Low-power wireless temperature and pressure sensor for aircraft

Abstract

This invention discloses a low-power wireless temperature and pressure sensor for aircraft, belonging to the field of aircraft temperature and pressure monitoring. It includes a temperature and pressure core, a control component, a battery component, and an antenna installed within the battery component. The outer shell of the temperature and pressure core connects to an interface corresponding to an aircraft wheel or landing gear buffer, used to sense the temperature and pressure data of the medium within the interface and transmit the data to the control component. The control component, installed inside the outer shell of the temperature and pressure core, processes the temperature and pressure data and transmits it to the battery component. The battery component, installed at the end of the temperature and pressure core furthest from the interface, supplies power to the control component and the temperature and pressure core, and transmits the processed temperature and pressure data to the antenna. The antenna transmits the temperature and pressure data radio frequency to a host computer. This invention enables temperature and pressure monitoring of aircraft wheels or landing gear buffers and wireless transmission to a host computer, solving the problems of existing wired pressure monitoring devices being complex to install, easily damaged, and unable to simultaneously monitor temperature information.

Description

Technical Field

[0001] This invention relates to the field of temperature and pressure monitoring for aircraft, specifically to a low-power wireless temperature and pressure sensor for aircraft, which is a miniaturized, low-power wireless temperature and pressure sensor. Background Technology

[0002] The tire pressure and temperature of aircraft wheels need to be monitored to ensure safe takeoff and landing. By obtaining real-time tire pressure and temperature information, onboard personnel can indirectly determine the wheel's usage or braking status and take timely countermeasures to ensure flight and landing safety. Current methods for real-time tire pressure monitoring involve installing tire pressure monitoring devices on the aircraft wheels and within the wheel axles. Onboard monitoring requires not only sensor connectors on the wheels to monitor internal air pressure, but also a rotary coupling device fixed within the wheel axle, connected via onboard cables to a controller in the equipment bay to transmit the signal data collected by the sensor connectors to a host computer. The entire device is large, occupies significant landing gear space, and the installation and disassembly process involves multiple components on the wheels and axles, with tangled wiring within the axles. Because existing onboard tire pressure monitoring devices utilize almost the maximum available space on the wheel axles, disassembly and maintenance are difficult, and repeated disassembly and assembly can cause varying degrees of damage to the components. Furthermore, existing tire pressure monitoring devices can only monitor tire pressure in real time, and currently do not have tire temperature information monitoring function, so they cannot obtain real-time temperature information to assist in judgment.

[0003] As a core component for absorbing aircraft impact loads, the landing gear buffer assembly requires regular maintenance to ensure safe takeoff and landing. Measuring the internal pressure of the landing gear buffer assembly is a crucial maintenance item to determine its inflation status and whether the pressure value meets regulations. Currently, the internal pressure of the buffer is measured on the ground using a pressure gauge, which is inconvenient as it requires the gauge to be installed. Simultaneously, it is also necessary to monitor the temperature of the landing gear buffer to further assess its operational status. However, current landing gear buffer temperature and pressure monitoring cannot transmit data to the aircraft in real time, thus failing to provide relevant reference data for the execution of actions during takeoff and landing.

[0004] Therefore, there is a need to provide a low-power wireless temperature and pressure sensor for aircraft to solve the above problems. Summary of the Invention

[0005] The technical problem to be solved:

[0006] To overcome the shortcomings of existing technologies, this invention provides a low-power wireless temperature and pressure sensor for aircraft. The sensor is installed on the aircraft wheel or landing gear buffer, measures temperature and pressure data through a temperature and pressure core, is powered by a battery, and transmits the collected temperature and pressure data to an onboard host computer via radio frequency communication. This solves the problems of existing wired pressure monitoring devices on aircraft being complex to install, easily damaged, and unable to monitor temperature information simultaneously.

[0007] The technical solution of this invention is: a low-power wireless temperature and pressure sensor for aircraft, comprising:

[0008] Thermo-pressure core, the outer shell of the thermo-pressure core is detachably connected to the interface corresponding to the aircraft wheel or landing gear buffer, and one end of the outer shell is provided with an air inlet, which is used to connect the inner cavity of the outer shell and the interface.

[0009] The control component is installed inside the housing of the thermo-pressure core and is electrically connected to the signal output terminal of the thermo-pressure core.

