CN106394899A - Daytime climbing flight method for reducing weight and size of solar unmanned aerial vehicle - Google Patents
Daytime climbing flight method for reducing weight and size of solar unmanned aerial vehicle Download PDFInfo
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- CN106394899A CN106394899A CN201610903406.XA CN201610903406A CN106394899A CN 106394899 A CN106394899 A CN 106394899A CN 201610903406 A CN201610903406 A CN 201610903406A CN 106394899 A CN106394899 A CN 106394899A
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- 230000033228 biological regulation Effects 0.000 claims description 2
- 230000000630 rising effect Effects 0.000 claims description 2
- 230000005611 electricity Effects 0.000 description 3
- 230000005484 gravity Effects 0.000 description 3
- 238000005381 potential energy Methods 0.000 description 3
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- 238000004146 energy storage Methods 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
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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
- B64D27/30—Aircraft characterised by electric power plants
- B64D27/35—Arrangements for on-board electric energy production, distribution, recovery or storage
- B64D27/353—Arrangements for on-board electric energy production, distribution, recovery or storage using solar cells
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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
- B64D41/00—Power installations for auxiliary purposes
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
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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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Abstract
The invention discloses a daytime climbing flight method for reducing the weight and size of a solar unmanned aerial vehicle, and belongs to the field of design of air vehicles. The daytime climbing flight method for reducing the weight and size of the solar unmanned aerial vehicle comprises the steps that with 24 hours as a cycle, the solar unmanned aerial vehicle cruises at a normal cruising altitude from the sunrise moment t1 to the time when a secondary power supply is fully charged; from the moment when the secondary power supply is fully charged, residual solar energy is fully used by the unmanned aerial vehicle for climbing flight; the unmanned aerial vehicle starts to descend with power after climbing to the specific altitude, and the unmanned aerial vehicle starts to slide downwards without power from the moment when the secondary power supply starts to participate in power supply till the unmanned aerial vehicle slides downwards to the normal cruising altitude; and the unmanned aerial vehicle cruises all over the night in a constant-altitude mode at the normal cruising altitude by means of energy provided by the secondary power supply till the sunrise moment of the next day, the circulating cycle of one day is ended, and the next cycle is started. According to the daytime climbing flight method for reducing the weight and size of the solar unmanned aerial vehicle, the flight strategy that the solar unmanned aerial vehicle climbs after noon and then falls, so that the energy demand for the secondary power supply is reduced, the weight of the secondary power supply is reduced to a certain extent, the weight and size of the solar unmanned aerial vehicle are reduced accordingly, and the feasibility of the scheme is improved.
Description
Technical field
The invention belongs to field of flight vehicle design, it is related to the conceptual design of solar energy unmanned plane, specifically one kind can subtract
Light solar energy unmanned aerial vehicle design weight, the climbing flight strategy in the daytime reducing its design size, improving concept feasible.
Background technology
Solar energy unmanned plane is a kind of unmanned vehicle by the use of solar radiation energy as the propulsion energy.White
My god, rely on wing and stabilizing surfaces laying photovoltaic cell convert solar energy into electrical energy, maintain dynamical system, Aerial Electronic Equipment and
The operation of payload, utilizes dump energy to be that airborne secondary power supply charges simultaneously；At night, using storage in secondary power supply
Energy maintains the normal operation of whole unmanned plane.If the energy of storage on daytime can meet the demand at night, solar energy is unmanned
Machine can realize permanent airflight in theory.Solar energy unmanned plane need not carry any fuel, and flying height is high, the cruise time
Long, overlay area is wide, can execute multiple-task, have the irreplaceable advantage of conventional aircraft, application prospect is boundless.
From the point of view of using value angle, the cruising altitude of solar energy unmanned plane is more high more favourable.Military aspect, increases flight
Height can be expanded the coverage area, improve survival ability；Civilian aspect, for remote sensing and communication relaying, improves flight high
Degree can increase transmitting effect distance.And from the point of view of concept feasible angle, flying height is higher, atmospheric density is less (especially
It is near space, air is very thin), overcome the level speed that gravity needs bigger, unmanned plane during flying required horsepower is also got over
Greatly；On the other hand, atmospheric density is less, and Reynolds number is lower, and lift-drag ratio is also less, further increases required horsepower.Two aspects
Effect limit the flying height of solar energy unmanned plane.For providing enough solar energys, the size of solar energy unmanned plane is general
Larger, to provide enough tile areas.
