CN114022975A - Method for preventing high-altitude evaporation loss of unmanned aerial vehicle - Google Patents
Method for preventing high-altitude evaporation loss of unmanned aerial vehicle Download PDFInfo
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- 238000000034 method Methods 0.000 title claims abstract description 29
- 238000001704 evaporation Methods 0.000 title claims abstract description 19
- 230000008020 evaporation Effects 0.000 title claims abstract description 19
- 239000000446 fuel Substances 0.000 claims abstract description 76
- 238000012423 maintenance Methods 0.000 claims abstract description 7
- 238000001816 cooling Methods 0.000 claims description 8
- 238000012545 processing Methods 0.000 claims description 6
- 238000004519 manufacturing process Methods 0.000 claims description 5
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims description 3
- 239000003921 oil Substances 0.000 abstract description 36
- 239000000295 fuel oil Substances 0.000 abstract description 24
- 206010063385 Intellectualisation Diseases 0.000 abstract description 3
- 229920006395 saturated elastomer Polymers 0.000 description 8
- 238000005265 energy consumption Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000002159 abnormal effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 230000000704 physical effect Effects 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 239000010729 system oil Substances 0.000 description 1
- 238000009423 ventilation Methods 0.000 description 1
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- G—PHYSICS
- G07—CHECKING-DEVICES
- G07C—TIME OR ATTENDANCE REGISTERS; REGISTERING OR INDICATING THE WORKING OF MACHINES; GENERATING RANDOM NUMBERS; VOTING OR LOTTERY APPARATUS; ARRANGEMENTS, SYSTEMS OR APPARATUS FOR CHECKING NOT PROVIDED FOR ELSEWHERE
- G07C5/00—Registering or indicating the working of vehicles
- G07C5/08—Registering or indicating performance data other than driving, working, idle, or waiting time, with or without registering driving, working, idle or waiting time
- G07C5/0808—Diagnosing performance data
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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
- B64D37/005—Accessories not provided for in the groups B64D37/02 - B64D37/28
-
- 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
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
- F02B77/00—Component parts, details or accessories, not otherwise provided for
- F02B77/08—Safety, indicating, or supervising devices
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- G—PHYSICS
- G07—CHECKING-DEVICES
- G07C—TIME OR ATTENDANCE REGISTERS; REGISTERING OR INDICATING THE WORKING OF MACHINES; GENERATING RANDOM NUMBERS; VOTING OR LOTTERY APPARATUS; ARRANGEMENTS, SYSTEMS OR APPARATUS FOR CHECKING NOT PROVIDED FOR ELSEWHERE
- G07C5/00—Registering or indicating the working of vehicles
- G07C5/006—Indicating maintenance
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- G—PHYSICS
- G07—CHECKING-DEVICES
- G07C—TIME OR ATTENDANCE REGISTERS; REGISTERING OR INDICATING THE WORKING OF MACHINES; GENERATING RANDOM NUMBERS; VOTING OR LOTTERY APPARATUS; ARRANGEMENTS, SYSTEMS OR APPARATUS FOR CHECKING NOT PROVIDED FOR ELSEWHERE
- G07C5/00—Registering or indicating the working of vehicles
- G07C5/08—Registering or indicating performance data other than driving, working, idle, or waiting time, with or without registering driving, working, idle or waiting time
- G07C5/0816—Indicating performance data, e.g. occurrence of a malfunction
- G07C5/0825—Indicating performance data, e.g. occurrence of a malfunction using optical means
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- G—PHYSICS
- G07—CHECKING-DEVICES
- G07C—TIME OR ATTENDANCE REGISTERS; REGISTERING OR INDICATING THE WORKING OF MACHINES; GENERATING RANDOM NUMBERS; VOTING OR LOTTERY APPARATUS; ARRANGEMENTS, SYSTEMS OR APPARATUS FOR CHECKING NOT PROVIDED FOR ELSEWHERE
- G07C5/00—Registering or indicating the working of vehicles
- G07C5/08—Registering or indicating performance data other than driving, working, idle, or waiting time, with or without registering driving, working, idle or waiting time
- G07C5/0816—Indicating performance data, e.g. occurrence of a malfunction
