Aircraft power source assembly and aircraft

Abstract

The present invention provides an aircraft power source assembly and an aircraft. The aircraft power source assembly includes a motor, a mounting support and an oil tank arranged along the axial direction of the aircraft power source assembly. The motor and the oil tank are fixedly connected to the mounting support, and also includes a pump body, a safety valve, an overflow valve and a first one-way valve. An oil supply channel and an oil return channel are provided in the mounting support, and a pressure supply port and an oil return port are provided on the outer wall of the mounting support. The pump body is arranged on the oil supply channel, and the overflow valve and the safety valve are both connected to the oil supply channel and are both located between the oil outlet end and the pressure supply port of the pump body. The first one-way valve is arranged on the oil supply channel, and the first one-way valve is located between the oil outlet end of the pump body and the overflow valve and is unidirectionally conducted from the pump body to the overflow valve. The aircraft power source assembly can integrate system components inside the power source assembly as much as possible under the premise of completing the function of the hydraulic system, save system installation and system pipelines to achieve aircraft weight reduction, and also reduce the leakage points of the hydraulic system.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft, and in particular to an aircraft power source component and an aircraft. Background Art

[0002] For large aircraft, there is plenty of space and weight. Its hydraulic system energy subsystem generally uses an electric pump or a mechanical pump to draw oil from the oil tank. The hydraulic system is designed with system protection devices, anti-backflow devices, oil return devices, etc. The system protection devices include high-pressure protection systems, thermal protection systems, and impurity protection systems. In this design, each component needs to be installed with a support, and the components are connected by pipes and pipe joints, which takes up a lot of space and has complex connecting pipes. For small aircraft, the space is small and the weight needs to be strictly controlled, so this solution is not applicable. Summary of the invention

[0003] The first purpose of the present invention is to provide an aircraft power source assembly that can be used for light amphibious aircraft. The aircraft power source assembly can integrate system components inside the power source assembly as much as possible while completing the functions of the hydraulic system, saving system installation and system piping to achieve aircraft weight reduction, while also reducing hydraulic system leakage points.

[0004] A second object of the present invention is to provide an aircraft having the above aircraft power source assembly.

[0005] To achieve the above first object, the present invention provides an aircraft power source assembly, comprising a motor, a mounting support and an oil tank arranged along the axial direction of the aircraft power source assembly, wherein the motor and the oil tank are both fixedly connected to the mounting support; the aircraft power source assembly also comprises a pump body, a safety valve, an overflow valve and a first one-way valve; the pump body is installed in the oil tank, the driving shaft of the pump body is connected to the driving shaft of the motor, and the driving shaft of the pump body and the driving shaft of the motor are both parallel to the axial direction of the aircraft power source assembly; the overflow valve and the safety valve are both arranged on the mounting support; the mounting support An oil supply channel and an oil return channel are provided in the support, a pressure supply port and an oil return port are provided on the outer wall of the mounting support, and the two ends of the oil return channel are connected to the oil tank and the oil return port respectively; the pump body is arranged on the oil supply channel, the oil inlet end of the pump body is connected to the oil tank, the oil outlet end of the pump body is connected to the pressure supply port, the overflow valve and the safety valve are both connected to the oil supply channel and are both located between the oil outlet end and the pressure supply port of the pump body; the first one-way valve is arranged on the oil supply channel, the first one-way valve is located between the oil outlet end of the pump body and the overflow valve and is unidirectionally conductive from the pump body to the overflow valve.

[0006] It can be seen from the above scheme that by setting the aircraft power source assembly into an integrated structure, components such as the safety valve and the overflow valve are arranged on the mounting support, and an oil supply channel and an oil return channel are opened inside the mounting support, and a pressure supply port and an oil return port are arranged on the outer wall of the mounting support, so that the system components are integrated inside the power source assembly, saving system installation and system piping, achieving aircraft weight reduction, and also reducing the leakage points of the hydraulic system.

[0007] A preferred solution is that the oil supply channel includes an upstream section of the pump body and a downstream section of the pump body, the two ends of the upstream section of the pump body are respectively connected to the oil inlet end of the pump body and the oil tank, the two ends of the downstream section of the pump body are respectively connected to the oil outlet end of the pump body and the pressure supply port, the safety valve, the overflow valve and the first one-way valve are all located in the downstream section of the pump body; the oil return channel includes an oil return port connecting section and an oil tank connecting section, the two ends of the oil return port connecting section are respectively connected to the oil return port and the upstream section of the pump body, and the oil tank connecting section is a part of the upstream section of the pump body.

