Pressure scanning valve for reusable aircraft

Abstract

The utility model discloses a pressure scanning valve for a reusable aircraft, which is characterized in that a pressure measuring interface connected with an external pipeline is arranged at the top of an upper cover, a mounting plate is respectively connected and fixed with the upper cover and a bottom cover, a pressure sensor assembly, a main control circuit board and a temperature monitoring sensor are all arranged on the mounting plate, an acceleration sensor is arranged on the bottom cover, and the main control circuit board is arranged on the bottom cover. The electric connector is arranged outside the bottom cover, the pressure sensor assembly, the monitoring temperature sensor, the acceleration sensor and the electric connector are all connected with the main control circuit board through cables, the pipeline switching sliding block is arranged between the upper cover and the mounting plate, the bottom of the bottom cover is connected with the driving assembly, and the output end of the driving assembly is connected to the pipeline switching sliding block. The pipeline switching slide block is driven to rotate; the position detection circuit board is arranged on the pipeline switching sliding block and provided with a contact in contact with the main control circuit board. The device has the advantages of being convenient to disassemble and assemble, wide in working temperature range, large in pressure measuring range, high in stability and the like, and supports on-line calibration and autonomous health state detection and evaluation.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft pressure measurement, in particular to a pressure scanning valve used for a reusable aircraft. Background Art

[0002] Reusable vehicles (spacecraft, launch vehicles, strategic drones, etc.) are one of the key development directions for future aerospace exploration. Countries are vigorously developing new types of reusable aerospace vehicles. Reusable vehicles must be reused frequently, densely, and efficiently, significantly improving space transportation capabilities and effectively reducing costs. These vehicles possess significant military and civilian value.

[0003] After completing a single flight mission, a reusable aircraft returns to perform necessary equipment maintenance and testing before it can resume its next mission. Therefore, minimizing the time between flights for equipment maintenance and testing is crucial to enabling reusable aircraft to perform missions at a high frequency, high density, and high efficiency.

[0004] At the same time, the pressure parameters of each component in the aircraft are key parameters in the aircraft, and the accurate and reliable measurement of pressure parameters plays a vital role in the success or failure of the aircraft's flight mission. The pressure parameter measurement of traditional aircraft is usually achieved by using multiple independently installed pressure sensors, which have problems such as difficulty in supporting online calibration, the need for disassembly for detection and calibration, high time and cost for detection and maintenance, and poor accessibility for maintenance. Therefore, the method of measuring pressure using independently installed pressure sensors can no longer adapt well to the application requirements of reusable aircraft. The pressure scanning valve has the function of multi-channel pressure parameter measurement, and some pressure scanning valves also have the function of "calibration / blowing", which can support "online detection" of the function and performance of the pressure sensor, and better meet the use requirements of reusable aircraft for its equipment components. However, in the existing technology, there are still many problems to be solved in order to better apply the pressure scanning valve to reusable aircraft, mainly including:

[0005] (1) Most existing pressure scanning valves have a narrow operating temperature range, especially those with "calibration / blowing" functions, which generally have an operating temperature range of -20℃ to 50℃. If they are used in a flight environment with an operating temperature range of -55℃ to 125℃ or even wider, auxiliary measures must be taken at the cost of increased volume and weight.

[0006] (2) The maximum pressure of the existing pressure scanning valve with "calibration / blowing" function is relatively low, usually ≤ 6 MPa, which is difficult to meet the measurement requirements of high-pressure (up to 30 MPa or even higher) scenarios in reusable aircraft components such as engines and fuel supply.

[0007] (3) The valve core of the switching valve body is prone to air leakage, which makes the product sealing unable to be guaranteed and seriously affects the product's working performance.

[0008] (4) Without a complete autonomous health detection and diagnosis design, it is difficult to provide decision-making recommendations for aircraft reuse repair, maintenance, life and reliability prediction, and flight release.

[0009] (5) The environmental test conditions such as shock, vibration, and temperature of reusable aircraft are more severe. Compared with traditional designs, the design constraints of pressure scanning valves such as long-term stable working performance and online health assessment functions are more prominent.

[0010] Therefore, how to realize a pressure scanning valve that takes into account high-pressure measurement scenario applications, supports a wide operating temperature range, has good long-term stable sealing performance, and has a complete autonomous health detection and diagnostic design, so as to better provide reliable and powerful support for the realization and application of reusable aircraft, is one of the important issues that urgently need to be solved in this technical field. Utility Model Content

[0011] The purpose of this utility model is to provide a pressure scanning valve for reusable aircraft. The goal is to achieve a pressure scanning valve that can be used in high-pressure measurement scenarios, supports a wide operating temperature range, has excellent long-term stable sealing performance, and has a complete autonomous health detection and diagnosis design. This meets the requirements of reusable aircraft for equipment maintenance and repair time, long-term stable operation, and autonomous health detection and diagnosis, thereby shortening the inspection time of reusable aircraft and reducing the inspection difficulty and cost.

[0012] In order to achieve the above purpose, the technical solution adopted by the utility model is:

[0013] A pressure scanning valve for a reusable aircraft, comprising: an upper cover, a pipeline switching slider, a mounting plate, a pressure sensor assembly, a bottom cover, a main control circuit board, a monitoring temperature sensor, an acceleration sensor, a position detection circuit board, an electrical connector, and a drive assembly;

[0014] The top of the upper cover is provided with a plurality of pressure measuring interfaces for connecting external pipelines. The top of the mounting plate is fixedly connected to the upper cover. The pressure sensor assembly is mounted on the mounting plate and sealed by a seal. The pipeline switching slider is arranged between the upper cover and the mounting plate. The pipeline switching slider is provided with a plurality of groups of pressure measuring pipelines. The pressure measuring pipelines are used to connect the pressure measuring interfaces with the pressure sensor assembly to realize the measurement function.

[0015] The bottom of the mounting plate is fixedly connected to the bottom cover, the bottom of the bottom cover is connected to the driving assembly, and the output end of the driving assembly passes through the bottom cover and the mounting plate, and is connected to the pipeline switching slider to drive the pipeline switching slider to rotate to switch the detection pipeline;

[0016] The main control circuit board and the monitoring temperature sensor are both mounted on the mounting plate, the acceleration sensor is mounted on the bottom cover, the electrical connector is arranged on the outside of the bottom cover, the pressure sensor assembly, the monitoring temperature sensor, the acceleration sensor and the electrical connector are all connected to the main control circuit board through cables; the position detection circuit board is mounted on the pipeline switching slider, and contacts are provided on the position detection circuit board, and the contacts are in contact with the main control circuit board.