- G07C5/0833—Indicating performance data, e.g. occurrence of a malfunction using audio means
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
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- General Physics & Mathematics (AREA)
- Aviation & Aerospace Engineering (AREA)
- Multimedia (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Combined Controls Of Internal Combustion Engines (AREA)
Abstract
The invention discloses a method for preventing high-altitude evaporation loss of an unmanned aerial vehicle, which comprises the following steps: s1, making a manual of the maximum fuel temperature limit requirement of the unmanned aerial vehicle at each flight altitude; s2, controlling the temperature of the fuel oil added into the unmanned aerial vehicle to be lower than the temperature of the fuel oil specified in the manual; s3, measuring and outputting the temperature data of the fuel in the fuel supply tank to the flying pipe computer in real time; s4, setting fuel temperature limit requirements under different air pressures, resolving in real time, supporting ground maintenance equipment input by airborne software, opening an interface, and injecting corresponding indexes of oil products according to different oil product characteristics; and S5, measuring the local atmospheric pressure value in real time, accessing the atmospheric pressure value into a flying pipe computer, resolving and downloading the fuel oil limit temperature in real time according to the atmospheric pressure value, remotely controlling and telemetering the downloading related faults, and prompting related operators. The invention has low cost and high intellectualization, can fully ensure the safety of a fuel system, avoids the high-altitude evaporation loss of the unmanned aerial vehicle, protects the driving for safe flight, and the like.
Description
Technical Field
The invention relates to the field of unmanned aerial vehicles, in particular to a method for preventing high-altitude evaporation loss of an unmanned aerial vehicle.
Background
The flying of the unmanned aerial vehicle technology is leaped forward suddenly, the requirement on the flying height of the unmanned aerial vehicle is higher and higher, most of the power systems used by the current unmanned aerial vehicles are piston engines, the piston engines use aviation gasoline as oil, the pressure on the free surface of the fuel oil in an oil tank is reduced along with the increase of the flying height, when the absolute pressure in the oil tank is reduced to the saturated vapor pressure of the fuel oil, the fuel oil supplied to the engines can separate out a large amount of 'air', the air dissolved in the fuel oil can quickly escape after reaching saturation, the fuel oil can be 'boiled', serious evaporation loss can be caused, the oil pump can generate vortex-air and cavitation due to the evaporation loss, the vortex-air can cause serious hydraulic impact on the oil pump, the pressure of the supplied oil is influenced, even the oil pump can be damaged, the phenomenon of air plug occurs in a pipeline, the engine can generate lean oil combustion, the normal driving of the engine is influenced, and even the aerial parking can be caused in serious cases, seriously affecting the execution of unmanned aerial vehicle tasks and threatening the flight safety of the unmanned aerial vehicle.
The traditional use method is as follows: the oil tank is pressurized to ensure that the absolute pressure in the oil tank is greater than the saturated vapor pressure of the fuel oil, and the pressurizing means comprises a pressurizing air pump and a high-pressure air bottle for compressing air.
The disadvantages brought by the traditional method are as follows: for example, the weight of the airplane is increased, the energy consumption of the airplane is increased, and the time of flight and the task load loading capacity of the airplane are severely limited; the leakage risk of the pressurized oil tank is increased, and potential safety hazards are brought to the use of the system; the piston engine that unmanned aerial vehicle used can't use the system pressure boost through schemes such as bleed air, can only pass through the mode of supercharged air pump or high-pressure compressed gas bottle, and the energy consumption demand is big.
