CN108216679A - A kind of solar energy unmanned plane population parameter determines method and system - Google Patents
A kind of solar energy unmanned plane population parameter determines method and system Download PDFInfo
- Publication number
- CN108216679A CN108216679A CN201711431237.5A CN201711431237A CN108216679A CN 108216679 A CN108216679 A CN 108216679A CN 201711431237 A CN201711431237 A CN 201711431237A CN 108216679 A CN108216679 A CN 108216679A
- Authority
- CN
- China
- Prior art keywords
- unmanned plane
- weight
- power
- energy
- solar
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- 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
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
Landscapes
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Photovoltaic Devices (AREA)
- Electric Propulsion And Braking For Vehicles (AREA)
Abstract
A kind of solar energy unmanned plane population parameter determines method and system, solar energy unmanned plane is using solar radiation as unique energy source, energy acquisition, energy expenditure, energy storage involved in its flight course, and aircraft body, energy source and power, flight management intercouple, therefore cannot directly apply mechanically the design method and process of conventional airplane.This method is based on the weight balancing of solar energy the weakest point, power-balance and energy balance relations in flight profile, mission profile, calculating is iterated to major parameters such as weight characteristic and aerodynamic characteristics, it can obtain the tentative programme population parameter for meeting war skill index request, mainly include：Unmanned plane gross weight and subsystem weight, with reference to shape, lift resistance ratio, solar cell tile rate and power characteristic for being matched on each core component of total system etc..The present invention provides a kind of determining methods suitable for solar energy unmanned plane population parameter, can be applied to the preliminary collectivity Scheme Design of the type unmanned plane.
Description
Technical field
The present invention relates to a kind of solar energy unmanned plane population parameters to determine method and system, preliminary for the type unmanned plane
Collectivity Scheme Design belongs to unmanned plane overall design technique field.
Background technology
Solar energy unmanned plane is the Electric aircraft using solar radiation as the energy, is Aeronautics and new energy technology
The product being combined.Daytime, solar energy unmanned plane rely on the solar cell that body surface is laid with by the solar radiation of absorption
Energy is converted to electric energy, for maintaining dynamical system, avionic device and the normal operation of payload, and to secondary cell
It charges；Night, solar energy unmanned plane discharge the electric energy stored in secondary cell, maintain the normal operation of whole system.Too
The positive energy unmanned plane cruise time is long, flying height is high, overlay area is wide, use cost is low, environmentally safe, can perform logical
Believe the multiple-tasks such as relaying, electronic reconnaissance, mobile networking, be that the flights such as orbiter, unmanned plane powered by conventional energy, high altitude airship are put down
The important supplement of platform, by extensive concern both domestic and external.
At this stage, solar energy unmanned plane is due to the energy, the limitation of dynamical system technical merit, in task mission phase always
Maintain faint energy balance, so during solar energy unmanned plane population parameter is determined, need centered on energy into
Row synthetic conceptual design.In addition, solar energy unmanned plane aerodynamic characteristic, solar cell power density, secondary cell can compare again, daytime
Climb or master-plans such as height that night glides in key variables all close associations, fatefully affect population parameter
It chooses.Therefore, the design method of conventional airplane is not particularly suited for solar energy unmanned plane.
At present there are mainly three types of the design methods of solar energy unmanned plane：(1) J.W.Youngblood propose based on Winter Solstice
The design method of the energy equilibrium of day (sun light intensity is most weak in the day) this day；(2) drafting that S.A.Brandt is proposed
The design method of constraints graph；(3) the setting based on weight balancing and energy balance that the designer A.Noth of Sky-Sailor is proposed
Meter method.Three kinds of methods are designed just for cruising condition constant-level flight, do not consider to reduce aircraft using energy storage is climbed
Scale and weight, not reflecting its entire flight course completely, the result of design is often bigger than normal.
Invention content
The technology of the present invention solves the problems, such as：It is overall a kind of solar energy unmanned plane has been overcome the deficiencies of the prior art and provide
Parameter determination method and system.Realize the quick design of the main population parameter of solar energy unmanned plane, solve the type nobody
Routine Airplane design method does not apply to and discloses the problem of design method result is bigger than normal during machine master-plan.
The present invention technical solution be：A kind of solar energy unmanned plane population parameter determines method, and step is as follows：
(1) design driver of unmanned plane and design time point are determined；
(2) iterative initial value of unmanned plane is set, including unmanned plane Gross Weight Takeoff initial value m0With lift resistance ratio initial value K0；
(3) input parameter of the unmanned aerial vehicle design determined according to step (1), with reference to weight balancing, power-balance and energy
The relationship of balance calculates the weight of unmanned plane subsystem and Gross Weight Takeoff mtotal；
(4) the unmanned plane Gross Weight Takeoff m that step (3) obtains is calculatedtotalWith step (2) unmanned plane Gross Weight Takeoff initial value m0It
Between deviation, if the deviation meets the weight error threshold value of setting, enter step (5), otherwise return to step (2) and update nothing
Man-machine Gross Weight Takeoff initial value m0；
(5) meet the Gross Weight Takeoff m of error threshold according to step (4)total, constrained with reference to unmanned plane shape, calculate nobody
The formal parameter of machine, and determine the lift resistance ratio K of unmanned plane；
(6) the lift resistance ratio K and lift resistance ratio initial value K in step (2) iterative initial value obtained by step (5) is calculated0Between deviation,
If the deviation meets lift resistance ratio error threshold, completion determines solar energy unmanned plane population parameter, otherwise return to step (2)
And update lift resistance ratio initial value K0。
The design driver of unmanned plane and design time point, the design driver packet of unmanned plane are determined in step (1)
Include flight date, operating latitude, night flight height, load weight, load power, airborne equipment weight, airborne equipment power, design
Lift coefficient, the span, aspect ratio, photoelectric conversion efficiency of the solar battery, solar cell surface density, solar panel battle array loss effect
Rate, accumulator can compare again, propulsion system power to weight ratio, propulsion system efficiency, power-supply controller of electric power to weight ratio, power-supply controller of electric efficiency,
The design time point of unmanned plane is solar irradiation energy is most weak in the range of flight date and operating latitude one day.
