CN113135299B - Design method for near space unmanned aerial vehicle power system - Google Patents
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- 238000013461 design Methods 0.000 title claims abstract description 53
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- 239000000295 fuel oil Substances 0.000 claims abstract description 8
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- 238000005265 energy consumption Methods 0.000 claims description 9
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- JBRZTFJDHDCESZ-UHFFFAOYSA-N AsGa Chemical compound [As]#[Ga] JBRZTFJDHDCESZ-UHFFFAOYSA-N 0.000 claims description 3
- 229910001218 Gallium arsenide Inorganic materials 0.000 claims description 3
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 claims description 3
- 239000002828 fuel tank Substances 0.000 claims description 3
- 239000003350 kerosene Substances 0.000 claims description 3
- 229910052744 lithium Inorganic materials 0.000 claims description 3
- 238000005457 optimization Methods 0.000 claims description 3
- 230000009467 reduction Effects 0.000 claims description 3
- 230000004580 weight loss Effects 0.000 claims description 2
- 230000009194 climbing Effects 0.000 description 6
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60L—PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES; SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL; MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
- B60L8/00—Electric propulsion with power supply from forces of nature, e.g. sun or wind
- B60L8/003—Converting light into electric energy, e.g. by using photo-voltaic systems
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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
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
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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
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/026—Aircraft characterised by the type or position of power plants comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine
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- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/60—Other road transportation technologies with climate change mitigation effect
- Y02T10/7072—Electromobility specific charging systems or methods for batteries, ultracapacitors, supercapacitors or double-layer capacitors
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- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
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Abstract
A design method of a near space unmanned aerial vehicle power system comprises a combined power system design method and an all-electric power system design method: when the unmanned aerial vehicle takes off, the load carrying fuel oil or the battery is the designated low-limit load, when the unmanned aerial vehicle is empty for a long time or changes along with the flying height, the flying weight of the aircraft is reduced continuously along with the continuous consumption of the carried fuel or the removal of the battery with the exhausted electric energy, and after part of power devices irrelevant to the continuous flying are removed, the total weight of the aircraft is reduced to 40-50% of the original takeoff weight, and the energy required for keeping the unmanned aerial vehicle flying normally is reduced by at least 40-50%; the unmanned aerial vehicle after weight reduction can maintain the idle time of the unmanned aerial vehicle per day to be more than 24 hours only by solar power generation and specified minimum battery capacity; can fly for 3 months continuously at the height of 20000-24000 meters in the adjacent space. The invention adopts an aircraft weight reduction method and a combined power system to solve the dilemma of the unmanned aerial vehicle in the near space in the world.
Description
Technical Field
The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to a design method of a power system of an unmanned aerial vehicle in a near space.
Background
The unmanned aerial vehicle has the specified load capacity, can keep equal-height level flight in an airspace of 2-2 ten thousand meters to 2 ten thousand-4 kilometers, and has practical significance only when the air-remaining time is at least 2 days. Such requirements seem to be modest, but this is currently a difficult goal to achieve in practice for the design, selection of materials and manufacture of near space drones.
The first very important difficulty is how the solar unmanned aerial vehicle flies from the ground to more than 2 kilometers. Of course, the drone may have a certain number of fully charged batteries to enable the drone to climb above 2 kilometers. However, the unmanned aerial vehicle designed according to the current industrial technology can climb to the weight of the battery carried by the unmanned aerial vehicle above 2 kilometers and almost accounts for 40-60% of the total weight of the unmanned aerial vehicle. For example, a solar drone with a takeoff weight of about 750 kilograms carries approximately 450 kilograms of batteries. The weight of the solar power generation film is about 100 kilograms, the weight of the carrying equipment is 30-50 kilograms, the weight of the flight control and power device is about 15 kilograms, and the weight of the aircraft is only about 150 kilograms left for the weight of the aircraft. In order to collect enough available solar energy, the area of the lifting surface of the solar unmanned aerial vehicle is as high as 140-200 square meters, and the wingspan is 60-70 meters. During the flight, the gust can reach 100-200 km/h, so that the solar unmanned aerial vehicle with the light-weight structure has no survival rate basically. The situation that the lightweight structure solar unmanned aerial vehicle is subjected to air disintegration and crash is reproduced in recent 20 years. The solar unmanned aerial vehicle which is called to fly to 23,000 meters in height and is the "Sunshen" solar unmanned aerial vehicle is disintegrated in the air during the second test flight, and the height is only 2,000 meters. In 2019, two 'West wind-S' level solar unmanned aerial vehicles of 'air passengers' are disassembled in the air (which is a cooperative project of 'air passengers' and Japan communication).
