Attitude control engine chamber pressure redundant measurement system and measurement method

Abstract

The present application relates to attitude control engine chamber pressure measurement system and method, specifically relates to a kind of attitude control engine chamber pressure redundancy measurement system and measurement method, solve the technical problem that the chamber pressure parameter of attitude control engine cannot be complete, accurate acquisition.The attitude control engine chamber pressure redundancy measurement system provided by the present application includes double-redundancy pressure sensor, acquisition unit, data acquisition and processing unit, switching unit and check unit.Double-redundancy pressure sensor is used to acquire two independent measurement signals, including two measurement channels that are independent of each other and share an input terminal, although an additional measurement channel is added, but its volume, weight and the sensor used in the past attitude control engine test are consistent.Check unit controls pressure loading assembly through PID controller, controls the pressure of gas source to double-redundancy pressure sensor, calculates sensitivity coefficient according to the pressure value measured by double-redundancy pressure sensor and standard pressure value, to realize in-situ calibration of double-redundancy pressure sensor.

Description

Technical Field

[0001] This invention relates to an attitude control engine chamber pressure measurement system and method, specifically to an attitude control engine chamber pressure redundancy measurement system and method. Background Technology

[0002] Attitude control engines adjust the flight trajectory and attitude of spacecraft by burning propellant in the combustion chamber. They are the power foundation for orbital insertion and attitude adjustment for various types of spacecraft, and their performance is a critical aspect of the entire model development process. Chamber pressure, as a crucial parameter required for the design of the attitude control engine's structure, combustion efficiency, and propulsion system, is an important basis for judging the engine's performance and reliability, and is of great significance to model development. Currently, the chamber pressure parameter measurement devices and methods used in attitude control engine testing are in a single-point mode. This mode is prone to problems in obtaining complete and accurate chamber pressure parameters under conditions of repeated start-stop cycles and high-frequency pulse operation, which adversely affects the model's development and finalization.

[0003] The measurement of the attitude control engine chamber pressure is limited by the strength of the engine chamber pressure measurement interface and the size and weight of the pressure sensor itself. Currently, a single pressure sensor, a single cable, a single acquisition system, and a single acquisition computer are commonly used to measure and acquire chamber pressure data. Each of these links is a single point of failure. If any link fails, it will be impossible to obtain the complete chamber pressure parameters of the attitude control engine during the test. Summary of the Invention

[0004] The purpose of this invention is to solve the technical problem that the chamber pressure parameters of attitude control engines cannot be obtained completely and accurately, and to provide a redundant measurement system and method for chamber pressure of attitude control engines.

[0005] To achieve the above objectives, the technical solution adopted by the present invention is as follows:

[0006] A redundant measurement system for engine chamber pressure in attitude control includes a pressure sensor, a data acquisition unit, and a data acquisition and processing unit connected in sequence. Its key feature is that:

[0007] The number of acquisition units and data acquisition and processing units are both two sets, and the two sets of acquisition units are respectively connected to the two sets of data acquisition and processing units;

[0008] The pressure sensor is a dual-redundant pressure sensor, used to acquire and output two independent sets of measurement signals; the dual-redundant pressure sensor includes two measurement channels, the two measurement channels share an input terminal that is connected to the combustion chamber of the attitude control engine to be measured through a pressure tapping tube, and the output terminals of the two measurement channels are respectively connected to the input terminals of the two acquisition units.

[0009] It also includes a calibration unit, which is used to perform on-site calibration of the dual-redundancy pressure sensor, including a pressure loading assembly, a gas source, a standard pressure sensor, a PID controller, and a pressure controller;

[0010] The gas source and the input terminal of the dual-redundant pressure sensor are connected through a pipeline. The pressure loading component and the standard pressure sensor are sequentially arranged on the pipeline between the gas source and the dual-redundant pressure sensor along the gas flow direction. The PID controller is electrically connected to the pressure controller, the standard pressure sensor, and the pressure loading component, respectively.

[0011] The pressure controller is used to set the pressure verification standard value and send it to the PID controller; the standard pressure sensor is used to measure the pressure value applied by the air source to the dual-redundant pressure sensor and send it to the PID controller; the PID controller controls the pressure loading component to shut down after the pressure applied by the air source to the dual-redundant pressure sensor reaches the pressure verification standard value.