The weight of unmanned plane subsystem and Gross Weight Takeoff m are calculated in the step (3)total, step is as follows：
(3.1) span in step (1) and aspect ratio calculate area of reference and housing construction weight；
(3.2) design lift coefficient in step (1), the unmanned plane Gross Weight Takeoff initial value m in step (2)0, step
(3.1) area of reference according to weight balancing relationship, calculates unmanned plane cruising speed；
(3.3) the unmanned plane Gross Weight Takeoff initial value m in step (2)0With lift resistance ratio initial value K0, ginseng in step (3.1)
The cruising speed in area, step (3.2) is examined, calculating unmanned plane climbs respectively pushes away needed for the flight of section, flat winged section and downslide section
Into power, according to power-balance relationship, UAV Propulsion System weight is calculated；
(3.4) to the required propeller power in the load power in step (1) and airborne equipment power, step (3.3) point
Not about time integral, the energy consumption of unmanned plane is obtained, according to energy balance relations, according to the solar cell photoelectricity in step (1)
Transfer efficiency, solar cell surface density, solar panel battle array loss efficiency calculation solar cell weight, according in step (1)
Accumulator can be again than calculating accumulator weight, power-supply controller of electric power to weight ratio, power-supply controller of electric efficiency calculation in step (1)
Power-supply controller of electric weight, according to cable weight in solar cell weight and battery weight computer；
(3.5) load weight in step (1) and airborne equipment weight, the construction weight in step (3.1), step
(3.3) the propulsion system weight in, the solar cell weight in step (3.4), battery weight, power-supply controller of electric weight and machine
Upper cable weight, determines Gross Weight Takeoff mtotal。
The constraint of unmanned plane shape includes wing taper ratio, fuselage length, fuselage maximum cross-section diameter, horizontal tail in step (5)
Tail capacity, vertical fin tail capacity, the horizontal tail arm of force, the vertical fin arm of force.
Suddenly the lift resistance ratio K of unmanned plane is determined in (5), step is as follows：
(5.1) formal parameter for calculating unmanned plane is constrained according to unmanned plane shape, including wing wing root chord length, wing wingtip
Chord length, mean aerodynamic chord, horizontal tail area, vertical fin area；
(5.2) the outer parameter of reference in the unmanned plane cruising speed in step (3) and Gross Weight Takeoff, step (5.2)
Number calculates the lift resistance ratio of unmanned plane.
The design point of unmanned plane is most weak for solar irradiation energy in the range of flight date and operating latitude in step (1) one
My god, the solar irradiation energy calculation step of unit area is as follows：
(a) sun vertical irradiation intensity：, the π (n-4)/365 of α in formula=2 is
Sun altitude, I=1367W/m2For solar constant, ε=0.017 is eccentricity of the earth, and n is the day ordinal number of flight date；
(b) solar irradiation intensity：In formulaFor declination angle, ω (t)=π-π t/12 are solar hour angle, and θ is geography
Latitude, at the time of t is in one day；
(c) solar irradiation energy：
Area of reference S=b in step (3.1)2/ AR, housing construction weight mfr=1.55S0.556AR0.651, b is in formula
The span, AR are aspect ratio, this formula is suitable for aspect ratio AR in the range of 15~30.
Unmanned plane cruising speed in step (3.2)G is acceleration of gravity in formula, and ρ is big
Air tightness, CLFor design lift coefficient.
Required propeller power is calculated respectively by section of climbing, flat winged section and downslide section in step (3.3)：
(a) climb required propeller power：In formulaFor the climb rate,
With height change, ηproFor propulsion system efficiency, the day for promoting that mean power is 2 times needed for the process of climbing can be approximately considered
Between cruise needed for propeller power；
(b) propeller power needed for cruising in the daytime：Ppro-cruise_day=mgV/K/ ηpro；
(c) propeller power needed for gliding：Ppro-slip=0, unpowered downslide is generally used to improve capacity usage ratio；
(d) propeller power needed for night cruise：Ppro-cruise-night=0.6mgV/K/ ηpro。
UAV Propulsion System weight m in step (3.3)pro=Ppro-climb/Kpro, K in formulaproFor propulsion system work(weight
Than.
To the required propulsion in the load power in step (1) and airborne equipment power, step (3.3) in step (3.4)
Power obtains the energy consumption of unmanned plane, step is as follows respectively about time integral：
(a) propulsion system consumes energy in the daytime：Epro_day=Ppro_cruise-dayt1+Ppro_cruiset2+Ppro-slipt3, promote
System night consumes energy：Epro_night=Ppro_cruise_nightt4, load consumes energy in the daytime：Epld_day=Ppld(t1+t2+
t3), load night consumption energy：Epld_night=Ppldt4, airborne equipment consumes energy in the daytime：Eav_day=Pav(t1+t2+t3),
Airborne equipment night consumes energy：Eav_night=Pavt4, P in formulapld、PavRespectively load power and airborne equipment power；
(b) accumulator output energy：Ebat=Epro_night+Epld_night+Eav_night；
(c) solar cell output energy：Esc=Ebat+Epro_day+Epld_day+Eav_day。
The weight of cable carries out as follows on accumulator, solar cell, power-supply controller of electric and machine in step (3.4)：
(a) battery weight：mbat=Ebat/Kbat, K in formulabatIt can compare again for accumulator；
(b) solar cell tile area：Ssc=Esc/(Esc0nscηcηmppt), n in formulascFor solar battery array photoelectric conversion
Efficiency, ηcEfficiency, η are lost for solar panel battle arraympptFor power-supply controller of electric efficiency；
(c) solar cell weight：msc=ρscSsc, ρ in formulascFor solar battery array surface density；
(d) power-supply controller of electric weight：mmppt=1280Sscnscηc/Kmppt, K in formulampptFor power-supply controller of electric power to weight ratio；
(e) cable weight on machine：mwire=0.08 (msc+mbat)。
Step (5.1) constrains the formal parameter for calculating unmanned plane according to unmanned plane shape, calculates as follows：
(a) wing wing root chord length：Cr=2S/ [b (1+ λ)], wing wingtip chord length：Ct=λ Cr, λ is taper ratio in formula；
(b) wing mean aerodynamic chord：
(c) horizontal tail area：C in formulaHTFor Horizontal Tail capacity, LHTFor the horizontal tail arm of force；
(d) vertical fin area：SVT=bSCVT/LVT, C in formulaVTFor vertical fin tail capacity, LVTFor the vertical fin arm of force.
