Integrated multifunctional oil supply pump with pressure self-sensing and mode self-adaption functions

Abstract

The invention belongs to the field of aviation fuel systems, and provides an integrated multifunctional fuel feed pump with pressure self-sensing and mode self-adaption functions, which comprises an upper pump assembly, a lower pump assembly, a motor controller assembly and a fuel discharge switch assembly, and the upper pump assembly and the lower pump assembly are respectively mounted on the upper side and the lower side of the motor controller assembly; the motor controller assembly provides a power source for the upper pump assembly and the lower pump assembly, the oil drainage switch assembly is installed on a flange plate at the bottom of the lower pump assembly, and the flange plate of the lower pump assembly is installed at the bottom of an oil tank. When the oil liquid completely submerges the oil supply pump, the upper pump assembly and the lower pump assembly simultaneously participate in pressurization work in a self-adaptive manner; when the airplane flies forward and the lower pump assembly is only submerged by oil in the oil tank, the lower pump assembly participates in pressurization work in a self-adaptive manner; when the airplane flies upside down and oil in the oil tank only submerges the upper pump assembly, the upper pump assembly participates in pressurization work in a self-adaptive mode. By means of the built-in pressure sensor, high-precision pressure self-sensing is achieved, and oil supply modes of forward flight and reverse flight of the aircraft are switched and adapted in a self-adaptive mode.

Description

Technical Field

[0001] This invention belongs to the field of aviation fuel systems and relates to a fuel supply pump, particularly an integrated multi-functional fuel supply pump with pressure self-sensing and mode self-adaptation functions. Background Technology

[0002] In aviation fuel delivery systems, the fuel pump is a core component ensuring the stable operation of the aircraft's power system, and its performance directly impacts flight safety. Traditional fuel pumps often employ pressure monitoring via external fuel lines connected to the pump outlet. This not only increases installation complexity but also makes it more difficult to ensure the reliability and sealing of the pipeline connections. During maintenance, the external pipeline is often constrained by the space of surrounding equipment, making the disassembly, repair, and calibration of the pressure sensor extremely inconvenient and significantly increasing manpower and time costs. Furthermore, due to the large distance between the sensor and the pump control system, signal transmission is prone to distortion and attenuation. Coupled with interference from factors such as pressure loss in the external pipeline and oil pulsation, the sensor's measurements cannot accurately reflect the actual pressure conditions at the pump outlet. Integrating the pressure sensor inside the pump body significantly shortens the pressure signal transmission path, effectively reducing pressure loss, signal interference, and attenuation, thereby obtaining more accurate and reliable pump outlet pressure data and providing strong support for the safe and stable operation of the fuel system.

[0003] Modern aircraft operate in a variety of complex and diverse attitudes and scenarios, leading to continuously increasing performance demands. Traditional single-end pump fuel supply systems, due to their limited functionality and poor adaptability, are no longer sufficient to meet the fuel supply needs of aircraft in various attitudes, including forward and inverted flight. This is particularly problematic in inverted flight, where there is a high risk of fuel supply interruption to the engines. Furthermore, to ensure flight safety, a continuous and stable supply of fuel to the engines must be maintained even if the fuel pump pressurization function fails. Additionally, in emergency troubleshooting and fuel pump maintenance scenarios, rapid fuel evacuation from the fuel tanks is necessary to improve aircraft supportability and maintenance convenience. Summary of the Invention

[0004] To address the aforementioned issues, this invention proposes an integrated multi-functional fuel pump with self-sensing pressure and self-adaptive mode functions. Based on a centrifugal pump structure, this fuel pump achieves accurate self-sensing pressure through a built-in pressure sensor, significantly improving measurement stability and reliability compared to external sensors. Simultaneously, it can intelligently identify aircraft flight attitude and adaptively switch fuel supply modes to suit various operating conditions, such as forward and backward flight. This highly integrates functions such as pressure sensing, adaptive mode switching, emergency fuel supply, and rapid fuel release, effectively meeting the fuel supply needs of aircraft in complex operating scenarios.

