Dual fuel dispensing system based on flight altitude and attitude
By using a dual-fuel blending system based on flight altitude and attitude, the blending ratio of SAF and RP-3 jet fuel is dynamically adjusted, solving the problem of low emission reduction efficiency caused by statically fixed blending ratios in existing technologies. This achieves efficient fuel utilization and improved economy, and is applicable to fuel blending control for various types of aircraft.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- JIANGSU UNIV
- Filing Date
- 2026-04-30
- Publication Date
- 2026-07-10
AI Technical Summary
The existing static premixing mode of SAF and RP-3 aviation kerosene cannot dynamically adjust the blending ratio according to flight altitude and attitude. This results in the high-cost SAF being inefficiently consumed during the cruise phase when emission reduction efficiency is low. It is difficult to achieve a balance between flight safety, environmental protection and emission reduction and operational economy, which limits the large-scale promotion of SAF in the civil aviation field.
A dual-fuel blending system based on flight altitude and attitude was designed. Through a remote control command sending unit, an altitude and attitude-based adaptive command generation unit, a main control unit, and a mechanical mixing unit, the system achieves the staged dynamic blending of SAF and RP-3 aviation kerosene. A closed-loop control architecture with dual pump independent drive and dual flow real-time detection is adopted to achieve a continuously adjustable blending ratio control of 0-50%.
It enhances emission reduction benefits, reduces fuel costs, and achieves efficient fuel utilization. It is applicable to fuel blending and regulation of aircraft such as civil airliners, general aviation, and cargo drones, and has both scientific research value and engineering practicality.
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Figure CN122354789A_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of aviation fuel blending and control technology, and in particular to a dual-fuel blending system based on flight altitude and attitude. Background Technology
[0002] Against the backdrop of global "dual carbon" goals and the green development of civil aviation, energy conservation, emission reduction, and low-carbon transformation in the aviation sector have become core directions for industry development. Sustainable aviation fuel (SAF), as a key path for the aviation industry to achieve deep decarbonization, has been recognized by the International Air Transport Association (IATA) as contributing approximately 65% of the aviation industry's emission reductions, and its large-scale application has become a global consensus in the aviation industry.
[0003] Currently, the ASTM D7566 standard has standardized various production methods for SAF (Self-Produced Air Fuse). Among them, HEFA (Heated Air Fuse) produced by hydrogenation has the highest technological maturity and the widest range of applications, with its life-cycle carbon emissions significantly lower than those of traditional domestically produced aviation kerosene RP-3. However, the large-scale application of SAF still faces many limitations: First, SAF prices are typically 2-5 times higher than traditional RP-3 aviation kerosene, placing a heavy operational burden on airlines; second, current airworthiness standards set a maximum blending ratio of 50% for most SAF processes, limiting the full realization of SAF's emission reduction potential; third, the carbon emission characteristics vary significantly across different stages of civil aviation flight, with the carbon emission intensity per unit time during takeoff and climb reaching 3-5 times that of the cruise phase, and the cumulative emissions during the cruise phase accounting for 70%-80% of the total emissions.
[0004] Currently, the industry generally adopts a static premixing mode for SAF and RP-3 aviation kerosene, with a fixed proportion throughout the flight. This mode cannot dynamically optimize the fuel ratio based on flight altitude, flight stage, and emission characteristics. As a result, the high-cost SAF is inefficiently consumed during the cruise phase when emission reduction efficiency is low. It is difficult to achieve a balance between flight safety, environmental protection and emission reduction, and operational economy, which restricts the large-scale promotion and application of SAF in the civil aviation field. Summary of the Invention
[0005] To address the aforementioned shortcomings in existing technologies, this application proposes a dual-fuel blending system based on flight altitude and attitude. This system can dynamically adjust the blending ratio of sustainable aviation fuel and conventional jet fuel according to flight altitude and attitude, thereby maximizing emission reduction benefits and achieving optimal fuel cost control while meeting the upper limit of airworthiness blending.