A kind of solar energy unmanned plane population parameter determines system, including：Determining module, setup module, weight computing module,
Deviation judgment module, lift resistance ratio determining module, lift resistance ratio error threshold judgment module；
Determining module determines the design driver of unmanned plane and design time point；
Setup module sets the iterative initial value of unmanned plane, including unmanned plane Gross Weight Takeoff initial value m0With lift resistance ratio initial value K0；
Weight computing module, the input parameter of unmanned aerial vehicle design according to determined by determining module, with reference to weight balancing, work(
Rate balances and the relationship of energy balance, calculates the weight of unmanned plane subsystem and Gross Weight Takeoff mtotal；
Deviation judgment module, the unmanned plane Gross Weight Takeoff m that calculated weight computing module obtainstotalWith setup module setting
Unmanned plane Gross Weight Takeoff initial value m0Between deviation, if the deviation meet setting weight error threshold value, send true to lift resistance ratio
Cover half block, otherwise setup module update unmanned plane Gross Weight Takeoff initial value m0；
Lift resistance ratio determining module, according to the Gross Weight Takeoff m for meeting error thresholdtotal, constrain, calculate with reference to unmanned plane shape
The formal parameter of unmanned plane, and determine the lift resistance ratio K of unmanned plane；
Lift resistance ratio error threshold judgment module calculates the lift resistance ratio K obtained by lift resistance ratio determining module and is set with setup module
Iterative initial value in lift resistance ratio initial value K0Between deviation, if the deviation meets lift resistance ratio error threshold, complete to solar energy
Unmanned plane population parameter determines that otherwise setup module updates lift resistance ratio initial value K0。
Compared with the prior art, the invention has the advantages that：
(1) present invention has extracted a kind of population parameter suitable for solar energy unmanned plane and has determined method, can instruct to set
Meter personnel are more completed quickly and effectively the design of the preliminary overall plan of the type unmanned plane.
(2) the present invention is based on the design philosophys for energy storage of climbing, and the design profile of solar energy unmanned plane is divided into section of climbing, is patrolled
Segment and downslide section, with it is single select cruise section as design profile compared with, more meet the actual use of the type unmanned plane
Pattern, design result are more accurate.
(3) incorporation engineering experience of the present invention, establishes fine mathematical model, and many hypothesis phases are used with original technology
Than design result is more reasonable.
(4) it is suitable for the population parameter of other electric propulsion unmanned planes determines that the scope of application is wider.
(5) present invention realizes the quick design of the main population parameter of solar energy unmanned plane, solves the type unmanned plane
Routine Airplane design method does not apply to and discloses the problem of design method result is bigger than normal during master-plan.
(6) present invention by programmings such as MATLAB or C languages by that can be realized and carry out test.Under MATLAB environment
A large amount of tests are carried out, process rate of convergence is fast and divergence-free situation occurs, and final design result can pass through simulating, verifying.
Description of the drawings
Fig. 1 is solar energy unmanned plane flight diagrammatic cross-section；
Fig. 2 is this method flow chart.
Specific embodiment
The specific embodiment of the present invention is further described in detail below in conjunction with the accompanying drawings.
Solar energy unmanned plane population parameter includes unmanned plane weight characteristic parameter, geometric shape parameter, parameter of aerodynamic characteristics,
And it is matched to power characteristic parameter on each core component of total system etc..The design of these population parameters is by solar energy unmanned plane
The characteristic of itself determines：Its energy comes from solar radiation, and flight date, flying height, geographical location will all influence flying quality；
Acquisition, consumption and the storage of energy involved in its flight course, it is closely related with energy technology level, energy supply mode etc..
The coupled relation between clearly each system is combed in design process, establishes simple as possible but distortionless mathematical model.
The multidisciplinary coupled relation and multi-subject design model that the present invention incorporates experience into, provide a method, can be in conceptual design
Realize that the quick of the main population parameter of solar energy unmanned plane determines with the schematic design phase.
Solar energy unmanned plane mainly includes housing construction, energy resource system, propulsion system, TT＆C system, navigation system, flies control
The subsystems such as system and mission payload system.Wherein, energy resource system provides all energy during solar energy unmanned plane during flying,
Including four part of cable on solar cell, accumulator, energy management device and machine.Housing construction and energy resource system occupy solar energy
The weight of more than 80% unmanned plane, parameter directly determine the scale of unmanned plane, are that population parameter needs emphasis to close when determining
The object of note.The present invention is referred to as airborne equipment for convenience of stating, by TT＆C system, navigation system, flight control system merging.
The present invention is to determine population parameter, the typical case of solar energy unmanned plane based on the complete section face of solar energy unmanned plane during flying
Flight profile, mission profile is as shown in Figure 1, daylong flight mainly includes four-stage：(1) climb a section t1：Unmanned plane uses solar cell
Combine with accumulator and power, quickly climb；(2) cruise section t in the daytime2：It remains flat using solar cell after to predetermined altitude to fly, remain
Remaining solar cell energy charges to accumulator；(3) downslide section t3：With the decrease of solar irradiation, it is impossible to remain flat and fly rear nothing
Power is snapped down to night cruising altitude, and solar cell charges to accumulator during this；(4) night cruise section t4：In more night height
It is put down and flown to second day by storage battery power supply on degree.Since entire flight profile, mission profile is not the process of a stable state, when design, is respectively
System input parameter and ideal climb altitude, time-to-climb, unpowered coasting time, night, which put down the winged time, to be needed to consider
It determines.
As shown in Fig. 2, the present invention provides a kind of solar energy unmanned plane population parameters to determine method, step is as follows：
(1) design driver and design point of unmanned plane are determined；
(2) iterative initial value of unmanned plane is set, including unmanned plane Gross Weight Takeoff initial value m0With lift resistance ratio initial value K0；
(3) input parameter of the unmanned aerial vehicle design determined according to step (1), with reference to weight balancing, power-balance and energy
The relationship of balance calculates the weight of unmanned plane primary sub-system and Gross Weight Takeoff mtotal；
(4) the unmanned plane Gross Weight Takeoff m that step (3) obtains is calculatedtotalWith step (2) unmanned plane Gross Weight Takeoff initial value m0It
Between deviation, if the deviation meets the weight error threshold value of setting, enter step (5), otherwise return to step (2) and update nothing
Man-machine Gross Weight Takeoff initial value m0；
(5) meet the Gross Weight Takeoff m of error threshold according to step (4)total, constrained with reference to unmanned plane shape, calculate shape
Parameter, and determine the lift resistance ratio K of unmanned plane；
(6) the lift resistance ratio K and lift resistance ratio initial value K in step (2) iterative initial value obtained by step (5) is calculated0Between deviation,
If the deviation meets lift resistance ratio error threshold, completion determines solar energy unmanned plane population parameter, otherwise return to step (2)
And update lift resistance ratio initial value K0。
The design driver and design point of unmanned plane, the design driver packet of unmanned plane are determined in the step (1)
Include flight date, operating latitude, night flight height, load weight, load power, airborne equipment weight, airborne equipment power, design
Lift coefficient, the span, aspect ratio, photoelectric conversion efficiency of the solar battery, solar cell surface density, solar panel battle array loss effect
Rate, accumulator can compare again, propulsion system power to weight ratio, propulsion system efficiency, power-supply controller of electric power to weight ratio, power-supply controller of electric efficiency.