[0005] The technical solution of the present invention is as follows: An integrated multi-functional fuel pump with pressure self-sensing and mode self-adaptation functions includes an upper pump assembly, a lower pump assembly, a motor controller assembly, and a drain switch assembly. The upper and lower pump assemblies are respectively mounted on the upper and lower sides of the motor controller assembly, which provides power to both assemblies. The drain switch assembly is mounted on the flange at the bottom of the lower pump assembly, and the flange of the lower pump assembly is mounted on the bottom of the fuel tank. When the fuel completely submerges the fuel pump, both the upper and lower pump assemblies simultaneously and automatically participate in pressurization. When the aircraft is flying upright and the fuel in the tank only submerges the lower pump assembly, the lower pump assembly automatically participates in pressurization. When the aircraft is flying inverted and the fuel in the tank only submerges the upper pump assembly, the upper pump assembly automatically participates in pressurization.

[0006] Furthermore, the lower pump assembly is a centrifugal pump, and the outlet of the lower pump assembly is connected to a vertically arranged outlet pipe through a second one-way valve assembly. The outlet pipe extends downward through the bottom of the oil tank, and a medium-temperature pressure sensor is installed in the inner cavity of the outlet pipe directly opposite the outlet of the lower pump assembly.

[0007] Furthermore, the upper pump assembly is a centrifugal pump, and the outlet of the upper pump assembly is connected to the top of a vertically arranged outlet pipe. The outlet pipe is provided with a first check valve assembly below the medium temperature and pressure sensor, and a third check valve assembly is provided above the medium temperature and pressure sensor.

[0008] Furthermore, the temperature and pressure sensor signals are connected to the motor controller assembly, and the motor speed in the motor controller assembly is automatically adjusted according to the temperature and pressure.

[0009] Furthermore, the motor shaft of the motor controller assembly extends upward into the upper pump assembly, and fuel flows into the motor through the gap in the motor shaft to complete the cooling of the motor.

[0010] Furthermore, it also includes an emergency fuel supply unit, specifically: a one-way bypass valve is installed on the side of the outlet pipe. When the pump pressurization fails, the one-way bypass valve is interrupted by the engine's self-priming force, and the oil in the tank directly enters the outlet pipe through the one-way bypass valve and is output to the engine.

[0011] Furthermore, the oil drain switch assembly includes a lower oil drain port, a valve core assembly, a valve stem, a spring, a pin, and an oil drain valve core support. The lower oil inlet is mounted on the housing of the lower pump assembly. The valve core assembly, spring, oil drain valve core support, and pin are sequentially mounted on the valve stem. The pin passes through both the oil valve core support and the valve stem. Under the action of the spring force, the valve core assembly is pressed tightly against the internal contact surface of the lower oil inlet.

[0012] Furthermore, the lower oil inlet is equipped with a guide groove for a mating pin. When it is necessary to quickly drain the fuel in the tank, the pin is pushed upward along the guide groove of the lower oil inlet until it reaches the limit, which drives the valve core of the drain valve to compress the spring stroke and push the valve stem upward to disengage the valve core assembly from the internal contact surface of the lower oil inlet.

[0013] Technical effects of the present invention: This invention achieves high-precision self-sensing of pressure through a built-in pressure sensor, effectively avoiding external interference and significantly improving measurement stability and data reliability. Simultaneously, it can intelligently identify the aircraft's flight attitude and adaptively switch fuel supply modes to suit various operating conditions, including forward and inverted flight. This invention achieves a high degree of integration of functions such as pressure sensing, adaptive mode switching, emergency fuel supply, and rapid fuel release, comprehensively meeting the fuel supply needs of aircraft in diverse operating scenarios and significantly improving the safety and adaptability of the fuel system. Attached Figure Description

[0014] To more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings used in the embodiments of the present invention 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.

[0015] Figure 1 This is a schematic diagram of the overall structure of the present invention.

[0016] Figure 2 This is a diagram of the external structure of the pump body.

[0017] Figure 3 This is a cross-sectional view of the pump body's internal structure.

[0018] Figure 4 This is a schematic diagram of the guide groove for the oil drain switch at the lower oil inlet.

[0019] Figure 5 Schematic diagram of the mounting components for the lower housing flange.

