02 system rsm970-ibis rev3[1]

RSM 970 S Training

CDRL: N/A Doc No: Rev: 3All information contained in this document remains the sole and exclusive property of the THALES Air System and shall not be disclosed in whole or in part by the recipient to third persons without the prior written consent of Thales Air System as the originator.

Air Systems Division

RSM 970SSYSTEM PRESENTATION

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RSM 970S SYSTEM Syllabus

SYLLABUS

PRINCIPLES

STANDARD CONFIGURATION

KEY FEATURES

FUNCTIONAL PRESENTATION

MAINTENANCE

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PRINCIPLES

RSM 970S SYSTEM PRINCIPLES

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FUNDAMENTAL PRINCIPLES OF SECONDARY SURVEILLANCE RA DARS

Interrogators on the ground generate 1030MHz RF pulse modulated messages to aircraft. These interrogation messages are known as INTERROGATION MODES.

The transponders carried on these aircraft detect the messages and answer by sending back 1090MHZ RF pulse modulated messages known as REPLIES.

Receivers on the ground look for these RF signals and process them for analysis by external equipment (extractors, processors and display console).

Transponder

SSR Radar

Aircraft

ATCC

REPLY: identification or altitude

Tracks and/or plots

INTERROGATION: Request for identificationor altitude

• Frame pulse detection• Range measurement• Azimuth measurement• Altitude decoding• Identif ication decoding

(1030MHz) (1090MHz)

Transponder

SSR RadarSSR Radar

Aircraft

ATCCATCC

REPLY: identification or altitude

Tracks and/or plots

INTERROGATION: Request for identificationor altitude

• Frame pulse detection• Range measurement• Azimuth measurement• Altitude decoding• Identif ication decoding

(1030MHz) (1090MHz)

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PURPOSE

The RSM970S SECONDARY RADAR is designed to locate and identify aircraft.

Unlike a primary radar, it requires the active participation of aircraft which must be fitted with a specific equipment : a TRANSPONDER.

This secondary surveillance radar (SSR) interrogates aircraft by means of RF pulse trains forming INTERROGATION MODES.


t

P1 P3

0.8µs 0.8µs

t

P1 P3

0.8µs 0.8µs

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“SSR” INTERROGATION MODES

1 , 2 , 3 Military modesA , C Civilian modes A = Identification mode3 = A C = Flight Level mode

Mode 1

Mode 2

Mode 3 / A

Mode C

P1t = 3µµµµs

t = 5µµµµs

t = 8µµµµs

t = 21µµµµs

P1

P1

P1

P3

P3

P3

P3

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“SSR” REPLIES

X Pulse(Usually absent)

F1 / F2 - 2 FRAMING PULSES (Bracket Pair )

From 0 up to 12 Data pulses (Reply Code )

F1 F2C1 A1 C2 A2 C4 A4 B1 D1 B2 D2 B4 D4X

0.45µs

20.3µs

1.45µs

If pulse present ==> bit = 1

If pulse absent ==> bit = 0

“SSR” REPLIES

X Pulse(Usually absent)

F1 / F2 - 2 FRAMING PULSES (Bracket Pair )

From 0 up to 12 Data pulses (Reply Code )

F1 F2C1 A1 C2 A2 C4 A4 B1 D1 B2 D2 B4 D4X

0.45µs

20.3µs

1.45µs

If pulse present ==> bit = 1

If pulse absent ==> bit = 0

Aircraft transponders interpret these questions and in turn, send out replies.

Replies are built with framing pulses encapsulating pulsed bits making data words. These words are known as CODES.

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All Call interrogation mode - AC

AC surveillance for SSR aircraft only: P1 - P3 - P4 Short 0.8µs (P4S).

AC surveillance for SSR and MODE S aircraft: P1 - P3 - P4 Long 1.6µs (P4L).

Note: P4L is not used in practice at the moment.

MODE S SECONDARY RADAR - INTERROGATION MODES

P1

8µs for identification

P3 P4

2µs

0.8µs 0.8µs 0.8µs1.6µs

21µs for altitudeP1

8µs for identification

P3 P4

2µs

0.8µs 0.8µs 0.8µs1.6µs

21µs for altitude

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Note: P2 inhibits the SSR transpondersP6

Guard intervalSync phase reversal

1st data bit last data bit0.25µs

UF

2µs 2.75µs

P1

0.8µs

P2

0.8µs

P6

56 or 112 bits, 0.25 µs each1.25µs 0.5µs0.5µs

UF

P6 (56 bits) = 16.25µs

P6 (112 bits) = 30.25µs

Note: P2 inhibits the SSR transpondersP6



UF

P6



UF

2µs 2.75µs

P1

0.8µs

P2

0.8µs

P6

56 or 112 bits, 0.25 µs each1.25µs 0.5µs0.5µs

UF

P6 (56 bits) = 16.25µs

P6 (112 bits) = 30.25µs

All Call and Roll Call interrogation mode – AC / RC

Acquisition, surveillance and data link for MODE S aircraft.

MODE S SECONDARY RADAR - INTERROGATION MODES

Note: UF message (Uplink Format) is encoded withDPSK modulation

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MODE S INTERROGATION FORMAT

FORMAT NO. (UF) MESSAGE LENGTH MODE S INTERROGATION R EQUEST

0

1, 2 and 3

4

5

6, 7, 8, 9 and 10

11

12, 13, 14 and 15

16

17, 18 and 19

20

22 and 23

24 (2-bit field)

21

Short (56 bits)

Short (56 bits)

Short (56 bits)

Short (56 bits)

Long(112 bits)

Long (112 bits)

Long (112 bits)

Long (112 bits)

Short air-air surveillance (ACAS)

Not defined

Surveillance, altitude request

Surveillance, identify request

Not defined

Mode S-only all-call

Not defined

Long air-air surveillance (ACAS)

Not defined

Comm-A, altitude request (SLM *)

Comm-A, identify request (SLM)

Not defined

Comm-C (ELM **)

* SLM: Standard Length Message** ELM: Extended Length Message

-

-

-

-

-

Refer to ICAO Annex 10

transmitted by the radar

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Preamble 8µs

Data block 56µs or 112µswith 1 bit = 1µs

4.5µs

0.5µs 0.5µs 0.5µs 0.5µs 0.5µs 0.5µs

DF

Bit 1 Bit 2 Bit 3 Bit 4 N -1 Bit N

8µs 9µs

0 0 1 0 0 0 1

DF example

Note: DF message (Downlink Format) is encoded with pulse modulation

MODE S SECONDARY RADAR – MODE S REPLY

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FORMAT NO. (DF) MESSAGE LENGTH MODE S INTERROGATION

0

1, 2 and 3

4

5

6, 7, 8, 9 and 10

11

12, 13, 14 and 15

16

17, 18 and 19

20

22 and 23

24 (2-bit field)

21

Short (56 bits)

Short (56 bits)

Short (56 bits)

Short (56 bits)

Long (112 bits)

Short air-air surveillance (ACAS)

Not defined

Surveillance, altitude reply

Surveillance, identify reply

Not defined

Mode S-all-call reply

Not defined

Long air-air surveillance (ACAS)

Not defined

Comm-B, altitude reply (SLM *)

Comm-B, identify reply (SLM)

Not defined

Comm-D (ELM **)

* SLM: Standard Length Message** ELM: Extended Length Message

-

-

-

-

-

Long (112 bits)

Long (112 bits)

Long (112 bits)

Refer to ICAO Annex 10processed by the radar

MODE S REPLY FORMAT

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MODE S SECONDARY RADAR – Example of interrogation & reply format

UF11

DF11

AC INTERROGATION MODE

P1 - P2 - P6UF11

From “THALES” radar what is your specific 24 bit S Mode address ?

