CN109441637B - An integrated system and method of aircraft surplus power using nitrogen pressurized fuel tank - Google Patents

Abstract

The invention relates to an airplane rich electric energy comprehensive utilization system utilizing nitrogen to pressurize an oil tank, which comprises: the system comprises a membrane separation system utilizing surplus power, a pressurized oil tank energy storage system and an energy release system. The membrane separation system utilizing surplus electric power can fully utilize surplus electric energy in an airplane power grid, and the airborne membrane separation system is driven to convert air introduced from the outside of an airplane into high-pressure oxygen and nitrogen. The boosting oil tank energy storage system can fully utilize huge space in the fuel oil tank, and the obtained high-pressure nitrogen is stored in the fuel oil tank. The energy release system can dynamically release high-pressure nitrogen stored in the fuel oil tank for refrigeration and power generation, and meets the refrigeration and short-time high-power electricity utilization requirements of the airplane. The invention fully utilizes the surplus electric energy of the airplane, realizes the transverse conversion, dispatching and storage of the electric energy from the air pressure energy to the cold energy and the electric energy, and ensures the efficient and safe work of the airplane. Has wide application in the aviation field.

Description

An integrated system and method of aircraft surplus power using nitrogen pressurized fuel tank

technical field

The invention belongs to the field of aerospace, and relates to a system and method for comprehensive utilization of aircraft surplus electric power by utilizing a nitrogen pressurized fuel tank.

technical background

With the continuous development of modern aircraft to more electricity and full electricity, the power demand of airborne equipment is increasing, and the power generation of airborne generators is also rising. The current rated power generation of airborne generators is designed to meet the maximum power demand under normal operating conditions. However, because the power demand of airborne equipment is not always at the maximum demand state, it will change with the flight stage. , causing the generator to have surplus power generation capacity in different flight stages, that is, the generator will be in an underload state. In some extreme cases, such as when high-power equipment such as laser weapons and radars work at the same time, the generator will have a short-term power shortage, and the generator will be overloaded for a short time. Whether it is underload or overload, it will adversely affect the operation of the generator. At present, the main way for aircraft to utilize surplus electricity is to store surplus electricity in batteries and supercapacitors. Due to the limited capacity of batteries and supercapacitors, it is difficult to utilize and store the excess airborne power generation capacity on a large scale. Therefore, a dynamic scheduling method that fully and reasonably utilizes the surplus power generation capacity of the aircraft power grid and can make up for the required power when the power grid is insufficient is of great significance to the power utilization of the aircraft and the good operation of the generator, so it has become urgent. issues that need resolving.

SUMMARY OF THE INVENTION

According to one aspect of the present invention, there is provided a system for comprehensive utilization of aircraft surplus power using nitrogen pressurized fuel tanks, which is characterized by comprising:

Electric motors, frequency converters, detection elements, controllers, on-board membrane separation systems, fuel tank air pressure sensors and fuel tanks, turbo electronic equipment air cooling systems, generators, super capacitors,

in:

The detection element is used to detect the current state of the aircraft grid of the aircraft. When there is surplus power in the aircraft grid,

The motor is used to convert part or all of the surplus power in the power grid into mechanical energy under the control of the controller, completing the extraction of the aircraft's surplus power,

The compressor in the airborne membrane separation system is driven by the mechanical energy to perform work, and compresses the air introduced from the outside of the aircraft into high-pressure gas, which is then separated into high-pressure oxygen and high-pressure nitrogen by the airborne membrane separation system,

The high-pressure oxygen is delivered to the aircraft cabin to supply air, adjust the pressure and oxygen supply inside the cabin, and make full use of the fuel tank for storing the high-pressure nitrogen in the space therein.

The fuel tank air pressure sensor is used to detect the air pressure in the fuel tank;

The turbine is used to be propelled by high-pressure nitrogen from the fuel tank. After the high-pressure nitrogen pushes the turbine, it becomes low-temperature, low-pressure nitrogen. The low-temperature and low-pressure nitrogen is used to cool the air-cooling system of the electronic equipment on the aircraft.

The generator, driven by the turbine, produces electricity to feed the supercapacitor and/or the aircraft grid.

According to another aspect of the present invention, a method for comprehensive utilization of aircraft surplus electric power based on the above-mentioned comprehensive utilization system for aircraft surplus electric power using nitrogen pressurized fuel tank is provided.