[0012] Furthermore, the pressure loading component, air source, standard pressure sensor, PID controller, dual-redundant pressure sensor, and the attitude control engine to be measured are located at the test front, while the acquisition unit, data acquisition and processing unit, and pressure controller are located in the measurement and control room.

[0013] It also includes a transfer unit set in the measurement and control room. The transfer unit is connected to the output end of the dual-redundant pressure sensor, the input ends of the two sets of acquisition units, the output end of the pressure controller, and the input end of the PID controller. It is used to transfer the two sets of measurement signals output by the dual-redundant pressure sensor to the two sets of acquisition units, and to transfer the pressure calibration standard value output by the pressure controller to the input end of the PID controller.

[0014] Furthermore, the switching unit includes a control console, a switching cabinet, and a signal converter connected in sequence;

[0015] The adapter cabinet has multiple sets of independent input and output terminals, and the input and output terminals are connected one-to-one. The pressure controller and PID controller are connected to the first set of input and output terminals respectively. The two output terminals of the dual-redundant pressure sensor are connected to the second and third sets of input terminals respectively. The second and third sets of output terminals are connected to the two input terminals of the signal adapter respectively, for receiving two sets of measurement signals.

[0016] The two output terminals of the signal converter are respectively connected to the input terminals of the two sets of acquisition units, and the two sets of measurement signals are output to the two sets of acquisition units respectively.

[0017] The control console is electrically connected to the signal converter and is used to send synchronization control signals, thereby enabling synchronous acquisition by the two sets of acquisition units and the two sets of data acquisition and processing units.

[0018] Furthermore, the dual-redundant pressure sensor includes a housing, pressure inlet heads and electrical connectors respectively disposed at both ends of the housing, and two sets of identical and independent measurement channels disposed inside the housing.

[0019] The input end of the pressure head is connected to the air source during on-site calibration, or to the attitude control engine to be measured during measurement, and the output end is connected to two sets of measurement channels;

[0020] The measurement channel measures the calibration pressure of the air source during on-site calibration, or measures the chamber pressure of the combustion chamber of the attitude control engine to be measured during measurement, including a pressure sensing chamber, a pressure core, and a signal conditioning board;

[0021] The pressure-sensing cavity is located inside the outer casing near the pressure inlet head and is connected to the output end of the pressure inlet head; the pressure core is located inside the pressure-sensing cavity, and the output end of the pressure core is connected to the input end of the signal conditioning board; the signal conditioning board is located outside the pressure-sensing cavity, and its output end is connected to the input end of the electrical connector.

[0022] The electrical connector has two independent input and output terminals, with each input terminal corresponding to the output terminal. The input terminal is connected to the output terminals of the two measurement channels respectively, and the output terminal is connected to the input terminals of the two acquisition units respectively via cables.

[0023] Furthermore, a Wheatstone bridge is provided on the pressure core.

[0024] Furthermore, the data acquisition and processing unit includes an independent sensor in-situ calibration module, an engine test real-time display module, and a test data rapid processing module.

[0025] Furthermore, the pressure loading assembly includes a flow control valve and a needle valve;

[0026] The flow control valve and the needle valve are sequentially installed on the pipeline between the gas source and the dual-redundant pressure sensor along the gas flow direction.

[0027] The flow control valve is electrically connected to the PID controller.

[0028] A method for measuring the redundancy of pressure in an attitude control engine chamber, based on the aforementioned attitude control engine chamber pressure redundancy measurement system, is characterized by including the following steps:

[0029] Step 1: Connect the dual-redundant pressure sensor to the air source, determine the rated chamber pressure of the attitude control engine to be measured, set the calibration range according to the rated chamber pressure, and adjust the parameters of the PID controller.

[0030] Step 2: Connect the dual-redundant pressure sensor to the air source and perform in-situ calibration of the dual-redundant pressure sensor to obtain the sensitivity coefficients of the two measurement channels of the dual-redundant pressure sensor.