[0008] It can be seen that the oil supply passage and the oil return passage share a portion, which can simplify the internal structure of the mounting seat.

[0009] A further solution is that a filter is provided on the fuel tank connecting section.

[0010] It can be seen that by providing a filter on the oil tank connecting section, impurities and foreign matter in the return oil can be prevented from entering the oil tank, and impurities and foreign matter in the oil can be prevented from entering the system.

[0011] A further solution is that a pressure differential indicator is also connected to the oil tank connecting section, the pressure differential indicator is connected in parallel with the filter screen, and the pressure differential indicator is arranged on the mounting support.

[0012] It can be seen that a pressure differential indicator is connected in parallel at both ends of the filter, and the pressure differential indicator is used to detect whether the oil filter is blocked.

[0013] A preferred solution is that the aircraft power source assembly also includes a second one-way valve, the oil supply channel and the oil tank are connected through an oil return pipe, the oil return pipe is connected to the first position between the first one-way valve and the oil outlet end of the pump body on the oil supply channel, the safety valve is arranged at the first position of the oil supply channel, and the second one-way valve is arranged on the oil return pipe and is unidirectionally conducted from one end close to the first position to one end away from the first position.

[0014] It can be seen that the provision of the second one-way valve prevents the oil from flowing in the reverse direction.

[0015] A preferred solution is that the pump body is fixed on the mounting support.

[0016] This shows that the stability of the installation of each component is guaranteed.

[0017] A preferred solution is that an oil level indicator is provided at one end of the oil tank away from the mounting support, and the oil level indicator is used to indicate the remaining amount of hydraulic oil in the oil tank.

[0018] A preferred solution is that the pressure supply port is also provided with a three-way joint, the three-way joint has an inlet, a first outlet and a second outlet, the inlet is connected to the oil supply channel, the first outlet is the hydraulic system pressure supply port, and the second outlet is the ground pressure supply port.

[0019] It can be seen that by setting a three-way joint, pressure can be supplied to the system as well as to the ground.

[0020] A preferred solution is that a ground pressure supply port is also provided on the outer wall of the mounting support, and the ground pressure supply port is arranged close to the pressure supply port and is communicated with the oil supply channel.

[0021] It can be seen from this that the ground pressure supply port can also be directly opened on the mounting support.

[0022] To achieve the above second objective, the present invention provides an aircraft, comprising the above aircraft power source assembly. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 It is a working principle diagram of the aircraft hydraulic energy subsystem in the aircraft embodiment of the present invention.

[0024] Figure 2 yes Figure 1 A partial enlarged view of point B in the middle.

[0025] Figure 3 It is a structural diagram of an embodiment of an aircraft power source assembly of the present invention.

[0026] Figure 4 It is a cross-sectional view of an embodiment of an aircraft power source assembly of the present invention.

[0027] Figure 5 It is a circuit diagram of a pressure signal device and an electric pump in a hydraulic energy subsystem of an aircraft according to an embodiment of the present invention. DETAILED DESCRIPTION

[0028] See also Figures 1 to 5 The aircraft of this embodiment includes an aircraft hydraulic energy subsystem, which includes a hydraulic system pipeline 1, an accumulator 2, a pressure signal device 3, a first circuit switch 4, an electromagnetic switch 5 and an aircraft power source component 6.

[0029] The aircraft power source assembly 6 includes an electric pump 61 , a mounting bracket 62 , an oil tank 63 , a safety valve 64 , a relief valve 65 , a first one-way valve 66 and a second one-way valve 67 .

[0030] The electric pump 61 includes a motor 611 and a pump body 612. The pump body 612 is a gear pump. The motor 611, the oil tank 63 and the pump body 612 are all fixedly connected to the mounting bracket 62. The motor 611, the mounting bracket 62 and the oil tank 63 are arranged along the axial direction of the aircraft power source assembly 6. The pump body 612 is installed in the oil tank 63. The drive shaft 6121 of the pump body 612 is connected to the drive shaft 6111 of the motor 611. The drive shaft 6121 of the pump body 612 and the drive shaft 6111 of the motor 611 are both parallel to the axial direction of the aircraft power source assembly 6.