Description of drawings

FIG. 1 is an overall schematic diagram of a comprehensive utilization system of aircraft surplus power utilizing nitrogen pressurized fuel tanks.

Figure 2 is a schematic diagram of an airborne membrane separation system.

Figure 3 is a schematic diagram of the operation of the membrane separation system utilizing surplus power.

Figure 4 is a schematic diagram of energy conversion.

Figure 5 is a schematic diagram of the working of the pressurized fuel tank energy storage system.

Figure 6 is a schematic diagram of the work of the energy release system.

Fig. 7 is the working flow chart of the system.

Description of reference numbers:

Motor(101) Frequency converter(102) Detection element(103)

Aircraft Power Grid (104) Controller (105) Airborne Membrane Separation System (106)

Aircraft cabin air supply system(107) Temperature sensor(1061)

Compressor(1062)

Membrane Separation System Solenoid Valve(1063) Filter(1064)

Hollow Fiber Membrane Separator(1065) Fuel Tank Filling Solenoid Valve(201)

Fuel tank air pressure sensor(202) Fuel tank(203)

Fuel tank air pressure relief valve(204) Fuel tank air release solenoid valve(301)

Turbine(302) Electronic Equipment Air Cooling System(303)

Generator(304) Supercapacitor(305) Controllable Switch(306)

Detailed ways

Related to the above-mentioned problems in the prior art, while the electrical energy cannot be reasonably utilized, the on-board cooling energy may be insufficient. As the power of the on-board equipment of modern aircraft is getting bigger and bigger, without the obvious improvement of efficiency, the calorific value of the equipment will also increase, causing its temperature to rise sharply, which will ultimately greatly affect the safety of the on-board equipment. Efficient work. Therefore, the timely and reasonable dissipation of the heat generated by the airborne equipment through the annular system is of great significance to the safe and efficient work of the aircraft. However, as the growth of the airborne heat sink of modern aircraft seriously lags behind the increase of power, it is increasingly unable to meet the heat dissipation requirements of the aircraft. Therefore, the current urgent demand for airborne equipment to generate more cooling energy in a reasonable and effective way.

The aircraft fuel tank is used to store fuel for the combustion of the aircraft engine. With the flight of the aircraft, the fuel inside the fuel tank is continuously consumed, leaving a huge space. The general practice is to fill the inside of the fuel tank with nitrogen, so that the pressure on the oil surface inside the fuel tank is slightly higher than the atmospheric pressure. This method not only ensures that the fuel inside the fuel tank is isolated from the air to prevent fire, but also improves the high-altitude system energy of the fuel system. . Although this method ensures the reliability of fuel utilization, it does not make full use of the huge space inside the fuel tank, which is of limited help in improving the energy utilization rate of the aircraft.

The nitrogen charged into the fuel tank in the current aircraft is mainly generated by the on-board membrane separation system, which is mainly composed of a temperature sensor, a compressor, a solenoid valve, a filter and a hollow fiber membrane separator. The schematic diagram is shown in Figure 2. shown. The working principle of the airborne membrane separator is to use the compressor to compress the air introduced from the outside into high-pressure gas, and then separate the high-pressure air into high-pressure nitrogen and high-pressure oxygen through the central control fiber membrane separator. Oxygen is used to supply the cabin due to pressurization inside the fuel tank.

To sum up, the current airborne surplus power generation capacity has not been fully utilized, and the cooling capacity of the aircraft is increasingly unable to meet the cooling needs of the airborne equipment. At the same time, the huge space inside the fuel tank has not been fully utilized, and The onboard membrane separation system can generate nitrogen for internal use in the fuel tank.

Therefore, the inventors of the present invention realized that converting surplus electrical energy into air pressure energy, utilizing the huge space inside the fuel tank for storage, and converting air pressure energy into cold energy and electrical energy at a reasonable time has great significance for the efficient and reasonable use of aircraft energy. The significance of the project has a strong feasibility.

