20201127 |