[0017] As a further improvement of the present invention, the drive assembly includes a bulkhead, a transmission shaft and a reduction motor; the bottom of the bulkhead is connected to the reduction motor, the top of the bulkhead is connected to the bottom cover, one end of the transmission shaft is connected to the output end of the reduction motor, and the other end of the transmission shaft passes through the bulkhead, the bottom cover and the mounting plate in sequence and is connected to the pipeline switching slider; under the drive of the reduction motor, the transmission shaft drives the pipeline switching slider to rotate.

[0018] As a further improvement of the present invention, an outer ring and an inner ring are provided on the top of the upper cover; multiple pressure measuring interfaces are evenly distributed on the outer ring, and a blow-off interface and a calibration interface are provided on the inner ring; a blow-off pipeline and a calibration pipeline are also provided in the pipeline switching slider, the blow-off pipeline is used to connect the pressure measuring interface and the blow-off interface, and the calibration pipeline is used to connect the calibration interface and the pressure sensor assembly; the reduction motor drives the pipeline switching slider to rotate to realize pipeline switching.

[0019] As a further improvement of the present invention, a first concave cavity is provided at the bottom of the upper cover, a first center hole is provided in the center of the first concave cavity, and an arc-shaped limiting groove is provided on the side of the concave cavity; a first flange and a second flange are also provided at the top of the upper cover, the first flange is used to be connected and fixed to the external structure, and the second flange is used to be connected and fixed to the mounting plate.

[0020] As a further improvement of the present invention, the top surface of the pipeline switching slider is provided with a front center axis, which is used to position in the first concave cavity of the upper cover and is connected to the first center hole; the bottom surface of the pipeline switching slider is provided with a rear center axis, which is used to install a position detection circuit board and connect the transmission shaft; the side of the pipeline switching slider is provided with a limit boss, and the limit boss matches the arc-shaped limit groove.

[0021] As a further improvement of the present invention, a hexagonal blind hole is provided inside the rear center shaft, a first threaded boss is provided at the tail of the rear center shaft, and the position detection circuit board is locked on the first threaded boss by a locking nut; a hexagonal column is provided at the head of the transmission shaft, and a fifth flange is provided at the tail of the transmission shaft, the hexagonal column matches the hexagonal blind hole, and the fifth flange is used to connect the reduction motor.

[0022] As a further improvement of the present invention, a second center hole is provided in the middle of the mounting plate, and the second center hole is used to install the rear center shaft; a plurality of first threaded holes and a plurality of third threaded holes are arranged in a ring on the bottom surface of the mounting plate, and the third threaded holes are located inside the first threaded holes; a pipeline is provided on the bottom surface of the first threaded hole to lead to the top surface of the mounting plate; and the third threaded hole is used to fix the main control circuit board;

[0023] The outer periphery of the mounting plate is uniformly distributed with a plurality of second threaded holes for fixing the upper cover and the bottom cover;

[0024] On the bottom surface of the mounting plate, a plurality of first mounting holes are evenly distributed around the second central hole, and a plurality of fourth threaded holes are evenly distributed around the first mounting hole for mounting a monitoring temperature sensor.

[0025] As a further improvement of the present invention, a second cavity is provided in the bottom cover, and a first through hole and a second through hole are provided in the second cavity. The second through hole is used to install the rear center shaft, and the first through hole is used to pass the external cable of the main control circuit board. A second threaded boss is also provided in the second cavity for installing the acceleration sensor.

[0026] The bottom surface of the bottom cover is provided with a first flange hole, which is locked with the second threaded hole of the mounting plate through a fastener, and the top surface of the bottom cover is provided with a fifth threaded hole for mounting the partition frame.

[0027] As a further improvement of the present invention, the bulkhead is provided with a third flange and a fourth flange, the third flange is used to be connected to the fifth threaded hole, and the fourth flange is used to be connected to the reduction motor; the side of the bulkhead is provided with a through hole for arranging cables to realize the connection between the electrical connector and the main control circuit board.

[0028] As a further improvement of the present invention, the main control circuit board is composed of n pressure signal conditioning circuit modules, m temperature signal conditioning circuit modules, a multiplexer A1 module, a multiplexer A2 module, a multiplexer A3 module, an A / D analog-to-digital conversion circuit module, a high-performance microprocessor module, a power conversion circuit module, a communication interface circuit module, a Flash / RAM Memory module, a position detection circuit module and a reduction motor control drive circuit module; the circuit modules are connected through the electronic circuits of the circuit board.

[0029] Compared with the prior art, the advantages of the present invention are:

[0030] The utility model relates to a pressure scanning valve for a reusable aircraft, and the main structure of the pressure scanning valve is composed of an upper cover, a mounting plate and a bottom cover connected in sequence. Furthermore, a plurality of pressure measuring interfaces for connecting to external pipelines are provided on the top of the upper cover, and a pressure measuring pipeline corresponding to the pressure measuring interface is provided in the pipeline switching slider. The pipeline switching slider is set between the upper cover and the mounting plate, and the pressure sensor assembly is mounted on the mounting plate. The connection between the pressure measuring interface and the pressure sensor assembly is realized by using the pipeline switching slider. At the same time, a driving component is also provided at the bottom of the bottom cover, and the driving component is connected to the pipeline switching slider. The driving component drives the pipeline switching slider to rotate, thereby realizing automatic switching of the detection pipeline. Furthermore, a main control circuit board and a monitoring temperature sensor are provided on the mounting plate, an acceleration sensor is provided on the bottom cover, and a pressure sensor is provided on the outside of the bottom cover. An electrical connector is set in the part, and the pressure sensor assembly, monitoring temperature sensor, acceleration sensor and electrical connector are all connected to the main control circuit board through cables, thereby realizing the corresponding detection function; by setting a position detection circuit board on the pipeline switching slider, the position detection circuit board contacts the main control circuit board through contacts, thereby realizing the working status of the electrical signal indication scanning valve. The utility model provides a pressure scanning valve that takes into account high-pressure measurement scenario applications, supports a wide operating temperature range (-55℃~125℃), has good long-term stable sealing performance, and has complete autonomous health detection and diagnosis design. It can well meet the requirements of reusable aircraft for short equipment maintenance time, long-term stable operation, and autonomous health detection and diagnosis, shortens the detection time of reusable aircraft, and reduces detection difficulty and detection cost. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the following briefly introduces the drawings required for use in the embodiments or descriptions of the prior art. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative labor.