The design point of unmanned plane is most weak for solar irradiation energy in the range of flight date and operating latitude in the step (1)
One day, the solar irradiation energy calculation step of unit area is as follows：
(a) sun vertical irradiation intensity：, the π (n-4)/365 of α in formula=2 is
Sun altitude, I=1367W/m2For solar constant, ε=0.017 is eccentricity of the earth, and n is the day ordinal number of flight date；
(b) solar irradiation intensity：In formulaFor declination angle, ω (t)=π-π t/12 are solar hour angle, and θ is geography
Latitude, at the time of t is in one day；
(c) solar irradiation energy：
The Gross Weight Takeoff initial value m of setting unmanned plane in the step (2)0With lift resistance ratio initial value K0, need to combine step (1)
In load weight, load power, airborne equipment weight, airborne equipment power, the span, given according to engineering experience.
The weight of unmanned plane primary sub-system and Gross Weight Takeoff m are calculated in the step (3)total, step is as follows：
(3.1) span in step (1) and aspect ratio calculate area of reference and housing construction weight：
Area of reference：S=b2/ AR, housing construction weight：mfr=1.55S0.556AR0.651, b is the span in formula, and AR is exhibition
String ratio, housing construction weight formula suggestion are applicable in aspect ratio AR in 15~30 ranges；
(3.2) design lift coefficient in step (1), the unmanned plane Gross Weight Takeoff initial value m in step (2)0, step
(3.1) area of reference in, according to weight balancing relationship, i.e., the lift and Gross Weight Takeoff that unmanned plane shape generates under cruising condition
It is equal, calculate unmanned plane cruising speed：
Unmanned plane cruising speed：G is acceleration of gravity in formula, and ρ is atmospheric density, CLFor
Design lift coefficient；
(3.3) the unmanned plane Gross Weight Takeoff initial value m in step (2)0With lift resistance ratio initial value K0, ginseng in step (3.1)
The cruising speed in area, step (3.2) is examined, calculating unmanned plane climbs respectively pushes away needed for the flight of section, flat winged section and downslide section
Into power, according to power-balance relationship, i.e. propeller power needed for unmanned plane during flying and propulsion system output power is equal, calculates nothing
Man-machine propulsion system weight：
(a) climb required propeller power：In formulaFor the climb rate,
With height change, it can be approximately considered and propeller power needed for the cruise in the daytime that mean power is 2 times is promoted needed for the process of climbing；
(b) propeller power needed for cruising in the daytime：Ppro-cruise_day=mgV/K/ ηpro, η in formulaproFor propulsion system efficiency；
(c) propeller power needed for gliding：Ppro-slip=0, unpowered downslide is generally used to improve capacity usage ratio；
(d) propeller power needed for night cruise：Ppro-cruise-night=0.6mgV/K/ ηpro；
(e) UAV Propulsion System weight mpro=Ppro-climb/Kpro, K in formulaproFor propulsion system power to weight ratio.
(3.4) to the required propeller power in the load power in step (1) and airborne equipment power, step (3.3) point
Not about time integral, the energy consumption of unmanned plane is obtained, according to energy balance relations, i.e. energy resource system output energy disappears with unmanned plane
Energy consumption is equal, photoelectric conversion efficiency of the solar battery, solar cell surface density, solar panel battle array damage in step (1)
Crash rate calculates solar cell weight, and the accumulator in step (1) can be again than calculating accumulator weight, according to step (1)
In power-supply controller of electric power to weight ratio, power-supply controller of electric efficiency calculation power-supply controller of electric weight, according to solar cell weight and electric power storage
Cable weight on the weight computer of pond：
(a) propulsion system consumes energy in the daytime：Epro_day=Ppro_cruise-dayt1+Ppro_cruiset2+Ppro-slipt3, promote
System night consumes energy：Epro_night=Ppro_cruise_nightt4, load consumes energy in the daytime：Epld_day=Ppld(t1+t2+
t3), load night consumption energy：Epld_night=Ppldt4, airborne equipment consumes energy in the daytime：Eav_day=Pav(t1+t2+t3),
Airborne equipment night consumes energy：Eav_night=Pavt4, P in formulapld、PavRespectively load power and airborne equipment power；
(b) accumulator output energy：Ebat=Epro_night+Epld_night+Eav_night, battery weight：mbat=Ebat/
Kbat, K in formulabatIt can compare again for accumulator；
(c) solar cell output energy：Esc=Ebat+Epro_day+Epld_day+Eav_day, solar cell tile area：Ssc
=Esc/(Esc0nscηcηmppt), n in formulascFor solar battery array electricity conversion, ηcEfficiency is lost for solar panel battle array,
ηmpptFor power-supply controller of electric efficiency；
(d) solar cell weight：msc=ρscSsc, ρ in formulascFor solar battery array surface density；
(e) power-supply controller of electric weight：mmppt=1280Sscnscηc/Kmppt, K in formulampptFor power-supply controller of electric power to weight ratio；
(f) cable weight on machine：mwire=0.08 (msc+mbat)。
(3.5) load weight in step (1) and airborne equipment weight, the construction weight in step (3.1), step
(3.3) the propulsion system weight in, the solar cell weight in step (3.4), battery weight, power-supply controller of electric weight and machine
Upper cable weight, determines Gross Weight Takeoff mtotal：
Gross Weight Takeoff：mtotal=mfr+mbat+msc+mwire+mmppt+mpro+mpld+mav
Weight error threshold value suggestion in the step (4) is taken as 0.1%, i.e., | mtotal-m0|/m0≤ 0.1%.