A second very important difficulty is how the solar unmanned aerial vehicle can realize long flight time lag space in the near space. To keep the unmanned aerial vehicle flying horizontally in the near space, the only energy source that can be adopted is solar energy, but because of day and night alternation, the whole solar power generation is not enough to maintain the unmanned aerial vehicle designed according to the current original concept flying at the same altitude of 24 hours all day.
Even if the solar unmanned aerial vehicle with the light-weight structure is adopted, the wing load of the aircraft is at least 4-6 kilograms per square meter, and the air is very thin above 20,000 meters and is only 1/30-1/35 of the air density of the ground. Thus, an aircraft flying at that altitude is very inefficient aerodynamically, requiring at least 10 kg/horsepower for the power density required to maintain a level flight, and a 800 kg aircraft requires about 120 horsepower (98,000 watts) for power. However, under a thin atmosphere, the propulsion power is inefficient, only about half of the ground, and the solar energy is required to be 180,000-200,000 watts, which is almost impossible because the current solar cell capacity is about 250-270 watts per square meter. It is quite obvious to solve a procedural flight problem:
before flying to a height of 20,000 m to 24,000 m, a drone is designed with sufficient strength and rigidity to be aerodynamically good, capable of flying from the ground to high altitudes, and obviously a very heavy aircraft.
After flying to the height of 20000 m to 24000 m, the aircraft can keep level flight by using the maximum solar energy which can be collected: it is quite obvious that the airplane has the ability to fly to the adjacent space during takeoff, and is a heavy airplane, and becomes a light airplane after going to high altitude, which is the only exit.
In order to make unmanned aerial vehicle possess long endurance performance, the designer has adopted multiple overall arrangement. The wings are used as main flight lifting bodies, and all developed near space unmanned aerial vehicles are wings with a large aspect ratio (more than 20) in order to improve lift-drag ratio. The lift-drag ratio of the whole unmanned aerial vehicle is higher than 19, and the wing aspect ratio of the unmanned aerial vehicle in the adjacent space reaches 24.
In conclusion, the unmanned aerial vehicle in the adjacent space reaches the height of 20,000-24,000 meters, which is the first necessary target. Many of the very "smart" concepts in the world, such as launching a drone into high altitude with a balloon, however, the high altitude balloon itself presents a serious challenge of raising the altitude, and the suspended drone is destroyed simultaneously when encountering strong wind.
Obviously, it is the most realistic and feasible solution to design an unmanned aerial vehicle that can fly from the ground to the high altitude by its own ability, and this approach is adopted by most scientific circles and projects in the world. However, it is almost impossible to let a light structure drone with such a large size fly to more than 20,000 meters in a complicated atmosphere.
The flight of an aircraft in the atmosphere requires two conditions to be met:
one is a good aerodynamic design to generate sufficient lift with available energy.
Secondly, the air flow has enough strength and rigidity under complex atmospheric conditions to ensure that the air flow does not destroy the air flow in flight, and the two conditions are not indispensable.
Disclosure of Invention
The invention provides a design method of an unmanned aerial vehicle power system in a near space, aiming at solving the defects in the prior art. Aim at solves unmanned aerial vehicle and takes off to carry battery weight overweight and crowded to account for fuselage structure weight, cause the problem of light-weight fuselage easy damage to and solve unmanned aerial vehicle and fly near the space, lean on solar energy power generation to be insufficient to maintain the problem of high flight such as unmanned aerial vehicle 24 hours all day totally.
In order to solve the technical problem, the invention adopts the following technical scheme.
