A new integrated auxiliary power unit for an aircraft

Abstract

The application discloses a novel integrated auxiliary power device for an aircraft, a valve body and an auxiliary power assembly arranged at two ends of the valve body, wherein the auxiliary power assembly comprises a high-pressure cylinder, an air cavity, a high-pressure cavity, an electromagnetic valve, an oil storage cylinder, a logic valve, an oil storage cavity, a high-pressure piston, a low-pressure piston, a logic one-way valve and an electromagnetic one-way valve, the high-pressure cylinder and the oil storage cylinder are respectively sleeved at the two ends of the valve body, the air cavity is arranged on the inner wall of the high-pressure cylinder, and the air cavity is arranged on the inner wall of the valve body. In the application, the electromagnetic valve, the logic valve and the one-way valve with different functions are integrated in the valve body, the accumulator and the oil storage unit composed of the high-pressure cylinder and the oil storage cylinder are utilized, the structure is compact, the installation space is reduced, the required power is reduced, the application working condition is wider, only a small-power unit is needed, large-power working condition can be realized, pilot control is adopted for large-flow switching, and large-flow electromagnetic switching impact is avoided.

Description

Technical Field

[0001] This invention belongs to the field of energy storage technology, specifically a novel integrated auxiliary power device for aircraft. Background Technology

[0002] An accumulator is an energy storage device in a hydraulic and pneumatic system. It converts the energy in the system into compressed energy or potential energy and stores it at the appropriate time. When the system needs it, it converts the compressed energy or potential energy into hydraulic or pneumatic energy and releases it to replenish the system. When the system pressure increases instantaneously, it can absorb this part of the energy to ensure that the pressure of the entire system is normal.

[0003] Traditional auxiliary power units use accumulators, which do not integrate related valves and have separate oil tanks, requiring a large installation space. In certain working conditions where installation space is limited, traditional designs cannot meet the requirements, necessitating a new type of auxiliary power unit. Existing auxiliary power units mainly provide instantaneous high pressure and high flow power to the actuator. To ensure stability and working efficiency under various conditions, the accumulator and oil storage unit are often set up separately with various valves and pipelines, resulting in poor integration and an inability to systematically reduce size, thus increasing the overall installation and maintenance difficulty. Summary of the Invention

[0004] The technical solution adopted in this invention is as follows: A novel integrated auxiliary power unit for aircraft, comprising:

[0005] Valve body;

[0006] An auxiliary power assembly is located at both ends of the valve body. The auxiliary power assembly includes a high-pressure cylinder, an air chamber, a solenoid valve, an oil reservoir, a logic valve, an oil reservoir, a high-pressure piston, a low-pressure piston, a logic check valve, and a solenoid check valve. The high-pressure cylinder and the oil reservoir are respectively fitted onto both ends of the valve body. The air chamber is located on the inner wall of the high-pressure cylinder and the valve body. The oil reservoir is located on the inner wall of the oil reservoir. The high-pressure piston is slidably embedded in the inner wall of the high-pressure cylinder. A cotter pin is located on the outer wall of one end of the high-pressure piston. The low-pressure piston is fitted onto the outer wall of one end of the high-pressure piston and slidably embedded in the inner wall of the oil reservoir. The solenoid valve, the logic valve, the logic check valve, and the solenoid check valve are all threadedly connected to the outer circumference of the valve body. The solenoid valve and the logic check valve are interconnected.

[0007] Furthermore, the outer wall of the high-pressure piston is provided with two high-pressure wear-resistant rings through a slot, and the center of the outer wall of the high-pressure piston is provided with a high-pressure main seal through a slot.

[0008] Furthermore, two low-pressure wear-resistant rings are embedded in the inner wall axis of the valve body through a slot, two low-pressure main seals are embedded in the inner wall axis of the valve body through a slot, and a high-pressure secondary seal and a retaining ring are embedded in the inner wall side of the valve body near the high-pressure piston through a slot.

[0009] Furthermore, the inner wall of the low-pressure piston is fitted with a low-pressure secondary seal through a slot.

[0010] Furthermore, a washer is slidably fitted on one end of the high-pressure piston, and a nut is threadedly connected to one end of the high-pressure piston.

