Publication: Magyar Közlöny
Issue: MK-2007-70 (Year: 2007, Number: 70)
Era: 2004-2010
Section: Melléklet a 2007. évi XLVI. törvényhez
Paragraph Index: 3491

b) 3. Each Type 101 m a lability duration parameters for one satellite ranging source. The ephemeris decorrelation param Modified count: as defined in 3.6.4.2.3. Additional message flag: as defined in 3.6.4.2.3 except applicable to Epheme source. ng source ID: as defined in 3.6.4.2.4. Is Pseudo 23/11/06 A 2007/70/II. szám A endix Annex 10 — Aeronautical Communications 3.6.5 DEFINITIONS OF PROTOCOLS FOR DATA APPLICATION Note This section defines the inter relationships of the data broadcast message parameters It provides definitions of parameters that are not transmitted but are used by either or both non aircraft and aircraft elements and that define terms applied to determine the navigation solution and its integrity 3.6.5.1 Measured and carrier smoothed pseudo range The broadcast correction is applicable to carrier smoothed code pseudo-range measurements that have not had the satellite broadcast troposphere and ionosphere corrections applied to them. The carrier smoothing is defined by the following filter: CSCn P D n 1 CSC n n 1 P (1 ) P ( )   O § ·   D  I  I ¨ ¸ S © ¹ where PCSCn the smoothed pseudo-range; PCSCn 1 the previous smoothed pseudo-range; P the raw pseudo-range measurement where the raw pseudo-range measurements are obtained from a carrier driven code loop, first order or higher and with a one-sided noise bandwidth greater than or equal to 0.125 Hz; Ȝ the L1 wavelength; the carrier phase; n 1 the previous carrier phase; and Į the filter weighting function equal to the sample interval divided by the time constant of 100 seconds. 3.6.5.2 Corrected pseudo range The corrected pseudo-range for a given satellite at time t is: PRcorrected PCSC PRC RRC (t tz-count) TC c (ǻtsv)L1 where PCSC the smoothed pseudo-range (defined in 3.6.5.1); RRC the pseudo-range correction rate (defined in 3.6.4.2); nt .2); 6.5 3.6.5.3.1 The tropospheric correction for a given satellite is: In I PRC the pseudo-range correction (defined in 3.6.4.2); t the current time; tz-cou the time of applicability derived from the modified -count (defined in 3.6.4 TC the tropospheric correction (defined in 3.6.5.3); and c and (ǻtsv)L1 are as defined in 3.1.2.2 for GPS satellites. 3. .3 TR P SP ERIC DE A h / h r i TC N h (1 e ) 0.002 sin (El )  '   Nr refractivity index from the Type 2 message (3.6.4.3); ǻh height of the aircraft above the GBAS reference point; where A 23/11/06 2007/70/II. szám Annex 10 — Aeronautical Communications Volume I 23/11/06 A Eli elevation angle of the ith satellite; and h0 troposphere scale height from the Type 2 message. 3.6.5.3.2 The residual tropospheric uncertainty is: h / h tropo n i h (1 e ) 0.002 sin (El )  ' V V   where ın the refractivity uncertainty from the Type 2 message (3.6.4.3). 3.6.5.4 Residual ionospheric uncertainty The residual ionospheric uncertainty for a given satellite is: ıiono Fpp ıvert_iono_gradient (xair 2 Ĳ vair) where Fpp the vertical-to-slant obliquity factor for a given satellite (3.5.5.5.2); ıvert_iono_gradient (as defined in 3.6.4.3); xair the distance (slant range) in metres between current aircraft location and the GBAS reference point indicated in the Type 2 message; Ĳ 100 seconds (time constant used in 3.6.5.1); and vair the aircraft horizontal approach velocity (metres per second). 