THIRD SEMINAR ON RRDPAE'98
THE FLYING DIDACTIC LABORATORY PROJECT
Andrzej TOMCZYK
Department of Control Systems, Rzeszów University of Technology, POLAND
Abstract
The article presents main thesis of the didactic flying laboratory project. Range of project
tasks and basic functions of the system are
shown. Paper contains preliminary project of the
on-board measuring system, and list of parameters proposed for measuring, processing, displayed on the screen and storing on the on-board
computer memory. Set of possible exercises to be
able to realization using the flying laboratory, and
perspective directions of system development are
presented.
measurements is adapting a light aircraft to teaching needs. Modification is based on employing
special on-board equipment and flight control
system.
The European Universities use the flying
classrooms, for example Cranfield University
uses two Jetstream 100 aircraft as an Integrated
Digital Measurement and Control Systems for
Teaching and Research,(1) and Delft University of
Technology employs Cessna Citation II as a
Flying Classroom Instrumentation System(2, 3) (see
figures 1 and 2).
1. Introduction
Practical training plays a very important role
in aeronautics engineers' education. This function
is performed by laboratory exercises. However,
laboratory stands, including flight simulators, do
not emulate many unique characteristics and
properties of aircraft and its on-board equipment.
Students' participation in real flight experiments is
an essential element of the process of establishing their engineering intuition. Many aviation universities, Cranfield University and Delft University
of Technology among others, employ the flying
laboratories in their teaching activities. We do not
have such equipment in Poland. The Rzeszow
Technical University instructs aeronautics designers and pilots. It comprises the Pilot Training Center which employs training airplanes. One of these
aircraft, the PZL M-20 'Mewa', will be used as a
flying didactic laboratory. This paper describes the
preliminary project of the PZL M-20 aircraft modification.
Education of aircraft engineers includes two
basic elements:
 theoretical classes, including lectures, seminars, and course projects,
 practical training: labs, industrial training, and
flight tests.
Flight tests are very expensive and require specialized equipment. Another method of flight
RRDPAE'98
FIG. 1. The Jetstream 100 as a Flying Laboratory
at Cranfield University
FIG. 2. The Cessna Citation II as a Flying Classroom at Delft University of Technology
A typical student station in the Jetstream 100
aircraft is presented on figure 3.(1) Figure 4 shows
the schematic drawing of Flying Classroom
1
Instrumentation System used on board of Cessna
Citation II aircraft(2). At present Delft University
staff prepares a new version of an on-board system.
FIG. 3. A student on-board station (Jetstream 100)
FIG. 4. Flying Classroom Instrumentation System
schematic drawing (Cessna Citation II)
The project will consist of three stages. First,
the aircraft will be equipped with measuring
equipment and a computer system designed for
storing, processing and displaying information.
Students taking part in the didactic flight will be
able to control the experiment, follow its course in
real time in flight and prepare detailed data postanalysis.
In the second stage of designing the laboratory, a digital flight control system will be included.
Its properties will be modifiable in order to evaluate the influence of design and regulation parameters on automatic flight control quality.
In the third stage, a fly-by-wire control system
will be installed which will allow modifications of
aircraft's dynamic and handling properties (TIFS Total In-Flight Simulator (4, 5,6) ).
RRDPAE'98
2. The main project assumptions
Flying laboratory project provides for adapting the PZL M-20 'Mewa" aircraft for the flying
laboratory by equipping it with on-board measurement and recording systems.
The first step of the project contains the following tasks:
1. The general project of the didactic onboard
equipment: equipment and systems specification.
2. The project of the onboard measurement
equipment and computer interface modules.
3. The project of electrical installation for additional equipment power supplies.
4. Building of the computer based measuring
system and laboratory integration of the
onboard equipment.
5. Creation and testing of the software for data
measuring, processing, recording, and postflight data analysis.
6. Modification and adaptation of the aircraft
structure for the requirements of Flying Laboratory.
7. Installation of the equipment, systems, and
students/teacher stands on-board the Flying
Laboratory.
8. Ground tests of all Flying Laboratory equipment and systems, sensor calibration.
9. Test flights of the Flying Laboratory, verification of the design solution and system evaluation.
10. Ground analysis of test flights data, verification of the post-flight data analysis software.
11. Preparation of students’ in-flight exercises
(textbook and measuring data forms).
The executive PZL M-20 "Mewa" aircraft,
equipped with two piston engines, has been selected for the purpose of building a flying laboratory for the following reasons:
 Pilot Training Center of Rzeszów University of
Technology use this type of plane for professional pilot education,
 A good flight performance of the aircraft,
 PZL M20 has relative good on-board equipment.
Figure 5 presents a diagram of students and additional equipment placement in the PZL M-20
cockpit.
The main functions of the on-board system
are:
2
 Measuring (sensors, transducers, e.t.c.
should be employed),
 Processing of the data (scaling, filtering,
smoothing, e.t.c.),
 Display measured signals in the real time,
 Storing data in the mass memory.