HAE solar energy unmanned plane is at present still in flying demonstration Qualify Phase, wherein topmost restraining factors
It is energy power system.In the state of the art, secondpower supply system energy density is relatively low, meets the needs of night flying
Secondary power supply weight is larger, accounts for more than the 35% of whole machine weight, seriously limits opening up of solar energy unmanned plane load-carrying ability
Exhibition and the raising of flying quality.And the raising of secondary power supply energy density needs to expend substantial amounts of manpower, financial resources and time, short-term
Inside it is difficult to obtain the breakthrough of big matter.
Content of the invention
The purpose of the present invention is on the premise of meeting use requirement, under identical energy power system technical merit,
By using the countermeasures declining again that climb after high noon, reducing the energy requirement to secondary power supply, replace partly secondary electricity
The weight in source, thus reducing design weight and the size of solar energy unmanned plane, improves concept feasible.
The invention provides the flying of declining again of climbing before a kind of sunset reducing solar energy unmanned aerial vehicle design weight and size
Row method, with 24 hours as a cycle, using the flight of " lower bound cruise is fully climbed and slowly declined lower bound cruise "
Mode.Specifically：In sunrise moment t1 to secondary power supply fully charged moment, solar energy unmanned plane is highly determined height and is patrolled normaling cruise
Boat；From the secondary power supply fully charged moment, unmanned plane makes full use of remaining solar energy climbing flight, by solar energy with height
Form stores；Start drive to decline, now secondary power supply does not work after rising to specified altitude assignment；It is not enough to tie up in solar energy
Hold the moment of the power demand of airborne equipment and mission payload, secondary power supply begins participating in power supply, now unmanned plane starts no to move
Power glides, until slip down to normaling cruise height.Patrolled using the energy fixed high more night that secondary power supply provides normaling cruise height
Navigate to sunrise moment next day, the cycle period of a day terminates, enter next circulation.Wherein, normaling cruise height is that flight is appointed
The minimum cruising altitude of business regulation.
The advantage of the present invention and feature are：
1st, under the premise of ensureing to get over night cruising altitude, design weight and the size of solar energy unmanned plane are reduced.Before sunset
The countermeasures declining again that climb can effectively reduce the working time of solar energy unmanned plane secondary power supply, in identical energy storage density
Under the conditions of reduce the weight needing to carry secondary power supply, directly reduce the gross weight of solar energy unmanned plane；Each daytime simultaneously
Gross energy required for night circulation reduces, and under conditions of identical conversion efficiency of solar cell, reduces and need to use solar-electricity
The area of pond plate, and then reduce wing area and the span of solar energy unmanned plane.Solar energy unmanned plane enormous size, typically real
The length of solar energy unmanned plane reaches tens of rice, leads to that its structural strength is low, it is big to realize difficulty, wind loading rating is weak, manufacture is difficult
Degree is big, high cost.The design weight and the size that reduce solar energy unmanned plane are difficult for the manufacturing reducing solar energy unmanned plane
Degree and cost, are improved its wind loading rating and are of great importance with structural strength.
2nd, on the premise of ensureing mission payload power draw in whole usage cycles, reduce solar energy unmanned plane to energy
The degree of dependence of origin system technical merit.The weight of solar energy unmanned plane and size are to energy resource system technical merit sensitivity relatively
Height, particularly high to the energy density sensitivity of secondary power supply.Secondary power supply energy density is relatively low to be to develop solar energy at present
The short slab of unmanned plane, relatively low energy density can lead to scheme size larger, result even in energy scheme cannot closed loop so that
Whole UAS is infeasible.The countermeasures declining again that climb before sunset can subtract under identical energy resource system technical merit
The design weight of Sunny energy unmanned plane and size, need not pay other costs.Climb before sunset the countermeasures section declining again
Weight about and energy can be also used for load and expand, and improves the load-carrying ability of solar energy unmanned plane.
Brief description
Fig. 1 is the power spectrum of solar energy unmanned plane；
Fig. 2 is solar energy unmanned plane during flying height and moment relation curve；
Fig. 3 is the relation curve in the energy of storage and moment in secondary power supply.
Specific embodiment
Below in conjunction with accompanying drawing and case study on implementation, the present invention is described in further detail.
In conjunction with Fig. 1 to Fig. 3, embodiments of the present invention are described.As shown in figure 1, the t1 moment is the sunrise moment, with 1 year
Day subnumber and different.In the t2 moment, the output of solar array is able to maintain that just normals cruise flight and other work(
The demand that rate is extracted.T1 to the t2 time period, solaode is not enough to maintain the power demand of UAS, by secondary power supply
Combine power supply with solar array.T2 to the t4 time period, ensureing propeller power, airborne equipment and mission payload power draw
On the basis of charge for secondary power supply, until the t4 moment, secondary power supply is full of, as shown in Figure 3.T1 to the t4 time period, solar energy
Normaling cruise height H1, height cruises unmanned plane calmly, and height H1 is carried out the minimum flight altitude that task is allowed.
As shown in Fig. 2 from the t4 moment, solar energy unmanned plane is climbed using remaining solar energy, and the climb rate is gradually reduced,
Up to the t5 moment, unmanned plane climbs H2 highly, and the remaining climb rate is 0.As shown in figure 3, secondary power supply not work during this
Make, store solar energy in the form of height.Described remaining solar energy refers in the case of the full electricity of secondary power supply, solar-electricity
All energy that pond battle array can provide, except the power draw of fixing equipment and load, are all used for climbing flight, that is, with potential energy shape
Formula stores solar energy.
From the t5 moment, solar energy unmanned plane starts drive and declines, until the t6 moment reaches H3 height, as Fig. 2 institute
Show.During this, solaode supplies for propulsion system on the basis of meeting airborne equipment and mission payload power draw
Electricity, secondary power supply does not work, and with the reduction of solar array available horsepower, the power that unmanned plane can be used for flying gradually subtracts
Little, fall off rate is gradually increased.The described t6 moment is that solar array output just can maintain airborne equipment and appoint
The moment of the power demand of business load.
From the t6 moment, solar energy is not enough to maintain the power demand of airborne equipment and mission payload, and secondary power supply is opened
Begin to participate in power supply, now solar energy unmanned plane proceeds to unpowered downslide, and propulsion system is in idling rating.Until the t7 moment, no
Man-machine dropping to normals cruise height H1.Within this time period of t5 to t7, solar energy unmanned plane overcomes resistance using gravity, always
Demand power relatively low it is achieved that the utilization of potential energy.
From after the t7 moment, solar energy unmanned plane is normaling cruise the fixed high cruise of height H1, using the energy in secondary power supply
Amount maintains night flying and other power demands, until next day sunrise moment t1 ＇, the cycle period of a day terminates, and enters next
Individual circulation.
Embodiment：
Design requirement：Flight time between the Spring Equinox to the Autumnal Equinox, operating latitude north latitude 35-degree, minimum cruising altitude 18km, appoint
Business load power 2kw, load weight 100kg, lift-drag ratio 30 of cruising.
For the solar energy unmanned plane in the fixed high cruise of 18km, for meeting above-mentioned design requirement, need wing area 344
, length 101.6m, gross weight 2030kg, wherein secondary power supply weight 854kg.Under identical design input, fixed high cruise is high
Degree is higher, and the unmanned plane size of needs and weight are all bigger, taking the fixed high cruise of 19km as a example, the wing that solar energy unmanned plane needs
Area is 474, length 119.2m, gross weight 2711kg, wherein secondary power supply weight 1176kg.
And using the countermeasures declining again that climb before sunset of the present invention：Night cruises in 18km, starts afternoon
Rise to 24km, then begin to decline, in dropping to 18km after the sunset, move in circles, the wing that solar energy unmanned plane needs
Area is 307, length 96.0m, gross weight 1714kg, wherein secondary power supply 658kg.High cruise fixed compared to 18km, the present invention
Described countermeasures can make design wing area and the span reduce 10.7% and 5.5% respectively, makes design gross weight and secondary
Power supply weight reduces 15.6% and 23.0% respectively.
Above case explanation solar energy unmanned plane can effectively reduce design weight using countermeasures of the present invention
And size, improve concept feasible.
Specific implementation process：
From the sunrise moment 6:00 to afternoon 14:15, solar energy unmanned plane is normaling cruise the fixed high cruise of height 18km.Wherein
6:00 to 7:06 time period, solaode is not enough to maintain the power demand of UAS, by secondary power supply and solar energy
Power supply combined by battery.7:06 to 14:15 time periods, in the base ensureing propeller power, airborne equipment and mission payload power draw
Charge for secondary power supply on plinth, until 14:In 15 moment, secondary power supply is full of.
From 14:In 15 moment, solar energy unmanned plane is climbed using remaining solar energy, and the climb rate is gradually reduced, until 16:
In 17 moment, unmanned plane climbs 24km highly, and the remaining climb rate is 0m/s, after 2.02h.Secondary power supply not work during this
Make, store solar energy in the form of height.
From 16:In 17 moment, solar energy unmanned plane starts drive and declines, and fall off rate is gradually increased, until 17:50
Reach 20.7km height, after 1.55h.During this, solaode is meeting airborne equipment and mission payload power carries
Power for propulsion system on the basis of taking, secondary power supply does not work.
From 17:In 50 moment, solar energy is not enough to maintain the power demand of airborne equipment and mission payload, secondary power supply
Begin participating in power supply, now solar energy unmanned plane starts unpowered downslide, propulsion system is in idling rating.Until 18:When 33
Carve, unmanned plane drops to normals cruise height 18km, after 0.71h.16:17 to 18:In 33 this periods, solar energy is unmanned
Machine overcomes resistance using gravity, required horsepower less it is achieved that the utilization of potential energy.
From 18:After 33 moment, solar energy unmanned plane is normaling cruise the fixed high cruise of height 18km, using in secondary power supply
Energy maintain night flying and other power demands, until sunrise moment next day, the cycle period of a day terminates, and enters next
Individual circulation.
Claims (1)
1. a kind of method of climbing flight in the daytime reducing solar energy unmanned plane weight and size it is characterised in that：With 24 hours it was
A cycle, in sunrise moment t1 to secondary power supply fully charged moment, solar energy unmanned plane is normaling cruise highly fixed high cruise；
From the secondary power supply fully charged moment, unmanned plane makes full use of remaining solar energy climbing flight, by solar energy with the shape of height
Formula stores；Start drive to decline, now secondary power supply does not work after rising to specified altitude assignment；It is not enough to maintain in solar energy
In the moment of the power demand of airborne equipment and mission payload, secondary power supply begins participating in power supply, and now unmanned plane is by under drive
Fall switchs to unpowered downslide, until slip down to normaling cruise height；Normaling cruise the energy that height utilizes secondary power supply to provide
Fixed high more night cruised to sunrise moment next day, and the cycle period of a day terminates, and entered next circulation；Wherein, normal cruise height
Degree is the minimum cruising altitude of aerial mission regulation.
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106951650A (en) * | 2017-03-28 | 2017-07-14 | 南京信息工程大学 | Unmanned plane endurance assessment system |
| CN107065927A (en) * | 2017-04-20 | 2017-08-18 | 杭州电子科技大学 | The quadrotor and control method of a kind of solar energy continuation of the journey |
| CN108820230A (en) * | 2018-05-31 | 2018-11-16 | 中国航天空气动力技术研究院 | A kind of energy management method of circulation flight in high-altitude solar powered aircraft more days |
| CN111767609A (en) * | 2020-05-22 | 2020-10-13 | 成都飞机工业（集团）有限责任公司 | Method for correcting climbing rate based on standard weight of test flight data |
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| CN103135556A (en) * | 2013-01-25 | 2013-06-05 | 北京航空航天大学 | Flight method for improving application performance of solar power unmanned aerial vehicle |
| CN103847970A (en) * | 2014-03-28 | 2014-06-11 | 北京理工大学 | Hybrid power unmanned aerial vehicle energy source control method based on power following |
| CN105398578A (en) * | 2015-11-12 | 2016-03-16 | 中国人民解放军国防科学技术大学 | Solar aircraft safety control method based on longitudinal flight path |
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2016
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Patent Citations (4)
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| CN102880185A (en) * | 2011-07-13 | 2013-01-16 | 波音公司 | Solar energy collection flight path management system for aircraft |
| CN103135556A (en) * | 2013-01-25 | 2013-06-05 | 北京航空航天大学 | Flight method for improving application performance of solar power unmanned aerial vehicle |
| CN103847970A (en) * | 2014-03-28 | 2014-06-11 | 北京理工大学 | Hybrid power unmanned aerial vehicle energy source control method based on power following |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106951650A (en) * | 2017-03-28 | 2017-07-14 | 南京信息工程大学 | Unmanned plane endurance assessment system |
| CN106951650B (en) * | 2017-03-28 | 2020-07-31 | 南京信息工程大学 | Unmanned aerial vehicle endurance evaluation system |
| CN107065927A (en) * | 2017-04-20 | 2017-08-18 | 杭州电子科技大学 | The quadrotor and control method of a kind of solar energy continuation of the journey |
| CN107065927B (en) * | 2017-04-20 | 2020-10-09 | 杭州电子科技大学 | Solar energy endurance four-rotor aircraft and control method |
| CN108820230A (en) * | 2018-05-31 | 2018-11-16 | 中国航天空气动力技术研究院 | A kind of energy management method of circulation flight in high-altitude solar powered aircraft more days |
| CN111767609A (en) * | 2020-05-22 | 2020-10-13 | 成都飞机工业（集团）有限责任公司 | Method for correcting climbing rate based on standard weight of test flight data |
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