[0006] The technical solution adopted in this invention is as follows: A dual-fuel delivery system based on flight altitude and attitude includes a remote control command transmission unit, an altitude and attitude-based adaptive command generation unit, a main control unit, and a mechanical hybrid unit. The remote control command sending unit sends the set SAF target mixing ratio command to the main control unit; The altitude and attitude-based adaptive command generation unit collects flight altitude data and aircraft pitch angle attitude data in real time, and sends the collected aircraft data to the main control unit. The main control unit includes a receiver, an RP-3 aviation kerosene supply unit, and an SAF fuel supply unit. The receiver receives the set SAF target blending ratio command sent by the remote control command sending unit, or generates the corresponding SAF target blending ratio command based on the aircraft altitude and attitude data. Based on the set SAF target blending ratio command or the generated SAF target blending ratio command, drive the RP-3 jet fuel supply unit and the SAF fuel supply unit; realize the staged dynamic blending of SAF and RP-3 jet fuel.
[0007] Furthermore, the remote control command sending unit includes a computer, a serial port transmission device 5, and a transmitter. The computer is connected to the transmitter through the serial port transmission device, inputs the set SAF target mixing ratio command to the transmitter, and sends the command to the main control part through the wireless communication link.
[0008] Furthermore, the altitude and attitude-based adaptive command generation unit includes an HC-SR04 ultrasonic ranging module, an MPU6050 electronic gyroscope, and a transmitter; the HC-SR04 ultrasonic ranging module and the MPU6050 electronic gyroscope collect flight altitude data and aircraft pitch angle attitude data in real time, respectively; the transmitter sends the collected aircraft data to the main control unit.
[0009] Furthermore, the method for generating target mixing ratio commands by the command adaptive generation unit based on height and attitude is as follows: During takeoff / climb: Entry conditions: Altitude 0–500 meters, and a large angle of ascent or continuous increase in altitude is detected; SAF blending ratio: 50%; During the transitional climb phase: Entry conditions: Altitude 500–9500 meters, attitude gradually and smoothly; SAF blending ratio: gradually decrease linearly from 50% to 10%; During the high-altitude cruise phase: Entry requirements: Altitude 9500–11000 meters, and level flight attitude detected; SAF blending ratio: 10%; During the transitional descent phase: Entry conditions: Descending from an altitude of over 9,500 meters to 500–3,000 meters, with the attitude shifting to a slight dive or the altitude continuing to decrease. SAF blending ratio: gradually increase linearly from 10% to 50%; During the final approach / landing phase: Entry conditions: The altitude drops back to 0–500 meters, and an approach glide or flattening attitude is detected; SAF blending ratio: Forced switch back to 50%.
[0010] Furthermore, the RP-3 jet fuel supply unit includes an RP-3 jet fuel storage unit, a water pump 10, and an RP-3 jet fuel delivery pipeline. During operation, the TB6612 drive module drives the water pump 10, which pumps a metered amount of RP-3 jet fuel from the RP-3 jet fuel storage unit into the RP-3 jet fuel delivery pipeline.
[0011] Furthermore, the SAF fuel supply unit includes an SAF fuel storage unit, a water pump, and an SAF fuel delivery pipeline. During operation, the TB6612 drive module drives the water pump, which pumps a metered amount of SAF fuel from the SAF fuel storage unit into the SAF fuel delivery pipeline.
[0012] Furthermore, the fuel delivery pipelines of the RP-3 jet fuel supply unit and the SAF fuel supply unit are equipped with YS-S401 water flow meter modules, and the YS-S401 water flow meter modules are connected to the flow display unit. The flow display unit includes an STM32 minimum system board and an OLED display module.
[0013] Furthermore, the mechanical mixing module includes a material mixing chamber, and the inlet of the material mixing chamber is connected to the SAF fuel delivery pipeline and the RP-3 jet fuel delivery pipeline; the SAF fuel and RP-3 jet fuel pumped in according to the SAF target blending ratio instruction are mixed in the material mixing chamber; the outlet of the mixed material is connected to the aircraft engine fuel supply pipeline.