Return to step (2) and unmanned plane Gross Weight Takeoff initial value m is updated in the step (4)0, it is proposed that in return to step (2)
Assignment m0=mtotal, convergence rate can be improved.
In the step (5) unmanned plane shape constraint include wing taper ratio, fuselage length, fuselage maximum cross-section diameter,
Horizontal Tail capacity, vertical fin tail capacity, the horizontal tail arm of force, the vertical fin arm of force, the step of determining unmanned plane lift resistance ratio K, are as follows：
(5.1) formal parameter for calculating unmanned plane is constrained according to unmanned plane shape, including wing wing root chord length, wing wingtip
Chord length, mean aerodynamic chord, horizontal tail area, vertical fin area, calculate as follows：
(a) wing wing root chord length：Cr=2S/ [b (1+ λ)], wing wingtip chord length：Ct=λ Cr, λ is taper ratio in formula；
(b) wing mean aerodynamic chord：
(c) horizontal tail area：C in formulaHTFor Horizontal Tail capacity, LHTFor the horizontal tail arm of force；
(d) vertical fin area：SVT=bSCVT/LVT, C in formulaVTFor vertical fin tail capacity, LVTFor the vertical fin arm of force.
(5.2) the outer parameter of reference in the unmanned plane cruising speed in step (3) and Gross Weight Takeoff, step (5.2)
Number, calculates the lift resistance ratio of unmanned plane, and the circular of lift resistance ratio refers to《Airplane design handbook -6th copy：Pneumatic design》
In chapter 6 and chapter 7 content.
Lift resistance ratio error threshold suggestion in the step (6) is taken as 1%, i.e., | K-K0|/K0≤ 1%.
Return to step (2) and lift resistance ratio initial value K is updated in the step (6)0, it is proposed that assignment K in return to step (2)0=K,
Convergence rate can be improved.
The course of work further illustrated the present invention below with a specific example：
Certain solar energy unmanned plane more than 10km between spring and autumn point on the south 40 ° of north latitude highly carries 20kg＆500W load and holds
Row task, it is contemplated that airborne equipment weight 30kg, power 500W, design lift coefficient 1.0, the span 60, aspect ratio 25 can be applied
Photoelectric conversion efficiency of the solar battery be 30%, surface density 0.6kg/m2, group battle array loss efficiency 95%, accumulator can compare again
400Wh/kg, propulsion system power to weight ratio 400W/kg, power-supply controller of electric power to weight ratio 1500W/kg, efficiency 95%.According to above-mentioned design
Input parameter, it is desirable that determine the population parameters such as weight and the shape of solar energy unmanned plane.
It is design point to select solar irradiation is most weak in task scope one day (40 ° of north latitude, September 22 days), sets unmanned plane
Gross Weight Takeoff initial value m0=600kg and lift resistance ratio initial value K0=25；Determine that night cruising altitude is 12km, cruising altitude is in the daytime
20km calculates the solar irradiation energy of design point whole day unit area；Area of reference is calculated, computer body construction weight calculates
Unmanned plane cruising speed under 20km height, respectively calculate climb, in the daytime cruise, glide, night cruise needed for propeller power；Successively
Cable weight on calculating propulsion system, accumulator, solar cell, power-supply controller of electric and machine, acquires unmanned plane gross weight；Pass through iteration
Acquire the Gross Weight Takeoff m for meeting weight error threshold valuetotal=550kg.
Wing taper ratio 0.5, fuselage length 15m, fuselage maximum cross-section diameter 0.5m are constrained according to the shape of unmanned plane2、
Horizontal Tail capacity 0.5, vertical fin tail capacity 0.01, horizontal tail arm of force 15m, vertical fin arm of force 14m calculate unmanned plane and refer to formal parameter；
Estimate the lift resistance ratio of unmanned plane；The lift resistance ratio K=28 for meeting lift resistance ratio error threshold is acquired by iteration.
Finally determining unmanned aerial vehicle design parameter is as follows：
Table 1
| Design parameter | Numerical value |
| Gross Weight Takeoff | 550kg |
| Lift resistance ratio | 28 |
| Solar cell tile rate | 60% |
| Area of reference | 144m2 |
| Wing root chord length | 1.6m |
| Wingtip chord length | 0.8m |
| Horizontal tail area | 6.0m2 |
| Vertical fin area | 6.2m2 |
| Construction weight | 200kg |
| Solar cell weight | 52kg |
| Battery weight | 168kg |
| Energy management device management | 21kg |
| Cable weight on machine | 17kg |
| Propulsion system weight | 43kg |
| Airborne equipment weight | 30kg |
| Load weight | 20kg |
If carrying out design just for surely high cruising condition, determining unmanned plane Gross Weight Takeoff is 582kg, lift resistance ratio is
29.5, design result is big compared with design result of the invention, and the difficulty realized in engineering is also big.
The present invention by programmings such as MATLAB or C languages by that can be realized and carry out test.Under MATLAB environment into
A large amount of tests are gone, process rate of convergence is fast and divergence-free situation occurs, and final design result can pass through simulating, verifying.
The content not being described in detail in description of the invention belongs to the known technology of professional and technical personnel in the field.
Claims (14)
1. a kind of solar energy unmanned plane population parameter determines method, it is characterised in that step is as follows：
(1) design driver of unmanned plane and design time point are determined；
(2) iterative initial value of unmanned plane is set, including unmanned plane Gross Weight Takeoff initial value m0With lift resistance ratio initial value K0；
(3) input parameter of the unmanned aerial vehicle design determined according to step (1), with reference to weight balancing, power-balance and energy balance
Relationship, calculate the weight of unmanned plane subsystem and Gross Weight Takeoff mtotal；
(4) the unmanned plane Gross Weight Takeoff m that step (3) obtains is calculatedtotalWith step (2) unmanned plane Gross Weight Takeoff initial value m0Between
Deviation, if the deviation meets the weight error threshold value of setting, enters step (5), otherwise return to step (2) and updates unmanned plane
Gross Weight Takeoff initial value m0；
(5) meet the Gross Weight Takeoff m of error threshold according to step (4)total, constrained with reference to unmanned plane shape, calculate unmanned plane
Formal parameter, and determine the lift resistance ratio K of unmanned plane；
(6) the lift resistance ratio K and lift resistance ratio initial value K in step (2) iterative initial value obtained by step (5) is calculated0Between deviation, if should
Deviation meets lift resistance ratio error threshold, then completes to determine solar energy unmanned plane population parameter, otherwise return to step (2) and more
New lift resistance ratio initial value K0。
2. a kind of solar energy unmanned plane population parameter according to claim 1 determines method, it is characterised in that：The step
(1) design driver of unmanned plane and design time point are determined in, the design driver of unmanned plane includes flight date, flies
Row latitude, night flight height, load weight, load power, airborne equipment weight, airborne equipment power, design lift coefficient, the wing
Exhibition, aspect ratio, photoelectric conversion efficiency of the solar battery, solar cell surface density, solar panel battle array loss efficiency, accumulator can weigh
Than, propulsion system power to weight ratio, propulsion system efficiency, power-supply controller of electric power to weight ratio, power-supply controller of electric efficiency, during the design of unmanned plane
Between one day most weak for solar irradiation energy in the range of flight date and operating latitude of point.