[0010] The battery assembly is fixed to the end of the thermo-pressure core that is away from the air inlet, and the battery assembly is electrically connected to the control assembly.

[0011] And an antenna, which is installed inside the battery pack, electrically connected to the battery pack, and wirelessly radio frequency connected to the host computer on the aircraft.

[0012] The temperature and pressure core is used to sense the temperature and pressure data of the medium entering the inner cavity of the temperature and pressure core through the air inlet in the installed interface, and transmits the temperature and pressure data to the control component; the control component is used to drive the temperature and pressure core to work, and transmits the temperature and pressure data collected by the temperature and pressure core to the battery component after processing; the battery component is used to power the control component and the temperature and pressure core, and transmits the temperature and pressure data processed by the control component to the antenna; the antenna is used to transmit the temperature and pressure data to the host computer in radio frequency mode.

[0013] Furthermore, the control component includes:

[0014] The control board is installed inside the housing of the temperature and pressure core. The control board is equipped with an AD conversion circuit, a signal amplification circuit, a filtering circuit, an RF transceiver circuit, and a power supply circuit. The AD conversion circuit is used to convert the temperature and pressure data signal collected by the temperature and pressure core into an analog-to-digital signal. The signal amplification circuit amplifies the converted signal. The filtering circuit is used to filter the amplified signal. The RF transceiver circuit is used to convert the filtered signal into an RF signal and send it to the battery pack. The power supply circuit is used to supply power.

[0015] Connectors, which are mounted on the control board, are used for electrical connection between the control board and the signal output terminals of the thermo-pressure core;

[0016] And multiple flexible sockets are evenly distributed around the control board at one end of the connector facing away from the control board. The flexible sockets are used for electrical connection between the control board and the battery assembly.

[0017] Furthermore, the wiring of the flexible socket is defined as power +, GND, and antenna radio frequency signal.

[0018] Furthermore, the battery assembly includes:

[0019] The main housing has an open end and a through hole at the other end. The open end of the main housing is connected and fixed to the end of the outer shell that is away from the air inlet. The end of the outer shell that is away from the air inlet is an open structure.

[0020] Antenna cover plate, installed at the through hole of the main housing, the antenna cover plate closes the through hole;

[0021] The battery, installed inside the main housing, is used to provide electrical power;

[0022] The circuit board is installed inside the main housing and is electrically connected to the battery. The antenna is installed inside the main housing and located inside the antenna cover. The circuit board is electrically connected to the antenna. The circuit board has multiple spring-loaded plugs, which are plugged into the spring sockets one by one for electrical connection between the circuit board and the control board.

[0023] Furthermore, the main housing has multiple axially protruding protrusions evenly distributed around its open end, and each protrusion has a countersunk hole; the outer ring of the outer housing has a groove corresponding to the protrusion, and the groove has a threaded hole corresponding to the countersunk hole; the protrusion and the groove are inserted into each other and fixedly connected by fasteners.

[0024] Furthermore, a limiting platform is provided between two adjacent slots, and multiple limiting platforms are located on the same plane. The plane where the limiting platforms are located is perpendicular to the outer shell axis of the temperature-pressed core.

[0025] Furthermore, a dustproof ring mounting groove is provided at the open end of the outer shell, and a dustproof ring is installed in the dustproof ring mounting groove. The dustproof ring is used to seal the gap at the joint between the outer shell and the main shell.

[0026] Furthermore, the main housing is made of stainless steel, and the antenna cover is made of polymer composite material.

[0027] Furthermore, the outer diameter wall of the housing near the air inlet is provided with external threads, which are used for threaded connection between the temperature and pressure sensor and the installed interface.

[0028] Furthermore, the sensor also includes a sealing ring, which is fitted into a sealing groove provided at the external thread end of the housing for airtight connection between the sensor and the interface.

[0029] Furthermore, a sealing groove is provided at the end of the external thread of the housing, and a sealing ring is installed in the sealing groove. The sealing ring is used for the gas seal between the temperature and pressure sensor and the installed interface.

