pi: asst. prof. joseph f. horn tel: (814) 865 6434 email: [email protected] graduate students: dooyong...
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![Page 1: PI: Asst. Prof. Joseph F. Horn Tel: (814) 865 6434 Email: joehorn@psu.edu Graduate Students: Dooyong Lee, PhD Candidate Derek Bridges, PhD Candidate Project](https://reader035.vdocuments.site/reader035/viewer/2022062716/56649dc75503460f94abbc15/html5/thumbnails/1.jpg)
PENNSTATE1 8 5 5
PI: Asst. Prof. Joseph F. HornTel: (814) 865 6434 Email: [email protected]
Graduate Students: Dooyong Lee, PhD CandidateDerek Bridges, PhD Candidate
Project PS 5.2Simulation and Control of Shipboard Launch and
Recovery Operations
2005 RCOE Program Review
May 3, 2005
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PENNSTATE1 8 5 5
• The shipboard launch and recovery task is one of the most challenging, training intensive, and dangerous of all rotorcraft operations
• The helicopter / ship dynamic interface (DI) is difficult to accurately model
• Industry and government could use better tools for analyzing shipboard operations to reduce the flight test time and cost to establish safe operating envelopes
• Workload requirements could be reduced using task-tailored control systems for shipboard operations
Background / Problem Statement
Technical Barriers• Accurate models require the integration of the time-varying
ship airwake and the flight dynamics of the helicopter
• Currently pilot workload requirements and HQ analysis must be assessed using expensive flight tests and piloted simulation. Better engineering tools needed to reduce costs for analyzing current and future ships / aircraft.
• A practical, fully autonomous or piloted assisted landing AFCS has not yet been developed, need to assess requirements and potential benefits
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PENNSTATE1 8 5 5
• Develop advanced simulation model of the shipboard dynamic interface
• Validate the model using available test data
• Use the model to develop advanced flight control systems to address workload issues in the DI
Task Objectives:
Approaches:
Expected Results:• A simulation tool for analyzing handling qualities in the DI and predicting safe landing envelopes
• A methodology for designing a task-tailored AFCS for shipboard operations
• A conceptual design of an autonomous landing systems and assessment of the system requirements for such a system (possible UAV applications)
• Develop a MATLAB/SIMULINK based simulation of the H-60 based on GenHel (will facilitate model improvements and control law development)
• Develop a maneuver controller to simulate pilot control during launch and recovery operations
• Integrate simulation with ship airwake models, investigate relative effects of steady and time-accurate CFD wakes, and stochastic wake models based on CFD and flight test data
• Simulate UH-60 operating off LHA and validate model with JSHIP flight test data
• Develop new concepts in AFCS design for shipboard operations
• Develop a real-time simulation facility of shipboard operations (using DURIP funds)
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PENNSTATE1 8 5 5
PSU DI Simulation Program
• Developed “tunable” pilot model for different levels of tracking tolerance
• Integrated CFD solutions of ship airwake with non-linear flight dynamics model
• Demonstrated using UH-60A / LHA combination, same as JSHIP flight test program
• Validated model with flight test data from JSHIP program
• Evaluate task tailored control laws
Matlab based DI simulation program(based on GENHEL)
Human pilot model(Optimal control model)
Time-accurateship airwake from CFD
Stochastic airwake model
Real-time simulation
Validation with flight test data
(from JSHIP program)Task-tailored control law design(using CONDUIT)
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PENNSTATE1 8 5 5
Stochastic Ship Airwake Modeling
• A method for extracting equivalent airwake disturbances from flight test data (or high order simulation model) has been developed