In order to solve the problems that the surplus power of the aircraft cannot be reasonably utilized and the heat sink capacity is insufficient during the flight of the aircraft, according to one aspect of the present invention, a system for comprehensive utilization of aircraft surplus power with a nitrogen pressurized fuel tank is proposed, which can make full use of the aircraft surplus power. The electrical energy is converted into the pressure potential energy of the gas by using the membrane separation system of the surplus electricity, and stored in the fuel tank, which solves the problem that the electrical energy cannot be fully utilized and stored. Reasonable selection of gas storage and degassing processes, dynamic adjustment of the cooling capacity and power generation of the gas to achieve dynamic matching of the heat sink and power requirements of the airborne equipment, and solve the problem of insufficient heat sink and short-term power shortage during the flight of the aircraft predicament. Therefore, the present invention not only fully utilizes the airborne energy, realizes the lateral conversion and scheduling of electric energy to cold energy, but also ensures the efficient and safe operation of the aircraft.

According to another aspect of the present invention, there is provided a comprehensive utilization system of aircraft surplus power utilizing nitrogen pressurized fuel tanks, including: a membrane separation system utilizing excess power, a pressurized fuel tank energy storage system, and an energy release system,

The membrane separation system utilizing surplus power includes a motor (101), a frequency converter (102), a detection element (103), a controller (105), an onboard membrane separation system (106), and an aircraft cabin air supply system (107);

The pressurized fuel tank energy storage system includes: a fuel tank charging solenoid valve (201), a fuel tank air pressure sensor (202), a fuel tank (203), and a fuel tank air pressure safety valve (204);

The energy release system includes: a fuel tank bleed solenoid valve (301), a turbine (302), an air cooling system for electronic equipment (303), a generator (304), a super capacitor (305) and a controllable switch (306).

Referring to FIG. 3 , the membrane separation system utilizing surplus power utilizes the detection element (103) to continuously detect the current state of the aircraft grid (104), and when there is surplus power generation capacity in the aircraft grid (104), the controller (105) According to the demand of the system and the state of the aircraft, part or all of the surplus power generation capacity in the power grid is converted into mechanical energy by the electric motor (101), and the extraction of the surplus power of the aircraft is completed. The rotating mechanical energy obtained by the electric motor (101) is used to drive the compressor (1062) in the onboard membrane separator (106) to do work, compress the air introduced from the outside of the aircraft into high pressure gas, and then the onboard membrane separator (106) separated into high-pressure oxygen and nitrogen. Oxygen is supplied to the cockpit, and nitrogen is delivered to the pressurized fuel tank energy storage system, which realizes the conversion of surplus electrical energy into air pressure energy, and ensures the oxygen supply of the aircraft cockpit. The energy conversion in the airborne membrane separation system is shown in the upper dashed box in Figure 4, including extracting surplus power from the aircraft grid (104), converting it into rotational mechanical energy through the motor (101), and then passing it through the compressor (1062). ) ( FIG. 2 ) becomes the air pressure energy of the air, and finally becomes the air pressure energy of the separated nitrogen gas after passing through the airborne membrane separation system (106).

Referring to Fig. 5, the pressurized fuel tank energy storage system can make full use of the space in the fuel fuel tank, and store high-pressure nitrogen gas obtained by the onboard membrane separation system (106) in the fuel fuel tank (203). The fuel tank charging solenoid valve (201) is used to control the on-off of the charging gas circuit; the fuel tank air pressure sensor (202) is used to monitor the current air pressure in the fuel tank in real time; Within the range, when the safety pressure is exceeded, it will automatically deflate and release the pressure.

Referring to FIG. 6 , the energy release system can release the high-pressure nitrogen stored in the fuel tank (203) through the fuel tank bleed solenoid valve (301), and the high-pressure nitrogen flows through the turbine (302) and pushes the turbine (302) to perform work. The nitrogen gas becomes low temperature and low pressure, and finally flows into the electronic equipment (303) for cooling the electronic equipment. The work done by the turbine (302) is converted into electrical energy by the generator (304) and supplied to the super capacitor (305). The fuel tank bleed solenoid valve (301) is used to control the on-off of the fuel tank bleed gas circuit, which is controlled by the controller (105); according to an embodiment of the present invention, the generator (304) is coaxial with the turbine (302) connected to convert the external work done by the expansion of the turbine (302) into electrical energy; the controllable switch (306) is used to control the electrical energy stored in the super capacitor (305) to be fed back to the power grid to make up for possible short-term occurrences in the power grid The power is insufficient, which is controlled by the controller (105). The energy conversion process in the energy release system is shown in the dashed box at the bottom of Figure 4. The energy conversion process is the nitrogen gas pressure energy stored in the fuel tank (203), after passing through the turbine (302) and performing work on it, the energy conversion process is converted. The energy is divided into two parts, one part is supplied to the air cooling system (303) of the electronic equipment in the form of cold energy, and the other part is converted into rotating mechanical energy to drive the generator (304) to do work, and finally the generator (304) generates electricity and feeds back to the aircraft power grid (104).