[0020] Figure 6 This is a diagram showing the installation location of the pressure sensor and the motor controller.

[0021] Figure 7 This is a cross-sectional view of the pressure sensor installation.

[0022] Figure 8 This is a schematic diagram of the dual pumps operating when the aircraft is in flight.

[0023] Figure 9 This is a schematic diagram of the single-pump operation when the aircraft is flying inverted.

[0024] Among them, 1—upper pump assembly, 2—lower pump assembly, 3—motor controller assembly, and 4—oil drain switch assembly; 101—Upper mounting housing, 102—Upper oil inlet, 103—Upper filter assembly, 104—Upper impeller, 105—Upper inducer, 106—Third check valve assembly, 107A—Sealing ring, 107B—Sealing ring, 108—Connecting pipe; 201—Lower mounting housing, 202—Lower impeller, 203—Lower inducer, 204—Sealing ring, 205—Elastic retaining ring for orifice, 206—Outlet pipe, 207—First one-way valve assembly, 208—Second one-way valve assembly, 209—Sealing gasket, 210—Medium temperature pressure sensor, 211—Socket, 212—One-way bypass valve assembly, 213—Lower filter assembly, 214—Graphite bearing; 401—Lower oil inlet, 402—Hexagonal self-locking nut, 403—Valve core assembly, 404—Valve core washer, 405—Valve stem, 406—Spring, 407—Pin, 408—Drain valve core support. Detailed Implementation

[0025] This section describes embodiments of the present invention, used to explain and illustrate the technical solutions of the present invention. Unless otherwise specified, the embodiments and features described herein can be combined with each other.

[0026] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicating directions or positional relationships, are given in the accompanying drawings and are used only for the convenience of describing the invention and simplifying the description, and do not indicate or imply that the device or device referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the invention. Furthermore, the terms "first," "second," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implying the number of indicated technical features. Thus, features defined with "first," "second," etc., may explicitly or implicitly include more than one of those features. In the description of this invention, unless otherwise stated, "a plurality of" means two or more.

[0027] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to fixed connections, detachable connections, or integrated connections; they can refer to mechanical connections or point connections; they can refer to direct connections or indirect connections through an intermediate medium; and they can refer to the internal communication between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0028] Example 1: An integrated multi-functional fuel pump with pressure self-sensing and mode self-adaptation functions includes an upper pump assembly 1, a lower pump assembly 2, a motor controller assembly 3, and a drain switch assembly 4. The upper pump assembly 1 and the lower pump assembly 2 are respectively installed on the upper and lower sides of the motor controller assembly 3. The motor controller assembly 3 provides a power source for the upper pump assembly 1 and the lower pump assembly 2. The drain switch assembly 4 is installed on the flange at the bottom of the lower pump assembly 2, and the flange of the lower pump assembly 2 is installed at the bottom of the fuel tank. When the fuel completely submerges the fuel pump, the upper pump assembly 1 and the lower pump assembly 2 simultaneously and self-adaptively participate in the pressurization operation. When the aircraft is flying upright and the fuel in the tank only submerges the lower pump assembly 2, the lower pump assembly 2 self-adaptively participates in the pressurization operation. When the aircraft is flying inverted and the fuel in the tank only submerges the upper pump assembly 1, the upper pump assembly 1 self-adaptively participates in the pressurization operation.

[0029] The lower pump assembly 2 is a centrifugal pump. The outlet of the lower pump assembly 2 is connected to the vertically arranged outlet pipe 206 through the second one-way valve assembly 208. The outlet pipe 206 extends downward through the bottom of the oil tank. A medium temperature pressure sensor 210 is installed in the inner cavity of the outlet pipe 206 directly opposite the outlet of the lower pump assembly 2.

[0030] The upper pump assembly 1 is a centrifugal pump. The outlet of the upper pump assembly 1 is connected to the top of the vertically arranged outlet pipe 206. The outlet pipe 206 is provided with a first check valve assembly 207 below the medium temperature pressure sensor 210, and a third check valve assembly 106 is provided above the medium temperature pressure sensor 210.