Method is similar to that used for turbulence models developed at NASA Ames (Ref. Labows and Tischler et al, MacFarland - SORBET Model)
Filters are derived to simulate the spectral properties of the airwake, can compare to traditional turbulence models (e.g. von Karman, Dryden)
Spectral filters are based on von Karman model, and modified to fit the desired forms of spectral characteristics
• Stochastic airwake model can be readily used for flight control optimization
HelicopterDynamics
Pilot stick inputs
SAS
++
+
White noise Linear filter
Stochastic airwake model
Optimized to reject disturbances
Designed to fit the spectral properties
of the airwake
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PENNSTATE1 8 5 5
Stochastic Ship Airwake ModelingSample Results for Vertical Component, 0° WOD
Extracted from simulationwith full time-varying airwake
von Karman Turbulence ModelLw = 37.8667 ft, w = 2.8067 ft/sec
32
2
1539.09754.19958.21
3398.07478.214
s
VL
sVL
sVL
sVL
sVL
VL
sHwww
wwww
“Best Fit” Spectral FilterLw =10.7156 ft, w = 4.81 ft/sec
32
2
8985.13169.35601.21
9173.05913.114
sV
Ls
V
Ls
V
L
sV
Ls
V
L
V
L
sHwww
wwww
Frequency (rad/sec)
PS
D o
f ve
rtic
al g
ust
co
mp
on
en
t, (
ft/s
ec)2
/(ra
d/s
ec)
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PENNSTATE1 8 5 5
Stochastic Ship Airwake Modeling
Equivalent Airwake DisturbancesFull Time-Varying Airwake
• Comparison of response with stochastic airwake model, equivalent disturbances and full time-varying airwake (spectral data averaged over five runs)
Frequency (rad/sec)
LA
TL
ON
PE
DC
OL
- Input autospectrum(0 deg WOD), dB
Autospectra identified by CIFER
Stochastic Airwake
LA
TL
ON
PE
DC
OL
Frequency (rad/sec)
- Input autospectrum(30 deg WOD), dB
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PENNSTATE1 8 5 5
• Using CONDUIT to optimize SAS gains• Include ADS-33 HQ specs as constraints in optimization• Include longitudinal acceleration feedback and pitch attitude feedback
Optimize for minimal gust
response
AirwakeSpectralFilters
Task-Tailored Control Design
Longitudinal accelerationfeedback to
improve gust response
Pitch attitude feedback to
provide closed-loop
stability
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PENNSTATE1 8 5 5
Stability Augmentation System
• Optimize gains using CONDUIT
Based on phase-lag compensator
Design parameters include the prefix “dpp_”
Roll SAS
Pitch SAS
Yaw SAS
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PENNSTATE1 8 5 5
HQ specs
• Selected design specs from CONDUIT as constraints
Closed-loop eigenvalues(EigLcG1), Gain/Phase margin(StbMgG1), Crossover frequency(CrsLnG1), Bandwidth for roll/pitch(BnwAtH1)
• New spec for disturbance rejection(DisRnL1)
Based on psd of angular rate response to corresponding gust input
Whitenoise
PSDTransfer function
)(
)()(
sq
sqsH
g
(Example) – Pitch rate
Frequency [rad/sec]M
agn
itu
de
[dB
]
Level I
Level II
Level III
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PENNSTATE1 8 5 5
HQ Specification Window
• Original SAS configurations - 30 degree WOD condition
rollpitchyaw
(1)(2)(3)
CrsLnG1 (1) CrsLnG1 (2) CrsLnG1 (3) EigLcG1 (1)EigLcG1 (2)EigLcG1 (3)StbMgG1 (1)StbMgG1 (2)StbMgG1 (3)BnwAtH1 (1)BnwAtH1 (2)DisRnL1 (2)DisRnL1 (3)DisRnL2 (1)
S J J
H H H
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PENNSTATE1 8 5 5
HQ Specification Window
• Modified SAS configurations - 30 degree WOD condition
S J J
H H H
CrsLnG1 (1) CrsLnG1 (2) CrsLnG1 (3) EigLcG1 (1)EigLcG1 (2)EigLcG1 (3)StbMgG1 (1)StbMgG1 (2)StbMgG1 (3)BnwAtH1 (1)BnwAtH1 (2)DisRnL1 (2)DisRnL1 (3)DisRnL2 (1)
rollpitchyaw
(1)(2)(3)
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PENNSTATE1 8 5 5
Simulation Results - Hovering Flight
• Angular rate responses (deg/sec)
Result with Original SAS configurationsResult with Optimized SAS configurations
Time [sec]
P,
de
g/s
ec
Q,
de
g/s
ec
R,
de
g/s
ec
- 30 degree WOD
P,
de
g/s
ec
Q,
de
g/s
ec
R,
de
g/s
ec
Time [sec]
- 0 degree WOD
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PENNSTATE1 8 5 5
Simulation Results - Hovering Flight
