KR100911454B1 - System for emergency protection of liquid rocket engine - Google Patents

Abstract

According to the present invention, a plurality of signal detection unit for sensing and transmitting the sensing information including the rotational speed information, vibration information, pressure information, temperature information, optical information according to the detection of the flame to be burned; A plurality of signal processing units provided to correspond to each signal sensing unit, and configured to digitally process sensing information received from the signal sensing unit, and compare the processed sensing information with previously stored threshold conditions to transmit a comparison result; Emergency stop that generates an emergency stop signal for emergency stop of the liquid rocket engine when the comparison result is received from the signal processor and each sensing information transmitted from two or more signal processors is out of the stored threshold condition at the same time. Control unit; And a liquid rocket engine emergency control system for controlling the operation of the liquid rocket engine, but including a liquid rocket control unit for emergencyly stopping the liquid rocket engine when an emergency stop signal is received from the emergency stop control unit. According to the disclosed liquid rocket engine emergency protection system, a multi-signal detection unit and a signal processing unit are built in multiple stages, and emergency protection of the liquid rocket engine is performed when information processed by two or more signal processing units simultaneously meets the emergency stop requirement. In addition, it is possible to improve the reliability of the emergency protection system by verifying the separate simulation signal.

Liquid Rocket Engine, Sensor, Emergency Stop, Emergency Protection

Description

System for emergency protection of liquid rocket engine

The present invention relates to a liquid rocket engine emergency protection system, and more particularly, to a liquid rocket engine emergency to stop the test in the shortest time in the event of an emergency during the liquid rocket engine test to safely protect the test equipment and the liquid rocket engine. It relates to a protection system.

Existing emergency protection systems for monitoring the emergency situations that may occur during liquid rocket engine testing and for premature termination of the test typically provide static pressure and temperature below the engine's measured frequency of 1 kHz, and equipment pressure and flow signals over time. Low-frequency emergency protection to monitor, and high-frequency emergency protection using vibration signals with a measurement frequency of 20 kHz or more to prematurely discontinue testing when high-frequency combustion instability occurs in liquid rocket engines.

However, the existing emergency protection system configuration is difficult to overcome the following problems.

Firstly, a malfunction in the system for emergency protection may result in an incorrect emergency protection command, causing an increase in the test cost or schedule of the liquid rocket engine.

Second, since the emergency protection command is generated by one judgment at the time of emergency protection judgment, there is a high possibility of an undesired emergency emergency protection command caused by electric noise at a moment.

The present invention has been made to solve the above-described problems, and the signal detection unit and the signal processor according to the construction of multiple, and the information analyzed by each of the two or more signal processor by comparing the information analyzed by each signal processor with a threshold value If the emergency stop requirement is met at the same time, the emergency stop command is transmitted to perform the emergency protection of the liquid rocket engine, and at the same time, it can generate a simulated signal to check whether the signal processing unit is malfunctioning, thereby improving the reliability of the system. The purpose is to provide an engine emergency protection system.

Liquid rocket engine emergency protection system of the present invention for achieving the above object, the sensing information including the rotational speed information, vibration information, pressure information, temperature information, optical information according to the detection of the flame to burn the liquid rocket engine A plurality of signal detection unit for sensing and transmitting; A plurality of signal processing units provided to correspond to each signal sensing unit, and configured to digitally process sensing information received from the signal sensing unit, and compare the processed sensing information with previously stored threshold conditions to transmit a comparison result; When receiving the comparison result from the signal processing unit, and each sensing information received from the two or more signal processing unit at the same time out of the previously stored threshold condition, generating an emergency stop signal for emergency stop of the liquid rocket engine Emergency stop control unit; And a liquid rocket control unit controlling the driving of the liquid rocket engine and emergency stopping the liquid rocket engine when the emergency stop signal is transmitted from the emergency stop control unit.

Here, the emergency stop control unit, part or all of the information included in each of the sensing information transmitted from the two or more signal processing unit, at the same time out of the pre-stored threshold condition, a predetermined time interval for a predetermined number of times In the case of successive departure, the emergency stop signal may be generated.

The emergency stop controller may further include an input unit configured to input and set information about the threshold condition, the threshold number of times, and the predetermined time interval.