S MODE ADRESS REPLY

Preambule - DF11

Hi “THALES” radar, my specific 24 bits S Mode address is ……

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TRANSMISSION PROBLEMS

Transponder triggered via a sidelobe

Antenna axis

Reply received via a sidelobe

Σ Antenna radiation pattern

Main lobe

Secoundary or sidelobe


Secondary surveillance radars use highly directive antennas.

The radiation pattern of such antennas is characterised by :

•a very narrow major beam width,•low-amplitude secondary lobes.

The use of such a system results in two possibilities :

•the transponder of an aircraft answers to a question emanating from the antenna via one of its secondary lobes ,

•a reply is picked up by the antenna via one of its secondary lobes.

In both cases, the antenna axis does not correspond to the direction of the aircraft so that there would be a major positioning error.

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When two aircrafts cross each other, their replies overlap. This results in mixing of the pulses, making them not easily usable by the extractors.

A

Bpulses from A

pulses from B

Garbling withoverlapping

Garbling withRF mixing

pulses from A

pulses from B

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Likewise, when a reply is reflected by an obstacle, it reaches the receiver with a delay with respect to the direct reply.

Multipath phenomena are a limitation to Mode S implementation

direct pulses

reflected pulses

garbling

direct path

reflected path

Multipath trajectories caused by a reflection in the elevation beam

Reflector (ground)


These risks may be lessened by use of the following means :

•on interrogation (ISLS and IISLS processes), the aircraft transponder detects interrogation via a side lobe but doesn't reply.

Mode S:

ISLS is implemented during Selective calls

IISLS is not implemented during Selective calls

•on reception (RSLS process), the secondary radar receiver detects and eliminates signals received through the side lobes,

Mode S :

RSLS is only used between Σ and Ω to cancel replies from the secondary lobes.

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ISLS PROCESS in SSR

ISLS = Interrogation with Side Lobe Suppression

channel ΣΣΣΣmain lobe

control channel ΩΩΩΩ

aircraft in axis of main lobe

Looking to their amplitudes,P1 & P3 are much greater than P2

the transponder is triggered

Looking to their amplitudes, P1& P3 are less than P2

the transponder is NOT triggered

P1 P2 P3

P1 P2 P3

aircraft in a sidelobe

2µs

2µs

ISLS PROCESS in SSR

At interrogation, the interrogator transmits :

•pulses P1 and P3 on the Σ channel and

•2 µs after P1 the pulse P2 on the Ω channel.

The energy radiated by the main lobe of the ΣΣΣΣ channel is greater than the energy radiated by the ΩΩΩΩ channel and the energy radiated by the ΩΩΩΩ channel is greater than the energy radiated by the ΣΣΣΣchannel sidelobes.

When the transponder is in the main lobe of the ΣΣΣΣ channel (antenna axis), it receives pulse P1 at a level upper than for the pulse P2 + K1 dB level and replies to interrogations when P1 ≥ P2 + K1 dB.

Note: 0 dB ≤ K1 ≤ +10 dB

If the level of P2 exceeds the level of P1, meaning that the interrogation has been transmitted via a secondary lobe, the transponder does not reply.

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ISLS PROCESS in Mode S

P2

P3P1 P4ΣΣΣΣ CHANNEL

Ω Ω Ω Ω CHANNEL

All Call interrogation mode - AC

All Call and Roll Call interrogation mode – AC / RC

Interrogation through the main lobe

Interrogation through a sidelobelobe

Identical to ISLS process in SSR

ΣΣΣΣ CHANNEL

Ω Ω Ω Ω CHANNEL

ΣΣΣΣ CHANNEL

Ω Ω Ω Ω CHANNEL

P6P1 P2

P5

P6P1 P2

P5

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TRANSMISSION BY THE INTERROGATOR

ΩΩΩΩ

ΣΣΣΣ

direct path

reflected path

reflecting obstacle

aircraft outside the Σ main lobe

ΣΣΣΣ

ΩΩΩΩ

P1

P1cont P2

P3

P1cont is attenuated with respect to P2


IISLS PROCESS

IISLS = Improved Interrogation with Side Lobe Suppr ession

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ΩΩΩΩ

ΣΣΣΣ

direct path

reflected path

reflecting obstacle

P1+ P1cont

P2 P3

Reception via the Σ main lobe

P1 variable position accordingto the delay due to the reflection

P1cont P2 P3

Reception outside the Σ main lobe


IISLS PROCESS

IISLS = Improved Interrogation with Side Lobe Suppr ession

RECEPTION BY THE TRANSPONDER

aircraft outside the Σ main lobe

IISLS PROCESS

When the aircraft is in the main lobe, pulses P1cont and P1 will arrive at the same time with a resulting level greater than P2 ; the transponder then replies to the interrogation.

Further, the transponder does not answer to interrogations which do not strictly correspond to SSR standards.

When the transponder rejects an interrogation due to interrogation via a secondary lobe or not complying with standards, it is self inhibited for 35 µs.

Any other interrogation arriving during this period(in particular the reflected ones) will receive no reply.

The IISLS is implemented on A/C interrogations only, not in mode S operation for it has a tendency to block the transponders.

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RSLS = Reception with Side Lobe Suppression

RSLS PROCESS

Looking to their amplitudes, pulses received via Ω are greater

than pulses received via channel Σ sidelobe.The reply is NOT DECODED

channel Σ

Looking to their amplitudes, pulses received via channel Σ main lobeare greater than pulses received via Ω.

The reply is DECODED

control channel Ω

ΣΣΣΣ

ΩΩΩΩ

ΩΩΩΩ

ΣΣΣΣ

aircraft in a sidelobeaircraft in axis of main lobe

RSLS PROCESS

The antenna used with the equipment features Σ and Ω channels ,each having a different directivity pattern.

•The ΩΩΩΩ channel has almost the same gain in all directions ; it is at least equal to the gain of the secondary lobes of the sum pattern ΣΣΣΣ.

•The main lobe of the ΣΣΣΣ channel has a gain greater than that of the ΩΩΩΩ channel.

The receiver compares the amplitude V of the signals received via the Σ and Ω channels.

•If V ΣΣΣΣ > V ΩΩΩΩ : the signal is from the ΣΣΣΣ main lobe and is to be taken into account.

•If V ΣΣΣΣ < V ΩΩΩΩ : the signal is from a ΣΣΣΣ secondary lobe; the receiver flags the corresponding signal for the extractor equipment.