[0031] The temperature and pressure sensor 210 is connected to the motor controller assembly 3, and automatically adjusts the motor speed in the motor controller assembly 3 according to the temperature and pressure.

[0032] The motor shaft of the motor controller assembly 3 extends upward into the upper pump assembly 1, and fuel flows into the motor through the gap in the motor shaft to complete the cooling of the motor.

[0033] It also includes an emergency fuel supply unit, specifically: a one-way bypass valve 212 is installed on the side of the outlet pipe 206. When the pump pressurization fails, the one-way bypass valve 212 is interrupted by the engine's self-priming force, and the oil in the tank directly enters the outlet pipe 206 through the one-way bypass valve 212 and is output to the engine.

[0034] The oil drain switch assembly 4 includes a lower oil drain port 401, a valve core assembly 403, a valve stem 405, a spring 406, a pin 407, and an oil drain valve core support 408. The lower oil inlet 401 is mounted on the housing of the lower pump assembly 2. The valve core assembly 403, spring 406, oil drain valve core support 408, and pin 407 are sequentially mounted on the valve stem 405. The pin 407 passes through both the oil valve core support 408 and the valve stem 405. Under the action of the spring force, the valve core assembly 403 is pressed tightly against the internal contact surface of the lower oil inlet 401.

[0035] The lower oil inlet 401 is provided with a guide groove for the mating pin 407. When it is necessary to quickly drain the fuel in the tank, the pin 407 is pushed to move upward along the guide groove of the lower oil inlet 401 until it reaches the limit. This causes the valve core support 408 of the drain valve to compress the spring 406, and pushes the valve stem 405 upward so that the valve core assembly 403 is separated from the internal contact surface of the lower oil inlet 401.

[0036] Example 2: Figure 1 This is a schematic diagram of the overall structure of the present invention. Figure 8 This is a schematic diagram of the dual pumps operating during aircraft flight. Figure 9 This is a schematic diagram of the single-pump operation during inverted flight.

[0037] refer to Figure 1 The oil pump of the present invention comprises four parts: an upper pump assembly 1, a lower pump assembly 2, a motor controller assembly 3, and an oil drain switch assembly 4.

[0038] The upper pump assembly 1 and lower pump assembly 2 are respectively mounted on the upper and lower sides of the motor controller assembly 3, which serves as the power source for the device. The fuel drain switch assembly 4 is mounted on the flange of the lower pump assembly 2, and the fuel supply pump is mounted to the bottom of the fuel tank via the flange of the lower pump assembly 2. This fuel supply pump uses a bottom-mounted structure. During flight, when the fuel in the tank completely submerges the fuel supply pump, both the upper pump assembly 1 and the lower pump assembly 2 simultaneously and automatically engage in pressurization. The pressurized fuel is then collected in the outlet pipeline and output. Figure 8 As shown; during normal flight, when the fuel level in the fuel tank is low and only submerges the lower pump assembly 2, the lower pump assembly 2 automatically adapts to participate in the pressurization operation, pressurizing the fuel before outputting it. At this time, the upper pump assembly 1 works synchronously under the drive of the motor shaft of the motor controller assembly 3, but does not participate in the fuel pressurization operation. During inverted flight, the fuel supply pump is inverted, and the fuel level in the fuel tank only submerges the upper pump assembly 1. The upper pump assembly 1 automatically adapts to participate in the pressurization operation, pressurizing the fuel before outputting it. At this time, the lower pump assembly 2 works synchronously under the drive of the motor shaft of the motor controller assembly 3, but does not participate in the fuel pressurization operation. Figure 9 As shown.

[0039] Figure 6 This is a diagram showing the installation location of the medium-temperature pressure sensor and the motor controller. Figure 7 This is a cross-sectional view of the installation of a medium-temperature pressure sensor.

[0040] refer to Figure 6 , Figure 7The medium-temperature pressure sensor 210 is installed in a specific space within the lower mounting housing 201. Through communication with the output pipeline of the lower mounting housing 201, it can directly measure the pressure of the fuel after pressurization when the fuel pump is working and output it to the host computer. Due to the shorter transmission path, the measurement result is more accurate. The motor 301 and controller 302 in the motor controller assembly 3 are integrated, achieving a highly integrated architecture. In both single-pump and dual-pump operating modes, the built-in pressure sensor can accurately measure the outlet pressure signal, achieving accurate pressure self-sensing.

