CN111060761A - Test simulation device, liquid rocket engine test system and test method - Google Patents
Test simulation device, liquid rocket engine test system and test method Download PDFInfo
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- CN111060761A CN111060761A CN201911288693.8A CN201911288693A CN111060761A CN 111060761 A CN111060761 A CN 111060761A CN 201911288693 A CN201911288693 A CN 201911288693A CN 111060761 A CN111060761 A CN 111060761A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
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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
- G01M15/02—Details or accessories of testing apparatus
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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
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R1/00—Details of instruments or arrangements of the types included in groups G01R5/00 - G01R13/00 and G01R31/00
- G01R1/28—Provision in measuring instruments for reference values, e.g. standard voltage, standard waveform
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Abstract
The invention provides a test simulation device, a liquid rocket engine test system and a test method, and aims to solve the technical problems that the existing liquid rocket engine test cannot verify the validity of a real sensor and a cable cannot perform single test on the sensor or a data acquisition system after test confirmation is carried out. The test simulation apparatus includes: the multi-path selector switch is used for controlling the switching of various wiring states between the sensor assembly and the data acquisition system; the standard signal source can realize the output of preset arbitrary waveform signals and is used for system calibration and simulating sensor stable signals and/or test process sensor signals; the voltage detection unit is used for detecting whether the power supply voltage of the sensor assembly meets the requirement or not and detecting the signal output of the sensor assembly; the test circuit comprises a zero position circuit of the analog acquisition system and a load state circuit of the analog resistance type sensor.
Description
Technical Field
The invention relates to a test simulation device, a liquid rocket engine test system and a test method.
Background
In a large liquid rocket engine test, test data is used as a final product of the test, directly influences the test process and is also a basis for evaluating the performance of the engine; because the single test has the characteristics of high test difficulty, high test cost and incapability of acquiring data for the second time at present, the working states of a test system and equipment need to be checked and tested before the test is carried out, and the effectiveness and the reliability of the test system are verified.
At present, the liquid rocket engine test is carried out after an engine electrical system is in butt joint with an engine test system, and has the following defects:
1. the type and the number of the test points are large in the test, and the cable needs to be switched for many times and finally enters a data acquisition system for data acquisition and storage; after the cables are tested and confirmed to be in butt joint, in order to ensure the correctness of the butt joint of a large number of cables, single test aiming at the sensor or the data acquisition system can not be carried out according to the process, so that partial test can not be carried out after the system is in butt joint.
2. Because most of sensors are all pre-installed on the liquid rocket engine and are difficult to disassemble, the sensors are installed on the liquid rocket engine during testing, so that the sensors are always kept static in the testing preparation process, the validity of the real sensors cannot be verified, the testing coverage of a testing system is insufficient, and the hidden danger that faults cannot be found in advance exists.
3. Because the test of a single parameter in the test usually involves a plurality of sets of data acquisition systems and a plurality of data real-time processing flows, the existing single-line and single-section inspection method does not have the combined test capability of software and hardware between systems.
Disclosure of Invention
The invention provides a test simulation device, a liquid rocket engine test system and a test method, and aims to solve the technical problems that the existing liquid rocket engine test cannot verify the validity of a real sensor and a cable cannot perform single test on the sensor or a data acquisition system after test confirmation is carried out.
The technical scheme of the invention is as follows:
the test simulation device is characterized in that: the device is arranged between a sensor assembly of a liquid rocket engine test system and a data acquisition system, and comprises a multi-way selector switch, a standard signal source, a voltage detection unit and a test circuit;
the multi-path selector switch is used for controlling the switching of various wiring states between the sensor assembly and the data acquisition system;
the standard signal source can realize the output of preset arbitrary waveform signals and is used for system calibration and simulating sensor stable signals and/or test process sensor signals;
the voltage detection unit is used for detecting whether the power supply voltage of the sensor assembly meets the requirement or not and detecting the signal output of the sensor assembly;
the test circuit comprises a zero position circuit of the analog acquisition system and a load state circuit of the analog resistance type sensor.
The invention also provides a test system for the liquid rocket engine test, which comprises a sensor assembly and a data acquisition system; it is characterized in that: the test simulation device is further included.