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RSLS PROCESS

Secondary lobe suppression

reception angle with VΣ > V Ω

antenna axis

Σ pattern

Ω pattern

+10 dB

0 dBK1

RSLS PROCESS

The RSM970S attributes a coefficient K1 (operational parameter adjusted from 0 up to + 10 dB) to the Ω channel in order to make sure that the gain of this channel is higher than that of any secondary lobe of the Σ channel.

In addition, the gain of the Ω channel is reduced in the main Σ lobe direction.

•the gain of the ΣΣΣΣ channel is maximum on the antenna axis,•the gain of the ΩΩΩΩ channel is minimum on the antenna axis.

Mode S : RSLS is activated on A/C interrogations (presence of P2 on Ω channel) and on A/C/S All call interrogations (presence on P5).

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MONOPULSE PROCESS

Antenna axisantenna rotation

ΣΣΣΣ

∆ ∆ ∆ ∆

ΣΣΣΣ

∆ ∆ ∆ ∆

ΣΣΣΣ

∆ ∆ ∆ ∆

a

bc

position a position b position c

Pulses received from aircraft in :

ΣΣΣΣ

∆ ∆ ∆ ∆ right-hand side lobe

∆ ∆ ∆ ∆ left-hand side lobe

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MONOPULSE PROCESS

Antenna radiation patterns

ΩΩΩΩ channel

ΣΣΣΣ channel

∆∆∆∆ channel

Antenna axis

ΣΣΣΣ ΩΩΩΩ

∆∆∆∆ reception lobe

transmission & reception lobes

Angle error measurement

The monopulse technique provides a means to measure the angle error for each pulse of the reply, this providing a better accuracy for azimuth position and an accurate way to discriminate garbled pulses.

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Every pulse is received via the Σ pattern with an amplitude A1 and via the ∆ pattern with an amplitude A2.

The amplitude ratio A2/A1, represents the pointing error, i.e. the angle between the antenna axis and the reception azimuth (Off Boresight Angle).

To get the angle error voltage, the RSM970S calculates the following ratio :

Vangle error =

and the sign = cos Θ

where Θ = phase shift between Σ and ∆ signals( 0° for LH sidelobe and 180° for RH sidelobe)

The azimuth accuracy is maximum along the antenna axis and the function f ( V angle error ) is proportional to the pointing error in the region of the main lobe.


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MONOPULSE PROCESS


angle error voltage = cos θ = cos θ

with θ = ∆ to Σ phase shift

V∆VΣ

A2A1

OBA

A1

A2

A

∆∆∆∆

ΣΣΣΣ

0° θ = 180 °θ = 180 °θ = 180 °θ = 180 °θ = 0 °θ = 0 °θ = 0 °θ = 0 °

Amplitude as a functionof the OBA

∆ Σ

Σ2

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MONOPULSE PROCESS

Main lobe refinement during reception

OBA variable according to K2

ΣΣΣΣ channel

∆∆∆∆ channel

+10 dB

-10 dB

K2

Main lobe refinement during reception

The difference in amplitude of the pulses received on both channels is maximum when the reply comes from a transponder located on the antenna axis.

RSM970S attributes a factor K2 (operational parameter), from -10 dB up to +10 dB, to the amplitude of the ∆ channel, in order to adjust the beamwidth of the Σ main lobe.

Note: -10 dB ≤ K2 ≤ +10 dB

With Mode S operation, K2 is used to increase the number of interesting pulses on Σ channel.

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MONOPULSE PROCESS

Angle error measurement∆∆∆∆ = 0

ΣΣΣΣ = ∆∆∆∆ΣΣΣΣ

∆∆∆∆

θθθθ(°)

A (dB)

0

≈≈≈≈ 3.2°+ 1000

OBA (mV)

θθθθ(°)

- 1000

0

Σ and ∆∆∆∆ curves represent “Sum” and “Difference” radiation patterns near the antenna radiation axis.

∆ ∆ ∆ ∆ / Σ/ Σ/ Σ/ Σ curve represent ∆ / Σ∆ / Σ∆ / Σ∆ / Σ ratio variation as a function of the OBA.

Example (in analog) of OBA computed by MDR with:

K1 = +10 dBK2 = -10 dB

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TVBC (TIME VARIABLE BASE CLIPPING)

TVBC validation

Log Σ

Time / range

0

1

noise

variation of TVBC law severity

TVBC (TIME VARIABLE BASE CLIPPING)

The RSM970S equipment includes a system which eliminates the replies whose levels are too low in the nearby zone.

This system works by validating pulses only if they exceed a threshold voltage varying with time.

Non mode S radar : TVBC is applied on log Σ pulses only

Mode S radar : TVBC is applied on both log Σ pulses and log ∆ pulses

In the basic version, these laws decrease by 6 dB per range octave, corresponding to propagation losses in space (1/R2).

The choice of different laws permits an accurate adjustment of the TVBC efficiency according to the environmental conditions.

The equipment also allows these laws to be modified in range and to be selected as a function of azimuth.

Several laws are fully programmable on site by the operator.

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INTERROGATION SEQUENCING

SSR Interrogations

P1 P3 P1 P3 P1 P3 P1 P3

Mode A Mode C Mode A Mode C

Keys: AC = All-Call

RC = Roll-Call

SSRAC

SSRAC

SSRAC

SSRAC

SSRAC

SSRAC

SSRAC

SSRAC

SSRAC

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INTERROGATION SEQUENCING

Mode S Interrogations

P1 P2 P6

Mode S-onlyall-call

P1 P3 P4S

Mode A

2.5 ms

ACRCAC RCAC RC AC RC

5 ms

RC = Roll-Call

Keys: AC = All-Call

P1 P2 P6 P1 P2 P6 P1 P2 P6 P1 P2 P6

RC1 RC2 RC3 RC4

Interrogations Listening windows

Reply to Reply toRC1

Reply toRC2

Reply toRC3RC4

UF11 8µS

P1 P2 P6

Mode S-onlyall-call

P1 P3 P4S

Mode C

UF11 21µS

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ALL-CALL LOCKOUT PROTOCOL

Example2 scans to acquire,RC…. + 2 scans before locking (to do not lock onto a reflection)(the number of scans before locking is an operational parameter)

ENTERINGMODE S

AIRCRAFT

AC RC AC RC

Lock-outcommandAcquisition No AC reply A/C reply

LOCKED-OUTMODE S

AIRCRAFT

MODE A/CAIRCRAFT

18s

ALL CALL LOCKOUT

• Purpose : To reduce the number of fruit for a given station (replies corresponding to interrogations generated by another station).

• Principle : A radar station can lock the aircraft transponders so that they will not answer later All call interrogations emanating from this station.

• The aircraft transponder recognises the II (Interrogator Identifier) or SI (Surveillance Identifier) code allocated to the station.

• The transponder will remain locked for a standard time (18 sec).

Mode S all-call replies are made or not made to a Mode S radar station according to:

- the II (Interrogator Identifier)

- or SI (Surveillance Identifier) code allocated to the station.