On the other hand, according to the present invention, it may further include a simulation signal generation unit interlocked with the emergency stop control unit, and generates a virtual simulation signal corresponding to the sensing information detected by the signal detection unit to transmit to the plurality of signal processing unit. In this case, the plurality of signal processing units, respectively, the digital signal processing and transmission of the simulation signal, the emergency stop control unit, the simulation signal received from each signal processing unit and the simulation signal generated from the simulation signal generator By comparing and analyzing, it is possible to determine whether there is an abnormality in each signal processing unit.

According to the liquid rocket engine emergency protection system according to the present invention provides the following effects.

First, by constructing multiple signal detectors and corresponding signal processors, and comparing the information analyzed by each signal processor with thresholds, the information processed by two or more signal processors corresponds to the emergency stop requirements simultaneously. It is possible to construct a multi-reliable liquid rocket engine emergency stop system by determining the emergency situation and sending the final emergency stop command.

Second, by generating a separate simulation signal can determine whether the malfunction of the signal processing unit of the present invention can improve the reliability of the liquid rocket engine emergency protection system.

Hereinafter, exemplary embodiments of the present invention will be described in detail with reference to the accompanying drawings. Prior to this, terms or words used in the present specification and claims should not be construed as being limited to the common or dictionary meanings, and the inventors should properly explain the concept of terms in order to best explain their own invention. Based on the principle that it can be defined, it should be interpreted as meaning and concept corresponding to the technical idea of the present invention.

Therefore, the embodiments described in the specification and the drawings shown in the drawings are only the most preferred embodiment of the present invention and do not represent all of the technical idea of the present invention, various modifications that can be replaced at the time of the present application It should be understood that there may be equivalents and variations.

1 is a configuration of the liquid rocket engine emergency protection system according to an embodiment of the present invention, Figure 2 is a detailed configuration of Figure 1, Figure 3 is a flow chart of the liquid rocket engine emergency protection using the configuration of FIG. .

As shown in Figure 1 or 2, the liquid rocket engine emergency protection system 100 according to an embodiment of the present invention, a plurality of signal detection unit 110, corresponding to the number of the signal detection unit 110 A plurality of signal processing unit 120, the emergency stop control unit 130 and the liquid rocket control unit 140 is included.

In the present invention, the signal sensing unit 110 and the three signal processing unit 120 is described as an example, but is not necessarily limited to the above-mentioned, if three or more are used to realize the object of the present invention Seems to be enough.

However, for the minimum system operation, system simplification, minimum construction cost, etc., it is preferable to install and drive three pieces each.

First, the signal detecting unit 110 detects various signals generated by the liquid rocket engine 10 and transmits them to the signal processing unit 120. The signal detecting unit 110 is provided in plural in the liquid rocket engine 10 to be inspected.

In more detail, the signal detecting unit 110 includes optical information which is sensing information about a flame combusted by the liquid rocket engine 10 as well as information on the rotational speed, vibration, pressure, and temperature of the liquid rocket engine 10. As a part for sensing and transmitting sensing information including information in real time, a rotation speed sensor, a vibration sensor, a pressure sensor, a temperature sensor, and an optical sensor for sensing each information may be provided.

That is, in the present invention, in determining whether the liquid rocket engine 10 is normal, the rotational speed of the turbopump mounted on the engine, the vibration, the pressure, the temperature, and the state of the flame generated during combustion (light shape, color, etc.) , Wavelength, etc.) are used.

Here, since the rotation speed sensor, vibration sensor, pressure sensor, temperature sensor and optical sensor is conventionally implemented in various examples, a more detailed description thereof will be omitted.

The signal processor 120 is provided in plural to correspond to each signal detector 110 so as to process the signals sensed by the respective signal detectors 110 individually, and received from the signal detector 110. The sensing information is digitally processed, and the processed sensing information is compared with previously stored threshold conditions, and the comparison results are collectively transmitted to the emergency stop controller 130.

In the digital signal processing, as illustrated in FIG. 2, an A / D converter 121 for converting sensing information into analog to digital (A / D), and the converted sensing information are digitally filtered and converted into a desired physical quantity, A digital signal processor (DSP) processor 122 may be used to compare the threshold conditions with each other and transmit a comparison result (whether or not the sensing information is out of the threshold condition, or a degree out of the threshold condition).

Then, the emergency stop control unit 130 receives each comparison result from the signal processing unit 120, and after the analysis result of the comparison result, each sensing information received from the two (or two or more) signal processing unit is stored in advance When the critical condition is simultaneously deviated, an emergency stop signal for emergency stop of the liquid rocket engine 10 is generated.

