CN103454089A - Device for measuring class of discontinuous parameters of solid rocket engine - Google Patents
Device for measuring class of discontinuous parameters of solid rocket engine Download PDFInfo
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- CN103454089A CN103454089A CN2013104157712A CN201310415771A CN103454089A CN 103454089 A CN103454089 A CN 103454089A CN 2013104157712 A CN2013104157712 A CN 2013104157712A CN 201310415771 A CN201310415771 A CN 201310415771A CN 103454089 A CN103454089 A CN 103454089A
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Abstract
The invention provides a device for measuring a class of discontinuous parameters of a solid rocket engine. The device for measuring the class of discontinuous parameters of the solid rocket engine comprises a case, an input panel with an input interface socket, a power supply switch and state indication, an output panel with an output interface socket, a power supply socket and a power supply diverter switch, a power supply patch core and a circuit board. A current limitation circuit of the circuit board is formed by connecting n channel measuring circuits in parallel and then connecting the n channel measuring circuits with a total current limitation resistor R0 in series. A power supply indication circuit of the circuit board is formed by connecting an ordinary luminous diode L and a power supply indication circuit resistor R1 in series. A single channel measuring circuit is formed by connecting a highlight luminous diode Li, a single blade switch K and a one-way shunting resistor R in series. According to the device for measuring the class of discontinuous parameters of the solid rocket engine, the luminous diode is used for observing each line of signals, current limiting measures are adopted to ensure that the current of each line of the signals is in the milliampere level, a BNC contact is used for unitizing and simplifying the switch over links, two power supply modes which are a battery mode and a power supply mode are provided, and therefore measurement of the class of discontinuous parameters in a solid rocket engine test can be achieved.
Description
Technical field
The invention belongs to Solid Rocket Engine Test observation and control technology field, be specially a kind of solid propellant rocket one class discontinuous parameter measurement mechanism.
Background technology
Need to measure the moment that the jet pipe blanking cover is opened in the Multiple Type Solid Rocket Motor Ground Test, and be mapped and analyze to obtain jet pipe blanking cover opening characteristic with thrust, pressure data; In the employing reversal nozzle is realized the test of thrust termination, blanking cover after also needing to measure shutdown command and sending on each reversal nozzle is blown, flame starts the moment of ejection from reversal nozzle, or arranges a plurality of measuring points on blanking cover is dished out track, is used for studying the performance that stops mechanism; In the test of examination jet vane ablation situation, control the rudder sheet at official hour and exit the wake flame district, measure rudder sheet post-set time, and calculate each rudder sheet synchronism of post-set time.
Above-mentioned several parameter is classified into a class discontinuous parameter, its measuring principle is that signal wire or sensor are installed in measuring position, by measured signal place in circuit according to a certain method, when in circuit, certain part is switched on or switched off, transient change will occur in some parameter in circuit, disconnect or become by disconnecting the state variation of connecting by connecting to become with high-speed figure collecting device real time record signal wire, realizing the measurement to such discontinuous parameter.
Now with measurement mechanism, comprise: resistor network; Signal-transmitting cable; The multiple breakout boxs such as 7 core aviation connectors, BNC connector, crocodile clip and O type connector; Source of stable pressure.During the inspection of line, be switched on or switched off signal wire or sensor, by the histogram on the magnetic tape station screen or collecting device Real-Time Monitoring voltage signal, judge that whether measuring circuit is normal.Use high-speed figure collecting device real time record signal during measurement, the moment that in analytic signal, voltage transient changes obtains tested discontinuous parameter.
Although now with measurement mechanism, can meet the Solid Rocket Engine Test request for utilization, exist the switching link too much, poor reliability, problem investigation be complicated, use very flexible, the observation intuitively must be by gathering or the shortcomings such as recording unit.
Summary of the invention
The technical matters solved
The problem existed for solving prior art, the present invention proposes a kind of solid propellant rocket one class discontinuous parameter measurement mechanism.
