Multipath output pressure sensor device for aviation lifesaving

Abstract

The utility model discloses a multi-output pressure sensor device for aviation lifesaving, and relates to the field of sensors. The multipath output pressure sensor device for aviation lifesaving comprises a sensor accommodating box, a circuit board fixed in the sensor accommodating box, a total pressure pipe and a static pressure pipe which are connected to the outer wall of the sensor accommodating box, at least three pressure sensors and at least one temperature sensor, and the pressure sensors and the temperature sensor are electrically connected with the circuit board. The total pressure pipe and the static pressure pipe are provided with a total pressure connector and a static pressure connector which are connected with an airplane airspeed pipe respectively, the two pressure sensors are fixed in the total pressure pipe and the static pressure pipe respectively, and a plurality of air circulation holes communicated with the inside and the outside are formed in one side of the sensor containing box. The at least one pressure sensor and the at least one temperature sensor detect the pressure and the temperature in the sensor containing box respectively. The multipath output pressure sensor device for aviation lifesaving can ensure that the pressure sensor and the temperature sensor stably work in overload, vibration and impact environments.

Description

Technical Field

[0001] The present application relates to the field of sensors, and more particularly, to a multi-channel output pressure sensor device for aviation life-saving applications. Background Art

[0002] In the field of aviation life-saving, the program controller used in the ejection seat needs to convert the total static pressure value in the aircraft airspeed system and the static pressure value at the height where the man-seat system is located after ejection from the aircraft into electrical signals for calculation and processing. The pressure sensor needs to withstand the tests of mechanical environments such as vibration, shock, and acceleration. Existing sensor devices for aviation life-saving may have problems such as unstable output, drift of sensor linearity, and decline in electrical insulation under such complex environments.

[0003] Therefore, there is a need for a multi-channel output and high-stability, high-reliability output sensor device to meet the usage requirements. Summary of the Utility Model

[0004] The purpose of the present application is to provide a multi-channel output pressure sensor device for aviation life-saving, which can ensure the stable operation of the pressure sensor and the temperature sensor under overload, vibration, and shock environments.

[0005] The present application is implemented as follows:

[0006] The present application provides a multi-channel output pressure sensor device for aviation life-saving, which includes a sensor housing, a circuit board fixed inside the sensor housing, a total pressure pipe and a static pressure pipe connected to the outer wall of the sensor housing, at least three pressure sensors and at least one temperature sensor. The pressure sensors and the temperature sensor are electrically connected to the circuit board. The circuit board is connected with an electrical connector extending out of the sensor housing. The total pressure pipe and the static pressure pipe are respectively provided with a total pressure joint and a static pressure joint for connecting the aircraft airspeed pipe. Two pressure sensors are respectively fixed inside the total pressure pipe and the static pressure pipe to detect the pressure inside the total pressure pipe and the static pressure pipe. One side of the sensor housing is provided with a plurality of air circulation holes communicating inside and outside. At least one pressure sensor and the temperature sensor are respectively fixed on the sensor housing to detect the pressure and temperature inside the sensor housing.

[0007] In some alternative embodiments, the top surface of the sensor housing is provided with a top opening. The sensor housing is connected by bolts with a top cover for closing the top opening. A circular first sealing ring is provided between the top cover and the top of the sensor housing.

[0008] In some alternative embodiments, the top of the sensor housing is provided with a first card slot, and at least a part of the first sealing ring is clamped in the first card slot.

[0009] In some alternative embodiments, an end opening is provided on an end face of the sensor accommodation box. The sensor accommodation box is bolted with an end cover plate for closing the end opening, and an annular second sealing ring is provided between the end cover plate and the end of the sensor accommodation box.

[0010] In some alternative embodiments, a second clamping groove is provided on a side of the end cover plate facing the end of the sensor accommodation box, and the second sealing ring is clamped in the second clamping groove.

[0011] In some alternative embodiments, a third clamping groove is provided on the top of the end cover plate, and at least a part of the first sealing ring is clamped in the third clamping groove.

[0012] In some alternative embodiments, the total pressure pipe and the static pressure pipe are respectively connected with connecting seat plates. The two connecting seat plates are respectively bolted to one end face of the sensor accommodation box. The pressure sensor includes a pressure sleeve and a pressure plug cover connected to one end of the pressure sleeve. A pressure core body is provided in the pressure sleeve. The ends of the pressure sleeves of the two pressure sensors away from the corresponding pressure plug covers are respectively connected with the total pressure pipe and the static pressure pipe.