The controller (105) is configured to receive the grid information output by the detection element (103), the pressure information of the fuel tank air pressure sensor (202), and the information of the air temperature sensor (1061) in the membrane separation system, according to the current operation of the aircraft Status and cooling demand, control the surplus power input by the inverter (102) to the motor, and turn on/off the switches of the membrane separation system solenoid valve (1063), the fuel tank charging solenoid valve (201) and the fuel tank venting solenoid valve (301). Operation, control the utilization of electric energy in the current grid, gas separation of membrane separation system, gas energy storage and gas release energy release of the system.

The advantages of the system and method for comprehensive utilization of aircraft surplus power using nitrogen pressurized fuel tanks according to the present invention include:

1. The invention makes full use of the volume of the fuel tank, converts the surplus electric energy into the high-pressure potential energy of the gas, and stores it, solves the problem that the surplus electric energy cannot be fully utilized and stored, and improves the energy utilization rate of the system.

2. Since the fuel tank is filled with high-pressure nitrogen, it will do work on the fuel, and the fuel will have more kinetic energy in the process of delivering the fuel to the engine, so the fuel delivery pump will do less work on the fuel, or even No, therefore, the invention reduces the power consumption of the fuel pump and saves energy.

3. The invention can dynamically adjust the energy storage and refrigeration of the system. When the refrigeration capacity of the aircraft is sufficient, the excess electric energy is converted into high-pressure gas for storage. When the cooling capacity of the aircraft is insufficient, the stored high-pressure gas is released for refrigeration, and the turbine The remaining working power is converted into electrical energy, which not only matches the cooling needs of the aircraft in time, and alleviates the dilemma that the current airborne heat sink is increasingly unable to meet the cooling needs, but also realizes the lateral conversion of energy, improves the utilization rate of energy, and ensures Airplanes fly efficiently and safely.

4. The invention converts all the surplus power in the aircraft power grid into cold energy through the system through reasonable scheduling, and can feed back the power generated by the super generator to the power grid when the instantaneous power in the power grid is insufficient. Therefore, The invention makes full use of the power generation capacity of the main generator and improves the power supply performance of the aircraft power grid.

5. The invention makes full use of the existing airborne equipment, reasonably connects the electrical system and the air compression cycle system, opens up the energy conversion chain from electric energy to cold energy and back to electric energy, makes full use of electric energy, and matches the demand for cold energy. , reducing the generation and consumption of other energy sources, and the energy conversion is efficient and reasonable.

The embodiments of the present invention will be further described in detail below with reference to the accompanying drawings.

Referring to FIG. 1 , according to an embodiment of the present invention, a comprehensive utilization system for aircraft surplus electricity utilizing nitrogen pressurized fuel tanks includes: a membrane separation system utilizing excess electricity, a pressurized fuel tank energy storage system, and an energy release system,

in,

The membrane separation system utilizing surplus power includes a motor (101), a frequency converter (102), a detection element (103), a controller (105), an onboard membrane separation system (106), and an aircraft cabin air supply system (107);

The pressurized fuel tank energy storage system includes: a fuel tank charging solenoid valve (201), a fuel tank air pressure sensor (202), a fuel fuel tank (203) and a fuel tank air pressure safety valve (204);

The energy release system mainly includes a fuel tank bleed solenoid valve (301), a turbine (302), an air cooling system for electronic equipment (303), a generator (304), a super capacitor (305) and a controllable switch (306).