Technical scheme
Technical scheme of the present invention is:
Described a kind of solid propellant rocket one class discontinuous parameter measurement mechanism, it is characterized in that: comprise cabinet, input panel with input interface socket, power switch and state indication, with the output slab of output interface socket, power supply base and power switching switch, power supply patchcord and circuit board; Input panel and output slab are fixed on cabinet, and circuit board is arranged in cabinet; Described input interface socket, output interface socket and power supply base are the bnc interface socket; The power switching switch adopts double-point double-throw switch, for switching battery or external power source;
Current-limiting circuit in circuit board by the parallel connection of n channel measurement circuit after, then with total current-limiting resistance R
0be composed in series; Power indicating circuit in circuit board is composed in series by common light emitting diode L and power indicating circuit resistance R 1; The single channel metering circuit is by high-brightness light emitting diode L
i, single-pole switch K and single channel shunt resistance R be composed in series, i=1 wherein, 2 ..., n; Electric current in the single channel metering circuit meets I=(U-U
1)/(R+n * R
0), requiring I is a milliampere level, the externally fed voltage U meets 5V≤U≤10V, high-brightness light emitting diode branch pressure voltage U
1≤ 3V, single channel shunt resistance R meets 2k Ω≤R≤5k Ω, total current-limiting resistance R
0meet 2k Ω≤R
0≤ 5k Ω, port number n meets 1≤n≤10.
Beneficial effect
The solid propellant rocket one class discontinuous parameter measurement mechanism that the present invention proposes uses simple, and during the inspection of line, observation is directly perceived; The switching connector is unitized, and the switching link is few; Lightweight, volume is little, power supply mode is flexible, can be used for portable measurement occasion; The problem investigation is simple; Cost is low.
The accompanying drawing explanation
Fig. 1: measuring principle figure of the present invention;
Fig. 2: apparatus of the present invention input panel schematic diagram;
Fig. 3: apparatus of the present invention output slab schematic diagram;
Fig. 4: apparatus of the present invention input, output slab and back panel wiring schematic diagram.
Embodiment
Below in conjunction with specific embodiment, the present invention is described:
With reference to accompanying drawing 4, solid propellant rocket one class discontinuous parameter measurement mechanism in the present embodiment comprises cabinet, input panel with input interface socket, power switch and state indication, with the output slab of output interface socket, power supply base and power switching switch, power supply patchcord and circuit board.Input panel and output slab are fixed by screws on cabinet, and circuit board is arranged in cabinet by mounting groove.
Input interface socket, output interface socket and power supply base are the bnc interface socket.Input panel as shown in Figure 2, has designed 10 passages, and bnc interface socket and status indicator lamp are distributed on panel.As shown in Figure 3, port number is corresponding with input for output slab, and each bnc interface socket is distributed on panel.The power switching switch adopts double-point double-throw switch, for switching battery or external power source.
As shown in Figure 4, the heart yearn of each bnc interface socket connects anode, outer shell joint negative terminal for device input, output slab and back panel wiring.
Current-limiting circuit in circuit board by the parallel connection of 10 channel measurement circuit after, then with total current-limiting resistance R
0be composed in series; Power indicating circuit in circuit board is composed in series by common light emitting diode L and power indicating circuit resistance R 1, uses common light emitting diode L indication Power supply; The single channel metering circuit is by high-brightness light emitting diode L
i, single-pole switch K and single channel shunt resistance R be composed in series, i=1 wherein, 2 ..., 10, use high-brightness light emitting diode L
iindicate each tested passage to be switched on or switched off state; Electric current in the single channel metering circuit meets I=(U-U
1)/(R+n * R
0), in order to guarantee I, be a milliampere level, measuring voltage U
out1under single-ended or two kinds of metering systems of difference, change in voltage is obvious, and the externally fed voltage U meets 5V≤U≤10V, high-brightness light emitting diode branch pressure voltage U
1≤ 3V, single channel shunt resistance R meets 2k Ω≤R≤5k Ω, total current-limiting resistance R
0meet 2k Ω≤R
0≤ 5k Ω, port number n meets 1≤n≤10.
R1=4.7k Ω in the present embodiment in power indicating circuit, total current-limiting resistance R
0=3k Ω, single channel shunt resistance R=4.7k Ω, high-brightness light emitting diode branch pressure voltage U used
1=2.5V.Use 9V lithium battery or direct-flow voltage regulation source power supply, when input end only has a road to connect, one-channel signal electric current I=0.844mA, measuring voltage U
out1=3.967V, when input end is all connected, one-channel signal electric current I=0.187mA, measuring voltage U
out1=0.879V.
The present embodiment is used light emitting diode to observe every road signal, take current limiting measures to guarantee that every road marking current is for a milliampere level, unitize and simplify the switching link with BNC connector, there are two kinds of power supply modes of battery and power supply, realization is measured the class discontinuous parameter in Solid Rocket Engine Test, during measurement, signal wire or tested sensor are received to signal input part, signal output is connected to the high-speed figure collecting device, and battery or external power source are connected to cabinet by the special-purpose patchcord of powering.