[0013] In some alternative embodiments, an annular seat plate gasket is provided between the connecting seat plate and the end face of the sensor accommodation box, and the connecting seat plate, the seat plate gasket and the sensor accommodation box are bolted together.

[0014] In some alternative embodiments, a sealing convex ring passing through the seat plate gasket is formed by the outer wall of the sensor accommodation box, and the outer wall of the sealing convex ring is in sealing fit with the inner wall of the seat plate gasket.

[0015] In some alternative embodiments, the circuit board is connected with an electrical connector extending out of the sensor accommodation box.

[0016] The beneficial effects of the present application are as follows: The multi-channel output pressure sensor device for aviation life-saving provided by the present application includes a sensor housing box, a circuit board fixed inside the sensor housing box, a total pressure pipe and a static pressure pipe connected to the outer wall of the sensor housing box, at least three pressure sensors and at least one temperature sensor. The pressure sensors and temperature sensors are electrically connected to the circuit board. The total pressure pipe and the static pressure pipe are respectively provided with a total pressure joint and a static pressure joint for connecting the aircraft pitot tube. Two pressure sensors are respectively fixed inside the total pressure pipe and the static pressure pipe to detect the pressures inside the total pressure pipe and the static pressure pipe. One side of the sensor housing box is provided with a plurality of air circulation holes communicating inside and outside. At least one pressure sensor and temperature sensor are respectively fixed on the sensor housing box to detect the pressure and temperature inside the sensor housing box. The multi-channel output pressure sensor device for aviation life-saving provided by the present application connects the aircraft pitot tube by arranging the total pressure pipe and the static pressure pipe on the outer wall of the sensor housing box, and obtains the aircraft dynamic pressure inside the total pressure pipe, the aircraft static pressure inside the static pressure pipe, the external pressure and the external temperature through the pressure sensors and temperature sensors arranged inside the sensor housing box, and transports them to the circuit board for output through the electrical connector, ensuring that the sensor device stably outputs the aircraft static and dynamic pressures under overload, vibration, and impact environments. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required for use in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of the present application, and thus should not be regarded as limiting the scope. For those of ordinary skill in the art, other related drawings can be obtained based on these drawings without creative efforts.

[0018] Figure 1 It is a schematic structural diagram of the multi-channel output pressure sensor device for aviation life-saving provided by the embodiment of the present application;

[0019] Figure 2 It is a partial structural schematic diagram of the multi-channel output pressure sensor device for aviation life-saving provided by the embodiment of the present application with the top cover removed;

[0020] Figure 3 It is an exploded structural schematic diagram of the multi-channel output pressure sensor device for aviation life-saving provided by the embodiment of the present application.

[0021] In the figure: 100, sensor accommodation box; 110, circuit board; 120, total pressure pipe; 130, static pressure pipe; 140, electrical connector; 150, pressure sensor; 151, pressure sleeve; 152, pressure plug; 153, pressure core; 160, temperature sensor; 170, total pressure joint; 180, static pressure joint; 190, top opening; 200, top cover plate; 210, first sealing ring; 220, first card slot; 230, end opening; 240, end cover plate; 250, second sealing ring; 260, second card slot; 270, connecting seat plate; 280, seat plate washer; 290, sealing convex ring; 300, air circulation hole; 310, third card slot; 320, connecting seat. Detailed implementation manners

[0022] To make the objectives, technical solutions, and advantages of the embodiments of this application clearer, the technical solutions in the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings in the embodiments of this application. Apparently, the described embodiments are some but not all of the embodiments of this application. Components of the embodiments of this application generally described and illustrated in the accompanying drawings here can be arranged and designed in various different configurations.

[0023] Therefore, the following detailed description of the embodiments of this application provided in the accompanying drawings is not intended to limit the scope of this application that is claimed, but merely represents selected embodiments of this application. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of this application without creative efforts fall within the scope of protection of this application.

[0024] It should be noted that like reference numerals and letters denote like items in the following drawings. Therefore, once an item is defined in one drawing, it does not need to be further defined and explained in subsequent drawings.

[0025] In the description of this application, it should be noted that the orientation or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings or the orientation or positional relationship in which the products of this application are customarily placed during use. This is only for the convenience of describing this application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as a limitation of this application. In addition, the terms "first", "second", "third", etc. are only used for descriptive distinction and should not be construed as indicating or implying relative importance.

