WO2023050615A1 - Venting device and venting control system for auxiliary tank of aircraft, and aircraft fuel supply system - Google Patents
Venting device and venting control system for auxiliary tank of aircraft, and aircraft fuel supply system Download PDFInfo
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- WO2023050615A1 WO2023050615A1 PCT/CN2021/141885 CN2021141885W WO2023050615A1 WO 2023050615 A1 WO2023050615 A1 WO 2023050615A1 CN 2021141885 W CN2021141885 W CN 2021141885W WO 2023050615 A1 WO2023050615 A1 WO 2023050615A1
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- fuel tank
- auxiliary fuel
- aircraft
- oil
- auxiliary
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- 239000000446 fuel Substances 0.000 title claims description 84
- 238000013022 venting Methods 0.000 title abstract description 9
- 238000004891 communication Methods 0.000 claims abstract description 8
- 239000012530 fluid Substances 0.000 claims abstract description 8
- 239000002828 fuel tank Substances 0.000 claims description 159
- 238000009423 ventilation Methods 0.000 claims description 94
- 238000001514 detection method Methods 0.000 claims description 16
- 239000003570 air Substances 0.000 claims description 8
- 239000012080 ambient air Substances 0.000 claims description 4
- 238000013461 design Methods 0.000 description 14
- 238000002955 isolation Methods 0.000 description 10
- 238000009530 blood pressure measurement Methods 0.000 description 4
- 238000010586 diagram Methods 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 238000012546 transfer Methods 0.000 description 4
- 239000003129 oil well Substances 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 239000000284 extract Substances 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000007726 management method Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/02—Tanks
- B64D37/14—Filling or emptying
- B64D37/16—Filling systems
- B64D37/18—Conditioning fuel during filling
Definitions
- the invention relates to a ventilation device for an aircraft auxiliary fuel tank, a ventilation control system and an aircraft fuel supply system.
- the main function of the auxiliary fuel tank system is to replenish fuel for the original wing fuel tank (basic fuel tank) of the aircraft.
- the fuel in the auxiliary fuel tank is usually not directly supplied to the engine for consumption, but the fuel in the auxiliary fuel tank is first transferred to the basic fuel tank.
- the fuel pump from the base tank supplies the engine consumption.
- the auxiliary fuel tank system in order to ensure that the internal pressure of the auxiliary fuel tank meets the structural strength requirements, that is, to maintain the difference between the gas pressure in the oil-free space in the fuel tank and the gas pressure outside the machine, it is necessary to Vent the auxiliary tank and monitor the pressure in the tank.
- Patent Document 1 Choinese Invention Patent CN103057714B proposes an auxiliary fuel system, which maintains the auxiliary Gas pressure in the oil-free space inside the tank.
- the aforementioned independent ventilation system is often an open ventilation system, that is, the auxiliary fuel tank is directly connected with the external environment via the ventilation fuel tank. Since the independent ventilation system is an open ventilation system, when the aircraft is flying at high altitude, it is difficult to replenish the fuel in the auxiliary fuel tank to the wings by pressurizing the interior of the auxiliary fuel tank with the gas in the cabin or the ambient gas outside the aircraft tank.
- the present invention is formed in order to solve the above-mentioned technical problems, and its purpose is to provide a ventilation device, a ventilation control system and an aircraft fuel supply system of an aircraft auxiliary fuel tank, which can fully utilize the ventilation system of the original model, and can be used without In the case of adding new equipment, such as transfer pumps or oil well pumps, which may become potential ignition sources, precise control of the auxiliary fuel tank has good safety and high reliability.
- the ventilation device of the aircraft auxiliary fuel tank of the present invention is used to maintain the gas pressure of the oil-free space in the auxiliary fuel tank, and is characterized in that it comprises: a vent pipe for the auxiliary fuel tank, and the vent pipe for the auxiliary fuel tank is connected to the auxiliary fuel tank and the wing oil tank arranged on the wing of the aircraft, so that the oil-free space in the auxiliary oil tank is in fluid communication with the oil-free space in the wing oil tank; and a breather valve, the breather valve is arranged on the auxiliary oil tank In the middle of the air pipe for the fuel tank, the opening is opened, closed or adjusted according to the pressure difference between the oil-free space in the auxiliary fuel tank and the environment outside the machine.
- a set of new ventilation system is not independently set for the auxiliary fuel tank, but is connected with the original aircraft wing ventilation system through the auxiliary fuel tank with a ventilation pipe, sharing a Vent the fuel tank for ventilation.
- the reason for this design is that the auxiliary fuel tank can usually withstand a certain pressure. Under normal circumstances, there is no need to ventilate during air flight, and the auxiliary fuel tank and wing tank will not be refueled at the same time, so there is less need for ventilation. Therefore, by connecting the auxiliary fuel tank with the ventilation system of the wing fuel tank of the original aircraft and sharing the ventilation fuel tank, the structure can be simplified and the weight of the aircraft can be reduced.
- the venting device of the auxiliary fuel tank is formed as a closed device by installing a vent valve on the vent pipe of the auxiliary fuel tank that can be opened, closed or adjusted according to the pressure difference between the oil-free space in the auxiliary fuel tank and the external environment. Therefore, since the inside of the auxiliary fuel tank is not communicated with the external environment, the auxiliary fuel tank can be pressurized by the gas in the cabin, thereby supplying fuel to the wing fuel tank. This improves safety by eliminating the need for equipment that could be a potential source of ignition, such as transfer or oil well pumps.
- the ventilation valve is a safety valve.
- the ventilation valve As a safety valve, when the ventilation valve is opened, the opening degree can be automatically adjusted according to the actual pressure. Therefore, the gas pressure in the auxiliary oil tank can be controlled more precisely and has good safety.
- the ventilation device On the basis of the ventilation device for the auxiliary fuel tank of the aircraft, preferably, the ventilation device also includes: a breather pipe for rapid pressure, and the breather pipe for rapid pressure is connected to the middle of the breather pipe for the auxiliary fuel tank for external use. Ambient air introduction; and a one-way valve, the one-way valve is arranged in the middle of the breather pipe for rapid pressure, and only allows the introduced external ambient air to flow to the auxiliary oil tank.
- the venting device also includes a quick-pressure breather and a one-way valve arranged on the quick-pressure breather, when the aircraft dives sharply and the external air pressure increases rapidly, the quick-pressure breather and the one-way valve will pass through the quick-pressure breather and the check valve. Introducing a part of the ambient air outside the aircraft can prevent the auxiliary fuel tank from being crushed during the sharp dive of the aircraft.
- the present invention also provides an aircraft fuel supply system, comprising: a ventilating fuel tank, the ventilating fuel tank is in fluid communication with the external environment through a ventilating fuel tank with one end arranged outside the aircraft; the wing fuel tank, the wing The fuel tank stores the fuel delivered to the engine of the aircraft; the wing fuel tank uses a vent pipe, and the wing fuel tank uses a vent pipe to connect the oil-free space in the wing fuel tank with the oil-free space in the ventilated fuel tank; and auxiliary The fuel tank, wherein the auxiliary fuel tank stores fuel supplied to the wing fuel tank, is characterized in that it also includes a ventilation device for the aircraft auxiliary fuel tank.
- the auxiliary fuel tank of the aircraft can withstand a certain pressure without ventilation in the air, and the auxiliary fuel tank and the wing fuel tank are generally not refueled at the same time, so there is less need for ventilation.
- the auxiliary fuel tank is connected to the wing fuel tank through the ventilation device, thereby sharing a set of ventilation system and a ventilation fuel tank with the wing fuel tank. Therefore, not only the structure of the ventilation subsystem in the fuel supply system is simplified, It also reduces the overall weight of the aircraft.
- the present invention also provides a ventilation control system for an aircraft auxiliary fuel tank, which is used to control the ventilation device, and is characterized in that it includes: a differential pressure sensor, which detects the air pressure in the auxiliary fuel tank. The pressure difference between the oil-free space and the external environment; and the auxiliary fuel control unit, the auxiliary fuel control unit receives the detection result of the pressure difference detected by the pressure difference sensor, and according to the pressure difference According to the detection result, the ventilation valve is opened and closed.
- the differential pressure sensor detects the pressure difference between the oil-free space in the auxiliary fuel tank and the outside environment, and transmits the detected pressure difference to the auxiliary fuel control unit, and then the auxiliary fuel control unit The unit opens and closes the vent valve according to the detection result of the pressure difference.
- the gas pressure in the auxiliary fuel tank can be precisely controlled.