[0031] Step 3: Input the sensitivity coefficients of the two measurement channels obtained in Step 2 into the data acquisition and processing unit, and connect the dual-redundant pressure sensor to the combustion chamber of the attitude control engine to be measured through the pressure tapping pipe;

[0032] Step 4: The dual-redundant pressure sensor acquires two measurement signals from a single chamber pressure measurement point of the attitude control engine under test and sends them to two sets of acquisition units; the two sets of acquisition units acquire two measurement signals respectively and send them to the data acquisition and processing unit.

[0033] Step 5: The data acquisition and processing unit processes, records, and displays the two received measurement signals based on the sensitivity coefficients of the two measurement channels of the dual-redundant pressure sensor, thereby obtaining the two chamber pressure signals at a single chamber pressure measurement point of the attitude control engine to be measured.

[0034] Furthermore, step 2 specifically includes:

[0035] 2.1 Connect the dual-redundant pressure sensor to the air source, set the pressure calibration standard value for the pressure controller, and send it to the PID controller;

[0036] 2.2 The PID controller activates the pressure loading component, enabling the air source to begin supplying air and loading pressure onto the dual-redundant pressure sensor to provide a verification pressure value.

[0037] 2.3 The standard pressure sensor measures and verifies the pressure value, and sends the obtained standard pressure measurement value to the PID controller;

[0038] 2.4 The PID controller determines whether the standard measured pressure value reaches the pressure verification standard value sent by the pressure controller. If the standard measured pressure value reaches the pressure verification standard value, the PID controller controls the pressure loading component to shut down, and the air source stops loading pressure onto the dual-redundant pressure sensor.

[0039] 2.5. The dual-redundant pressure sensor measures and verifies the pressure value, and sends the two measurement signals to two sets of acquisition units;

[0040] 2.6 The two sets of acquisition units acquire two measurement signals respectively and send them to the data acquisition and processing unit. The data acquisition and processing unit records the pressure calibration standard value and the corresponding measurement pressure values ​​of the two measurement channels.

[0041] 2.7 Change the pressure calibration standard value set on the pressure controller and send it to the PID controller. Repeat steps 2.2-2.6 to obtain at least 36 sets of pressure calibration standard values ​​and the corresponding measured pressure values ​​of the two measurement channels.

[0042] 2.8. The least squares method is used to fit at least 36 sets of pressure calibration standard values ​​and the corresponding measured pressure values ​​of the two measurement channels to obtain the sensitivity coefficients of the two measurement channels of the dual-redundant pressure sensor.

[0043] Furthermore, the pressure calibration standard value set by the pressure controller is greater than or equal to the rated chamber pressure of the attitude control engine to be measured, and is set using a three-pass, six-gear rise and return method;

[0044] The "three-round six-gear up-and-down" process refers to setting six gears sequentially from low to high and then from high to low, repeating this process three times.

[0045] Compared with the prior art, the present invention has the following beneficial technical effects:

[0046] 1. The attitude control engine chamber pressure redundancy measurement system provided by the present invention uses a dual-redundant pressure sensor to measure the chamber pressure, and can collect two measurement signals, avoiding the problem of not being able to obtain complete chamber pressure parameters due to failure of any link, and effectively improving the reliability of the attitude control engine chamber pressure parameter measurement system.

[0047] 2. The attitude control engine chamber pressure redundancy measurement system provided by the present invention adds a calibration unit, which can perform on-site in-situ calibration of the dual-redundancy pressure sensor before formal testing, thus ensuring the measurement accuracy of the dual-redundancy pressure sensor.

[0048] 3. In the attitude control engine chamber pressure redundancy measurement system provided by the present invention, although the dual-redundancy pressure sensor has two sets of pressure cores and two sets of signal conditioning boards inside, its size and weight are consistent with the sensors used in previous attitude control engine tests, and it does not affect the measurement accuracy of the system. Attached Figure Description

[0049] Figure 1 This is a schematic diagram of the attitude control engine chamber pressure redundancy measurement system provided in an embodiment of the present invention.