3.6.5.5 PR TECTI N E E S 3.6.5.5.1 Category I precision approach and AP The signal-in-space vertical and lateral protection levels (VPL and LPL) are upper confidence bounds on the error in the position relative to the GBAS reference point defined as: VPL MAX VPLHO,VPLH1 LPL MAX LPLHO,LPLH1 3.6.5.5.1.1 Normal measurement conditions 3.6.5.5.1.1.1 The vertical protection level (VPLH0) and lateral protection level (LPLH0), assuming that normal measurement conditions (i.e. no faults) exist in all reference receivers and on all ranging sources, is calculated as: N H0 ffmd i i i 1 VPL K s_vert uV ¦ N H0 ffmd i i i 1 LPL K s_lat uV ¦ where Kffmd the multiplier derived from the probability of fault-free missed detection; s_verti sv,i sx,i tan (GPA); s_lati sy,i; 2007/70/II. szám A endix Annex 10 — Aeronautical Communications sx,i the partial derivative of position error in the x-direction with respect to pseudo-range error on the ith satellite; sy,i the partial derivative of position error in the y-direction with respect to pseudo-range error on the ith satellite; sv,i the partial derivative of position error in the vertical direction with respect to pseudo-range error on the ith satellite; GPA the glidepath angle for the final approach path (3.6.4.5.1); N the number of ranging sources used in the position solution; and i the ranging source index for ranging sources used in the position solution. .1.2 For a general-least-squares position solution, the projection matrix S is defined as: S (G W G) G W S S S { u u u u « » " where Gi cos Eli cos Azi cos Eli sin in Eli 1 ith and N W ;  Note The coordinate reference frame is defined such that x is along trac positive forward y is crosstrac positive left the local level tangent plane and v is the positive up and orthogonal to x and y in 3.6.5.5.1 x,1 x,2 x,N y,1 y,2 y,N T S S S S S S  ª º « » « » " " T v,1 v,2 v,N t,1 t,2 t,N S S S « » « » ¬ ¼ " Azi s row of G; ª º V « » " V « » « » « » « » V ¬ ¼ " # # % # " where ı2 i ı 2 pr_gnd,i ı 2 tropo,i ı 2 pr_air,i ı 2 iono,i; where ıpr_gnd,i ı pr_gnd for the ith ranging source (3.6.4.2); ıtropo,i the residual tropospheric uncertainty for the ith ranging source (3.6.5.3); ıiono,i the residual ionospheric delay (due to spatial decorrelation) uncertainty for the ith ranging source (3.6.5.4); and ıpr_air,i receiver i multipath i (El ) (El ) V  V th , the standard deviation of the aircraft contribution to the corrected pseudo-range error for the i ranging source. The total aircraft contribution includes the receiver contribution (3.6.8.2.1) and a standard allowance for airframe multipath; where ımultipath(Eli) , the standard model for the contribution of airframe multipath (in metres); Eli the elevation angle for the ith ranging source (in degrees); and Azi the azimuth for the ith ranging source taken counterclockwise for the x axis (in degrees). Note To improve readability the subscript i was omitted from the projection matrix s e uation i El /10 deg 0.13 0.53e  A 23/11/06 2007/70/II. szám Annex 10 — Aeronautical Communications Volume I 3.6.5.5.1.2 Faulted measurement conditions When the Type 101 message is broadcast without B parameter blocks, the alues for VPLH1 and LPLH1 are defined as zero. Otherwise, the vertical protection level (VPLH1) and lateral protection level LH1), a m ceiver, are: LPLH1 max LPLj where VPLj and LPLj for j 1 to 4 are VPLj B_vertj Kmd ıvert,H1 and LPLj B_latj Kmd ılat,H1 and  B_vertj (s_verti Bi,j); latj (s_lati Bi,j); Bi,j the broadcast differences between the broadcast pseudo-range corrections and the corrections obtained excluding the jth reference receiver measurement for the ith ranging source; Kmd the multiplier derived from the probability of missed detection given that the ground subsystem is faulted; ı2 vert,H1 (s_vert2 i ı_H12

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