Publication: Magyar Közlöny
Issue: MK-2007-70 (Year: 2007, Number: 70)
Era: 2004-2010
Section: Melléklet a 2007. évi XLVI. törvényhez
Paragraph Index: 3482

a) the IODFj shall match the IOD time out interval for fast co 3.5.7.5 Precise differential correction function. If SBAS provides a precise differential correction function, it shall comply with the requirements contained in this section in addition to the basic differential correction function requirements in 3.5.7.4. 23/11/06 A 2007/70/II. szám A endix Annex 10 — Aeronautical Communications 3.5.7.5.1 Performance of precise differential correction function. Given any valid combination of active data, the probability of an out-of-tolerance condition for longer than the relevant time-to-alert shall be less than 2 10 7 during any approach, assuming a user with zero latency. The time-to-alert shall be 5.2 seconds for an SBAS that supports precision pproach or APV-II operations, and 8 seconds for an SBAS that supports APV-I operations. An out-of-tolerance condition r 27 essages) shall be repeated three times after the initial notification of the alert condition for a total of four times in 4 seconds. a is defined to be data that has not timed out per This re uirement includes core satellite onstellation(s) and S AS failures Note Subse uent messages can be transmitted at the normal update rate and IODIk (up to 11 Type 18 essages, corresponding to the 11 IGP bands). The IGP mask values shall indicate whether or not data are being provided for ach IGP. If IGP Band 9 is used, then the IGP mask values for IGPs north of 55 N in Bands 0 through 8 shall be set to “0”. If P k essage shall equal the IODIk broadcast in the IGP mask message (Type 18 message) used to designate the IGPs for which data are provided in that message. 3.5.7.5.2.1 Recommendation hen the I P mas is changed S AS should repeat the Type message several 3.5.7.5.3 Ionospheric corrections. SBAS shall broadcast ionospheric corrections for the IGPs designated in the IGP mask (IGP mask values equal to “1”). 3.5.7.5.4 Ionospheric integrity data. For each IGP for which corrections are provided, SBAS shall broadcast GIVEI ata such that the integrity requirement in 3.5.7.5.1 is met. If the ionospheric correction or ı 2 i,GIVE exceed their coding range, BAS shall indicate that the IGP is unhealthy (designated in the correction data). If ı 2 i,GIVE cannot be determined, SBAS shall indicate that the IGP is “Not Monitored” (designated in the GIVEI coding). pe 10 message) such that the integrity quirement in 3.5.7.5.1 is met. .5.7. there is a change in any Type 27 message data. 3.5.7.6.3 Cloc ephemeris covariance matrix. If clock-ephemeris covariance matrix data are broadcast, they shall be broadcast for all monitored satellites as defined in 3.5.4.10 (Type 28 message) and Type 27 messages shall not be broadcast. 3.5.7.7 M NIT RIN 3.5.7.7.1 S AS radio fre uency monitoring The SBAS shall monitor the SBAS satellite parameters shown in a shall be defined as a horizontal error exceeding the HPLSBAS or a vertical error exceeding the VPLSBAS (as defined in 3.5.5.6). When an out-of-tolerance condition is detected, the resulting alert message (broadcast in a Type 2 to 5 and 6, 24, 26 o m Note Active dat c 3.5.7.5.2 Ionospheric grid point (I P) mas . SBAS shall broadcast an IGP mask m e IG Band 10 is used, then the IGP mask values for IGPs south of 55 S in Bands 0 through 8 shall be set to “0”. The IODIk shall change when there is a change of IGP mask values in the kth band. The new IGP mask shall be broadcast in a Type 18 essage before it is referenced in a related Type 26 message. The IODI in Type 26 m m times before referencing it in a Type message to ensure that users receive the new mas The same I DI should be used for all bands d S 3.5.7.5.5 Degradation data. SBAS shall broadcast degradation parameters (Ty re PTI NA FUNCTI NS 3.5.7.6.1 Timing data. If UTC time parameters are broadcast, they shall be as defined in 3.5.4.8 (Type 12 message). 