- the ventilation control system further includes: a differential pressure switch, and the differential pressure switch senses the difference between the oil-free space in the auxiliary fuel tank and the external environment The pressure difference is opened and closed according to the sensing result of the pressure difference, the auxiliary fuel control unit receives the sensing result from the differential pressure switch, compares the sensing result with the sensing result, and when the comparison results are consistent , the auxiliary fuel control unit determines that the detection result of the pressure difference is correct.
- the ventilation control system by adopting a non-similar design of pressure measurement, that is, by comparing whether the sensing result of the differential pressure switch is consistent with the detection result of the differential pressure sensor, the accuracy of gas pressure measurement in the auxiliary fuel tank can be improved, thereby enabling Improve the reliability of the ventilation control system.
- the ventilation device of the aircraft auxiliary fuel tank of the present invention can accurately control the inside of the auxiliary fuel tank without adding new equipment such as a transmission pump or an oil pump that may become a potential ignition source, and has good safety and high safety. reliability.
- Fig. 1 is a schematic diagram of an aircraft fuel supply system according to an embodiment of the present invention, showing the ventilation device of the auxiliary fuel tank of the present invention.
- Fig. 2 is a schematic diagram of a ventilation control system for an auxiliary oil tank according to an embodiment of the present invention.
- FIG. 3 is a structural diagram of an auxiliary fuel control unit in the ventilation control system in FIG. 2 .
- a fuel supply system and an auxiliary fuel tank breather device according to an embodiment of the present invention will be described.
- FIG. 1 is a schematic diagram of an aircraft fuel supply system O according to an embodiment of the present invention.
- the fuel supply system O comprises the ventilation oil tank 1 and the wing oil tank 2 that are arranged on the left side wing LF and the right side wing RF of the aircraft (here, for simplicity, only the left side wing is shown
- the ventilation oil tank 1 and the wing oil tank 2), the auxiliary oil tank 3 that is arranged on the cabin of the fuselage and is positioned at the rear side of the wing.
- the breather fuel tank 1 is a fuel tank used to communicate the fuel supply system O with the outside environment, and the breather tube (not shown) that is arranged outside the machine and the other end is set in the oil-free space of the breather fuel tank 1 is connected with the machine. Fluid communication with the external environment.
- the vent tank 1 is provided at the tip of the left wing LF and the right wing RF.
- the wing fuel tank 2 is arranged on the left side wing LF and the right wing RF, and is closer to the aircraft fuselage side than the ventilating fuel tank 1.
- the oil-free space in the wing tank 2 is in fluid communication with the oil-free space in the wing tank 2.
- the wing fuel tank 2 stores fuel to be delivered to an engine (not shown) of the aircraft.
- Auxiliary fuel tank 3 is an internally stored fuel tank for replenishing wing fuel tank 2, which is connected to two wing fuel tanks 2 provided on the left wing LF and right wing RF through the breather pipe P2 for the auxiliary fuel tank, The wing oil tank 2 which is closer to the auxiliary oil tank 3 is connected, so that the oil-free space in the auxiliary oil tank 3 is in fluid communication with the oil-free space in the wing oil tank 2 .
- the fuel delivery valve (not shown) that is arranged on the wing fuel tank 2 Open, the fuel stored in the auxiliary fuel tank 3 is supplied to the wing fuel tank 2 through a fuel delivery pipe (not shown), and the fuel in the wing fuel tank 2 is replenished.
- the aircraft fuel supply system O includes a ventilation device for the auxiliary fuel tank 3 .
- This breather device includes the above-mentioned breather pipe P2 for the auxiliary tank and a breather valve V provided in the middle of the breather pipe P2 for the auxiliary tank.
- the ventilation valve V is a valve that opens, closes or adjusts the opening degree according to the pressure difference between the oil-free space in the auxiliary mailbox 3 and the external environment, such as a spring safety valve.
- the above-mentioned ventilation device also includes a quick-pressure ventilation pipe P3 and a one-way valve V1.
- One end of the breather pipe P3 for rapid pressure is connected to the middle of the breather pipe P2 for the auxiliary fuel tank, and the other end is connected to the atmosphere outside the machine. It flows from the outside of the machine to the inside of the auxiliary oil tank 3.
- FIG. 2 shows the ventilation control system 4 of the auxiliary tank 3 of the present embodiment.
- the ventilation control system 4 is a control system for opening and closing the ventilation valve V provided in the middle of the ventilation pipe P2 for the auxiliary fuel tank, and includes a differential pressure sensor 5, an auxiliary fuel control unit 6, a differential pressure switch 7, and an auxiliary fuel isolation unit 8.
- the differential pressure sensor 5 is a sensor for detecting the pressure difference between the gas in the oil-free space in the auxiliary fuel tank 3 and the ambient gas outside the machine, and the differential pressure switch 7 is used for sensing the gas in the oil-free space in the auxiliary fuel tank 3 and the pressure difference outside the machine. A switch that is opened or closed based on the pressure difference of the ambient gas and the sensed result of the pressure difference.
- the auxiliary fuel isolation unit 8 is a signal processing unit that receives the sensed value of the pressure difference sensed by the differential pressure switch 7 and converts the signal type of the sensed value before sending it to the auxiliary fuel control unit 6 .
- the auxiliary fuel control unit 6 is a comprehensive control unit, which extracts the wheel-borne signal of the aircraft from the aircraft's avionics system control unit 9, collects the button state signal (fuel supply state signal) of the auxiliary fuel control board, and reads the pressure difference After receiving the detected value of the pressure difference detected by the sensor 5 and the switch state signal of the converted pressure difference switch 7 transmitted by the auxiliary fuel isolation unit 8, it is judged whether it is necessary to open the ventilation through the combinational logic circuit shown in Fig. 3 Valve V or close vent valve V. In addition, after reading the detection value of the pressure difference detected by the pressure difference sensor 5 , the auxiliary fuel control unit 6 compares the detection value with a preset design value and obtains a comparison result signal.
- the auxiliary fuel control unit 6 receives the switch state signal of the differential pressure switch 7 transmitted from the auxiliary fuel isolation unit 8, it compares the switch state signal with the above-mentioned comparison result signal and generates the working condition of the differential pressure sensor 5. status signal.
- the fuel supply status signal and the wheel load signal are input to an OR gate circuit at the same time, and at the same time, the detection signal of the pressure difference detected by the pressure difference sensor 5 and The working status signal of the differential pressure sensor 5 is input to a NAND gate circuit at the same time, the above-mentioned OR gate circuit and the NAND gate circuit are connected in parallel and then connected to an AND gate circuit, and the switch control signal of the ventilation valve V is output through the AND gate circuit .
- the fuel supply status signal, the wheel load signal, the comparison result signal and the working status signal of the differential pressure sensor 5 as the input signal, and the control signal of the vent valve V as the output signal are all one-bit binary signals (including A high level signal is 1 and a low level signal is 0).
- the fuel supply status signal is a low-level signal, that is, 0 (not in the refueling state or fuel supply state)
- the wheel load signal is a high-level signal, that is, 1 (the aircraft is in the air flight state)
- the pressure difference The comparison result signal of the detected value of the differential pressure of the sensor 5 and the design value is a low-level signal, that is, 0 (the detected value is greater than the designed value), and the working state signal of the differential pressure sensor 5 is a low-level signal, that is, 0 (the differential pressure sensor 5 No fault occurs, in normal working condition), then the output result of the combinational logic circuit is 1, indicating that the ventilation valve V needs to be opened. On the other hand, if the output result of the combinational logic circuit is 0, it means that the ventilation valve V needs to be closed.
- the differential pressure sensor 5 obtains the pressure difference between the gas in the oil-free space in the auxiliary fuel tank 3 and the ambient gas outside the machine by respectively detecting the gas pressure in the oil-free space in the auxiliary fuel tank 3 and the gas pressure outside the machine.
- the differential pressure switch 7 senses and detects the pressure difference between the gas in the oil-free space in the auxiliary fuel tank 3 and the ambient gas outside the machine, and opens and closes according to the pressure difference, and simultaneously sends a signal to the auxiliary fuel isolation unit 8 to indicate the pressure difference.
- the pressure difference switch 7 when the sensed value of the pressure difference is greater than the preset design value, the pressure difference switch 7 is closed and generates a discrete signal equivalent to a low-level signal; when the sensed value is less than the design value, The differential pressure switch 7 opens and generates a discrete signal corresponding to a high level signal.
- the auxiliary fuel isolation unit 8 receives the discrete signal from the differential pressure switch 7, and after performing signal type conversion on the discrete signal, sends the converted switch state signal of the differential pressure switch 7 to the auxiliary fuel control unit 8 .