[0026] In addition, terms such as "horizontal", "vertical", "hanging", etc. do not require the components to be absolutely horizontal or hanging, but can be slightly inclined. For example, "horizontal" only means that its direction is more horizontal relative to "vertical", and does not mean that the structure must be completely horizontal, but can be slightly inclined.

[0027] In the description of the present application, it should also be noted that unless otherwise clearly specified and limited, the terms "arranged", "installed", "connected", and "coupled" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the communication inside two components. For those of ordinary skill in the art, the specific meanings of the above terms in the present application can be understood according to specific situations.

[0028] In the present application, unless otherwise clearly specified and limited, the first feature being "on" or "under" the second feature may include the direct contact between the first and second features, or may include the situation where the first and second features are not in direct contact but in contact through other features between them. Moreover, the first feature being "above", "over" and "on top of" the second feature includes that the first feature is directly above and obliquely above the second feature, or simply means that the horizontal height of the first feature is higher than that of the second feature. The first feature being "under", "beneath" and "underneath" the second feature includes that the first feature is directly below and obliquely below the second feature, or simply means that the horizontal height of the first feature is lower than that of the second feature.

[0029] The features and performance of the multi-output pressure sensor device for aviation life-saving of the present application will be further described in detail below in conjunction with embodiments.

[0030] As Figure 1 , Figure 2 and Figure 3 shown, the embodiment of the present application provides a multi-output pressure sensor device for aviation life-saving, which includes a sensor housing 100, a top cover plate 200, an end cover plate 240, four pressure sensors 150 and a temperature sensor 160. A top opening 190 and an end opening 230 are respectively provided at the top and one end of the sensor housing 100. A circuit board 110 is fixedly connected inside the sensor housing 100 by bolts. The pressure sensors 150 and the temperature sensor 160 are respectively electrically connected to the circuit board 110. Two pressure sensors 150 are respectively used to detect the pressures in the total pressure pipe 120 and the static pressure pipe 130, and two pressure sensors 150 and the temperature sensor 160 are respectively used to detect the pressure and temperature inside the sensor housing 100. Six air circulation holes 300 for communicating inside and outside are respectively provided on both sides of the sensor housing 100.

[0031] One end of the outer wall of the sensor housing box 100 away from the end opening 230 is connected with a total pressure pipe 120 and a static pressure pipe 130. One ends of the total pressure pipe 120 and the static pressure pipe 130 are respectively provided with a total pressure joint 170 and a static pressure joint 180 for connecting the aircraft airspeed tube, and the other ends are respectively connected with connection seat plates 270 for closing the corresponding total pressure pipe 120 and static pressure pipe 130. The two connection seat plates 270 are respectively connected to one end face of the sensor housing box 100 by bolts. An annular seat plate gasket 280 is arranged between the connection seat plate 270 and the end face of the sensor housing box 100. The connection seat plate 270, the seat plate gasket 280 and the sensor housing box 100 are connected by bolts. A sealing convex ring 290 passing through the seat plate gasket 280 is formed by the protrusion of the outer wall of the sensor housing box 100. The outer wall of the sealing convex ring 290 is in sealing cooperation with the inner wall of the seat plate gasket 280. Pressure sensors 150 are respectively fixedly connected in the total pressure pipe 120 and the static pressure pipe 130. A connection seat 320 is formed by the protrusion of the inner bottom wall of the sensor housing box 100. The connection seat 320 is connected with two other pressure sensors 150 and a temperature sensor 160. Each pressure sensor 150 includes a pressure sleeve 151 and a pressure plug 152 connected to one end of the pressure sleeve 151. A pressure core 153 is arranged in the pressure sleeve 151. One ends of the pressure sleeves 151 of the two pressure sensors 150 away from the corresponding pressure plugs 152 are connected to the inner walls of the total pressure pipe 120 and the static pressure pipe 130 by threads. The two other pressure sensors 150 and the temperature sensor 160 are respectively connected to the connection seat 320 by threads.