A design method of an unmanned aerial vehicle power system in a near space comprises a design method of a combined power system and a design method of an all-electric power system, and is characterized in that the design method of the combined power system or the design method of the all-electric power system is that the carrying capacity of fuel oil or batteries carried by the unmanned aerial vehicle during takeoff is the minimum carrying capacity, when the unmanned aerial vehicle is in idle time and is changed along with the flying height, the flying weight of the aircraft is continuously reduced along with the continuous consumption of the fuel carried by the unmanned aerial vehicle or the discarding of the batteries with electric energy exhausted, when part of power devices irrelevant to the continuous flying are discarded finally, the total weight of the aircraft is reduced to 40-50% of the original takeoff weight, and due to the reduction of the flying weight of the unmanned aerial vehicle, the energy required by the normal flying of the unmanned aerial vehicle is synchronously reduced by at least 40-50%; the unmanned aerial vehicle after weight reduction can maintain the air-remaining time of the unmanned aerial vehicle every day to be more than 24 hours only by solar power generation and the minimum battery loading capacity; the flying near space unmanned aerial vehicle can continuously fly for at least 3 months at the height of 20,000-24,000 meters in the near space, and the design concept of the unmanned aerial vehicle is called as an aircraft weight reduction method;
the combined power system is a synthetic power system of the unmanned aerial vehicle adopting two power sources with different forms, and the two power sources respectively work in different time periods during flight to provide flying energy for the unmanned aerial vehicle in the adjacent space;
firstly, a solar power generation film covering the surface of an unmanned aerial vehicle in an adjacent space is used for generating power to supply power to an unmanned aerial vehicle propulsion system, and meanwhile, a storage battery carried by the unmanned aerial vehicle is charged;
secondly, a fuel power generation system is installed on the unmanned aerial vehicle in the adjacent space, a power generator is driven by a fuel engine to supply energy to a propulsion system of the unmanned aerial vehicle, and meanwhile, a battery carried by the unmanned aerial vehicle can also be charged; the coordination of the two powers of the 'combined power system' formed by the two different power systems is full-automatic optimization, and the working period is adjusted and controlled to achieve intelligent control.
The design method of the combined power system comprises the following steps:
step one, designing the weight of an energy storage battery carried by the unmanned aerial vehicle during takeoff to be about one fourth or less of the original design weight (because the electrical efficiency of the energy storage battery is improved); the stored energy of the battery with the weight can meet the requirement that the unmanned aerial vehicle after weight reduction (by using an aircraft weight reduction method) can maintain the unmanned aerial vehicle to be vacant for more than 24 hours each day by only solar power generation.
Step two, when the unmanned aerial vehicle is designed, the total weight of fuel carried by the unmanned aerial vehicle during takeoff and part of fuel power devices which can be thrown off can be 50-60% of the total weight of the unmanned aerial vehicle during takeoff; the electric quantity of the solar power generation system for supplying electric energy, which is used as the near space unmanned aerial vehicle to keep flying at the height of 20,000-24,000 meters in the near space, is required to be more than 24 hours of flight energy.
And step three, when the fuel of the unmanned aerial vehicle is exhausted after the unmanned aerial vehicle is left empty for several days, the fuel tank and the power generation system are thrown away, at the moment, the weight of the unmanned aerial vehicle is reduced by 40-50%, the energy consumption is very low, and due to the very low energy consumption, the unmanned aerial vehicle can be flown by only using the solar power generation and the energy storage battery, so that the unmanned aerial vehicle can be maintained for at least 3 months.
The design method of the combined power system comprises the following examples:
weight when unmanned aerial vehicle takes off: 720-770 kg of energy storage battery, 100-120 kg of energy storage battery, 350 kg of fuel oil, 230-250 kg of self weight of unmanned aerial vehicle and 40-50 kg of effective load;
the service life is repeatedly designed: 100 take-offs and landings, 10,000 flight hours;
power facilities: the surface is covered with a gallium arsenide film which can generate 50,000 watts, a kerosene engine drives a generator to generate 6,000 watts, and the total power reaches 56,000 watts;
altitude and idle time: keeping the horizontal flight at the height of 24,000 meters for 25-35 days;
flight speed range: the height is 18,000-24,000 meters. The flight speed is 250-120 km/h, and the takeoff speed is 35-40 km/h;
flight height: a maximum flying height of 28,000 meters and a cruising height of 20,000 meters to 24,000 meters;
taking off and landing modes: running takeoff or traction takeoff, and wheel type running landing.