- the auxiliary fuel control unit 8 draws the aircraft's wheel-borne signal from the aircraft's avionics system control unit 9, collects the button status signal (that is, the fuel supply status signal) from the auxiliary fuel control board, and receives the signal transmitted from the auxiliary fuel isolation unit 8. switch state signal, and read the detection value of the pressure difference detected by the pressure difference sensor 5. After reading the detection value of the pressure difference detected by the pressure difference sensor 5 , the auxiliary fuel control unit 8 compares the detection value with the preset design value of the pressure difference and generates a comparison result signal.
- the auxiliary fuel control unit 8 compares the comparison result signal with the switch state signal and generates the working state signal of the differential pressure sensor 5. Specifically, if the comparison result signal and the switch state signal are signals of the same state (for example, both are low-level signals), then it is determined that the differential pressure sensor 5 has not broken down and is in a normal working state, and the auxiliary fuel control unit 8 generates Low level working status signal.
- the auxiliary fuel control unit 8 judges whether the differential pressure sensor 5 fails by means of non-similar design of pressure measurement.
- the fuel supply status signal, wheel load signal, comparison result signal and working status signal as input signals are input into the combined logic circuit shown in Fig. 3, and the switch control signal of the ventilation valve V is output after the operation of the logic circuit.
- the auxiliary then control unit 6 sends the switch control signal to the ventilation valve V, so as to open and close the ventilation valve V.
- the ventilation device of the above-mentioned embodiment of the present invention is a closed ventilation device, and is connected with the ventilation system of the original wing oil tank 2 .
- the auxiliary fuel tank of the aircraft can withstand a certain pressure without ventilation in the air, and the auxiliary fuel tank and the wing fuel tank are generally not refueled at the same time, so there is less need for ventilation.
- the auxiliary fuel tank is connected to the wing fuel tank through the ventilation device, thereby sharing a set of ventilation system and a ventilation fuel tank with the wing fuel tank. Therefore, not only the structure of the ventilation subsystem in the fuel supply system is simplified, It also reduces the overall weight of the aircraft.
- the venting device is a closed venting device, it can precisely control the pressure in the fuel tank.
- the pressure difference is within a reasonable range, it can not only ensure the normal operation of the auxiliary fuel system, but also prevent the structure of the fuel tank from being damaged due to excessive pressure. damage.
- the ventilation control system of the above-mentioned embodiment of the present invention is a control system based on a non-similar design.
- the two can simultaneously detect the pressure of the oil-free space in the auxiliary oil tank 3 and the environment outside the machine. Poor, and compare the test results of the two to ensure the accuracy of pressure measurement, improve the safety of the fuel tank structure and the reliability of the system.
- the breather device includes the breather pipe P2 for the auxiliary fuel tank, the breather valve V provided on the breather pipe P2 for the auxiliary fuel tank, the breather pipe P3 for rapid pressure connected to the breather pipe P2 for the auxiliary fuel tank, and the breather pipe P3 installed on the speed
- the one-way valve V1 of the pressure-use vent pipe P3 has been described, but it is not limited thereto.
- the venting device of the auxiliary fuel tank 3 may not include the rapid pressure vent pipe P3 and the check valve V1, but may only include the vent pipe P2 for the auxiliary fuel tank and the vent valve V provided on the vent pipe P2 for the auxiliary fuel tank.
- the ventilation control system 4 of the auxiliary fuel tank 3 includes a differential pressure sensor 5, an auxiliary fuel control unit 6, a differential pressure switch 7 and an auxiliary fuel isolation unit 8, but is not limited to this.
- the ventilation control system 4 may only include the differential pressure sensor 5 and the auxiliary fuel control unit 6 without starting from the non-similar design, so that the opening and closing control of the ventilation valve V can also be realized.
- each embodiment can be freely combined, or each embodiment can be appropriately modified or omitted.
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Abstract
A venting device for an auxiliary tank of an aircraft. The venting device is configured to maintain the gas pressure of a fuel-free space in the auxiliary tank, and is characterized in that same comprises a vent pipe for the auxiliary tank, wherein the vent pipe for the auxiliary tank is connected between the auxiliary tank and wing tanks arranged on aircraft wings, so that the fuel-free space in the auxiliary tank is in fluid communication with fuel-free spaces in the wing tanks; and a vent valve, which is arranged midway in the vent pipe for the auxiliary tank, wherein the vent valve is opened or closed or the opening degree thereof is adjusted according to the magnitude of the pressure difference between the fuel-free space in the auxiliary tank and the environment outside an aircraft.
Description
本发明涉及一种飞机辅助油箱的通气装置、通气控制***以及飞机燃油供给***。The invention relates to a ventilation device for an aircraft auxiliary fuel tank, a ventilation control system and an aircraft fuel supply system.
已知，民用飞机一般通过在原有机型的基础上加装辅助油箱***来增加飞机的载油量，从而提高飞机的续航能力。并且，辅助油箱***一般都在原有机型设计完成并取证之后再进行设计、生产、制造和安装。It is known that civil aircraft generally increase the fuel capacity of the aircraft by installing an auxiliary fuel tank system on the basis of the original model, thereby improving the endurance of the aircraft. Moreover, the auxiliary fuel tank system is generally designed, produced, manufactured and installed after the design of the original model is completed and evidence is obtained.
辅助油箱***的主要功能是为飞机原有机翼油箱(基本油箱)补充燃油，辅助油箱内的燃油通常不是直接供给发动机进行消耗，而是先将辅助燃油箱内的燃油转输至基本油箱，通过基本油箱的燃油泵供给发动机消耗。辅助油箱***在加油过程中或在燃油转输过程中，为了保证辅助油箱内部压力满足结构强度要求，即维持油箱内的无油空间的气体压力与机外环境气体压力之间的差值，需要对辅助油箱内进行通气并对油箱内的压力进行监控。The main function of the auxiliary fuel tank system is to replenish fuel for the original wing fuel tank (basic fuel tank) of the aircraft. The fuel in the auxiliary fuel tank is usually not directly supplied to the engine for consumption, but the fuel in the auxiliary fuel tank is first transferred to the basic fuel tank. The fuel pump from the base tank supplies the engine consumption. During the refueling process or fuel transfer process of the auxiliary fuel tank system, in order to ensure that the internal pressure of the auxiliary fuel tank meets the structural strength requirements, that is, to maintain the difference between the gas pressure in the oil-free space in the fuel tank and the gas pressure outside the machine, it is necessary to Vent the auxiliary tank and monitor the pressure in the tank.
目前，关于辅助油箱的常规通气方式，专利文献1(中国发明专利CN103057714B)提出了一种辅助燃油***，通过为辅助油箱单独设立一套新的通气***(包括独立的通气油箱)，从而维持辅助油箱内的无油空间的气体压力。并且，上述独立的通气***往往是开式通气***，即，辅助油箱经由通气油箱与机外环境直接连通。由于该独立的通气***是开式通气***，因此，当飞机在高空飞行时，难以通过舱内气体或机外环境气体对辅助油箱内部增压的方式将该辅助油箱内的燃油补给至机翼油箱。考虑到上述情况，为了实现辅助油箱内的燃油向机翼油箱的补给，通常采用在辅助油箱内加装输油泵或者在机翼油箱内加设抽油泵等技术手段。如此一来，能够在不对辅助油箱进行增压的情况下，将辅助油箱内的燃油补给至机翼油箱，从而使得该开式通气***满足辅助油箱的通气需求。At present, regarding the conventional ventilation method of the auxiliary fuel tank, Patent Document 1 (Chinese Invention Patent CN103057714B) proposes an auxiliary fuel system, which maintains the auxiliary Gas pressure in the oil-free space inside the tank. Moreover, the aforementioned independent ventilation system is often an open ventilation system, that is, the auxiliary fuel tank is directly connected with the external environment via the ventilation fuel tank. Since the independent ventilation system is an open ventilation system, when the aircraft is flying at high altitude, it is difficult to replenish the fuel in the auxiliary fuel tank to the wings by pressurizing the interior of the auxiliary fuel tank with the gas in the cabin or the ambient gas outside the aircraft tank. In view of the above situation, in order to realize the supply of fuel in the auxiliary fuel tank to the wing fuel tank, technical means such as adding a fuel delivery pump in the auxiliary fuel tank or adding an oil suction pump in the wing fuel tank are usually adopted. In this way, the fuel in the auxiliary fuel tank can be replenished to the wing fuel tank without pressurizing the auxiliary fuel tank, so that the open ventilation system meets the ventilation requirements of the auxiliary fuel tank.