[0041] Figure 2 , Figure 3 This is a schematic diagram of the external and internal structure of the pump body.

[0042] refer to Figure 2 , Figure 3 The lower pump assembly 2 includes a lower mounting housing 201, a lower impeller 202, a lower inducer 203, a sealing ring 204, an elastic retaining ring for the bore 205, an outlet pipe 206, a one-way valve assembly (207, 208), a sealing gasket 209, and a medium-temperature pressure sensor 210. Figure 7 (as shown), socket 211, one-way bypass valve assembly 212, lower filter assembly 213, graphite bearing 214.

[0043] The fuel pump adopts a bottom-mounted structure and is mounted on the fuel tank via a lower mounting housing 201 flange and a sealing gasket 209. The lower mounting housing 201 is connected to the lower part of the motor controller assembly 3 by screws. The lower motor shaft of the motor controller assembly 3 passes through a pre-drilled hole in the graphite bearing 214 mounted on the lower mounting housing 201. Fuel can flow into the motor through this pre-drilled hole for cooling. The lower impeller 202 and lower inducer 203 are sequentially mounted on the lower motor shaft end of the motor controller assembly 3. The outlet pipe 206, under the action of the sealing ring 204 and the elastic retaining ring 205, achieves a tight seal with the flange of the lower mounting housing 201. The sealing and connection, the one-way valve assembly (207, 208) are installed in the pipe channel of the lower mounting housing 201, respectively responsible for ensuring the one-way flow of fluid in the main pipeline and the lower pump pipeline, and preventing liquid backflow. The medium temperature pressure sensor 210 is installed inside the lower mounting housing 201, and the measuring end is connected to the pipe channel. The socket 211 is installed on the flange of the lower mounting housing 201. The one-way bypass valve assembly 212 is installed on the pipeline of the lower mounting housing 201. The lower filter assembly 213 is installed around the oil inlet of the lower mounting housing 201.

[0044] When the aircraft is in a normal flight attitude and the fuel tank has low fuel levels, the fuel supply pump automatically recognizes this flight state. At this time, the fuel only covers the lower pump inlet, but the upper pump inlet is suspended. Only the lower pump participates in the fuel pressurization operation. The motor controller assembly 3 drives the lower impeller 202 and the lower inducer 203 through the motor shaft to draw fuel from the fuel tank into the lower mounting housing 201 through the lower filter assembly 213. After the fuel is pressurized, it is output sequentially through the one-way valve assembly 208, the lower mounting housing 201, the one-way valve assembly 207, and the outlet pipe 206. At this time, the one-way valve assembly 106 in the upper pump assembly is closed to ensure that fuel does not enter the upper pump assembly and affect the performance of the fuel supply pump. At this time, the built-in medium temperature pressure sensor 210 can accurately sense the oil pressure value in the outlet pipe when the single lower pump is pressurizing, realizing the pressure self-sensing function.

[0045] refer to Figure 2 , Figure 3 The upper pump assembly 1 includes an upper mounting housing 101, an upper oil inlet 102, an upper filter assembly 103, an upper impeller 104, an upper inducer 105, a one-way valve assembly 106, sealing rings (107A, 107B), and a connecting pipe 108. The upper mounting housing 101 is mounted to the motor controller assembly 3 with screws. The upper filter assembly 103 is mounted to the upper part of the upper oil inlet 102 with screws. The upper oil inlet 102 is mounted to the upper mounting housing 101 with screws. The motor controller assembly 3... The upper motor shaft extends into the upper mounting housing 101, and fuel can flow into the motor through the gap in the motor shaft to cool the motor. The upper impeller 104 and the upper inducer 105 are sequentially installed on the upper motor shaft end of the motor controller assembly 3. The one-way valve assembly 106 is installed on the outlet channel of the upper mounting housing 101 by screws. The upper part of the connecting pipe 108 is connected to the outlet of the upper mounting housing 101 through the sealing ring 107A, and the lower part of the connecting pipe 108 is connected to the pipeline of the lower mounting housing 201 through the sealing ring 107B.

