a flight procedure design method for rnp to xls with...

Japan-US Aviation Environmental Workshop Fukutake Hall, University of Tokyo, 29 November 2017

A Flight Procedure Design Method for RNP to xLS with Shallow Segment

Sonosuke Fukushima, Ryota Mori, Shinji Saitoh

Electronic Navigation Research Institute, National Institute of Maritime, Port and Aviation Technology

Outline

1. Background 2. “RNP to xLS” Procedure Design

Assumption & Method 3. Full-Flight Simulator Trials 4. Summary

US-Japan Aviation Environmental Workshop, University of Tokyo, 29 Nov. 2017

3

1. Advantage of RNP to xLS


FACF IAF

Intermediate Segment

FAF

FAF FACF

IAF

RNP AR RNP to xLS

xLS

FAF

No PA PA

PA

FAF


4

1. Glideslope Intercept Altitude


Hot Day

Cold Day

Normal Day

Dfap

Zfap

θ Zdcp


Intermediate Segment used barometric altitude while final approach segment depends on geometric altitude.

5

1. Temperature Correction


International Standard Atmosphere (ISA) Temp 15°C at Mean Sea Level, Lapse rate ~ –2°C per 1,000 ft

1000 2000 3000 4000 5000

Altitude on MLS (FT)

0

200

400

600

Corr

ectio

n (F

T) ∆ISA = 20°C 6.8 %

∆ISA = 10°C 3.4 %

Altitude on MLS (FT)

Alti

tude

Cor

rect

ion

(FT)

∆ISA = 30°C 10.2 %

GS should be captured after capturing LOC. For short intermediate design, GS capture may

happen before LOC capture.

6

1. Difficulty of Procedure Design


GS Capture Point

LOC Capture Point

Hot Day

Cold Day

Normal Day

7

1. Shallow segment

FAA PARC reported RNP to xLS procedure design using Shallow Intermediate Segments

Improving flight efficiency: Long level segment decrease it. Considering capture condition and guideline.


∆ISA > 0°C Normal Day

Intercept Point

Cold Day

∆ISA = 0°C

∆ISA < 0°C

Hot Day

Length Angle

Discussing more detail, and optimum design method

8

2. Assumption of procedure design


1. ARINC 424 compliance

ARINC 424-19 specification are supposed All type of aircraft does not support 424-20

2. Hottest day temperature ∆ISA = 30°C 113°F MSL

424-19 (2008) “All such approach procedures

must begin at the FACF” “The rules of coding GLS

approach procedure are understood to be identical to those of LOC coding”

424-20 (2011) “The final approach coding

of GLS instrument approach procedures does not require the coding of a FACF waypoint”

9

2. Assumption of procedure design


3. Glideslope & Localizer capture timing

5. Glideslope capture boundary a half dot

Type A aircraft are supposed

Type A aircraft allows Glideslope capture before Localizer capture

Type B aircraft inhibits Glideslope capture before Localizer capture

4. Glideslope pointer exceed one dot Pilots need a buffer for pushing APP switch

Critical

10

2. Procedure design


WP 3

WP 4 WP

2 WP 1

（90FT）

X.X NM

CF LEG

RW24R

WP 1

WP 3

RF LEG

TF LEG

MAX 180KIAS

At 3189FT

GLS: GKW (FREQ: 21475)

WP 4 At 3189FT

2.0 NM

WP 0

3.0 NM

V/A 3.0 V/A 3.0

ANG

LEN

WP 2

ANG

TF LEG

5.0 LEN 7.85 X.X

LEN (NM)

ANG (deg)

A 1.0 1.4 B 1.5 1.5 C 2.0 1.6

TOTAL 17.85

FACF FAF GS intercept alt: 1700FT GS crossing alt: 1053FT

2.5NM

11

2. Deviation & Capture points


FACF FAF

∆ISA 0°C

VNAV

∆ISA 30°C

GS Dev

Capture

0 1 2 3 4 5

-2

-1

0

1

2

Distance to FAF (NM)