[0011] Furthermore, the outer circumferential surface of the valve body is threaded with a first connector, a second connector, and a third connector.

[0012] Furthermore, a logic process plug is threadedly connected to one side of the outer wall of the valve body, and the logic process plug is interconnected with the logic valve through the valve body.

[0013] Furthermore, an electromagnetic process plug is threadedly connected to one side of the outer wall of the valve body, and the electromagnetic process plug is interconnected with the electromagnetic check valve through the valve body.

[0014] Furthermore, one end of the high-pressure cylinder is threadedly connected to an air inlet connector.

[0015] Furthermore, multiple connecting screws are provided through the outer walls of the adjacent ends of the high-pressure cylinder and the oil storage cylinder, and an elastic washer is fitted on one end of each connecting screw, and one end of each connecting screw is threaded to the edge of the outer wall at both ends of the valve body.

[0016] In summary, due to the adoption of the above technical solution, the beneficial effects of the present invention are:

[0017] In this invention, because it integrates solenoid valves, logic valves and check valves with different functions into the valve body, and utilizes an accumulator and oil storage unit composed of a high-pressure cylinder and an oil storage cylinder, the structure is compact, reducing installation space and power requirements, and the application conditions are more extensive. Only a small power unit is needed to achieve high power conditions. At the same time, pilot control is adopted for large flow reversal to avoid the impact of large flow electromagnetic reversal. Attached Figure Description

[0018] Figure 1 This is a schematic diagram of the hydraulic connection principle of the present invention (solenoid valve de-energized state);

[0019] Figure 2 This is a schematic diagram of the hydraulic connection principle of the present invention (solenoid valve power supply state);

[0020] Figure 3 This is the front view of the present invention;

[0021] Figure 4 This is a cross-sectional view of the present invention;

[0022] Figure 5 This is a side sectional view of the present invention;

[0023] Figure 6 This is a cross-sectional view of the electromagnetic check valve of the present invention.

[0024] The diagram shows the following components: 1. High-pressure cylinder; 2. Inflation connector; 3. High-pressure connecting screw; 4. Elastic washer; 5. Valve body; 6. Solenoid valve; 8. Oil reservoir; 9. Logic process plug; 10. Logic valve; 11. High-pressure piston; 12. High-pressure main seal; 13. High-pressure wear ring; 14. High-pressure secondary seal; 15. Retaining ring; 16. Low-pressure wear ring; 17. Low-pressure main seal; 18. Low-pressure secondary seal; 19. Low-pressure piston; 20. Washer; 21. Nut; 22. Cotter pin; 23. First connector; 24. Second connector; 25. Third connector; 26. Logic check valve; 27. Solenoid process plug; 28. Solenoid check valve; 101. Air chamber; 501. High-pressure chamber; 801. Oil reservoir. Detailed Implementation

[0025] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the invention.

[0026] This invention is intended to explain the invention and is not intended to limit the invention.

[0027] Example 1

[0028] Refer to the attached drawings in the instruction manual. Figures 1-6 A novel integrated auxiliary power unit for aircraft, comprising:

[0029] Valve body 5;