[0030] The beneficial effects of this invention are as follows: This invention provides a low-power wireless temperature and pressure sensor for aircraft, installed on aircraft wheels or landing gear buffers, for monitoring temperature and pressure data of the wheels or buffers. This structure uses battery power and wireless communication to transmit the monitored temperature and pressure data signals, avoiding the need to lay power and communication cables inside the aircraft landing gear wheel axles. Furthermore, the structure of this invention has no structural interoperability with other onboard products; installation and disassembly only involve the sensor itself, making operation simple.

[0031] This invention, through the design of the outer shell structure of the thermo-pressure core, enables the sensor to be fixed at the interface corresponding to the aircraft wheel or landing gear buffer. The medium inside the tire or the medium inside the buffer can enter the outer shell of the thermo-pressure core, and the temperature and pressure of the medium can be monitored through the thermo-pressure sensitive element inside the shell.

[0032] This invention integrates a control component within the housing of a temperature and pressure core. The control component is electrically connected to both the temperature and pressure core and the battery assembly. It processes the temperature and pressure data collected by the core and transmits it to the battery assembly. Furthermore, the data is wirelessly transmitted to a host computer on the aircraft via an antenna within the battery assembly. This wireless transmission of temperature and pressure data avoids the problems of complex wiring, susceptibility to damage, and space constraints associated with existing wired pressure monitoring devices.

[0033] The antenna assembly of this invention incorporates a battery to power the control components and the thermo-pressure core, achieving self-powering for the sensor and eliminating the need for an external power source, thus simplifying complex power supply wiring. The battery is electrically connected to the circuit board, and its output voltage is regulated by a thermo-pressure circuit on the circuit board.

[0034] In the antenna assembly, the antenna and the circuit board are electrically connected. The spring-loaded plug installed on the circuit board is connected to the elastic socket on the control board. In addition to the power supply wiring, the wiring of the elastic socket and the spring-loaded plug also includes an antenna radio frequency signal line, which can transmit the temperature and pressure data processed by the control board to the antenna through the circuit board.

[0035] In this invention, the junction between the outer shell of the thermobaric core and the main shell of the antenna assembly employs multiple protrusions and slots for insertion and positioning. Multiple flexible sockets on the internal control board connect to multiple spring-loaded plugs in the antenna assembly, with each flexible socket having the same wiring definition. During assembly, alignment of any protrusion or slot ensures the correct connection between the flexible socket and the spring-loaded plug, guaranteeing electrical connectivity between the control board and the antenna assembly. Therefore, there are no directional restrictions when assembling the battery assembly and the thermobaric core, making assembly convenient.

[0036] The outer shell of the thermo-pressure core and the main shell of the antenna assembly are sealed and fixed together, and all functional components are set in the inner cavity of the two, making the sensor structure small and compact. Its total axial length does not exceed 40mm and its diameter is 30-32mm. When used in aircraft wheels, it can meet the requirements of threaded connection strength, dynamic balance and installation space at the wheel interface. Attached Figure Description

[0037] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0038] Figure 1 This is a schematic diagram of the external structure of a low-power wireless temperature and pressure sensor for aircraft according to the present invention.

[0039] Figure 2 This is an exploded view of the structure of a low-power wireless thermobaric sensor for aircraft according to the present invention.

[0040] Figure 3 This is a schematic diagram of the battery assembly structure in this invention;

[0041] Figure 4 This is a schematic diagram illustrating the working principle of the present invention.

[0042] In the diagram: 1. Temperature-pressure core, 11. Outer shell, 111. Groove, 112. Threaded hole, 113. Limiting platform, 114. Dustproof ring mounting groove, 115. External thread, 116. Sealing groove, 2. Control component, 21. Control board, 22. Connector, 23. Flexible socket, 24. Screw, 3. Battery assembly, 31. Main shell, 311. Protrusion, 312. Countersunk hole, 32. Antenna cover, 33. Antenna, 34. Battery, 35. Circuit board, 36. Spring-loaded plug, 4. Countersunk screw, 5. Dustproof ring, 6. Sealing ring. Detailed Implementation

[0043] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0044] An embodiment of the low-power wireless temperature and pressure sensor for aircraft according to the present invention, such as... Figure 1 , Figure 2As shown, the device includes a temperature and pressure core 1, a control component 2 installed within the temperature and pressure core 1, and a battery component 3 that interfaces with the temperature and pressure core 1. The sensor is battery-powered and transmits signals wirelessly, and is used for temperature and pressure monitoring of aircraft wheels and tires or landing gear buffers.