[0031] The overflow valve 65 and the safety valve 64 are both arranged on the mounting support 62. The mounting support 62 is provided with an oil supply channel 621 and an oil return channel 622. The outer wall of the mounting support 62 is provided with a pressure supply port 623 and an oil return port 624. The two ends of the oil return channel 622 are respectively connected to the oil tank 63 and the oil return port 624. The pump body 612 is arranged on the oil supply channel 621. The oil inlet end of the pump body 612 is connected to the oil tank 63, and the oil outlet end of the pump body 612 is connected to the pressure supply port 623. The overflow valve 65 and the safety valve 64 are both connected to the oil supply channel 621 and are both located between the oil outlet end of the pump body 612 and the pressure supply port 623. When the system is overheated, the volume of the oil in the system will expand due to thermal expansion, and the excess liquid will overflow through the overflow valve 65. When the system pressure is too high, the pressure can be automatically released through the safety valve 64. The safety valve 64 opens when the system pressure is too high, and closes when the pressure in the system drops to a specified value, ensuring that the system pressure does not exceed the specified value. A refueling plug 632 is also provided on the outer wall of the oil tank 63, and a refueling port 6321 and a vent 6322 are provided on the refueling plug 632.

[0032] The first one-way valve 66 is disposed on the oil supply passage 621 . The first one-way valve 66 is located between the oil outlet of the pump body 612 and the relief valve 65 and is unidirectionally conductive from the pump body 612 to the relief valve 65 .

[0033] The oil supply channel 621 includes an upstream section 6211 of the pump body and a downstream section 6212 of the pump body. The two ends of the upstream section 6211 of the pump body are respectively connected to the oil inlet end of the pump body 612 and the oil tank 63. The two ends of the downstream section 6212 of the pump body are respectively connected to the oil outlet end of the pump body 612 and the pressure supply port 623. The safety valve 64, the overflow valve 65 and the first one-way valve 66 are all located in the downstream section 6212 of the pump body.

[0034] The oil return passage 622 includes an oil return port connection section 6221 and an oil tank connection section 6222. The two ends of the oil return port connection section 6221 are respectively connected to the oil return port 624 and the pump body upstream section 6211. The oil tank connection section 6222 is a part of the pump body upstream section 6211. In this way, the oil supply passage 621 and the oil return passage 622 share a part, which can simplify the internal structure of the mounting seat.

[0035] A filter screen 68 is provided on the oil tank connection section 6222, and a differential pressure indicator 69 is also connected to the oil tank connection section 6222. The differential pressure indicator 69 is connected in parallel with the filter screen 68 and is provided on the mounting bracket 62. By providing the filter screen 68 on the oil tank connection section 6222, impurities and foreign objects in the return oil can be prevented from entering the oil tank 63, and impurities and foreign objects in the oil can be prevented from entering the system. A differential pressure indicator 69 is connected in parallel at both ends of the filter screen 68, and the differential pressure indicator 69 is used to detect whether the oil filter is blocked.

[0036] The oil supply channel 621 is connected to the oil tank 63 through the return oil pipe 60. The return oil pipe 60 is connected to the first position A between the first one-way valve 66 on the oil supply channel 621 and the oil outlet end of the pump body 612. The safety valve 64 is arranged at the first position A of the oil supply channel 621. The second one-way valve 67 is arranged on the return oil pipe 60 and is unidirectionally conducted from one end close to the first position A to the end far away from the first position A.

[0037] An oil level indicator 631 is provided at one end of the oil tank 63 away from the mounting support 62 . The oil level indicator 631 is used to indicate the remaining amount of hydraulic oil in the oil tank 63 .

[0038] The pressure supply port 623 is also provided with a three-way joint 625, which has an inlet 6251, a first outlet 6252 and a second outlet 6253. The inlet 6251 is connected to the oil supply channel 621, the first outlet 6252 is a hydraulic system pressure supply port, and the second outlet 6253 is a ground pressure supply port. By providing the three-way joint 625, pressure can be supplied to the system or to the ground.

