Small Aeronautical Electromagnetic Temperature-Flow Valve

Abstract

The present invention relates to a small aviation electromagnetic temperature-flow valve. An electromagnetic hydraulic lock and a spool valve assembly are respectively installed in the valve body of the temperature-flow valve. The oil inlet end of the electromagnetic hydraulic lock is connected to the oil inlet P, and the oil outlet end is connected to the control oil circuit H. The control oil circuit H is connected to the main valve oil inlet end of the spool valve assembly or the oil return oil circuit of the spool valve assembly. The electromagnetic hydraulic lock consists of a valve element assembly and an electromagnet. The coil assembly in the electromagnet is connected to a push rod through a movable iron core. The push rod is placed in the valve element assembly. An inner steel ball seat and an outer steel ball seat are provided in the valve element assembly body. A guide seat is provided below the outer steel ball seat. A push rod is provided between the inner steel ball seat and the outer steel ball seat, and a steel ball is provided between the inner steel ball seat and the push rod. The spool valve assembly consists of a valve core, a valve body, a valve sleeve and a piston. The valve body passes through the valve sleeve piston and the valve core. The present invention can be installed in the oil circuit of a small unmanned aerial vehicle, and can solve the technical problem that the small unmanned aerial vehicle is prone to high-altitude oil circuit condensation during flight, which in turn leads to no power output of the aircraft.

Description

Technical Field

[0001] The invention relates to an aviation solenoid valve, in particular to a flow regulating valve capable of rapidly increasing the oil temperature of an aircraft hydraulic system under low-temperature and extreme cold conditions. Background Art

[0002] Under the condition of unchanged flight altitude, due to the limitation of take-off weight, small UAVs have adopted streamlined measures for various onboard equipment. The oil circuit is smaller than that of normal aircraft, but it is easy to produce condensation of high-altitude oil circuits during actual flight, which leads to no power output of the aircraft. Chinese patent publication number CN104632741B discloses a warm flow system of a hydraulic ram air turbine (RAT). When the RAT is in a standby non-working state, the valve core is in a closed state under the action of the preload of the spring. At this time, the high-pressure oil of the aircraft hydraulic system enters the RAT hydraulic pump from A through the throttle hole on the valve core, and returns to the hydraulic system through the gaps of the hydraulic pump to the low-pressure housing cavity. This "warm flow" can keep the RAT hydraulic pump in a "hot backup" state at all times. When the RAT is started, the high-pressure oil it outputs can overcome the spring preload, open the valve core, enter the aircraft hydraulic system, and provide emergency hydraulic energy for the aircraft. The invention can significantly improve the starting speed of hydraulic RAT in high-altitude and low-temperature environments, significantly increase the survival rate of the aircraft, and can be applied to different types of hydraulic airborne ram air turbines (RAT). However, the warm flow system has a complex structure and a large volume, and cannot be applied to small drones.

[0003] In view of the above problems, it is necessary to add a small aviation temperature flow valve in the oil circuit. Summary of the invention

[0004] In order to ensure that the oil circuit of an aircraft does not condense at high altitudes and to ensure that no additional weight of the aircraft is added, the present invention provides a small aviation electromagnetic temperature flow valve, which can quickly increase the oil temperature of the aircraft hydraulic system.

[0005] To achieve the above object, the technical solution of the present invention is as follows:

[0006] A small aviation electromagnetic temperature flow valve includes an electromagnetic hydraulic lock and a spool valve assembly. The electromagnetic hydraulic lock and the spool valve assembly are respectively installed in the valve body. The oil inlet end of the electromagnetic hydraulic lock is connected to the oil inlet P, and the oil outlet end is connected to the control oil circuit H. The control oil circuit H is connected to the main valve oil inlet end of the spool valve assembly or the oil return oil circuit of the spool valve assembly. The electromagnetic hydraulic lock consists of a valve element assembly and an electromagnet. The coil assembly in the electromagnet is connected to a push rod through a movable iron core. The push rod is placed in the valve element assembly. An inner steel ball seat and an outer steel ball seat are arranged in the valve element assembly body. A guide seat is arranged under the outer steel ball seat. A push rod is arranged between the inner steel ball seat and the outer steel ball seat, and a steel ball is arranged between the inner steel ball seat and the push rod. The spool valve assembly includes a valve sleeve, a spool and a piston. The piston and the spool are connected through the valve sleeve in the valve body.

[0007] Further, after the electromagnetic hydraulic lock is powered on, the push rod pushes the steel ball onto the sealing ring belt of the inner steel ball seat, closing the valve in the valve element assembly, and communicating the control oil circuit H of the main valve with the oil return. After the electromagnetic hydraulic lock is powered off, the steel ball is pressed onto the sealing ring belt of the outer steel ball seat under the action of hydraulic pressure, opening the valve in the valve element assembly, and connecting the control oil circuit H of the main valve with the oil inlet P.