3. a kind of solar energy unmanned plane population parameter according to claim 1 determines method, it is characterised in that：The step
(3) weight of unmanned plane subsystem and Gross Weight Takeoff m are calculated intotal, step is as follows：
(3.1) span in step (1) and aspect ratio calculate area of reference and housing construction weight；
(3.2) design lift coefficient in step (1), the unmanned plane Gross Weight Takeoff initial value m in step (2)0, step (3.1)
In area of reference, according to weight balancing relationship, calculate unmanned plane cruising speed；
(3.3) the unmanned plane Gross Weight Takeoff initial value m in step (2)0With lift resistance ratio initial value K0, the plane of reference in step (3.1)
Product, the cruising speed in step (3.2), calculate unmanned plane and climb and promote work(needed for the flight of section, flat winged section and downslide section respectively
Rate according to power-balance relationship, calculates UAV Propulsion System weight；
(3.4) the required propeller power in the load power in step (1) and airborne equipment power, step (3.3) is closed respectively
In time integral, the energy consumption of unmanned plane is obtained, according to energy balance relations, according to the solar cell opto-electronic conversion in step (1)
Efficiency, solar cell surface density, solar panel battle array loss efficiency calculation solar cell weight, according to the electric power storage in step (1)
Chi Nengchong is than calculating accumulator weight, power-supply controller of electric power to weight ratio, power-supply controller of electric efficiency calculation power supply in step (1)
Controller weight, according to cable weight in solar cell weight and battery weight computer；
(3.5) load weight in step (1) and airborne equipment weight, the construction weight in step (3.1), step
(3.3) the propulsion system weight in, the solar cell weight in step (3.4), battery weight, power-supply controller of electric weight and machine
Upper cable weight, determines Gross Weight Takeoff mtotal。
4. a kind of solar energy unmanned plane population parameter according to claim 1 determines method, it is characterised in that：The step
(5) constraint of unmanned plane shape includes wing taper ratio, fuselage length, fuselage maximum cross-section diameter, Horizontal Tail capacity, vertical fin tail in
Capacity, the horizontal tail arm of force, the vertical fin arm of force.
5. a kind of solar energy unmanned plane population parameter according to claim 1 determines method, it is characterised in that：The step
(5) the lift resistance ratio K of unmanned plane is determined in, step is as follows：
(5.1) formal parameter for calculating unmanned plane is constrained according to unmanned plane shape, including wing wing root chord length, wing wing tip chord
Length, mean aerodynamic chord, horizontal tail area, vertical fin area；
(5.2) the reference formal parameter in the unmanned plane cruising speed in step (3) and Gross Weight Takeoff, step (5.2), meter
Calculate the lift resistance ratio of unmanned plane.
6. a kind of solar energy unmanned plane population parameter according to claim 2 determines method, it is characterised in that：The step
(1) design point of unmanned plane is most weak for solar irradiation energy in the range of flight date and operating latitude in one day, unit area
Solar irradiation energy calculation step it is as follows：
(a) sun vertical irradiation intensity：I0=I [(1+ ε cos α)/(1- ε2)]2, the π (n-4)/365 of α in formula=2 is altitude of the sun
Angle, I=1367W/m2For solar constant, ε=0.017 is eccentricity of the earth, and n is the day ordinal number of flight date；
(b) solar irradiation intensity：In formulaFor declination angle, ω (t)=π-π t/12 are solar hour angle, and θ is geography
Latitude, at the time of t is in one day；
(c) solar irradiation energy：
7. a kind of solar energy unmanned plane population parameter according to claim 3 determines method, it is characterised in that：The step
(3.1) the area of reference S=b in2/ AR, housing construction weight mfr=1.55S0.556AR0.651, b is the span in formula, and AR is exhibition string
Than this formula is suitable for aspect ratio AR in the range of 15~30.
8. a kind of solar energy unmanned plane population parameter according to claim 3 determines method, it is characterised in that：The step
(3.2) unmanned plane cruising speed inG is acceleration of gravity in formula, and ρ is atmospheric density, CLTo set
Count lift coefficient.
9. a kind of solar energy unmanned plane population parameter according to claim 3 determines method, it is characterised in that：The step
(3.3) required propeller power is calculated respectively by section of climbing, flat winged section and downslide section in：
(a) climb required propeller power：In formulaFor the climb rate, with height
Degree variation, ηproFor propulsion system efficiency, it can be approximately considered and mean power be promoted to be 2 times needed for the process of climbing patrol in the daytime
Propeller power needed for boat；
(b) propeller power needed for cruising in the daytime：Ppro_cruise_day=mgV/K/ ηpro；
(c) propeller power needed for gliding：Ppro_slip=0, unpowered downslide is generally used to improve capacity usage ratio；
(d) propeller power needed for night cruise：Ppro_cruise_night=0.6mgV/K/ ηpro。
10. a kind of solar energy unmanned plane population parameter according to claim 3 determines method, it is characterised in that：The step
Suddenly UAV Propulsion System weight m in (3.3)pro=Ppro_climb/Kpro, K in formulaproFor propulsion system power to weight ratio.
