CN216241633U - Hydraulic control system for endurance test equipment of airplane self-pressurization oil tank - Google Patents
Hydraulic control system for endurance test equipment of airplane self-pressurization oil tank Download PDFInfo
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- CN216241633U CN216241633U CN202122799136.1U CN202122799136U CN216241633U CN 216241633 U CN216241633 U CN 216241633U CN 202122799136 U CN202122799136 U CN 202122799136U CN 216241633 U CN216241633 U CN 216241633U
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Abstract
A hydraulic control system for endurance test equipment of an aircraft self-pressurization oil tank comprises a low-pressure oil way and a high-pressure oil way, wherein the low-pressure oil way is provided with an oil supply oil way and an oil return oil way which are connected with an oil return port of the aircraft self-pressurization oil tank; the oil supply oil path comprises an oil pump, an oil supply regulating valve and an overflow regulating valve, the oil supply regulating valve is used for regulating the oil supply amount, one end of the oil supply regulating valve is connected with the oil pump, and the other end of the oil supply regulating valve is connected with the oil return port; the overflow regulating valve is connected with the oil supply regulating valve in parallel and is used for overflowing redundant oil supply to the oil return tank; the oil return oil way comprises a ball valve and an oil return adjusting valve which are connected in series, and the oil return adjusting valve is used for adjusting the oil return amount and discharging the oil return into the oil tank. The hydraulic control reversing valve is replaced by the pneumatic ball valve for reversing, the pneumatic ball valve has the advantages of simple and reliable structure, low cost, easiness in maintenance and the like, particularly, a gradual change process is carried out on the on-off of hydraulic oil in the opening or closing process, the switching impact is relieved in the gradual change process, and the stability of a test system is ensured.
Description
Technical Field
The utility model relates to the technical field of self-pressurization oil tanks, in particular to a hydraulic control system for endurance test equipment of an airplane self-pressurization oil tank.
Background
With the rise of aviation industry in China, the related matched research and test work of airplanes is also developed successively. As an important hydraulic element on the airplane, the self-pressurization oil tank of the airplane is related to the reliability in the whole flying process, so that the requirement on the comprehensive performance of the hydraulic oil tank of the airplane is higher and higher. In order to ensure that the self-pressurization oil tank of the airplane can stably run for a long time in an airplane hydraulic system, the endurance test of the self-pressurization oil tank of the airplane is also important.
Fig. 1 shows a hydraulic control system of a conventional endurance testing device for an aircraft self-pressurization oil tank, in which reference numeral 1 denotes an aircraft self-pressurization oil tank to be tested, reference numeral 2 denotes a connection structure of a high-pressure oil path hydraulic element, and the rest are connection structures of low-pressure oil path hydraulic elements. The piston area in the high-pressure cavity of the aircraft self-pressurization oil tank is small, the piston area in the low-pressure cavity is large, and the high-pressure oil way is used for providing constant high oil pressure for the high-pressure cavity. The low-pressure cavity of the self-pressurization oil tank of the airplane is provided with an oil return port and an oil outlet, wherein the oil outlet is used for pressure relief. The low-pressure oil path provides test oil pressure for the low-pressure cavity through the regulating valve 3 and the hydraulic control reversing valve 4, wherein the hydraulic control reversing valve 4 is used for reversing. Compared with other reversing valves, the hydraulic control reversing valve 4 is more suitable for reversing large-flow hydraulic oil. After the oil way is communicated, the hydraulic control reversing valve 4 supplies oil to the oil return port, so that the piston moves leftwards; after the direction is changed, the hydraulic control reversing valve 4 cuts off the oil supply path, and the piston moves to the right. The piston can reciprocate by repeatedly opening and closing the hydraulic control reversing valve 4, so that the aim of testing the comprehensive performance of the self-pressurization oil tank of the airplane can be achieved.