[0045] The temperature and pressure core 1 is installed at the interface corresponding to the aircraft wheel or landing gear buffer. It is used to sense the temperature and pressure data of the medium inside the wheel tire or the buffer and transmit it to the control component 2. The temperature and pressure core is an integrated component that combines a temperature sensor and a pressure sensor. It can simultaneously measure the temperature and pressure of the measured medium in real time and convert the measured physical quantity into an electrical signal output, realizing synchronous monitoring of temperature and pressure. The core of the temperature and pressure core is a temperature and pressure sensitive element, and the outer shell provides protection. In this embodiment, a large-range core 1 is selected according to the installation environment, with a maximum range of 45MPa. In this embodiment, the outer shell structure of the temperature and pressure core 1 is mainly improved to adapt it to the operating environment of this invention and to facilitate its installation with the control component 2 and the battery component 3.

[0046] The outer shell 11 of the thermo-pressure core 1 is an open-ended structure with an air inlet at the other end, encapsulating a thermo-pressure sensitive element. An external thread 115 is provided on the outer diameter wall of the outer shell 11 near the air inlet end, for detachable connection to a corresponding interface on an aircraft wheel (or landing gear buffer). The air inlet connects the medium inside the outer shell 11 to the interface, enabling temperature and pressure monitoring of the medium within the tire or buffer. To ensure threaded connection strength, the external thread 115 uses an MJ reinforced thread (metric aerospace-grade thread), and correspondingly, the thread on the interface of the connected wheel or landing gear buffer also uses an MJ reinforced thread. The outer diameter of the outer shell 11 near the open end is larger than the diameter at its external thread 115, forming a mounting step on the outer wall of the outer shell 11 for installation positioning of the thermo-pressure core 1. The distance from the air inlet to the mounting step is L1. A sealing groove 116 is provided at the tail end of the external thread 115 near the mounting step for installing a sealing ring 6. The sealing ring 6 enables an airtight seal between the thermostatic core 1 and the installation interface, preventing leakage of the internal medium of the tire or buffer. When the internal pressure of the tire or buffer exceeds 15MPa, the sealing ring 6 is replaced with a copper gasket. The open end of the outer shell 11 is docked and fixed to the battery assembly 3. An annular protrusion is provided on the outer diameter wall of the outer shell 11 near the open end. Three slots 111 are evenly distributed on the annular protrusion, dividing the annular protrusion into three arc rings, thus forming three limiting platforms 113. The three limiting platforms 113 are located on the same plane, and their plane is perpendicular to the axis of the outer shell 11 of the thermostatic core 1. Each slot 111 is provided with a threaded hole 112. The slots 111, limiting platforms 113, and threaded holes 112 are designed for the insertion and fixing of the main shell 31 in the battery assembly 3.

[0047] The control component 2 is installed inside the housing of the temperature and pressure core 1 and is electrically connected to the signal output terminal of the temperature and pressure core 1. The control component 2 is used to drive the temperature and pressure core 1 to work and to process the temperature and pressure data collected by the temperature and pressure core 1 and transmit it to the battery assembly 3.

[0048] Specifically, the control assembly 2 includes a control board 21, a connector 22 mounted on and electrically connected to the control board 21, and a resilient socket 23. The control board 21 is mounted inside the housing 11 of the thermo-pressure core by three screws 24. Three protruding support portions are provided inside the housing 11 to support the control board 21 so that it is mounted perpendicular to the axis of the housing 11. All three screws 24 pass through the control board 21 and are fixedly connected to the corresponding support portions.