Claims (1)
1. solid propellant rocket one a class discontinuous parameter measurement mechanism, it is characterized in that: comprise cabinet, input panel with input interface socket, power switch and state indication, with the output slab of output interface socket, power supply base and power switching switch, power supply patchcord and circuit board; Input panel and output slab are fixed on cabinet, and circuit board is arranged in cabinet; Described input interface socket, output interface socket and power supply base are the bnc interface socket; The power switching switch adopts double-point double-throw switch, for switching battery or external power source;
Current-limiting circuit in circuit board by the parallel connection of n channel measurement circuit after, then with total current-limiting resistance R
0be composed in series; Power indicating circuit in circuit board is composed in series by common light emitting diode L and power indicating circuit resistance R 1; The single channel metering circuit is by high-brightness light emitting diode L
i, single-pole switch K and single channel shunt resistance R be composed in series, i=1 wherein, 2 ..., n; Electric current in the single channel metering circuit meets I=(U-U
1)/(R+n * R
0), requiring I is a milliampere level, the externally fed voltage U meets 5V≤U≤10V, high-brightness light emitting diode branch pressure voltage U
1≤ 3V, single channel shunt resistance R meets 2k Ω≤R≤5k Ω, total current-limiting resistance R
0meet 2k Ω≤R
0≤ 5k Ω, port number n meets 1≤n≤10.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2013104157712A CN103454089A (en) | 2013-09-12 | 2013-09-12 | Device for measuring class of discontinuous parameters of solid rocket engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2013104157712A CN103454089A (en) | 2013-09-12 | 2013-09-12 | Device for measuring class of discontinuous parameters of solid rocket engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103454089A true CN103454089A (en) | 2013-12-18 |
Family
ID=49736704
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2013104157712A Pending CN103454089A (en) | 2013-09-12 | 2013-09-12 | Device for measuring class of discontinuous parameters of solid rocket engine |
Country Status (1)
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| CN (1) | CN103454089A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104239698A (en) * | 2014-09-01 | 2014-12-24 | 中国航天科技集团公司第四研究院四〇一所 | Time sequence correcting method of solid rocket engine vibration distortion signal |
| CN105281158A (en) * | 2015-11-04 | 2016-01-27 | 甘肃省地震局 | Adapter |
| CN110500202A (en) * | 2019-08-19 | 2019-11-26 | 西安航天动力测控技术研究所 | A kind of method of Automatic-searching solid propellant rocket fire end time |
| CN112526058A (en) * | 2020-11-04 | 2021-03-19 | 东南大学 | Small-thrust solid propellant grain combustion and propulsion performance detection test device |
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2013
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| JPH07230342A (en) * | 1994-02-18 | 1995-08-29 | Fujitsu General Ltd | Power back-up circuit |
| CN201570893U (en) * | 2009-11-03 | 2010-09-01 | 中兴通讯股份有限公司 | Power supply device |
| CN201749361U (en) * | 2010-06-29 | 2011-02-16 | 无锡隆盛科技有限公司 | Aging test-bed circuit of engine electronic control unit |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104239698A (en) * | 2014-09-01 | 2014-12-24 | 中国航天科技集团公司第四研究院四〇一所 | Time sequence correcting method of solid rocket engine vibration distortion signal |
| CN104239698B (en) * | 2014-09-01 | 2018-03-16 | 中国航天科技集团公司第四研究院四0一所 | Solid propellant rocket vibrates the time series modification method of distorted signal |
| CN105281158A (en) * | 2015-11-04 | 2016-01-27 | 甘肃省地震局 | Adapter |
| CN110500202A (en) * | 2019-08-19 | 2019-11-26 | 西安航天动力测控技术研究所 | A kind of method of Automatic-searching solid propellant rocket fire end time |
| CN110500202B (en) * | 2019-08-19 | 2022-03-15 | 西安航天动力测控技术研究所 | Method for automatically searching combustion termination time of solid rocket engine |
| CN112526058A (en) * | 2020-11-04 | 2021-03-19 | 东南大学 | Small-thrust solid propellant grain combustion and propulsion performance detection test device |
| CN112526058B (en) * | 2020-11-04 | 2022-05-24 | 东南大学 | Small-thrust solid propellant grain combustion and propulsion performance detection test device |
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Application publication date: 20131218 |