发明内容Contents of the invention
发明所要解决的技术问题The technical problem to be solved by the invention
然而，在如上述那样单独设立一套辅助油箱专用的通气***的情况下，需要额外增加新设备(例如，传输泵或抽油泵，甚至是独立的通气油箱)以及相关线缆，增加了点火源的风险，同时也额外增加了通气***管理，增加了飞机的重量以及研制成本。However, in the case of setting up a dedicated ventilation system for the auxiliary fuel tank as mentioned above, additional new equipment (for example, transfer pumps or oil well pumps, or even an independent ventilation tank) and related cables need to be added, which increases the number of ignition sources. At the same time, it also increases the management of the ventilation system, which increases the weight of the aircraft and the cost of development.
本发明是为了解决上述技术问题而形成的，其目的是提供一种飞机辅助油箱的通气装置、通气控制***以及飞机燃油供给***，能够充分地利用原有机型的通气***，并且能够在不增设诸如传输泵或抽油泵这样可能成为潜在点火源的新设备的情况下，精准地控制辅助油箱内，具有良好的安全性和较高的可靠性。The present invention is formed in order to solve the above-mentioned technical problems, and its purpose is to provide a ventilation device, a ventilation control system and an aircraft fuel supply system of an aircraft auxiliary fuel tank, which can fully utilize the ventilation system of the original model, and can be used without In the case of adding new equipment, such as transfer pumps or oil well pumps, which may become potential ignition sources, precise control of the auxiliary fuel tank has good safety and high reliability.
解决技术问题所采用的技术方案Technical solutions adopted to solve technical problems
本发明的飞机辅助油箱的通气装置用于维持所述辅助油箱内的无油空间的气体压力，其特征在于，包括：辅助油箱用通气管，所述辅助油箱用通气管连接在所述辅助油箱与设置于飞机机翼的机翼油箱之间，使得所述辅助油箱内的无油空间与所述机翼油箱内的无油空间流体连通；以及通气阀，所述通气阀设置于所述辅助油箱用通气管的中途，根据所述辅助油箱内的无油空间与机外环境的压力差的大小打开、关闭或者调节开度。The ventilation device of the aircraft auxiliary fuel tank of the present invention is used to maintain the gas pressure of the oil-free space in the auxiliary fuel tank, and is characterized in that it comprises: a vent pipe for the auxiliary fuel tank, and the vent pipe for the auxiliary fuel tank is connected to the auxiliary fuel tank and the wing oil tank arranged on the wing of the aircraft, so that the oil-free space in the auxiliary oil tank is in fluid communication with the oil-free space in the wing oil tank; and a breather valve, the breather valve is arranged on the auxiliary oil tank In the middle of the air pipe for the fuel tank, the opening is opened, closed or adjusted according to the pressure difference between the oil-free space in the auxiliary fuel tank and the environment outside the machine.
根据所述飞机辅助油箱的通气装置，在本发明中，并未为辅助油箱独立设置一套新的通气***，而是通过辅助油箱用通气管与原有的飞机机翼通气***连接，共用一个通气油箱进行通气。这样设计的原因在于，辅助油箱通常可以承受一定的压力，在正常情况下，在空中飞行的过程中无需通气，并且辅助油箱和机翼油箱不会同时加油，因而对通气需求较少。因此，通过使辅助油箱与原机机翼油箱的通气***连接并共用通气油箱，能够简化结构，减轻飞机的重量。此外，通过在辅助油箱用通气管设置能够根据辅助油箱内的无油空间与机外环境的压力差的大小打开、关闭或调节开度的通气阀，使得辅助油箱的通气装置形成为闭式装置，由此，由于辅助油箱的内部不与机外环境连通，因此，能够利用舱内气体对辅助油箱进行增压，从而将燃油补给至机翼油箱。如此一 来，不需要设置诸如传输泵或抽油泵这样可能成为潜在点火源的设备，能够提高安全性。According to the ventilation device of the aircraft auxiliary fuel tank, in the present invention, a set of new ventilation system is not independently set for the auxiliary fuel tank, but is connected with the original aircraft wing ventilation system through the auxiliary fuel tank with a ventilation pipe, sharing a Vent the fuel tank for ventilation. The reason for this design is that the auxiliary fuel tank can usually withstand a certain pressure. Under normal circumstances, there is no need to ventilate during air flight, and the auxiliary fuel tank and wing tank will not be refueled at the same time, so there is less need for ventilation. Therefore, by connecting the auxiliary fuel tank with the ventilation system of the wing fuel tank of the original aircraft and sharing the ventilation fuel tank, the structure can be simplified and the weight of the aircraft can be reduced. In addition, the venting device of the auxiliary fuel tank is formed as a closed device by installing a vent valve on the vent pipe of the auxiliary fuel tank that can be opened, closed or adjusted according to the pressure difference between the oil-free space in the auxiliary fuel tank and the external environment. Therefore, since the inside of the auxiliary fuel tank is not communicated with the external environment, the auxiliary fuel tank can be pressurized by the gas in the cabin, thereby supplying fuel to the wing fuel tank. This improves safety by eliminating the need for equipment that could be a potential source of ignition, such as transfer or oil well pumps.
在所述飞机辅助邮箱的通气装置的基础上，优选，所述通气阀是安全阀。On the basis of the ventilation device of the aircraft auxiliary mailbox, preferably, the ventilation valve is a safety valve.
通过将所述通气阀设为安全阀，在通气阀打开时，能够根据实际的压力大小自动地调节开度。因此，能够更精确地控制辅助油箱内的气体压力，并且具有良好的安全性。By setting the ventilation valve as a safety valve, when the ventilation valve is opened, the opening degree can be automatically adjusted according to the actual pressure. Therefore, the gas pressure in the auxiliary oil tank can be controlled more precisely and has good safety.
在所述飞机辅助油箱的通气装置的基础上，优选，所述通气装置还包括：速压用通气管，所述速压用通气管连接于所述辅助油箱用通气管的中途，供机外环境气体引入；以及单向阀，所述单向阀设置于速压用通气管的中途，仅允许被引入的所述机外环境气体向所述辅助油箱流动。On the basis of the ventilation device for the auxiliary fuel tank of the aircraft, preferably, the ventilation device also includes: a breather pipe for rapid pressure, and the breather pipe for rapid pressure is connected to the middle of the breather pipe for the auxiliary fuel tank for external use. Ambient air introduction; and a one-way valve, the one-way valve is arranged in the middle of the breather pipe for rapid pressure, and only allows the introduced external ambient air to flow to the auxiliary oil tank.
由于所述通气装置还包括速压用通气管和设置于该速压用通气管的单向阀，当飞机急剧俯冲而使得外界气压迅速增大时，通过该速压用通气管和单向阀引入一部分的机外环境气体，能够防止辅助油箱在飞机急剧俯冲的过程中被压坏。Since the venting device also includes a quick-pressure breather and a one-way valve arranged on the quick-pressure breather, when the aircraft dives sharply and the external air pressure increases rapidly, the quick-pressure breather and the one-way valve will pass through the quick-pressure breather and the check valve. Introducing a part of the ambient air outside the aircraft can prevent the auxiliary fuel tank from being crushed during the sharp dive of the aircraft.
此外，本发明还提供了一种飞机燃油供给***，包括：通气油箱，所述通气油箱通过一端设置于机外的通气油箱用通气管与机外环境流体连通；机翼油箱，所述机翼油箱贮存有向飞机的发动机输送的燃油；机翼油箱用通气管，所述机翼油箱用通气管连接所述机翼油箱内的无油空间与所述通气油箱内的无油空间；以及辅助油箱，所述辅助油箱贮存有向所述机翼油箱补给的燃油，其特征在于，还包括所述飞机辅助油箱的通气装置。In addition, the present invention also provides an aircraft fuel supply system, comprising: a ventilating fuel tank, the ventilating fuel tank is in fluid communication with the external environment through a ventilating fuel tank with one end arranged outside the aircraft; the wing fuel tank, the wing The fuel tank stores the fuel delivered to the engine of the aircraft; the wing fuel tank uses a vent pipe, and the wing fuel tank uses a vent pipe to connect the oil-free space in the wing fuel tank with the oil-free space in the ventilated fuel tank; and auxiliary The fuel tank, wherein the auxiliary fuel tank stores fuel supplied to the wing fuel tank, is characterized in that it also includes a ventilation device for the aircraft auxiliary fuel tank.
通常情况下，飞机的辅助油箱能够承受一定的压力且在空中无需通气，并且，辅助油箱和机翼油箱一般不会同时加油，因此对通气需求较少。考虑到上述情况，使辅助油箱通过所述通气装置与机翼油箱连接，从而与机翼油箱共用一套通气***和一个通气油箱，因此，不仅简化了燃油供给***中的通气子***的结构，还减轻了飞机的整体重量。Normally, the auxiliary fuel tank of the aircraft can withstand a certain pressure without ventilation in the air, and the auxiliary fuel tank and the wing fuel tank are generally not refueled at the same time, so there is less need for ventilation. Considering the above situation, the auxiliary fuel tank is connected to the wing fuel tank through the ventilation device, thereby sharing a set of ventilation system and a ventilation fuel tank with the wing fuel tank. Therefore, not only the structure of the ventilation subsystem in the fuel supply system is simplified, It also reduces the overall weight of the aircraft.