II/SI code definition

The II/SI code is a site dependent parameter:

− Interrogator Identifier (II code from "0" to "15"; the "0" value is to be avoided following ICAO recommendations ),

− Surveillance Identifier (SI code from "1" to "63" ).

CAUTION

the II / SI code is assigned by the local authority

it must not be modified by the operator

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Mode S radar station main features

surveillance of SSR-only and Mode S equipped aircraft via all-call interrogations, acquisition of Mode S aircraft via Mode S all-call interrogations, surveillance of acquired Mode S aircraft via roll-call interrogations, data transmission/reception to/from acquired Mode S aircraft using roll-call

interrogations, message broadcast to all Mode S aircraft, messages broadcast from Mode S aircraft, surveillance data link between Mode S stations (surveillance network).

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Reply processing

The Mode S radar station processes SSR or Mode S replies:

processing of SSR reply received from any aircraft:• detection of the transponder frame pulses,• range measurement,• azimuth measurement by monopulse processing,• altitude report by decoding the "C" code reply,• identification by decoding the "A" code reply,

processing of Mode S reply received from Mode S transponder:• detection of Mode S reply preamble and data block,• range measurement,• azimuth measurement by monopulse processing,• identification by decoding the aircraft address from all-call reply,• flight parameters (at least "A" code and Flight Level or "C" code) and

messages by decoding Mode S roll-call replies.

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Surveillance protocols

The Mode S radar station can request surveillance data from a Mode S transponder via a surveillance or Comm-A interrogation.

The transponder having recognised its address sends the required data to the radar station via a surveillance or Comm-B reply as required.The Comm-B reply enables enhanced surveillance.

The "surveillance, altitude" reply and the "Comm-B, altitude" reply contain : altitude: code C (by 50- or 25-feet steps) requested at each antenna scan, flight status:

• alert condition when identity code A has been changed by the pilot,• SPI (Special Position Indicator) condition,• aircraft airborne or on the ground.

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Surveillance protocols

The "surveillance identity" reply and the "Comm-B identity" reply contain :

identity: code 3/A (same as SSR) requested by the station in the first roll-call interrogation following aircraft acquisition (done again if OBA is not correct),

flight status: same data as above.

In surveillance or Comm-A interrogations made during roll-call periods:− aircraft altitude is required every antenna scan,− aircraft identity is required at acquisition (any change being indicated in flight status),

on periodic request, at least every 18 s.Once aircraft have been acquired, one interrogation (altitude request) is performed per aircraft and per antenna scan.

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Air-air surveillance (ACAS) protocol

An Airborne Collision Avoidance System (ACAS) can request surveillance data from a Mode S transponder via an air-air surveillance interrogation.

The transponder having recognised its address sends the required data to the ACAS via an air-air surveillance reply,

this reply being fruit for the radar station .

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REGISTER ALLOCATIONRegister No. Assignment Minimum update rate

Not valid

Unassigned

Linked Comm-B, segment 2



Extended squitter airbone position

Extended squitter surface position

Extended squitter status

Extended squitter identif ication and type

Extended squitter airbone velocity

Extended squitter event-driven information

Air/air information 1 (aircraft state)

Air/air information 2 (aircraft intent)

Reserved for air/air state information

Reserved for ACAS

Data link capability report

Reserved for extension to data link capability report

Common usage GICB capability report

Mode S specif ic services capability report

Aircraft identif ication

Aircraft registration number

Antenna positions

Reserved for antenna position

Reserved for aircraft parameters

Aircraft type

Unassigned

0016

0116

0216

0316

0416

0516

0616

0716

0816

0916

0A16

0B16

0C16

0D16

-0E16

0F16

1016

1116

-1616

1716

1816

-1F16

2016

2116

2216

2316

2416

2516

2616

-2F16

N/A

N/A

N/A

N/A

N/A

0.2 s

0.2 s

1.0 s

15.0 s

0.2 s

variable

1.0 s

1.0 s

To be determided

To be determided

< 4.0 s

5.0 s

5.0 s

5.0 s

5.0 s

15.0 s

15.0 s

15.0 s

15.0 s

15.0 s

N/A


Register No. Assignment Minimum update rate

Not valid

Unassigned




Extended squitter airbone position

Extended squitter surface position

Extended squitter status

Extended squitter identif ication and type

Extended squitter airbone velocity

Extended squitter event-driven information

Air/air information 1 (aircraft state)

Air/air information 2 (aircraft intent)

Reserved for air/air state information

Reserved for ACAS

Data link capability report

Reserved for extension to data link capability report

Common usage GICB capability report

Mode S specif ic services capability report

Aircraft identif ication

Aircraft registration number

Antenna positions

Reserved for antenna position

Reserved for aircraft parameters

Aircraft type

Unassigned

0016

0116

0216

0316

0416

0516

0616

0716

0816

0916

0A16

0B16

0C16

0D16

-0E16

0F16

1016

1116

-1616

1716

1816

-1F16

2016

2116

2216

2316

2416

2516

2616

-2F16

N/A

N/A

N/A

N/A

N/A

0.2 s

0.2 s

1.0 s

15.0 s

0.2 s

variable

1.0 s

1.0 s

To be determided

To be determided

< 4.0 s

5.0 s

5.0 s

5.0 s

5.0 s

15.0 s

15.0 s

15.0 s

15.0 s

15.0 s

N/A


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REGISTER ALLOCATION

ACAS active resolution advisory3016

3116-3F 16

4016

4116

4216

4316

4416

4516

4616

4716

4816

4916

-4F16

5016

5116

5216

5316

5416

5516

5616

47 16-5E16

5F16

6016

6116

6216

-6F16

7016

-E016

E1 16-E216

E316

-F016

F116

F2 16-FF 16

Unassigned

Aircraft intentionNext w ay-point identif ierNext w ay-point position

Next w ay-point information

Meteorological routine air report

Meteorological hazard reportReserved for f light management system Mode 1

Reserved for f light management system Mode 2VHF channel reportUnassigned

Track and turn reportPosition report coarse

Position report f ineAir-referenced state vector

Way-point 1Way-point 2Way-point 3

UnassignedQuasi-static parameter monitoring

Heading and speed reportExtended squitter emergency/priority status

Reserved for e xtended squitterUnassigned

Reserved for Mode S BITEUnassignedReserved for military use

Unassigned

N/A

1.0 s1.0 s1.0 s

0.5 s

1.0 s

1.0 sTo be determided

To be determided5.0 sN/A

1.0 s0.5 s

0.5 s0.5 s

5.0 s5.0 s

5.0 s

N/A0.5 s

1.0 s1.0 s

N/A

N/AN/ATo be determined

N/A


ACAS active resolution advisory3016

3116-3F 16

4016

4116

4216

4316

4416

4516

4616

4716

4816

4916

-4F16

5016

5116

5216

5316

5416

5516

5616

47 16-5E16

5F16

6016

6116

6216

-6F16

7016

-E016

E1 16-E216

E316

-F016

F116

F2 16-FF 16

Unassigned

Aircraft intentionNext w ay-point identif ierNext w ay-point position

Next w ay-point information

Meteorological routine air report

Meteorological hazard reportReserved for f light management system Mode 1

Reserved for f light management system Mode 2VHF channel reportUnassigned

Track and turn reportPosition report coarse

Position report f ineAir-referenced state vector

Way-point 1Way-point 2Way-point 3

UnassignedQuasi-static parameter monitoring

Heading and speed reportExtended squitter emergency/priority status

Reserved for e xtended squitterUnassigned

Reserved for Mode S BITEUnassignedReserved for military use

Unassigned

N/A

1.0 s1.0 s1.0 s

0.5 s

1.0 s

1.0 sTo be determided

To be determided5.0 sN/A

1.0 s0.5 s

0.5 s0.5 s

5.0 s5.0 s

5.0 s

N/A0.5 s

1.0 s1.0 s

N/A

N/AN/ATo be determined

N/A


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REGISTER BDS 20 - AIRCRAFT IDENTIFICATION (Call Sign )