[0050] Figure 2 This is a structural diagram of the dual-redundancy pressure sensor in an embodiment of the present invention;

[0051] The annotations in the attached figures are explained as follows:

[0052] 1-Attitude control engine to be measured, 2-Dual redundancy pressure sensor, 3-Adapter cabinet, 4-Signal adapter, 5-Control console, 6-Acquisition unit, 7-Data acquisition and processing unit, 8-Pressure controller, 9-PID controller, 10-Standard pressure sensor, 11-Pressure loading assembly, 12-Air source;

[0053] 21-Pressure inlet head, 22-Pressure sensing chamber, 23-Pressure core, 24-Signal conditioning board, 25-Electrical connector, 26-Outer shell. Detailed Implementation

[0054] The following detailed description, in conjunction with the accompanying drawings and specific embodiments, outlines a redundancy measurement system and method for attitude control engine chamber pressure. Those skilled in the art should understand that these embodiments are merely illustrative of the technical principles of the invention and are not intended to limit the scope of protection of the invention.

[0055] A redundant measurement system for engine chamber pressure in attitude control, such as Figure 1 As shown, it includes a pressure sensor, a data acquisition unit 6, and a data acquisition and processing unit 7 connected in sequence, and also includes a transfer unit and a verification unit.

[0056] The calibration unit, pressure sensor, and the attitude control engine 1 to be measured are located at the test front, while the transfer unit, acquisition unit 6, and data acquisition and processing unit 7 are located in the measurement and control room.

[0057] There are two sets of acquisition units 6 and two sets of data acquisition and processing units 7. The input terminals of the two sets of acquisition units 6 are connected to the output terminals of the adapter unit. The output terminals of the two sets of acquisition units 6 are connected to the two sets of data acquisition and processing units 7. The data acquisition and processing unit 7 includes an independent sensor in-situ calibration module, an engine test real-time display module, and a test data rapid processing module.

[0058] The pressure sensor is a dual-redundant pressure sensor 2, used to acquire and output two independent sets of measurement signals. The dual-redundant pressure sensor 2 includes two measurement channels, which share a single input terminal. The input terminal is connected to the calibration unit during on-site calibration, or connected to the combustion chamber of the attitude control engine 1 under test through a pressure tapping pipe during measurement. The output terminals of the two measurement channels are respectively connected to the adapter unit.

[0059] like Figure 2As shown, the dual-redundant pressure sensor 2 includes a housing 26, pressure inlets 21 and electrical connectors 25 respectively disposed at both ends of the housing 26, and two sets of identical and independent measurement channels disposed inside the housing 26. The input end of the pressure inlet 21 is connected to the calibration unit during on-site calibration, or connected to the combustion chamber of the attitude control engine 1 under test via a pressure tap during measurement; its output end is connected to the two sets of measurement channels. The electrical connector 25 has two independent input and output ends, with each input end corresponding to the output end. The input end is connected to the output end of each of the two sets of measurement channels, and the output end is connected to the input end of the adapter unit via a cable.

[0060] The measurement channel is used to measure the calibration pressure applied by the air source 12 during on-site calibration, or to measure the chamber pressure of the combustion chamber of the attitude control engine 1 under test during measurement. It includes a pressure sensing chamber 22, a pressure core 23, and a signal conditioning board 24. The pressure sensing chamber 22 is located inside the housing 26 near the pressure inlet head 21 and is connected to the pressure inlet head 21. The pressure core 23 is located inside the pressure sensing chamber 22, and its output is connected to the input of the signal conditioning board 24. The signal conditioning board 24 is located outside the pressure sensing chamber 22, and its output is connected to the input of the electrical connector 25. A Wheatstone bridge is installed on the pressure core 23 to perform piezoelectric conversion on the measurement signal. The signal conditioning board 24 converts the millivolt voltage signal output by the Wheatstone bridge into a standard (1-5)V voltage output signal.

[0061] The pressure source enters the pressure sensing chamber 22 of its respective pressure core 23 through the pressure inlet head 21. The two sets of signal conditioning boards 24 are powered separately and their output signals do not interfere with each other. The dual-redundant pressure sensor 2 uses the Wheatstone bridge principle for piezoelectric conversion. Its size and weight are consistent with the sensors used in previous attitude control engine tests.

