Aviation hydraulic pump multi-stage pressure regulation control device and control method

Abstract

The invention relates to an aviation hydraulic pump multi-stage pressure regulation control device and a control method thereof.The multi-stage pressure regulation control device comprises an oil way on-off control device and a multi-stage pressure regulation device, and the oil way on-off control device is used for selectively connecting or isolating oil ways of different pressure grades according to the flight state of an aircraft; the multi-stage pressure adjusting device is connected with the oil way on-off control device and used for adjusting the working pressure of the hydraulic pump to the corresponding pressure grade according to the selected oil way. The working pressure of the hydraulic pump can be changed and adjusted according to the flight state of an aircraft, and the hydraulic pump is in a high-pressure working state in a high-pressure load flight state and provides high pressure for a hydraulic system. In the low-pressure load flight state, the hydraulic pump is in the low-pressure working state, and low pressure is provided for the hydraulic system. And at the starting moment, the hydraulic pump is in a lowest pressure working state, so that the hydraulic pump is started in a lowest power loss mode, and the starting burden of the engine and the onboard power supply power are reduced.

Description

Technical Field

[0001] The present application relates to the technical field of aviation hydraulic pumps, and in particular to a multi-stage pressure regulating control device for an aviation hydraulic pump capable of automatically adjusting the working pressure according to the flight status of an aircraft and a control method thereof. Background Art

[0002] As the power element of the aircraft hydraulic system, the hydraulic pump is a device that converts mechanical energy into hydraulic energy. In the prior art, the pressure of the hydraulic pump is set and designed according to the peak pressure of the hydraulic system. However, the load of the hydraulic system varies with the flight state of the aircraft. Therefore, the highest pressure is only required for a short time in a certain flight state, and only low pressure is required for most of the other flight states. That is to say, during the flight of the aircraft, the hydraulic pump will only work under the high-pressure load demand of the hydraulic system for a very short time, and it works under the low-pressure load demand of the hydraulic system for most of the rest of the time, so there is a large waste of energy.

[0003] At the same time, for the onboard electric pump and engine hydraulic pump, the hydraulic pump works under the rated pressure at the moment of starting, and the required input power (electrical power, mechanical power) is relatively large, which greatly increases the starting burden of the engine and the onboard power supply power.

[0004] It should be noted that the information disclosed in this background technology section is only intended to deepen the understanding of the overall background technology of the present invention, and should not be regarded as an admission or suggestion in any form that the information constitutes the prior art known to those skilled in the art. Summary of the invention

[0005] In view of the above-mentioned deficiencies in the prior art, the present invention provides an aviation hydraulic pump multi-stage pressure regulation control device and control method, aiming to solve the problem in the prior art that the working pressure of the hydraulic pump cannot be flexibly adjusted according to the flight status of the aircraft, resulting in energy waste and increased engine starting burden.

[0006] To achieve the above object, the present invention adopts the following technical solutions: In a first aspect, the present invention provides a multi-stage pressure regulating control device for an aviation hydraulic pump, comprising: an oil circuit on-off control device, which is connected to the high-pressure outlet oil circuit of the hydraulic pump and is used to selectively connect or isolate oil circuits of different pressure levels according to the flight status of the aircraft; a multi-stage pressure regulating device, which is connected to the oil circuit on-off control device and is used to adjust the working pressure of the hydraulic pump to a corresponding pressure level according to the selected oil circuit; Wherein, the multi-stage pressure regulating device includes at least three closed chambers, each of which corresponds to a different working pressure level, and each closed chamber is connected to the follower chamber of the hydraulic pump swash plate variable mechanism through an oil circuit.

[0007] Furthermore, the oil circuit on-off control device includes a left electromagnet, a right electromagnet, a left spring, a right spring, an oil inlet and a plurality of oil circuit outlets. The oil inlet is connected to the high-pressure outlet oil circuit of the hydraulic pump through the oil circuit. Each oil circuit outlet is respectively connected to a closed chamber of the multi-stage pressure regulating device. The oil inlet and one of the oil circuit outlets are selectively connected by controlling the power-on state of the left electromagnet and the right electromagnet.

[0008] Furthermore, the multi-stage pressure regulating device also includes a pressure regulating spring and a valve core assembly, and the valve core assembly moves under the action of the pressure regulating spring according to the pressure change of the oil circuit, thereby selectively connecting one of the closed chambers to the follower chamber of the hydraulic pump variable mechanism.

