PROBLEM SOLVING METHODOLOGY
There is a preferred approach to problem solving in engineering. Rather than using a haphazard
plug and crunch approach, you should use a systematic procedure characterized by a
prescribed format. This will help you to think ab

Pressure and Temperature
Sensors, Signal Condi5oning
Object:
Find a way to sense a physical quantity, such as pressure or temperature,
which produces a voltage that varies in a predictable way with a change
in the quantity being measured.
Many cl

AA320 Aerospace instrumentation
Homework #2 Week of October 12, 2015
This homework assignment is due Friday, Oct. 16 at noon.
1. Multiple capacitors: Consider capacitors in parallel and in series:
Vc
C1
C2
C1
Vc
Parallel
C2
Series
Parallel case: The same

AA 320 Why is Report Writing Important?
The short answer:
Your grade depends on it.
The real answer:
A consistent complaint among aerospace companies and graduate advisors is that students
lack the ability to effectively communicate their work. In order t

AA320 Section AA
The Title
Primary Author, Another Author, and Another Author
William E. Boeing Department of Aeronautics & Astronautics
University of Washington, Seattle, WA 98195-2400
YY-MM-DD
Nomenclature
The Nomenclature goes here. Here is an example

AA 320 - Aerospace Instrumentation - Autumn 2015
Two 50-min lectures, one 1-hr-50-min lab per week; 3 credits
Goals:
This course is intended to give Aeronautics and Astronautics majors both analytical
and practice-oriented tools for understanding elect

AA 320 Report Writing Guide
Even the most innovative development or great discovery is useless unless it is effectively
communicated to others in the field. Thus, you will prepare a concise ( no more than 6-7 pages),
but complete report in accordance with

AA320 Aerospace Instrumentation
Homework #5 Week of November 2, 2015
1. Summing two frequencies:
In Lab #5 you added a signal from the power line at 60 Hz to a signal from the function generator of
approximately the same frequency. You should have seen a

AA 320 - Uncertainty Analysis Notes
Assume N measurements are made to determine the average or mean value of (xi/N) = x for a quantity
which has true value X.
! ! !
!
! !
The standard deviation for a set of N measurements is: ! =
The closer x is to X, the

AA320 Aerospace Instrumentation
Lab 2 - Week of October 12, 2015
RC Circuit, RC Filter
This lab introduces the use of the oscilloscope and function generator, and examines the behavior and use
of RC circuits.
1. RC circuit:
This experiment demonstrates th

Saving Oscilloscope Waveforms to a Thumb Drive
(Tektronix TBS 1052-EDU Oscilloscope)
1. Insert the thumb drive into the oscilloscope
2. Set up the Print button:
a) Push the Utility button in the upper right quadrant of the front panel.
The remaining instr

Using the Oscilloscopes Cursors to Measure Amplitude and Time
Tektronix TBS 1052-EDU Oscilloscope
Amplitude:
1. Push the Cursor front-panel button to see the Cursor Menu.
1. Push the Type side-menu button. A pop-out menu should appear showing a scrollable

310 Final
Orbit determination
I.
know r , v
r v
hz
Nx
1
, N = K h, = cos ^-1 (
(0 <180), e =
, h = rv, i= cos^-1 (
[(v^2 r
h
N
e
e
2
2
1 h
1 N e
h 2 2
r r v r v ], e =
(0 < <180), = e r 1 0 < <180)
1+ 2 ( v ) , = cos
r
N e
r
r
( )=cos1
r
cos1
Vr =
II.

AA311 Atmospheric Flight Mechanics
Autumn 2015
HW#3 Due: 10/26/15 (Mon)
Textbook (7 probs): 4.30, 4.32, 4.34, 4.35, 4.38, 4.47, 4.60
Prob 1 Given: A skydiver jumps out of a perfectly good balloon from an altitude of 120,000 ft and
reaches terminal velocit

ORBITAL MECHANICS 53
Table 3.3 Relations dening an elliptical orbit
_-_
Eccentcity e
e = 5 (3.19) e = 55 1 (3.39)
a . a
L e = U r) (3.20) e = rP (3.40)
1 (ra + rp) a
r; r1
= 3.28
e r1 cos 61 r2 cos 6; ( )
Flight path angle y
tan _ esin0 (331)
y 1 + eco

AA311 Atmospheric Flight Mechanics
Autumn 2015
HW#5 Due: 11/16/15 (Mon)
Textbook (11 probs): 5.16, 5.20, 5.21, 5.22, 5.24, 5.26, 5.30, 6.1, 6.4, 6.6, 6.8
Prob 1 The drag on the hull of a ship depends in part on the height of the water waves generated by t

AA311 Atmospheric Flight Mechanics
Autumn 2015
HW#7 Due: 12/11/15 (Fri)
Textbook (3 probs): 7.2, 7.3 (ans: 384 N-m), 7.4 (ans: -240 N-m)
Prob 1 Consider an experimental aircraft flying at 220 ft/s and an altitude of 9,000 ft. The airfoil has a
chord of 3

AA311 Atmospheric Flight Mechanics
Autumn 2015
HW#1 Due: 10/9/15 (Fri)
From Text:
2.2
Consider 1 kg of helium at 500K. Assuming that the total internal energy of the helium is due to
the mean kinetic energy of each atom summed over all the atoms, calculat

AA311: Airplane Terminology
Vertical Stabilizer
Propeller
Wing
Horizontal Stabilizer
Fuselage
Landing Gear
Control Surfaces
Left Aileron
Elevator
Right Landing Flap
Rudder
1
Another View
Rudder
Vertical Stabilizer
Cockpit
Cowl
Trim Tab
Axis of Rotation
Ax

AA311: History of Flight
The Wright Brothers
10:35am on Dec. 17, 1903
Kill Devil Hills (4 mi south of Kitty Hawk, North Carolina)
Orville and Wilbur Wright and 5 local witnesses
12 second, 120 foot flight of the Wright Flyer I (Orville piloting)
Considere

Homework 1
Friday, 8 January, 2016
09:30
Due: 11:59pm Friday January 15 2016
Place elecrronic version (pdf) in the Catalyst Dropbox.
[square brackets correspond to the corresponding problem in the textbook]
1. Degrees of freedom
For each of the diagrams i

AA320 Aerospace Instrumentation
Summary Notes Week of Nov. 16, 2015
1. I-to-V converter:
Some sensors used in aerospace instrumentation generate a current instead of a voltage. An example is a
photodiode, which generates a current proportional to the ligh

AA 320 Aerospace Instrumentation
Homework #7 Week of November 16, 2015
(due at same time as lab report)
1. Transimpedance amplifier and photodiode:
a) The two rules we have been using for op-amps give a very accurate account of the operation of the
transi

LF411
Low Offset, Low Drift JFET Input Operational Amplifier
General Description
Features
These devices are low cost, high speed, JFET input operational amplifiers with very low input offset voltage and guaranteed input offset voltage drift. They require

c
First calculate the damping ratio, =2 = 0.157
1
1
The system transfer function H() = 2+ = 4000010072+2000
|H()|2 =
1.016 4
1
4.067 2 + 1.69
Therefore, the PSD of the response () = |()|2 () where () =
() = . .
+.
The mean square value 2 = ()
= 1.0164

AA320 Aerospace Instrumentation
Summary Notes Week 1
Current and Voltage
At the most basic level, electronics is about manipulating the flow of electric charges (electrons)
by voltages (potential differences). The force on an electric charge is
F = qE
Whe

c
First calculate the damping ratio, =2 = 0.157
1
1
The system transfer function H() = 2+ = 4000010072+2000
|H()|2 =
1.016 4
1
4.067 2 + 1.69
Therefore, the PSD of the response () = |()|2 () where () =
() = . .
+.
The mean square value 2 = ()
= 1.0164

AA 312 HW 4 Yifan wang
Respond for critically damped system
Set initial position 0 =0, then 0 = ,
We know from chapter 1 that solution for critically damped system x(t) = [0 (0 + 0 )] ]
Plug in 0 =0, 0 = , x(t) =
Using the same method,
For an over damped

INA118
INA
118
INA
118
Precision, Low Power
INSTRUMENTATION AMPLIFIER
DESCRIPTION
FEATURES
LOW OFFSET VOLTAGE: 50V max
LOW DRIFT: 0.5V/C max
LOW INPUT BIAS CURRENT: 5nA max
HIGH CMR: 110dB min
INPUTS PROTECTED TO 40V
WIDE SUPPLY RANGE: 1.35 to 18V
LOW QU