[0046] When the aircraft is in an inverted flight attitude, the fuel supply pump automatically recognizes this flight state. The fuel only covers the upper pump inlet, but the lower pump inlet is suspended. Only the upper pump participates in the fuel pressurization operation. The pump body is inverted, and the motor controller assembly 3 drives the upper impeller 104 and the upper inducer 105 through the motor shaft. The fuel in the fuel tank is sucked into the upper mounting housing 101 through the upper filter assembly 103 and the upper inlet 102. After the fuel is pressurized, it is output through the one-way valve assembly 106, the connecting pipe 108, the lower mounting housing 201, the one-way valve assembly 207, and the outlet pipe 206. At this time, the one-way valve assembly 208 is closed to ensure that the fuel does not enter the lower pump assembly and affect the performance of the fuel supply pump. At this time, the medium temperature pressure sensor 210 can accurately sense the oil pressure value of the outlet pipe when the single upper pump is pressurizing, realizing the pressure self-sensing function.

[0047] When the aircraft is in a normal flight attitude and there is a lot of fuel in the fuel tank, the fuel supply pump automatically recognizes this flight state. At this time, the fuel completely covers the fuel inlet of the upper and lower pumps, and the upper and lower pumps participate in the pressurization operation at the same time. After the fuel is pressurized by the upper pump assembly 1 and the lower pump assembly 2, it is output through the outlet pipe 206. At this time, the one-way valve assemblies 106, 207 and 208 are all open to ensure that the fuel pressurized by the upper and lower pumps can be smoothly output through the outlet pipe 206. At this time, the built-in medium temperature pressure sensor 210 can accurately sense the oil pressure value of the outlet pipe when the dual pumps work together to pressurize, realizing the pressure self-sensing function.

[0048] refer to Figure 2 , Figure 3 The drain switch 4 includes a lower oil inlet 401, a hexagonal self-locking nut 402, a valve core assembly 403, a valve core washer 404, a valve stem 405, a spring 406, a pin 407, and a drain valve core support 408. The lower oil inlet 401 is mounted to the lower mounting housing 201 by screws. The hexagonal self-locking nut 402, valve core assembly 403, valve core washer 404, spring 406, drain valve core support 408, and pin 407 are sequentially mounted on the valve stem 405. The pin 407 passes through both the drain valve core support 408 and the valve stem 405. Under the spring force, the valve core assembly 403 is pressed tightly against the internal contact surface of the lower oil inlet 401, thus ensuring the drain switch is closed.

[0049] refer to Figure 2 , Figure 3 To ensure that fuel can still be smoothly delivered to the engine with low flow resistance when the fuel pump fails and the boost is interrupted, an emergency fuel supply unit was designed. A one-way bypass valve 212 is installed on the side of the outlet pipe to establish a fuel delivery channel in emergency situations, stabilizing pressure and flow to continuously supply fuel to the engine. When the pump boost fails, the one-way bypass valve 212 opens under the engine's self-priming force, and fuel in the fuel tank is directly output to the engine through the one-way bypass valve 212, one-way valve assembly 207, and outlet pipe 206, effectively improving the emergency fuel supply capability of the fuel system.

[0050] Figure 4 This is a schematic diagram of the guide groove for the drain switch at the lower oil inlet. The state shown in the diagram is the drain switch in the closed state.

[0051] refer to Figure 3 , Figure 4To enable rapid fuel draining, a drain switch is installed at the lower inlet of the fuel pump. When it is necessary to quickly drain the fuel from the tank, the push pin 407 moves upward along the guide groove of the lower inlet 401 until it reaches the limit. During this process, the drain valve core support 408 compresses the spring 406, thereby pushing the valve stem 405 upward, causing the valve core assembly 403 to disengage from the internal contact surface of the lower inlet 401. Fuel can then be discharged through the lower mounting housing 201 via the drain switch 4, achieving rapid fuel draining. This switch adopts a minimalist transmission design, combining the advantages of easy operation, compact structure, and tight sealing, significantly improving the maintenance efficiency and safety of the fuel system.