[0039] The hydraulic system pipeline 1 is connected to the hydraulic system pressure supply port of the three-way joint 625, and the pressure signal device 3 and the pressure accumulator 2 are both connected to the hydraulic system pipeline 1. The pressure signal device 3 is located between the pressure accumulator 2 and the hydraulic system pressure supply port. The pressure signal device 3 is provided with a pressure signal device switch 31, and the pressure signal device switch 31 is closed or opened according to the pressure of the hydraulic oil in the hydraulic system pipeline 1. The pressure accumulator 2 is provided with a charging valve 21 and a micro air pressure gauge 22.

[0040] The hydraulic system pipeline 1 is also provided with an oil filter 12 and a pressure sensor 13, both of which are located between the pressure signal device 3 and the pressure accumulator 2, and the oil filter 12 is located between the pressure signal device 3 and the pressure sensor 13. The setting of the oil filter 12 can prevent impurities and foreign matter in the oil from entering the system. The pressure sensor 13 transmits the corresponding electrical signal to the integrated electronic system according to the pressure in the hydraulic system pipeline 1, and the integrated electronic system displays the pressure value in the system to the pilot.

[0041] See also Figure 5The electromagnetic switch 5 includes a second circuit switch 51 and an electromagnetic coil 52. The first circuit switch 4, the electromagnetic coil 52 and the pressure signal switch 31 are connected in series to the first branch 71. The second circuit switch 51 and the electric pump 61 are connected in series to the second branch 72. The first branch 71 is connected in parallel to the second branch 72.

[0042] The control method of the aircraft hydraulic energy subsystem of this embodiment includes:

[0043] When the aircraft is performing a mission, the working circuit switch of the aircraft power source assembly 6, that is, the first circuit switch 4, is closed, and the hydraulic energy subsystem starts to work automatically.

[0044] When the pressure of the hydraulic oil in the hydraulic system pipeline 1 is lower than the preset lower limit threshold, the pressure signal switch 31 is closed, the electromagnetic coil 52 is energized and the second circuit switch 51 is attracted, the electric pump 61 starts to work and delivers hydraulic oil to the high-pressure oil output end 11 of the aircraft hydraulic energy subsystem, and the high-pressure oil reaches the control elements of each execution subsystem through the first one-way valve 66, the oil filter 12, and the accumulator 2. Preferably, the preset lower limit threshold is 6.1 Mpa.

[0045] When each execution subsystem is not working, the aircraft power source assembly 6 charges the pressure of the accumulator 2 to a set pressure value, that is, 10.5 MPa.

[0046] When the pressure of the hydraulic oil in the hydraulic system pipeline 1 is higher than the above-mentioned set pressure value, that is, the preset upper limit threshold, the pressure signal switch 31 is disconnected, the second circuit switch 51 is disconnected, the electric pump 61 stops working, and the accumulator 2 delivers hydraulic oil to the high-pressure oil output terminal 11 of the aircraft hydraulic energy subsystem. Preferably, the preset upper limit threshold is 10.5Mpa.

[0047] As can be seen from the above, by setting the aircraft power source assembly into an integrated structure, the components such as the safety valve and the overflow valve are all arranged on the mounting support, and the oil supply channel and the oil return channel are opened inside the mounting support, and the pressure supply port and the oil return port are arranged on the outer wall of the mounting support, so that the system components are integrated inside the power source assembly, saving system installation and system pipelines, and realizing the weight reduction of the aircraft. The aircraft power source assembly realizes the integrated design of hydraulic system oil storage, pressure supply, and protection, reducing the problem of multi-component installation space and the problem of multiple leakage points of pipeline joints. At the same time, the structure of this device is simple, safe and reliable, light in weight and low in cost. In addition, the hydraulic energy subsystem can use a pressure signal device to automatically control the start and stop of the electric pump according to the pressure of the hydraulic oil in the pressure pipe of the hydraulic system, ensuring that the electric pump stops working within the working pressure range of the hydraulic system, and the electric pump starts when the pressure is lower than the set pressure, avoiding the hydraulic pump from being damaged due to long-term operation, thereby greatly shortening the effective working time of the electric pump. At the same time, for the safety and reliability of the system, the energy storage device can safely lower the landing gear after the energy system fails, ensuring that the aircraft can land safely. The accumulator is set as an energy storage device. When the system is working normally, it can keep the system pressure within the working range for a long time, shorten the starting frequency of the electric pump, and ensure the safe lowering of the landing gear in the event of a system failure.