另一方面，本发明还提供了一种飞机辅助油箱的通气控制***，用于对所述通气装置进行控制，其特征在于，包括：压差传感器，所述压差传感器检测所述辅助油箱内的无油空间与所述机外环境的压力差；以及辅助燃油控制单 元，所述辅助燃油控制单元接收由所述压差传感器检测到的所述压力差的检测结果，并且根据所述压力差的检测结果对所述通气阀进行打开、关闭。On the other hand, the present invention also provides a ventilation control system for an aircraft auxiliary fuel tank, which is used to control the ventilation device, and is characterized in that it includes: a differential pressure sensor, which detects the air pressure in the auxiliary fuel tank. The pressure difference between the oil-free space and the external environment; and the auxiliary fuel control unit, the auxiliary fuel control unit receives the detection result of the pressure difference detected by the pressure difference sensor, and according to the pressure difference According to the detection result, the ventilation valve is opened and closed.
根据本发明的飞机辅助油箱的通气控制***，通过压差传感器检测辅助油箱内的无油空间与机外环境的压力差，将检测出的压力差传递至辅助燃油控制单元，然后，辅助燃油控制单元根据该压力差的检测结果对通气阀进行打开、关闭。由此，能够对辅助油箱内的气体压力进行精准控制。According to the ventilation control system of the aircraft auxiliary fuel tank of the present invention, the differential pressure sensor detects the pressure difference between the oil-free space in the auxiliary fuel tank and the outside environment, and transmits the detected pressure difference to the auxiliary fuel control unit, and then the auxiliary fuel control unit The unit opens and closes the vent valve according to the detection result of the pressure difference. As a result, the gas pressure in the auxiliary fuel tank can be precisely controlled.
在所述飞机辅助油箱的通气控制***的基础上，优选，所述通气控制***还包括：压差开关，所述压差开关感知所述辅助油箱内的无油空间与所述机外环境的压力差，并且根据所述压力差的感知结果打开、关闭，所述辅助燃油控制单元接收来自所述压差开关的感知结果，对所述检测结果和所述感知结果进行比较，当比较结果一致时，所述辅助燃油控制单元判定所述压力差的检测结果正确。On the basis of the ventilation control system of the auxiliary fuel tank of the aircraft, preferably, the ventilation control system further includes: a differential pressure switch, and the differential pressure switch senses the difference between the oil-free space in the auxiliary fuel tank and the external environment The pressure difference is opened and closed according to the sensing result of the pressure difference, the auxiliary fuel control unit receives the sensing result from the differential pressure switch, compares the sensing result with the sensing result, and when the comparison results are consistent , the auxiliary fuel control unit determines that the detection result of the pressure difference is correct.
根据所述通气控制***，通过采用压力测量的非相似设计，即通过比较压差开关的感知结果与压差传感器的检测结果是否一致，能够提高辅助油箱内的气体压力测量的准确性，从而能够提高该通气控制***的可靠性。According to the ventilation control system, by adopting a non-similar design of pressure measurement, that is, by comparing whether the sensing result of the differential pressure switch is consistent with the detection result of the differential pressure sensor, the accuracy of gas pressure measurement in the auxiliary fuel tank can be improved, thereby enabling Improve the reliability of the ventilation control system.
发明效果Invention effect
根据本发明的飞机辅助油箱的通气装置，能够在不增设诸如传输泵或抽油泵这样可能成为潜在点火源的新设备的情况下，精准地控制辅助油箱内，具有良好的安全性和较高的可靠性。According to the ventilation device of the aircraft auxiliary fuel tank of the present invention, it can accurately control the inside of the auxiliary fuel tank without adding new equipment such as a transmission pump or an oil pump that may become a potential ignition source, and has good safety and high safety. reliability.
图1是本发明一实施方式的飞机燃油供给***的示意图，示出了本发明的辅助油箱的通气装置。Fig. 1 is a schematic diagram of an aircraft fuel supply system according to an embodiment of the present invention, showing the ventilation device of the auxiliary fuel tank of the present invention.
图2是本发明一实施方式的辅助油箱的通气控制***的示意图。Fig. 2 is a schematic diagram of a ventilation control system for an auxiliary oil tank according to an embodiment of the present invention.
图3是图2中的通气控制***中的辅助燃油控制单元的架构图。FIG. 3 is a structural diagram of an auxiliary fuel control unit in the ventilation control system in FIG. 2 .
下面，首先参照图1，对本发明的一实施方式的燃油供给***以及辅助油 箱的通气装置进行说明。Next, referring to Fig. 1 first, a fuel supply system and an auxiliary fuel tank breather device according to an embodiment of the present invention will be described.
图1是本发明一实施方式的飞机燃油供给***O的示意图。如图1所示，燃油供给***O包括设置于飞机的左侧机翼LF和右侧机翼RF的通气油箱1和机翼油箱2(此处，为了简便，仅示出了左侧机翼的通气油箱1和机翼油箱2)、设置在机身的位于机翼后侧的机舱内的辅助油箱3。其中，通气油箱1是用于使燃油供给***O与机外环境连通的油箱，通过一端设置于机外且另一端设置于该通气油箱1的无油空间的通气管(未图示)与机外环境流体连通。在本实施方式中，通气油箱1设置于左侧机翼LF和右侧机翼RF的翼尖。机翼油箱2设置于左侧机翼LF和右侧机翼RF的、比通气油箱1靠飞机机身侧的部分，通过机翼油箱用通气管P1与通气油箱1连接，以使通气油箱1内的无油空间与机翼油箱2内的无油空间流体连通。并且，在本实施方式中，作为基本油箱(又称为主油箱或消耗油箱)，机翼油箱2内贮存有向飞机的发动机(省略图示)输送的燃油。辅助油箱3是内部贮存有用于对机翼油箱2进行补给的油箱，其通过辅助油箱用通气管P2与设置于左侧机翼LF和右侧机翼RF的两个机翼油箱2中的、与该辅助油箱3的距离较近的机翼油箱2连接，以使辅助油箱3内的无油空间与该机翼油箱2内的无油空间流体连通。当机翼油箱2内的燃油减少一定程度时，具体而言，当机翼油箱2内的燃油的液面降低至一定水平时，设置于该机翼油箱2的输油阀(未图示)打开，贮存在辅助油箱3内的燃油通过输油管(未图示)供给至机翼油箱2，对该机翼油箱2内的燃油进行补给。FIG. 1 is a schematic diagram of an aircraft fuel supply system O according to an embodiment of the present invention. As shown in Figure 1, the fuel supply system O comprises the ventilation oil tank 1 and the wing oil tank 2 that are arranged on the left side wing LF and the right side wing RF of the aircraft (here, for simplicity, only the left side wing is shown The ventilation oil tank 1 and the wing oil tank 2), the auxiliary oil tank 3 that is arranged on the cabin of the fuselage and is positioned at the rear side of the wing. Wherein, the breather fuel tank 1 is a fuel tank used to communicate the fuel supply system O with the outside environment, and the breather tube (not shown) that is arranged outside the machine and the other end is set in the oil-free space of the breather fuel tank 1 is connected with the machine. Fluid communication with the external environment. In this embodiment, the vent tank 1 is provided at the tip of the left wing LF and the right wing RF. The wing fuel tank 2 is arranged on the left side wing LF and the right wing RF, and is closer to the aircraft fuselage side than the ventilating fuel tank 1. The oil-free space in the wing tank 2 is in fluid communication with the oil-free space in the wing tank 2. In addition, in the present embodiment, as a basic fuel tank (also called a main fuel tank or a consumable fuel tank), the wing fuel tank 2 stores fuel to be delivered to an engine (not shown) of the aircraft. Auxiliary fuel tank 3 is an internally stored fuel tank for replenishing wing fuel tank 2, which is connected to two wing fuel tanks 2 provided on the left wing LF and right wing RF through the breather pipe P2 for the auxiliary fuel tank, The wing oil tank 2 which is closer to the auxiliary oil tank 3 is connected, so that the oil-free space in the auxiliary oil tank 3 is in fluid communication with the oil-free space in the wing oil tank 2 . When the fuel in the wing fuel tank 2 decreases to a certain extent, specifically, when the liquid level of the fuel in the wing fuel tank 2 drops to a certain level, the fuel delivery valve (not shown) that is arranged on the wing fuel tank 2 Open, the fuel stored in the auxiliary fuel tank 3 is supplied to the wing fuel tank 2 through a fuel delivery pipe (not shown), and the fuel in the wing fuel tank 2 is replenished.