333435363738394041424344454647484950515253545556

MSB

CHARACTER 5

MSB

CHARACTER 6

MSB

CHARACTER 7

MSB

CHARACTER 8

FIELD

1234567891011121314151617181920212223242526272829303132

BDS Code 2 0

MSB

CHARACTER 1

MSB

CHARACTER 2

MSB

CHARACTER 3

MSB

CHARACTER 4

FIELD

333435363738394041424344454647484950515253545556

MSB

CHARACTER 5

MSB

CHARACTER 6

MSB

CHARACTER 7

MSB

CHARACTER 8

FIELD

1234567891011121314151617181920212223242526272829303132

BDS Code 2 0

MSB

CHARACTER 1

MSB

CHARACTER 2

MSB

CHARACTER 3

MSB

CHARACTER 4

FIELD

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UPLINK FORMAT

112 bits

56 bits

PC : 3 RR : 5 DI : 3 SD : 16 AP : 2400101UF 05Surveillance Identity Request

RC : 2 NC : 4 AP : 2411 MC :80Comm -C (Extended Length Message)

IP : 2401011 PR : 4 IC : 4 ----16 ---UF 11Mode S Only All-Call

PC : 3 RR : 5 DI : 3 SD : 16 AP : 2410101 MA :56UF 21Comm -A Identity Request

PC : 3 RR : 5 DI : 3 SD : 1610100 MA :56 AP : 24UF 20Comm -A Altitude Request

UF 16 10000 RL : 1 AQ : 1 AP : 24- 4 --- --------- 18 ----------- 3 - MU :56(ACAS) Long Air-Air Surveillance

RL : 1 AQ : 1 AP : 2400000 - 4 --- --------- 18 ----------- 3 -UF 00(ACAS) Short Air-Air Surveillance

PC : 3 RR : 5 DI : 3 SD : 16 AP : 2400100UF 04Surveillance Altitude Request

UF 24

CL :3


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DOWNLINK FORMAT

112 bits

56 bits

FS : 3 DR : 5 UM : 6 ID : 13 AP : 2400101DF=05Surveillance , Identity

IP : 2401011 CA : 3 AA : 24DF=11All - Call Reply

FS : 3 DR : 5 UM : 6 ID : 13 AP : 2410101 MB : 56DF=21Comm -B , Identity

FS : 3 DR : 5 UM : 6 AC : 1310100 MB : 56 AP : 24DF=20Comm -B , Altitude

FS : 3 DR : 5 UM : 6 AC : 13 AP : 2400100DF=04Surveillance , Altitude

Comm -D ( Extended Length Message ) KE : 1 ND : 4 AP : 2411 MD : 80--1--

(ACAS) Short Air-Air Surveillance DF=00 VS : 1 RI : 4 AP : 2400000 --- 7 ------

-- 2 -- AC : 13

(ACAS) Long Air-Air Surveillance DF=16 10000 AP : 24MU :56VS : 1 RI : 4--- 7 ------

-- 2 -- AC : 13

DF=24

Refer to ICAO Annex 10112 bits

56 bits

FS : 3 DR : 5 UM : 6 ID : 13 AP : 2400101DF=05Surveillance , Identity

IP : 2401011 CA : 3 AA : 24DF=11All - Call Reply

FS : 3 DR : 5 UM : 6 ID : 13 AP : 2410101 MB : 56DF=21Comm -B , Identity

FS : 3 DR : 5 UM : 6 AC : 1310100 MB : 56 AP : 24DF=20Comm -B , Altitude

FS : 3 DR : 5 UM : 6 AC : 13 AP : 2400100DF=04Surveillance , Altitude

Comm -D ( Extended Length Message ) KE : 1 ND : 4 AP : 2411 MD : 80--1--

(ACAS) Short Air-Air Surveillance DF=00 VS : 1 RI : 4 AP : 2400000 --- 7 ------

-- 2 -- AC : 13

(ACAS) Long Air-Air Surveillance DF=16 10000 AP : 24MU :56VS : 1 RI : 4--- 7 ------

-- 2 -- AC : 13

DF=24


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SURVEILLANCE CLUSTER NETWORK (SCN)

SURVEILLANCE CLUSTER NETWORK (SCN)Issue

•Usually, a radar has overlapping area with other radars. If the stations are not co−ordinated, they must be allocated different II codes and operate with the multisite all−call lockout protocol active. •As only sixteen II codes are available, it may be impossible to assign a unique II code to each radar station.

SCN purpose•To overcome this problem, the operation with SI codes (64 codes are available) will be possible when aircraft will be equipped with SI codes transponders.•The SCN makes it possible to co−ordinate Mode S radar stations surveillance activity in overlapping areas via a ground network.

SCN advantages•The group of radar stations then uses the same II code forming a cluster. Radar stations in a cluster exchange track information to allow an aircraft acquisition directly in roll−call transaction.•Another advantage obtained with the SCN is that radar stations can send additional information to an adjacent station having missed aircraft detection.

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Network aided / Standalone modes

Within a cluster, a Mode S station can operate according to two modes:

− the network aided mode:the connection between the station and the SCN is enabled and the station performs the surveillance co-ordination mission,

−the standalone mode:the connection between the station and the SCN is disabled and the station does not perform the surveillance co-ordination mission.

The Mode S station operates with a Radar Parameter Set (RPS) identified by its name, selected among up to sixteen RPSs depending on the Network aided or Standalone mode of operation.

RPS features

The RPS describes the following parameter values:

− II/SI code to be used by the radar,

− coverage map name (surveillance, track initialisation, intermittent lockout, lockout),

− scheduling parameters:

•AC/RC operational pattern,

•all-call staggering maximum deviation,

− I/R map selector (power attenuation, ISLS/IISLS, TVBC). Two I/R maps are programmed and one is selected.

In the network aided mode, the selection of the RPS to be applied is made according to a pre-defined policy (site dependent parameter) depending on the cluster state.

In the stand-alone mode, the Mode S station operates with a RPS corresponding to this mode.