[0048] In addition, the pump body and the mounting support can also be integrally formed, or the pump body and the mounting support can be fixedly connected by welding or screwing. The ground pressure supply port can also be directly opened on the mounting support, that is, the outer wall of the mounting support is also provided with a ground pressure supply port, which is arranged close to the pressure supply port and is connected to the oil supply channel. The above changes can also achieve the purpose of the present invention.

[0049] Finally, it should be emphasized that the above is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various changes and modifications. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. An aircraft power source assembly, characterized in that: It comprises a motor, a mounting support and an oil tank arranged along the axial direction of the aircraft power source assembly, wherein the motor and the oil tank are both fixedly connected to the mounting support; The aircraft power source assembly also includes a pump body, a safety valve, a relief valve and a first one-way valve; The pump body is installed in the oil tank, the driving shaft of the pump body is connected to the driving shaft of the motor, and the driving shaft of the pump body and the driving shaft of the motor are parallel to the axial direction of the aircraft power source assembly; The overflow valve and the safety valve are both arranged on the mounting support; An oil supply channel and an oil return channel are provided in the mounting support, and along the axial direction of the aircraft power source assembly, the oil supply channel and the oil return channel are located between the motor and the oil tank, a pressure supply port and an oil return port are provided on the outer wall of the mounting support, and the two ends of the oil return channel are respectively connected to the oil tank and the oil return port, the pressure supply port is connected to the oil tank only through the oil supply channel, and the oil return port is connected to the oil tank only through the oil return channel, and a filter is provided in the oil return channel; The pump body is arranged on the oil supply passage, the oil inlet end of the pump body is communicated with the oil tank, the oil outlet end of the pump body is communicated with the pressure supply port, the overflow valve and the safety valve are both communicated with the oil supply passage and are both located between the oil outlet end of the pump body and the pressure supply port; The first one-way valve is arranged on the oil supply passage, and the first one-way valve is located between the oil outlet end of the pump body and the relief valve and is one-way conducting from the pump body to the relief valve; The oil supply passage comprises an upstream section of the pump body and a downstream section of the pump body, the two ends of the upstream section of the pump body are respectively connected to the oil inlet end of the pump body and the oil tank, the two ends of the downstream section of the pump body are respectively connected to the oil outlet end of the pump body and the pressure supply port, the safety valve, the overflow valve and the first one-way valve are all located in the downstream section of the pump body; The oil return passage comprises an oil return port connecting section and an oil tank connecting section, the two ends of the oil return port connecting section are respectively connected to the oil return port and the upstream section of the pump body, and the oil tank connecting section is a part of the upstream section of the pump body; The filter screen is located on the fuel tank connecting section; The aircraft power source assembly also includes a second one-way valve, the oil supply channel is connected to the oil tank through an oil return pipe, the oil return pipe is connected to a first position between the first one-way valve and the oil outlet end of the pump body on the oil supply channel, the safety valve is arranged at the first position of the oil supply channel, and the second one-way valve is arranged on the oil return pipe and is unidirectionally conducted from one end close to the first position to one end away from the first position.

2. The aircraft power source assembly according to claim 1, characterized in that: The oil tank connecting section is also connected with a pressure difference indicator, the pressure difference indicator is connected in parallel with the filter screen, and the pressure difference indicator is arranged on the mounting support.

3. The aircraft power source assembly according to claim 1, characterized in that: The pump body is fixed on the mounting support.

4. The aircraft power source assembly according to any one of claims 1 to 3, characterized in that: An oil level indicator is arranged at one end of the oil tank away from the mounting support, and the oil level indicator is used to indicate the remaining amount of hydraulic oil in the oil tank.

5. The aircraft power source assembly according to any one of claims 1 to 3, characterized in that: The pressure supply port is also provided with a three-way joint, which has an inlet, a first outlet and a second outlet. The inlet is connected to the oil supply channel, the first outlet is a hydraulic system pressure supply port, and the second outlet is a ground pressure supply port.

6. The aircraft power source assembly according to any one of claims 1 to 3, characterized in that: A ground pressure supply port is also provided on the outer wall of the mounting support, and the ground pressure supply port is arranged close to the pressure supply port and is communicated with the oil supply channel.

7. An aircraft, characterized in that The invention comprises an aircraft power source assembly as claimed in any one of claims 1 to 6.

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