[0049] The control board 21 is equipped with an AD conversion circuit, a signal amplification circuit, a filtering circuit, an RF transceiver circuit, and a power supply circuit. The AD conversion circuit converts the temperature and pressure data signals collected by the temperature and pressure core 1 from analog to digital. The signal amplification circuit amplifies the converted signal. The filtering circuit filters the amplified signal. The RF transceiver circuit receives and transmits RF signals; upon receiving a wake-up command from the host computer, it converts the filtered signal into an RF signal and sends it to the battery pack 3, which transmits and receives signals via the antenna 33 in the battery pack 3. The power supply circuit provides power, and its energy comes from the battery pack 3. Through the circuitry on the control board 21, it drives the connected temperature and pressure core 1. All components on the control board 21 and the temperature and pressure core 1 are powered by the battery pack 3, ensuring continuous power supply to the product. The control board 21 is the core of the product's control system. Using the Wireless Sensing SIP protocol, it listens for RF signals under software control and automatically enters sleep mode when idle to save energy. Based on product usage experience, the host computer can wake up multiple sensors within 20 seconds of the aircraft being powered on. Taking the host computer waking up up to 3 sensors in turn as an example, the sensors are switched from "deep sleep" to "working mode". The sensor sleep time is set to 6 seconds. According to the chip characteristics, the RF listening time is 8ms and the transmission time is 10ms. After 6 seconds, the RF communication module is opened to listen for 8ms, and then it returns to sleep state. This cycle is repeated continuously to reduce power consumption and extend battery life.

[0050] A connector 22 is installed on the side of the control board 21 facing the support. One end of the connector 22 is electrically connected to the control board 21, and the other end is electrically connected to the signal output terminal of the thermo-pressure core 1. The connector 22 realizes the electrical connection between the control board 21 and the thermo-pressure core 1. This allows the temperature and pressure data collected by the thermo-pressure core 1 to be processed in the control board 21. At the same time, the control board 21 can also drive the thermo-pressure core 1 to work.

[0051] Three flexible sockets 23 are installed on the open end of the control board 21 facing the housing 11. The three flexible sockets 23 are evenly distributed around the circumference of the control board 21 and are used for electrical connection between the control board 21 and the battery assembly 3. The wiring definitions of the three flexible sockets 23 are the same: power +, GND (ground), and antenna radio frequency signal, which enables the transmission of power supply and antenna signal.

[0052] The battery assembly 3 is fixedly connected to the open end of the outer casing 11. The battery assembly 3 is electrically connected to the control assembly 2 and wirelessly connected to the host computer on the aircraft via radio frequency communication. The battery assembly 3 is used to power the control assembly 2 and the temperature and pressure core 1, and to transmit the temperature and pressure data processed by the control assembly 2 to the host computer via radio frequency.

[0053] Specifically, such as Figure 3 As shown, the battery assembly 3 includes a main housing 31, an antenna cover 32, an antenna 33, a battery 34, a circuit board 35, and three spring-loaded connectors 36. The main housing 31 is made of stainless steel, with one end open and the other end having a through hole. The antenna cover 32 is installed at the through hole of the main housing 31 and closes the through hole. To ensure antenna transmission performance, the antenna cover 32 is made of non-metallic materials, such as the polymer composite material polyetheretherketone (PEEK), and must also meet environmental requirements, including withstanding rain, humidity, mold, salt spray, and acidic atmospheres. The antenna 33 is installed inside the antenna cover 32, within the main housing 31, and is used for wireless radio frequency transmission and reception between the antenna and the host computer. The antenna ensures that the host computer can receive wireless communication signals within a 2-meter range. The battery 34 is installed inside the main housing 31 and provides power to the entire sensor. The circuit board 35 is installed inside the main housing 35 and is electrically connected to the battery 34 and the antenna 33. The circuit board 35 has three spring-loaded connectors 36, which are connected one-to-one with three flexible sockets 23 on the control board 21, thus establishing an electrical connection between the circuit board 35 and the control board 21. The wiring definitions of the three spring-loaded connectors 36 are identical and match those of the flexible sockets 23. The circuit board 35 has a voltage regulator circuit that regulates the output voltage of the battery 34 before supplying it to the control board 21 through the spring-loaded connectors 36 and 23, and then to the temperature and pressure core 1 through the connector 22 on the control board 21. The temperature and pressure data processed by the control board 21 enters the circuit board 35 through the signal lines in the spring-loaded sockets 23 and 36, and then enters the antenna 33 through the corresponding circuits within the circuit board 35, transmitting the radio frequency signal to the host computer. The spring-loaded connector 36 is the tallest component on the circuit board 35. During installation, ensure that the interface of the spring-loaded connector 36 is exposed. Apply glue from the point where the spring-loaded connector 36 is close to the circuit board 35 to encapsulate the antenna 33, battery 34, circuit board 35 and housing 31 as a whole, ensuring the tightness of the connection and effectively coping with the high vibration and impact environment conditions on the aircraft.