[0062] While using a dual-redundant pressure sensor 2 to measure the chamber pressure of the attitude control engine 1 can meet the requirements of redundant measurement, due to the sensitivity drift and zero-point drift characteristics of the dual-redundant pressure sensor 2, it is necessary to perform on-site in-situ calibration of the dual-redundant pressure sensor 2 before the formal test to ensure its measurement accuracy. Therefore, this embodiment includes a calibration unit to perform on-site calibration of the dual-redundant pressure sensor 2.

[0063] The calibration unit includes a pressure loading component 11, a gas source 12, a standard pressure sensor 10, a PID controller 9, and a pressure controller 8. The pressure loading component 11, gas source 12, standard pressure sensor 10, and PID controller 9 are located at the test front, while the pressure controller 8 is located in the measurement and control room.

[0064] The gas source 12 is connected to the input terminal of the dual-redundant pressure sensor 2 via a pipeline. The pressure loading assembly 11 and the standard pressure sensor 10 are sequentially arranged on the pipeline between the gas source 12 and the dual-redundant pressure sensor 2 along the flow direction of the gas output from the gas source 12. The pressure controller 8 is connected to the adapter unit, and the PID controller 9 is electrically connected to the adapter unit, the standard pressure sensor 10, and the pressure loading assembly 11, respectively. The pressure controller 8 is used to set the pressure calibration standard value and send it to the PID controller 9 through the adapter unit. The standard pressure sensor 10 is used to measure the pressure value loaded by the gas source 12 onto the dual-redundant pressure sensor 2 and send it to the PID controller 9. The PID controller 9 controls the pressure loading assembly 11 to shut down after the pressure loaded by the gas source 12 onto the dual-redundant pressure sensor 2 reaches the pressure calibration standard value.

[0065] The pressure loading assembly 11 includes a flow control valve and a needle valve connected in sequence to the input and output. The flow control valve and the needle valve are arranged in sequence along the gas flow direction on the pipeline between the gas source 12 and the dual-redundant pressure sensor 2. The flow control valve is electrically connected to the PID controller 9.

[0066] The transfer unit is used to transfer the two sets of measurement signals output by the dual-redundant pressure sensor 2 to the two sets of acquisition units 6 respectively, and to transfer the pressure calibration standard value output by the pressure controller 8 to the PID controller 9. It includes a control console 5, a transfer cabinet 3 and a signal converter 4 connected in sequence.

[0067] The adapter cabinet 3 has multiple sets of independent input and output terminals, with each input terminal connected to the corresponding output terminal. The pressure controller 8 and PID controller 9 are connected to the first set of input and output terminals, respectively. The two output terminals of the dual-redundant pressure sensor 2 are connected to the second and third sets of input terminals, respectively. The second and third sets of output terminals are connected to the two input terminals of the signal adapter 4, respectively. The two output terminals of the signal adapter 4 are connected to the input terminals of the two acquisition units 6, respectively, outputting the two sets of measurement signals to the two acquisition units 6. The control console 5 is electrically connected to the signal adapter 4 and is used to send synchronous control signals to the acquisition units 6 and the data acquisition and processing unit 7, realizing synchronous acquisition by the two acquisition units 6 and the data acquisition and processing unit 7.

[0068] This embodiment also provides a method for measuring the redundancy of the chamber pressure of an attitude control engine, based on the above-mentioned attitude control engine chamber pressure redundancy measurement system, including the following steps:

[0069] Step 1: Determine the rated chamber pressure of the attitude control engine 1 to be measured. Based on the rated chamber pressure, set the calibration range to 0MPa~2.5MPa. Adjust the parameters of the PID controller 9 as follows: P=50, I=100, D=25.