[0032] Figure 1 This is a schematic diagram of the three-dimensional structure principle of a pressure scanning valve for a reusable aircraft in a specific embodiment of the present utility model;

[0033] Figure 2 Schematic diagram of the structural principle of the upper cover in a specific embodiment of the present invention; wherein Figure (a) is a main view and Figure (b) is a stereogram;

[0034] Figure 3Schematic diagram of the structural principle of the pipeline switching slider in a specific embodiment of the present utility model; wherein, Figure (a) is a main view, Figure (b) is a cross-sectional view taken along AA in Figure (a), and Figure (c) is a cross-sectional view taken along BB in Figure (a);

[0035] Figure 4 Schematic diagram of the structural principle of the mounting plate in a specific embodiment of the present invention; wherein, Figure (a) is a rear view, and Figure (b) is a front view;

[0036] Figure 5 This is a schematic diagram of the structural principle of the pressure sensor assembly in a specific embodiment of the present utility model;

[0037] Figure 6 This is a schematic diagram of the structural principle of the bottom cover in a specific embodiment of the present utility model; Figure (a) is a three-dimensional diagram, and Figure (b) is a main view;

[0038] Figure 7 This is a schematic diagram of the structural principle of the partition frame in a specific embodiment of the present utility model;

[0039] Figure 8 This is a schematic diagram of the structural principle of the transmission shaft in a specific embodiment of the present utility model;

[0040] Figure 9 This is a schematic diagram of the structural principle of the main control circuit board in a specific embodiment of the present utility model;

[0041] Figure 10 This is a schematic diagram of the structural principle of a temperature monitoring sensor in a specific embodiment of the present utility model;

[0042] Figure 11 This is a schematic diagram of the structural principle of the acceleration sensor in a specific embodiment of the present utility model;

[0043] Figure 12 This is a schematic diagram of the structural principle of the position detection circuit board in a specific embodiment of the present utility model;

[0044] Figure 13 This is a schematic diagram of the structural principle of a locking nut in a specific embodiment of the present utility model;

[0045] Figure 14 This is a cross-sectional view of the pressure scanning valve in the blow-off calibration state in a specific embodiment of the present utility model;

[0046] Figure 15 This is a cross-sectional view of the pressure scanning valve in the measurement state in a specific embodiment of the present utility model;

[0047] Figure 16 This is a cross-sectional view of the installation of a monitoring temperature sensor for a pressure scanning valve in a specific embodiment of the present utility model;

[0048] Figure 17This is a cross-sectional view of the installation of the acceleration sensor of the pressure scanning valve in a specific embodiment of the present utility model;

[0049] Figure 18 This is a cross-sectional view of the internal structure of the pressure scanning valve in a specific embodiment of the present utility model;

[0050] Figure 19 This is a diagram showing the realization of the pressure scanning valve measurement function in a specific embodiment of the present utility model;

[0051] Figure 20 This is a diagram showing the implementation of the pressure scanning valve calibration function in a specific embodiment of the present utility model;

[0052] Figure 21 This is a diagram showing the blow-off function of the pressure scanning valve in a specific embodiment of the present utility model;

[0053] Figure 22 This is a diagram of the electrical circuit composition of the pressure scanning valve in a specific embodiment of the present utility model;

[0054] Figure 23 This is a diagram showing the function switching of the pressure scanning valve in a specific embodiment of the present utility model;

[0055] Figure 24 This is a diagram illustrating the implementation of autonomous health detection and diagnosis of a pressure scanning valve in a specific embodiment of the present utility model.

[0056] Legend: 1. Upper cover; 1001. Pressure measuring interface; 1002. Blow-off interface; 1003. Calibration interface; 1004. First flange; 1005. Second flange; 1006. First center hole; 1007. First annular groove; 1008. First concave cavity; 1009. Arc-shaped limit groove; 1010. Connecting pipe; 1011. Outer ring; 1012. Inner ring; 2. Pipeline switching slider; 2001. Pressure measuring pipe; 2002 , blow-off pipeline; 2003, calibration pipeline; 2004, front center axis; 2005, rear center axis; 2006, first threaded boss; 2007, hexagonal blind hole; 2008, limit boss; 3, mounting plate; 3001, first threaded hole; 3002, pipeline; 3003, second threaded hole; 3004, third threaded hole; 3005, fourth threaded hole; 3006, first mounting hole; 3007, second center hole; 3008, second annular Groove; 4. Pressure sensor assembly; 4001. Threaded interface; 5. Bottom cover; 5001. Second concave cavity; 5002. First flange hole; 5003. Fifth threaded hole; 5004. First through hole; 5005. Second through hole; 5006. Second threaded boss; 6. Bulkhead; 6001. Third flange; 6002. Fourth flange; 6003. Through hole; 6004. Third center hole; 7. Drive shaft; 7001. Hexagonal prism; 7002 , fifth flange; 8. reduction motor; 9. seal; 10. main control circuit board; 101. second mounting hole; 102. fourth center hole; 11. monitoring temperature sensor; 1101. second flange hole; 12. acceleration sensor; 1201. third flange hole; 13. position detection circuit board; 1301. contact; 1302. fifth center hole; 14. locking nut; 1401. sixth threaded hole; 15. fastener; 16. electrical connector. DETAILED DESCRIPTION

[0057] The following describes the embodiments of the present invention in detail, examples of which are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. Figures 1 to 24 The described embodiments are exemplary and intended to be used to explain the present invention, but should not be understood as limiting the present invention.

[0058] In the description of the present invention, it should be understood that the terms "length", "width", "up", "down", "left", "right", "front", "back", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.

[0059] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of the technical features being referred to. Thus, a feature specified as "first" or "second" may explicitly or implicitly include one or more of such features. In the description of this utility model, "plurality" means two or more, unless otherwise specifically defined.

[0060] In this utility model, unless otherwise expressly specified or limited, the terms "install," "connect," "connect," "fix," "mount," and the like should be understood in a broad sense. For example, they may refer to fixed connection, detachable connection, or integration; mechanical connection or electrical connection; direct connection or indirect connection through an intermediate medium; internal communication between two components or interaction between two components. Those skilled in the art will understand the specific meanings of the above terms in this utility model based on specific circumstances.

[0061] Example

[0062] like Figure 1 、 Figure 14 、 Figure 15 and Figure 18 As shown, the pressure scanning valve for reusable aircraft of the present invention includes: an upper cover 1, a pipeline switching slider 2, a mounting plate 3, a pressure sensor assembly 4, a bottom cover 5, a main control circuit board 10, a monitoring temperature sensor 11, an acceleration sensor 12, a position detection circuit board 13, an electrical connector 16 and a drive component.