[0054] The open ends of the main housing 31 and the outer housing 11 are fixed together. Three axially protruding protrusions 311 are evenly distributed around the circumference of the open end of the main housing 31, each protruding protrusion having a countersunk hole 312. The three protrusions 311 correspond to the three slots 111 on the open end of the outer housing 11. The open end of the main housing 31 is fitted over the open end of the outer housing 11, allowing the three protrusions 311 to insert into the three slots 111. The limiting platform 113 abuts against the end faces between two adjacent protrusions 311 of the main housing 31, forming an axial limit on the main housing 31. After the protrusions 311 and slots 111 are in place, the countersunk holes 312 align with the threaded holes 112, and the main housing 31 and the outer housing 11 are fixed together by countersunk screws 4.

[0055] Since the wireless temperature and pressure sensor of this invention is used in high-pressure environments, such as the pressure on the buffer support reaching 20MPa or more, in addition to the interface between the temperature and pressure core 1 and the aircraft requiring reinforced threads, this invention also achieves anti-loosening by pre-reserving a fuse hole 313 on the main housing 31. The fuse hole 313 is located on the outer wall of the main housing 31, and the fuse hole 313 on the main housing 31 is fixed to the corresponding pre-reserved fuse hole on the aircraft using stainless steel wire.

[0056] To ensure the sealing of the joint between the main housing 31 and the outer housing 11 and to prevent moisture, water mist, dust, etc. from entering the sensor through the gap at the joint, in this embodiment, a dustproof ring mounting groove 114 is provided on the outer diameter wall of the open end of the outer housing 11. The dustproof ring 5 is installed in the dustproof ring mounting groove 114, and the gap at the joint between the outer housing 11 and the main housing 31 is sealed by the dustproof ring 5 to prevent external debris from entering.

[0057] like Figure 1 As shown, the sensor of this invention is installed on the wheel and landing gear buffer. When installed on the wheel, the product is subjected to centrifugal force as the wheel rotates. Considering issues such as the thread strength, dynamic balance, and installation space at the wheel connection, the product adopts a miniaturized design. Based on actual usage conditions, the dimensional reference values ​​are given in Table 1:

[0058] Table 1 Reference values ​​for the outer dimensions of the sensor of the present invention

[0059]

[0060] Specific working principle:

[0061] When using, such as Figure 4As shown, the battery's rated voltage output is 3.3V DC. Through the spring-loaded connector 36 on the circuit board 35, electrical energy is transmitted to the control board 21. The control board 21 and the temperature and pressure core 1 are electrically connected via connector 22, allowing the control board to transmit electrical energy to the temperature and pressure core 1 and drive it to operate. The temperature and pressure core 1 transmits the detected temperature and pressure signals to the control board 21 via connector 22. After AD conversion, amplification, and linear correction by the control board 21, the signals are sent to the antenna 33 via the radio frequency circuit on the control board 21. The signals are then transmitted from the non-metallic area on the top of the product (i.e., the antenna cover 32) to the host computer via the antenna 33.

[0062] When replacing the battery assembly, simply remove screw 4 to replace the entire battery assembly 3. The battery assembly 3 is non-directional; simply align the protrusion 311 with the slot 111. The three sets of flexible sockets 23 and spring-loaded plugs 36 on the circuit board can be matched arbitrarily. The dust seal 5 enhances the sealing at the connection between the battery assembly 3 and the thermo-pressure core 1, making product installation and disassembly convenient.

[0063] In summary, the low-power wireless temperature and pressure sensor for aircraft provided by this invention is a low-power wireless sensor capable of monitoring the temperature and pressure data of aircraft wheels, tires, and shock absorbers. This sensor is battery-powered and communicates via RF radio frequency. The product is threaded onto the wheel or shock absorber, making installation simple and facilitating rapid use and maintenance. Data can be directly uploaded to the aircraft for display. During routine maintenance of the wheels and landing gear, it is not necessary to disassemble the wireless temperature and pressure sensor.

