Test SIS + RCS

Speed of the target

Relative bearing of the target

Range if the frequency is modulated FMCW.

Permits to discriminate clutter/moving targets

2.7

36

11.1

The pulse repetition frequency

The Doppler shift of the received signal

Pulse repetition period

The transmitted peak power

The ability to detect nose and tail radar targets, also in side lobes clutter. 


The ability to detect and track ground targets

The ability to detect high speed targets

By comparing the velocity of the received energy with the velocity of the transmitted energy.

By measuring the Doppler shift that occurs in the returning signal.

by comparing the magnitude of transmitted pulses with the magnitude of returned pulses

Generating the highly accurate clock signals used to generate radio frequency signals

Compensating noise in tracking due to own aircraft movements

Stabilizing the antenna rotation with respect to inertial reference (horizon)

antenna inertial stabilization (horizontal) / Automatic tilt control

Compensation of echoes (receiver): reduece noise in tracking

SAR calculations: very precise /accureate/low latency data

Display Ground / north stabilization

The best radar antenna configuration for covering 360 degrees around the aircraft is nose- mounted

The waveguides are mainly used for conducting high power pulses from the transmitter to the antenna

Radars typically use 28 VDC power

Synchronizer

Mixer

Duplexer

Circulator

Increases the antenna Gain.

Makes necessary increasing the waveguide run between circulator and receiver, to compensate

Reduces only the losses of the received echo

Reduces the losses in both the Transmitted RF and the Received Echo

Reduces the losses in the Transmitted RF

Allows a better detection range

Allows for the same detection range a smaller antenna

In fighters, to discriminate very near targets

To detect very big ships when sea state is very low.

Ships / Surface targets classification

To detect small targets at High Sea States

Uses ships movement to obtain shape

only one dimension

Straight and level flight, high constant speed, direct to the target

Orbit (circular) flight path centered in the target, maximum roll of 5º

Straight and level flight, high constant speed, perpendicular to the target.

The integration is much easier than in classic architecture radars.

The TRM matrix is very demanding in terms of cooling

There is no transmitter, but there is one receiver

should be always pressurized, using dedicated compressors

must have a minimum pressure differential with respect to cabin air

should be designed minimizing the number of joints, bends, and turns, to reduce insertion 
loss.

Admit structural stress, so they can be used to support other structures in the airframe

Air to Air Refueling Support System (AARSS)

Automatic Dependant Surveillance - Broadcast (ADS-B).

Advanced Surface Movement Guidance and Control Systems (A-SMGCS)

Traffic Collision Avoidance System (TCAS/ACAS).

Enhanced Traffic Collision Avoidance System (ETCAS)

Time to-go to the threat.

Distance to-go to the threat.

Time to-go to the CPA (Closest Point to Approach)

Distance to-go to the CPA (Closest Point to Approach)

Both TCAS will continue to request the crew to climb but at different rates than initially.

TCAS of aircraft B will request the crew to continue with the climb and TCAS of aircraft A will 
change to request the crew to descend.

Both TCAS will request the crew to descend.

The aircraft B (higher Mode S address) reverse the sense of its maneuver (Descends).

Mode 3/A: 03

Mode S: 12345A

Modo C: 4 dígitos SIN D1

Modo S: 6 dígitos en HEX

Modo 1: 2 dígitos (0-7)(0-3)

Modo 2: 4 dígitos (0-7)(0-7)(0-7)(0-7)

Modo 3/A: 4 dígitos (0-7)(0-7)(0-7)(0-7)

Modo 4: 3 pulsos

Modo 5: como modo S pero crypto

Protection against descent below minimum height. 





Landing gear up advisory

Windshear Detection and Alerting

Protection against altitude loss after take off


The use of aircraft inertial navigation system. 


The use of aircraft roll attitude signal.

The use current aircraft position and altitude referenced to a terrain elevation database to predict flight path conflicts with terrain elevation and provide graphic display of the conflicting terrain.

Landing gear interlock switch to obtain landing gear up-down status. 


Fuel system to compute aircraft weight in order to evaluate aircraft climb performance.

Radio altimeter

Air Data Computer (Altitude, Airspeed, Verditcal Speed, Temperature).