Disclosure of Invention
The invention aims to overcome the defects of the prior art, provides a method for preventing the high-altitude evaporation loss of an unmanned aerial vehicle, has low cost and high intellectualization, can fully ensure the safety of a fuel system, avoids the high-altitude evaporation loss of the unmanned aerial vehicle, protects the driving for safe flight, and the like.
The purpose of the invention is realized by the following scheme:
a method for preventing high-altitude evaporation loss of an unmanned aerial vehicle comprises the following steps:
and resolving and judging the current oil safety in real time according to preset logic by using a flight tube computer, an atmospheric data system and airborne software.
Further, comprising the sub-steps of:
s1, manufacturing a handbook of the maximum fuel temperature limit requirement of the unmanned aerial vehicle at each flight altitude according to the characteristics of the oil product;
s2, controlling the temperature of the fuel added into the unmanned aerial vehicle to be lower than the temperature of the fuel specified in the manual according to the manual requirement in the step S1;
s3, measuring and outputting the temperature data of the fuel in the fuel supply tank to the flying pipe computer in real time by using the fuel temperature sensor arranged in the fuel supply tank;
s4, setting fuel temperature limit requirements under different air pressures in the onboard software, resolving in real time, supporting ground maintenance equipment input by the onboard software, opening an interface, and injecting corresponding indexes of oil products according to different oil product characteristics;
s5, installing an atmospheric data system on the unmanned aerial vehicle, measuring in real time to obtain a local atmospheric pressure value, accessing the atmospheric pressure value into a flight control computer, and resolving and downloading fuel limiting temperature in real time by airborne software according to the atmospheric pressure value; when the fuel temperature monitored by the fuel temperature sensor exceeds the limiting condition, the related faults are remotely controlled, telemetered and downloaded, related operators are prompted, the flight operators are warned to carry out further processing, and the safety of flight oil is guaranteed.
Further, in step S2, the method includes the steps of: and pre-judging the added fuel according to the loaded waypoint information, prompting crew members if the current fuel temperature exceeds the target height limit temperature and does not meet the requirement, refilling or circularly cooling the fuel in the aircraft after performing related operations such as fuel cooling and the like, and controlling the temperature of the added fuel in the aircraft.
Further, in step S4, the index includes the reid vapor pressure of the oil.
Further, in step S5, the atmospheric pressure value is accessed to the flight pipe computer through a serial port.
Further, in step S5, the flight operator is alerted by color or voice for further processing.
The beneficial effects of the invention include:
the embodiment of the invention has low cost and high intellectualization, utilizes the onboard computer, the high-precision atmospheric data sensor and the onboard software to monitor the fuel oil state in real time, solves the fuel oil state in real time according to the preset logic and judges the safety of the current fuel oil in real time, fully ensures the safety of a fuel oil system, can avoid the high-altitude evaporation loss of an unmanned aerial vehicle, and protects the driving for safe flight.
The embodiment of the invention has the following advantages: the weight of an oil tank of a machine body can be reduced, and for the oil tank with the system oil carrying capacity of 1000L, the structural weight of simple pressurization can be reduced by more than 10 kg; secondly, compared with the traditional pressurization scheme, the single engine can reduce the installation and use of the ventilation pressurization valve, the safety valve, the gas cylinder or the gas pump and other accessory pipelines, the single engine cost can be saved by more than 100000 yuan for an ordinary piston engine, the single engine can reduce the weight of a finished product by 3-5 kg, and the method has good economical efficiency in popularization and use and can directly or indirectly generate good economic benefits.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
FIG. 1 is an exemplary flow chart of use of an embodiment of the present invention;
FIG. 2 is a schematic diagram of the configuration of an embodiment of the present invention;
fig. 3 shows the relationship between saturated vapor pressure and temperature for some type of aviation gasoline.
Detailed Description
All features disclosed in all embodiments in this specification, or all methods or process steps implicitly disclosed, may be combined and/or expanded, or substituted, in any way, except for mutually exclusive features and/or steps.