[0063] In this embodiment, a plurality of pressure measuring interfaces 1001 for connecting external pipelines are provided on the top of the upper cover 1, the top of the mounting plate 3 is connected and fixed to the upper cover 1, the pressure sensor assembly 4 is installed on the mounting plate 3 and sealed by the seal 9, and the pipeline switching slider 2 is arranged between the upper cover 1 and the mounting plate 3. A plurality of groups of pressure measuring pipelines 2001 are provided in the pipeline switching slider 2. The pressure measuring pipelines 2001 are used to realize the connection between the pressure measuring interface 1001 and the pressure sensor assembly 4 to realize the measurement function.

[0064] The bottom of the mounting plate 3 is connected and fixed to the bottom cover 5, the bottom of the bottom cover 5 is connected to the driving assembly, and the output end of the driving assembly passes through the bottom cover 5 and the mounting plate 3, and is connected to the pipeline switching slider 2 to drive the pipeline switching slider 2 to rotate to realize the switching of the detection pipeline.

[0065] The main control circuit board 10 and the monitoring temperature sensor 11 are both mounted on the mounting plate 3, the acceleration sensor 12 is mounted on the bottom cover 5, and the electrical connector 16 is disposed on the outside of the bottom cover 5. The pressure sensor assembly 4, the monitoring temperature sensor 11, the acceleration sensor 12, and the electrical connector 16 are all connected to the main control circuit board 10 via cables. The position detection circuit board 13 is mounted on the pipeline switching slider 2. The position detection circuit board 13 is provided with contacts 1301, which contact the main control circuit board 10. In this embodiment, two contacts 1301 are provided on the position detection circuit board 13, and the main control circuit board 10 is provided with a circuit that is consistent with the rotation limit angle of the pipeline switching slider 2. When the pipeline switching slider 2 is at the limit angle, the contacts 1301 on the position detection circuit board 13 connect the circuit on the main control circuit board 10, indicating the operating status of the scanning valve through an electrical signal.

[0066] The pressure scanning valve of this embodiment is fully equipped with autonomous health detection and diagnosis design, which can provide decision-making suggestions for aircraft reuse repair, maintenance, life and reliability prediction, and flight release.

[0067] like Figure 14 As shown, the drive assembly includes a bulkhead 6, a drive shaft 7, and a reduction motor 8. The bottom of the bulkhead 6 is connected to the reduction motor 8, and the top of the bulkhead 6 is connected to the bottom cover 5. One end of the drive shaft 7 is connected to the output of the reduction motor 8. The other end of the drive shaft 7 passes through the bulkhead 6, bottom cover 5, and mounting plate 3 in sequence before connecting to the pipeline switching slider 2. Driven by the reduction motor 8, the drive shaft 7 drives the pipeline switching slider 2 to rotate.

[0068] like Figure 2 As shown, the top of the upper cover 1 is provided with an outer ring 1011 and an inner ring 1012. Multiple pressure measuring interfaces 1001 are evenly distributed on the outer ring 1011, and a blow-off interface 1002 and a calibration interface 1003 are provided on the inner ring 1012. Connecting pipes 1010 are provided in the pressure measuring interface 1001, the blow-off interface 1002 and the calibration interface 1003. Figure 3 As shown, the pipeline switching slider 2 is further provided with a purge pipeline 2002 and a calibration pipeline 2003. The purge pipeline 2002 is connected to the pressure measuring interface 1001 and the purge interface 1002 via corresponding connecting pipelines 1010, and the calibration pipeline 2003 is connected to the calibration interface 1003 and the pressure sensor assembly 4 via corresponding connecting pipelines 1010. The purge pipeline 2002 can connect the purge interface 1002 in parallel with each pressure measuring interface 1001 to achieve a purge function, and the calibration group pipeline 2003 can connect the calibration interface 1003 in parallel with each pressure sensor pipeline in the pressure sensor assembly 4 to achieve a unified calibration function.

[0069] like Figure 2As shown, the bottom of the upper cover 1 is provided with a first concave cavity 1008, the center of which is provided with a first central hole 1006, and the side of the concave cavity 1008 is provided with an arc-shaped limiting groove 1009. The pipe outlet in the concave cavity 1008 is provided with a first annular groove 1007 for mounting the seal 9. The top of the upper cover 1 is also provided with a first flange 1004 and a second flange 1005. The first flange 1004 is used for connecting and fixing to the external structure, and the second flange 1005 is used for connecting and fixing to the mounting plate 3.

[0070] like Figure 3 As shown, the top surface of the pipeline switching slider 2 is provided with a front central axis 2004, which is used to position itself within the first concave cavity 1008 of the upper cover 1 and connects to the first center hole 1006. The bottom surface of the pipeline switching slider 2 is provided with a rear central axis 2005, which is used to mount the position detection circuit board 13 and connect to the transmission shaft 7. The reduction motor 8 drives the pipeline switching slider 2 to rotate left and right to switch pipelines. The side of the pipeline switching slider 2 is provided with a limiting boss 2008, which matches the arc-shaped limiting groove 1009 to limit the rotation angle of the pipeline switching slider 2.

[0071] like Figure 3 As shown, a hexagonal blind hole 2007 is provided inside the rear middle shaft 2005, and a first threaded boss 2006 is provided at the tail of the rear middle shaft 2005. The position detection circuit board 13 is locked on the first threaded boss 2006 by a locking nut 14. Figure 12 and Figure 13 As shown, a sixth threaded hole 1401 is provided in the locking nut 14, a fifth center hole 1302 is provided on the position detection circuit board 13, the fifth center hole 1302 is passed through the tail of the rear center axis 2005, and the sixth threaded hole 1401 is threadedly connected to the first threaded boss 2006 to realize locking the position detection circuit board 13 at the tail of the rear center axis 2005.

[0072] like Figure 8 As shown, a hexagonal column 7001 is provided at the head of the transmission shaft 7 , and a fifth flange 7002 is provided at the tail of the transmission shaft 7 . The hexagonal column 7001 matches the hexagonal blind hole 2007 , and the fifth flange 7002 is used to connect the reduction motor 8 .

[0073] like Figure 4 As shown, a second center hole 3007 is provided in the middle of the mounting plate 3, and the second center hole 3007 is used to install the rear center shaft 2005. The bottom surface of the mounting plate 3 is annularly arranged with multiple first threaded holes 3001 and multiple third threaded holes 3004, and the third threaded holes 3004 are located inside the first threaded holes 3001; the bottom surface of the first threaded holes 3001 is provided with a pipe 3002 to lead to the top surface of the mounting plate 3, and the top surface of the pipe 3002 is provided with a second annular groove 3008 for installing the seal 9. The third threaded hole 3004 is used to fix the main control circuit board 10. Figure 9 As shown, a plurality of second mounting holes 101 are provided on the periphery of the main control circuit board 10, and a fourth center hole 102 is provided in the middle of the main control circuit board 10. The fourth center hole 102 is used to pass through the rear center axis 2005, and fasteners 15 are screwed into the second mounting holes 101 and the third threaded holes 3004 to achieve the connection and fixation of the main control circuit board 10 and the mounting plate 3.