[0008] Further, when the control oil circuit H is connected to the oil inlet P, the valve of the spool valve assembly closes, and the oil inlet of the small aviation temperature flow valve is cut off. When the control oil circuit H is connected to the oil return, the valve of the spool valve assembly opens, and the oil inlet of the small aviation temperature flow valve opens. Further, a safety valve is also installed in the valve body, and the electromagnetic hydraulic lock is connected in parallel with the safety valve.

[0009] Further, the safety valve consists of a housing, a spring, a small ball and a base. The base is installed in the housing, the small ball is arranged on the base, and the small ball is connected to the spring to provide overflow protection for the system pressure in the power-off situation.

[0010] Further, an adjustable orifice is also arranged in the valve body. The adjustable orifice consists of a rotary piston and a locking screw. The rotary piston is connected to the locking screw, and the rotary piston is adjusted through the locking screw.

[0011] The beneficial effects of the present invention are as follows:

[0012] The present invention can be installed in the oil circuit of a small unmanned aerial vehicle, and can solve the technical problem that the oil circuit in the air is prone to condensation during the flight of the small unmanned aerial vehicle, which may lead to the loss of power output of the aircraft. When powered on, the electromagnet generates suction, the push rod closes the valve, the control oil circuit of the main valve is connected to the oil return, the valve opens, and the oil inlet of the temperature flow valve opens. The adjustable orifice adjusts the rotary piston through the screw to limit the required flow rate, and can automatically adjust the temperature of the oil in the main flow channel after takeoff. When powered off, the solenoid valve closes, and the safety valve is used for system pressure protection, overflowing the excess flow through the safety valve. Description of the Drawings

[0013] Figure 1 is the top view of the structure of the small aviation electromagnetic temperature flow valve of the present invention;

[0014] Figure 2 is the main sectional view of the structure of the small aviation electromagnetic temperature flow valve of the present invention;

[0015] Figure 3 is the schematic diagram of the small aviation electromagnetic temperature flow valve of the present invention;

[0016] Figure 4 is the sectional view of the structure of the valve flap assembly;

[0017] Figure 5 is the front view of the structure of the adjustable orifice;

[0018] Figure 6 is Figure 5 the sectional view along P-P in

[0019] In the figure: 1 - safety valve, 2 - valve flap assembly, 3 - spool valve assembly, 4 - electromagnet, 5 - adjustable orifice, 6 - electro-hydraulic lock, 21 - inner steel ball seat, 22 - outer steel ball seat, 23 - guide seat, 31 - valve core, 32 - valve body, 33 - valve sleeve, 41 - coil assembly; 42 - movable iron core, 43 - push rod. Specific embodiments

[0020] The present invention will be further described below in conjunction with the accompanying drawings and embodiments.

[0021] As Figures 1 to 3 shown, the small aviation electromagnetic temperature flow valve of the present invention includes a safety valve 1, a spool valve assembly 3, an adjustable orifice 5, and an electro-hydraulic lock 6.

[0022] A safety valve 1, an electro-hydraulic lock 6, and a spool valve assembly 3 are installed in the valve body of the small aviation temperature flow valve, and an adjustable orifice 5 communicating with the spool valve assembly 3 is provided on the valve body. The electro-hydraulic lock 6 is connected in parallel with the safety valve 1. Among them, the oil inlet ends of the electro-hydraulic lock 6 and the safety valve 1 are connected to the inlet oil P, and the oil outlet ends are connected to the control oil circuit H. The control oil circuit H is connected to the main valve oil inlet end of the spool valve assembly 3 or the oil return oil circuit of the spool valve assembly 3.

[0023] As Figure 4As shown in the figure, the electromagnetic hydraulic lock 6 is composed of a valve component 2 and an electromagnet 4. The electromagnet 4 mainly consists of a coil assembly 41, a movable iron core 42, a push rod 43, etc. The coil assembly 41 is connected to the push rod 43 through the movable iron core 42, and the push rod 43 is placed in the valve component 2. The valve component 2 mainly consists of a steel ball, an inner steel ball seat 21, an outer steel ball seat 22, a guide seat 23, etc. An inner steel ball seat 21 and an outer steel ball seat 22 are provided inside the valve component 2 body. A guide seat 23 is provided below the outer steel ball seat 22. A push rod 43 is provided between the inner steel ball seat 21 and the outer steel ball seat 22, and a steel ball is provided between the inner steel ball seat 21 and the push rod 43.