Fig. 3 shows a schematic diagram of a membrane separation system utilizing surplus power according to an embodiment of the present invention, wherein a detection element (103) is installed on the single-phase electric wire of the generator output to detect the single-phase output of the generator The effective value of the current is used to judge the working state of the generator and the working state of the aircraft power grid (104). The input of the frequency converter (102) is connected to the aircraft grid (104), and the output of the inverter (102) is connected to the motor (101). The controller (105) controls the electrical energy input from the grid to the motor (101). The rated power of the selected electric motor (101) should not be less than the maximum surplus power generation capacity of the aircraft power grid (104). In this system, the signal of the detection element (103) is the input of the controller (105), and the control signal of the frequency converter (102) is the output of the controller (105).

2 is a schematic diagram of a membrane separation system utilizing surplus power according to an embodiment of the present invention, wherein the compressor (1062) is coaxially connected to the motor (101), and the power of the compressor (1062) requires Match with the motor (101). The function of the compressor is to compress the low-pressure air introduced in the onboard membrane separation system into high-pressure air. The airborne membrane separation system (106) includes a temperature sensor (1061), an air compressor (1062), a membrane separation system solenoid valve (1063), a filter (1064), and a hollow fiber membrane separator (1065) for separating The air is separated into oxygen and nitrogen. The temperature sensor (1061) is used to detect the current temperature of the air drawn from the air, and its detection signal is input to the controller (105). According to an embodiment of the present invention, the hollow fiber membrane separator (1065) needs to ensure that the bleed air temperature is lower than 55°C during operation. When the bleed air temperature exceeds 55°C, close the bleed air solenoid valve (1063) to prevent the high temperature air from damaging the hollow fiber membrane. The hollow fiber membrane separator can only have high working efficiency when it works under relatively high pressure. According to an embodiment of the present invention, the gas pressure at the outlet of the air compressor (1062) is maintained at 1 MPa.

Fig. 5 shows a schematic diagram of a supercharged fuel tank energy storage system according to an embodiment of the present invention, wherein the fuel tank charging solenoid valve (201) is used to control the on-off of the fuel tank charging gas circuit, which is controlled by the controller (105). ) control; the fuel tank air pressure sensor (202) is used to detect the air pressure in the fuel tank (203), and its measurement range needs to meet the measurement requirements of the fuel tank pressure; the space other than the fuel inside the fuel tank (203) is used to store the on-board membrane The high-pressure nitrogen obtained by the separation system (106), so the pressure of the fuel tank must exceed the maximum storage pressure set in this system. The oil tank air pressure safety valve (204) is used to remove the air in the oil tank in time when the air pressure in the oil tank is higher than the safety pressure, and quickly reduce the air pressure in the oil tank to below the safety pressure.

Figure 6 shows a schematic diagram of a bleed air refrigeration system according to an embodiment of the present invention. The oil tank bleed solenoid valve (301) is used to control the on-off of the oil tank bleed air circuit, which is controlled by the controller (105). The turbine (302) is used to expand and refrigerate the high-pressure gas stored in the fuel tank (203), and lead the obtained low-temperature nitrogen gas to the electronic equipment cooling system (303), which plays the role of cooling the electronic equipment. Therefore, under the maximum storage pressure set by the system, the maximum cooling capacity of the selected turbine (302) should meet the cooling demand of the system. In order to reasonably utilize and store the mechanical energy emitted by the turbine (302), according to an embodiment of the present invention, the generator (304) is coaxially connected to the turbine (302), and the output of the generator (304) is connected to the super capacitor (305) connect. In order to control the discharge of the super capacitor (305) and make up for possible short-term power shortage in the power grid, the super capacitor (305) and the aircraft power grid (104) are connected by wires, and a controllable switch (306) is added in the middle. The controllable switch (306) is controlled by the controller (105) and can be controlled at any time.

In the present invention, the controller (105) is the part that implements the dynamic scheduling. (105) of the controller is used to:

According to the grid information output by the detection element (103), the pressure information of the fuel tank gas pressure sensor (202), and the current working state and cooling demand of the aircraft, the output of the frequency converter (102) is controlled, thereby controlling the utilization of electric energy and gas consumption in the grid compression;

According to the cooling demand of the system and the air pressure of the fuel tank, determine whether to open or close the fuel tank charging solenoid valve (201) and the fuel tank venting solenoid valve (301), so as to control the system to be in the charging or deflating state;

By detecting the state of the aircraft power grid (104), it is determined whether to open or close the controllable switch (306), so as to decide whether to feed back the electric energy in the super capacitor (305) to the power grid.

