RU2476850C1 - Method of rocket engine control and diagnostics - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: proposed method consists in intermittent measurement of engine and engine compartment controlled parameters, their comparison with preset threshold values and executing control and diagnostics proceeding the results of comparison. Said controlled parameters include temperature and pressure in gas and fluid channels of engine and engine compartment. Note here that, additionally, derivate changes of parameters in time are defined to be compared with their appropriate threshold values. in case derivatives exist in the limits of threshold values, fault is considered tolerable to continuation of test and engine is changed into lower power conditions to feed inert medium into engine compartment.

EFFECT: higher validity of diagnostics.

1 cl, 1 dwg

Description

The invention relates to methods for functional monitoring and diagnosing a condition during testing of complex pneumohydraulic objects, for example rocket engines (RD).

A known method of monitoring the state of a liquid rocket engine (LRE), which consists in measuring control parameters and comparing them with acceptable (threshold) values, which is implemented using an information-measuring system (see, for example, "Tests LRE". Edited by Levin V . I. Moscow, Mechanical Engineering, 1981, p.199).

This method monitors the state of the object and does not allow to diagnose a malfunction, i.e. determine the place, degree and name of the malfunction.

Closest to the claimed method is a method for monitoring and diagnosing a rocket engine, which consists in the fact that cyclically measure the parameters of the engine and the engine compartment, compare them with predetermined threshold values and diagnose (localize) a malfunction if the current parameter value exceeds its threshold level and turn off the engine (RF patent 2393450, G01M 15/14) is the closest analogue.

The known method of monitoring and diagnosis does not allow to diagnose the degree of malfunction, and any excess of the threshold values of the measured parameters is recorded as a failure, and the engine is turned off. However, the test program is not completed and requires repetition on additional material. At the same time, the experience of the operation and testing of the taxiway shows that there is a large group of malfunctions associated with minor leaks in the liquid and gas paths, in which it is possible to continue the test and carry out its program.

The technical result of the present invention is to increase the reliability of the control and diagnosis of taxiways by determining in the process of diagnosing the degree of malfunction at which the continuation of the test and the execution of its program is acceptable, and eliminating the failure of the taxiway.

The specified technical result is achieved by the fact that in the method of monitoring and diagnosing a rocket engine, which consists in cyclically measuring the parameters of the engine and the engine compartment, comparing them with predetermined threshold values and comparing the results of monitoring and diagnosing the engine, it is new that the derived changes are additionally determined parameters over time, compare them with their threshold values and, if derivatives are within the threshold values, I fix the degree of fault, allowed for the continuation of the tests the engine is transferred to the reduced mode and fed into the engine compartment inert environment.

Operations to transfer the engine to a lower mode and supply an inert medium to the engine compartment allow the material of the engine, cable network and devices located in the engine compartment to be protected from the effects of an aggressive environment with relatively small malfunctions. As an inert medium during bench tests, the engine compartment is choked with water, and during flight tests, pressurization gas (nitrogen or helium) is used.

The essence of the claimed invention is illustrated by the drawing, which shows a diagram of an information management system for implementing the method.

In this diagram, the monitoring and diagnosing object (RD) is indicated by the number 1. Pressure sensors and temperature sensors 2 are installed in the gas paths of the engine, and pressure and temperature sensors 3 are installed in the liquid paths. Pressure and temperature sensors are installed in the engine compartment 4. Sensors 2.3.4 connected to the inputs of the switching device 5. The output of the switching device 5 is connected through the interface device 6 to the input of the computer 7, which through the interface device 8 is connected to the magnetic storage media 9 (designed to analyze the operation of systems ) and with the command device 10 included in the control system (CS) 11 of the taxiway, which in turn is connected to the input of the device 5. An inert medium source 12 is additionally installed in the engine compartment, which is triggered by a command from the command device 10 of the control system 11 with an acceptable degree of malfunction. The command device 10, depending on the results of monitoring and diagnostics in the control system 11, gives commands to switch the engine to a lower mode and to supply an inert medium when the derivatives of the parameter changes within the threshold values are found and to turn off the engine when the parameters and their derivatives go beyond the threshold values.

The method is as follows.

Prior to testing the taxiway in a known manner, for example, using its mathematical model, form threshold values of the measured parameters (temperature and pressure in gas and liquid paths) and their derivatives but time and enter them and the control system 11.

When the taxiway is working, sensors 2, 3, 4 cyclically measure the current values of the parameters in the liquid and gas paths of the engine, as well as the pressure and temperature in the engine compartment.

The signals of the measured parameters and the signals of the threshold values of the parameters and their time derivatives are supplied to the switching device 5, where the operation of comparing the measured values of each parameter and their derivatives with the values of its threshold levels is performed, after which the mismatch signals through the interface device 6 are sent to the computer 7, where the signals are processed and transmitted through the interface unit for recording on the storage media 9 and the command device 10.

When all parameters are in the range between threshold levels, the engine state is assumed normal and the taxiway continues to operate. When any of the parameters goes beyond its threshold level, the derivative of its change is compared with its threshold values.

When the derivatives of the parameter changes in time are found within the threshold values, the degree of the malfunction that arises is admissible to continue the test, and in order to preserve the material of the engine and the devices and cable network located in the engine compartment, the engine is put into reduced mode and a command is sent to the compartment inert medium from source 12.

When the derivatives change in time over their threshold values, they turn off the engine and stop the test.

Claims (1)

A method of monitoring and diagnosing a rocket engine, which consists in cyclically measuring the parameters of the engine and engine compartment, comparing them with predetermined threshold values and comparing the results of monitoring and diagnosing the engine, characterized in that they further determine the time-dependent derivatives of the parameters, compare them with their threshold values and, if the derivatives are within the threshold values, fix the degree of malfunction as permissible, then for Test report has to translate the engine at reduced mode and is fed into the engine compartment inert medium.

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