[0074] In this embodiment, a plurality of second threaded holes 3003 are evenly distributed on the periphery of the mounting plate 3 for fixing the upper cover 1 and the bottom cover 5.

[0075] On the bottom surface of the mounting plate 3, four first mounting holes 3006 are evenly distributed around the second center hole 3007, and four fourth threaded holes 3005 are evenly distributed around the first mounting hole 3006 for mounting the monitoring temperature sensor 11. Figure 10 and Figure 16 As shown, four second flange holes 1101 are provided on the periphery of the monitoring temperature sensor 11, and the monitoring temperature sensor 11 is arranged in the first mounting hole 3006. The fastener 15 is screwed into the second flange hole 1101 and the fourth threaded hole 3005 to achieve the installation and fixation of the monitoring temperature sensor 11 to the bottom surface of the mounting plate 3.

[0076] like Figure 5 As shown, the pressure sensor assembly 4 is provided with a threaded interface 4001, which matches the first threaded hole 3001. The pressure sensor assembly 4 is installed and fixed to the mounting plate 3 by screwing a fastener 15 into the first threaded hole 3001 and the threaded interface 4001.

[0077] like Figure 6 As shown, the bottom cover 5 is provided with a second cavity 5001, and the second cavity 5001 is provided with a first through hole 5004 and a second through hole 5005. The second through hole 5005 is used to install the rear center shaft 2005, and the first through hole 5004 is used for the main control circuit board 10 to pass the external cable. The second cavity 5001 is also provided with a second threaded boss 5006 for installing the acceleration sensor 12. Figure 11 and Figure 17 As shown, four third flange holes 1201 are provided on the periphery of the acceleration sensor 12, and the third flange holes 1201 match the second threaded boss 5006. The acceleration sensor 12 is installed on the bottom cover 5 by screwing the fasteners 15 into the three flange holes 1201 and the second threaded boss 5006.

[0078] like Figure 6 As shown, a first flange hole 5002 is provided on the bottom surface of the bottom cover 5, and the first flange hole 5002 is locked with the second threaded hole 3003 of the mounting plate 3 through a fastener 15. A fifth threaded hole 5003 is provided on the top surface of the bottom cover 5 for mounting the bulkhead 6.

[0079] like Figure 7 As shown, the bulkhead 6 is provided with a third flange 6001 and a fourth flange 6002. The third flange 6001 is used to connect to the fifth threaded hole 5003, and the fourth flange 6002 is used to connect to the reduction motor 8. A through hole 6003 is provided on the side of the bulkhead 6 for routing cables and connecting the electrical connector 16 to the main control circuit board 10.

[0080] In this embodiment, when assembling the pressure scanning valve, first install each seal 9 into the first annular groove 1007 of the upper cover 1 and the second annular groove 3008 of the mounting plate 3, then insert the front center axis 2004 of the pipeline switching slider 2 into the first center hole 1006 of the upper cover 1, and align the limiting boss 2008 with the arc-shaped limiting groove 1009, then cover the mounting plate 3 in the first concave cavity 1008 of the upper cover 1, and lock the upper cover 1 and the mounting plate 3 with the fastener 15. When the pipeline switching slider 2 is at the limiting angle, the corresponding pipelines of the upper cover 1, the pipeline switching slider 2 and the mounting plate 3 are just docked, and the seam is located within the sealing range of the seal 9. The valve core of the switching valve body is reliable and not easy to leak, and the sealing of the product is reliably guaranteed to meet the measurement requirements of high-pressure scenarios of reusable aircraft.

[0081] In this embodiment, the mounting plate 3 can integrate n pressure sensor assemblies 4 to achieve n-channel pressure measurement, which can meet the pressure measurement requirements of components such as the engine, air intake, and fuel supply system of a reusable aircraft. The n pressure sensor assemblies 4 can be configured with a unified pressure measurement range or with different pressure measurement ranges. The pressure measurement range can include 0-1MPa, 0-4MPa, 0-8MPa, 0-15MPa, 0-20MPa, 0-30MPa, etc. as required. The pressure measurement type of the pressure sensor assembly 4 can be configured as absolute pressure or gauge pressure.

[0082] In this embodiment, the n pressure measuring interfaces 1001, purge interfaces 1002, and calibration interfaces 1003 in the upper cover 1 can adopt mechanical interfaces of uniform specifications, such as M10 ferrule interfaces, to facilitate the external mechanical connection and interchangeability of the pressure measuring channel, purge channel, and calibration channel.

[0083] In the pressure scanning valve for reusable aircraft of this embodiment, each pipeline is a circular pipe with a diameter of 1 mm, and the diameter is 1.2 mm to consider the processing error. If the maximum pressure measurement is 30 MPa, the locking force F1 required for sealing a single pipeline is approximately 3000×0.122×0.785≈33.912 N. Assuming that the eight pressure measurement interfaces 1001 reach the maximum pressure at the same time during operation, the required total minimum sealing locking force F2 is 8×F1=8×33.912≈271.296 N. Taking twice the margin, assume that the friction coefficient between the pipeline switching slider 2 and the seal 9 is u=0.3, and the distance L between the center of the pipeline and the center of the valve body is 0.03 m. At this time, the torque T1 is 2×F2×u×L=271.296×2×0.3×0.03≈4.88 Nm. Because pipeline switching slider 2 requires sealing on both its upper and lower surfaces, the maximum friction torque T2 is approximately 4.88 × 2 ≈ 9.76 Nm. The output torque of reduction motor 8 must be at least greater than the maximum friction torque T2 to properly drive pipeline switching slider 2, thereby switching the pressure scanning valve between the "measurement" and "calibration / purge" functions.

[0084] like Figure 19 As shown, when the pressure scanning valve for reusable aircraft of this embodiment realizes the "measurement" function, the pipeline switching slider 2 must be switched to the "measurement" position to ensure that the 1st to nth pressure measuring interfaces 1001 in the upper cover 1 are respectively connected to the 1st to nth pressure measuring pipelines 2001 and the 1st to nth pressure sensor assemblies 4 in the pipeline switching slider 2, thereby realizing the measurement of the pressure of the external pressure measuring points 1 to n.