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SCN Centralised approach :

A cluster controller is responsible for maintaining the overall coherency:

- the cluster controller knows the coverage maps of each radar,- it informs a radar when an aircraft is entering the radar coverage,

- it centralises all SCN data exchanged between the radars belonging to the cluster.

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SCN Distributed approach :

Radars are able to co-ordinate themselves:

- all radar stations are interconnected via the network and directly exchange SCN data,

- each radar knows the coverage limits of the adjacent zones,

- a radar informs the adjacent one when an aircraft is entering its coverage.

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MAIN OPERATIONAL FUNCTIONS

SCN

All-call/Roll-call interrogationscheduling and generation

AIRCRAFTMode S transponder

AIRCRAFTSSR-only transponder

. Video pulse reply generation

. Pulse analysis and validation

. Identif ication of pulses relevantto SSR and Mode S

Mode S reply processing:. Reply preamble and data block detection. Range measurement. Azimuth measurement. Aircraft address decoding. Flight parameter decoding

SSR reply processing:. Frame pulse detection. Range measurement. Azimuth measurement. Altitude report decoding. Identif ication decoding

ATC

Mode Sand SSR

plotcombination

SSR REPLIESMODE S REPLIES

SSR, INTERMODE ANDMODE S INTERROGATION S

SSR REPLIES

SSR AND INTERMODEINTERROGATIONS

MODE S

RADAR

Surveillancecoordinationmessages

SSR/Mode Stracks and/or plots

SCN

All-call/Roll-call interrogationscheduling and generation

AIRCRAFTMode S transponder

AIRCRAFTSSR-only transponder

. Video pulse reply generation

. Pulse analysis and validation

. Identif ication of pulses relevantto SSR and Mode S



SSR reply processing:. Frame pulse detection. Range measurement. Azimuth measurement. Altitude report decoding. Identif ication decoding

ATC

Mode Sand SSR

plotcombination

SSR REPLIESMODE S REPLIES

SSR, INTERMODE ANDMODE S INTERROGATION S

SSR REPLIES

SSR AND INTERMODEINTERROGATIONS

MODE S

RADAR

Surveillancecoordinationmessages

SSR/Mode Stracks and/or plots

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RSM 970S SYSTEM CONFIGURATION

STANDARD CONFIGURATION

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∆∆∆∆

EA 2000DRIVE MECHANISM

JTAROTARY JOINT

ΩΩΩΩ∆∆∆∆

∑∑∑∑

NTPS 1

SWITCH 1

* OPTIONALATCC GDLP *SCN *

pLINES / MODEMS

SITE MONITOR

AA 2000ANTENNA CONTROL CABINET

AE 2000POWER SUPPLY CABINET

IBISINDICATORRADARINFORMATIONSYSTEM

(BIS)

SITEDEPENDENTPARAMETERSTOOLSLOCALTERMINAL

SUPERVISORTERMINAL

LTM

SDPT

MODEM

Mains(3Φ,N,G)

STM

MODEM

TechnicalRoom

Mains to other equipment

REMOTECONTROLMONITORINGSYSTEM

DACF

ANCILLARYEQUIPMENT

TRCchannel 2

STX 2000TRANSMITTER

TRCchannel 1

MDRPMDR

MMXC

DPC PC - 1

MDRPMDR

MMXC

STX 2000TRANSMITTER

RFUC•

• •∑∑∑∑

ΩΩΩΩ∑∑∑∑

ΩΩΩΩ

∑∑∑∑


∑∑∑∑


DPC PC - 2

SWITCH 2

NTPS 2

SWITCH SUP

TOM cabinet

Optical encoder 2Optical encoder 1

- RSM 970 S -CIRIUS ARCHITECTURE

RCMS

SWITCH VIDEO

∆∆∆∆

EA 2000DRIVE MECHANISM

JTAROTARY JOINT


∑∑∑∑

NTPS 1

SWITCH 1

SWITCH 1

* OPTIONALATCC GDLP *SCN *

pLINES / MODEMS

SITE MONITOR

AA 2000ANTENNA CONTROL CABINET

AE 2000POWER SUPPLY CABINET

IBISINDICATORRADARINFORMATIONSYSTEM

(BIS)

SITEDEPENDENTPARAMETERSTOOLSLOCALTERMINAL

SUPERVISORTERMINAL

LTM

SDPT

MODEM

Mains(3Φ,N,G)

STM

MODEM

TechnicalRoom

Mains to other equipment



DACF

ANCILLARYEQUIPMENT

TRCchannel 2

STX 2000TRANSMITTER

STX 2000TRANSMITTER

TRCchannel 1

MDRPMDR

MMXC

DPC PC - 1DPC PC - 1

MDRPMDR

MMXC

STX 2000TRANSMITTER

STX 2000TRANSMITTER

RFUC•

• •∑∑∑∑

ΩΩΩΩ∑∑∑∑

ΩΩΩΩ

∑∑∑∑


∑∑∑∑


DPC PC - 2DPC PC - 2

SWITCH 2

SWITCH 2

NTPS 2

SWITCH SUP

SWITCH SUP

TOM cabinet

Optical encoder 2Optical encoder 1

- RSM 970 S -CIRIUS ARCHITECTURE

RCMS

SWITCH VIDEO


PRESENTATION OF THE EQUIPMENTThe RSM970S carries out the functions of a dual interrogator / receiver and signal and data processing equipment.The dual architecture of the RSM970S includes two separated I/R channels.This design makes easy maintenance on one channel while the second channel remains operational.

The RSM970S equipment is composed of two I/R channels including each:- inside the TRC (Transmitter Receiver Cabinet)

one STX 2000 transmitter,one MDRP receiver/processor,the RFUC, interface function between the two I/R channels and the antenna, is common to the both channels.

-inside the TOM (Tracking Output and Miscellaneous) cabinetone DPC PC data processor associated with I/O Ethernet LAN,one NTPS providing the Time Stamping Function unit (option).

ASSOCIATED EQUIPMENTThe RSM970S uses AS 909 secondary antenna via the rotary joint JTA.The radar station includes :

two I / R channels,one IBIS local maintenance display,one AA 2000 antenna control cabinet which controls the antenna drive mechanism EA 2000,one AE 2000 power distribution cabinet,a Remote Control and Monitoring System for operating the station from a distance.

The two azimuth encoders, located in the rotary joint, transmit the angular position of the antenna in digital form.