The invention also provides a test method based on the test system for the liquid rocket engine test, which comprises the following test links:
and (3) normal measurement state of the system:
the data acquisition system is directly connected with the sensor, the test simulation device does not access the data acquisition system and intervene the data measurement of the data acquisition system, and the data measurement state of the normal connection of the data acquisition system and the corresponding sensor is realized;
testing the whole system simulation load:
through switching a multi-way switch in the test simulation device, a test circuit in the test simulation device is connected with the sensor in parallel at a signal port and a power supply port between the data acquisition system and the sensor, the output signal of the sensor is changed, and the load state of the sensor is simulated;
the data acquisition system is isolated from the sensor by switching a multi-path switch in the test simulation device, a standard signal source in the test simulation device replaces the sensor at the signal input end of the data acquisition system, and a standard signal source output signal is compiled according to a real test signal, so that the sensor is replaced to simulate the whole-process sensor signal output of the test;
and (3) no-load test of a data acquisition system:
the data acquisition system is isolated from the sensor by switching a multi-path switch in the test simulation device, the sensor is replaced by the test simulation device at the signal input end of the data acquisition system, and the no-load state of the sensor is simulated by accessing a test circuit or a standard signal source in the simulation device instead of the sensor, so that the no-load test of the data acquisition system is realized;
monitoring power supply of a data acquisition system:
the voltage detection unit of the test simulation device is connected to the power output end of the data acquisition system and the power detection ports at the two ends of the sensor by switching a multi-path switch in the test simulation device, so that the power supply of the data acquisition system and the monitoring of the voltages at the two ends of the sensor are realized;
monitoring sensor signals:
the voltage detection unit of the test simulation device is connected to the signal output end of the data acquisition system and the signal output end of the sensor through a multi-path switch in the switch test simulation device, and the signal output of the sensor is monitored.
The invention has the advantages that:
1. according to the invention, a set of test simulation device is arranged between the sensor and the data acquisition system, and under the condition of ensuring that the connection state of the liquid rocket engine test system is not changed, the multi-way switch combination is arranged, so that the single equipment inspection test and the full system test of the full system connection of the sensor and the data acquisition system of the liquid rocket engine test system can be still developed after the engine test system is in butt joint with the engine electrical system.
2. The invention uses the built-in test circuit or standard signal source, can simulate the load state and the no-load state of the sensor in the full system state, and can fully verify the working state of the test system including the sensor.
3. During the preparation period of the liquid rocket engine test, the built-in standard signal source and voltage detection unit can complete the detection of the original signal of the sensor and the detection of the power supply of the data acquisition system on the butt joint surface of the sensor and the data acquisition system of the liquid rocket engine test system, thereby ensuring the effectiveness of a key inspection link.
4. The invention uses the standard signal source, can realize the whole-process analog output of the signal change of each sensor in the test process in the whole test process of the liquid rocket engine, enables the data acquisition system and the control system to truly receive the signal of the sensor, and can carry out the related logic judgment test of the liquid rocket engine test system based on the actual signal of the sensor.
5. The invention adopts the standard signal source, has the online calibration capability to the data acquisition system, realizes automatic inspection and result report output in the test of the test system by the remote communication control switch combination, and improves the efficiency and the accuracy of information test.
Drawings
FIG. 1 is a schematic diagram of a liquid rocket engine test system of the present invention.
FIG. 2 is a schematic diagram of a test simulation apparatus in the liquid rocket engine test system according to the present invention.
Fig. 3 is a connection state diagram of the sensor, the test simulation device and the data acquisition system in a normal measurement state of the system.
Fig. 4 is a first connection state diagram of the sensor, the test simulation device and the data acquisition system under the conditions of the whole system simulation load test and the no-load test of the data acquisition system.
Fig. 5 is a second connection state diagram of the sensor, the test simulation device and the data acquisition system under the conditions of the whole system simulation load test and the data acquisition system no-load test.
FIG. 6 is a diagram of the connection status of the sensor, the test simulation device and the data acquisition system during power supply monitoring of the data acquisition system.
FIG. 7 is a diagram of the connection state of the sensor, the test simulation device and the data acquisition system during the monitoring of the sensor signal.
Detailed Description
The invention is further described below with reference to the accompanying drawings.
As shown in fig. 1, the test system for testing the liquid rocket engine provided by the invention is an improvement on the existing test system for testing the liquid rocket engine, and particularly, a test simulation device is added between a sensor assembly (comprising a thrust sensor, a temperature sensor, a pressure sensor and a flow sensor) and a data acquisition system of the existing test system for testing the liquid rocket engine.
The test simulation device is connected with the sensor assembly through a cable; the test simulation device comprises a multi-path selector switch, a standard signal source, a voltage detection unit and a test circuit.
And the multi-path selector switch is used for controlling the switching of various wiring states between the sensor assembly and the data acquisition system, and can adopt manual switching or program control switching.