[0009] Further, the multi-stage pressure regulating device forms four closed chambers through multiple valve core components, which are A closed chamber, B closed chamber, C closed chamber and D closed chamber from left to right. The A closed chamber, B closed chamber, C closed chamber and D closed chamber are respectively connected to the hydraulic pump swash plate variable mechanism follower chamber through the oil circuit. The A closed chamber, B closed chamber and C closed chamber are respectively connected to an oil circuit outlet of the oil circuit on-off control device, and the D closed chamber is connected to the oil tank through the oil return port. When the A closed chamber, B closed chamber and C closed chamber are respectively connected to the hydraulic pump high-pressure outlet oil circuit through the oil circuit on-off control device, the corresponding hydraulic pump working pressures are P a , P b , P c , which satisfies the relationship P a ﹤P b ﹤P c .

[0010] Furthermore, each of the valve core assemblies includes a valve core and a push rod, and the pressure regulating spring applies force to the valve core through the push rod to make the valve core move in the valve body.

[0011] Furthermore, the oil circuit on-off control device and the multi-stage pressure regulating device are designed as modular structures and can be customized according to different aircraft models and hydraulic system requirements.

[0012] In a second aspect, the present invention provides a control method using the aircraft hydraulic pump multi-stage pressure regulating control device described in the first aspect, comprising: S1 selectively controls the energizing state of the electromagnet of the oil circuit on-off control device according to the flight state of the aircraft, so as to connect or isolate oil circuits of different pressure levels; S2 adjusts the working pressure of the hydraulic pump to a corresponding pressure level through the multi-stage pressure regulating device according to the selected oil circuit.

[0013] Furthermore, the control method also includes: when the aircraft engine hydraulic pump or electric pump is started, controlling the oil circuit on-off control device to connect the oil circuit with the lowest pressure level, so that the hydraulic pump is started in the lowest power loss mode.

[0014] Furthermore, the working pressure of the hydraulic pump is monitored, and when the working pressure reaches a set value, the working pressure of the hydraulic pump is adjusted by the multi-stage pressure regulating device to keep it constant.

[0015] The beneficial effects of the present invention are: The working pressure of the hydraulic pump can be adjusted according to the flight status of the aircraft. In the high-pressure load flight state, the hydraulic pump is in a high-pressure working state and provides high pressure to the hydraulic system. In the low-pressure load flight state, the hydraulic pump is in a low-pressure working state and provides low pressure to the hydraulic system. At the moment of starting, the hydraulic pump is in the lowest pressure working state, so that the hydraulic pump starts in the lowest power loss mode, reducing the engine starting burden and the onboard power supply power. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 According to some embodiments of the present invention, a schematic diagram of a multi-stage pressure regulating control device for an aviation hydraulic pump is shown. DETAILED DESCRIPTION

[0017] The technical features and advantages of the present invention are described in more detail below in conjunction with the accompanying drawings, so that the advantages and features of the present invention can be more easily understood by those skilled in the art, thereby making a clearer and more definite definition of the protection scope of the present invention.

[0018] See also Figure 1 The embodiment of the present invention provides a multi-stage pressure regulating control device for an aviation hydraulic pump, which mainly includes: an oil circuit on-off control device 100 and a multi-stage pressure regulating device 200; wherein the oil circuit on-off control device 100 mainly includes a left electromagnet 110, a left spring 120, a right spring 130, a right electromagnet 140, an oil inlet P0, three oil circuit outlets P a , P b and P c The oil inlet P0 is connected to the P port of the hydraulic pump high pressure outlet oil circuit 500 through the P0-P oil circuit 310, and the oil inlet P0 and one of the oil circuit outlets P0 are selectively connected by controlling the power-on state of the left electromagnet 110 and the right electromagnet 140. a , P b or P c .

[0019] The multi-stage pressure regulating device 200 includes a valve body 210, a valve core assembly and a pressure regulating spring 290; the valve core assembly includes: a first valve core assembly 220, a second valve core assembly 250, and a third valve core assembly 270, wherein the first valve core assembly 220, the second valve core assembly 250, the third valve core assembly 270 and the pressure regulating spring 290 are sequentially arranged in the valve body 210, wherein the first valve core assembly 220, the second valve core assembly 250, and the third valve core assembly 270 separate the interior of the valve body 210 into four independent closed chambers: A closed chamber 230, B closed chamber 240, C closed chamber 260 and D closed chamber 280, and the pressure regulating spring 290 is arranged in the D closed chamber 280. The multi-stage pressure regulating device 200 also includes three oil inlets P respectively communicating with the A closed chamber 230, the B closed chamber 240, and the C closed chamber 260 a ’ , P b ’ and P c ’ , one oil return port R and four control oil ports P a ’’ , P b ’’ , P c ’’ and P r .