[0052] Figure 5 This is a schematic diagram of the mounting components for the lower housing flange.

[0053] refer to Figure 5 The components mounted on the flange of the lower mounting housing 201 include the oil drain switch assembly 4, the outlet pipe 206, and the socket 211.

[0054] This invention proposes an integrated multi-functional fuel pump with pressure self-sensing and mode self-adaptation functions. The fuel pump may include the aforementioned upper pump assembly, lower pump assembly, motor controller assembly, and fuel drain switch assembly. This invention deeply integrates core functions such as pressure sensing, adaptive mode switching, emergency fuel supply, and rapid fuel drain, accurately adapting to the complex and ever-changing operating scenarios during flight, and comprehensively ensuring the stability and reliability of fuel supply.

[0055] This invention designs a fuel pump device with pressure self-sensing function. It achieves accurate pressure self-sensing through built-in pressure sensor, which can monitor the fuel line pressure status in real time and provide accurate data support for the operation of the fuel system. Compared with external sensors, it significantly improves measurement stability and reliability. At the same time, in order to realize that the electrical circuit of the pressure sensor, the three-phase wire of the motor, and the Hall sensor circuit are all connected through the same electrical connector, the pressure sensor is integrated with the motor and the wire is inserted into the motor.

[0056] This invention designs a multi-pump structure with mode self-adaptation function, which can intelligently identify the aircraft's flight attitude and adaptively switch between single-down pump, single-up pump, and dual-pump collaborative operation modes to achieve adaptive matching of fuel supply modes under conditions such as forward and backward flight.

[0057] To solve the fuel leakage problem when a fuel pump operates alone, this invention constructs a three-stage one-way blocking structure. One-way valves are installed at the outlets of the upper pump, lower pump, and the entire pump. This design can not only ensure flexible switching between the upper and lower pumps operating independently or in tandem, but also effectively prevent backflow of fuel in the fuel system, significantly improving the sealing and reliability of the fuel supply system.

[0058] This invention designs an emergency fuel supply unit that ensures fuel can still be smoothly delivered to the engine with low flow resistance even when the fuel pump fails and is not in operation. A one-way bypass valve is installed on the side of the outlet pipeline to establish a fuel delivery channel in emergency situations, thereby stabilizing pressure and flow to continuously supply fuel to the engine and effectively improving the emergency fuel system's reliability.

[0059] This invention proposes a 360° rotatable outlet pipe joint structure. Axial positioning constraint is achieved through an elastic retaining ring, ensuring stable installation while releasing its circumferential rotational freedom. This design effectively solves the space constraints encountered during fuel system piping installation, significantly improving the flexibility and ease of pump body piping layout.

[0060] This invention integrates a highly convenient fuel drain switch. A linear push pin drives the drain valve in a vertical reciprocating motion, achieving rapid fuel release and sealing of the fuel tank. The switch employs a minimalist transmission design, combining ease of operation, compact structure, and tight sealing, significantly improving the maintenance efficiency and safety of the fuel system.

[0061] The motor of this invention adopts oil-inlet forced cooling technology. Under pressure, fuel flows through the inside of the motor and fully exchanges heat with the heat-generating components of the motor, quickly absorbing and carrying away a large amount of heat generated during the operation of the motor, significantly improving the power density of the motor.

[0062] This invention adopts a deep integration design scheme of motor and controller to achieve a highly integrated architecture. The controller replaces the traditional circuit board with an integrated module, which simplifies the internal structure and further reduces the weight of the product. It simultaneously achieves the goals of product lightweighting and miniaturization, and realizes a dual breakthrough in performance and weight reduction.