[0064] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A low-power wireless temperature and pressure sensor for aircraft, characterized in that, include: Thermo-pressure core, the outer shell of the thermo-pressure core is detachably connected to the interface corresponding to the aircraft wheel or landing gear buffer, and one end of the outer shell is provided with an air inlet, which is used to connect the inner cavity of the outer shell and the interface. The control component is installed inside the housing of the thermo-pressure core and is electrically connected to the signal output terminal of the thermo-pressure core. The battery assembly is fixed to the end of the thermo-pressure core that is away from the air inlet, and the battery assembly is electrically connected to the control assembly. And an antenna, which is installed inside the battery pack, electrically connected to the battery pack, and wirelessly radio frequency connected to the host computer on the aircraft. The temperature and pressure core is used to sense the temperature and pressure data of the medium entering the inner cavity of the temperature and pressure core through the air inlet of the installed interface, and transmits the temperature and pressure data to the control component; the control component is used to drive the temperature and pressure core to work, and transmits the temperature and pressure data collected by the temperature and pressure core to the battery component after processing; the battery component is used to power the control component and the temperature and pressure core, and transmits the temperature and pressure data processed by the control component to the antenna; the antenna is used to transmit the temperature and pressure data to the host computer in radio frequency mode. The control component includes: The control board is installed inside the housing of the temperature and pressure core. The control board is equipped with an AD conversion circuit, a signal amplification circuit, a filtering circuit, an RF transceiver circuit, and a power supply circuit. The AD conversion circuit is used to convert the temperature and pressure data signal collected by the temperature and pressure core into an analog-to-digital signal. The signal amplification circuit amplifies the converted signal. The filtering circuit is used to filter the amplified signal. The RF transceiver circuit is used to convert the filtered signal into an RF signal and send it to the battery pack. The power supply circuit is used to supply power. Connectors, which are mounted on the control board, are used for electrical connection between the control board and the signal output terminals of the thermo-pressure core; And multiple flexible sockets, evenly distributed around the circumference of the control board at the back connector end, the flexible sockets are used for electrical connection between the control board and the battery assembly; The battery assembly includes: The main housing has an open end and a through hole at the other end. The open end of the main housing is connected and fixed to the end of the outer shell that is away from the air inlet. The end of the outer shell that is away from the air inlet is an open structure. Antenna cover plate, installed at the through hole of the main housing, the antenna cover plate closes the through hole; The battery, installed inside the main housing, is used to provide electrical power; The circuit board is installed inside the main housing and is electrically connected to the battery. The antenna is installed inside the main housing and located inside the antenna cover. The circuit board is electrically connected to the antenna. The circuit board has multiple spring-loaded plugs, which are plugged into the spring sockets one by one for electrical connection between the circuit board and the control board.

2. The low-power wireless temperature and pressure sensor for aircraft according to claim 1, characterized in that, The wiring of the flexible socket is defined as power +, GND, and antenna radio frequency signal.

3. The low-power wireless temperature and pressure sensor for aircraft according to claim 1, characterized in that, The main housing has multiple axially protruding protrusions evenly distributed around its open end, and each protrusion has a countersunk hole; the outer ring of the outer shell has a groove corresponding to the protrusion, and the groove has a threaded hole corresponding to the countersunk hole; the protrusion and the groove are inserted into each other and fixedly connected by fasteners.

4. The low-power wireless temperature and pressure sensor for aircraft according to claim 3, characterized in that, A limiting platform is provided between two adjacent slots. Multiple limiting platforms are located on the same plane, and the plane where the limiting platforms are located is perpendicular to the outer shell axis of the temperature-pressed core.

5. The low-power wireless temperature and pressure sensor for aircraft according to claim 1, characterized in that, The open end of the outer shell is provided with a dustproof ring mounting groove, in which a dustproof ring is installed. The dustproof ring is used to seal the gap at the joint between the outer shell and the main shell.

6. The low-power wireless temperature and pressure sensor for aircraft according to claim 1, characterized in that, The main housing is made of stainless steel, and the antenna cover is made of polymer composite material.

7. The low-power wireless temperature and pressure sensor for aircraft according to claim 1, characterized in that, The outer diameter wall of the housing near the air inlet is provided with external threads, which are used for threaded connection between the temperature and pressure sensor and the installed interface.

8. The low-power wireless temperature and pressure sensor for aircraft according to claim 7, characterized in that, A sealing groove is provided at the end of the external thread of the housing, and a sealing ring is installed in the sealing groove. The sealing ring is used for the gas seal between the temperature and pressure sensor and the installed interface.

Images