[0020] The first oil circuit outlet P of the oil circuit on-off control device 100 a By P a -P a ’ The oil circuit 320 is connected to the first oil inlet P of the multi-stage pressure regulating device 200. a ’ Connect, second oil circuit outlet P b Through oil line P b -P b ’ 330 and the second oil inlet P of the multi-stage pressure regulating device 200 b ’ Connect, third oil circuit outlet P c Through oil line P c -P c ’ 340 and the third oil inlet P of the multi-stage pressure regulating device 200 c ’ The four closed chambers of the multi-stage pressure regulating device 200 are, from left to right, closed chamber A 230, closed chamber B 240, closed chamber C 260 and closed chamber D 280. The closed chamber A 230 is connected to the first oil inlet port P a ’ The B closed cavity 240 is connected to the second oil inlet P b’ The C closed cavity 260 is connected to the third oil inlet P c ’ The D closed chamber 280 is communicated with the oil tank 400 through the oil return port R.

[0021] The first control oil port P of the multi-stage pressure regulating device 200 a ’’ By P a ’’ -P K The oil passage 350 and the oil port P of the hydraulic pump swash plate variable mechanism follower chamber 600 k Connect, the second control oil port P b ’’ By P b ’’ -P K The oil circuit 360 and the P of the swash plate variable mechanism follower chamber 600 k The third control oil port P c ’’ By P c ’’ -P K The oil circuit 370 and the P of the swash plate variable mechanism follower chamber 600 k The fourth control oil port P r By P r -P K Oil circuit 380 and P of the swash plate variable mechanism follower chamber k The oil return port R is connected to the oil tank 400.

[0022] The multi-stage pressure regulating device 200 is divided into three pressure levels, each level corresponds to a working pressure P. When the closed chamber A 230, the closed chamber B 240, and the closed chamber C 260 are connected to the P port of the hydraulic pump high-pressure outlet oil circuit 500 through the oil circuit on-off control device 100, the corresponding working pressures of the hydraulic pump are P A , P B , P C , where the relationship P is satisfied A ﹤P B ﹤P C .

[0023] The working principle and control method of the multi-stage pressure regulating control device of the embodiment of the present invention are as follows: 1. When the aircraft is in a low-pressure load flight state, the left electromagnet 110 and the right electromagnet 140 of the oil circuit on-off control device 100 are not energized. Under the joint action of the left spring 120 and the right spring 130, the oil inlet P0 is connected to the second oil circuit outlet P0 through the internal oil circuit. b Connected, the first oil outlet P a , the third oil outlet Pc The high-pressure oil P from the high-pressure outlet oil circuit passes through P0-P b Oil circuit, P b -P b ’ The oil path 330 enters the B closed chamber 240 of the multi-stage pressure regulating device 200 , and acts on the left side of the B valve core 251 and the B push rod 252 and the right side of the A valve core 221 and the A push rod 222 .

[0024] a) When the pressure of the high pressure oil P does not reach the set pressure P B When the pressure regulating spring 290 is applied, the valve core B 251 connects the B closed chamber 240 to the second control oil port P b ’’ The B closed chamber 240 is not in communication with the swash plate variable mechanism follower chamber 600, and the A closed chamber 230 is not in communication with the first control oil port P a ’’ , C closed chamber 260 and the third control oil port P c ’’ The oil in the swash plate variable mechanism follower chamber 600 enters the D closed chamber 280 through the Pr-Pk oil circuit 380, and flows back to the oil tank 400 through the oil return port R. The swash plate is in a large angle state, and the hydraulic pump is at pressure P B Working under the pressure of P B The hydraulic energy; b) When the pressure of the high-pressure oil P reaches the set pressure P B When the hydraulic pressure overcomes the action of the pressure regulating spring 290, the valve core B 251 and the push rod B 252 move to the right, and the B closed chamber 240 is connected to the second control oil port P b ’’ The port is connected, that is, the B closed chamber 240 is connected through P b ’’ -Pk oil circuit 360 communicates with the swash plate variable mechanism follower chamber 600, and A closed chamber 230 communicates with the first control oil port P a ’’ , C closed chamber 260 and the second control oil port P c ’’ , D closed cavity 280 and the fourth control oil port P r The high-pressure oil P of the high-pressure outlet oil circuit 500 enters the swash plate variable mechanism follower chamber 600, pushing the swash plate to reduce its angle until it drops to zero. The swash plate is in a zero angle state, and the hydraulic pump is at a pressure of P. B Working under the condition of stopping supplying hydraulic energy to the hydraulic system, the hydraulic pump realizes the function of constant pressure variable.