What is shown in FIG. 7 is the comprehensive utilization method of aircraft surplus power based on the above-mentioned comprehensive utilization system of aircraft surplus power using nitrogen pressurized fuel tank of the present invention, which includes:

A0) After the aircraft starts to fly, the invented system starts to work, the system is initialized first, and initial values are assigned to each parameter;

A1) Detect the temperature of the air introduced into the membrane separator through the temperature sensor (1061), when the temperature exceeds the normal range (55°C) acceptable to the hollow fiber membrane separation system, close the solenoid valve (1063) of the membrane separation system, and shut down The electric motor (101), the system does not pressurize the air, and the on-board membrane separation system (106) does not work;

A2) When the intake air temperature of the system is within the normal range, the gas pressure inside the fuel tank is detected by the fuel tank air pressure sensor (202), and the current state of the aircraft power grid (104) is detected by the sensing detection element (103), and the detected The signal is input to the controller (105),

A3) The controller (105) judges whether the pressure inside the fuel tank (203) exceeds the rated pressure;

A4) If the gas pressure inside the fuel tank (203) does not exceed the rated pressure, the controller (105) opens the fuel tank charging solenoid valve (201), and then judges the current aircraft power grid (104) according to the input signal of the detection element (103). ) has surplus electricity,

A5) If there is surplus power, calculate the current surplus power Pu, adjust the frequency converter (102) to make the input power of the motor (101) be the force Pu, and then the motor (101) drives the compressor (1062) to The _N2 produced by the carrier membrane separation system is compressed into the fuel tank (203),

A6) If there is no surplus power, continue to judge whether the aircraft power grid (104) is currently overloaded. If the aircraft power grid (104) is overloaded, jump to the working process of the deflation refrigeration system, and open the fuel tank deflation solenoid valve (301) to start discharging Air-cooled power generation, so that the electric energy generated by the generator (304) can supply power to the grid;

A7) If the aircraft generator is not currently overloaded, the process proceeds to step A8);

A8) The controller (105) judges whether the cooling energy used for the cooling of the air cooling system (303) of the electronic equipment is insufficient, and if the cooling energy is insufficient, it opens the fuel tank bleed solenoid valve (301) to store it in the fuel tank (203) The gas is released, the gas passes through the turbine (302) to push the turbine to do work, and drives the generator (304) to generate electricity, and at the same time, the gas changes from high-pressure gas to low-temperature and low-pressure gas, and is sent to the electronic equipment air cooling system (303) for cooling Electronic equipment, the generator (304) charges the supercapacitor (305) with the generated electric energy; if the cold energy is sufficient, the process returns to step A1) and starts again from A1);

A9) If it is determined in step A3) that the pressure inside the fuel tank (203) exceeds the rated pressure, open the fuel tank bleed solenoid valve (301) to start deflation and refrigeration, release the gas inside the fuel tank (203), and lower the fuel tank (203) Internal pressure;

A10) At the end of a work cycle, the process judges whether the flight of the current aircraft ends, if not, the process returns to step A1) to start a new cycle; if the flight ends, the process ends.

According to another aspect of the present invention, a method for comprehensive utilization of aircraft surplus power based on a comprehensive utilization system for aircraft surplus power utilizing nitrogen pressurized fuel tanks is provided, and the comprehensive utilization system for aircraft surplus power includes:

Electric motor (101), frequency converter (102), detection element (103), controller (105), onboard membrane separation system (106), fuel tank air pressure sensor (202) and fuel tank (203), turbine (302), Generator (304), Supercapacitor (305),

It is characterized by including:

A1) Detect the temperature of the air introduced into the membrane separator, and when the temperature exceeds the normal range (55°C) acceptable to the hollow fiber membrane separation system (1065), shut down the motor (101) to make the onboard membrane separation system (106) ) is in an inoperative state;

A2) When the intake air temperature of the system is within the normal range, detect the gas pressure inside the fuel tank (203), use the detection element (103) to detect the current state of the aircraft power grid (104), and input the detected signal to the controller (105),

A4) When the gas pressure inside the fuel tank (203) does not exceed the rated pressure, open the air-filled gas path from the onboard membrane separation system (106) to the fuel tank (203), and then according to the input signal of the detection element (103) , judging whether the current aircraft grid (104) has surplus power,