[0030] An auxiliary power assembly is located at both ends of the valve body 5. This auxiliary power assembly includes a high-pressure cylinder 1, an air chamber 101, a high-pressure chamber 501, a solenoid valve 6, an oil reservoir 8, a logic valve 10, an oil reservoir 801, a high-pressure piston 11, a low-pressure piston 19, a logic check valve 26, and a solenoid check valve 28. The high-pressure cylinder 1 and the oil reservoir 8 are respectively fitted onto both ends of the valve body 5. The air chamber 101 is located on the inner wall of the high-pressure cylinder 1 and the inner wall of the valve body 5. The oil reservoir 801 is located on the inner wall of the oil reservoir 8. Piston 11 is slidably embedded in the inner wall of high-pressure cylinder 1. Cotter pin 22 is located on the outer wall of one end of high-pressure piston 11. Low-pressure piston 19 is sleeved on the outer wall of one end of high-pressure piston 11 and slidably embedded in the inner wall of oil reservoir 801. Solenoid valve 6, logic valve 10, logic check valve 26, and solenoid check valve 28 are all threadedly connected to the outer circumference of valve body 5. Solenoid valve 6 and logic check valve 26 are interconnected, and logic valve 10 and solenoid check valve 28 are interconnected. (Refer to the attached drawings in the instruction manual.) Figure 1 Description and interface definitions: Port P connects to the hydraulic system's oil supply port; Port D connects to the hydraulic system's oil return port; Port G connects to the actuator's high-pressure port; Port H connects to the actuator's oil return port. Refer to the accompanying diagram in the manual. Figure 1 Description and interface definitions: Port P connects to the hydraulic system's oil supply port; Port D connects to the hydraulic system's oil return port; Port G connects to the actuator's high-pressure port; Port H connects to the actuator's oil return port. Refer to the accompanying diagram in the manual. Figure 1 The novel auxiliary power unit mainly consists of a one-way valve, an accumulator (the accumulator is composed of a high-pressure cylinder 1, an air chamber 101, a high-pressure chamber 501, and a high-pressure piston 11), a logic valve 10, a solenoid valve 6, a one-way valve, an oil storage unit (the oil storage unit is composed of a low-pressure piston 19, an oil storage cylinder 8, and an oil storage chamber 801), and related accessories, as described in the accompanying drawings. Figure 1 The description states that when solenoid valve 6 is de-energized, it operates in its lower position. Pilot oil from the right side of logic valve 10 returns to the low-pressure end via solenoid valve 6 and logic check valve 26. After being reset by the spring, logic valve 10 operates in its left position. At this time, high-pressure ports P and G are disconnected, and the hydraulic pump starts, connecting its suction port to port D. The hydraulic pump then draws oil from the reservoir, and the high-pressure oil passes through the check valve to accumulator for energy storage. After energy storage is complete, the pump stops, and logic check valve 26 acts as a check valve. At this point, the accumulator contains the required high-pressure oil. (Refer to the attached diagram in the instruction manual.) Figure 2 The description states that when solenoid valve 6 is energized, it operates in its upper position. At this time, the high-pressure oil in the accumulator supplies pilot oil to logic valve 10 through solenoid valve 6, and logic valve 10 operates in its right position. Simultaneously, the high-pressure oil in accumulator 2 supplies high-pressure oil and instantaneous flow to the actuator through logic valve 10, causing the actuator to operate. The actuator then returns the oil to the storage unit for reuse in the next cycle, forming a closed-loop function. (Refer to the attached diagram in the instruction manual.) Figure 1The description explains that the function of the logic check valve 26 is to prevent the back pressure generated by the return oil from affecting the pilot port of the logic valve 10. The air chamber 101 is formed by the high-pressure cylinder 1 and the high-pressure piston 11, and the high-pressure chamber 501 is formed by the high-pressure cylinder 1, the high-pressure piston 11, and the valve body 5. Wear-resistant rings and seals are used to isolate the air chamber 101 and the high-pressure chamber 501. The oil storage chamber 801 is formed by the oil storage cylinder 8, the low-pressure piston 19, and the valve body 5. All seals are used to seal the hydraulic oil of the new integrated auxiliary power unit to prevent external and internal leakage. Before use, the air chamber 101 is filled with gas at a certain pressure through the air charging connector. Referring to the diagram, when the solenoid valve 6 is de-energized, the hydraulic pump starts, and the pump suction port is connected to port D. At this time, the hydraulic pump draws oil from the oil storage chamber 801, and the high-pressure oil passes through the check valve to store energy in the high-pressure chamber 501. Piston 11 moves to the left, compressing gas to create high pressure. Simultaneously, low-pressure piston 19 moves to the left, discharging oil to supply the pump. After energy storage, the pump stops, and the check valve acts as a check valve. High-pressure chamber 501 contains a certain volume of high-pressure hydraulic oil. When solenoid valve 6 is energized, it operates in its upper position. At this time, the high-pressure oil in high-pressure chamber 501 provides pilot oil to logic valve 10 via solenoid valve 6, and logic valve 10 operates in its right position. The high-pressure oil in high-pressure chamber 501 then provides high-pressure oil and instantaneous flow to the actuator via logic valve 10. The actuator then operates, and high-pressure piston 11 moves to the right, reducing the size of high-pressure chamber 501. Oil storage chamber 801 subsequently expands, and the oil returned to the actuator is stored in the oil storage unit for the next cycle, forming a closed-loop function. (Refer to the attached diagrams in the instruction manual.) Figure 1 The function of setting the logic check valve 26 is to prevent the back pressure generated by the return oil from affecting the pilot port of the logic valve 10.