[0014] Furthermore, the serial port transmission device uses a USB to serial port module.
[0015] Furthermore, the transmitter includes an STM32 minimum system board and an OLED display module, and the receiver includes an STM32 minimum system board, an OLED display module, an NRF24L01 wireless transmission module, and a TB6612 driver module. After receiving the SAF target blending ratio instruction, the TB6612 driver module 7 drives the RP-3 jet fuel supply unit and the SAF fuel supply unit to work according to the SAF target blending ratio instruction.
[0016] The beneficial effects of this invention are: This invention breaks through the limitations of the traditional fixed-ratio blending mode on the ground, and can realize the staged dynamic blending of sustainable aviation fuel and traditional aviation kerosene based on flight altitude and attitude, thereby increasing emission reduction benefits.
[0017] This invention adopts a closed-loop control architecture with dual pump independent drive and dual flow real-time detection, which can achieve a continuously adjustable aviation fuel blending ratio of 0-50%, control error ≤ ±2%, system response time ≤ 20ms, avoid fuel waste caused by flow fluctuations, and ensure efficient fuel utilization.
[0018] This invention constructs a dual control architecture with remote control mode and altitude mapping mode. It adopts a separate design of transmitter, main control part and hybrid module to achieve physical isolation between the control end and the fuel area. It can meet the needs of laboratory steady-state testing and adapt to the dynamic mixing needs of real flight profile, and has both scientific research value and engineering practicality.
[0019] This invention is directly compatible with the retrofitting of existing civil aviation fuel systems. Under the same emission reduction level, it can significantly reduce fuel costs compared with a fixed blending scheme. After large-scale promotion, it has outstanding economic and ecological benefits and is applicable to fuel blending and control scenarios of various aircraft such as civil airliners, general aviation, and cargo drones. Attached Figure Description
[0020] Figure 1 This is a schematic diagram of the overall architecture of a dual-fuel distribution system based on flight altitude and attitude according to the present invention.
[0021] The components include: 1. STM32 minimum system board, 2. OLED display module, 3. NRF24L01 wireless transmission module, 4. Computer, 5. Serial port transmission device, 6. HC-SR04 ultrasonic module, 7. TB6612 driver module, 8. YF-S401 water flow meter module, 9. MPU6050 electronic gyroscope, 10. Water pump, 11. Mechanical hybrid module, 12. Remote control command sending unit, 13. Altitude and attitude-based adaptive command generation unit, and 14. Main control section. Detailed Implementation
[0022] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are for illustrative purposes only and are not intended to limit the invention.
[0023] Reference Figure 1 The present invention provides a dual-fuel distribution system based on flight altitude and attitude, comprising a remote control command sending unit 12, a command adaptive generation unit 13 based on altitude and attitude, a main control unit 14, and a mechanical hybrid unit.
[0024] More specifically, the remote control command sending unit 12 includes a computer 4, a serial port transmission device 5, and a transmitter. The computer 4 connects to the transmitter via the serial port transmission device 5 and inputs the set SAF target mixing ratio command to the transmitter. The transmitter then sends the command to the main control unit 14 via a wireless communication link. The transmitter includes an STM32 minimum system board 1, an OLED display module 2, and an NRF24L01 wireless transmission module 3. The STM32 minimum system board 1 establishes a connection with the computer 4 and receives the data input by the computer 4 via the serial port transmission device 5. The OLED display module 2 displays the data input via the serial port transmission device 5 and verifies the normality of data transmission. The NRF24L01 wireless transmission module 3 communicates with the main control unit 14.
[0025] More specifically, the altitude and attitude-based adaptive command generation unit 13 includes an HC-SR04 ultrasonic ranging module 6, an MPU6050 electronic gyroscope 9, and a transmitter. The HC-SR04 ultrasonic ranging module 6 and the MPU6050 electronic gyroscope 9 collect flight altitude data and aircraft pitch angle attitude data in real time, respectively. The transmitter includes an STM32 minimum system board 1 and an NRF24L01 wireless transmission module 3. The function of the STM32 minimum system board 1 is to organize the data obtained by the sensors (through the HC-SR04 ultrasonic ranging module and the MPU6050 electronic gyroscope) and package it for transmission to the main control unit. The transmitter transmits the altitude and attitude data to the main control unit 14 for execution via a wireless link through the NRF24L01 wireless transmission module 3.
