Institute of Flight Systems

Recent Activities

102 ACGSC Committee Meeting

17 October 2008, Niagara Falls, New York

Oliver Brieger, German Aerospace Center (DLR)

[email protected]

Institute of Flight SystemsInstitute of Flight Systems

ACGSC Meeting, October 17, 2008, Slide 2

Member of Hermann von Helmholtz-Association of National Research Centers (HGF)

DLR is Germany’s aerospace research center and space agency


DLR

performs basic research

develops novel technologies

builds and operates large-scale test facilities

assumes management tasks

trains junior scientists


Sites

31 research institutes and

scientific/technical

facilities at

8 sites

4 branches

German-Dutch

Wind Tunnels (DNW)

European Transonic

Wind Tunnel (ETW)

German Armed Forces

Flight Test Center

ManchingManching


Institute of Flight Systems

Flight Mechanics & Flight Dynamics,

SysID and Modelling

Flight Sciences

Dynamic Interaction between Human

Operator and Machine

Cognectics

Control Technology and Application,

Advanced Autonomy

Guidance & Control

System Integration of S.-Critical Systems,

Systems Engineering

Systems & Flight Safety

Technology Validation by Experiment

DLRReportDLR

Report

Theory Ground Experiment Flight Test & Research

DLRReportDLR

Report


Flying Testbeds

Full access to experimental systems and equipment -> in house design

EC 135 - FHS VFW 614 ATTAS ARTIS-Family (Micro,Midi, Maxi)

Bo-105

USTOL /MIL Demo ?

(in acquisition)A 320 Advanced Technology Research Aircraft - ATRA


Aircraft Wake Vortex & Atmospheric Turbulences: Modelling, Interaction and Control

1. Theory2. Messurement3. Modelling4. Solutions5. Verification6. Application


A400M Low Level Flight Functions with ATTAS

Inflight Simuation and Demonstration of Advanced Low Level Flight Functions forLarge Transport Aircraft


Active Control Technology – Improved Mission Effectiveness (ACT-IME) with EC 135 FHS

• Successful Demonstration of new EC-F functions• New active Sidestick concept


WASLA-HALE – Remote Mission Steering and Integration of UAV into Air Traffic Management

COM 1

COM 3

Command Data Linkwith Intercom

COM 2

Relais A/C

AFCS /ATHRFMSMMS-BordRAPIN+

GCS BraunschweigGCS Manching


Rotorcraft - New Technologies

Active Twist Blade on Test Rig

Innovative New Rotor

but: „Circle-shaped Rotor-Wing“limits economy of fast flight

• Only 25% of noise• Only 10% of vibration level,

reducing scheduled maintenance cost > 50%

• Marginal Improvement of Efficiency


Flight Test Group ManchingInvolved in all aspects of military flight testing

(mainly HQ, CFH and performance)

For Eurofighter/ Typhoon

soon for A400Mup

dwn

STP (t)STP (t)

XK()XK()

SXX()SXX()

EXX()EXX()

up

dwn

STP (t)STP (t)

XK()XK()

SXX()SXX()

EXX()EXX()

up

dwn

STP (t)STP (t)

XK()XK()

SXX()SXX()

EXX()EXX()


Based on GRATE and ATLAS systems developed in the late 80s to evaluate handling qualities during air-to-surface tracking

Array of lighted targets are placed at predefined positions on the ground

During a prolonged gun attack, target lights are illuminated in a predefined sequence

Pilot has to acquire and track the respective target expeditiously and precisely, being forced to react continuously using a high gain piloting technique

Employed to assess and optimize tracking filter with respect to gross acquisition and fine tracking

Eurofighter Air-to-Surface HQ Evaluation for Swing-Role Adaptation (Ground Attack Test Equipment II - GRATE II)

Target AreaAircraft

xy


Flight Test Parameters and Simulated Attack Geometry

2,4 NM(14339 ft)

~1,4 NM(8506 ft)

1500 ft

10°

4030 ft

22 secs (=16016 ft) mit 431 KTAS (=400 KDAS)

Versuch: 20 secs (=14560 ft) mit 4

31 KTAS2 secs

2,6 NM(15772 ft)

4281 ft

300-500ft

~ 4800 ft

2,4 NM(14339 ft)

~1,4 NM(8506 ft)

1500 ft

10°

4030 ft

22 secs (=16016 ft) mit 431 KTAS (=400 KDAS)

Versuch: 20 secs (=14560 ft) mit 4

31 KTAS2 secs

2,6 NM(15772 ft)

4281 ft

300-500ft

~ 4800 ft


Employment of GRATE II for Pilot Model IdentificationOptimization of Target Array Geometry

Requirement: nearly uniform and small angle variations (0.4 - 1 deg) due to small perturbations approach

Ap

ert

ure

An

gle

[d

eg

]x1

x2

y1 y2

x3=y3

x4

y5

x5

x

133 m

123 m

112 m

y4

1 deg limit

0.4 deg limit

Distance x to reference target

4 x 21.5 m

102 m

yLast angle alteration


Input Signal into the Pilot-Aircraft SystemDefined by:

The varying line of sight between the aircraft and the individual targets

Target illumination sequence

x1 x2 x3 x4 x5

x

1+2

3+4

Distance x to the reference target [m]

Ap

ert

ure

an

gle

pro

gre

ssio

n [

de

g]

2

3

A

mp

litu

de

[d

eg

]

-5000 -4000 -3000 -2000 -1000

r(t)

vx1

vx5

vx3

vx4 vx4

vx3

3

2

1

0

-1

-2

-3

Distance x to the reference target [m]

Multi-step Approximation

34

2134

2 1


Frequency [rad/s]

CP 0.5

C 0.5

P 0.5

0 /2 3/2 2

Amplitude [deg]

Sequence Selection

Maximized power spectra over a wide frequency range → Fourier Analysis

P

N

kkkj

N

j

N

jj

C

vvtiN

vNt

tt

T

R

1

1

1

11

22

2

)cos(21

)(

)cos(12

|)(|

0 /2 3/2 2

maximum of C

Frequency [rad/s]

Am

plit

ud

e S

pe

ctru

m

t = 2.25s – 3s

t [s] [rad/s]

2)(

)cos(12

t

tt

zero location



Pilot Model IdentificationResults

Documents

Institute of Flight Systems