[0031] Refer to the attached drawings in the instruction manual. Figures 1-6Two high-pressure wear-resistant rings 13 are fitted onto the outer wall of the high-pressure piston 11 through a slot. A high-pressure main seal 12 is fitted onto the center of the outer wall of the high-pressure piston 11 through a slot. Two low-pressure wear-resistant rings 16 are embedded into the inner wall axis of the valve body 5 through a slot. The low-pressure wear-resistant rings 16 ensure the wear resistance of the outer wall of the high-pressure piston 11 and prevent damage that could lead to uneven energy storage. Two low-pressure main seals 17 are embedded into the inner wall axis of the valve body 5 through a slot. A high-pressure secondary seal 14 and a retaining ring 15 are embedded into the inner wall of the valve body 5 near the high-pressure piston 11 through a slot. The high-pressure secondary seal 14 and the retaining ring 15 ensure the sealing of the high-pressure chamber 501. A low-pressure secondary seal 18 is embedded into the inner wall of the low-pressure piston 19 through a slot. A washer 20 is slidably fitted onto one end of the high-pressure piston 11, and a nut is threaded onto one end of the high-pressure piston 11. 21. The outer circumferential surface of the valve body 5 is threaded with a first connector 23, a second connector 24, and a third connector 25, respectively. The first connector 23, the second connector 24, and the third connector 25 facilitate the setting of P, D, G, and H. A logic process plug 9 is threaded on one side of the outer wall of the valve body 5, and the logic process plug 9 is interconnected with the logic valve 10 through the valve body 5. An electromagnetic process plug 27 is threaded on one side of the outer wall of the valve body 5, and the electromagnetic process plug 27 is interconnected with the electromagnetic check valve 28 through the valve body 5. An air filling connector 2 is threaded on one end of the high pressure cylinder 1. Multiple connecting screws 3 are installed through the outer walls of the adjacent ends of the high pressure cylinder 1 and the oil reservoir 8. An elastic washer 4 is fitted on one end of each connecting screw 3, and one end of each connecting screw 3 is threaded to the edge of the outer wall at both ends of the valve body 5.

[0032] The following provides a detailed description of the usage method of a novel integrated auxiliary power unit for aircraft provided by an embodiment of the present invention. The usage method includes the following steps: Interface definition: Port P is connected to the hydraulic system supply port, Port D is connected to the hydraulic system return port; Port G is connected to the high-pressure port of the actuator, and Port H is connected to the return port of the actuator. Refer to the accompanying drawings for details. Figure 1 Description and interface definitions: Port P connects to the hydraulic system's oil supply port; Port D connects to the hydraulic system's oil return port; Port G connects to the actuator's high-pressure port; Port H connects to the actuator's oil return port. Refer to the accompanying diagram in the manual. Figure 1 The novel auxiliary power unit mainly consists of a one-way valve, an accumulator (the accumulator is composed of a high-pressure cylinder 1, an air chamber 101, a high-pressure chamber 501, and a high-pressure piston 11), a logic valve 10, a solenoid valve 6, a one-way valve, an oil storage unit (the oil storage unit is composed of a low-pressure piston 19, an oil storage cylinder 8, and an oil storage chamber 801), and related accessories, as described in the accompanying drawings. Figure 1The description states that when solenoid valve 6 is de-energized, it operates in its lower position. Pilot oil from the right side of logic valve 10 returns to the low-pressure end via solenoid valve 6 and logic check valve 26. After being reset by the spring, logic valve 10 operates in its left position. At this time, high-pressure ports P and G are disconnected, and the hydraulic pump starts, connecting its suction port to port D. The hydraulic pump then draws oil from the reservoir, and the high-pressure oil passes through the check valve to accumulator for energy storage. After energy storage is complete, the pump stops, and logic check valve 26 acts as a check valve. At this point, the accumulator contains the required high-pressure oil. (Refer to the attached diagram in the instruction manual.) Figure 2 The description states that when solenoid valve 6 is energized, it operates in its upper position. At this time, the high-pressure oil in the accumulator supplies pilot oil to logic valve 10 through solenoid valve 6, and logic valve 10 operates in its right position. Simultaneously, the high-pressure oil in accumulator 2 supplies high-pressure oil and instantaneous flow to the actuator through logic valve 10, causing the actuator to operate. The actuator then returns the oil to the storage unit for reuse in the next cycle, forming a closed-loop function. (Refer to the attached diagram in the instruction manual.) Figure 1 The function of setting the logic check valve 26 is to prevent the back pressure generated by the return oil from affecting the pilot port of the logic valve 10.