[0026] The main control unit 14 includes a receiver, an RP-3 aviation kerosene supply unit, and an SAF fuel supply unit. The receiver includes an STM32 minimum system board 1, an OLED display module 2, an NRF24L01 wireless transmission module 3, and a TB6612 driver module 7. The NRF24L01 wireless transmission module 3 communicates wirelessly with the remote control command transmission unit 12 and the altitude and attitude-based adaptive command generation unit 13. The STM32 minimum system board 1 is used to calculate the received commands and convert them into corresponding PWM signals to drive the motor. The OLED display module 2 displays the data transmitted through the wireless transmission module, as well as the corresponding modes, such as altitude and attitude angle parameters.
[0027] Among them, the remote control command sending unit 12 directly sends out the pre-set target mixing ratio command.
[0028] The command adaptive generation unit 13, based on altitude and attitude, issues altitude and attitude data. The STM32 minimum system board 1 on the receiving end calculates the flight phase based on the altitude and attitude data, and generates the corresponding SAF target blending ratio command to realize the staged dynamic blending of sustainable aviation fuel and traditional aviation kerosene, thereby increasing emission reduction benefits.
[0029] More specifically, the method by which the height- and attitude-based instruction adaptive generation unit 13 generates the target mixing ratio instruction is as follows: During takeoff / climb: Entry conditions: Altitude 0–500 meters, and a large angle of ascent (or continuous increase in altitude) is detected.
[0030] SAF blending ratio: 50%. Targeted emission reduction in high near-ground emission areas.
[0031] The “SAF blending ratio” mentioned in this embodiment refers to the proportion of SAF in the total volume.
[0032] During the transitional climb phase: Entry conditions: Altitude 500–9500 meters, attitude gradually and smoothly.
[0033] SAF blending ratio: gradually decrease linearly from 50% to 10% to avoid sudden changes in flow rate.
[0034] During the high-altitude cruise phase: Entry requirements: altitude 9500–11000 meters, and level flight attitude detected.
[0035] SAF blending ratio: 10%. Prioritize fuel cost control during periods of lower environmental impact.
[0036] During the transitional descent phase: Entry conditions: The altitude drops from above 9,500 meters to 500–3,000 meters, and the attitude changes to a slight dive (or the altitude continues to decrease).
[0037] SAF blending ratio: gradually increase linearly from 10% to 50% to prepare for landing.
[0038] During the final approach / landing phase: Entry conditions: The altitude drops back to 0–500 meters, and an approach glide or flattening attitude is detected.
[0039] SAF blending ratio: Forced to switch back to 50%. Return to the near-ground high-pollution zone to enhance emission reduction effect.
[0040] Upon receiving the SAF target blending ratio instruction, the TB6612 drive module 7 drives the RP-3 jet fuel supply unit and the SAF fuel supply unit to work according to the SAF target blending ratio instruction.
[0041] More specifically, the RP-3 jet fuel supply unit includes an RP-3 jet fuel storage unit, a water pump 10, and an RP-3 jet fuel delivery pipeline. During operation, the TB6612 drive module 7 drives the water pump 10, which pumps a metered amount of RP-3 jet fuel from the RP-3 jet fuel storage unit into the RP-3 jet fuel delivery pipeline.
[0042] More specifically, the SAF fuel supply unit includes an SAF fuel storage unit, a water pump 10, and an SAF fuel delivery pipeline. During operation, the TB6612 drive module 7 drives the water pump 10, which pumps a metered amount of SAF fuel from the SAF fuel storage unit into the SAF fuel delivery pipeline.