Dev

iatio

n (d

ot)

LOC Capture

Case-B

GS Capture ∆ISA = 0°C

∆ISA = 30°C

12

2. Calculation of ANGmax


Given LEN, others

ANG = ANG + ∆

IF dist( ) < dist( ) & Max GS > 1.0 dot

Output ANGmax

Iteration Algorithm

Calc

dist ( ) : distance along RF to from FAF

FACF FAF

0°C VNAV

∆ISA 30°C

GS Dev

get close to

Capture

FAA ORDER 8260.58A, PANS-OPS

13

3. Simulator Trials


Standard procedures based on ARINC 424 specification were coded by NAV database provider

FMS vender checked the database quality, and converted to FMS loadable database

Flight simulations with variable temp were conducted in ANA flight training center

14

3. Comparison with FFSIM


Horizontal distance to FAF along RF course (NM)

CACLULATED FFSIM (NO WIND CASE)

0 1 2 3 4 5

-2

-1

0

1

2

LOC

∆ISA=0°C

15°C

30°C GS

0 1 2 3 4 5

-2

-1

0

1

2∆ISA=0°C

15°C

30°C GS

A Dev

iatio

n (D

OT)

A LOC

15

3. Comparison with FFSIM


Horizontal distance to FAF along RF course (NM)

CACLULATED FFSIM (NO WIND CASE)

0 1 2 3 4 5

-2

-1

0

1

2

45°C

∆ISA=0°C

15°C

30°C GS

LOC B

0 1 2 3 4 5

-2

-1

0

1

2 ∆ISA=0°C

15°C

30°C GS

LOC C 0 1 2 3 4 5

-2

-1

0

1

2 ∆ISA=0°C

15°C

30°C GS

Dev

iatio

n (D

OT)

LOC C

0 1 2 3 4 5

-2

-1

0

1

2

B 45°C

∆ISA=0°C

15°C

30°C GS

LOC

Dev

iatio

n (D

OT)

0 1 2 3 4 5-40

-20

0

20

40

16

3. Altitude Variation before FAF


Alti

tude

Var

iatio

n (F

T) Severe Turbulence

IAS(KT)

200

160

FLAP 5

FLAP 25 FLAP 20

0 1 2 3 4 5-40

-20

0

20

40

Altitude Variation is affected by the Flap Extension, and not exceed +20 FT even severe turbulence condition

Distance to FAF (NM) Distance to FAF (NM)

None Wind Altitude Variation

17

4. Intermediate LEN .vs. ANG


+50FT (20FT + Margin)

1500 2000 2500 3000 3500 4000 4500

FAF altitude (FT)

0.2

0.4

0.6

0.8

1

1.2

1.4

1.6

1.8

2

Max

imum

inte

rmid

iate

seg

men

t ang

le (

deg)

Length of intermediate segment (NM)

∆ISA = 30°C

2.0 1.9

1.8 1.7

1.6 1.5

1.4 1.3

1.2

1.1 1.0

FAF altitude (FT)

Max

inte

rmed

iate

seg

men

t ang

le (d

eg)

Direct Proportion

Inverse Proportion

LEN .vs. ANG

FAF ALT. vs. ANG

Additional assumption By FFSIM experiments

LTP 36 ft, TCH 54ft, Length of LOC to THD 4320 m, Course width 210 m

US-Japan Aviation Environmental Workshop, University of Tokyo, 29 Nov. 2017 18

5. Summary

Development of RNP to xLS procedures with shallow intermediate segment were discussed

The design method of shallow intermediate segments were proposed based on the assumptions

Full flight simulator trials confirmed that the method enables to design procedure even in the high temperature condition

Findings also revealed altitude variations required a buffer

The revised algorithm will enable the development of the procedures design criteria

Thank you for your attention !


Quoted from : Sonosuke Fukushima, Ryota Mori, Shinji Saitoh, “Geometric Approach for RNP Transition to xLS Procedure Design,” 36th Digital Avionics Systems Conference, Sept. 2017.

a flight procedure design method for rnp to xls with...

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