The design method of the full-electric power system comprises the following steps:
step one, designing the weight of a battery carried by the unmanned aerial vehicle during takeoff to be 60% of the total takeoff weight of the unmanned aerial vehicle;
step two, the exhausted battery is thrown away for multiple times between flying to 24000 meters after the unmanned aerial vehicle takes off, and the flat flying energy of at least 18 hours can be maintained until the rest battery is charged; at the moment, the total weight of the whole unmanned aerial vehicle is reduced to 60% of the total weight of the unmanned aerial vehicle during takeoff;
charging the rest batteries while generating power by solar energy for at least 6 hours, wherein the energy of the charged batteries and the energy generated by the solar energy are equal to the energy required by the unmanned aerial vehicle for flat flight for 24 hours a day; because the total weight of the whole unmanned aerial vehicle is reduced by 40 percent, the energy consumption is very low, the unmanned aerial vehicle can maintain the idle time of at least 3 months by only using the solar power generation and the energy storage battery for the flight of the plane.
The second step includes the following examples: the unmanned aerial vehicle is designed to throw away the battery exhausted after taking off for three times, wherein each time is one fifth of the total weight of the battery, 10000 meters throw away one fifth of the weight of the battery, then rise by 10000 meters, then throw away one fifth of the weight of the battery, fly to 24000 meters, then throw away one fifth of the weight of the battery, and leave two fifths of the battery, and the battery can maintain the flat flight energy for at least 18 hours after being charged; the total weight of the whole unmanned aerial vehicle is reduced to 60% of the total weight of the unmanned aerial vehicle during takeoff.
The specific examples of the design method of the full-electric power system are as follows: the takeoff weight of the unmanned aerial vehicle is 150 kilograms, the wing area is about 25 square meters, 90 kilograms of lithium batteries are arranged, 10 kilograms of equipment are arranged, the weight of the aircraft structure is about 50 kilograms, and the aircraft structure comprises power, navigation and flight control.
Advantageous effects of the invention
1. The invention adopts two new concepts of 'aircraft weight reduction method' and 'combined power system' for unmanned aerial vehicle design to solve the dilemma faced by the unmanned aerial vehicle in the near space in the world. Both of these approaches have been supported by basic flight records. The total weight of the airplane is reduced to 40-50% of the original takeoff weight when the airplane reaches a critical space by fuel oil or batteries carried by the unmanned airplane during takeoff and batteries continuously consumed along with the fuel or batteries exhausted by electric energy; the weight of the plane is reduced by half, so that the unmanned plane flying in a critical space can keep the unmanned plane vacant time per day for more than 24 hours only by solar power generation and the minimum battery capacity; the near space unmanned aerial vehicle can continuously fly for at least 3 months at the height of 20,000-24,000 meters in the near space.
2. The invention breaks through the long-term thought that the unmanned aerial vehicle in the near space has to be provided with heavy batteries and light structures when the unmanned aerial vehicle is required to fly high and long-term navigation, and depends on the very occasional big unmanned aerial vehicle with good weather that the whole lift-off process is breezy. Through designing two design new concept aircraft weight loss methods "and" combination driving system "of unmanned aerial vehicle in-process for close on space unmanned aerial vehicle can require different unmanned aerial vehicle of rational design according to different tasks. Effectively reduced critical space unmanned aerial vehicle's preparation and use cost. Especially, the method is particularly important for the aerial base station in the communication field, can break through the limitation of a small satellite scheme, and creates a new era.
Drawings
FIG. 1 illustrates a design method of a near space unmanned aerial vehicle hybrid power system according to the present invention;
fig. 2 is a design method of the near space unmanned aerial vehicle full-electric power system.
Detailed Description
Design principle of the invention
1. Unmanned aerial vehicle flies to be high, only meaningful when long voyage, but flies to be high and the time of long voyage is a pair of contradiction again: the flying height requires that the unmanned aerial vehicle can reach the height of a critical space only by carrying enough fuel or batteries when taking off, and the weight of the fuel or the batteries at the taking off occupies 40 to 50 percent of the total weight of the aircraft when the unmanned aerial vehicle reaches the height. The weight of the unmanned aerial vehicle body is required to be reduced as much as possible during long-endurance, and the unmanned aerial vehicle can save electricity as much as possible only because the weight of the unmanned aerial vehicle body is reduced as much as possible, so that the air-remaining time of the unmanned aerial vehicle is as long as possible.