[0043] More preferably, in order to achieve visual observation of dual fuel supply, YS-S401 water flow meter modules 8 are installed on the fuel delivery pipelines of the RP-3 jet fuel supply unit and the SAF fuel supply unit. The YS-S401 water flow meter module 8 is connected to the flow display unit, which includes an STM32 minimum system board 1 and an OLED display module 2.
[0044] The mechanical mixing module 11 includes a material mixing chamber, the inlet of which is connected to the SAF fuel delivery pipeline and the RP-3 jet fuel delivery pipeline. SAF fuel and RP-3 jet fuel, pumped in according to the SAF target blending ratio command, are mixed within the material mixing chamber. The mixed material outlet is connected to the aircraft engine fuel supply pipeline.
[0045] More specifically, the serial port transmission device 5 uses a USB to serial port module to establish a wired communication connection with the host computer.
[0046] In this embodiment, the main control unit 14 and the STM32 minimum system board 1 use the same model of STM32 minimum system board.
[0047] In this embodiment, the HC-SR04 ultrasonic ranging module 6 adopts the HC-SR04 ultrasonic module, and the MPU6050 electronic gyroscope 9 adopts the MPU6050 gyroscope.
[0048] Based on the above system architecture design, the system of this invention can achieve two working modes: remote control and altitude mapping. Specifically: In remote control mode, computer 4 inputs the set SAF target blending ratio command to transmitter through serial port transmission device 5. The transmitter sends the command to main control part 14 through wireless communication link. Main control part 14 converts the target blending ratio into the target flow rate of the two fuels. The TB6612 drive module 7 drives the water pumps 10 in the two supply pipelines to operate respectively. The YS-S401 water flow meter module 8 in the two supply pipelines collects the actual flow rate of the two pipelines in real time and feeds it back to main control part 14 to form closed-loop control. Finally, the two fuels enter the mechanical mixing module 11 to complete uniform mixing and output.
[0049] In altitude mapping mode, the HC-SR04 ultrasonic ranging module 6 collects flight altitude data in real time, and the MPU6050 electronic gyroscope 9 collects pitch angle and attitude data of the aircraft in real time. The data is synchronously transmitted to the transmitter 12. The transmitter 12 calculates the flight stage based on the cross-calculation of altitude and attitude data, generates the corresponding target mixing ratio command, and sends it to the main control part 14 for execution via wireless link.
[0050] The above embodiments are only used to illustrate the design concept and features of the present invention, and their purpose is to enable those skilled in the art to understand the content of the present invention and implement it accordingly. The protection scope of the present invention is not limited to the above embodiments. Therefore, all equivalent changes or modifications made based on the principles and design ideas disclosed in the present invention are within the protection scope of the present invention.
Claims
1. A dual-fuel delivery system based on flight altitude and attitude, characterized in that, It includes a remote control command sending unit (12), a command adaptive generation unit based on altitude and attitude (13), a main control unit (14), and a mechanical hybrid unit; The remote control command sending unit (12) sends the set SAF target mixing ratio command to the main control part (14). The altitude and attitude-based instruction adaptive generation unit (13) collects flight altitude data and aircraft pitch angle attitude data in real time, and sends the collected aircraft data to the main control unit (14). The main control unit (14) includes a receiver, an RP-3 aviation kerosene supply unit, and an SAF fuel supply unit; the receiver receives the set SAF target mixing ratio command sent by the remote control command sending unit (12), or generates the corresponding SAF target mixing ratio command based on the aircraft altitude and attitude data. Based on the set SAF target blending ratio command or the generated SAF target blending ratio command, drive the RP-3 jet fuel supply unit and the SAF fuel supply unit; realize the staged dynamic blending of SAF and RP-3 jet fuel.
2. The dual-fuel distribution system based on flight altitude and attitude according to claim 1, characterized in that, The remote control command sending unit (12) includes a computer (4), a serial port transmission device 5 and a transmitter. The computer 4 is connected to the transmitter through the serial port transmission device 5, and inputs the set SAF target mixing ratio command to the transmitter. The transmitter sends the command to the main control part 14 through the wireless communication link.