Conventionally, only one signal detecting unit (or a sensor) is installed to determine whether the emergency situation occurs, but in this case, there is a disadvantage in that the reliability of the detected value and the processing result is deteriorated. A case may occur that causes a stop.

On the contrary, in the present invention, for example, as illustrated in FIGS. 2 and 3, the sensing information transmitted from the two signal detection units 110 among the three signal detection units 110 installed in the liquid rocket engine 10 ( The case where some or all of the information included in the sensing information deviates from the threshold at the same time may be determined as an emergency, thereby further improving the reliability of the system.

As an example, when the rotational speed information, the vibration information, and the optical information transmitted from the two signal detection units 110 deviate from the threshold at the same time, an emergency stop signal may be generated.

In addition, the emergency stop control unit 130, as a result of analyzing the comparison result between the sensing information and the threshold condition, some or all information included in the sensing information transmitted from the two (or two or more) signal processing unit 120 Simultaneously deviates from the predetermined threshold condition, but continuously exits at a predetermined time interval (ex, several seconds interval) by a predetermined threshold number (ex, two times) as an emergency situation, the emergency of the liquid rocket engine 10 An emergency stop signal is issued.

That is, in FIGS. 2 and 3, it may be problematic for reliability to be determined as an emergency situation in which each sensing information sensed by the two signal detectors 110 is out of the threshold condition at the same time. It may cause an emergency stop.

Therefore, the sensing information sensed by the two signal detectors 110 simultaneously exits the critical condition, and at the same time, at least two times or two or more times, the critical condition is judged as the emergency situation to determine reliability. It is desirable to improve.

In summary, the present invention compares the information analyzed by each signal processor 120 with a threshold value and the information processed by the two or more signal processors 120 corresponds to the emergency stop requirements at the same time and this phenomenon persists several times or more. By judging the case as an emergency and sending the final emergency stop command, it is possible to construct multiple reliable liquid rocket engine emergency stop systems.

The emergency stop controller 130 includes an input unit 131 and a display unit 132.

The input unit 131 is a part for inputting an emergency protection criterion, that is, a part for receiving and setting information on the threshold condition, the number of times, and the predetermined time interval for determining whether the sensing information is abnormal, including a keyboard, a mouse, It may be implemented by an input means such as a touch screen. Here, the set threshold condition may be transmitted to the signal processor 120 to be used for comparison with the sensing information.

In addition, the display unit 132 may display a value set by the input unit 131 and, as a result of being out of the threshold condition for each signal detection unit 110, the degree of departure, the number of departures, the phrase for notifying an emergency stop when an emergency stop signal is generated or The image may be displayed in real time, and may be implemented by various display means generally known, such as a PC screen.

On the other hand, the liquid rocket control unit 140 is a part for controlling the driving of the liquid rocket engine 10 in normal, when the emergency stop signal is transmitted from the emergency stop control unit 130 serves to safely stop the liquid rocket engine (10) Do it.

The present invention may include a simulation signal generation unit 150 to check whether the signal processing unit 120 that receives the sensing information in the normal operation of the system 100.

The simulation signal generator 150 is interlocked with the emergency stop controller 130 to exchange each information, and generates a virtual simulation signal corresponding to the sensing information sensed by the signal detector 110 to generate a plurality of signals. Transfer to the processing unit 120.

Of course, the simulation signal generation unit 150 may be implemented to generate a simulation signal when a simulation signal generation command transmitted through the setting of the input unit 131 is received at the emergency stop control unit 130 and the input unit 131. ) May also include a function of selecting or setting a desired simulation signal from among various simulation signals.

Here, a separate signal amplifier 151 may be installed at the rear end of the simulation signal generator 150 to be configured as a simulation signal having electrical characteristics similar to those of the actual sensor (voltage level, current level, etc.). have.

On the other hand, in this case, the plurality of signal processing unit 120, the digital signal processing and transmits the simulated signal, respectively, the emergency stop control unit 130, the simulated signal and the simulated signal generation unit (transmitted by each signal processing unit 120) ( Comparative simulation between the simulated signals generated in 150) is performed to mask the identity.

For example, in the case of the simulated signal processed by some signal processing unit 120, when it is determined that there is a problem in terms of the same as the generated simulation signal, the corresponding signal processing unit 120 is recognized as abnormal. In actual testing, it may cause abnormal operation of the system 100 (a problem such as incorrectly determining that the sensed sensing information is out of a critical condition even though the engine is in normal operation).