[0025] 2. When the aircraft is in a high-voltage load flight state, the left electromagnet 110 of the oil circuit on-off control device 100 is powered off, the right electromagnet 140 is powered on, and the oil inlet P0 is connected to the third oil circuit outlet P c Connected, the first oil outlet P a , Second oil outlet P b are isolated, and the high-pressure oil P from the high-pressure outlet oil circuit 500 passes through P0-P c Oil circuit, P c -P c ’ The oil path 340 enters the C closed chamber 260 of the multi-stage pressure regulating device 200 , and acts on the left side of the C valve core 271 and the C push rod 272 and the right side of the B valve core 251 and the B push rod 252 .

[0026] a) When the pressure of the high pressure oil P does not reach the set pressure P C When the pressure regulating spring 290 is applied, the C valve core 271 connects the C sealing chamber 260 with the third control oil port P c ’’ The port is isolated, that is, the C closed chamber 260 is not in communication with the swash plate variable mechanism follower chamber 600, and the A closed chamber 230 is not in communication with the first control oil port P a ’’ , B closed cavity 240 and the second control oil port P b ’’ The oil in the swash plate variable mechanism follower chamber 600 enters the D closed chamber 280 through the Pr-Pk oil circuit 380, and flows back to the oil tank 400 through the oil return port R. The swash plate is in a large angle state, and the hydraulic pump is at a pressure of P C Working under the pressure of P C The hydraulic energy; b) When the pressure of the high-pressure oil P reaches the set pressure P C When the hydraulic pressure overcomes the action of the pressure regulating spring 290, the C valve core 271 and the C push rod 272 move to the right, and the C closed chamber 260 is connected to the third control oil port P c ’’ Connected, that is, C closed chamber 260 through P c ’’ -Pk oil circuit 370 communicates with the swash plate variable mechanism follower chamber 600, and A closed chamber 230 communicates with the first control oil port P a ’’ , B closed cavity 240 and the second control oil port P b ’’ , D closed cavity 280 and the fourth control oil port P r The high-pressure oil P of the high-pressure outlet oil circuit 500 enters the swash plate variable mechanism follower chamber 600, pushing the swash plate to reduce its angle until it drops to zero. The swash plate is in a zero angle state, and the hydraulic pump is at a pressure of P.C Working under the condition of stopping supplying hydraulic energy to the hydraulic system, the hydraulic pump realizes the function of constant pressure variable.

[0027] 3. When the hydraulic pump or electric pump of the aircraft engine is started, the left electromagnet 110 of the oil circuit on-off control device 100 is energized, the right electromagnet 140 is de-energized, and the oil inlet P0 is connected to the first oil circuit outlet P a Connected, the second oil outlet P b , the third oil outlet P c are isolated, and the high-pressure oil P from the high-pressure outlet oil circuit 500 passes through P0-P a Oil circuit, P a -P a ’ The oil passage 320 enters the A closed chamber 230 of the multi-stage pressure regulating device 200 , and acts on the left side of the A valve core 221 and the A push rod 222 .