在本实施方式中，飞机燃油供给***O包括辅助油箱3的通气装置。该通气装置包括上述辅助油箱用通气管P2以及设置于该辅助油箱用通气管P2的中途的通气阀V。通气阀V是根据辅助邮箱3内的无油空间与机外环境的压力差的大小打开、关闭或调节开度的阀，例如是弹簧式安全阀。此外，上述通气装置还包括速压用通气管P3以及单向阀V1。速压用通气管P3的一端连接在辅助油箱用通气管P2的中途，另一端与机外环境大气连通，单向阀V1设置于该速压用通气管P3的中途，仅允许机外环境气体从机外流向辅助油箱3的内部。In this embodiment, the aircraft fuel supply system O includes a ventilation device for the auxiliary fuel tank 3 . This breather device includes the above-mentioned breather pipe P2 for the auxiliary tank and a breather valve V provided in the middle of the breather pipe P2 for the auxiliary tank. The ventilation valve V is a valve that opens, closes or adjusts the opening degree according to the pressure difference between the oil-free space in the auxiliary mailbox 3 and the external environment, such as a spring safety valve. In addition, the above-mentioned ventilation device also includes a quick-pressure ventilation pipe P3 and a one-way valve V1. One end of the breather pipe P3 for rapid pressure is connected to the middle of the breather pipe P2 for the auxiliary fuel tank, and the other end is connected to the atmosphere outside the machine. It flows from the outside of the machine to the inside of the auxiliary oil tank 3.
接着，使用图2，对本实施方式中的辅助油箱3的通气控制***4进行说明。Next, the ventilation control system 4 of the auxiliary tank 3 in this embodiment will be described using FIG. 2 .
图2示出了本实施方式的辅助油箱3的通气控制***4。需要说明的是，为了便于理解，在图2中省略了速压用通气管P3和单向阀V1。通气控制***4是用于对设置于辅助油箱用通气管P2的中途的通气阀V进行开闭的控制***，包括压差传感器5、辅助燃油控制单元6、压差开关7以及辅助燃油隔离单元8。压差传感器5是用于检测辅助油箱3内的无油空间的气体与机外环境气体的压力差的传感器，压差开关7是用于感知辅助油箱3内的无油空间的气体与机外环境气体的压力差且根据压力差的感知结果打开或关闭的开关。辅助燃油隔离单元8是接收由压差开关7感知到的压力差的感知值并对该感知值的信号类型进行转换后发送给辅助燃油控制单元6的信号处理单元。辅助燃油控制单元6是一种综合控制单元，其从飞机的航电***控制单元9抽引飞机的轮载信号，采集辅助燃油控制板的按钮状态信号(燃油供给状态信号)，读取压差传感器5检测到的压力差的检测值，同时接收由辅助燃油隔离单元8传递而来的转换后的压差开关7的开关状态信号后，通过图3所示的组合逻辑电路判断是否需要打开通气阀V或关闭通气阀V。此外，辅助燃油控制单元6在读取压差传感器5检测到的压力差的检测值后，将该检测值与预先设定的设计值进行比较并获取比较结果信号。并且，辅助燃油控制单元6在接收到由辅助燃油隔离单元8传递而来的压差开关7的开关状态信号后，将该开关状态信号与上述比较结果信号进行比较并生成压差传感器5的工作状态信号。FIG. 2 shows the ventilation control system 4 of the auxiliary tank 3 of the present embodiment. It should be noted that, for ease of understanding, in FIG. 2 , the breather pipe P3 for rapid pressure and the one-way valve V1 are omitted. The ventilation control system 4 is a control system for opening and closing the ventilation valve V provided in the middle of the ventilation pipe P2 for the auxiliary fuel tank, and includes a differential pressure sensor 5, an auxiliary fuel control unit 6, a differential pressure switch 7, and an auxiliary fuel isolation unit 8. The differential pressure sensor 5 is a sensor for detecting the pressure difference between the gas in the oil-free space in the auxiliary fuel tank 3 and the ambient gas outside the machine, and the differential pressure switch 7 is used for sensing the gas in the oil-free space in the auxiliary fuel tank 3 and the pressure difference outside the machine. A switch that is opened or closed based on the pressure difference of the ambient gas and the sensed result of the pressure difference. The auxiliary fuel isolation unit 8 is a signal processing unit that receives the sensed value of the pressure difference sensed by the differential pressure switch 7 and converts the signal type of the sensed value before sending it to the auxiliary fuel control unit 6 . The auxiliary fuel control unit 6 is a comprehensive control unit, which extracts the wheel-borne signal of the aircraft from the aircraft's avionics system control unit 9, collects the button state signal (fuel supply state signal) of the auxiliary fuel control board, and reads the pressure difference After receiving the detected value of the pressure difference detected by the sensor 5 and the switch state signal of the converted pressure difference switch 7 transmitted by the auxiliary fuel isolation unit 8, it is judged whether it is necessary to open the ventilation through the combinational logic circuit shown in Fig. 3 Valve V or close vent valve V. In addition, after reading the detection value of the pressure difference detected by the pressure difference sensor 5 , the auxiliary fuel control unit 6 compares the detection value with a preset design value and obtains a comparison result signal. And, after the auxiliary fuel control unit 6 receives the switch state signal of the differential pressure switch 7 transmitted from the auxiliary fuel isolation unit 8, it compares the switch state signal with the above-mentioned comparison result signal and generates the working condition of the differential pressure sensor 5. status signal.
关于辅助燃油控制单元6的控制架构，如图3所示，燃油供给状态信号和轮载信号被同时输入至一个或门电路，与此同时，压差传感器5检测到的压力差的检测信号和压差传感器5的工作状态信号被同时输入至一个与非门电路，上述或门电路和与非门电路并联连接后与一个与门电路连接，通过该与门电路输出通气阀V的开关控制信号。在本实施方式中，作为输入信号的燃油供给状态信号、轮载信号、比较结果信号和压差传感器5的工作状态信号以及作为输出信号的通气阀V的控制信号均为一位二进制信号(包括高电平信号即1和低电平信号即0)。Regarding the control structure of the auxiliary fuel control unit 6, as shown in Figure 3, the fuel supply status signal and the wheel load signal are input to an OR gate circuit at the same time, and at the same time, the detection signal of the pressure difference detected by the pressure difference sensor 5 and The working status signal of the differential pressure sensor 5 is input to a NAND gate circuit at the same time, the above-mentioned OR gate circuit and the NAND gate circuit are connected in parallel and then connected to an AND gate circuit, and the switch control signal of the ventilation valve V is output through the AND gate circuit . In this embodiment, the fuel supply status signal, the wheel load signal, the comparison result signal and the working status signal of the differential pressure sensor 5 as the input signal, and the control signal of the vent valve V as the output signal are all one-bit binary signals (including A high level signal is 1 and a low level signal is 0).
作为逻辑判断的一例，假设燃油供给状态信号为低电平信号即0(未处于加油状态或燃油补给状态)、轮载信号为高电平信号即1(飞机处于空中飞行的状态)、压差传感器5的压力差的检测值与设计值的比较结果信号为低电平信号即0(检测值大于设计值)以及压差传感器5的工作状态信号为低电平信号即0(压差传感器5未发生故障，处于正常工作状态)，则通过该组合逻辑电路的输出结果为1，表示需要打开通气阀V。另一方面，若该组合逻辑电路的输出结果为0，则表示需要关闭通气阀V。As an example of logical judgment, assume that the fuel supply status signal is a low-level signal, that is, 0 (not in the refueling state or fuel supply state), the wheel load signal is a high-level signal, that is, 1 (the aircraft is in the air flight state), and the pressure difference The comparison result signal of the detected value of the differential pressure of the sensor 5 and the design value is a low-level signal, that is, 0 (the detected value is greater than the designed value), and the working state signal of the differential pressure sensor 5 is a low-level signal, that is, 0 (the differential pressure sensor 5 No fault occurs, in normal working condition), then the output result of the combinational logic circuit is 1, indicating that the ventilation valve V needs to be opened. On the other hand, if the output result of the combinational logic circuit is 0, it means that the ventilation valve V needs to be closed.
接着，在上述说明的基础上，对基于本实施方式的通气控制***4的针对通气阀V的开闭控制进行详细描述。Next, on the basis of the above description, the opening and closing control of the ventilation valve V by the ventilation control system 4 of this embodiment will be described in detail.