3.5.7.6.2 Service indication. If service indication data are broadcast, they shall be as defined in 3.5.4.9 (Type 27 message) and Type 28 messages shall not be broadcast. The IODS in all Type 27 messages shall increment when Table B-55 and take the indicated action. A 23/11/06 2007/70/II. szám Annex 10 — Aeronautical Communications Volume I Note In addition to the radio fre uency monitoring re uirements in this section it will be necessary to ma e special provisions to monitor pseudo range acceleration specified in Chapter and carrier phase noise specified in and correlation loss in unless analysis and testing shows that these parameters cannot exceed the stated limits 3.5.7.7.2 Data monitoring SBAS shall monitor the satellite signals to detect conditions that will result in improper operation of differential processing for airborne receivers with the tracking performance defined in Attachment D, 8.11. 3.5.7.7.2.1 The ground subsystem shall use the strongest correlation peak in all receivers used to generate the pseudorange corrections. 3.5.7.7.2.2 The ground subsystem shall also detect conditions that cause more than one zero crossing for airborne receivers that use the Early-Late discriminator function as defined in Attachment D, 8.11. 3.5.7.7.2.3 The monitor action shall be to set UDRE to “Do Not Use” for the satellite. 3.5.7.7.2.4 SBAS shall monitor all active data that can be used by any user within the service area. 3.5.7.7.2.5 SBAS shall raise an alarm within 5.2 seconds if any combination of active data and GNSS signals-in-space sults i all raise an alarm within 8 seconds if any combination of active data and GNSS signals-in-space sults in an out-of-tolerance condition for en-route through APV I (3.5.7.4.1). s to all failure conditions including failures in core satellite constellation(s) or S AS tellites This monitoring assumes that the aircraft element complies with the re uirements of RTCA D C except as pe 3.5.7.8 Robustness to core satellite constellation(s) failures. Upon occurrence of a core satellite constellation(s) ed. Note The parameters that are referred to in th are define Note Some of the re uirements of this section may not apply to e uipment that integrates add ional navigation sensors AS with iner avigation sensors 3.5. SS receiver. Except as specifically noted, the SBASble GNSS rece the signals and meet the requirements specified (GPS rec and/or 3.2.3.1 (G SS receiver). Pseudonts for each satellite shall b using c ts and r which deviates in 200 seconds after i , relative respo fined in 3.6.5.1 i en the code phase a rated carrier phase p to 0.01 metre pe d. 3.5. f data. The receiver shall use data from S message only if the CRC of this message tion of a Type 0 messag om an SBAS satellite shall result in desel that satellite and all d iscarded for at le minute. For GP es, the receiver ly long-term correctio the IODE and ast significant bi DC. For GL atellites, the receiver corrections only if the of reception (t NASS ep s inside the followin s defined in 3.5.4.4.1: tLT L  tr  tLT L Not ing the S AS satellite re n an out-of-tolerance condition for precision approach or APV II (3.5.7.5.1). 3.5.7.7.2.6 SBAS sh re Note The monitoring applie sa su rseded by and Attachment D satellite anomaly, SBAS shall continue to operate normally using the available healthy satellite signals that can be track 3.5.8 AIRCRAFT ELEMENTS is section d in it such as e uipment that integrates S tial n 8.1 S AS AS capable N capa iver shall process A of the SB in 3.1.3.1 eiver) LON range measureme e smoothed ni on arrier measuremen to the steady-state a smoothing filte nse o ilter de less than 0.1 metre with tializati nd teg f the f n the presence of drift betwe in of u r secon 8.1.1 Conditions for use o an SBA has been verified. Recep e fr e f shall app ction o ata from that satellite shall be d ns only if the IOD matches both ast 1 S satellit 8 le ts r of the IO O s hemeris i NASS shall apply long-term g IOD validity interval, a time ) of the GLO V e This re uirement does not imply that the receiver has to stop trac 23/11/06 A 2007/70/II. szám A endix Annex 10 — Aeronautical Communications 3.5.8.1.1.1 The receiver s ted with that data matches the IODP associated with the PRN mask. 3.5.8.1.1.2 The receiver shall use SBAS-provided ionospheric data (IGP vertical delay estimate and GIVEIi) only if the IODIk associated with that data in a Type 26 message matches the IODIk associated with the relevant IGP band mask transmitted in a Type 18 message. 