[0028] a) When the pressure of the high pressure oil P does not reach the set pressure P A When the pressure regulating spring 290 is applied, the valve core A 221 connects the closed chamber A 230 to the first control oil port P a ’’ The A closed chamber 230 is not in communication with the swash plate variable mechanism follower chamber 600, and the B closed chamber 240 is not in communication with the second control oil port P b ’’ , C closed chamber 260 and the third control oil port P c ’’ The oil in the swash plate variable mechanism follower chamber 600 enters the D closed chamber 280 through the Pr-Pk oil circuit 380, and flows back to the oil tank 400 through the oil return port R. The swash plate is in a large angle state, and the hydraulic pump is at pressure P A Working under the pressure of P A The hydraulic energy; b) When the pressure of the high-pressure oil P reaches the set pressure P A When the hydraulic pressure overcomes the action of the pressure regulating spring 290, the valve core A 221 and the push rod A 222 move to the right, and the closed chamber A 230 is connected to the first control oil port P a ’’ Connected, that is, A closed chamber 230 through P a ’’ -Pk oil circuit 350 communicates with the swash plate variable mechanism follower chamber 600, and B closed chamber 240 communicates with the second control oil port P b ’’ , C closed chamber 260 and the third control oil port P c ’’ , D closed cavity 280 and the fourth control oil port P rThere is no communication. The high-pressure oil P in the high-pressure outlet oil circuit 500 enters the follow-up chamber 600 of the swashplate variable mechanism, pushing the swashplate to reduce its angle until it drops to zero. The swashplate is in the zero-angle state, and the hydraulic pump operates under the pressure P A and stops providing hydraulic energy to the hydraulic system, realizing the constant-pressure variable function of the hydraulic pump.

[0029] P a ’’ -P K In the three oil circuits of oil circuit 350, P b ’’ -P K In the three oil circuits of oil circuit 360, P c ’’ -P K In the three oil circuits of oil circuit 370, when there is a high-pressure outlet pressure P in any one of the oil circuits, that is, when the A closed chamber 230 is connected to the first control oil port P a ’’ and the B closed chamber 240 is connected to the second control oil port P b ’’ and the C closed chamber 260 is connected to the third control oil port P c ’’ As long as there is one connection, the fourth control oil port P r and the D closed chamber 280 are both in a disconnected state, and P r -P k Oil circuit 380 is not connected to the D closed chamber 280. When and only when P a ’’ -P K In the three oil circuits of oil circuit 350, P b ’’ -P K In the three oil circuits of oil circuit 360, P c ’’ -P K The pressures in the three oil circuits of oil circuit 370 are respectively lower than the corresponding P A 、P B 、P C That is, when the A closed chamber 230 is not connected to the first control oil port P a ’’ 、the B closed chamber 240 is not connected to the second control oil port P b ’’ 、and the C closed chamber 260 is not connected to the third control oil port P c ’’ In this case, P r -P k Oil circuit 380 is connected to the D closed chamber 280, that is, the P k port is connected to the D closed chamber 280, and the follow-up chamber 600 of the swashplate variable mechanism of the hydraulic pump passes through the P k port, P r -Pk The oil path 380 is in communication with the D closed chamber 280 , and further communicates with the oil tank 400 through the oil return port R.

[0030] The multi-stage pressure regulating control device of the embodiment of the present invention can regulate the pressure of the hydraulic pump according to the flight state of the aircraft. In the high-pressure load flight state, the hydraulic pump is in a high-pressure working state and provides high pressure to the hydraulic system. In the low-pressure load flight state, the hydraulic pump is in a low-pressure working state and provides low pressure to the hydraulic system. At the moment of starting, the hydraulic pump is in the lowest pressure working state, so that the hydraulic pump starts in the lowest power loss mode, reducing the starting burden of the engine and the power supply power on the aircraft.

[0031] In the description of the embodiments of the present invention, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "center", "top", "bottom", "top", "bottom", "inside", "outside", "inner side", "outer side" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the purpose of facilitating the description of the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention. Among them, "inside" refers to an internal or enclosed area or space. "Periphery" refers to the area surrounding a specific component or a specific area.

[0032] In the description of the embodiments of the present invention, the terms "first", "second", "third", and "fourth" are used for descriptive purposes only and are not to be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Thus, a feature defined as "first", "second", "third", and "fourth" may explicitly or implicitly include one or more of the features. In the description of the present invention, unless otherwise specified, "multiple" means two or more.

[0033] In the description of the embodiments of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "install", "connect", "connect", and "assemble" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a direct connection, or an indirect connection through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0034] In the description of the embodiments of the present invention, specific features, structures, materials or characteristics may be combined in a suitable manner in any one or more embodiments or examples.

[0035] In the description of the embodiments of the present invention, it should be understood that "-" and "~" represent the range between two values, and the range includes the endpoints. For example: "AB" represents a range greater than or equal to A and less than or equal to B. "A~B" represents a range greater than or equal to A and less than or equal to B.