Through the verification of the simulated signal, it is possible to confirm whether the normal operation for each channel of each signal processing unit 120 before the actual test, there is an advantage that can be confirmed in advance before the operation of the system 100.

Hereinafter, the emergency protection method using the system 100 of the present invention as described above will be described in more detail with reference to FIG. 3.

First, the input unit 131 receives and sets a criterion for emergency protection (critical condition, threshold number of times, predetermined time interval, etc.) (S1).

Then, prepare the emergency protection system 100 of the present invention before the start of the test (S2).

The test start command is transmitted from the liquid rocket control unit 140 corresponding to the engine test facility (S3) and starts to interlock with the emergency protection system 100 of the present invention (S4).

Next, among the sensing information S5 acquired from various sensors of the signal detecting unit 110, the signal processing unit 120 obtains a sensing signal in the monitoring time section (for a preset monitoring time) of the emergency protection system 100 ( S6).

In this case, the signal processor 120 performs digital filtering on the sensing signal (S7), and also converts the electrical signal into an actual physical quantity (S8), and then performs a comparison operation with a preset emergency protection condition. (S9), whether the normal or abnormal operation of each sensing information based on the emergency protection condition is determined by the signal detecting unit 110 (S10).

In addition, the emergency stop control unit 130 combines the determination results of the same variables (same sensing information in the sensing information) of the three emergency protection determination modules (S11), and the two emergency protection determination results of the three emergency protection conditions are determined. It is determined whether or not (S12), and if the emergency protection judgment is observed the same two times in a row (S13).

Here, the emergency stop control unit 130, if all of the conditions of the above step S12 and S13 is met, by the final transmission (S14) of the emergency protection command to the test facility main computer (liquid rocket control unit; 140) by the liquid rocket engine ( 10) Stop the operation immediately and safely.

As described above, although the present invention has been described by way of limited embodiments and drawings, the present invention is not limited thereto and is intended by those skilled in the art to which the present invention pertains. Of course, various modifications and variations are possible within the scope of equivalents of the claims to be described.

1 is a block diagram of a liquid rocket engine emergency protection system according to an embodiment of the present invention,

2 is a detailed configuration diagram of FIG.

3 is a flow chart of a liquid rocket engine emergency protection using the configuration of FIG. 1 or FIG.

<Explanation of symbols for the main parts of the drawings>

Liquid rocket engine emergency protection system

110 ... signal detector 120 ... signal processor

121 ... A / D converter 122 ... DSP processing unit

130 ... Emergency stop control unit 131 Input unit

132 Display ... 140 Liquid rocket control unit

150 ... simulation signal generator 151 ... signal amplifier

Claims (4)

A plurality of signal sensing units for sensing and transmitting sensing information including rotation speed information, vibration information, pressure information, temperature information, and optical information according to the detection of a flame that is combusted; A plurality of signal processing units provided to correspond to each signal sensing unit, and configured to digitally process sensing information received from the signal sensing unit, and compare the processed sensing information with previously stored threshold conditions to transmit a comparison result; When receiving the comparison result from the signal processing unit, and each sensing information received from the two or more signal processing unit at the same time out of the previously stored threshold condition, generating an emergency stop signal for emergency stop of the liquid rocket engine Emergency stop control unit; And Liquid rocket engine emergency protection system for controlling the operation of the liquid rocket engine, the liquid rocket engine to emergency stop the liquid rocket engine when receiving the emergency stop signal from the emergency stop control unit. According to claim 1, The emergency stop control unit, When some or all information included in each sensing information transmitted from the two or more signal processing units simultaneously deviates from a previously stored threshold condition and continuously deviates at a predetermined time interval by a predetermined threshold number of times, the emergency Liquid rocket engine emergency protection system, characterized in that for generating a stop signal. According to claim 2, The emergency stop control unit, The liquid rocket engine emergency protection system, characterized in that it further comprises an input unit for inputting and setting the information on the threshold condition, the threshold frequency, the predetermined time interval. The method of claim 1, And a simulation signal generation unit interlocked with the emergency stop control unit and generating a virtual simulation signal corresponding to the sensing information detected by the signal detection unit and transmitting the virtual simulation signal to the plurality of signal processing units. The plurality of signal processing units, respectively digital signal processing and transmitting the simulated signal, The emergency stop control unit, the liquid rocket, characterized in that whether the abnormality of each signal processing unit by comparing and analyzing the simulation signal received from each signal processing unit and the simulation signal generated in the simulation signal generation unit mutually Engine emergency protection system.

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