Example 1
As shown in fig. 1 to 3, a method for preventing high altitude evaporation loss of an unmanned aerial vehicle comprises the steps of:
and resolving and judging the current oil safety in real time according to preset logic by using a flight tube computer, an atmospheric data system and airborne software.
Example 2
On the basis of the embodiment 1, the method comprises the following substeps:
s1, manufacturing a handbook of the maximum fuel temperature limit requirement of the unmanned aerial vehicle at each flight altitude according to the characteristics of the oil product;
s2, controlling the temperature of the fuel added into the unmanned aerial vehicle to be lower than the temperature of the fuel specified in the manual according to the manual requirement in the step S1;
s3, measuring and outputting the temperature data of the fuel in the fuel supply tank to the flying pipe computer in real time by using the fuel temperature sensor arranged in the fuel supply tank;
s4, setting fuel temperature limit requirements under different air pressures in the onboard software, resolving in real time, supporting ground maintenance equipment input by the onboard software, opening an interface, and injecting corresponding indexes of oil products according to different oil product characteristics;
s5, installing an atmospheric data system on the unmanned aerial vehicle, measuring in real time to obtain a local atmospheric pressure value, accessing the atmospheric pressure value into a flight control computer, and resolving and downloading fuel limiting temperature in real time by airborne software according to the atmospheric pressure value; when the fuel temperature monitored by the fuel temperature sensor exceeds the limiting condition, the related faults are remotely controlled, telemetered and downloaded, related operators are prompted, the flight operators are warned to carry out further processing, and the safety of flight oil is guaranteed.
Example 3
On the basis of embodiment 2, in step S2, the method includes the steps of: and pre-judging the added fuel according to the loaded waypoint information, prompting crew members if the current fuel temperature exceeds the target height limit temperature and does not meet the requirement, refilling or circularly cooling the fuel in the aircraft after performing related operations such as fuel cooling and the like, and controlling the temperature of the added fuel in the aircraft.
In another embodiment of the present invention based on embodiment 2, it should be noted that in step S4, the index includes the reid vapor pressure of the oil product.
In another embodiment of the present invention based on embodiment 2, it should be noted that, in step S5, the atmospheric pressure value is accessed to the flight pipe computer through a serial port.
In another embodiment of the present invention based on embodiment 2, it should be noted that in step S5, the flight operator is alerted by color or voice for further processing.
In other embodiments based on embodiment 2, knowing the reid vapor pressure of the oil used by the unmanned aerial vehicle, the atmospheric computer can calculate the atmospheric pressure at the current flying height of the unmanned aerial vehicle in real time, calculate the saturated vapor pressure limit of the oil through the target flying height, calculate the fuel temperature at the target flying height through a relation graph 3 of the saturated vapor pressure and the temperature, limit the fuel temperature through onboard software, monitor the fuel pressure in real time, prompt a pilot when the temperature reaches the saturated vapor pressure at the flying height, monitor the working state of the engine in real time, monitor and control the use of a fuel system, ensure that the engine is in the optimal working state, prevent the unsmooth fuel supply caused by the evaporation loss of the fuel, prevent the abnormal working condition of a pipeline gas plug from influencing the normal fuel supply of the engine, and avoid the risk of the unsmooth fuel supply of the engine and even the air parking of the engine.
Firstly, manufacturing a relevant manual of the maximum fuel temperature limit requirement of the unmanned aerial vehicle at each flight altitude according to the oil characteristics;
secondly, controlling the temperature of fuel added into the machine to be lower than the specified fuel temperature in the manual according to the manual requirement;
the fuel temperature sensor is arranged on the fuel supply tank and is used for measuring and outputting the temperature of the fuel in the fuel supply tank in real time;
the method comprises the steps of manufacturing airborne software, setting fuel temperature limit requirements under different air pressures by the airborne software, calculating in real time, supporting ground maintenance equipment input by the software, opening relevant interfaces, injecting corresponding indexes of oil products according to different oil product characteristics, wherein the indexes include the Reid vapor pressure of the oil products, and the saturated vapor pressure limit at each temperature deduced by the Reid vapor pressure of three kinds of common aviation gasoline is shown in figure 3.