FLIGHT
INSTRUMEN TS
Instructor's panel
PILOT
EXPERIMENT
COORDINATOR
(Instructor)
the system. The main modules of the measurement equipment are:
 Inertial Reference Unit (IRU),
 Air Data Computer (ADC),
 Satellite Navigation System (GPS),
 Instrument Landing System (ILS),
 Radio Navigation System (VOR),
 Distance Measuring Equipment (DME),
 force and displacement sensors.
Schematic diagram of the on-board integrated
measurement system is shown on figure 6.
During flight, several flight parameters will be
measured, presented on monitors, and registered
in the memory of the on-board computer. The list
of parameters is presented in Table 1 (figure 7).
Main Screen
COMPUTER
3. The planned activities
STUDENT
B
STUDENT
A
2nd Screen
STUDENT
C
STUDENT
D
A D DITIONA L M EAS UREM EN T
EQU IPM EN T
FIG. 5. The basic elements of the system in the
PZL M-20 "Mewa" cockpit
The important propriety of a flying laboratory
is the possibility of involving students directly in
the experiment. Basis for their participation is
displaying flight parameters in real time.
The form of data presentation during the flight
are the following:
 Classic flight instruments (virtual computer
generated pictures),
 EFIS-like presentation (Electronic Flight Instrumentation System),
 Head-up display presentation (on the computer
screen),
 Engineering data presentation: typical (preplanned) or user's defined display.
The flying laboratory will be equipped with
complete set of sensors, navigation systems, and
an on-board computer to integrate all modules of
RRDPAE'98
Active student participation in preparing and
conducting measurement flights is an important
didactic task.
The following students' activities in a frame of
the flight test experiments are planned:
 Preparing a plan of the test flight: flight
conditions, kind of aircraft maneuvers, list of
displayed and stored signals,
 Observation the chosen parameters during
the flight and active participation in the experiment,
 Post flight data analysis and conclusions
(written report).
The flying laboratory will assist the process of
student education in many ways. The main goals
of the flying laboratory using will be as following:
 Support in education of aerodynamics, flight
mechanics and aircraft performance, flight
dynamics and handling qualities, on-board
instruments and systems, navigation aides,
flight control systems, flight test methodology,
 In-flight testing of instruments and systems
prepared by students as a course and diploma projects,
 The perspective development:
 User's modified automatic flight control
system,
 Flight management system development,
 Fly-by-wire control system,
 Experimental user-friendly control system for General Aviation Aircraft.
3
ENGINE
PARAMETERS
SUPPLAY
VOLTAGE
A - analog
A
A/D
CONVERTER
DISPLACEMENT
SENSORS
FORCE
SENSORS
A
RS-485
D - digital
D
IRU
A
A
VOR I
VOR II
RS-485
GPS
A
A
A
ANALOG SIGNALS
STANDARYZATION
ILS
LOC/GP
DME
RS-485
0/1
BINARY
SIGNALS
ADC
INTERFACE CARDS
ON-BOARD
COMPUTER
KEYBOARD
MAIN
STUDENTS'
LCD SCREEN
2nd
STUDENTS'
LCD SCREEN
INSTRUCTOR'S
LCD SCREEN
(Optionally)
FIG. 6. Schematic diagram of the on-board integrated measurement system
From the aeronautical engineer's point of
view, the flying laboratory allows to design many
various teaching exercises. The following student
classes have been planned, as listed below.
A. Preliminary post-flight analysis of the test results
 Filtering, processing and scaling of the
recorded signals
 Pitot-static system calibration, the airspeed and altitude correction
 Accuracy analysis
 Reducing the measured airspeed to ISA
values (IAS, CAS, EAS, TAS, Ma)
 Reducing the non-standard aircraft weight
and non-standard engine power (thrust)
B. Aircraft performance
 Normal take-off and landing
 Climb performance
 Minimal control speed
 Turn performance
 Flight path reconstruction
C. Static stability
 The neutral point
 Elevator trim curve
 Speed stability
RRDPAE'98
D. Dynamic stability
 Short period approximation
 Phugoid approximation
 Roll mode approximation
 Dutch mode approximation
E. Maneuverability
 Stick force per G
 Elevator angle per G
 Roll response
 Rudder response
 Handling qualities
F. Navigation
 GPS navigation
 VOR/DME area navigation
 TAS/heading/time navigation
 ILS approach
G. Identification procedures
 Airplane model identification
 Aerodynamic parameters identification
 Flight control system properties specification
4
Table 1.
No
1.
2.
3.
4.
5.
6.
7.
8.
9.
10.
11.
12.
13.
14.
15.
16.
17.
18.
19.
20.
21.
22.
23.
24.
25.
26.
27.
28.
29.
30.
31.
32.
33.
34.
Name
Pitch angle
Bank angle
Magnetic heading
Pitch rate
Roll rate
Yaw rate
Longitudinal acceleration
Lateral acceleration
Vertical acceleration
Pressure altitude
Vertical speed
Indicated airspeed
True airspeed
Static air temperature
Longitude
Latitude
Ground speed
Track angle
Geodesy height
True vertical velocity
GMT time
Vertical deviation
Localizer deviation
Cross track deviation I
Cross track deviation II
DME distance
DME distance rate
Elevator angle
Elevator trim tab angle
Aileron angle (right)
Rudder angle
Elevator control force
Aileron control force
Engine parameters
Notation
PA
BA
HDG
Q
P
R
AX
AY
AZ
ALT
VS
IAS
TAS
SAT
LON
LAT
GS
TA
GH
TVV
T
GP
LOC
CTD1
CTD2
XD
XV
EA
ETT
AIA
RUA
EF
AF
{array}
Unit
deg
deg
deg
deg/sec
deg/sec
deg/sec
m/sec2
m/sec2
m/sec2
m
m/sec
m/sec
m/sec
K
deg
deg
m/s
deg
m
m/sec
h:m:s
deg
deg
deg
deg
NM
kt
deg
deg
deg
deg
N
N
Range
15
45
0360
50
50
20
10
10
-2040
05000
20
10120
10150
220320
180
90
0-150
0360
05000
20
1.5
10
30
30
0250
250
-1525
30
40
25
300
200
Source
Type
IRU
D
ADC
D
GPS
D
ILS
A
VOR I
VOR II
A
A
DME
A
P
P
P
P
F
F
A
A
A
A
A
A
FIG. 7. The list of the measured signals, where: D - digital signal, A - analog signal;
P - displacement sensor, F - force sensor
A flight experiment will result in student report, which will include results of calculations and
analysis of registered data. The specialized
ground station for data analysis will consist of 5 to
8 PC's connected by local network. Windows NT
operating system and MATLAB/SIMULINK software will be used as basic programs. Specialized
procedures for flight test data analysis will be prepared by teachers and students.
 Education and training of flight test engineers and test pilots,
 Some research flight test can be carried
out; for example: Simplified Control of
General Aviation Aircraft (7).
Employing a flying laboratory in the process of student education will allow to gather new
insights. It will become possible to develop and
perfect new activities, for example:
 Development and updating of relevant
syllabuses and didactic materials,
 Development and maintaining of continuing education/retraining courses,
The flying laboratory project is the first of its
kind in Poland. It is assumed that the Warsaw
University of Technology students will also extensively use the Flying Laboratory, and the foreign
aeronautics students will be invited as well.
Department of Control Systems at Rzeszów
University of Technology has practical knowledge
concerning design, construction, and flight tests of
the APC-1P autopilot for general aviation and
RRDPAE'98
5. Conclusions
5
commuter aircraft (8, 9, 10). This auto-pilot was used
on-board of the PZL M-20 "Mewa" aircraft. Within
the framework of designing control system for
unmanned aircraft (UMA)(11), miniaturized air data
computers (ADC) and Inertial Reference Unit
(IRU), based on fiber optics gyros, have been
developed (12, 13, 14). This equipment may be used
in the on-board measurement system of the flying
laboratory.
FIG. 8. PZL M-20 "Mewa" aircraft as a Flying Laboratory at Rzeszów University of Technology
The grounds for an on-board computer
software to integrate the measurement system
have also been developed. The building of the
flying laboratory is one of the elements of TEMPUS II project to aid education of aircraft engineers. The first stage of the project is described in
the JEP-12095-97 project, being currently jointly
developed by European aeronautics universities
working within the framework of STAR - Specialized Training in Aeronautics and Research.
The current stage of the project allows to expect
the first stage of the flying laboratory project to be
completed in mid-2000.
References
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Measurement and Control System for Teaching and Research. Aerogram, vol. 7, No 2,
Cranfield University, Cranfield, UK, p. 14-20
2. Mulder J.A., Kruijsen E.A.C. (1994): In-Flight
Student Exercises with the DUT Citation II.
On-board System Description. Delft University
of Technology Press, Delft, NL
RRDPAE'98
3. Sridhar J.K., Fritschy J., Hulshoff S., Mulder
J.A. (1997): Cessna Citation II Flight Tests.
Engine
Modeling,
Aerodynamic
Model
Identyfication and Software Development. TU
Delft Memorandum M-797, Delft, NL
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SAE/AIAA Paper No 985551, 1998 World
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3(31)/93, Warszawa, p. 601-619
11. Gruszecki [ed.] (1995-99): Autonomous Navigation and Flight Control System for Unmanned Aircraft. Reports of the Control Systems Department, Rzeszów University of
Technology, Rzeszów (in Polish, unpublished)
12. Grzybowski J., Lipiec P. (1998): Microprocessor Based Air Data Computer. Scientific Reports No 168, vol. 1, Rzeszów University of
Technology, Rzeszów, p. 303-310 (in Polish)
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Unmanned Aerial Vehicle. Scientific Reports
No 168, vol. 1, Rzeszów University of Technology, Rzeszów, p. 369-376 (in Polish)
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and Correction of Errors of the Inertial Reference Unit (IRU). Proceedings of the International Scientific Conference MECHANICS'98,
vol. 2, Rzeszów, p. 367-378 (in Polish)
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