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RSM970S CABINET ARRANGEMENT

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RSM970S CABINET ARRANGEMENT

TRC Cabinet

TOM Cabinet

AA 2000

Rear view

AE 2000 TOM Cabinet

TRC Cabinet

Front view

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TRC CABINET

Front view Rear view

MDRP 1

MDRP 2

Σ 1

Ω 1

Σ 2

Ω 2

ID 1

ID 2

FAN UNIT 1

FAN UNIT 2

POWER SUPPLY UNIT 1

POWER SUPPLY UNIT 2

RFUC

RFUC

LOMB

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NTPS 1

NTPS 2

PLINES 1

PLINES 2

IBIS PC

DPC PC 1

DPC PC 2

RCMS PC

+5V

+5V

+15V

+15V

Optical encoder 1

Optical encoder 2

SW 1

SW 2

SW Sup

SW Video


TOM CABINET

Rear viewFront view

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RSM 970S SYSTEM KEY FEATURES

KEY FEATURES

TECHNICAL CHARACTERISTICSRF characteristics Radar frequencies:

Interrogation frequency : 1030 MHz ± 10 KHzReception frequency : 1090 MHz ± 3 MHzMaximum antenna gain : 27 dBi

Antenna azimuth beam width : 3.2°

Transmitted peak power : 2570 W

VSWR : < 1.5 (cabinet output)

Isolation between channels : 70 Db

RF change over switching time: < 100 ms

System start-up

−System response time (time between the start-up command and the sending of a plot on a surveillance line): 4.5 minutes

−Initial aircraft acquisition: at least 99 % of aircraft present in the surveillance coverage of the system within 10 antenna scans after the first plot has been output on the surveillance link

−Control and Monitoring System time synchronisation: from GPS receiver time information with a minimum precision of 1 s

−Radar processing time stamping accuracy < 2 ms

−System time performance when not synchronised on external signal:drift 20 ms per month

Control and monitoring

−On-line fault reporting time : < 2 s after the fault is detected

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RSM 970S SYSTEM FUNCTIONAL PRESENTATION

FUNCTIONAL PRESENTATION

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AERIAL SUBSYSTEM

AERIAL SUB-SYSTEMAS 909

JTA

EA2000P

AA2000NGB

+5V +15V

+5V +15V

RF SIGNALS TO/FROM

RFUC

MMXC 1

MMXC 2

TRC CABINET

∆ Σ Ω

Σ, Ω, ∆

Rotation

TO MMXC

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AS909 - PATTERN DISTRIBUTION AMPLITUDE

Column number

For Ω diagram, the rear column receives half the total power, and front column 18 is fed with a 180° phase signal.

Σ CHANNEL

∆ CHANNEL

Ω CHANNEL

3534333231302928272625242322212019181 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17

Α dB

- 15

- 25

- 30

- 35

- 40

- 42

- 20

- 10

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INTERROGATION / RECEPTION

BIT

POWER SUPPLY5 V, + 15 V

FROM TRCCABINET(DCS)

L.O.

BIT REPORTS

BIT TRIGGER

TO/FROM MMXC

LOCALOSCILLATORGENERATION

ΩΩΩΩΣΣΣΣ ∆ ∆ ∆ ∆

Log Σ Log ΩLog ∆ f (∆/Σ )

FROM RFUC

VIDEOPROCESSING

MDR

ANALOG VIDEOGENERATION

RSLSCONTROLS

QRSLS Log Σ,Log ∆

and f (∆/Σ)

Log ΣTO STX 2000 VIA LOMB

Test signal

STX2000 TRANSMITTER

RFUC

Transmitter SUM HPA

MMXC

Transmitter CONTROL HPA

Transmitter Interface Driver


MDR RECEIVER

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RFUC


ϕ

Σ ∆Ω

ΣΣ ΩΩ ∆∆

MDRP 1 MDRP 2

ϕϕ

Σ

1Σ

2Ω

1Ω

2

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PROCESSING MAIN FUNCTIONS

Fan, DCS Status + DC Supply

Interrogation Controls

MMXC

NTPS

MRP

RFUC ControlsBIT Status

Azimuth data from Optical Encoder To/From RFUC

MRC

From TRC

To/From oMMXC

LAN Switch Supervisor

Operator controlsOperational parameters

DPC - PC

PLines

To/From STX 2000

Synchronisation BIT Status

To/From MDR

ControlsSynchronisation

BIT StatusVideos

Transmission inhibition controlFrom AA 2000

Monitoring messages

To IBIS

Maintenance / LogΣ / Pulses presence videos

Time message BITE

AC/RC Sequencing RC transactions Mode S replies SSR RepliesBIT Status

( Ethernet GIGABIT )

To/From oDPC/MRPPlots + Monitoring messages

Reply reports, tracks,Coverage maps

To IBIS

To/From SDPT/CBP

Operator controlsMaintenance data

To/From RCMS

Data Link messages Tracks/plots

BITEOps parameters

ATCC (PSR) (SCN) (GDLP) (LU)

LAN Switch

Video

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PROCESSING MAIN FUNCTIONS

MMXC 1

DPC-PC 1

MMXC 2

DPC-PC 2

LAN Switch 1 LAN Switch 2

NTPS 1 NTPS 2

PLines 1 PLines 2

GIGABIT Ethernet

I/O Ethernet LAN

Serial lines

Modem

To/From users

Modem

To/From users

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Opticalencoders

RFUCMMXC 1

DPC PC 1

MMXC 2

DPC PC 2

STX 2000-2

MDR 2

RFUC Status

GigabitGigabit

TRC 1

SWITCH SUP

BIT Status

CHANNEL 2CHANNEL 1

MODEM

Supervisor Ethernet LAN

DACF

TRC 2

RFUC Status

BIT Status

BIT Status Controls

BIT Status Controls

STX 2000-1

MDR 1

EA 2000

AA 2000

AE 2000IBIS SDPT / LTM

MODEM

STM

BITE and Remote Control Monitoring System (RCMS)

BITE FUNCTIONS

The following functions are performed at the level of the BITE of each equipment:

• Acquisition of digital and analogue statuses,

• Processing of this information to check the correct operation or, in the event of a failure, to determine the faulty unit,

• Management of front panel indicators (local reports),

• Continuous monitoring of the configuration status,

• Management of controls from / to remote control function,

The following data are exchanged with the DRU :

• Correct operation statuses,

• In case of a failure, a code corresponding to the faulty function,

• Command and acknowledgement of remote control orders.

• Any equipment status or parameter requested by the operator.

The DACF unit interfaces ancillary units such as mains and antenna control cabinets, air conditioning system, UPS, safety devices using opto-couplers and relays.

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BUILT-IN TEST (BIT)

Built-in test is based on:

-internal test ⇒ test integrated in equipment itself,

-external test ⇒ implementation of a Long Loop Test (LLT) with the use of a Mode S Site Monitor.

INTERNAL TEST to:

locally detect failure,

transmit information to the remote control and monitoring function in order to advise the maintenance team and give information to isolate the faulty LRU(s).

detect critical failures of I/R channel equipment in order to control I/R channel hot switchover.

BIT RESULT CENTRALIZATION

• Except for the I/R channel part, BIT results are directly transmitted to the remote control and monitoring function.

• For I/R channel equipment local BIT reports are transmitted to a central BIT device which performs:

• acquisition of local BIT reports,

•filtering, to eliminate false failures and to output failure codes,

•analysis, to eliminate derived failure codes (which are only failure consequences) and elaborate source failure diagnosis (failure origin),

•LRU diagnosis, to identify potential failed LRUs,

•updating of I/R channel status and state,

•data formatting and transmission to the remote control and monitoring function,

•channel hot switchover control.