Aircraft Sensors (Angle of Attack, Flap position, Landing gear position). TRUE

IRS/AHRS. FMS/GPS. ILS/MLS. EFIS. Control Panel. TRUE

An accident or incident in which the airplane becomes out of flight crew's control with the result of a crash into ground. 


An accident or incident in which the airplane, under the flight crew's control, is intentionally subject to an emergency landing.

An accident or incident in which the airplane, under the flight crew's control, is inadvertently flown into terrain, obstacles, or water without either sufficient or timely flight crew awareness to prevent the event.

The aircraft height over terrain is too low to extend the landing gear.


The landing gear cannot be extended, therefore the flight crew need to perform an emergency landing.

For alerting the pilot that the landing gear is not armed when flying with the landing gear unarmed either below 500ft or slower than 159 knots.

Provide height over terrain display in final approach and low level flights (search and rescue, covert operation, etc).

Correct the baro-altitude errors at low altitude

Provide height over terrain to other aircraft systems

Replace baro-altitude at low altitude

As near as possible from displays output data corruption.

As near as possible from RALT antennas to minimize RF signal losses.

At fix distance from RALT antennas

Always in the main landing gear bay

TAWS to provide altitude over terrain for GPWS modes.

Audio Management System to provide altitude call-outs to the flight crew.

Hydraulic data to inhibit landing gear down command.

Displays System to provide radio-altitude data to flight crew

Is always catastrophic as the safety of the landing relies on the Radio Altimeter indication.

May be up to catastrophic on Category 3 precision approaches.

Depends on the category (minimum decision height) of the approach.

The Radio Altitude is only informative and has not safety effect.

The severity of RA failures depend of the precision approaches category.RA is the source of the decision height.

Cylinder

Sphere

Disk

Its RCS is approximately the same than the RCS of a PEC plane of dimensions 20x20 meters at 5 GHz.

Its RCS is approximately half of the RCS of a PEC plane of dimensions 20x20 meters at 5 GHz.

ts RCS is approximately double of the RCS of a PEC plane of dimensions 20x20 meters at 5 GHz.

Its RCS is approximately four times lower the RCS of a PEC plane of dimensions 20x20 meters at 5 GHz.

Its RCS is approximately double of the RCS of a PEC cylinder of radius equal to 2 meters and 10 meters long at 5GHz.

Its RCS is the same than the RCS of a PEC cylinder of radius equal to 2 meters and 10 meters long at 5 GHz.

Its RCS is approximately the same than the RCS of a PEC sphere of radius equal to 2 meters at 5GHz.

Its RCS is approximately half of the RCS of a PEC sphere of radius equal to 2 meters at 5GHz.

Its RCS is approximately a quarter of the RCS of a PEC sphere of radius equal to 2 meters at 5GHz.

Trihedral --> f3

Dihedral -->f3

Plate --> f2

sphere --> f

Straight edge --> f

Curved edge --> f-1

Corner --> f-2

Circular cylinder --> f2

Place the equipment as far as possible from the antenna to have appropriate losses and avoid excessive reflections

Ensure that VSWR is around 1.5:1

Have a correct antenna bonding (around 2.5 mOhms)

Place the equipment as close as possible from the antenna to have appropriate losses and avoid excessive reflections.

Have a homogeneous human machine interface to ensure the use is compatible.

It is not possible to install all these systems on the same aircraft, there will be too much interference among them.

A blanking system enables/disables RF transmission/reception ensuring sufficient RF interoperability of transmitters and receivers

When it is interrogated at 1090MHz

When it is interrogated at 1030MHz

Mode 2 is military

All civil transponder modes

Only modes 1, 2, C and A 


Civil mode S

ADS-B OUT

MADS-B Out

allows the measurement of the Doppler frequency.


has a range resolution not depending on the signal bandwidth.

has a range resolution depending on the pulse duration.

Relatively high frequencies and they have a high angular resolution

Relatively low frequencies and they have a high angular resolution.

Relatively high frequencies and they have a low angular resolution

Relatively low frequencies and they have a low angular resolution

dBsm = 10log10(σ)

dBsm = 10log10( σ^2)

dBsm = 20log10(|σ^1/2|)

dBsm = 20 log10(σ)

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