11. a kind of solar energy unmanned plane population parameter according to claim 3 determines method, it is characterised in that：The step
Suddenly the required propeller power in the load power in step (1) and airborne equipment power, step (3.3) is closed respectively in (3.4)
In time integral, the energy consumption of unmanned plane is obtained, step is as follows：
(a) propulsion system consumes energy in the daytime：Epro_day=Ppro_cruise_dayt1+Ppro_cruiset2+Ppro_slipt3, propulsion system
Night consumes energy：Epro_night=Ppro_cruise_nightt4, load consumes energy in the daytime：Epld_day=Ppld(t1+t2+t3), it carries
Lotus night consumes energy：Epld_night=Ppldt4, airborne equipment consumes energy in the daytime：Eav_day=Pav(t1+t2+t3), it is airborne to set
Standby night consumes energy：Eav_night=Pavt4, P in formulapld、PavRespectively load power and airborne equipment power；
(b) accumulator output energy：Ebat=Epro_night+Epld_night+Eav_night；
(c) solar cell output energy：Esc=Ebat+Epro_day+Epld_day+Eav_day。
12. a kind of solar energy unmanned plane population parameter according to claim 3 determines method, it is characterised in that：The step
Suddenly the weight of cable carries out as follows on accumulator, solar cell, power-supply controller of electric and machine in (3.4)：
(a) battery weight：mbat=Ebat/Kbat, K in formulabatIt can compare again for accumulator；
(b) solar cell tile area：Ssc=Esc/(Esc0nscηcηmppt), n in formulascFor solar battery array electricity conversion,
ηcEfficiency, η are lost for solar panel battle arraympptFor power-supply controller of electric efficiency；
(c) solar cell weight：msc=ρscSsc, ρ in formulascFor solar battery array surface density；
(d) power-supply controller of electric weight：mmppt=1280Sscnscηc/Kmppt, K in formulampptFor power-supply controller of electric power to weight ratio；
(e) cable weight on machine：mwire=0.08 (msc+mbat)。
13. a kind of solar energy unmanned plane population parameter according to claim 5 determines method, it is characterised in that：The step
Suddenly (5.1) constrain the formal parameter for calculating unmanned plane according to unmanned plane shape, calculate as follows：
(a) wing wing root chord length：Cr=2S/ [b (1+ λ)], wing wingtip chord length：Ct=λ Cr, λ is taper ratio in formula；
(b) wing mean aerodynamic chord：
(c) horizontal tail area：C in formulaHTFor Horizontal Tail capacity, LHTFor the horizontal tail arm of force；
(d) vertical fin area：SVT=bSCVT/LVT, C in formulaVTFor vertical fin tail capacity, LVTFor the vertical fin arm of force.
14. a kind of solar energy unmanned plane population parameter determines system, it is characterised in that including：Determining module, setup module, weight
Computing module, deviation judgment module, lift resistance ratio determining module, lift resistance ratio error threshold judgment module；
Determining module determines the design driver of unmanned plane and design time point；
Setup module sets the iterative initial value of unmanned plane, including unmanned plane Gross Weight Takeoff initial value m0With lift resistance ratio initial value K0；
Weight computing module, the input parameter of unmanned aerial vehicle design according to determined by determining module, puts down with reference to weight balancing, power
The relationship of weighing apparatus and energy balance calculates the weight of unmanned plane subsystem and Gross Weight Takeoff mtotal；
Deviation judgment module, the unmanned plane Gross Weight Takeoff m that calculated weight computing module obtainstotalWith setup module setting nobody
Machine Gross Weight Takeoff initial value m0Between deviation, if the deviation meet setting weight error threshold value, send to lift resistance ratio and determine mould
Block, otherwise setup module update unmanned plane Gross Weight Takeoff initial value m0；
Lift resistance ratio determining module, according to the Gross Weight Takeoff m for meeting error thresholdtotal, constrained with reference to unmanned plane shape, calculate nobody
The formal parameter of machine, and determine the lift resistance ratio K of unmanned plane；
Lift resistance ratio error threshold judgment module calculates the lift resistance ratio K obtained by lift resistance ratio determining module and changes with what setup module was set
For lift resistance ratio initial value K in initial value0Between deviation, if the deviation meets lift resistance ratio error threshold, complete to solar energy nobody
Machine population parameter determines that otherwise setup module updates lift resistance ratio initial value K0。
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711431237.5A CN108216679B (en) | 2017-12-26 | 2017-12-26 | Solar unmanned aerial vehicle overall parameter determination method and system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711431237.5A CN108216679B (en) | 2017-12-26 | 2017-12-26 | Solar unmanned aerial vehicle overall parameter determination method and system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108216679A true CN108216679A (en) | 2018-06-29 |
| CN108216679B CN108216679B (en) | 2020-03-24 |
Family
ID=62648325
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711431237.5A Active CN108216679B (en) | 2017-12-26 | 2017-12-26 | Solar unmanned aerial vehicle overall parameter determination method and system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108216679B (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109631933A (en) * | 2018-12-20 | 2019-04-16 | 北京航空航天大学 | A kind of net energy distribution map for solar powered aircraft continuation of the journey assessment |
| CN110816879A (en) * | 2019-10-28 | 2020-02-21 | 西北工业大学 | Comprehensive energy detection system based on solar unmanned aerial vehicle |
| CN111498122A (en) * | 2020-04-24 | 2020-08-07 | 成都飞机工业（集团）有限责任公司 | Control method for electric power consumption of unmanned aerial vehicle |
| CN112591133A (en) * | 2020-12-24 | 2021-04-02 | 中国航空工业集团公司西安飞机设计研究所 | Design method for overall parameters of solar unmanned aerial vehicle flying day and night |
| CN113753256A (en) * | 2021-09-19 | 2021-12-07 | 中国航空工业集团公司西安飞机设计研究所 | Optimization design method for parameters of shipborne unmanned early warning machine top layer |
| CN114491958A (en) * | 2021-12-28 | 2022-05-13 | 中国航天空气动力技术研究院 | Method for determining flight profile of solar unmanned aerial vehicle in near space long endurance |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20140103158A1 (en) * | 2012-10-12 | 2014-04-17 | Benjamin Lawrence Berry | AirShip Endurance VTOL UAV and Solar Turbine Clean Tech Propulsion |