And an air data system is arranged on the aircraft to measure in real time to obtain a local atmospheric pressure value, the data is accessed into the flight tube computer through a serial port, and the onboard software resolves and downloads the fuel limiting temperature in real time according to the atmospheric data.
When the fuel temperature exceeds the limit condition, the system remotely controls and telemeters to download related faults and prompts related operators, and warns flight operators to further process in a color or voice mode, so that the safety of the flight fuel is ensured.
In other embodiments based on embodiment 2, fuel oil is filled according to relevant requirements in a compiled manual, the temperature of the added fuel oil is controlled according to the flight altitude of a task when the fuel oil is filled, a sensor is powered on after filling is finished, the temperature of the fuel oil is output, a flight management computer collects relevant data, pre-judgment is carried out on the added fuel oil according to loaded waypoint information, if the current temperature of the fuel oil exceeds the target altitude limit temperature and does not meet the requirements, a crew is prompted to refill or carry out internal fuel oil circulation cooling after relevant operations such as fuel oil cooling, and the temperature of the fuel oil added into the engine is controlled.
If the fuel temperature meets the requirement, the aircraft can fly, relevant atmospheric data are collected in real time in the flying process, relevant data are interpreted in real time through the fuel temperature and an onboard computer, the current safety of the flying fuel is solved in real time, and if the flight condition is not met, relevant alarm information is downloaded through remote control and remote measurement to prompt a pilot to adjust a relevant flight strategy; and if the requirement is met, continuing to carry out the current flight.
The invention has the following technical advantages:
1) use of Reid vapor pressure: the Reid vapor pressure is an important physical property of volatile fuel oil, is a very important factor for aviation fuel oil, and influences the air resistance characteristic when an engine is started, heated or flies at high altitude, and is defined as follows: the temperature was 37.8 ℃ and the gas-liquid ratio was 4 at saturated vapor pressure.
2) The pressure difference value of the Reid vapor of different oil properties is large, portable ground maintenance equipment supports injection of the Reid vapor of different oils, the system automatically records and stores the Reid vapor pressure, and the Reid vapor pressure is judged in real time according to preset logic and is applied intelligently.
3) The whole process is automatically judged by the onboard computer, information can be downloaded in real time, special operation is not needed by using maintenance personnel, the whole process is completed by the onboard computer, and interference brought by human factors is avoided.
4) Traditional pressure boost mode, different oils require differently to the boost pressure, lead to boost pressure to match the difficulty, and fuselage structure etc. need carry out corresponding improvement and enhancement after the pressure boost, and the too big weight that leads to of boost pressure doubles the increase, and boost pressure undersize can't reach the system requirement. The scheme provided by the invention can avoid the problems.
5) The embodiment of the invention has safe use and easy operation, and can safely operate without complex equipment.
6) The data used by the invention are all from high-precision and redundant sensors, the sensors can quickly feed back various data for the flight management computer to judge in real time, the synchronism is good, the data can be fed back in time, and the risk caused by hysteresis is avoided.
The parts not involved in the present invention are the same as or can be implemented using the prior art.
The above-described embodiment is only one embodiment of the present invention, and it will be apparent to those skilled in the art that various modifications and variations can be easily made based on the application and principle of the present invention disclosed in the present application, and the present invention is not limited to the method described in the above-described embodiment of the present invention, so that the above-described embodiment is only preferred, and not restrictive.
Other embodiments than the above examples may be devised by those skilled in the art based on the foregoing disclosure, or by adapting and using knowledge or techniques of the relevant art, and features of various embodiments may be interchanged or substituted and such modifications and variations that may be made by those skilled in the art without departing from the spirit and scope of the present invention are intended to be within the scope of the following claims.
Claims (6)
1. The method for preventing the high-altitude evaporation loss of the unmanned aerial vehicle is characterized by comprising the following steps of:
and resolving and judging the current oil safety in real time according to preset logic by using a flight tube computer, an atmospheric data system and airborne software.
2. A method for preventing high altitude evaporation loss of unmanned aerial vehicles according to claim 1, comprising the sub-steps of:
s1, manufacturing a handbook of the maximum fuel temperature limit requirement of the unmanned aerial vehicle at each flight altitude according to the characteristics of the oil product;
s2, controlling the temperature of the fuel added into the unmanned aerial vehicle to be lower than the temperature of the fuel specified in the manual according to the manual requirement in the step S1;
s3, measuring and outputting the temperature data of the fuel in the fuel supply tank to the flying pipe computer in real time by using the fuel temperature sensor arranged in the fuel supply tank;
s4, setting fuel temperature limit requirements under different air pressures in the onboard software, resolving in real time, supporting ground maintenance equipment input by the onboard software, opening an interface, and injecting corresponding indexes of oil products according to different oil product characteristics;
s5, installing an atmospheric data system on the unmanned aerial vehicle, measuring in real time to obtain a local atmospheric pressure value, accessing the atmospheric pressure value into a flight control computer, and resolving and downloading fuel limiting temperature in real time by airborne software according to the atmospheric pressure value; when the fuel temperature monitored by the fuel temperature sensor exceeds the limiting condition, the related faults are remotely controlled, telemetered and downloaded, related operators are prompted, the flight operators are warned to carry out further processing, and the safety of flight oil is guaranteed.
3. The method for preventing high altitude evaporation loss of unmanned aerial vehicle according to claim 1, wherein in step S2, the method comprises the following steps: and pre-judging the added fuel according to the loaded waypoint information, prompting crew members if the current fuel temperature exceeds the target height limit temperature and does not meet the requirement, refilling or circularly cooling the fuel in the aircraft after performing related operations such as fuel cooling and the like, and controlling the temperature of the added fuel in the aircraft.
4. The method for preventing high altitude evaporation loss of unmanned aerial vehicle according to claim 1, wherein in step S4, the index includes reid vapor pressure of oil.
5. The method for preventing high altitude evaporation loss of unmanned aerial vehicle as claimed in claim 1, wherein in step S5, the atmospheric pressure value is connected to the flying pipe computer through a serial port.
6. The method for preventing high altitude evaporation loss of unmanned aerial vehicle as claimed in claim 1, wherein in step S5, flight operator is alerted by color or voice for further processing.
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Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU20166U1 (en) * | 2001-07-09 | 2001-10-20 | Открытое акционерное общество "Техприбор" | ON-BOARD FUEL METERING SYSTEM |
| US20140020460A1 (en) * | 2012-07-19 | 2014-01-23 | Honeywell International Inc. | Methods and systems for monitoring engine oil temperature of an operating engine |
| US20150217153A1 (en) * | 2013-12-02 | 2015-08-06 | Philip E. Jones | Aircraft fuel systems |
| US10094305B1 (en) * | 2017-08-28 | 2018-10-09 | GM Global Technology Operations LLC | Gasoline Reid Vapor Pressure detection with brushless fuel pump |
| CN109799837A (en) * | 2017-11-16 | 2019-05-24 | 四川省微技购科技有限公司 | A kind of UAV flight control system |
| RU2699869C1 (en) * | 2018-09-07 | 2019-09-11 | Публичное акционерное общество "Авиационная холдинговая компания "Сухой" | Method of determining the sufficiency of cooling oil in a turbojet engine |
| CN110510133A (en) * | 2019-09-12 | 2019-11-29 | 西安京东天鸿科技有限公司 | Unmanned plane fuel-tank pressurization system and unmanned plane |
| CN110542085A (en) * | 2019-08-28 | 2019-12-06 | 中国民用航空总局第二研究所 | Fuel oil constant temperature and pressure control system of oil burner |
| CN211116285U (en) * | 2019-11-29 | 2020-07-28 | 中国航天空气动力技术研究院 | Unmanned aerial vehicle plateau fuel controller |
| KR102189967B1 (en) * | 2019-06-05 | 2020-12-14 | 한국항공우주산업 주식회사 | Dissolved Oxygen Measurement Method on ground Simulating the Temperature Change in Aircraft Fuel Tank during climb |
| CN112249344A (en) * | 2020-10-10 | 2021-01-22 | 西安爱生技术集团公司 | High-altitude air-entraining and pressurizing system and method for unmanned aerial vehicle oil tank |
| CN113107674A (en) * | 2021-04-17 | 2021-07-13 | 西北工业大学 | Small-size piston carburetor engine real-time data monitoring and adjustment system |
-
2021
- 2021-10-25 CN CN202111237898.0A patent/CN114022975B/en active Active
Patent Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU20166U1 (en) * | 2001-07-09 | 2001-10-20 | Открытое акционерное общество "Техприбор" | ON-BOARD FUEL METERING SYSTEM |
| US20140020460A1 (en) * | 2012-07-19 | 2014-01-23 | Honeywell International Inc. | Methods and systems for monitoring engine oil temperature of an operating engine |
| US20150217153A1 (en) * | 2013-12-02 | 2015-08-06 | Philip E. Jones | Aircraft fuel systems |
| US10094305B1 (en) * | 2017-08-28 | 2018-10-09 | GM Global Technology Operations LLC | Gasoline Reid Vapor Pressure detection with brushless fuel pump |
| CN109799837A (en) * | 2017-11-16 | 2019-05-24 | 四川省微技购科技有限公司 | A kind of UAV flight control system |
| RU2699869C1 (en) * | 2018-09-07 | 2019-09-11 | Публичное акционерное общество "Авиационная холдинговая компания "Сухой" | Method of determining the sufficiency of cooling oil in a turbojet engine |
| KR102189967B1 (en) * | 2019-06-05 | 2020-12-14 | 한국항공우주산업 주식회사 | Dissolved Oxygen Measurement Method on ground Simulating the Temperature Change in Aircraft Fuel Tank during climb |
| CN110542085A (en) * | 2019-08-28 | 2019-12-06 | 中国民用航空总局第二研究所 | Fuel oil constant temperature and pressure control system of oil burner |
| CN110510133A (en) * | 2019-09-12 | 2019-11-29 | 西安京东天鸿科技有限公司 | Unmanned plane fuel-tank pressurization system and unmanned plane |
| CN211116285U (en) * | 2019-11-29 | 2020-07-28 | 中国航天空气动力技术研究院 | Unmanned aerial vehicle plateau fuel controller |
| CN112249344A (en) * | 2020-10-10 | 2021-01-22 | 西安爱生技术集团公司 | High-altitude air-entraining and pressurizing system and method for unmanned aerial vehicle oil tank |
| CN113107674A (en) * | 2021-04-17 | 2021-07-13 | 西北工业大学 | Small-size piston carburetor engine real-time data monitoring and adjustment system |
Non-Patent Citations (3)
| Title |
|---|
| 石日昕;: "飞机燃油***高空性及其计算", 河北工业科技, no. 04, pages 244 - 246 * |
| 肖连勇;常诚;陈志龙;: "高温燃油对航空发动机控制***的影响分析", 内燃机与配件, no. 10, 30 May 2017 (2017-05-30), pages 32 - 33 * |
| 郝毓雅;鲁勇帅;: "飞机燃油温度的影响因素分析", 工程与试验, no. 03, 15 September 2019 (2019-09-15), pages 19 - 20 * |
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