The standard signal source can realize the output of preset arbitrary waveform signals and is used for system calibration, simulation of sensor stable signals and/or test process sensor signals.
And the voltage detection unit is used for detecting whether the power supply voltage of the sensor assembly meets the requirement or not and also detecting the signal output of the sensor assembly.
The test circuit comprises a zero position circuit of the analog acquisition system and a circuit for simulating the load state of the resistance sensor.
The test simulation device can realize manual or automatic switching of the communication state of the data acquisition system and each sensor through a multi-way switch (such as a relay), including direct communication and isolation, or connection and isolation with a test circuit and a voltage detection unit.
As shown in fig. 2, taking a four-wire sensor of a typical test system as an example, a port of the sensor includes a signal +, a signal-, a power supply +, and a power supply-, in order to ensure accuracy of a power supply voltage of the sensor, a six-wire system is generally adopted for measurement, that is, one of the sensor sides is connected with one of the power supply + and the power supply-for power supply detection. Different test states can be realized through switching.
1. And (3) normal measurement state of the system:
as shown in fig. 3, the data acquisition system is directly connected to the sensor by switching the multi-way switch in the test simulation device, and the test simulation device does not access the data acquisition system itself and intervene in the data measurement of the data acquisition system, thereby realizing the data measurement state in which the data acquisition system is normally connected to the corresponding sensor.
In a normal measurement state of the system, the connection states of the sensors, the test simulation device and the ports of the data acquisition system are as shown in table 1 below, and at this time, the test simulation device is not connected to the data acquisition system.
TABLE 1
2. Testing the whole system simulation load:
the whole system simulation load test refers to the test and inspection of the working states of the sensor and the data acquisition system under the load state.
2.1 as shown in fig. 4, when the whole system simulates the load test, the test circuit inside the test simulation device can be connected in parallel with the sensor at the signal port and the power port between the data acquisition system and the sensor by switching the multi-way switch in the test simulation device, so as to change the output signal of the sensor, simulate the load state of the sensor and realize the simulation of the load at the sensor end;
the test circuit mainly aims at the resistance type sensor, and the resistance is connected in parallel to a sensor power supply and a signal end by switching a multi-path switch in the test simulation device, so that the signal output of the sensor is changed, and the load state of the sensor is simulated.
At this time, the connection states of the respective ports of the sensor, the test simulation apparatus, and the acquisition apparatus are as shown in table 2 below.
TABLE 2
2.2 as shown in fig. 5, when the whole system simulates the load test, the data acquisition system and the sensor can be isolated by switching the multi-way switch in the test simulation device, the sensor is replaced by the standard signal source in the test simulation device at the signal input end of the data acquisition system, and the standard signal source output signal is compiled according to the real test signal, so that the sensor is replaced to simulate the whole process sensor signal output of the test, and the requirement of the data acquisition system for logically judging the data is met.
At this time, the connection states of the sensors, the test simulation apparatus, and the data acquisition system are shown in table 3 below.
TABLE 3
3. And (3) no-load test of a data acquisition system:
the switch switching state of the data acquisition system during no-load test is the same as that of the full-system simulation load test, the circuit connection relationship is shown in fig. 4 and 5, the data acquisition system is isolated from the sensor, the sensor is replaced by the test simulation device at the signal input end of the data acquisition system, and the no-load test of the data acquisition system is realized by accessing an internal test circuit or a standard signal source of the simulation device to replace the sensor to simulate the no-load state of the sensor. The test circuit and the standard signal source mainly aim at a resistance or voltage type sensor, and realize zero output of the analog sensor by short-circuiting the positive and negative ends of a signal of the sensor or inputting a zero-voltage signal.
The connection states of the ports of the sensor, the test simulation device and the data acquisition system when the test circuit simulates the no-load state of the sensor are shown in the following table 4.
TABLE 4
The connection states of the ports of the sensor, the test simulation device and the data acquisition system when the standard signal source simulates the sensor in the no-load state are shown in the following table 5.
TABLE 5
4. Monitoring power supply of a data acquisition system:
as shown in fig. 6, by switching the multi-way switch in the test simulation device, the voltage detection unit of the test simulation device is connected to the power output end of the data acquisition system and the power detection ports at the two ends of the sensor, so as to realize the power supply of the data acquisition system and the monitoring of the voltage at the two ends of the sensor.
At this time, the connection states of the sensors, the test simulation apparatus, and the ports of the data acquisition system are as shown in table 6 below.