2. The solution of the invention is as follows: the power consumption of the unmanned aerial vehicle is divided into two stages, namely a climbing stage and a level flight stage, wherein enough fuel or battery must be ensured in the climbing stage, so that the weight of the fuel or battery carried by the unmanned aerial vehicle in the climbing stage must be ensured to be capable of flying to a critical space of more than 2400 meters; the weight is reduced as much as possible in the flat flight stage, and the weight reduction method comprises two aspects, on one hand, redundant fuel or batteries are thrown away after the unmanned aerial vehicle finishes the climbing stage, and on the other hand, in the flat flight stage, the weight of the batteries only meets the power consumption weight of the unmanned aerial vehicle in the period without sunshine in one day. The weight of the battery is designed according to 24 hours of power supply. And in the climbing stage, the unmanned aerial vehicle discards redundant fuel or batteries, for the former, the fuel is naturally consumed along with the climbing of the aircraft, only power generation equipment needs to be discarded, for the latter, a random discarding method is adopted, and batteries which are exhausted by electric energy are discarded every 1 ten thousand meters until a small amount of batteries which only meet the electricity consumption of 1 day in the flat flight stage are reserved. In the flat flight stage, the solar energy generates electricity for at least 6 hours, the energy storage battery is charged for 6 hours, the energy storage battery after being charged for 6 hours can ensure 24-hour electricity utilization, and the electricity generation of the solar energy can completely meet 24-hour electricity utilization in one day. The method of solar power generation and battery charging is carried out in cycles every day, and the unmanned aerial vehicle can be guaranteed to have at least 3 months of idle time. The 3-month empty time calculation is based on charging the battery 1 time per day, and can be charged 100 times in total.
In a word, the design of the near space unmanned aerial vehicle adopting the design concept is an intelligent design. The comprehensive system engineering of a task, airplane performance, takeoff weight, airplane size, airplane structural strength, intelligent power system and throwing mechanism.
Based on the principle, the invention designs a design method of a near space unmanned aerial vehicle power system.
A design method of an unmanned aerial vehicle power system in a near space comprises a combined power system design method and an all-electric power system design method, and is characterized in that the combined power system design method or the all-electric power system design method is used, the amount of fuel oil or batteries carried by an unmanned aerial vehicle during takeoff is the minimum load, when the unmanned aerial vehicle is in idle time and changes along with the flight altitude, the flight weight of the aircraft is continuously reduced along with continuous consumption of the carried fuel or discarding of batteries with electric energy depletion, and after a part of power devices irrelevant to continuous flight are discarded finally, the total weight of the aircraft is reduced to 40-50% of the original takeoff weight. Due to the reduction of the flight weight of the unmanned aerial vehicle, the energy required for keeping the unmanned aerial vehicle flying normally is reduced by at least 40-50% synchronously; the unmanned aerial vehicle after weight reduction can maintain the air-remaining time of the unmanned aerial vehicle every day to be more than 24 hours only by solar power generation and the minimum battery loading capacity; the flying near space unmanned aerial vehicle can continuously fly for 3 months at the height of 20000-24000 meters in the near space at least, and the design concept of the unmanned aerial vehicle is called as an aircraft weight reduction method.
The combined power system is a synthetic power system of the unmanned aerial vehicle adopting two power sources with different forms, and the two power sources respectively work in different time periods during flight to provide flying energy for the unmanned aerial vehicle in the adjacent space;
firstly, a solar power generation film covering the surface of an unmanned aerial vehicle in an adjacent space is used for generating power to supply power to an unmanned aerial vehicle propulsion system, and meanwhile, a storage battery carried by the unmanned aerial vehicle is charged;
secondly, a fuel power generation system is installed on the unmanned aerial vehicle in the adjacent space, a power generator is driven by a fuel engine to supply energy to a propulsion system of the unmanned aerial vehicle, and meanwhile, a battery carried by the unmanned aerial vehicle can also be charged; the coordination of the two powers of the 'combined power system' formed by the two different power systems is full-automatic optimization, and the working period is adjusted and controlled to achieve intelligent control.
