My Air Craft for Modifications

Something about my Aircraft B-737-400

Crew 2

Passengers 146 / 159, max. 189

Propulsion 2 Turbofan Engines

Engine Model CFM Intl. CFM56-3B2, CFM56-3C

Engine Power (each) 98 / 105 kN 22000 / 23500 lbf

Speed 933 km/h 504 kts

580 mph

Mmo (max. Mach) Mach 0.82

Service Ceiling 11.278 m 37.000 ft

Range 5.186 km 2.800 NM 3.222 mi.

Empty Weight 33.650 kg 74.185 lbs

max. Takeoff Weight 68.039 kg 150.000 lbs

max. Landing Weight 56.246 kg 124.000 lbs

Wing Span 28,88 m 94,8 ft

Wing Area 105,4 m² 1135 ft²

Length 36,40 m 119,4 ft

Height 11,07 m 36,3 ft

First Flight 19.02.1988

Production Range 1988-2000

Total Production 486

Courtesy of British Airways

Instrument Landing System ( ILS) (A synopsis)

Instrument Landing System ( ILS)

1. ILS is the only Navigational Aid for Landing and final Approach having two transmitters installed at far end of the Runway.This is system that uses VHF & UHF radio waves. ILS has been in usage since 1946.This is only because of ILS system that today the AFCS has been very efficient even during automatic landing.
2. Unlike ILS the VOR,ADF and DME are the navigational aid for airway or air route.
3. The two subsystems of ILS systems are (1) Localizer (LOC) (2) Glide Slope (GS)

Localiser

The horizontal navigational aid for landing of and air craft is called localiser that sets the plane aligned with the center line of the runway.

The localizer transmits VHF with frequency range of 108-112 MHz with increment of 0.5 MHz.

The Localiser transmits two lobs let & right with 90 Hz & 150 Hz.The lobs cut each other or extended center line of the runway.the localiser have also there morse code.the lobs as shown as under:

Glide Slope

The vertical navigational aid for landing is called glide slope(GS).Glide Slope transmit UHF of 328.6 - 335 Mhz.The glide slope frequency is automatically set when the crew tune the frequency of localier.

Marker Beacons

In Instruments landing system the visual and audible cues to the crew are provided by an other very important navigational aid that is called "MARKER BEACONS".The marker beacons are sites at two or three distances on the extended center lines of the runway and provides the NavAid to confirm the crew of progress.They transmit 75 Mhz with there unique morse code with 3-4 W of power. The marker beacons are divided in to three categories such as (1) Outer Marker (2) Middle Marker  (3) Inner Marker

(1) Outer Marker (OM): the outer marker is sited at 4 - 7 miles from runway thresholds.It Transmit dash dash(- -) morse code by operating at frequency of 400 Hz.When the aircraft approaches at Outer marker the Cyan light in on on ILS instrument and the OM icons gets high on the display.

(2) Middle Marker (MM): the milddle marker is sited at 3500 ft from runway thresholds.It Transmit alternating dash dot(- .) morse code by operating at frequency of 1300 Hz.When the aircraft approaches at Outer marker the Yellow light in on on ILS instrument and the MM icons gets high on the display.

 (3) Inner Marker (MM): the inner marker is sited at 2000 ft from runway thresholds.It Transmit dot dot(..) morse code by operating at frequency of 3000 Hz.When the aircraft approaches at Outer marker the White light in on on ILS instrument and the IM icons gets high on the display. 

MIL-STD-1553

Something About MIL-STD-1553......
1)Its a Military Standard of Aviation Data Bus Its used to Interface different components ,modules with commons data bus.

2)MIL-STD-1553B defines the term Time Division Multiplexing (TDM) as 
“the transmission of information from several signal sources through one 
communications system with different signal samples staggered in time to 
form a composite pulse train.”

3)Data Rate 1 MHz 
Word Length 20 bits 
Data Bits / Word 16 bits 
Message Length Maximum of 32 data words 
Transmission Technique Half-duplex 
Operation Asynchronous 
Encoding Manchester II bi-phase 
Protocol Command/response 
Bus Control Single or Multiple 
Fault Tolerance Typically Dual Redundant, second 
bus in “Hot Backup” status 
Message Formats Controller to terminal 
Terminal to controller 
Terminal to terminal 
Broadcast 
System control 
Number of Remote Terminals Maximum of 31 
Terminal Types Remote terminal 
Bus controller 
Bus monitor 
Transmission Media Twisted shielded pair 
Coupling Transformer and direct 

Courses Domains in Radar
Following are the domain of Coursers covered in Radar System Communication.
1)Electromagnetic waves
2)Microwave and radiating system
3)Signals & Systems
4)Analogue and Digital Communication/ Electronics
5)Control System

Did you know!!!!!!!!!