3.5.8.1.1.3 The receiver shall us e most recently ed integrity dat hich the IODFj equals 3 or the IODFj matches the IODFj associated with the correction data lied (if corre ided). 3.5.8.1.1.4 The receiver shall apply any regional degradation to the ı2 i,UDREas defined by a Type 27 service message. If a Type 27 message with a new IODS indicates a higher for the user location, the higher įUDRE shall be applied immediately. A lower įUDRE in a new Type 27 message ot be applied unt omplete set of messages with the new IODS has been received. 3.5.8.1.1.5 The receiver shall ly satellite-specific degradation to the RE 2 as defined by a Type 28 clockephemeris covariance matrix message įUDRE derived f Type 28 messag be applied immediately. 3.5.8.1.1.6 For GPS satellites, the receiver shall apply long-term corrections only if the IOD matches both the IODE and 8 LSBs of the IODC. Note For S AS satellites there is no mechanism n s E ranging tion data (Type message) and long rm corrections 3.5.8.1.1.7 In the event of a loss of four successive SBAS messages, the receiver shall no longer support SBAS-based 3.5.8.1.1.8 The receiver shall not use a broadcast data parameter after it has timed out as defined in Table B-56. Data Associated message types En-route, terminal, NPA time-out Precision approach, APV time-out hall use integrity or correction data only if the IODP associa e th receiv a for w fast being app ctions are prov įUDRE shall n il the c app ıi,UD e shall . The rom a that li func te precision approach or APV operations. able Data time out inter als Clock-ephemeris covariance matrix SBAS in test mode N/A N/A 600 s 600 s 2 to 6, 24 18 s 12 s 360 s 240 s 86 400 s a message PRN mask UDREI Fast corrections 2 to 5, 24 (see Table B-57) (see Table B-57) Long-term corrections 24, 25 360 s 240 s GEO ranging function data 360 s 240 s Fast correction degradation 360 s 240 s Degradation parameters Ionospheric grid mask 1 200 s 1 200 s Ionospheric corrections, GIVEI 600 s 600 s Timing data 86 400 s GLONASS time offset 600 s 600 s Almanac data None None Service level 86 400 s 86 400 s Note The time out intervals are defined from the end of the reception of A 23/11/06 2007/70/II. szám Annex 10 — Aeronautical Communications Volume I able Fast correction time out inter al e aluation Fast correction degradation factor indicator (aii) NPA time-out interval for fast corrections (Ifc) PA time-out interval for fast corrections (Ifc) 180 s 120 s 180 s 120 s 153 s 102 s 135 s 90 s 135 s 90 s 117 s 78 s 45 s 30 s 12 s 99 s 66 s 81 s 54 s 63 s 42 s 45 s 30 s 27 s 18 s 27 s 18 s 27 s 18 s 18 s 12 s 18 s 3.5.8.1.1.9 The receiver shall not use a fast correction if ǻt for the associated RRC exceeds the time-out interval for fast corrections, or if the age of the RRC exceeds 8ǻt. 3.5.8.1.1.10 The calculation of the RRC shall be reinitialized if a “Do Not Use” or “Not Monitored” indication is AN IN FUNCTI N ns. The root-mean-square (1 sigma) of the total airborne error cont for an SBAS satellite at the minimum received signal power level (Chapter 3, 3.7.3.4.4.3) under the worst interference environment as defined in 3.7 shall be less than or equal to 1.8 metres, excluding multipath effects, tropospheric and ionospheric residual errors. Note The aircraft element will bound the errors caused by multipath and troposphere ( ) For the purpose of ma) vironment as defined in 3.7 shall be less than or equal to metres, excluding multipath, tropospheric and ionospheric errors. received for that satellite. 3.5.8.1.1.11 For SBAS-based precision approach or APV operations, the receiver shall only use satellites with elevation angles at or above 5 degrees. 