[0063] The above description is merely a specific embodiment of the present invention, providing a detailed description of the invention. Parts not covered herein are conventional techniques. However, the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in the present invention should be included within the scope of protection of the present invention. The scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. An integrated multi-functional oil supply pump with pressure self-sensing and mode self-adaptation functions, characterized in that, The system includes an upper pump assembly (1), a lower pump assembly (2), a motor controller assembly (3), and a drain switch assembly (4). The upper pump assembly (1) and the lower pump assembly (2) are respectively installed on the upper and lower sides of the motor controller assembly (3). The motor controller assembly (3) provides a power source for the upper pump assembly (1) and the lower pump assembly (2). The drain switch assembly (4) is installed on the flange at the bottom of the lower pump assembly (2). The flange of the lower pump assembly (2) is installed at the bottom of the fuel tank. When the fuel completely submerges the fuel supply pump, the upper pump assembly (1) and the lower pump assembly (2) simultaneously adapt to participate in the pressurization operation. When the aircraft is flying normally and the fuel in the fuel tank only submerges the lower pump assembly (2), the lower pump assembly (2) adapts to participate in the pressurization operation. When the aircraft is flying backwards and the fuel in the fuel tank only submerges the upper pump assembly (1), the upper pump assembly (1) adapts to participate in the pressurization operation.

2. The integrated multi-functional oil pump with pressure self-sensing and mode self-adaptation functions as described in claim 1, characterized in that, The lower pump assembly (2) is a centrifugal pump. The outlet of the lower pump assembly (2) is connected to the vertically arranged outlet pipe (206) through the second one-way valve assembly (208). The outlet pipe (206) extends downward through the bottom of the oil tank. A medium temperature pressure sensor (210) is installed in the inner cavity of the outlet pipe (206) facing the outlet of the lower pump assembly (2).

3. The integrated multi-functional oil pump with pressure self-sensing and mode self-adaptation functions according to claim 2, characterized in that, The upper pump assembly (1) is a centrifugal pump. The outlet of the upper pump assembly (1) is connected to the top of the vertically arranged outlet pipe (206). The outlet pipe (206) is provided with a first check valve assembly (207) below the medium temperature pressure sensor (210) and a third check valve assembly (106) above the medium temperature pressure sensor (210).

4. The integrated multi-functional oil pump with pressure self-sensing and mode self-adaptation functions according to claim 3, characterized in that, The temperature and pressure sensor (210) is connected to the motor controller assembly (3) and automatically adjusts the motor speed in the motor controller assembly (3) according to the temperature and pressure.

5. The integrated multi-functional oil pump with pressure self-sensing and mode self-adaptation functions as described in claim 1, characterized in that, The motor shaft of the motor controller assembly (3) extends upward into the upper pump assembly (1), and fuel flows into the motor through the gap between the motor shafts to cool the motor.

6. The integrated multi-functional oil supply pump with pressure self-sensing and mode self-adaptation functions according to claim 1, characterized in that, It also includes an emergency fuel supply unit, specifically: a one-way bypass valve (212) is installed on the side of the outlet pipe (206). When the pump pressurization fails, the one-way bypass valve (212) is interrupted by the self-priming force of the engine, and the oil in the tank directly enters the outlet pipe (206) through the one-way bypass valve (212) and is output to the engine.

7. The integrated multi-functional oil pump with pressure self-sensing and mode self-adaptation functions according to claim 1, characterized in that, The oil drain switch assembly (4) includes a lower oil drain port (401), a valve core assembly (403), a valve stem (405), a spring (406), a pin (407), and an oil drain valve core support (408). The lower oil inlet (401) is mounted on the housing of the lower pump assembly (2). The valve core assembly (403), spring (406), oil drain valve core support (408), and pin (407) are sequentially mounted on the valve stem (405). The pin (407) passes through both the oil valve core support (408) and the valve stem (405). Under the action of the spring force, the valve core assembly (403) is pressed tightly against the internal contact surface of the lower oil inlet (401).

8. The integrated multi-functional oil supply pump with pressure self-sensing and mode self-adaptation functions according to claim 7, characterized in that, The lower oil inlet (401) is provided with a guide groove for the mating pin (407). When it is necessary to quickly drain the fuel in the tank, the pin (407) is pushed to move upward along the guide groove of the lower oil inlet (401) until it reaches the limit. This causes the valve core support (408) of the drain valve to compress the spring (406) and push the valve stem (405) upward so that the valve core assembly (403) is separated from the internal contact surface of the lower oil inlet (401).

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