[0070] Step 2: Connect the dual-redundant pressure sensor 2 to the air source 12, and perform in-situ calibration on the dual-redundant pressure sensor 2 to obtain the sensitivity coefficients of the two measurement channels of the dual-redundant pressure sensor 2, specifically:

[0071] 2.1 Connect the dual-redundant pressure sensor 2 to the air source 12, set the pressure calibration standard value for the pressure controller 8, and send it to the PID controller 9;

[0072] 2.2 The PID controller 9 turns on the pressure loading component 11, so that the air source 12 starts to deliver air, and loads pressure onto the dual-redundant pressure sensor 2 to provide a verification pressure value;

[0073] 2.3 The standard pressure sensor 10 measures and verifies the pressure value, and sends the obtained standard pressure measurement value to the PID controller 9;

[0074] 2.4 The PID controller 9 determines whether the standard measured value of the pressure has reached the pressure calibration standard value. If the standard measured value of the pressure has reached the pressure calibration standard value, the PID controller 9 controls the pressure loading component 11 to close, and the air source 12 stops loading pressure onto the dual-redundant pressure sensor 2.

[0075] 2.5. The dual-redundant pressure sensor 2 measures and verifies the pressure value, and sends the two measurement signals to the two sets of acquisition units 6;

[0076] 2.6 The two sets of acquisition units 6 respectively acquire two measurement signals and send them to the data acquisition and processing unit 7. The data acquisition and processing unit 7 records the pressure calibration standard value and the corresponding measurement pressure values ​​of the two measurement channels.

[0077] 2.7 Change the pressure calibration standard value set by the pressure controller 8 and send it to the PID controller 9. Repeat steps 2.2-2.6 to obtain at least 36 sets of pressure calibration standard values ​​and the corresponding measured pressure values ​​of the two measurement channels. The pressure threshold set by the pressure controller 8 is greater than or equal to the rated chamber pressure of the attitude control engine 1 to be measured, and is set using a three-pass six-gear rise and fall method. The three-pass six-gear rise and fall method means setting six gears from low to high and then from high to low in sequence, repeating three times.

[0078] 2.8. The least squares method is used to fit at least 36 sets of pressure calibration standard values ​​and the corresponding measured pressure values ​​of the two measurement channels to obtain the sensitivity coefficients of the two measurement channels of the dual-redundant pressure sensor 2.

[0079] Step 3: Input the sensitivity coefficients of the two measurement channels obtained in Step 2 into the data acquisition and processing unit 7, and connect the dual-redundant pressure sensor 2 to the combustion chamber of the attitude control engine 1 to be measured through the pressure pipe.

[0080] Step 4: The dual-redundant pressure sensor 2 collects two measurement signals from a single chamber pressure measurement point of the attitude control engine 1 to be measured, and sends them to the transfer unit. The transfer unit transfers the two measurement signals to two sets of acquisition units 6 respectively. The two sets of acquisition units 6 collect the two measurement signals respectively and send them to the data acquisition and processing unit 7.

[0081] Step 5: The data acquisition and processing unit 7 processes, records, and displays the two received measurement signals based on the sensitivity coefficients of the two measurement channels of the dual-redundant pressure sensor 2, thereby obtaining the two chamber pressure signals at a single chamber pressure measurement point of the attitude control engine 1 to be measured.