As shown in fig. 1, the method for designing the combined power system includes the following steps:
step one, designing the weight of an energy storage battery carried by the unmanned aerial vehicle during take-off to be about one quarter or less of the original design weight (because the electrical efficiency of the energy storage battery is improved); the stored energy of the battery with the weight can meet the requirement that the unmanned aerial vehicle after weight reduction (by using an aircraft weight reduction method) can maintain the unmanned aerial vehicle to be vacant for more than 24 hours each day by only solar power generation.
Step two, when the unmanned aerial vehicle is designed, the total weight of fuel carried by the unmanned aerial vehicle during takeoff and part of fuel power devices which can be thrown off can be 50-60% of the total weight of the unmanned aerial vehicle during takeoff; the electric quantity of the solar power generation system for supplying electric energy, which is used as the near space unmanned aerial vehicle to keep flying at the height of 20,000-24,000 meters in the near space, is required to be more than 24 hours of flight energy.
And step three, when the fuel of the unmanned aerial vehicle is exhausted after the unmanned aerial vehicle is left empty for several days, the fuel tank and the power generation system are thrown away, at the moment, the weight of the unmanned aerial vehicle is reduced by 40-50%, the energy consumption is very low, and due to the very low energy consumption, the unmanned aerial vehicle can be flown by only using the solar power generation and the energy storage battery, so that the unmanned aerial vehicle can be maintained for at least 3 months.
Unmanned aerial vehicle design example of combined power system:
unmanned aerial vehicle weight when taking off: 720-770 kg of energy storage battery, 100-120 kg of energy storage battery, 350 kg of fuel oil, 230-250 kg of self weight of unmanned aerial vehicle and 40-50 kg of effective load;
repeated design life: 100 take-offs and landings, 10,000 flight hours;
power facilities: the surface is covered with a gallium arsenide film which can generate 50,000 watts, a kerosene engine drives a generator to generate 6,000 watts, and the total power reaches 56,000 watts;
altitude and idle time: keeping the horizontal flight at the height of 24,000 meters for 25-35 days;
flight speed range: the height is 18,000-24,000 meters. The flight speed is 250-120 km/h, and the takeoff speed is 35-40 km/h;
flight height: a maximum flying height of 28,000 meters, a cruising height of 20,000 meters to 24,000 meters;
taking off and landing modes: running takeoff or traction takeoff, and wheel type running landing.
As shown in fig. 2, the method for designing an all-electric power system includes the following steps:
step one, designing the weight of a battery carried by the full-electric unmanned aerial vehicle during takeoff to be about 40-60% of the total takeoff weight of the unmanned aerial vehicle;
step two, the unmanned aerial vehicle is designed to throw off the exhausted battery for multiple times between flying to 24,000 meters after taking off until the rest battery can maintain the flat flying energy for at least 18 hours after being charged; at the moment, the total weight of the whole unmanned aerial vehicle is reduced to 60% of the total weight of the unmanned aerial vehicle during takeoff;
charging the rest batteries while generating power by solar energy for at least 6 hours, wherein the energy of the charged batteries and the energy generated by the solar energy are equal to the energy required by the unmanned aerial vehicle for flat flight for 24 hours a day; because the total weight of the whole unmanned aerial vehicle is reduced by 40 percent, the energy consumption is very low, the unmanned aerial vehicle can be kept in the air for at least 3 months only by using the solar power generation and the energy storage battery to fly by the aircraft.
The second step includes the following examples: the unmanned aerial vehicle is designed to throw off the battery exhausted by the battery for three times after taking off, wherein each time is one fifth of the total weight of the battery, one fifth of the weight of the battery is thrown off by 10000 meters, then the battery is lifted by 10000 meters, then one fifth of the weight of the battery is thrown off by the unmanned aerial vehicle after flying to 24000 meters, then one fifth of the weight of the battery is thrown off, and two fifths of the battery is left, and the battery can maintain the flat flying energy for at least 18 hours after being charged; the total weight of the whole unmanned aerial vehicle is reduced to 60% of the total weight of the unmanned aerial vehicle during takeoff.