[0036] In the description of the embodiments of the present invention, the term "and / or" herein is merely a description of the association relationship of associated objects, indicating that three relationships may exist. For example, A and / or B may represent: A exists alone, A and B exist at the same time, and B exists alone. In addition, the character " / " herein generally indicates that the associated objects before and after are in an "or" relationship.

[0037] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A multi-stage pressure regulating control device for an aviation hydraulic pump, characterized in that: include: an oil circuit on-off control device, which is connected to the high-pressure outlet oil circuit of the hydraulic pump and is used to selectively connect or isolate oil circuits of different pressure levels according to the flight status of the aircraft; a multi-stage pressure regulating device, which is connected to the oil circuit on-off control device and is used to adjust the working pressure of the hydraulic pump to a corresponding pressure level according to the selected oil circuit; Wherein, the multi-stage pressure regulating device includes at least three closed chambers, each of which corresponds to a different working pressure level, and each closed chamber is connected to the follower chamber of the hydraulic pump swash plate variable mechanism through an oil circuit.

2. The multi-stage pressure regulating control device for an aviation hydraulic pump according to claim 1, characterized in that: The oil circuit on-off control device includes a left electromagnet, a right electromagnet, a left spring, a right spring, an oil inlet and a plurality of oil circuit outlets. The oil inlet is connected to the high-pressure outlet oil circuit of the hydraulic pump through the oil circuit. Each oil circuit outlet is respectively connected to a closed chamber of the multi-stage pressure regulating device. The oil inlet and one of the oil circuit outlets are selectively connected by controlling the power-on state of the left electromagnet and the right electromagnet.

3. The multi-stage pressure regulating control device for an aviation hydraulic pump according to claim 1, characterized in that: The multi-stage pressure regulating device also includes a pressure regulating spring and a valve core assembly. The valve core assembly moves under the action of the pressure regulating spring according to the pressure change of the oil circuit, thereby selectively connecting one of the closed chambers to the follower chamber of the hydraulic pump variable mechanism.

4. The multi-stage pressure regulating control device for an aviation hydraulic pump according to claim 3, characterized in that: The multi-stage pressure regulating device forms four closed chambers through multiple valve core components, which are A closed chamber, B closed chamber, C closed chamber and D closed chamber from left to right. The A closed chamber, B closed chamber, C closed chamber and D closed chamber are respectively connected to the hydraulic pump swash plate variable mechanism follower chamber through the oil circuit. The A closed chamber, B closed chamber and C closed chamber are respectively connected to an oil circuit outlet of the oil circuit on-off control device, and the D closed chamber is connected to the oil tank through the oil return port. When the A closed chamber, B closed chamber and C closed chamber are respectively connected to the hydraulic pump high-pressure outlet oil circuit through the oil circuit on-off control device, the corresponding hydraulic pump working pressures are P a , P b , P c , which satisfies the relationship P a ﹤P b ﹤P c .

5. The multi-stage pressure regulating control device for an aviation hydraulic pump according to claim 4, characterized in that: Each of the valve core components includes a valve core and a push rod. The pressure regulating spring applies force to the valve core through the push rod to make the valve core move in the valve body.

6. The multi-stage pressure regulating control device for an aviation hydraulic pump according to claim 1, characterized in that: The oil circuit on-off control device and the multi-stage pressure regulating device are designed as modular structures and can be customized according to different aircraft models and hydraulic system requirements.

7. A control method using the multi-stage pressure regulating control device for an aviation hydraulic pump according to any one of claims 1 to 6, characterized in that: include: S1 selectively controls the energizing state of the electromagnet of the oil circuit on-off control device according to the flight state of the aircraft, so as to connect or isolate oil circuits of different pressure levels; S2 adjusts the working pressure of the hydraulic pump to a corresponding pressure level through the multi-stage pressure regulating device according to the selected oil circuit.

8. The control method according to claim 7, characterized in that: Also includes: When the hydraulic pump or electric pump of the aircraft engine is started, the oil circuit on-off control device is controlled to connect the oil circuit with the lowest pressure level, so that the hydraulic pump is started in the lowest power loss mode.

9. The control method according to claim 8, characterized in that: The working pressure of the hydraulic pump is monitored, and when the working pressure reaches a set value, the working pressure of the hydraulic pump is adjusted by the multi-stage pressure regulating device to keep it constant.

Images