A5) When the aircraft power grid (104) has surplus power, determine the current surplus power Pu, adjust the frequency converter (102) to make the input power of the motor (101) be Pu, and use the motor (101) to drive the onboard membrane separation system The compressor (1062) in (106) compresses the nitrogen gas produced by the on-board membrane separation system into the fuel tank (203),

A6) When the aircraft power grid (104) has no surplus power, determine whether the aircraft power grid (104) is currently overloaded. If the aircraft power grid (104) is overloaded, the compressed nitrogen in the fuel tank (203) is used to drive the turbine (302) to drive power generation The aircraft (304) generates electricity, and the electric power generated by the generator (304) is used to supply power to the aircraft power grid (104),

A7) If the aircraft grid (104) is not currently overloaded, the process proceeds to step A8);

A8) The controller (105) judges whether the cooling energy used for cooling the air cooling system (303) of the electronic equipment is insufficient. If the cooling energy is insufficient, the compressed nitrogen in the fuel tank (203) is used to drive the turbine (302) to drive the generator (304) Power generation, while the compressed nitrogen gas changes from high pressure gas to low temperature and low pressure gas, and is sent to the electronic equipment air cooling system (303) of the aircraft to cool the electronic equipment, and uses the electrical energy generated by the generator (304) Charge the supercapacitor (305); if the cold energy is sufficient, the process returns to step A1) and repeats from A1).

Claims (9)

1. The utility model provides an utilize surplus electric power of aircraft of nitrogen gas pressure boost oil tank to synthesize utilizes system which characterized in that includes:

a motor (101), a frequency converter (102), a detection element (103), a controller (105), an onboard membrane separation system (106), a fuel tank air pressure sensor (202), a fuel oil tank (203), a turbine (302), a generator (304) and a super capacitor (305),

wherein:

the detection element (103) is used to detect the current state of the aircraft electrical network (104) of the aircraft and, when there is surplus electrical power in the aircraft electrical network (104),

the electric motor (101) is used for converting part or all of surplus electric power in the power grid into mechanical energy under the control of the controller (105), so that the extraction of the surplus electric power of the airplane is completed,

the compressor (1062) in the on-board membrane separation system (106) is driven by said mechanical energy to perform work, compressing the air introduced from outside the aircraft into a high-pressure gas, which is subsequently separated by the on-board membrane separation system (106) into high-pressure oxygen and high-pressure nitrogen,

said high pressure oxygen is delivered to the cabin of the aircraft for supply (107), regulating the pressure and oxygen supply inside the cabin,

the fuel tank (203) is fully utilized for storing the high-pressure nitrogen in the space therein,

the tank air pressure sensor (202) is used for detecting air pressure in a fuel oil tank (203);

the turbine (302) is used for being pushed by high-pressure nitrogen from a fuel oil tank (203), the high-pressure nitrogen pushes the turbine (302) to work and then turns into low-temperature and low-pressure nitrogen, and the low-temperature and low-pressure nitrogen is used for cooling electronic equipment on the airplane by an electronic equipment air cooling system (303),

the generator (304) generates electrical power, driven by the turbine (302), which is supplied to the super capacitor (305) and/or the aircraft electrical grid (104).

2. The comprehensive utilization system of surplus electric power of an aircraft according to claim 1, further comprising:

the oil tank air bleed solenoid valve (301) is used for controlling the on-off of an oil tank air bleed air path and is controlled by the controller (105);

and the controllable switch (306) is used for controlling the connection and disconnection of the super capacitor (305) to the power line of the aircraft power grid (104) and is controlled by the controller (105).

3. The comprehensive utilization system of surplus electric power of an aircraft according to claim 1 or 2, characterized by further comprising:

and the oil tank inflation electromagnetic valve (201) is used for controlling the on-off of an inflation gas path from the airborne membrane separation system (106) to the fuel oil tank (203).

4. The comprehensive utilization system of surplus electric power of an aircraft according to claim 1 or 2, characterized by further comprising:

and the tank air pressure safety valve (204) is used for automatically deflating and releasing pressure when the air pressure of the fuel tank (203) exceeds the safety pressure.