Claims

1. A redundant measurement system for the chamber pressure of an attitude control engine, comprising a pressure sensor, a data acquisition unit (6), and a data acquisition and processing unit (7) connected in sequence, characterized in that: The number of the acquisition unit (6) and the data acquisition and processing unit (7) are both two sets, and the two sets of acquisition units (6) are respectively connected to the two sets of data acquisition and processing units (7); The pressure sensor is a dual-redundant pressure sensor (2), used to collect and output two independent sets of measurement signals; the dual-redundant pressure sensor (2) includes two measurement channels, and the two measurement channels share one input terminal; the input terminal is connected to the combustion chamber of the attitude control engine (1) to be measured through a pressure-sensing pipe, and the output terminals of the two measurement channels are respectively connected to the input terminals of the two sets of acquisition units (6); It also includes a calibration unit for on-site calibration of the dual-redundant pressure sensor (2), which includes a pressure loading assembly (11), an air source (12), a standard pressure sensor (10), a PID controller (9), and a pressure controller (8). The gas source (12) is connected to the input end of the dual-redundant pressure sensor (2) through a pipeline. The pressure loading component (11) and the standard pressure sensor (10) are sequentially arranged on the pipeline between the gas source (12) and the dual-redundant pressure sensor (2) along the gas flow direction. The PID controller (9) is electrically connected to the pressure controller (8), the standard pressure sensor (10), and the pressure loading component (11) respectively. The pressure controller (8) is used to set the pressure verification standard value and send it to the PID controller (9); the standard pressure sensor (10) is used to measure the pressure value loaded by the gas source (12) onto the dual-redundant pressure sensor (2) and send it to the PID controller (9); the PID controller (9) controls the pressure loading component (11) to shut down after the pressure loaded by the gas source (12) onto the dual-redundant pressure sensor (2) reaches the pressure verification standard value; The pressure loading component (11), air source (12), standard pressure sensor (10), PID controller (9), dual-redundant pressure sensor (2) and the attitude control engine to be measured (1) are located at the test front, and the acquisition unit (6), data acquisition and processing unit (7) and pressure controller (8) are located in the measurement and control room. It also includes a transfer unit set in the measurement and control room. The transfer unit is connected to the output end of the dual-redundant pressure sensor (2), the input ends of the two sets of acquisition units (6), the output end of the pressure controller (8), and the input end of the PID controller (9). It is used to transfer the two sets of measurement signals output by the dual-redundant pressure sensor (2) to the two sets of acquisition units (6) respectively, and to transfer the pressure verification standard value output by the pressure controller (8) to the input end of the PID controller (9).

2. The attitude control engine chamber pressure redundancy measurement system according to claim 1, characterized in that: The switching unit includes a control console (5), a switching cabinet (3) and a signal converter (4) connected in sequence. The adapter cabinet (3) has multiple independent input and output terminals, and the input and output terminals are connected one-to-one. The pressure controller (8) and the PID controller (9) are respectively connected to the first set of input and output terminals. The two output terminals of the dual-redundant pressure sensor (2) are respectively connected to the second and third sets of input terminals. The second and third sets of output terminals are respectively connected to the two input terminals of the signal adapter (4) to receive two sets of measurement signals. The two output terminals of the signal converter (4) are respectively connected to the input terminals of the two sets of acquisition units (6) to output the two sets of measurement signals to the two sets of acquisition units (6). The control console (5) is electrically connected to the signal converter (4) and is used to send a synchronization control signal, thereby realizing the synchronous acquisition of two sets of acquisition units (6) and two sets of data acquisition and processing units (7).

3. The attitude control engine chamber pressure redundancy measurement system according to claim 1 or 2, characterized in that: The dual-redundant pressure sensor (2) includes a housing (26), pressure inlet heads (21) and electrical connectors (25) respectively disposed at both ends of the housing (26), and two sets of identical and independent measurement channels disposed inside the housing (26). The input end of the pressure head (21) is connected to the air source (12) during on-site calibration, or connected to the combustion chamber of the attitude control engine (1) to be measured through a pressure pipe during measurement, and the output end is connected to two sets of measurement channels; The measurement channel is used to measure the calibration pressure loaded by the gas source (12) during on-site calibration, or to measure the chamber pressure of the combustion chamber of the attitude control engine (1) to be measured during measurement, including the pressure sensing chamber (22), the pressure core (23) and the signal conditioning board (24). The pressure-sensing cavity (22) is located inside the outer casing (26) near one end of the pressure inlet head (21) and is connected to the output end of the pressure inlet head (21); the pressure core (23) is located inside the pressure-sensing cavity (22), and the output end of the pressure core (23) is connected to the input end of the signal conditioning board (24); the signal conditioning board (24) is located outside the pressure-sensing cavity (22), and its output end is connected to the input end of the electrical connector (25); The electrical connector (25) has two sets of independent input and output terminals, and the input terminals and output terminals are connected one-to-one. The input terminals are connected to the output terminals of the two sets of measurement channels respectively, and the output terminals are connected to the input terminals of the two sets of acquisition units (6) respectively through cables.

4. The attitude control engine chamber pressure redundancy measurement system according to claim 3, characterized in that: A Wheatstone bridge is provided on the pressure core (23).