The existing endurance test equipment has the problems that the hydraulic control reversing valve 4 in the low-pressure oil way needs to be quickly and frequently reversed, the valve core can be driven only by pilot operation of the hydraulic control reversing valve 4 except that the hydraulic control reversing valve is easy to block and damage, and for the hydraulic control reversing valve with a large drift diameter, the elastic force of a valve core reset spring is large, and the valve core can be driven to move only by supplying pilot oil pressure of more than 0.5MPa in the switching process. Therefore, the whole system is greatly vibrated in the switching process, and the stability of the test system and the service life of the self-pressurization oil tank of the airplane are influenced.
SUMMERY OF THE UTILITY MODEL
In order to overcome the defects in the background art, the utility model discloses a hydraulic control system for endurance test equipment of an aircraft self-pressurization oil tank, which adopts the following technical scheme:
a hydraulic control system for endurance test equipment of an aircraft self-pressurization oil tank comprises a low-pressure oil way for supplying oil to a low-pressure cavity of the aircraft self-pressurization oil tank and a high-pressure oil way for supplying oil to a high-pressure cavity of the aircraft self-pressurization oil tank, wherein the low-pressure oil way is provided with an oil supply oil way and an oil return oil way which are connected with an oil return port of the low-pressure cavity; the oil supply oil path comprises an oil pump, an oil supply regulating valve and an overflow regulating valve, the oil supply regulating valve is used for regulating the oil supply amount, one end of the oil supply regulating valve is connected with the oil pump, and the other end of the oil supply regulating valve is connected with the oil return port; the overflow regulating valve is connected with the oil supply regulating valve in parallel and is used for overflowing redundant oil supply to the oil return tank; the oil return oil way comprises a ball valve and an oil return adjusting valve which are connected in series, and the oil return adjusting valve is used for adjusting the oil return amount and discharging the oil return into the oil tank.
According to the technical scheme, the oil supply oil way further comprises an overflow valve, a flowmeter and a pressure sensor, wherein the overflow valve, the flowmeter and the pressure sensor are connected between the oil return port and the oil supply regulating valve.
According to the technical scheme, the oil supply oil path further comprises a refrigerating and heating unit, and the refrigerating and heating unit is connected between the oil pump and the oil supply adjusting valve and used for heating or cooling hydraulic oil.
The technical scheme is further improved, and the ball valve is a pneumatic ball valve; the oil supply regulating valve, the overflow regulating valve and the oil return regulating valve are all pneumatic regulating valves.
Due to the adoption of the technical scheme, the utility model has the following beneficial effects:
compared with the background art, the pneumatic ball valve has the advantages of large force, quick response and easy control. Compared with a hydraulic control reversing valve, the pneumatic ball valve has the advantages of simple and reliable structure, low cost, easiness in maintenance and the like, and the phenomenon that a valve core is stuck does not need to be worried about.
Because the hydraulic control reversing valve is not arranged to realize reversing, pilot oil pressure does not need to be provided for the hydraulic control reversing valve. It is particularly important that the pneumatic ball valve has a gradual change process for the on-off of the hydraulic oil during the opening or closing process, and the gradual change process slows down the switching impact. Compared with a hydraulic control reversing valve, the utility model reduces the vibration of the whole system caused by switching, and ensures the stability of the test system and the service life of the self-pressurization oil tank of the airplane.
Drawings
Fig. 1 is a schematic diagram of a hydraulic control system of a conventional endurance testing device for a self-pressurization oil tank of an aircraft.
FIG. 2 is a schematic diagram of the hydraulic control system of the present invention.
In the figure: 1. an aircraft self-pressurization oil tank; 2. a high-pressure oil path; 3. adjusting a valve; 4. a hydraulic control directional control valve; 5. an oil supply path; 5.1, an oil pump; 5.2, an oil supply regulating valve; 5.3, overflow regulating valve; 5.4, an overflow valve; 5.5, a pressure sensor; 5.6, a refrigerating and heating unit; 5.7, a flow meter; 6. an oil return path; 6.1, a pneumatic ball valve; 6.2 and an oil return regulating valve.
Detailed Description
Preferred embodiments of the present invention are described below with reference to the accompanying drawings. It should be understood by those skilled in the art that these embodiments are only for explaining the technical principle of the present invention, and are not intended to limit the scope of the present invention. It should be noted that in the description of the present invention, the terms of direction or positional relationship indicated by the terms "front", "rear", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the directions or positional relationships shown in the drawings, which are for convenience of description only, and do not indicate or imply that the device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention.