5. The comprehensive utilization method of the surplus electric power of the airplane based on the comprehensive utilization system of the surplus electric power of the airplane utilizing the nitrogen to pressurize the oil tank comprises the following steps:

a motor (101), a frequency converter (102), a detection element (103), a controller (105), an onboard membrane separation system (106), a fuel tank air pressure sensor (202), a fuel oil tank (203), a turbine (302), a generator (304) and a super capacitor (305),

it is characterized by comprising:

A1) detecting the temperature of the air introduced into the membrane separator, and when the temperature is equal to or higher than 55 ℃, shutting down the motor (101) to enable the onboard membrane separation system (106) to be in an idle state;

A2) when the inlet air temperature of the system is lower than 55 ℃, the air pressure in the oil tank is detected, the current state of an aircraft power grid (104) of the aircraft is detected by a detection element (103), and the detected signal is input to a controller (105),

A3) the controller (105) determines whether the pressure inside the fuel tank (203) exceeds a rated pressure,

A4) when the gas pressure in the fuel oil tank (203) does not exceed the rated pressure, the charging gas path from the airborne membrane separation system (106) to the fuel oil tank (203) is opened, then whether the current aircraft power grid (104) has surplus power or not is judged according to the input signal of the detection element (103),

A5) when the airplane power grid (104) has surplus power, determining the current surplus power Pu, adjusting the frequency converter (102) to enable the input power of the motor (101) to be Pu, driving a compressor (1062) in the airborne membrane separation system (106) by the motor (101) to compress nitrogen produced by the airborne membrane separation system into a fuel oil tank (203),

A6) when the aircraft power grid (104) has no surplus power, judging whether the aircraft power grid (104) is overloaded currently, if the aircraft power grid (104) is overloaded, driving a turbine (302) to drive a generator (304) to generate power by using compressed nitrogen in a fuel oil tank (203), and supplying the power to the aircraft power grid (104) by using the power generated by the generator (304),

A7) if the aircraft electrical grid (104) is not currently overloaded, processing proceeds to step A8);

A8) the controller (105) judges whether the cooling energy for cooling the electronic equipment air cooling system (303) is insufficient, if the cooling energy is insufficient, the turbine (302) is driven by the compressed nitrogen in the fuel oil tank (203) to drive the generator (304) to generate electricity, meanwhile, the compressed nitrogen is changed into low-temperature and low-pressure gas from high-pressure gas, and the low-temperature and low-pressure gas is sent to the electronic equipment air cooling system (303) of the airplane to cool the electronic equipment, and the super capacitor (305) is charged by the electric energy generated by the generator (304); if the cold energy is sufficient, the process returns to step A1) and is resumed from A1).

6. The method for comprehensively utilizing surplus electric power of an aircraft according to claim 5, characterized by further comprising:

judging whether the pressure inside the fuel oil tank (203) exceeds the rated pressure by using the controller (105);

when the pressure in the fuel oil tank (203) is judged to exceed the rated pressure, a tank air bleed solenoid valve (301) is opened to start air bleed cooling, and/or air bleed pressure relief is carried out by using an air pressure safety valve (204) of the fuel oil tank (203).

7. The method for comprehensively utilizing surplus power of an aircraft according to claim 5 or 6, characterized by further comprising:

after step A8) is performed, it is determined whether the current flight of the aircraft is finished, and if not, the process returns to step a1) to start a new cycle; if the flight is over, the process ends.

8. The method for comprehensively utilizing surplus electric power of an aircraft according to claim 5 or 6, characterized by comprising the following steps:

the step A1) comprises the following steps: the temperature of the air introduced into the membrane separator is detected by an intake air temperature sensor (1061), and when the temperature is equal to or higher than 55 deg.c, a membrane separation system solenoid valve (1063) is closed,

the step A2) comprises the following steps: the gas pressure inside the fuel tank is detected by a fuel tank pressure sensor (202),

the step A4) comprises the following steps: and opening a tank inflation solenoid valve (201) from the onboard membrane separation system (106) to an inflation gas path of a fuel tank (203).

9. The method for comprehensively utilizing surplus electric power of an aircraft according to claim 5 or 6, characterized by comprising the following steps:

when it is judged in the step A8 that the cooling energy for cooling the electronic equipment air cooling system (303) is insufficient, the compressed nitrogen in the fuel tank (203) drives the turbine (302) to drive the generator (304) to generate power by opening the tank bleed solenoid valve (301) on the gas path from the fuel tank (203) to the turbine (302).

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