OPERABILITY STATUS

The operability status of a function or equipment (example : transmitter) is get from failure code presence or absence:

•CORRECT if the function is operating correctly, no failure code is present,

•WARNING if the central BIT has detected a failure with no impact on the system capabilities, performance or safety.A warning failure code is present,

•ALARM if the central BIT has detected a failure with an impact on the system capabilities, performance or safety.An alarm failure code is present.

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RCMS Equipment

The RCMS allows the operator to perform locally and remotely:

• monitoring,• control• management facilities for events related to monitoring and control.

Due to its important role, the RCMS is also monitored.

The RCMS is based on two main equipment:• one I/O Data Acquisition and Control Function unit (DACF),

• two personal computers, each one associated with a printer:

a Local Terminal Monitor (LTM),

a Supervisor Terminal Monitor (STM).

Note: The Data Regrouping Unit (DRU) software is installed on the LTM.

RCMS can be disconnected from the radar without impact on radar services provided to the ATC centre.

All information is transmitted to / from the DRU via a Supervision Ethernet network carrying the following information:

• Correct operation codes,

• In case of a failure, code corresponding to the faulty function,

• Command and acknowledgement of remote control orders,

• Any equipment status or parameter requested from the local or remote computer.

The RCMS data link is separated from the radar data links. In case of failure of radar data links, the monitoring of the radar system and of the radar data distribution is still possible.

RCMS provides its functions :

• at station level for system optimisation and preventive/ corrective maintenance,

• at Central Maintenance Room level for the remote system control and monitoring

The corresponding control and monitoring consoles are provided with a multi-function keyboard and a mouse.

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RCMS DISPLAY

RCMS Monitoring

A synopsis of the station is displayed in the form of a block diagram. The selection of any part of the system is possible using the mouse. Pull out menus allow for presentation of more detailed information.

The console provides:

- a graphic coloured status indication for equipment elements, showing particularly faults and unavailability,

- pull out menus showing functions and monitored parameters where appropriate, displaying their current values,

- system status codes.

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SITE DEPENDENT PARAMETERS

Site dependent parameters provide radar operation adjustment to site conditions and offer reserved values to adapt radar operations to user requirements.

These operational parameters: are initially set at installation (and logged in the installation manual), must be re-programmed after some maintenance actions (spares programmed

with default values), must be changed if the site conditions change.

These parameters are used in: I/R channel equipment (one set per channel), Mode S site monitor (one set per SMS channel).

As the LLT is processed by an I/R channel with SMS participation and the SMS has its own processing device, LLT parameters are defined on both SMS and I/R channels with SDPT/CBP & SMSP software running on a PC.

SDPT/CBP OPERATING MODE

SDPT/CBP can be used in "disconnected" or "connecte d" operating modes :

•“disconnected” to display and change parameters from SDPT/CBP internal files without I/R channel operation disruption,

•“connected” to:

•pick-up files from I/R channel to display and change parameters as indisconnected mode,

•transfer files from SDPT/CBP to I/R channel for parameter application,

•change and apply a few parameters in a direct access way.

The SDPT/CBP integrates safety functions to:

•check correct data exchange between the SDPT/CBP and the I/R channel,

•perform configuration management through:

•file revision identification,

•comparison of files from different I/R channels.

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AE 2000 ASSOCIATED EQUIPMENT

DACF

AE 2000R

DACF

AE 2000R DACF Unit

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IBIS Maintenance Display Monitor

The IBIS (Indicator Radar and Information System - BIS) display console function is provided for maintenance purpose, by mainly displaying information extracted at different points of the radar chain so that:• fault isolation is easier,• radar performance can be checked.

The mains following different types of data are displayed from the MDRP:• a Log Σ video and pulse/presence video from channel 1 or channel 2,• a maintenance video from channel 1 or channel 2:

- OBA diagram,- power diagram.With the maintenance video, IBIS enables the displa y of radar adjustment

patterns.

These videos are distributed to IBIS display via the Video LAN .

The mains following different types of data are displayed from the DPC PC via the SupervisionLAN :• plots and tracks with associated information.In addition, the following data are displayed:• system controlling data; IBIS configuration, display definition, maps, etc..,• statistics on the flow of the data transmitted on the line (tracks and plots number),• bearing and range measurement via vectors between different points (geographical, track, etc..).

IBIS MMI offers facilities to adapt the display:data selection, data filtering, radar image re centre and resize,…The different categories of data are all able to be displayed simultaneously

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SITE MONITOR BLOCK DIAGRAM

SITE MONITOR PRINCIPLE

The SMS is built with a transponder.

Depending on the ICAO level of the built-in transponder, the SMS is known as SMS-1 for level 1 and SMS-3 for level 3.

The SMS is a completely doubled equipment (SMS chanel 1 and chanel 2). For the radar, the SMS is seen as two single Site Monitors, each with its own independent parameters (codes, range, level, etc.).

PURPOSE:

•to perform the long loop test (LLT) of the station, using pre-defined interrogation sequences for:

confirming the correct global operation of the radar (detection, lockout, Site Monitor state etc.),

•testing "NON BITED" radar components including parts of the I/R redundant channels,

•to collect SMS BIT results to be checked by the operator to confirm LLT status according to SMS status,

•to update LLT global status according to LLT1 and LLT2 statuses.

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I/R CHANNEL SWITCHOVER

For high availability purpose, the radar station includes a dual I/R channel with automatic switchover in case of failure declaration

⇒ hot switchover

Channel switchover may also be performed:

manually for maintenance purpose ⇒ cold switchover

automatically for test purpose ⇒ preset cold switchover

The switchover process is the same but NOT the initiating conditions.

HOT SWITCHOVER

Hot switchover takes place in case of failure declaration, the failure being detected by any channel.

Hot switchover is initiated by the "to load" channel.

COLD SWITCHOVER

Cold switchover is initiated by a manual action:

•in remote mode by a RCMS control (remote position),

•in local mode by a SDPT/CBP or RCMS control (local position).

Cold switchover may be used whatever the I/R channel state (operational or maintenance).

It enables the operator to change the configuration state.

PRESET COLD SWITCHOVER

The BIT performed on the "to load" channel is less extensive than the one applied to the "to antenna” channel because radar global operation cannot be checked by LLT.

Moreover, the switchover function is only exhaustively checked during its operation.

Consequently, a complete check on the radar operation requires an automatically-triggered cold switchover to be periodically performed, that is the preset cold switchover.

It is to be programmed on each channel via operational parameters (miscellaneous operational parameters):

•first preset cold switchover date,

•preset cold switchover period,

•preset cold switchover authorisation (for activation or deactivation).

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MAINTENANCE

RSM 970S SYSTEM MAINTENANE

MAINTENANCE FUNCTION

The maintenance function enables the operator to:

•monitor the operational status of the system thanks to the BIT integrated in radar equipment and thanks to the SMS external test equipment,

•monitor radar performance by using radar data sampling and display,

•control system or equipment states and modes,

•adjust radar operational parameters to site dependent conditions.

The maintenance function is ensured by means of:

•RCMS,

•maintenance facilities:

•radar maintenance display (IBIS),

•SMS ("long loop test"),

•SDPT/CBP tool.

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Air Systems Division

Thank you for your attention

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