首先，压差传感器5通过分别检测辅助油箱3内的无油空间的气体压力与机外环境气体压力，从而获取辅助油箱3内的无油空间的气体与机外环境气体之间的压力差。与此同时，压差开关7感知检测辅助油箱3内的无油空间的气体与机外环境气体的压力差，并且根据压力差的大小打开、关闭，同时向辅助燃油隔离单元8发送一个表示该压差开关7打开或关闭的离散量信号。在本实施方式中，例如，当压力差的感知值大于预先设定的设计值时，压差开关7关闭并产生相当于低电平信号的离散量信号，当该感知值小于设计值时，压差开关7打开并产生相当于高电平信号的离散量信号。Firstly, the differential pressure sensor 5 obtains the pressure difference between the gas in the oil-free space in the auxiliary fuel tank 3 and the ambient gas outside the machine by respectively detecting the gas pressure in the oil-free space in the auxiliary fuel tank 3 and the gas pressure outside the machine. At the same time, the differential pressure switch 7 senses and detects the pressure difference between the gas in the oil-free space in the auxiliary fuel tank 3 and the ambient gas outside the machine, and opens and closes according to the pressure difference, and simultaneously sends a signal to the auxiliary fuel isolation unit 8 to indicate the pressure difference. Discrete signal for opening or closing of differential pressure switch 7. In this embodiment, for example, when the sensed value of the pressure difference is greater than the preset design value, the pressure difference switch 7 is closed and generates a discrete signal equivalent to a low-level signal; when the sensed value is less than the design value, The differential pressure switch 7 opens and generates a discrete signal corresponding to a high level signal.
接着，辅助燃油隔离单元8接收来自压差快关7的离散量信号，并且对该离散量信号进行信号类型转换后，将转换后的压差开关7的开关状态信号发送至辅助燃油控制单元8。Next, the auxiliary fuel isolation unit 8 receives the discrete signal from the differential pressure switch 7, and after performing signal type conversion on the discrete signal, sends the converted switch state signal of the differential pressure switch 7 to the auxiliary fuel control unit 8 .
辅助燃油控制单元8从飞机的航电***控制单元9抽引飞机的轮载信号，从辅助燃油控制板采集按钮状态信号(即燃油供给状态信号)，接收从辅助燃油隔离单元8传递而来的开关状态信号，并且读取由压差传感器5检测到的压力差的检测值。在读取到由压差传感器5检测到的压力差的检测值后，辅助燃油控制单元8将该检测值与预先设定好的压力差的设计值进行比较并生成比较结果信号。具体而言，当检测值大于设计值时，生成的比较结果信号是低电平信号即0，当检测值小于设计值时，生成的比较结果信号是高电平信号即1。接着，在接收到从辅助燃油隔离单元6传递来的开关状态信号后，辅助燃油控 制单元8将比较结果信号与开关状态信号进行比较并生成压差传感器5的工作状态信号。具体而言，若比较结果信号与开关状态信号是相同状态的信号(例如，都是低电平信号)，则判定压差传感器5并未发生故障，处于正常工作状态，辅助燃油控制单元8生成低电平的工作状态信号。若比较结果信号与开关状态信号是不同状态的信号(例如，一个是高电平信号而另一个是低电平信号)，则判定压差传感器5发生故障，辅助燃油控制单元8生成高电平的工作状态信号。也就是说，在本实施方式中，辅助燃油控制单元8通过压力测量的非相似设计的方式对压差传感器5是否发生故障进行判断。The auxiliary fuel control unit 8 draws the aircraft's wheel-borne signal from the aircraft's avionics system control unit 9, collects the button status signal (that is, the fuel supply status signal) from the auxiliary fuel control board, and receives the signal transmitted from the auxiliary fuel isolation unit 8. switch state signal, and read the detection value of the pressure difference detected by the pressure difference sensor 5. After reading the detection value of the pressure difference detected by the pressure difference sensor 5 , the auxiliary fuel control unit 8 compares the detection value with the preset design value of the pressure difference and generates a comparison result signal. Specifically, when the detection value is greater than the design value, the generated comparison result signal is a low-level signal, that is, 0, and when the detection value is smaller than the design value, the generated comparison result signal is a high-level signal, that is, 1. Then, after receiving the switch state signal transmitted from the auxiliary fuel isolation unit 6, the auxiliary fuel control unit 8 compares the comparison result signal with the switch state signal and generates the working state signal of the differential pressure sensor 5. Specifically, if the comparison result signal and the switch state signal are signals of the same state (for example, both are low-level signals), then it is determined that the differential pressure sensor 5 has not broken down and is in a normal working state, and the auxiliary fuel control unit 8 generates Low level working status signal. If the comparison result signal and the switch state signal are signals of different states (for example, one is a high-level signal and the other is a low-level signal), then it is determined that the differential pressure sensor 5 fails, and the auxiliary fuel control unit 8 generates a high level working status signal. That is to say, in this embodiment, the auxiliary fuel control unit 8 judges whether the differential pressure sensor 5 fails by means of non-similar design of pressure measurement.
然后，作为输入信号的燃油供给状态信号、轮载信号、比较结果信号和工作状态信号被输入图3所示的组合逻辑电路，通过该逻辑电路的运算后，输出通气阀V的开关控制信号。辅助然后控制单元6将该开关控制信号发送至通气阀V，从而对通气阀V进行打开、关闭。Then, the fuel supply status signal, wheel load signal, comparison result signal and working status signal as input signals are input into the combined logic circuit shown in Fig. 3, and the switch control signal of the ventilation valve V is output after the operation of the logic circuit. The auxiliary then control unit 6 sends the switch control signal to the ventilation valve V, so as to open and close the ventilation valve V.
(实施方式的技术效果)(Technical Effects of Embodiments)
本发明的上述实施方式的通气装置是一种闭式通气装置，且与原有的机翼油箱2的通气***连接。通常情况下，飞机的辅助油箱能够承受一定的压力且在空中无需通气，并且，辅助油箱和机翼油箱一般不会同时加油，因此对通气需求较少。考虑到上述情况，使辅助油箱通过所述通气装置与机翼油箱连接，从而与机翼油箱共用一套通气***和一个通气油箱，因此，不仅简化了燃油供给***中的通气子***的结构，还减轻了飞机的整体重量。此外，由于该通气装置是闭式通气装置，可以对油箱内压力进行精准控制，当压差在合理范围的时候，既能保证辅助燃油***正常工作，又不会因为压力过大，导致油箱结构损坏。The ventilation device of the above-mentioned embodiment of the present invention is a closed ventilation device, and is connected with the ventilation system of the original wing oil tank 2 . Normally, the auxiliary fuel tank of the aircraft can withstand a certain pressure without ventilation in the air, and the auxiliary fuel tank and the wing fuel tank are generally not refueled at the same time, so there is less need for ventilation. Considering the above situation, the auxiliary fuel tank is connected to the wing fuel tank through the ventilation device, thereby sharing a set of ventilation system and a ventilation fuel tank with the wing fuel tank. Therefore, not only the structure of the ventilation subsystem in the fuel supply system is simplified, It also reduces the overall weight of the aircraft. In addition, since the venting device is a closed venting device, it can precisely control the pressure in the fuel tank. When the pressure difference is within a reasonable range, it can not only ensure the normal operation of the auxiliary fuel system, but also prevent the structure of the fuel tank from being damaged due to excessive pressure. damage.
本发明的上述实施方式的通气控制***是一种基于非相似设计的控制***，通过设置压差开关和压差传感器，使两者同时检测辅助油箱3内的无油空间与机外环境的压力差，并对两者的检测结果进行比较来确保压力测量的准确性，提高了油箱结构的安全性和***的可靠性。The ventilation control system of the above-mentioned embodiment of the present invention is a control system based on a non-similar design. By setting a differential pressure switch and a differential pressure sensor, the two can simultaneously detect the pressure of the oil-free space in the auxiliary oil tank 3 and the environment outside the machine. Poor, and compare the test results of the two to ensure the accuracy of pressure measurement, improve the safety of the fuel tank structure and the reliability of the system.
(其他实施方式)(Other implementations)
在上述实施方式中，针对通气装置包括辅助油箱用通气管P2、设置于该 辅助油箱用通气管P2的通气阀V、连接于辅助油箱用通气管P2的速压用通气管P3以及设置于速压用通气管P3的单向阀V1的情况进行了说明，但并不限于此。例如，该辅助油箱3的通气装置也可不包括速压用通气管P3和单向阀V1，可仅包括辅助油箱用通气管P2、设置于该辅助油箱用通气管P2的通气阀V。In the above-mentioned embodiment, the breather device includes the breather pipe P2 for the auxiliary fuel tank, the breather valve V provided on the breather pipe P2 for the auxiliary fuel tank, the breather pipe P3 for rapid pressure connected to the breather pipe P2 for the auxiliary fuel tank, and the breather pipe P3 installed on the speed The case of the one-way valve V1 of the pressure-use vent pipe P3 has been described, but it is not limited thereto. For example, the venting device of the auxiliary fuel tank 3 may not include the rapid pressure vent pipe P3 and the check valve V1, but may only include the vent pipe P2 for the auxiliary fuel tank and the vent valve V provided on the vent pipe P2 for the auxiliary fuel tank.