[0033] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A novel integrated auxiliary power unit for aircraft, characterized in that, include: Valve body (5); An auxiliary power assembly is located at both ends of the valve body (5), wherein: the auxiliary power assembly includes a high-pressure cylinder (1), an air chamber (101), a high-pressure chamber (501), a solenoid valve (6), an oil reservoir (8), a logic valve (10), an oil reservoir (801), a high-pressure piston (11), a low-pressure piston (19), a logic check valve (26), and a solenoid check valve (28). The high-pressure cylinder (1) and the oil reservoir (8) are respectively sleeved at both ends of the valve body (5). 01) The gas chamber (101) is located on the inner wall of the high-pressure cylinder (1), the gas cavity (101) is located on the inner wall of the valve body (5), the oil storage chamber (801) is located on the inner wall of the oil storage cylinder (8), the high-pressure piston (11) is slidably embedded in the inner wall of the high-pressure cylinder (1), the cotter pin (22) is located on the outer wall of one end of the high-pressure piston (11), the low-pressure piston (19) is sleeved on the outer wall of one end of the high-pressure piston (11), and the low-pressure piston (19) is slidably embedded in the oil storage chamber (801). 1) On the inner wall, the solenoid valve (6), logic valve (10), logic check valve (26) and solenoid check valve (28) are all threadedly connected to the outer circumference of the valve body (5). The solenoid valve (6) and logic check valve (26) are interconnected, and the logic valve (10) and solenoid check valve (28) are interconnected. The outer wall of the high-pressure piston (11) is provided with two high-pressure wear-resistant rings (13) through slots. The center of the outer wall of the high-pressure piston (11) is connected to the outer wall of the valve body (5). A high-pressure main seal (12) is provided through a slot; two low-pressure wear-resistant rings (16) are embedded in the inner wall axis of the valve body (5) through a slot; two low-pressure main seals (17) are embedded in the inner wall axis of the valve body (5) through a slot; a high-pressure secondary seal (14) and a retaining ring (15) are respectively embedded in the inner wall of the valve body (5) near the high-pressure piston (11); a low-pressure secondary seal (18) is embedded in the inner wall of the low-pressure piston (19) through a slot.

2. The novel integrated auxiliary power unit for aircraft as described in claim 1, characterized in that: One end of the high-pressure piston (11) is slidably fitted with a washer (20), and one end of the high-pressure piston (11) is threadedly connected with a nut (21).

3. A novel integrated auxiliary power unit for aircraft as described in claim 2, characterized in that: The outer circumferential surface of the valve body (5) is threaded with a first connector (23), a second connector (24) and a third connector (25).

4. A novel integrated auxiliary power unit for aircraft as described in claim 3, characterized in that: The outer wall of the valve body (5) is threaded with a logic process plug (9), and the logic process plug (9) is connected to the logic valve (10) through the valve body (5).

5. A novel integrated auxiliary power unit for aircraft as described in claim 4, characterized in that: An electromagnetic process plug (27) is threadedly connected to one side of the outer wall of the valve body (5), and the electromagnetic process plug (27) is interconnected with the electromagnetic check valve (28) through the valve body (5).

6. A novel integrated auxiliary power unit for aircraft as described in claim 5, characterized in that: One end of the high-pressure cylinder (1) is threadedly connected to an air inlet connector (2).

7. A novel integrated auxiliary power unit for aircraft as described in claim 6, characterized in that: Multiple connecting screws (3) are provided through the outer walls of the high-pressure cylinder (1) and the oil storage cylinder (8) at their respective close ends. Each connecting screw (3) has an elastic washer (4) fitted at one end, and one end of each connecting screw (3) is threaded to the outer wall edge of both ends of the valve body (5).

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