3.5.8.1.1.12 The receiver shall no longer support SBAS-based precision approach or APV operation using a particular satellite if the UDREIi received is greater than or equal to 12. .5.8.2 R 3.5.8.2.1 Precision approach and AP operatio ribution to the error in a corrected pseudo-range predicting service the multipath error is assumed to be less than metres ( sig 3.5.8.2.2 Departure en route terminal and non precision approach operations. The root-mean-square (1 sigma) of the total airborne contribution to the error in a corrected pseudo-range for an SBAS satellite at the minimum received signal ower level (Chapter 3, 3.7.3.4.4.3) under the worst interference en p 23/11/06 A 2007/70/II. szám A endix Annex 10 — Aeronautical Communications 3.5.8.2.3 S AS satellite position 3.5.8.2.3.1 Position computation. The receiver shall decode Type 9 message and determine the code phase offset and position (XG, YG, G) of the SBAS satellite. 3.5.8.2.3.2 S AS satellite identification. The receiver shall discriminate between SBAS satellites. Note This re uirement applies to false ac uisition of a satellite due to cross correlation 3.5.8.2.4 Almanac data 3.5.8.2.4.1 Recommendation The almanac data provided by the S AS should be used for ac uisition Note ealth and status information is provided in the E almanac data to support ac uisition but need not be used as a condition for use of that satellite 3.5.8.3 NSS satellite status function. The receiver shall exclude satellites from the position solution if they are entified as “Do Not Use” by SBAS. If SBAS-provided integrity is used, the receiver shall not be required to exclude GPS satellites based on the GPS-provided ephemeris health flag as required in 3.1.3.1.1 or to exclude GLONASS satellites based on GLONASS-provided ephemeris health flag as required in 3.2.3.1.1. e ble grity is not provided y S AS A AS or AS may be used to provide integrity if available erence environment as defined in 3.7 shall be less than or equal to 0.4 metres, xcluding multipath effects, tropospheric and ionospheric residual errors. The RMS of the total airborne contribution to the rror in a corrected pseudo-range for a GLONASS satellite at the minimum received signal power level (Chapter 3, 3.2.5.4) equal to 0.8 metres, excluding multipath effects, tropospheric and ionospheric residual errors. ate corrections and the broadcast ionospheric corrections. For GLONASS satellites, the ionospheric corrections received from the SBAS shall be 3.5.8.4.2.2 The receiver shall use a general-least-squares position solution. 3.5.8.4.2.3 The receiver shall apply a tropospheric model such that residual pseudo-range errors have a mean value ( ) metres and a 1 sigma deviation less than 0.07 metres. Note A model was developed that meets this re uirement uidance is provided in Attachment D id Note In the case of a satellite designated unhealthy by the core satellite constellation(s) health flag S AS may b to broadcast ephemeris and cloc corrections that will allow the user to continue using the satellite a Note If satellites identified as Not Monitored by S AS are used in the position solution inte b 3.5.8.4 ASIC AND PRECISE DIFFERENTIA FUNCTI NS 3.5.8.4.1 Core satellite constellation(s) ranging accuracy The root-mean-square (1 sigma) of the total airborne contribution to the error in a corrected pseudo-range for a GPS satellite at the minimum received signal power level (Chapter 3, 3.7.3.1.5.4) under the worst interf e e under the worst interference environment as defined in 3.7 shall be less than or 3.5.8.4.2 Precision approach and AP operations 3.5.8.4.2.1 The receiver shall compute and apply long-term corrections, fast corrections, range r multiplied by the square of the ratio of GLONASS to GPS frequencies (fGLONASS/fGPS)2. less than 0.15 A 23/11/06 2007/70/II. szám Annex 10 — Aeronautical Communications Volume I 3.5.8.4.2.4 The receiver shall compute and apply horizontal and vertical protection levels defined in 3.5.5.6. In this computation, ıtropo shall be: i 0.12 m 0.002 sin ( ) u  T where și is the elevation angle of the ith satellite. In addition, ıair shall satisfy the condition that a normal distribution with zero mean and a standard deviation equal to ıair bounds the error distribution for residual aircraft pseudo-range errors as follows: n y y y f (x)dx Q for all 0 and f § · d t ¨ ¸ V V © ¹ ³ y n y y f (x)dx Q for all  f § · d t ¨ ¸ V V © ¹ ³ w re he fn(x) probability density function of the residual aircraft pseudo-range error and

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