The design example of the full-electric power system is as follows:
the BDM-A5 full-electric unmanned aerial vehicle has the take-off weight of 150 kilograms, the wing area of about 25 square meters, 90 kilograms of lithium batteries, 10 kilograms of equipment and 50 kilograms of airplane structure weight (including power, navigation and flight control). When the flying height reaches 10,000 m, 20 kg of batteries are thrown by a parachute. Fly to 20,000 meters high and throw another 20 kilograms of batteries. Flying to 24000 m high and throwing 20 kg of battery. The weight of the whole aircraft is reduced to 90 kilograms, the wing load is reduced from 6 kilograms per square meter to 3.6 kilograms per square meter, the solar energy generation of the whole aircraft is about 250 watts per square meter x 40 square meter =10,000 watts, the required power for maintaining 2-ten-thousand-meter flat flight is only 2,500-3,000 watts, the accumulated energy storage of the solar energy in 4-6 hours can reach 10,000 watts x 6 hours =60,000 watts per hour, the flat flight energy can be maintained for about 18 hours, and the rest 30 kilograms of batteries can fly for 6 hours, so that the aircraft can fly for at least 24 hours in a space of 20000 meters-24000 meters. As long as the onboard equipment is normal, the drone can fly in a space of 18,000-20,000 meters for a long time, at least 3 months.
The above description is only a preferred embodiment of the present invention, and the protection scope of the present invention is not limited to the above embodiments, and all technical solutions belonging to the idea of the present invention belong to the protection scope of the present invention. It should be noted that modifications and embellishments within the scope of the invention may occur to those skilled in the art without departing from the principle of the invention, and are considered to be within the scope of the invention.
Claims (2)
1. A design method of an unmanned aerial vehicle power system in a near space comprises a combined power system design method and an all-electric power system design method, and is characterized in that the combined power system design method or the all-electric power system design method is used, the carrying capacity of fuel oil or batteries carried by an unmanned aerial vehicle during takeoff is the minimum carrying capacity, when the unmanned aerial vehicle is in idle time and is increased or changed along with the flying height, the flying weight of the unmanned aerial vehicle is continuously reduced along with the continuous consumption of the fuel carried by the unmanned aerial vehicle or the discarding of the batteries with electric energy, when part of power devices irrelevant to the continuous flying are discarded finally, the total weight of the unmanned aerial vehicle is reduced to 40-50% of the takeoff weight, and due to the reduction of the flying weight of the unmanned aerial vehicle, the energy required by the unmanned aerial vehicle for keeping normal flying is synchronously reduced by 40-50%; the unmanned aerial vehicle after weight loss only depends on solar power generation and the minimum battery loading capacity, and the unmanned aerial vehicle can be kept in the air for 24 hours every day; the unmanned aerial vehicle can continuously fly for at least 3 months at the height of 20,000-24,000 meters in the adjacent space, and the design concept of the unmanned aerial vehicle is called as an aircraft weight reduction method;
the combined power system is a synthetic power system of the unmanned aerial vehicle adopting two power sources in different forms, and the two power sources respectively work in different time periods during flight to provide flying energy for the unmanned aerial vehicle;
firstly, a solar power generation film covered on the surface of the unmanned aerial vehicle is used for generating power to supply power to an unmanned aerial vehicle propulsion system and simultaneously charge a battery carried by the unmanned aerial vehicle;
secondly, a fuel power generation system is installed on the unmanned aerial vehicle, a generator is driven by a fuel engine to supply energy to a propulsion system of the unmanned aerial vehicle, and meanwhile, a battery carried by the unmanned aerial vehicle can be charged; the coordination of the two powers of the combined power system formed by the two different power systems is full-automatic optimization, and the working period is adjusted and controlled to achieve intelligent control;
the design method of the combined power system comprises the following steps:
firstly, designing the weight of a battery carried by the unmanned aerial vehicle during takeoff by using the aircraft weight reduction method, wherein only the stored energy of the battery with the weight can meet the requirement that the unmanned aerial vehicle after weight reduction can maintain the unmanned aerial vehicle to be vacant for 24 hours every day only by solar power generation;