• SAS outputs (%)
Result with Original SAS configurationsResult with Optimized SAS configurations
- 30 degree WOD
Time [sec]
RS
AS
, %
PS
AS
, %
YS
AS
, %
RS
AS
, %
PS
AS
, %
YS
AS
, %
Time [sec]
- 0 degree WOD
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PENNSTATE1 8 5 5
• Pilot stick inputs (%)
Simulation Results - Hovering Flight
- 0 degree WOD - 30 degree WOD
Time [sec] Time [sec]
Result with Original SAS configurationsResult with Optimized SAS configurations
Lateral cyclic input : Left 0%, Right 100%Longitudinal cyclic input : Forward 0% , Aft 100%Collective input : Down 0%, Up 100%Pedal input : Left 0%, Right 100%
LA
T,
%L
ON
, %
PE
D,
%C
OL
, %
LA
T,
%L
ON
, %
PE
D,
%C
OL
, %
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PENNSTATE1 8 5 5
Simulation Results - Hovering Flight
• Angular rate autospectrum (dB)
Result with Original SAS configurationsResult with Optimized SAS configurations
- 30 degree WOD
P,
dB
Q,
dB
R,
dB
- 0 degree WOD
Autospectra identified by CIFER
P,
dB
Q,
dB
R,
dB
Frequency [rad/sec] Frequency [rad/sec]
![Page 17: PI: Asst. Prof. Joseph F. Horn Tel: (814) 865 6434 Email: joehorn@psu.edu Graduate Students: Dooyong Lee, PhD Candidate Derek Bridges, PhD Candidate Project](https://reader035.vdocuments.site/reader035/viewer/2022062716/56649dc75503460f94abbc15/html5/thumbnails/17.jpg)
PENNSTATE1 8 5 5
• Pilot stick input autospectrum (dB)
Simulation Results - Hovering Flight
- 0 degree WOD - 30 degree WOD
Frequency [rad/sec] Frequency [rad/sec]
Result with Original SAS configurationsResult with Optimized SAS configurations
LA
T,
dB
LO
N,
dB
PE
D,
dB
CO
L,
dB
Autospectra identified by CIFER
LA
T,
dB
LO
N,
dB
PE
D,
dB
CO
L,
dB
![Page 18: PI: Asst. Prof. Joseph F. Horn Tel: (814) 865 6434 Email: joehorn@psu.edu Graduate Students: Dooyong Lee, PhD Candidate Derek Bridges, PhD Candidate Project](https://reader035.vdocuments.site/reader035/viewer/2022062716/56649dc75503460f94abbc15/html5/thumbnails/18.jpg)
PENNSTATE1 8 5 5
H infinity Controller for SAS
• Include frequency-dependent weight functions for control inputs and outputs• Produce a controller K∞
to reduce the tracking deviations to reject disturbances
• We is a high-gain low-pass filter for good tracking and disturbance rejection• Wu is a low-gain high-pass filter to improve the robustness and to limit the control activity
H∞ controller(K∞)
Aircraft(UH-60)
Weighting(We)
Weighting(Wu)
Gust Filter(Wg)
+ + +
-
dw
d
uee
eu
yref + +
dt
![Page 19: PI: Asst. Prof. Joseph F. Horn Tel: (814) 865 6434 Email: joehorn@psu.edu Graduate Students: Dooyong Lee, PhD Candidate Derek Bridges, PhD Candidate Project](https://reader035.vdocuments.site/reader035/viewer/2022062716/56649dc75503460f94abbc15/html5/thumbnails/19.jpg)
PENNSTATE1 8 5 5
H infinity Controller Design
22212
12111
21
DDC
DDC
BBA
G
uDwDxCy
uDwDxCz
uBwBxAx
22212
12111
21
x
• Obtain a controller solving a classical 4-block problem based on 8-rigid-state linearized aircraft model 3 diagonal components of weighting functions iterate to find the optimal weighting parameters
w
z
u
yAircraft
We
Wu
=dw
dt=
pqr
=ee
eu=
rsaspsasysas
=, , , , ,
14-state H∞ controller
u
w
x
DDC
DDC
BBA
y
z
x
22212
12111
21
![Page 20: PI: Asst. Prof. Joseph F. Horn Tel: (814) 865 6434 Email: joehorn@psu.edu Graduate Students: Dooyong Lee, PhD Candidate Derek Bridges, PhD Candidate Project](https://reader035.vdocuments.site/reader035/viewer/2022062716/56649dc75503460f94abbc15/html5/thumbnails/20.jpg)
PENNSTATE1 8 5 5
Simulation Results - Hovering Flight
• Angular rate responses (deg/sec)
Time [sec]
P,
de
g/s
ec
Q,
de
g/s
ec
R,
de
g/s
ec
- 30 degree WOD
P,
de
g/s
ec
Q,
de
g/s
ec
R,
de
g/s
ec
Time [sec]
- 0 degree WOD
Result with Original SAS configurationsResult with Optimized SAS configurationsResult with H infinity controller
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PENNSTATE1 8 5 5
Simulation Results - Hovering Flight
• SAS outputs (%)
- 30 degree WOD
Time [sec]
RS
AS
, %
PS
AS
, %
YS
AS
, %
RS
AS
, %
PS
AS
, %
YS
AS
, %
Time [sec]