A hydraulic control system for endurance test equipment of an aircraft self-pressurization oil tank comprises a low-pressure oil circuit and a high-pressure oil circuit 2, wherein the high-pressure oil circuit 2 is used for providing relatively constant high oil pressure for a high-pressure cavity of the aircraft self-pressurization oil tank 1, as shown in figure 2. The low-pressure cavity of the airplane self-pressurization oil tank 1 is provided with an oil return port and an oil outlet, and the low-pressure oil path provides test oil pressure for the oil return port of the low-pressure cavity.
In order to solve the technical problem in the background technology, the low-pressure oil way is provided with an oil supply oil way 5 and an oil return oil way 6 which are connected with an oil return port of the self-pressurization oil tank 1 of the airplane. The oil supply path 5 comprises an oil pump 5.1, an oil supply regulating valve 5.2 and an overflow regulating valve 5.3, in this embodiment, the oil pump 5.1 is a gear pump with a fixed flow rate, one end of the oil supply regulating valve 5.2 is connected with the oil pump 5.1, and the other end is connected with the oil return port, and is used for regulating the oil supply amount of the oil supplied to the oil return port of the aircraft self-pressurization oil tank 1. The overflow regulating valve 5.3 is connected in parallel with the oil supply regulating valve 5.2, and is used for overflowing the surplus oil supply from the gear pump to the oil tank and keeping the stability of the oil supply. This enables the aircraft to move from the piston of the pressurised fuel tank 1 to the left at a constant speed. Typically, the flow rate set by the fuel supply regulating valve 5.2 is greater than the flow rate set by the spill regulating valve 5.3. For the convenience of control, the oil supply regulating valve 5.2 and the overflow regulating valve 5.3 are pneumatic regulating valves, and compared with electromagnetic control, pneumatic control has the advantages of large force and quick response.
The oil return path 6 comprises a ball valve and an oil return regulating valve 6.2 which are connected in series, in this embodiment, the oil return regulating valve 6.2 is a pneumatically controlled regulating valve, and the ball valve is a pneumatically controlled ball valve. The oil inlet end of the pneumatic ball valve 6.1 is connected with the oil outlet end of the oil supply regulating valve 5.2, and the oil outlet end of the oil return regulating valve 6.2 is communicated with the oil tank. The pneumatic ball valve 6.1 is used for opening or closing the oil return oil way 6, and the oil return regulating valve 6.2 is used for regulating the oil return amount and discharging the oil return from the oil return port of the pressurized oil tank 1 of the airplane into the oil tank. Compared with an electromagnetic ball valve, the pneumatic ball valve 6.1 has the advantages of large force, quick response and easiness in control. Compared with a hydraulic control reversing valve, the pneumatic ball valve 6.1 has the advantages of low cost, simple and reliable structure, easiness in maintenance and the like, and the phenomenon that a valve core is stuck does not need to be worried about.
When the pneumatic ball valve 6.1 is closed, the backflow is blocked, so that the oil supply regulating valve 5.2 supplies oil to an oil return opening of the aircraft self-pressurization oil tank 1; when the pneumatic ball valve 6.1 is opened, the pressure of a low-pressure cavity of the aircraft self-pressurization oil tank 1 is reduced, and part of hydraulic oil flows into the oil return regulating valve 6.2 from the oil return opening and then flows back to the oil tank through the oil return regulating valve 6.2. In order to reduce impact, the flow set by the oil return regulating valve 6.2 is smaller than the flow set by the oil supply regulating valve 5.2, and after the pneumatic ball valve 6.1 is opened, a certain oil pressure is reserved in the low-pressure cavity, so that the airplane can move towards the right side at a constant speed from the piston of the pressurized oil tank 1.