[0032] The top cover plate 200 is connected to the top of the sensor housing box 100 by bolts to close the top opening 190. The end cover plate 240 is connected to one end of the sensor housing box 100 by bolts to close the end opening 230. The circuit board 110 is connected with an electrical connector 140 that penetrates through the top cover plate 200 and extends out of the sensor housing box 100. A through hole for the electrical connector 140 to extend out is arranged on the top cover plate 200. An annular first sealing ring 210 is arranged between the top cover plate 200 and the top of the sensor housing box 100. A C-shaped first clamping groove 220 is arranged on the top of the sensor housing box 100. A third clamping groove 310 is arranged on the top of the end cover plate 240. When the end cover plate 240 is connected to one end of the sensor housing box 100 by bolts to close the end opening 230, the first clamping groove 220 and the third clamping groove 310 cooperate to accommodate and clamp the first sealing ring 210. An annular second sealing ring 250 is arranged between the end cover plate 240 and the end of the sensor housing box 100. A second clamping groove 260 is arranged on the side of the end cover plate 240 facing the end of the sensor housing box 100. The second sealing ring 250 is clamped in the second clamping groove 260.

[0033] The multi-output pressure sensor device for aviation life-saving provided by the embodiment of the present application is connected with a total pressure pipe 120 and a static pressure pipe 130 on the outer wall of one end of the sensor accommodation box 100 away from the end opening 230. The total pressure pipe 120 and the static pressure pipe 130 are respectively provided with a total pressure joint 170 and a static pressure joint 180 for connecting the aircraft pitot tube. The dynamic pressure gas and static pressure gas in the aircraft pitot tube can be introduced into the total pressure pipe 120 and the static pressure pipe 130 through the total pressure joint 170 and the static pressure joint 180. Then, the pressure sensors 150 respectively fixed in the total pressure pipe 120 and the static pressure pipe 130 detect the pressures of the dynamic pressure gas and static pressure gas in the total pressure pipe 120 and the static pressure pipe 130 and output them through the circuit board 110. At the same time, the air circulation holes 300 arranged on the side of the sensor accommodation box 100 can introduce external air, and the other two pressure sensors 150 and the temperature sensor 160 arranged in the sensor accommodation box 100 detect the pressure and temperature in the sensor accommodation box 100 and output them through the circuit board 110, ensuring that the sensor device stably outputs the dynamic and static pressures of the aircraft, the ambient pressure and the temperature under the overload, vibration and impact environments.

[0034] The total pressure pipe 120 and the static pressure pipe 130 are respectively connected with connection seat plates 270 for closing the corresponding total pressure pipe 120 and static pressure pipe 130. The two connection seat plates 270 are respectively connected to one end face of the sensor accommodation box 100 by bolts. One end of the pressure sleeves 151 of the two pressure sensors 150 away from the corresponding pressure plugs 152 is threadedly connected to the total pressure pipe 120 and the static pressure pipe 130. The connection seat plates 270 can stably connect the total pressure pipe 120 and the static pressure pipe 130 with the pressure sleeves 151 of the two pressure sensors 150, improving the connection stability among the total pressure pipe 120, the static pressure pipe 130, the sensor accommodation box 100 and the two pressure sensors 150, ensuring that the pressure cores 153 in the pressure sleeves 151 of the two pressure sensors 150 accurately detect the pressures of the dynamic pressure gas and static pressure gas in the total pressure pipe 120 and the static pressure pipe 130. At the same time, an annular seat plate gasket 280 is arranged between the connection seat plate 270 and the end face of the sensor accommodation box 100, which can improve the anti-vibration performance of the connection seat plate 270, ensuring that the total pressure pipe 120 and the static pressure pipe 130 are stably connected to the sensor accommodation box 100 under the overload, vibration and impact environments. A sealing convex ring 290 passing through the seat plate gasket 280 is formed by the convexity on the outer wall of the sensor accommodation box 100. The outer wall of the sealing convex ring 290 is in sealing fit with the inner wall of the seat plate gasket 280, and the cooperation between the sealing convex ring 290 formed by the convexity on the outer wall of the sensor accommodation box 100 and the seat plate gasket 280 can improve the stability between the connection seat plate 270 and the sensor accommodation box 100.