- 0 degree WOD
Result with Original SAS configurationsResult with Optimized SAS configurationsResult with H infinity controller
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PENNSTATE1 8 5 5
Simulation Results - Hovering Flight
• Pilot stick inputs (%)
- 0 degree WOD - 30 degree WOD
Time [sec] Time [sec]
LA
T,
%L
ON
, %
PE
D,
%C
OL
, %
LA
T,
%L
ON
, %
PE
D,
%C
OL
, %
Result with Original SAS configurationsResult with Optimized SAS configurationsResult with H infinity controller
![Page 23: PI: Asst. Prof. Joseph F. Horn Tel: (814) 865 6434 Email: joehorn@psu.edu Graduate Students: Dooyong Lee, PhD Candidate Derek Bridges, PhD Candidate Project](https://reader035.vdocuments.site/reader035/viewer/2022062716/56649dc75503460f94abbc15/html5/thumbnails/23.jpg)
PENNSTATE1 8 5 5
Simulation Results - Hovering Flight
• Angular rate autospectrum (dB)
- 30 degree WOD
P,
dB
Q,
dB
R,
dB
- 0 degree WOD
Autospectra identified by CIFER
P,
dB
Q,
dB
R,
dB
Frequency [rad/sec] Frequency [rad/sec]
Result with Original SAS configurationsResult with Optimized SAS configurationsResult with H infinity controller
![Page 24: PI: Asst. Prof. Joseph F. Horn Tel: (814) 865 6434 Email: joehorn@psu.edu Graduate Students: Dooyong Lee, PhD Candidate Derek Bridges, PhD Candidate Project](https://reader035.vdocuments.site/reader035/viewer/2022062716/56649dc75503460f94abbc15/html5/thumbnails/24.jpg)
PENNSTATE1 8 5 5
Simulation Results - Hovering Flight
• Pilot stick input autospectrum (dB)
- 0 degree WOD - 30 degree WOD
Frequency [rad/sec] Frequency [rad/sec]
LA
T,
dB
LO
N,
dB
PE
D,
dB
CO
L,
dB
Autospectra identified by CIFER
LA
T,
dB
LO
N,
dB
PE
D,
dB
CO
L,
dB
Result with Original SAS configurationsResult with Optimized SAS configurationsResult with H infinity controller
![Page 25: PI: Asst. Prof. Joseph F. Horn Tel: (814) 865 6434 Email: joehorn@psu.edu Graduate Students: Dooyong Lee, PhD Candidate Derek Bridges, PhD Candidate Project](https://reader035.vdocuments.site/reader035/viewer/2022062716/56649dc75503460f94abbc15/html5/thumbnails/25.jpg)
PENNSTATE1 8 5 5
Rotorcraft Flight Simulator
• Flight dynamics model is based on Genhel• Use FlightGear environment for visualization
• Integrated with time-varying airwake data from CFD• Integrated with CHARM freewake model
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PENNSTATE1 8 5 5
Schedule and Milestones
Tasks 2001 2002 2004 2005
• Update GenHel Simulation for shipboard simulation
• Develop simplified MATLAB Sim for control design
• Interface GenHel with ship air wake solutions and ship motion
• Develop maneuver controller• Validation of DI simulation
(using JSHIP data)• Develop stochastic airwakes
disturbance model and develop physical understanding
• Develop real-time simulation capability at PSU
• Incorporate CHARM free wake into the model
• Task tailored control law design, support with real-time simulator at PSU
• Lee PhD Degree• Derek Bridges PhD Degree
2003
CompletedShort TermLong Term
2006
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PENNSTATE1 8 5 5
•Developed stochastic airwake disturbance model for 0° and 30° WOD, use for off-line analysis, real-time simulation and flight control design
•Real-time simulation facility is ready, integrated with time-varying airwake model and CHARM freewake model
•Developed task-tailored control laws using CONDUIT and H infinity control method
•Presented results at 2004 AIAA AFM conference, paper published in AIAA Journal of Aircraft, paper submitted to Journal of Aerospace Engineering (special issue on shipboard aviation)
2004 Accomplishments
Planned Accomplishments for 2005•Will present results at 2005 AHS Forum and submit as journal article•Continue to update and improve model, include the deck ground effects •Further study in task tailored control laws to improve disturbance rejection•Expand flight control design efforts, autonomous landing flight control system, position hold over ship deck
• Investigate use of equivalent airwake disturbances as tool for validating ship CFD airwake models.
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PENNSTATE1 8 5 5
Technology Transfer Activities:
Leveraging or Attracting Other Resources or Programs:
Recommendations atthe 2004 Review:
Actions Taken:
• Presented results at 2004 AIAA AFM Conference• Briefing to Navy Flight Dynamics Group at in Summer 2004, planning further interaction.
• Obtained JSHIP flight test data for validation, Cdr. Kevin Delemar at NRTC is contact • Integrating with CHARM free wake model• Integrated model and controllers with simulation facility developed under DURIP funds
Get with Navy to focus the project and also to interface with CFD activities (flow field).
Met with Navy. Received recommendations and we are planning more interaction. Proposed use of equivalent airwake disturbance model as tool for validation of CFD airwakes.
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PENNSTATE1 8 5 5
Overview of Accomplishments2001-2005
Advanced Simulation Model for Shipboard Operations• Interface with time accurate CFD solutions of ship airwake• High order Peters-He inflow• Tunable OCM pilot model • MATLAB / Simulink version of model for rapid
development and control design• Validation against JSHIP flight test data • Implemented in real-time simulation facility at PSU
Stochastic Airwake Disturbance Model• Method for extracting equivalent disturbances from simulation
with full CFD airwake (can also be applied to flight test data)• Derived spectral filters to represent airwake disturbances
Task-Tailored Control Design for Shipboard Operations• Optimized SAS for operation in airwake using CONDUIT®
• Use spectral filters in control synthesis• Optimized SAS using H∞ synthesis
Publications• 5 conference papers, 1 journal paper published, 1 journal paper under review
Extracted from simulationwith full time-varying airwake
von Karman Turbulence ModelLw = 37.8667 ft, w = 2.8067 ft/sec
32
2
1539.09754.19958.21
3398.07478.214
sV
Ls
V
Ls
V
L
sV
Ls
V
L
V
L
sHwww
wwww
“Best Fit” Spectral FilterLw =10.7156 ft, w = 4.81 ft/sec
32
2
8985.13169.35601.21
9173.05913.114
sVL
sVL
sVL
sVL
sVL
VL
sHwww
wwww
Frequency (rad/sec)
PS
D o
f v
ert
ica
l g
us
t c
om
po
ne
nt,
(ft
/se
c)2
/(ra
d/s
ec
)
Extracted from simulationwith full time-varying airwake
von Karman Turbulence ModelLw = 37.8667 ft, w = 2.8067 ft/sec
32
2
1539.09754.19958.21
3398.07478.214
sV
Ls
V
Ls
V
L
sV
Ls
V
L
V
L
sHwww
wwww
“Best Fit” Spectral FilterLw =10.7156 ft, w = 4.81 ft/sec
32
2
8985.13169.35601.21
9173.05913.114
sVL
sVL
sVL
sVL
sVL
VL
sHwww
wwww
Frequency (rad/sec)
PS
D o
f v
ert
ica
l g
us
t c
om
po
ne
nt,
(ft
/se
c)2
/(ra
d/s
ec
)
Optimize for minimal gust
response
AirwakeSpectralFilters
Longitudinal accelerationfeedback to
improve gust response
Pitch attitude feedback to
provide closed-loop
stability
Optimize for minimal gust
response
Optimize for minimal gust
response
AirwakeSpectralFilters
Longitudinal accelerationfeedback to
improve gust response
Pitch attitude feedback to
provide closed-loop
stability
![Page 30: PI: Asst. Prof. Joseph F. Horn Tel: (814) 865 6434 Email: joehorn@psu.edu Graduate Students: Dooyong Lee, PhD Candidate Derek Bridges, PhD Candidate Project](https://reader035.vdocuments.site/reader035/viewer/2022062716/56649dc75503460f94abbc15/html5/thumbnails/30.jpg)
PENNSTATE1 8 5 5
Future Path
Additional Basic Research
Transition to Applications / Applied Research
• Should pursue similar analyses to study effects of building airwakes on UAVs operating in urban areas, proposed as follow on for next RCOE
• Potential to investigate impacts on shipboard handling qualities requirements – Maritime ADS-33.
• Could make further efforts to pursue the fully coupled problem, model effect of rotor wake on ship airwake, would need more CFD expertise
• Apply equivalent airwake disturbance method to validate ship airwake CFD analysis. Airwake disturbance can be extracted from flight test and compared to simulation with CFD wake
• Use stochastic airwake model as a simplified and more compact model for use in trainers
• Apply maneuver controller and simulation for analysis of new aircraft and new ship designs