[0024] After the electromagnetic hydraulic lock is powered on and operates, the push rod 43 of the electromagnet pushes the steel ball onto the sealing ring belt of the inner steel ball seat 21, and the valve in the valve component 2 closes, and the control oil circuit H of the main valve communicates with the return oil; after the electromagnetic hydraulic lock is powered off, under the action of the hydraulic pressure, the steel ball is pressed onto the sealing ring belt of the outer steel ball seat 22 again, and the valve in the valve component 2 opens, and the control oil circuit H of the main valve is connected to the inlet oil P.

[0025] The spool valve assembly 3 mainly consists of a spool 31, a valve body 32, a valve sleeve 33 and a piston. The piston and the spool 31 are connected inside the valve body 32 through the valve sleeve 33.

[0026] When the control oil circuit H is connected to the inlet oil P, the valve of the spool valve assembly 3 closes, and the inlet oil of the small aviation flow valve is cut off; when the control oil circuit H is connected to the return oil, the valve of the spool valve assembly 3 opens, and the inlet oil of the small aviation flow valve opens.

[0027] As Figure 5 shown in Figure 6, the adjustable orifice 5 mainly consists of a rotating piston and a locking screw. The rotating piston is connected to the locking screw, and the rotating piston can be adjusted by the locking screw to limit different orifice sizes according to different aircraft.

[0028] The safety valve 1 mainly consists of a housing, a spring, a small ball and a base. A base is installed inside the housing, a small ball is provided on the base, and the small ball is connected to the spring. It provides overflow protection for the system pressure in the power-off situation.

[0029] The electromagnet is responsible for receiving electrical signals and converting them into mechanical motion, so that the electromagnet generates a certain suction force, and the push rod of the electromagnet makes corresponding movements; the valve component is the pilot control switch of the flow valve. When the electromagnet is powered off, the valve opens, and the control oil circuit of the main valve is connected to the inlet oil. When the electromagnet is powered on, the valve closes, and the main valve control oil circuit is connected to the return oil; the spool valve component is the actuator of the flow valve. When the control oil circuit is connected to the inlet oil, the valve closes, and the inlet oil of the small aviation flow valve is cut off. When the control oil circuit is connected to the return oil, the valve opens; the function of the adjustable orifice is that when the small aviation flow valve is powered on, the spool valve component opens the inlet window, and the flow rate is adjusted through the adjustable orifice; the safety valve is that when the flow valve is powered off, the safety valve provides overflow protection for the system pressure.

Claims

1. A small aviation electromagnetic temperature and flow valve, comprising an electromagnetic hydraulic lock and a spool valve assembly, Characterized in that: The electromagnetic hydraulic lock and the spool valve assembly are respectively installed in the valve body. The oil inlet end of the electromagnetic hydraulic lock is connected to the oil inlet P, and the oil outlet end is connected to the control oil circuit H. The control oil circuit H is connected to the main valve oil inlet end of the spool valve assembly or the oil return oil circuit of the spool valve assembly; The electromagnetic hydraulic lock consists of a valve element assembly and an electromagnet. The coil assembly in the electromagnet is connected to a push rod through a movable iron core. The push rod is placed in the valve element assembly. An inner steel ball seat and an outer steel ball seat are arranged in the valve element assembly body. A guide seat is arranged below the outer steel ball seat. A push rod is arranged between the inner steel ball seat and the outer steel ball seat. The spool valve assembly includes a valve sleeve, a spool and a piston. The piston and the spool are connected through the valve sleeve in the valve body; A safety valve is also installed in the valve body. The electromagnetic hydraulic lock and the safety valve are connected in parallel; An adjustable orifice is also provided in the valve body; The safety valve consists of a housing, a spring, a small ball and a base. The base is installed in the housing. A small ball is arranged on the base. The small ball is connected to the spring to provide overflow protection for the system pressure in the power-off state; When the electromagnetic hydraulic lock is energized, the push rod pushes the steel ball onto the sealing ring band of the inner steel ball seat, closing the valve in the valve element assembly and connecting the control oil circuit H and the oil return of the main valve; When the electromagnetic hydraulic lock is de-energized, the steel ball is pressed onto the sealing ring band of the outer steel ball seat under the action of hydraulic pressure, opening the valve in the valve element assembly and connecting the control oil circuit H of the main valve to the oil inlet P; When the control oil circuit H is connected to the oil inlet P, the valve of the spool valve assembly closes, cutting off the oil inlet of the small aviation temperature and flow valve; When the control oil circuit H is connected to the oil return, the valve of the spool valve assembly opens, opening the oil inlet of the small aviation temperature and flow valve.

2. The small aviation electromagnetic temperature and flow valve according to claim 1, Characterized in that: The adjustable orifice consists of a rotary piston and a locking screw. The rotary piston is connected to the locking screw, and the rotary piston is adjusted through the locking screw.

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