[0085] like Figure 20 and Figure 21As shown, in this embodiment of the pressure scanning valve for a reusable aircraft, to implement the "calibration / purge" function, the pipeline switching slider 2 must be switched to the "calibration / purge" position. The main process for implementing the "calibration" function is as follows: the first through nth calibration pipelines 2003 in the pipeline switching slider 2 are interconnected, and the first through nth calibration pipelines 2003 in the pipeline switching slider 2 are connected to the first through nth pressure sensor assemblies 4, respectively, in a one-to-one correspondence. The calibration interface 1003 in the upper cover 1 is also connected to the first through nth calibration pipelines 2003 in the pipeline switching slider 2. Simultaneously, the calibration interface 1003 in the upper cover 1 is connected to an external standard pressure source. By inputting a standard pressure source with different pressure values, the pressure scanning valve's electrical circuitry, software algorithms, and other components coordinate to achieve pressure measurement calibration of the first through nth pressure sensor assemblies 4 in the pressure scanning valve. The main implementation process of the "blowing" function is as follows: the 1st to nth blow-off pipelines 2002 in the pipeline switching slider 2 are set to be interconnected, and the 1st to nth blow-off pipelines 2002 in the pipeline switching slider 2 are respectively connected to the 1st to nth pressure measuring interfaces 1001 in the upper cover 1 in a one-to-one correspondence, and the blow-off interface 1002 in the upper cover 1 is connected to the 1st to nth blow-off pipelines 2002 in the pipeline switching slider 2. At the same time, the blow-off interface 1002 in the upper cover 1 is connected to an external blow-off pressure source. A blow-off pressure source with a certain pressure value is input through the blow-off interface 1002 to blow off impurities or excess materials in the pipeline between the 1st to nth pressure measuring interfaces 1001 in the upper cover 1 and the external pressure measuring points 1 to n, thereby avoiding pipeline blockage and reducing the risk of abnormal pressure measurement function or deterioration of measurement accuracy of the pressure scanning valve, so that the pressure scanning valve can be better applied to reusable aircraft.

[0086] like Figure 22 As shown, the electrical circuit of the pressure scanning valve for reusable aircraft of this embodiment includes: n pressure sensor assemblies 4, a reduction motor 8, a main control circuit board 10, an acceleration sensor 12, m monitoring temperature sensors 11, a position detection circuit board 13, an electrical connector 16, and connecting cables between the above parts (not shown in the figure). The pressure sensor assembly 4 is electrically connected to the main control circuit board 10 through a connecting cable. The reduction motor 8 is electrically connected to the main control circuit board 10 through a connecting cable. The acceleration sensor 12 is electrically connected to the main control circuit board 10 through a connecting cable. The monitoring temperature sensor 11 is electrically connected to the main control circuit board 10 through a connecting cable. The electrical connector 16 is electrically connected to the main control circuit board 10 through a connecting cable. The position detection circuit board 13 is electrically connected to the main control circuit board 10 through a connecting cable.

[0087] like Figure 22As shown, the main control circuit board 10 performs functions such as signal conditioning, signal conversion, signal processing and calibration, data storage, position detection, reduction motor drive control, and power conversion. It comprises n pressure signal conditioning circuit modules, m temperature signal conditioning circuit modules, multiplexer A1 module, multiplexer A2 module, multiplexer A3 module, an A / D analog-to-digital conversion circuit module, a high-performance microprocessor module, a power conversion circuit module, a communication interface circuit module, a Flash / RAM memory module, a position detection circuit module, and a reduction motor control and drive circuit module. Each circuit module is connected via the circuit board's electronic circuitry.

[0088] The high-performance microprocessor module of the main control circuit board 10 realizes functions such as data processing, signal selection and switching control, reduction motor control, position detection and judgment of the pipeline switching slider, data reception and transmission, health detection and diagnosis.

[0089] The high-performance microprocessor in the main control circuit board 10 can adopt an embedded microprocessor chip with a main frequency of not less than 400MHz to support high-speed acquisition and conversion of multi-channel temperature and pressure data, fault diagnosis logic algorithm, health assessment algorithm, and other software modules. Fast operation.

[0090] The power conversion circuit module of the main control circuit board 10 converts the external power supply through the electrical connector 16 into the power supply required by other circuit modules.

[0091] The Flash / RAM Memory module of the main control circuit board 10 is used to store collected data such as temperature measurement, pressure measurement, acceleration sensor monitoring, monitored temperature, fault records, health status, etc. The Flash / RAM Memory module of the main control circuit board 10 can use SDRAM and Nand Flash data storage chips with large capacity and fast write speed.

[0092] The pressure signal conditioning circuit module of the main control circuit board 10 amplifies or converts the pressure signal output by the pressure sensor assembly 4 .

[0093] The temperature signal conditioning circuit module of the main control circuit board 10 amplifies or converts the temperature signal output by the pressure sensor assembly 4 .

[0094] The A / D conversion circuit module of the main control circuit board 10 performs analog-to-digital (A / D) conversion on the signals output by the multiplexer A1, multiplexer A2, and multiplexer A3 modules, converting them into corresponding digital quantities. These digital quantities are then transmitted to the high-performance microprocessor module of the main control circuit board 10 for processing and conversion, resulting in temperature measurement data, pressure measurement output, and temperature measurement data, pressure measurement data, and monitored temperature data. The A / D conversion circuit module of the main control circuit board 10 can utilize an A / D conversion chip and supporting circuitry with a resolution of at least 16 bits and a conversion rate of at least 1 MSPS to perform analog-to-digital conversion of multi-channel temperature measurement signals, pressure measurement signals, and monitored temperature signals.

[0095] The multi-channel signal selector A1 module of the main control circuit board 10 is output by the high-performance microprocessor of the main control circuit board 10 to select the switching control signal, select one or more signals amplified or converted by the pressure signal conditioning circuit and transmit them to the A / D analog-to-digital conversion circuit module of the main control circuit board 10 for analog-to-digital (A / D) conversion.

[0096] The multi-channel signal selector A2 module of the main control circuit board 10 is output by the high-performance microprocessor of the main control circuit board 10 to select the switching control signal, select one or more signals amplified or converted by the temperature signal conditioning circuit and transmit them to the A / D analog-to-digital conversion circuit module of the main control circuit board 10 for analog-to-digital (A / D) conversion.

[0097] The multi-channel signal selector A3 module of the main control circuit board 10 is output by the high-performance microprocessor of the main control circuit board 10 to select the switching control signal, and time-sharingly selects the output signals of the 1st to mth monitoring temperature sensor signals 12 to be transmitted to the A / D analog-to-digital conversion circuit module of the main control circuit board 10 for analog-to-digital (A / D) conversion.