TABLE 6
5. Monitoring sensor signals:
as shown in fig. 7, by switching the multi-way switch in the test simulation device, the voltage detection unit of the test simulation device is connected to the signal output end of the data acquisition system and the signal output end of the sensor, and the signal output of the sensor is monitored, so as to verify the accuracy of the output state of the sensor and the measurement value of the data acquisition system. At this time, the connection states of the sensor, the simulation device, and the acquisition device are as shown in table 7 below.
TABLE 7
6. Automatic testing:
automatic test and data result output of all measuring points of the liquid rocket engine test system are realized through programmable solid-state relay switch combination and standard signal source combination.
Claims (3)
1. Test analogue means, its characterized in that: the device is arranged between a sensor assembly of a liquid rocket engine test system and a data acquisition system, and comprises a multi-way selector switch, a standard signal source, a voltage detection unit and a test circuit;
the multi-path selector switch is used for controlling the switching of various wiring states between the sensor assembly and the data acquisition system;
the standard signal source can realize the output of preset arbitrary waveform signals and is used for system calibration and simulating sensor stable signals and/or test process sensor signals;
the voltage detection unit is used for detecting whether the power supply voltage of the sensor assembly meets the requirement or not and detecting the signal output of the sensor assembly;
the test circuit comprises a zero position circuit of the analog acquisition system and a load state circuit of the analog resistance type sensor.
2. The liquid rocket engine test system comprises a sensor assembly and a data acquisition system; the method is characterized in that: further comprising the test simulation apparatus of claim 1.
3. The test method of the liquid rocket engine test system based on claim 2, characterized by comprising the following test links:
and (3) normal measurement state of the system:
the data acquisition system is directly connected with the sensor, the test simulation device does not access the data acquisition system and intervene the data measurement of the data acquisition system, and the data measurement state of the normal connection of the data acquisition system and the corresponding sensor is realized;
testing the whole system simulation load:
through switching a multi-way switch in the test simulation device, a test circuit in the test simulation device is connected with the sensor in parallel at a signal port and a power supply port between the data acquisition system and the sensor, the output signal of the sensor is changed, and the load state of the sensor is simulated;
the data acquisition system is isolated from the sensor by switching a multi-path switch in the test simulation device, a standard signal source in the test simulation device replaces the sensor at the signal input end of the data acquisition system, and a standard signal source output signal is compiled according to a real test signal, so that the sensor is replaced to simulate the whole-process sensor signal output of the test;
and (3) no-load test of a data acquisition system:
the data acquisition system is isolated from the sensor by switching a multi-path switch in the test simulation device, the sensor is replaced by the test simulation device at the signal input end of the data acquisition system, and the no-load state of the sensor is simulated by accessing a test circuit or a standard signal source in the simulation device instead of the sensor, so that the no-load test of the data acquisition system is realized;
monitoring power supply of a data acquisition system:
the voltage detection unit of the test simulation device is connected to the power output end of the data acquisition system and the power detection ports at the two ends of the sensor by switching a multi-path switch in the test simulation device, so that the power supply of the data acquisition system and the monitoring of the voltages at the two ends of the sensor are realized;
monitoring sensor signals:
the voltage detection unit of the test simulation device is connected to the signal output end of the data acquisition system and the signal output end of the sensor through a multi-path switch in the switch test simulation device, and the signal output of the sensor is monitored.
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| CN112098097A (en) * | 2020-08-20 | 2020-12-18 | 西安航天动力试验技术研究所 | High-reliability measuring system for simultaneously acquiring multiple types of parameters |
| CN112326254A (en) * | 2020-10-30 | 2021-02-05 | 西安航天动力试验技术研究所 | State detection device and method for liquid ramjet test system |
| CN113155467A (en) * | 2021-01-19 | 2021-07-23 | 中国人民解放军63921部队 | Online health management method based on advanced shutdown of liquid rocket sublevel engine |
| CN113514248A (en) * | 2021-05-11 | 2021-10-19 | 潍柴动力股份有限公司 | Data processing method and device for sensor in engine |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112098097A (en) * | 2020-08-20 | 2020-12-18 | 西安航天动力试验技术研究所 | High-reliability measuring system for simultaneously acquiring multiple types of parameters |
| CN112326254A (en) * | 2020-10-30 | 2021-02-05 | 西安航天动力试验技术研究所 | State detection device and method for liquid ramjet test system |
| CN113155467A (en) * | 2021-01-19 | 2021-07-23 | 中国人民解放军63921部队 | Online health management method based on advanced shutdown of liquid rocket sublevel engine |
| CN113514248A (en) * | 2021-05-11 | 2021-10-19 | 潍柴动力股份有限公司 | Data processing method and device for sensor in engine |
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