5. The attitude control engine chamber pressure redundancy measurement system according to claim 4, characterized in that: The data acquisition and processing unit (7) includes an independent sensor in-situ calibration module, an engine test real-time display module, and a test data rapid processing module.

6. The attitude control engine chamber pressure redundancy measurement system according to claim 5, characterized in that: The pressure loading assembly (11) includes a flow control valve and a needle valve; The flow control valve and the needle valve are sequentially installed on the pipeline between the gas source (12) and the dual-redundant pressure sensor (2) along the gas flow direction; The flow control valve is electrically connected to the PID controller (9).

7. A method for measuring the redundancy of chamber pressure in an attitude control engine, based on the attitude control engine chamber pressure redundancy measurement system according to any one of claims 1-6, characterized in that, Includes the following steps: Step 1: Determine the rated chamber pressure of the attitude control engine (1) to be measured, set the calibration range according to the rated chamber pressure, and adjust the parameters of the PID controller (9); Step 2: Connect the dual-redundant pressure sensor (2) to the air source (12), perform in-situ calibration of the dual-redundant pressure sensor (2), and obtain the sensitivity coefficients of the two measurement channels of the dual-redundant pressure sensor (2); Step 3: Input the sensitivity coefficients of the two measurement channels obtained in Step 2 into the data acquisition and processing unit (7), and connect the dual-redundant pressure sensor (2) to the combustion chamber of the attitude control engine (1) to be measured through the pressure pipe; Step 4: The dual-redundant pressure sensor (2) collects two measurement signals from a single chamber pressure measurement point of the attitude control engine (1) to be measured and sends them to two sets of acquisition units (6); the two sets of acquisition units (6) collect two measurement signals respectively and send them to the data acquisition and processing unit (7). Step 5: The data acquisition and processing unit (7) processes, records, and displays the two received measurement signals based on the sensitivity coefficients of the two measurement channels of the dual-redundant pressure sensor (2), and obtains the two chamber pressure signals at a single chamber pressure measurement point of the attitude control engine (1) to be measured.

8. The attitude control engine chamber pressure redundancy measurement method according to claim 7, characterized in that, Step 2 specifically involves: 2.1 Connect the dual-redundant pressure sensor (2) to the air source (12), set the pressure verification standard value in the pressure controller (8), and send it to the PID controller (9). 2.2 The PID controller (9) opens the pressure loading component (11), so that the air source (12) starts to deliver air, loads pressure onto the dual-redundant pressure sensor (2), and provides a verification pressure value; 2.3 The standard pressure sensor (10) measures and verifies the pressure value, and sends the obtained standard pressure measurement value to the PID controller (9). 2.4 The PID controller (9) determines whether the standard measured value of the pressure reaches the pressure verification standard value. If the standard measured value of the pressure reaches the pressure verification standard value, the PID controller (9) controls the pressure loading component (11) to close, and the air source (12) stops loading pressure onto the dual-redundant pressure sensor (2). 2.

5. Dual-redundant pressure sensor (2) measures and verifies the pressure value and sends the two measurement signals to two sets of acquisition units (6); 2.6 The two sets of acquisition units (6) acquire two measurement signals respectively and send them to the data acquisition and processing unit (7). The data acquisition and processing unit (7) records the pressure calibration standard value and the corresponding measurement pressure values ​​of the two measurement channels. 2.7 Change the pressure calibration standard value set by the pressure controller (8) and send it to the PID controller (9). Repeat steps 2.2-2.6 to obtain at least 36 sets of pressure calibration standard values ​​and the corresponding measured pressure values ​​of the two measurement channels. 2.

8. The least squares method is used to fit at least 36 sets of pressure calibration standard values ​​and the corresponding measured pressure values ​​of the two measurement channels to obtain the sensitivity coefficients of the two measurement channels of the dual-redundant pressure sensor (2).

9. The attitude control engine chamber pressure redundancy measurement method according to claim 8, characterized in that: The pressure calibration standard value set by the pressure controller (8) is greater than or equal to the rated chamber pressure of the attitude control engine (1) to be measured, and is set in a three-pass, six-gear rise and return method. The "three-round six-gear up-and-down" process refers to setting six gears sequentially from low to high and then from high to low, repeating this process three times.

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