[0098] The position detection circuit module of the main control circuit board 10 detects and processes the signal output by the position detection circuit board 13 to determine whether the current position of the pipeline switching slider is in the "measurement" state, the "calibration / blowing" state, or other states.

[0099] The reduction motor control driving circuit module of the main control circuit board 10 outputs a motor control signal from a high-performance microprocessor of the main control circuit board 10 to drive the reduction motor 8 to move.

[0100] The communication interface circuit module is controlled by a high-performance microprocessor of the main control circuit board 10 to implement a communication protocol interface such as RS422 or Ethernet to receive external data or output data.

[0101] In this embodiment, the pressure sensor assembly 4 includes a pressure sensitive core, a measuring temperature sensor, a sealing structure, etc., which realizes the pressure signal and temperature signal of the pressure measuring channel, and transmits them to the pressure signal conditioning circuit and temperature signal conditioning circuit of the main control circuit board 10 through the connecting cable for conditioning.

[0102] In this embodiment, the reduction motor 8 comprises a motor and a reduction mechanism, and is driven by the reduction motor control drive circuit module of the main control circuit board 10. Rotation of the reduction motor 8 drives the pipeline switching slider 2, which in turn rotates the position detection circuit board 13, thereby switching the pressure scanning valve between the "measurement" and "calibration / purge" functional states and detecting the current position of the pipeline switching slider 2.

[0103] In this embodiment, the accelerometer 12 is a triaxial accelerometer, used to measure the vibration and overload of the pressure scanning valve in six directions during operation in a reusable aircraft. Specifically, the triaxial accelerometer can have a range of at least ±30g and a response frequency of at least 20kHz. It communicates and exchanges data with the main control circuit board 10 via a connecting cable, monitoring the vibration and overload experienced by the pressure scanning valve. Vibration and overload information serves as one of the information sources for diagnosing and evaluating the health of the pressure scanning valve.

[0104] In this embodiment, a monitoring temperature sensor 11 is mounted on the sensor mounting plate 3 to monitor the temperature of the core components within the pressure scanning valve. Temperature sensors 11 can be configured with a measurement range of ≮ -50°C to +150°C. A maximum number of m sensors (m ≥ 2) can be configured to achieve redundant and reliable detection. The temperature value measured by the monitoring temperature sensor 11 serves as a source of information for diagnosing and assessing the health of the pressure scanning valve.

[0105] In this embodiment, the position detection circuit board 13 is used to detect the current position of the pipeline switching slider 2 to realize the detection of the "measurement" and "calibration / blowing" functional states of the pressure scanning valve.

[0106] In this embodiment, the electrical connector 16 is used for electrical interconnection and information exchange between the pressure scanning valve and external equipment, thereby realizing functions such as power supply, data input and output of the pressure scanning valve.

[0107] like Figure 23As shown, the pressure scanning valve for reusable aircraft of this embodiment implements the process of switching between the "measurement" and "calibration / blowing" functions: the main control circuit board 10 receives the "function switching" command through the electrical connector 16, and switches the function of the pipeline switching slider 2 according to the current position of the pipeline switching slider 2. Specifically, the main control circuit board 10 drives the reduction motor 8 to rotate through the connecting cable, and the reduction motor 8 drives the pipeline switching slider 2 to rotate through the transmission shaft 7. At the same time, the transmission shaft 7 drives the position detection circuit board 13 to rotate. The main control circuit board 10 determines whether the current position of the pipeline switching slider 2 has reached the position required by the "function switching" command by detecting the position of the position detection circuit board 13. If the current position of the pipeline switching slider 2 has reached the position required by the "function switching" command, the main control circuit board 10 controls the reduction motor 8 to stop rotating.

[0108] like Figure 24 As shown, the process for implementing autonomous health monitoring and diagnosis of a reusable aircraft pressure scanning valve in this embodiment is as follows: The information source for pressure scanning valve health diagnosis and assessment is primarily based on the acceleration sensor 12, the monitoring temperature sensor 11, and the pressure sensor assembly 4. The acceleration sensor 12 and the monitoring temperature sensor 11 provide vibration / shock and temperature monitoring information, which are the most common flight environment parameters that significantly impact the function, performance, and lifespan of the pressure scanning valve. The pressure and temperature measurement data output by the pressure sensor assembly 4, while serving as core measurement data, also serves as an information source for autonomous health monitoring and diagnosis of the pressure scanning valve. The data of the information sources for autonomous health detection and diagnosis of the above three pressure scanning valves are transmitted to the main control circuit board 10, and the high-performance microprocessor of the main control circuit board 10 performs real-time analysis and processing according to the set health detection and diagnosis algorithm, and combines historical fault information and abnormal data to evaluate the service life, health status, etc. of the pressure scanning valve, thereby realizing the autonomous health detection and diagnosis function of the pressure scanning valve, in order to achieve the rapid reuse of reusable aircraft, shorten the maintenance cycle of the reusable aircraft after its return, guide the reuse maintenance and release strategy, and evaluate the reliability of the reusable aircraft to complete the next mission.

[0109] The above description is merely a preferred embodiment of the present invention. The scope of protection of the present invention is not limited to the above embodiment. All technical solutions based on the concept of the present invention are within the scope of protection of the present invention. It should be noted that for those skilled in the art, certain improvements and modifications that do not depart from the principles of the present invention should also be considered within the scope of protection of the present invention.

Claims

1. A pressure scanning valve for a reusable aircraft, characterized in that: include: Upper cover (1), pipeline switching slider (2), mounting plate (3), pressure sensor assembly (4), bottom cover (5), main control circuit board (10), monitoring temperature sensor (11), acceleration sensor (12), position detection circuit board (13), electrical connector (16) and drive assembly; The top of the upper cover (1) is provided with a plurality of pressure measuring interfaces (1001) for connecting to external pipelines. The top of the mounting plate (3) is fixedly connected to the upper cover (1). The pressure sensor assembly (4) is mounted on the mounting plate (3) and sealed by a sealing member (9). The pipeline switching slider (2) is arranged between the upper cover (1) and the mounting plate (3). The pipeline switching slider (2) is provided with a plurality of groups of pressure measuring pipelines (2001). The pressure measuring pipelines (2001) are used to connect the pressure measuring interfaces (1001) with the pressure sensor assembly (4) to realize a measurement function. The bottom of the mounting plate (3) is connected and fixed to the bottom cover (5), the bottom of the bottom cover (5) is connected to the driving component, and the output end of the driving component passes through the bottom cover (5) and the interior of the mounting plate (3), and is connected to the pipeline switching slider (2) to drive the pipeline switching slider (2) to rotate and realize switching of the detection pipeline; The main control circuit board (10) and the monitoring temperature sensor (11) are both mounted on the mounting plate (3); the acceleration sensor (12) is mounted on the bottom cover (5); the electrical connector (16) is arranged outside the bottom cover (5); the pressure sensor assembly (4), the monitoring temperature sensor (11), the acceleration sensor (12) and the electrical connector (16) are all connected to the main control circuit board (10) via cables; the position detection circuit board (13) is mounted on the pipeline switching slider (2); a contact (1301) is provided on the position detection circuit board (13); and the contact (1301) is in contact with the main control circuit board (10).