Because the hydraulic control reversing valve is not arranged in the system, pilot oil pressure does not need to be provided for the hydraulic control reversing valve. It is particularly important that the pneumatic ball valve 6.1 has a gradual change process for the on-off of the hydraulic oil during the opening or closing process, and the gradual change process slows down the reversing impact. Compared with a hydraulic control reversing valve, the pneumatic ball valve 6.1 reduces the vibration caused by switching to the whole system, ensures the stability of the test system and protects the self-pressurization oil tank 1 of the airplane.
For the safety of the system, the oil supply circuit 5 further comprises an overflow valve 5.4, a flowmeter 5.7 and a pressure sensor 5.5, wherein the overflow valve 5.4, the flowmeter 5.7 and the pressure sensor 5.5 are connected between the oil return port and the oil supply regulating valve 5.2. The pressure sensor 5.5 is used for monitoring the oil supply pressure, when the oil pressure of the low-pressure cavity is too high, the overflow valve 5.4 is opened, part of hydraulic oil is discharged, and the oil pressure of the low-pressure cavity is kept stable. The flow meter 5.7 is used for monitoring the oil supply amount, and the moving speed of the piston can be judged according to the oil supply amount.
In order to eliminate the influence of the oil temperature on the test, the oil supply path 5 further comprises a refrigerating and heating unit 5.6, and the refrigerating and heating unit 5.6 is connected between the oil pump 5.1 and the oil supply regulating valve 5.2 and used for heating or cooling hydraulic oil so as to keep the oil temperature constant.
The present invention is not described in detail in the prior art. Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the utility model, the scope of which is defined in the appended claims and their equivalents.
Claims (4)
1. The utility model provides a hydraulic control system for durable test equipment of aircraft self-pressurization oil tank, includes the low pressure oil circuit of fuel feeding to aircraft self-pressurization oil tank low-pressure chamber and the high-pressure oil circuit of fuel feeding to aircraft self-pressurization oil tank high-pressure chamber, and wherein, the low pressure oil circuit is equipped with fuel feeding oil circuit and the oil return oil circuit, characterized by that be connected with low pressure chamber oil return opening: the oil supply oil path comprises an oil pump, an oil supply regulating valve and an overflow regulating valve, the oil supply regulating valve is used for regulating the oil supply amount, one end of the oil supply regulating valve is connected with the oil pump, and the other end of the oil supply regulating valve is connected with the oil return port; the overflow regulating valve is connected with the oil supply regulating valve in parallel and is used for overflowing redundant oil supply to the oil return tank; the oil return oil way comprises a ball valve and an oil return adjusting valve which are connected in series, and the oil return adjusting valve is used for adjusting the oil return amount and discharging the oil return into the oil tank.
2. The hydraulic control system for an aircraft self-pressurization tank endurance test apparatus of claim 1, wherein: the oil supply oil way also comprises an overflow valve, a flowmeter and a pressure sensor, wherein the overflow valve, the flowmeter and the pressure sensor are connected between the oil return port and the oil supply regulating valve.
3. The hydraulic control system for an aircraft self-pressurization tank endurance test apparatus of claim 1, wherein: the oil supply oil path further comprises a refrigerating and heating unit, and the refrigerating and heating unit is connected between the oil pump and the oil supply regulating valve and used for heating or cooling hydraulic oil.
4. The hydraulic control system for an aircraft self-pressurization tank endurance test apparatus of claim 1, wherein: the ball valve is a pneumatic ball valve; the oil supply regulating valve, the overflow regulating valve and the oil return regulating valve are all pneumatic regulating valves.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122799136.1U CN216241633U (en) | 2021-11-12 | 2021-11-12 | Hydraulic control system for endurance test equipment of airplane self-pressurization oil tank |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122799136.1U CN216241633U (en) | 2021-11-12 | 2021-11-12 | Hydraulic control system for endurance test equipment of airplane self-pressurization oil tank |
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| Publication Number | Publication Date |
|---|---|
| CN216241633U true CN216241633U (en) | 2022-04-08 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202122799136.1U Active CN216241633U (en) | 2021-11-12 | 2021-11-12 | Hydraulic control system for endurance test equipment of airplane self-pressurization oil tank |
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| CN (1) | CN216241633U (en) |
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2021
- 2021-11-12 CN CN202122799136.1U patent/CN216241633U/en active Active
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