此外，在上述实施方式中，基于非相似设计的理念，辅助油箱3的通气控制***4包括压差传感器5、辅助燃油控制单元6、压差开关7以及辅助燃油隔离单元8，但并不限于此。例如，也可不从非相似设计的角度出发，可使该通气控制***4仅包括压差传感器5和辅助燃油控制单元6，由此，也能够实现通气阀V的开闭控制。In addition, in the above embodiments, based on the concept of non-similar design, the ventilation control system 4 of the auxiliary fuel tank 3 includes a differential pressure sensor 5, an auxiliary fuel control unit 6, a differential pressure switch 7 and an auxiliary fuel isolation unit 8, but is not limited to this. For example, the ventilation control system 4 may only include the differential pressure sensor 5 and the auxiliary fuel control unit 6 without starting from the non-similar design, so that the opening and closing control of the ventilation valve V can also be realized.
此外，本发明在其范围内，能将各实施方式自由组合，或是将各实施方式适当变形、省略。In addition, within the scope of the present invention, each embodiment can be freely combined, or each embodiment can be appropriately modified or omitted.
符号说明Symbol Description
O 燃油供给***O fuel supply system
LF 飞机左翼LF aircraft left wing
RF 飞机右翼RF aircraft right wing
1 通气油箱1 vent tank
2 机翼油箱2 wing fuel tanks
3 辅助油箱3 Auxiliary fuel tanks
4 通气控制***4 ventilation control system
5 压差传感器5 differential pressure sensor
6 辅助燃油控制单元6 Auxiliary fuel control unit
7 压差开关7 differential pressure switch
8 辅助燃油隔离单元8 Auxiliary fuel isolation unit
P1 机翼油箱用通气管P1 Snorkel for wing fuel tank
P2 辅助油箱用通气管P2 Breather pipe for auxiliary fuel tank
P3 速压用通气管P3 breather for quick pressure
V 通气阀V breather valve
V1 单向阀V1 check valve
Claims (6)
- 一种飞机辅助油箱的通气装置，用于维持所述辅助油箱内的无油空间的气体压力，其特征在于，包括：A ventilation device for an aircraft auxiliary fuel tank, for maintaining the gas pressure in the oil-free space in the auxiliary fuel tank, characterized in that it comprises:辅助油箱用通气管，所述辅助油箱用通气管连接在所述辅助油箱与设置于飞机机翼的机翼油箱之间，使得所述辅助油箱内的无油空间与所述机翼油箱内的无油空间流体连通；以及The auxiliary fuel tank is connected with a ventilation pipe for the auxiliary fuel tank, and the auxiliary fuel tank is connected between the auxiliary fuel tank and the wing fuel tank arranged on the wing of the aircraft, so that the oil-free space in the auxiliary fuel tank is connected to the air in the wing fuel tank. oil-free space fluid communication; and通气阀，所述通气阀设置于所述辅助油箱用通气管的中途，根据所述辅助油箱内的无油空间与机外环境的压力差的大小打开、关闭或者调节开度。A breather valve, the breather valve is arranged in the middle of the breather pipe for the auxiliary fuel tank, and is opened, closed or adjusted according to the pressure difference between the oil-free space in the auxiliary fuel tank and the environment outside the machine.
- 如权利要求1所述的飞机辅助油箱的通气装置，其特征在于，所述通气阀是安全阀。The ventilation device for an aircraft auxiliary fuel tank according to claim 1, wherein the ventilation valve is a safety valve.
- 如权利要求1所述的飞机辅助油箱的通气装置，其特征在于，还包括：The ventilation device of aircraft auxiliary fuel tank as claimed in claim 1, is characterized in that, also comprises:速压用通气管，所述速压用通气管连接于所述辅助油箱用通气管的中途，供机外环境气体引入；以及A breather pipe for rapid pressure, which is connected to the middle of the breather pipe for the auxiliary fuel tank, for the introduction of external ambient gas; and单向阀，所述单向阀设置于速压用通气管的中途，仅允许被引入的所述机外环境气体向所述辅助油箱流动。A one-way valve, the one-way valve is arranged in the middle of the breather pipe for rapid pressure, and only allows the introduced external ambient air to flow to the auxiliary oil tank.
- 一种飞机燃油供给***，包括：An aircraft fuel supply system, comprising:通气油箱，所述通气油箱通过一端设置于机外的通气油箱用通气管与机外环境流体连通；A ventilating oil tank, the ventilating oil tank is in fluid communication with the environment outside the machine through a ventilating pipe provided at one end of the ventilating oil tank outside the machine;机翼油箱，所述机翼油箱贮存有向飞机的发动机输送的燃油；Wing fuel tanks storing fuel delivered to the engines of the aircraft;机翼油箱用通气管，所述机翼油箱用通气管连接所述机翼油箱内的无油空间与所述通气油箱内的无油空间；以及a vent pipe for the wing fuel tank, the vent pipe for the wing fuel tank connects the oil-free space in the wing fuel tank with the oil-free space in the vented fuel tank; and辅助油箱，所述辅助油箱贮存有向所述机翼油箱补给的燃油，an auxiliary fuel tank storing fuel to replenish the wing tanks,其特征在于，It is characterized in that,还包括权利要求1至3中任一项所述的飞机辅助油箱的通气装置。It also includes the ventilation device of the aircraft auxiliary fuel tank according to any one of claims 1 to 3.
- 一种飞机辅助油箱的通气控制***，用于对权利要求1至3中任一项所述的飞机辅助油箱的通气装置进行控制，其特征在于，包括：A ventilation control system for an aircraft auxiliary fuel tank, used to control the ventilation device for an aircraft auxiliary fuel tank according to any one of claims 1 to 3, characterized in that it comprises:压差传感器，所述压差传感器检测所述辅助油箱内的无油空间与所述机外环境的压力差；以及a differential pressure sensor that detects a pressure difference between an oil-free space in the auxiliary fuel tank and the external environment; and辅助燃油控制单元，所述辅助燃油控制单元接收由所述压差传感器检测到的所述压力差的检测结果，并且根据所述压力差的检测结果对所述通气阀进行打开、关闭。An auxiliary fuel control unit, the auxiliary fuel control unit receives the detection result of the pressure difference detected by the pressure difference sensor, and opens and closes the ventilation valve according to the detection result of the pressure difference.
- 如权利要求5所述的飞机辅助油箱的通气控制***，其特征在于，还包括：The ventilation control system of aircraft auxiliary fuel tank as claimed in claim 5, is characterized in that, also comprises:压差开关，所述压差开关感知所述辅助油箱内的无油空间与所述机外环境的压力差，并且根据所述压力差的感知结果打开、关闭，a differential pressure switch, the differential pressure switch senses the pressure difference between the oil-free space in the auxiliary oil tank and the external environment, and is opened and closed according to the sensing result of the pressure difference,所述辅助燃油控制单元接收来自所述压差开关的感知结果，对所述检测结果和所述感知结果进行比较，当比较结果一致时，所述辅助燃油控制单元判定所述压力差的检测结果正确。The auxiliary fuel control unit receives the sensing result from the differential pressure switch, compares the sensing result with the sensing result, and when the comparison results are consistent, the auxiliary fuel control unit determines the detection result of the pressure difference correct.
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|---|---|---|---|
| CN202111158140.8 | 2021-09-30 | ||
| CN202111158140.8A CN113772107B (en) | 2021-09-30 | 2021-09-30 | Ventilation device of aircraft auxiliary fuel tank, ventilation control system and aircraft fuel supply system |
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| PCT/CN2021/141885 WO2023050615A1 (en) | 2021-09-30 | 2021-12-28 | Venting device and venting control system for auxiliary tank of aircraft, and aircraft fuel supply system |
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| WO (1) | WO2023050615A1 (en) |
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| CN113772107B (en) * | 2021-09-30 | 2023-02-03 | 中国商用飞机有限责任公司 | Ventilation device of aircraft auxiliary fuel tank, ventilation control system and aircraft fuel supply system |
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| CN113772107B (en) | 2023-02-03 |
| CN113772107A (en) | 2021-12-10 |
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