2. The pressure scanning valve for a reusable aircraft according to claim 1, characterized in that: The driving assembly includes a bulkhead (6), a transmission shaft (7) and a reduction motor (8); the bottom of the bulkhead (6) is connected to the reduction motor (8), the top of the bulkhead (6) is connected to the bottom cover (5), one end of the transmission shaft (7) is connected to the output end of the reduction motor (8), and the other end of the transmission shaft (7) passes through the bulkhead (6), the bottom cover (5) and the mounting plate (3) in sequence and is connected to the pipeline switching slider (2); under the drive of the reduction motor (8), the transmission shaft (7) drives the pipeline switching slider (2) to rotate.

3. The pressure scanning valve for a reusable aircraft according to claim 2, characterized in that: The top of the upper cover (1) is provided with an outer ring (1011) and an inner ring (1012); a plurality of pressure measuring interfaces (1001) are evenly distributed on the outer ring (1011); a blow-off interface (1002) and a calibration interface (1003) are provided on the inner ring (1012); a blow-off pipeline (2002) and a calibration pipeline (2003) are also provided in the pipeline switching slider (2); the blow-off pipeline (2002) is used to connect the pressure measuring interface (1001) and the blow-off interface (1002); the calibration pipeline (2003) is used to connect the calibration interface (1003) and the pressure sensor assembly (4); the reduction motor (8) drives the pipeline switching slider (2) to rotate to realize pipeline switching.

4. The pressure scanning valve for a reusable aircraft according to claim 2, characterized in that: The bottom of the upper cover (1) is provided with a first concave cavity (1008), the center of the first concave cavity (1008) is provided with a first center hole (1006), and the side of the first concave cavity (1008) is provided with an arc-shaped limiting groove (1009); the top of the upper cover (1) is also provided with a first flange (1004) and a second flange (1005), the first flange (1004) is used for connecting and fixing with an external structure, and the second flange (1005) is used for connecting and fixing with a mounting plate (3).

5. The pressure scanning valve for a reusable aircraft according to claim 4, characterized in that: The top surface of the pipeline switching slider (2) is provided with a front center axis (2004), and the front center axis (2004) is used to be positioned in the first concave cavity (1008) of the upper cover (1) and connected to the first center hole (1006); the bottom surface of the pipeline switching slider (2) is provided with a rear center axis (2005), and the rear center axis (2005) is used to install a position detection circuit board (13) and connect the transmission shaft (7); the side of the pipeline switching slider (2) is provided with a limiting boss (2008), and the limiting boss (2008) matches the arc-shaped limiting groove (1009).

6. The pressure scanning valve for a reusable aircraft according to claim 5, characterized in that: The rear middle shaft (2005) is provided with a hexagonal blind hole (2007) inside, the rear middle shaft (2005) is provided with a first threaded boss (2006) at the tail end, and the position detection circuit board (13) is locked on the first threaded boss (2006) via a locking nut (14); the head of the transmission shaft (7) is provided with a hexagonal column (7001), the tail end of the transmission shaft (7) is provided with a fifth flange (7002), the hexagonal column (7001) matches the hexagonal blind hole (2007), and the fifth flange (7002) is used to connect to the reduction motor (8).

7. The pressure scanning valve for a reusable aircraft according to claim 6, characterized in that: A second center hole (3007) is provided in the middle of the mounting plate (3), and the second center hole (3007) is used to install the rear center shaft (2005); a plurality of first threaded holes (3001) and a plurality of third threaded holes (3004) are arranged in a circular manner on the bottom surface of the mounting plate (3), and the third threaded holes (3004) are located inside the first threaded holes (3001); a pipeline (3002) is provided on the bottom surface of the first threaded hole (3001) to lead to the top surface of the mounting plate (3); and the third threaded hole (3004) is used to fix the main control circuit board (10); The mounting plate (3) is evenly distributed with a plurality of second threaded holes (3003) on its periphery for fixing the upper cover (1) and the bottom cover (5); On the bottom surface of the mounting plate (3), a plurality of first mounting holes (3006) are evenly distributed around the second center hole (3007), and a plurality of fourth threaded holes (3005) are evenly distributed around the first mounting hole (3006) for mounting a monitoring temperature sensor (11).

8. The pressure scanning valve for a reusable aircraft according to claim 7, characterized in that: A second concave cavity (5001) is provided in the bottom cover (5), and a first through hole (5004) and a second through hole (5005) are provided in the second concave cavity (5001), the second through hole (5005) being used for installing the rear center shaft (2005), and the first through hole (5004) being used for passing an external cable of the main control circuit board (10); a second threaded boss (5006) is also provided in the second concave cavity (5001) for installing the acceleration sensor (12); The bottom surface of the bottom cover (5) is provided with a first flange hole (5002), and the first flange hole (5002) is locked with the second threaded hole (3003) of the mounting plate (3) through a fastener (15). The top surface of the bottom cover (5) is provided with a fifth threaded hole (5003) for installing the partition frame (6).

9. The pressure scanning valve for a reusable aircraft according to claim 8, characterized in that: The partition frame (6) is provided with a third flange (6001) and a fourth flange (6002), the third flange (6001) is used to be connected to the fifth threaded hole (5003), and the fourth flange (6002) is used to be connected to the reduction motor (8); the side of the partition frame (6) is provided with a through hole (6003) for arranging cables to realize the connection between the electrical connector (16) and the main control circuit board (10).

10. The pressure scanning valve for a reusable aircraft according to any one of claims 1 to 9, characterized in that: The main control circuit board (10) is composed of n pressure signal conditioning circuit modules, m temperature signal conditioning circuit modules, a multiplexer A1 module, a multiplexer A2 module, a multiplexer A3 module, an A / D analog-to-digital conversion circuit module, a high-performance microprocessor module, a power conversion circuit module, a communication interface circuit module, a Flash / RAM Memory module, a position detection circuit module, and a reduction motor control drive circuit module; each circuit module is connected via an electronic circuit of the circuit board.

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