step two, when the unmanned aerial vehicle is designed, the total weight of fuel carried by the unmanned aerial vehicle during takeoff and a part of thrown fuel power device can be 50-60% of the takeoff weight of the unmanned aerial vehicle; the electric quantity of the solar power generation system for providing electric energy for the unmanned aerial vehicle to keep flying at the height of 20,000-24,000 meters in the adjacent space is required to be more than 24 hours of flight energy;
step three, when the fuel of the unmanned aerial vehicle is exhausted after the unmanned aerial vehicle is left empty for several days, the fuel tank and the power generation system are thrown away, at the moment, the weight of the unmanned aerial vehicle is reduced by 40-50%, the energy consumption is very low, and due to the very low energy consumption, the unmanned aerial vehicle can be flown only by using solar power generation and a battery, so that the unmanned aerial vehicle can be maintained for at least 3 months;
the design method of the full-electric power system comprises the following steps:
step one, designing the weight of a battery carried by the unmanned aerial vehicle during takeoff to be 60% of the total takeoff weight of the unmanned aerial vehicle;
step two, the exhausted battery is thrown away for multiple times between flying to 24000 meters after the unmanned aerial vehicle takes off, and the flat flying energy of at least 18 hours can be maintained until the rest battery is charged; at the moment, the total weight of the whole unmanned aerial vehicle is reduced to 60% of the takeoff weight of the unmanned aerial vehicle;
charging the rest batteries while generating power by solar energy for at least 6 hours, wherein the energy of the charged batteries and the energy generated by the solar energy are equal to the energy required by the unmanned aerial vehicle for flat flight for 24 hours a day; because the total weight of the whole unmanned aerial vehicle is reduced by 40 percent, the energy consumption is very low, the unmanned aerial vehicle can fly only by using the solar power generation and energy storage battery, and the air-remaining time of the unmanned aerial vehicle can be maintained for at least 3 months;
the parameters of the unmanned aerial vehicle designed by the combined power system design method are as follows:
unmanned aerial vehicle weight of taking off: 720-770 kg of battery weight, 100-120 kg of battery weight, 350 kg of fuel oil weight, 230-250 kg of self weight of the unmanned aerial vehicle and 40-50 kg of effective load;
repeated design life: 100 take-offs and landings, 10,000 flight hours;
power facilities: the surface is covered with a gallium arsenide film which can generate 50,000 watts, a kerosene engine drives a generator to generate 6,000 watts, and the total power reaches 56,000 watts;
altitude and idle time: keeping the horizontal flight at the height of 24,000 meters for 25-35 days;
flight speed range: the height is 18,000-24,000 meters, the flying speed is 250-120 km/h, and the takeoff speed is 35-40 km/h;
flight height: a maximum flying height of 28,000 meters and a cruising height of 20,000 meters to 24,000 meters;
taking off and landing modes: running takeoff or traction takeoff, and wheel type running landing.
2. The design method of the adjacent space unmanned aerial vehicle power system as claimed in claim 1, wherein: the second step of the design method of the full electric power system comprises the following steps: the unmanned aerial vehicle is designed to throw off the battery exhausted by the battery for three times after taking off, wherein each time is one fifth of the total weight of the battery, one fifth of the weight of the battery is thrown off by 10000 meters, then the battery is lifted by 10000 meters, then one fifth of the weight of the battery is thrown off by the unmanned aerial vehicle after flying to 24000 meters, then one fifth of the weight of the battery is thrown off, and two fifths of the battery is left, and the battery can maintain the flat flying energy for at least 18 hours after being charged; at the moment, the total weight of the whole unmanned aerial vehicle is reduced to 60% of the total weight of the unmanned aerial vehicle during takeoff;
the parameters of the unmanned aerial vehicle designed by adopting the full-electric power system are as follows:
unmanned aerial vehicle takes off weight and is 150 kilograms, and the wing area is about 25 square meters, has 90 kilograms of lithium cell, and equipment 10 kilograms, and unmanned aerial vehicle structure is about 50 kilograms, the unmanned aerial vehicle structure includes power, navigation, flies the accuse device.
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| US20030230671A1 (en) * | 2000-08-24 | 2003-12-18 | Dunn James P. | Fuel cell powered electric aircraft |
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| CN103840745A (en) * | 2013-09-13 | 2014-06-04 | 武汉美格科技有限公司 | Solar energy system for unmanned plane to use |
| CN204021254U (en) * | 2014-07-03 | 2014-12-17 | 刘泰麟 | A kind of solar power flight instruments |
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