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electrical Plane (ePlane)

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electrical pLane

Software tools for electrical aircraft design

The models are enabling issue identification much sooner in the process and significantly reduces the time required for each iterative cycle.
The use of quickly modelling is providing a greater depth of knowledge at any point in the pre-design project lifecycle
With "ePlane" can investigate new concepts of energy systems for future electrical aircrafts.

Lane (plattform 2.xxx)

The program "ePlane" includes a variety variants of e-planes, electrical engines, aerodynamics and flight paths. The development of flight dynamics models is a key aspect of the electrical aircraft design process. The basic modeling core "Lane" is to construct e-aircraft models around a dynamics motion equations of a flight vehicles. Particular attention is given to mathematical models and techniques for analysis of aircrafts.

Product Description

The software enables aircraft specialists from all disciplines to work in a collaborative environment on a quickly modeling and simulation solution. The research and modelling components are based on mathematical models and techniques for analysis, simulation, and evaluation of flying qualities. The quickly modeling help to reduce mistakes and the need for rework and significantly reduces the time required for pre-design cycle.
The ePlane program allows users (students, scientist, aircraft modelers, preliminary design engineers) to investigate an aircraft configuration

Program ePLane 2.xxx (platform 2.xxx):

  • calculates the complete range of performance parameters over a user-specified range of ballistic and aerodynamic variables;

  • friendly report generation;

  • is designed for simplicity and flexibility in its use;

  • provides the user with useful quick-look (evaluate) functions for the examination of a wide variety of data (e.g. thrust, fuel flow, lift, drag, etc.). Lane provides a powerful framework to support the iterative and non-unique process of unconventional aircraft pre-design (electrical airplanes, railgunes etc.
 

electrical aircraft
pre-design
e-plane ballistics calculation program
flight dynamic
 aerothermodynamic
e-aircraft flightflight simulation of objects in atmosphereePLANE program to calculate trajectories
Trajectory Design
Computational
Electric Propulsion Missions
aircraft flight dynamics

 

 

 

 

  

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

     

Report Example

NOMENCLATURE

Subscripts

bat   Battery
f       Flight
o       Start
e       End

Symbols

a        Speed of sound
AR      Aspect ratio
Cd      Total drag coefficient
Cdo    Parasite drag coefficient
Cdi     Induced drag coefficient
Cl       Lift Coefficient
D        Drag force
dt      Integration step
E        Energy
Ek      Kinetic energy
Ep      Potential energy
e        Oswald’s efficiency factor;  Lift-to-Drag ratio
F        Force
f         Friction coefficient
g        Acceleration due to gravity
H        Height, flight level, operating altitude
L         Lift force, Takeoff field length
Lw      Wing loading
M        Mach number
m        Weight
n         Load factor
P         Power; Pressure
q         Dynamic pressure; Heat flow
R         Range
Re       Reynolds number
r          Radius
S         Wing area
T         Thrust; Temperature
t          Time
x         Horizontal distance
V         Flight speed; Volume

α        Angle of attack
ε         Aerodynamic Efficiency
γ         Flight path angle
η         Energy efficiency
ρ         Density

Acronyms and Abbreviations

AIAA    The American Institute of Aeronautics and Astronautics
FAR      Federal Aviation Regulations
FL         Flight Level
FC        Fuel Cell
HAP      High Altitude Platform
HTA      Heavier Than Air
ICAO    International Civil Aviation Organization
ISA       International Standard Atmosphere
JAR      Joint Airworthiness Regulations
LTA       Lighter Than Air
MTOW  Maximum Takeoff Weight
PI          Performance index
TOFL    Takeoff Field Length
SFC      Specific Fuel Consumption
UAV      Unmanned Aerial Vehicle

Mission profile

Initial Conditions

Weight, m0,(MTOW), kg = 50900
Area (S), m2 = 106,1
Angle (γo), grad = 8
Height (Ho), m = 1
Velocity (Vo), m/s = 1
Flight Speed (Vf), m/s = 134,7
Flight Altitude (Hf), m = 3000
Integration Step, s = 0,01

Aerodynamic Characteristics

ε = Cl / Cd (max)  = 32
Start
Cl (max) = 1,6
Cdo = 0,016
deltaCd = 0
Aspect Ratio (wing), AR = 14,1
Oswald"s efficiency factor = 0,88
γ, deg = 8

Flight
Cl (max) = 1,3
Cdo = 0,00996
deltaCd = 0
Aspect Ratio (wing), AR = 14,1
Oswald"s efficiency factor = 0,933

Landing
Cl (max) = 3
Cdo = 0,06
deltaCd = 0
Aspect Ratio (wing), AR = 14,1
Oswald"s efficiency factor = 0,83
γ, deg = -3

Aerodynamic polars Cl=f(Cd)

Results of calculation

Range, m
Endurance, s 
Wing Loading, kg/m2

Start
Speed at take-off, Vs, m/s
Speed at take-off (+20%), m/s
Rolling friction coefficient, f
Take-off Field Length (TOFL), xs, m
Time to climb, ta,

Flight
Thrust (F), N
Velocity (Vo), m/s

Landing
Airplane descent, xd, m
Glide angle γ (εmax),
Minimum speed, Vlmin, m/s
Minimum speed*1,3, m/s
Rolling friction coefficient,
Landing Field Length (LFL), xl,

Propulsion system
Thrust (max) (F), N
Thrust / MTOW
Specific energy , (E), Wh/kg
Energy efficiency (System), η
Battery weight, mbat, kg
Battery weight (mbat/m0), % 

 

 

 
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