| CN105398561A (en) * | 2015-11-12 | 2016-03-16 | 中国人民解放军国防科学技术大学 | Solar aircraft |
| CN106143909A (en) * | 2016-07-15 | 2016-11-23 | 北京航空航天大学 | A kind of modularized combination type solar energy unmanned aerial vehicle design scheme |
| CN106516074A (en) * | 2016-10-24 | 2017-03-22 | 北京航空航天大学 | Deformable lift and buoyancy integrated aircraft aerodynamic configuration |
| RU2016117486A (en) * | 2016-05-04 | 2017-11-10 | Федеральное государственное казенное военное образовательное учреждение высшего образования "Военный учебно-научный центр Военно-воздушных сил "Военно-воздушная академия имени профессора Н.Е. Жуковского и Ю.А. Гагарина" (г. Воронеж) Министерства обороны Российской Федерации | Method for remote determination of spatial distribution of thermophysical parameters of the earth's surface |
| CN107368090A (en) * | 2017-08-01 | 2017-11-21 | 北京航空航天大学 | A kind of fixed-wing solar energy unmanned plane endurance method of estimation |
-
2017
- 2017-12-26 CN CN201711431237.5A patent/CN108216679B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20140103158A1 (en) * | 2012-10-12 | 2014-04-17 | Benjamin Lawrence Berry | AirShip Endurance VTOL UAV and Solar Turbine Clean Tech Propulsion |
| CN105398561A (en) * | 2015-11-12 | 2016-03-16 | 中国人民解放军国防科学技术大学 | Solar aircraft |
| RU2016117486A (en) * | 2016-05-04 | 2017-11-10 | Федеральное государственное казенное военное образовательное учреждение высшего образования "Военный учебно-научный центр Военно-воздушных сил "Военно-воздушная академия имени профессора Н.Е. Жуковского и Ю.А. Гагарина" (г. Воронеж) Министерства обороны Российской Федерации | Method for remote determination of spatial distribution of thermophysical parameters of the earth's surface |
| CN106143909A (en) * | 2016-07-15 | 2016-11-23 | 北京航空航天大学 | A kind of modularized combination type solar energy unmanned aerial vehicle design scheme |
| CN106516074A (en) * | 2016-10-24 | 2017-03-22 | 北京航空航天大学 | Deformable lift and buoyancy integrated aircraft aerodynamic configuration |
| CN107368090A (en) * | 2017-08-01 | 2017-11-21 | 北京航空航天大学 | A kind of fixed-wing solar energy unmanned plane endurance method of estimation |
Non-Patent Citations (1)
| Title |
|---|
| 张芳: "特种太阳能飞机总体参数设计方法研究", 《科学技术与工程》 * |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109631933A (en) * | 2018-12-20 | 2019-04-16 | 北京航空航天大学 | A kind of net energy distribution map for solar powered aircraft continuation of the journey assessment |
| CN110816879A (en) * | 2019-10-28 | 2020-02-21 | 西北工业大学 | Comprehensive energy detection system based on solar unmanned aerial vehicle |
| CN110816879B (en) * | 2019-10-28 | 2022-09-06 | 西北工业大学 | Comprehensive energy detection system based on solar unmanned aerial vehicle |
| CN111498122A (en) * | 2020-04-24 | 2020-08-07 | 成都飞机工业（集团）有限责任公司 | Control method for electric power consumption of unmanned aerial vehicle |
| CN112591133A (en) * | 2020-12-24 | 2021-04-02 | 中国航空工业集团公司西安飞机设计研究所 | Design method for overall parameters of solar unmanned aerial vehicle flying day and night |
| CN112591133B (en) * | 2020-12-24 | 2023-03-14 | 中国航空工业集团公司西安飞机设计研究所 | Design method for overall parameters of solar unmanned aerial vehicle flying day and night |
| CN113753256A (en) * | 2021-09-19 | 2021-12-07 | 中国航空工业集团公司西安飞机设计研究所 | Optimization design method for parameters of shipborne unmanned early warning machine top layer |
| CN113753256B (en) * | 2021-09-19 | 2023-04-18 | 中国航空工业集团公司西安飞机设计研究所 | Optimization design method for parameters of shipborne unmanned early warning machine top layer |
| CN114491958A (en) * | 2021-12-28 | 2022-05-13 | 中国航天空气动力技术研究院 | Method for determining flight profile of solar unmanned aerial vehicle in near space long endurance |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108216679B (en) | 2020-03-24 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108216679A (en) | A kind of solar energy unmanned plane population parameter determines method and system | |
| Lee et al. | Optimal path planning of solar-powered UAV using gravitational potential energy | |
| Gao et al. | Energy management strategy for solar-powered high-altitude long-endurance aircraft | |
| Panagiotou et al. | Conceptual design of a hybrid solar MALE UAV | |
| Shaoqi et al. | Flight strategy optimization for high-altitude long-endurance solar-powered aircraft based on Gauss pseudo-spectral method | |
| Klesh et al. | Energy-optimal path planning for solar-powered aircraft in level flight | |
| CN107745819A (en) | A kind of fixed-wing solar powered aircraft | |
| CN112060983B (en) | New energy unmanned aerial vehicle hybrid power supply architecture assessment method | |
| CN105279290A (en) | Four-engine propeller airplane endurance performance calculating method | |
| Guo et al. | Development of a solar electric powered UAV for long endurance flight | |
| CN107368090B (en) | Fixed-wing solar unmanned aerial vehicle time-of-flight estimation method | |
| Mateja et al. | Towards energetic autonomy of UAV | |
| Clarke et al. | Evaluating the Performance and Acoustic Footprint of Aircraft for Regional and Urban Air Mobility | |
| Orefice et al. | Performance calculation for hybrid-electric aircraft integrating aero-propulsive interactions | |
| Meng et al. | Energy management strategy of hybrid energy system for a multi-lobes hybrid air vehicle | |
| He et al. | Optimization and analysis of hybrid electric system for distributed propulsion tilt-wing UAV | |
| Huang et al. | Energy-optimal path planning for solar-powered UAVs monitoring stationary target | |
| Chen et al. | Comprehensive optimization of the unmanned tilt-wing cargo aircraft with distributed propulsors | |
| Koning et al. | Mid-Fidelity Computational Fluid Dynamics Analysis of the Elytron 4S UAV Concept | |
| Sukhov et al. | Analysis of mass-energy balance of unmanned aircraft fueled by solar energy | |
| Zhang et al. | Overall design and sensitivity analysis of solar aircraft based on feasible region planning method | |
| Dinca et al. | Solar UAVs—More Aerodynamic Efficiency or More Electrical Power? Energies 2023, 16, 3778 | |
| Koster | Hyperion-three years of novel aircraft design | |
| Hong et al. | Taiwan solar-powered UAV flight endurance record | |
| Bughman | Modeling and Testing Powerplant Subsystems of a Solar UAS |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |