AVS1230_ Lab 1 2023(2)
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Jordy Keurntjes AVS1230
September 19th
AVS 1230
Lab 1
Aircraft Flight Controls
Purpose:
Identify primary and secondary flight controls and apply their effect on aircraft flight. Categorize the planform of several aircraft.
Reference:
Electronic Flight Book - COA
Internet Activities:
Part 1: Aircraft planform
Internet search
Identify the planform of the 11 different types of aircraft according to their wing shapes. List the
aircraft and the type of their planform(wing shape).
Aircraft
Planform
1
Supermarine Spitfire Eliptical Wing
2
Seversky-35
Semi-Elliptical Wing
3
Piper PA 38
Rectengular Wing
4
P-51 Mustang Tapered Wing
5
Mirage 2000
Delta
6
English Electric Canberra Constant Chord with Tapered Outer
7
Lockheed Martin F-22 Raptor
Tapezoidal
8
Aérospatiale-BAC Concorde
Ogive
9
Boeing 787 Dreamliner
Swept Back Wings
10
Suko Su-47 Berkut
Swept Forward Wings
11
General Dynamics F-
111 Aardvark
Variable Sweep Wings
Jordy Keurntjes AVS1230
September 19th
Part 2: WMU Fleet Flight Controls
EFB Toolkit
1.
The primary flight controls on the Cirrus SR20 are ___________________ actuated. (Finals Question)
A. Hydraulically
B. Cable
C. Pneumatic
2.
What type of flap is installed on the Cirrus SR20?
See Cirrus Manual (7-22) EFB Toolkit
A. Plain
B. Split
C.
Single-slotted flaps
D. Fowler
3.
Which flight controls on the Cirrus SR20 have ground adjustable trim tabs?
A. Rudder
B. Elevator C. Aileron 4.
The Cirrus SR20 has electric trim to control Pitch and Roll
SEMINOLE, Hangar 3.
Note: Do not enter the Seminole cockpit without permission.
What is Item A marked on the Seminole in Hangar 3?
What type of Trim tab is Item A.1 (Servo or Anti Servo)
Jordy Keurntjes AVS1230
September 19th
5.
In what position must the flaps be to allow passengers to enter the cabin of the Seminole?
6.
Which flight control is used to control pitch on the Seminole?
7.
The flaps on the Seminole are ___________________ actuated.
A. Manually
B. Electrically
C. Hydraulically
D. Pneumatically
8.
The stabilator trim on the Seminole can be electrically or __________________ operated.
Cessna 172 Lab aircraft located in Hangar 2.
What type of flap does the 172R use?
Single Slotted Flaps What is Item A
Single Slotted Flaps
Item B
Elevator
Item C
Horizontal stabilizers Item D
Elevator trim tab
King Air Hangar 4
Item A
Trim tab for rudder
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Engineering Mechanics
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▸ View Available Hint(s)
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Engineering Mechanics
Statics (Equilibrium of a Particle)
Ayad A. M.
Q/ Use the conditions of equilibrium to solve the following problem
and find the magnitude of the resultant force acting on the screw eye
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F- 250 N
F- 150 N
30
105
9 68% O
底 )
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Datal
3
7
5
7
3
Data 2
-7
4
7
-9
7
8
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Data 3
Store the data in a 3x8 array (use variable name data), where each row is storing the corresponding set of row
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4
-9
1
1
5
6
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In Gotham City, the departments of Administration (A), Health (H), and Transportation (T) are
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amount of the services produced by the other departments and itself, as shown in Table 1. Suppose
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year,
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H.
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b) =PI()*B2^2 * B3
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Read and analyze the following questions and answer themvery carefully. Show your complete (show unit cancellation)and step-by-step solution and box your final answer. Use threedecimal places.
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د ميکانيك شهري 2021.pdf
UNIVERSITY OF BASRAH - COLLEGE OF ENGINEERING
DEPARTMENT OF CIVIL ENGINEERING
Subject: Engineering Mechanics-Static
Class: 1st year, 1st term
Exam. : Semester
Date: 16/3/2021
Examiner: Dr. Mazin, Dr. Aqeel, Dr.Ahid and Dr.Jaffar
Time: 1.5Hours
Q1] (10 Marks)
A- In Fig.A , If the resultant force acting on the bracket is to be 642 N directed
along the positive x axis, determine the magnitude of F.
B- In Fig.B , Determine the magnitude of the resultant force acting on the screw
eye and its direction measured clockwise from the x axis.
C- In Fig.C , Resolve the 100N force into components along the u and v axes, and
determine the magnitude of each of these components.
D- In Fig.D, Determine the moment of the force about point O.
300 N
60N
25°
32
45°
60°
505 N
50°
40N
Fig. A
50 N
Fig. B
400 N
100N
28°
18
2.12 m
Fig. C
2.12 m
Fig.D
Q2] (10 Marks)
A- In Fig.A , Replace the loading system by an equivalent resultant force and
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