* Full Form of RADAR  is Radio Detection and Ranging.
*Radar is uses to detect object,its range,altitude and speed by using Radio waves.
* Its was secretly developed before and during World War II.

COMMAND SIGNAL DETECTION

COMMAND SIGNAL DETECTION
Chapter 4  COMMAND SIGNAL DETECTION
 Automatic Flight Control by E.H.J Pallet & Shwan Coyle.


Signal & Sensor

Electrical command from Pilot to Control Surface or A control Surface's respond in the form of voltage is call command signal And the sensors which detects are call command signal sensor & transducer.
These sensors are of inductive type and works on the basis of transformer  with fixed primary winding & variable secondary wingdings.

Types of command signals:

There are followed type of these inductive type command signals sensors

1) E & I Bar Sensor
2) Moving  vane Sensors
3) Synchros

E & I Bar Sensor:

This is and inductive type sensor used for position attitude changes.The AC signal is applied on Center limb of 'E' when there is defection in 'I'
this shows that there is an attitude changes in respective control surface with this E&I bars sensor is coupled.And if there is no deflection means
the control surface has maintained it leveled position.



Moving Vanes Sensors

This inductive type sensor is also used for attitude changes with their respective steering gyroscope.
The two sensor are used.One is having its vane in the inner gimbals of gyro for pitch attitude where as the other is having in the outer gimbals for roll attitude sensing.
The AC signal is applied on the 1 and 3 ends of the sensor with 180 degree phase shift.
If the vane is at the center position 2 this means that the aircraft is at level flight.if the vane is varied between the 1 & 2 or 2 &3 then it means
there is and attitude change with respective control surfaces.
 

Synchros

The synchronous self inductive type signal detectors are called synchros and are of type:

1) Torque Synchro
2) Control Sysnchro
3) Differential Synchro
4) Resolver

Torque Synchro: This is used for a very small movement in aircraft.This is use to detect angular position.And in instruments
On transmitting end (TX) its had generator and generating shaft whereas on receiving End (TR) it had AC motor.


 
Control Syncho: This is used to detected the signal from large movements such as control surfaces.It has same function as torque but there is a Transformer on Receiving end (CT).


Differential Synchro: The synchronous signal detector that uses the error difference between two angular position us called differential synchro.Its uses TDX/CDX in between
Torque and Control Sysnchro and the  symbols are given as:


Resolver: An interesting sysnchro that converts cartisan co-ordinates systems to Polar Co-ordinates and vice versa is called Resolver.

Amazing Information

Amazing Information

  (Chapter11) of Automatic Flight Control by E.H.J Pallet & Shawn Coyle

--Fly by wire is the concept that provide effective computer link between the
pilot control and control surface.

--This concept was implemented first in Concorde(elevon control)
& Boeing 767 for its wing control spoilers.

-- Airbus A320 was the only plane which FBW was designed for.

--  The increased effectiveness by Side-Stick(*1) Control column

Advantages of FBW Control System:

1) Weight Saving
2) Reduced Maintenance Time
3) Gust Load Alleviation
4) Automatic Manoeuvre  Envelop Protection
5) Improved Handling
6) Fuel saving

(*1) Side Stick Control Column id the replacement of Control Column/Wheel Control Column.
     A light weight control stick Which is fixed by Pilot Arm in Cockpit                        

 Architecture of FBW

In advacne FWB Conrol System There are two basic termonologies are used
such Arcitecture & Conrol Laws.This system is also called actvie control system.

Architecture

The genaral Layout of the components such as computers and thier function are
called architecture.These copomuter are working with redundancy to inhance the stability
and the less failure system
In A320 there are seven operational computer working with ARINC 429
DATa Bus in communication among them and listed as under

1) ELACs Elevator/Aileron Computer   (2)
2) SECs  Spoilrer/Elevator Comouter  (3)  
3) FACs  Flight Augmentation Computer(2)

Control Laws

The maanner in which the operational computers are expected to control the control surfaces are called Colrol Laws
Keeping in mind the conpcet of redundancy & the safety factors  these conrols law are listed as under with there respective comuters

Normal Conrtol Law    ---ELACs
Alternate Conrol Law  ---SECs
Direct Control Law    --Strick to Elevator/Direct Control
Mechanical Backup     --Mechanical Link to the Pitch Trim

Special C-Star(C*) Control Law:

C* is the special type of Pitch Control Law which has much acceptance in commercial airlines.
This is a flight path command control law even at low speed including pitch command rate.In general the pilot is
able to select a particular flight path with particular angle such as level flight.Once this particular flight path with angle is
achieved then if Pilot releases the control stick this law ensures that that particular angle is retained
By introduction of pitch ate command this helps us to overcome Lags& over pitch activity allow speed and in flare mode at 50 ft above the
ground.