CN114022975B - Method for preventing unmanned aerial vehicle from high-altitude evaporation loss - Google Patents
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- 238000000034 method Methods 0.000 title claims abstract description 31
- 238000001704 evaporation Methods 0.000 title claims abstract description 16
- 230000008020 evaporation Effects 0.000 title claims abstract description 16
- 239000000446 fuel Substances 0.000 claims abstract description 90
- 239000003921 oil Substances 0.000 claims abstract description 41
- 239000000295 fuel oil Substances 0.000 claims abstract description 11
- 238000012423 maintenance Methods 0.000 claims abstract description 7
- 238000004519 manufacturing process Methods 0.000 claims abstract description 5
- 238000001816 cooling Methods 0.000 claims description 7
- 238000005259 measurement Methods 0.000 claims description 4
- 238000012545 processing Methods 0.000 claims description 3
- 206010063385 Intellectualisation Diseases 0.000 abstract description 3
- 229920006395 saturated elastomer Polymers 0.000 description 6
- 230000007547 defect Effects 0.000 description 3
- 238000005265 energy consumption Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 239000000243 solution Substances 0.000 description 2
- 235000014676 Phragmites communis Nutrition 0.000 description 1
- 230000002159 abnormal effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000009835 boiling Methods 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
- 230000000704 physical effect Effects 0.000 description 1
- 239000010729 system oil Substances 0.000 description 1
- 238000009423 ventilation Methods 0.000 description 1
Classifications
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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
-
- 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)
- Physics & Mathematics (AREA)
- 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 unmanned aerial vehicle from high-altitude evaporation loss, which comprises the following steps: s1, manufacturing a manual required by the highest fuel temperature limitation of the unmanned aerial vehicle at each flying height; 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 a manual; s3, measuring and outputting the temperature data of the fuel in the fuel supply tank to the fly tube computer in real time; s4, setting fuel temperature limit requirements under different air pressures, resolving in real time, enabling airborne software to support ground maintenance equipment input, opening an interface, and injecting corresponding indexes of oil products according to different oil product characteristics; s5, measuring the local atmospheric pressure value in real time, accessing the local atmospheric pressure value into a flywheel computer, resolving and downloading the fuel limit temperature in real time according to the atmospheric pressure value, remotely controlling and remotely measuring related faults, and prompting related operators. The invention has low cost and high intellectualization, can fully ensure the safety of the fuel system, avoids the high-altitude evaporation loss of the unmanned aerial vehicle, protects the navigation 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 unmanned aerial vehicle technology suddenly and suddenly advances, the flying height requirement on unmanned aerial vehicle is higher and higher, the driving system that current unmanned aerial vehicle used mostly is piston engine, piston engine uses the oil to be aviation petrol, along with flying height increase, the pressure on the fuel free surface in the oil tank drops, when absolute pressure in the oil tank drops to the saturated vapor pressure of fuel, the fuel of supplying engine can separate out a large amount of "air", the air that dissolves in the fuel can escape rapidly after reaching saturation, the fuel will take place "boiling", cause serious evaporation loss, evaporation loss can cause the oil pump to take place vortex air, cavitation, the vortex air can lead to the serious hydraulic impact of oil pump, influence fuel feeding flow pressure, even probably damage the oil pump, the phenomenon of air lock takes place in the pipeline, lean oil burning appears in the engine, influence engine normal driving, even probably cause sky to stop when serious, seriously influence unmanned aerial vehicle task's execution and threat unmanned aerial vehicle flight safety.
The traditional use method comprises the following steps: pressurizing the oil tank to ensure that the absolute pressure in the oil tank is larger than the saturated vapor pressure of the fuel oil, wherein the pressurizing means comprises a high-pressure gas cylinder which is not limited by a pressurizing gas pump and compressed gas.
The traditional method has the following defects: such as increasing the weight of the aircraft, increasing the energy consumption of the aircraft, etc., would severely limit the endurance and mission load carrying capacity of the aircraft; the leakage risk of the pressurized oil tank is increased, and potential safety hazards are brought to the system use; the piston engine that unmanned aerial vehicle used can't carry out the pressure boost to the system through schemes such as bleed air and use, only can be through the mode of pressure boost air pump or high-pressure compressed gas cylinder, and the energy consumption demand is big.
Disclosure of Invention
The invention aims to overcome the defects of the prior art, and provides a method for preventing the unmanned aerial vehicle from high-altitude evaporation loss, which has the advantages of low cost and high intellectualization, can fully ensure the safety of a fuel system, avoids the unmanned aerial vehicle from high-altitude evaporation loss, protects the unmanned aerial vehicle for safe flight and the like.
The invention aims at realizing the following scheme:
a method of preventing high altitude evaporation loss of an unmanned aerial vehicle comprising the steps of:
and calculating in real time and judging the current oil use safety in real time according to preset logic by using a flight tube computer, an atmosphere data system and airborne software.
Further, the method comprises the following substeps:
s1, manufacturing a manual for limiting the highest fuel temperature under each flying height of the unmanned aerial vehicle according to the oil product characteristics;
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 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 fly tube computer in real time by using a fuel temperature sensor arranged in the fuel supply tank;
s4, setting fuel temperature limiting requirements under different air pressures in the onboard software, resolving in real time, enabling the onboard software to support ground maintenance equipment input, opening an interface, and injecting corresponding indexes of the oil products according to different oil product characteristics;
s5, installing an atmosphere data system on the unmanned aerial vehicle, measuring in real time to obtain a local atmosphere pressure value, accessing the atmosphere pressure value into a flight tube computer, and calculating and downloading fuel limit temperature in real time by using airborne software according to the atmosphere pressure value; when the fuel temperature monitored by the fuel temperature sensor exceeds the limiting condition, remote control and remote measurement downloads related faults and prompts related operators, so that the flight operators are warned to further process the faults, and the safety of the fuel for flight is ensured.
Further, in step S2, the steps include: and (3) pre-judging the added fuel according to the loading waypoint information, if the current fuel temperature exceeds the target height limit temperature and does not meet the requirement, prompting a crew, re-filling or performing engine fuel circulation cooling after performing related operations such as fuel cooling and the like, and controlling the temperature of the added fuel.
Further, in step S4, the index includes the rad vapor pressure of the oil.
Further, in step S5, the atmospheric pressure value is accessed to the femto computer through a serial port.
Further, in step S5, the flight operator is alerted to further processing by means of color or speech.
The beneficial effects of the invention include:
the embodiment of the invention has low cost and high intellectualization, utilizes an onboard computer, a high-precision atmospheric data sensor and onboard software to monitor the fuel state in real time, calculates and judges the current fuel use safety in real time according to the preset logic, fully ensures the safety of a fuel system, can avoid the high-altitude evaporation loss of an unmanned plane, and protects the unmanned plane for safe flight.
The embodiment of the invention has the following advantages: firstly, the weight of the engine body oil tank can be reduced, and for the oil tank with the system oil loading of 1000L, the weight of a structure which is simply pressurized can be reduced by more than 10 kg; and compared with the traditional pressurizing scheme, the single machine can reduce the installation and use of accessory pipelines such as a ventilation pressurizing valve, a safety valve, a gas cylinder or a gas pump, and the like, and for a common piston engine, the single machine cost can be saved by more than 100000 yuan, the single machine can reduce the weight of a finished product by 3-5 kg, and the popularization and the use of the method have good economical efficiency and can directly or indirectly generate good economic benefits.
Drawings
In order to more clearly illustrate the embodiments of the invention or the technical solutions of the prior art, the drawings which are used in the description of the embodiments or the prior art will be briefly described, it being obvious that the drawings in the description below are only some embodiments of the invention, and that other drawings can be obtained according to these drawings without inventive faculty for a person skilled in the art.
FIG. 1 is a flow chart illustrating an example of use of an embodiment of the present invention;
FIG. 2 is a schematic diagram of the embodiment of the present invention;
fig. 3 shows the saturated vapor pressure versus temperature for certain types of aviation gasolines.
Detailed Description
All of the features disclosed in all of the embodiments of this specification, or all of the steps in any method or process disclosed implicitly, except for the mutually exclusive features and/or steps, may be combined and/or expanded and substituted in any way.
Example 1
As shown in fig. 1 to 3, a method for preventing high-altitude evaporation loss of an unmanned aerial vehicle comprises the following steps:
and calculating in real time and judging the current oil use safety in real time according to preset logic by using a flight tube computer, an atmosphere data system and airborne software.
Example 2
On the basis of example 1, the method comprises the following substeps:
s1, manufacturing a manual for limiting the highest fuel temperature under each flying height of the unmanned aerial vehicle according to the oil product characteristics;
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 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 fly tube computer in real time by using a fuel temperature sensor arranged in the fuel supply tank;
s4, setting fuel temperature limiting requirements under different air pressures in the onboard software, resolving in real time, enabling the onboard software to support ground maintenance equipment input, opening an interface, and injecting corresponding indexes of the oil products according to different oil product characteristics;
s5, installing an atmosphere data system on the unmanned aerial vehicle, measuring in real time to obtain a local atmosphere pressure value, accessing the atmosphere pressure value into a flight tube computer, and calculating and downloading fuel limit temperature in real time by using airborne software according to the atmosphere pressure value; when the fuel temperature monitored by the fuel temperature sensor exceeds the limiting condition, remote control and remote measurement downloads related faults and prompts related operators, so that the flight operators are warned to further process the faults, and the safety of the fuel for flight is ensured.
Example 3
On the basis of embodiment 2, in step S2, the steps of: and (3) pre-judging the added fuel according to the loading waypoint information, if the current fuel temperature exceeds the target height limit temperature and does not meet the requirement, prompting a crew, re-filling or performing engine fuel circulation cooling after performing related operations such as fuel cooling and the like, and controlling the temperature of the added fuel.
In other embodiments of the present invention based on embodiment 2, it should be noted that, in step S4, the index includes the rad 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 femto computer through a serial port.
In other embodiments of the present invention based on embodiment 2, it should be noted that, in step S5, the flight operator is alerted to further processing by means of color or voice.
In other embodiments of the present invention based on embodiment 2, the rad vapor pressure of the oil product used by the unmanned aerial vehicle is known, the atmospheric computer can calculate in real time the atmospheric pressure at the current flight altitude of the unmanned aerial vehicle, calculate the saturated vapor pressure limit of the oil product through the target flight altitude, calculate the target flight altitude fuel temperature through the relation chart 3 of the saturated vapor pressure and the temperature, limit the fuel temperature through the airborne software, monitor the fuel pressure in real time, prompt the pilot when the temperature reaches the saturated vapor pressure at the flight altitude, monitor the working state of the engine in real time, monitor and control the use of the fuel system, ensure the engine to be in the optimal working state, prevent the abnormal working condition of the oil supply and the air plug of the pipeline caused by the evaporation loss of the fuel, influence the normal oil supply of the engine, and avoid the risks of the unsmooth oil supply and even air parking of the engine.
Firstly, according to the oil product characteristics, preparing a related manual for limiting the highest fuel temperature under each flying height of the unmanned aerial vehicle;
secondly, according to the requirements of the manual, controlling the temperature of the fuel oil added into the engine to be lower than the temperature of the fuel oil specified in the manual;
the fuel temperature sensor is arranged in 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 atmospheric pressures by the airborne software, resolving in real time, supporting ground maintenance equipment input by the software, opening related interfaces, injecting corresponding indexes of the oil products according to different oil product characteristics, wherein the indexes comprise, but are not limited to, the Reid vapor pressure of the oil products, and figure 3 is a saturation vapor pressure limit under each temperature deduced from the Reid vapor pressures of three common aviation gasoline.
And an atmosphere data system is installed on the aircraft to measure and obtain a local atmosphere pressure value in real time, the data is accessed into a flight tube computer through a serial port, and the airborne software calculates and downloads the fuel limit temperature in real time according to the atmosphere data.
When the temperature of the fuel exceeds the limiting condition, remote control and remote measurement downloads related faults and prompts related operators, and the system alerts flight operators to further process in a color or voice mode so as to ensure the safety of the fuel for flight.
In other embodiments based on embodiment 2 of the invention, fuel filling is performed according to related requirements in a compiled manual, the temperature of the fuel is controlled to be added according to the mission flying height when the fuel is filled, a sensor is electrified after the filling is completed, the temperature of the fuel is output, a flight tube computer collects related data and then pre-judges the fuel to be added according to loading waypoint information, if the current temperature of the fuel exceeds the target height limit temperature and does not meet the requirements, a crew is prompted, the fuel is refilled after related operations such as fuel cooling and the like or the engine fuel is cooled in a circulating way, and the temperature of the fuel to be added into the engine is controlled.
If the fuel temperature meets the requirements, the flight can be carried out, relevant atmospheric data are collected in real time in the flight process, the relevant data are interpreted in real time by an onboard computer through the fuel temperature, the current flight fuel safety is solved in real time, and if the flight conditions are not met, relevant alarm information is downloaded through remote control telemetry, so that a pilot is prompted to adjust relevant flight strategies; if the requirements are met, continuing the current flight.
The invention has the following technical advantages:
1) Use of the Reid vapor pressure: the reed vapor pressure is an important physical property of volatile fuel, a very important factor for aviation fuel, affecting the air resistance characteristics at engine start, temperature rise or high altitude flight, and is defined by: the temperature was 37.8℃and the vapor-liquid ratio was 4.
2) The difference of the Reid vapor pressures of different oil products is larger, the portable ground maintenance equipment supports the injection of the Reid vapor pressures of different oil products, and the system automatically records and stores, judges 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, no special operation is needed for maintenance personnel, and the whole process is completed by the onboard computer, so that interference brought by human factors is avoided.
4) The traditional pressurizing mode has the defects that the pressurizing pressure is difficult to match due to different oil products with different pressurizing pressure requirements, the fuselage structure after pressurizing and the like are required to be correspondingly improved and enhanced, the weight is increased by times due to overlarge pressurizing pressure, and the pressurizing pressure is too small to meet the system requirements. The scheme provided by the invention can avoid the problems.
5) The embodiment of the invention is safe to use and easy to operate, and can safely run without complex equipment.
6) The data used by the invention are all from the high-precision and redundant sensors, the sensors can rapidly feed back various data, the flight tube computer can carry out real-time judgment, the synchronism is good, the feedback can be timely carried out, and the risk caused by hysteresis is avoided.
The invention is not related in part to the same as or can be practiced with the prior art.
The foregoing technical solution is only one embodiment of the present invention, and various modifications and variations can be easily made by those skilled in the art based on the application methods and principles disclosed in the present invention, not limited to the methods described in the foregoing specific embodiments of the present invention, so that the foregoing description is only preferred and not in a limiting sense.
In addition to the foregoing examples, those skilled in the art will recognize from the foregoing disclosure that other embodiments can be made and in which various features of the embodiments can be interchanged or substituted, and that such modifications and changes can be made without departing from the spirit and scope of the invention as defined in the appended claims.
Claims (5)
1. A method for preventing high-altitude evaporation loss of an unmanned aerial vehicle, comprising the steps of:
the method comprises the steps of calculating and judging the current oil use safety in real time according to preset logic by utilizing a flight tube computer, an atmosphere data system and airborne software; the method specifically comprises the following substeps:
s1, manufacturing a manual for limiting the highest fuel temperature under each flying height of the unmanned aerial vehicle according to the oil product characteristics;
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 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 fly tube computer in real time by using a fuel temperature sensor arranged in the fuel supply tank;
s4, setting fuel temperature limiting requirements under different air pressures in the onboard software, resolving in real time, enabling the onboard software to support ground maintenance equipment input, opening an interface, and injecting corresponding indexes of the oil products according to different oil product characteristics;
s5, installing an atmosphere data system on the unmanned aerial vehicle, measuring in real time to obtain a local atmosphere pressure value, accessing the atmosphere pressure value into a flight tube computer, and calculating and downloading fuel limit temperature in real time by using airborne software according to the atmosphere pressure value; when the fuel temperature monitored by the fuel temperature sensor exceeds the limiting condition, remote control and remote measurement downloads related faults and prompts related operators, so that the flight operators are warned to further process the faults, and the safety of the fuel for flight is ensured.
2. The method for preventing high altitude evaporation loss of unmanned aerial vehicle according to claim 1, comprising the steps of, in step S2: and (3) pre-judging the added fuel according to the loading waypoint information, if the current fuel temperature exceeds the target height limit temperature and does not meet the requirement, prompting a crew, re-filling or performing engine fuel circulation cooling after performing fuel cooling related operation, and controlling the temperature of the added engine fuel.
3. The method of claim 1, wherein in step S4, the index includes a rad vapor pressure of an oil.
4. The method for preventing high-altitude evaporation loss of unmanned aerial vehicle according to claim 1, wherein in step S5, the atmospheric pressure value is connected to the fly-tube computer through a serial port.
5. The method of claim 1, wherein in step S5, the flight operator is alerted to further processing by means of color or speech.
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