[0035] Among them, a top opening 190 and an end opening 230 are respectively provided at the top and one end of the sensor accommodation box 100. The sensor accommodation box 100 is respectively bolted with a top cover plate 200 and an end cover plate 240 for closing the top opening 190 and the end opening 230, which can facilitate the staff to disassemble and assemble the top cover plate 200 and the end cover plate 240 and then maintain and replace the internal electronic components, improving the maintainability. At the same time, a first sealing ring 210 and a second sealing ring 250 are respectively provided between the top cover plate 200 and the end cover plate 240 and the sensor accommodation box 100, which can ensure the connection airtightness between the top cover plate 200 and the end cover plate 240 and the sensor accommodation box 100. Moreover, a first clamping groove 220 and a third clamping groove 310 for fitting and clamping the first sealing ring 210 are respectively provided at the top of the sensor accommodation box 100 and the end cover plate 240, and a second clamping groove 260 for clamping the second sealing ring 250 is provided at the end of the end cover plate 240, which can ensure the stable and reliable position of the first sealing ring 210 and the second sealing ring 250, improving the airtightness of the device and the service life of the first sealing ring 210 and the second sealing ring 250.

[0036] The embodiments described above are some, but not all, of the embodiments of the present application. The detailed description of the embodiments of the present application is not intended to limit the scope of the present application claimed, but merely represents selected embodiments of the present application. All other embodiments obtained by those of ordinary skill in the art based on the embodiments in the present application without creative efforts fall within the scope of protection of the present application.

Claims

1. A multi-output pressure sensor device for aviation life-saving, characterized in that: It includes a sensor accommodating box, a circuit board fixed in the sensor accommodating box, a total pressure pipe and a static pressure pipe connected to the outer wall of the sensor accommodating box, at least three pressure sensors and at least one temperature sensor, the pressure sensor and the temperature sensor are electrically connected to the circuit board, the total pressure pipe and the static pressure pipe are respectively provided with a total pressure joint and a static pressure joint for connecting to an aircraft airspeed tube, two pressure sensors are respectively fixed in the total pressure pipe and the static pressure pipe to detect the pressure in the total pressure pipe and the static pressure pipe, one side of the sensor accommodating box is provided with a plurality of air circulation holes connecting the inside and the outside, at least one pressure sensor and the temperature sensor are respectively fixed in the sensor accommodating box to detect the pressure and temperature in the sensor accommodating box.

2. The multi-output pressure sensor device for aviation lifesaving according to claim 1, characterized in that: The top surface of the sensor accommodating box is provided with a top opening, and the sensor accommodating box is connected with a top cover plate for closing the top opening by bolts, and an annular first sealing ring is provided between the top cover plate and the top of the sensor accommodating box.

3. The multi-output pressure sensor device for aviation lifesaving according to claim 2, characterized in that: A first card slot is provided on the top of the sensor housing box, and at least a portion of the first sealing ring is carded in the first card slot.

4. The multi-output pressure sensor device for aviation lifesaving according to claim 2, characterized in that: The end surface of the sensor accommodating box is provided with an end opening, and the sensor accommodating box is connected to an end cover plate for closing the end opening by bolts, and an annular second sealing ring is provided between the end cover plate and the end of the sensor accommodating box.

5. The multi-channel output pressure sensor device for aviation life-saving according to claim 4, characterized in that: A second clamping groove is provided on one side of the end cover plate facing the end of the sensor containing box, and the second sealing ring is clamped in the second clamping groove.

6. The multi-channel output pressure sensor device for aviation lifesaving according to claim 4, characterized in that: A third slot is provided on the top of the end cover plate, and at least a portion of the first sealing ring is clamped in the third slot.

7. The multi-output pressure sensor device for aviation lifesaving according to claim 1, characterized in that: The total pressure pipe and the static pressure pipe are respectively connected with connecting seat plates, and the two connecting seat plates are respectively connected to the end surface of one end of the sensor containing box by bolts. The pressure sensor includes a pressure sleeve and a pressure plugging cover connected to one end of the pressure sleeve. A pressure core is arranged in the pressure sleeve. The pressure sleeves of the two pressure sensors are respectively connected to the total pressure pipe and the static pressure pipe at one end away from the corresponding pressure plugging cover.

8. The multi-output pressure sensor device for aviation lifesaving according to claim 7, characterized in that: An annular seat plate gasket is provided between the connecting seat plate and the end surface of the sensor accommodating box, and the connecting seat plate, the seat plate gasket and the sensor accommodating box are connected by bolts.

9. The multi-output pressure sensor device for aviation lifesaving according to claim 8, characterized in that: The outer wall of the sensor housing box is raised to form a sealing convex ring that passes through the seat plate gasket, and the outer wall of the sealing convex ring is sealed and matched with the inner wall of the seat plate gasket.

10. The multi-output pressure sensor device for aviation life-saving according to claim 1, characterized in that: The circuit board is connected with an electrical connector extending out of the sensor housing box.

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