3. The dual-fuel distribution system based on flight altitude and attitude according to claim 1, characterized in that, The altitude and attitude-based adaptive command generation unit (13) includes an HC-SR04 ultrasonic ranging module 6, an MPU6050 electronic gyroscope 9, and a transmitter; the HC-SR04 ultrasonic ranging module 6 and the MPU6050 electronic gyroscope 9 collect flight altitude data and aircraft pitch angle attitude data in real time, respectively; the transmitter sends the collected aircraft data to the main control unit 14.
4. The dual-fuel distribution system based on flight altitude and attitude according to claim 1, characterized in that, The method for generating the target mixing ratio command by the height and attitude-based adaptive command generation unit (13) is as follows: During takeoff / climb: Entry conditions: Altitude 0–500 meters, and a large angle of ascent or continuous increase in altitude is detected; SAF blending ratio: 50%; During the transitional climb phase: Entry conditions: Altitude 500–9500 meters, attitude gradually and smoothly; SAF blending ratio: gradually decrease linearly from 50% to 10%; During the high-altitude cruise phase: Entry requirements: Altitude 9500–11000 meters, and level flight attitude detected; SAF blending ratio: 10%; During the transitional descent phase: Entry conditions: Descending from an altitude of over 9,500 meters to 500–3,000 meters, with the attitude shifting to a slight dive or the altitude continuing to decrease. SAF blending ratio: gradually increase linearly from 10% to 50%; During the final approach / landing phase: Entry conditions: The altitude drops back to 0–500 meters, and an approach glide or flattening attitude is detected; SAF blending ratio: Forced to switch back to 50%.
5. A dual-fuel distribution system based on flight altitude and attitude according to claim 1, characterized in that, The RP-3 jet fuel supply unit includes an RP-3 jet fuel storage unit, a water pump 10, and an RP-3 jet fuel delivery pipeline. During operation, the TB6612 drive module 7 drives the water pump 10, which pumps a metered amount of RP-3 jet fuel from the RP-3 jet fuel storage unit into the RP-3 jet fuel delivery pipeline.
6. A dual-fuel delivery system based on flight altitude and attitude according to claim 1, characterized in that, The SAF fuel supply unit includes an SAF fuel storage unit, a water pump 10, and an SAF fuel delivery pipeline. During operation, the TB6612 drive module 7 drives the water pump 10, which pumps a metered amount of SAF fuel from the SAF fuel storage unit into the SAF fuel delivery pipeline.
7. A dual-fuel distribution system based on flight altitude and attitude according to claim 1, characterized in that, The fuel delivery pipelines of the RP-3 jet fuel supply unit and the SAF fuel supply unit are equipped with YS-S401 water flow meter modules 8, and the YS-S401 water flow meter modules 8 are connected to the flow display unit. The flow display unit includes an STM32 minimum system board 1 and an OLED display module 2.
8. A dual-fuel delivery system based on flight altitude and attitude according to claim 1, characterized in that, The mechanical mixing module 11 includes a material mixing chamber, and the inlet of the material mixing chamber is connected to the SAF fuel delivery pipeline and the RP-3 aviation kerosene delivery pipeline; the SAF fuel and RP-3 aviation kerosene pumped in according to the SAF target blending ratio instruction are mixed in the material mixing chamber; the outlet of the mixed material is connected to the aircraft engine fuel supply pipeline.
9. A dual-fuel delivery system based on flight altitude and attitude according to claim 1, characterized in that, The serial port transmission device 5 uses a USB to serial port module.
10. A dual-fuel delivery system based on flight altitude and attitude according to claim 1, characterized in that, The transmitter includes an STM32 minimum system board 1 and an OLED display module 2. The receivers each include an STM32 minimum system board 1, an OLED display module 2, an NRF24L01 wireless transmission module 3, and a TB6612 driver module 7. After receiving the SAF target blending ratio instruction, the TB6612 driver module 7 drives the RP-3 jet fuel supply unit and the SAF fuel supply unit to work according to the SAF target blending ratio instruction.