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fi > 2 000 MHz
* Applies to aircraft re no on-board satellite communi
** Applies to aircraft s on-board satellite communicatio
i ≤ 1
1 562.15625 MHz < fi ≤ 1 583.6525 MHz Linearly dec
1 583.65625 MHz < fi ≤ 1 592.9525 MH
1 592.9525 MHz < fi ≤ 1 609.36 MHz –149
–8.5 dBW
installations where there a
installations where there i
cations.
ns.
23/11/06 APP B-122
Appendix B Annex 10 — Aeronautical Communications
3.7.3 BAND-LIMITED NOISE-LIKE INTERFERENCE
3.7.3.1 GPS AND SBAS RECEIVERS
3.7.3.1.1 After steady-state navigation has been precision approach
phase of flight or used on aircraft with on-board satellite communications shall meet the performance objectives with noiselike
interfering signals present in the frequency range of 1 575.42 MHz ±Bwi/2 and with power levels at the antenna port
equal to the inte al level of –164.5 dBW
t the antenna port.
Note.— Bwi is the equivalent noise bandwidth of the interference signal.
3.7.3.1.2 GPS and SBAS re eir performance objectives with
interference thresholds for band-limited noise-like signals 3 dB less than specified in Table B-84. For terminal area and en-route
steady-state navigation op al acquisition of the GPS a ior to steady-state navigation, the
interference thresholds for band-lim se-like signals shall be 6 dB less than those specified in Table B-84.
3.7.3.2 GLONASS RECEIVERS
3.7.3.2.1 After steady-state navigation has been established, GLONASS receivers used for the precision approach
phase of flight or used on aircraft with on-board sa unications shall meet the performance objectives while
receiving noise-like interferin the antenna port equal to the
interference thresholds defined i he antenna port.
Note.— fk is the centre frequency of a GLONASS channel k 602 MHz + k × 0.6525 MHz and k = –7 to + 13 as
defined in Table B-16 and Bwi is the equivalent noise b e s
ONASS receivers used for non-prec hall meet their pe objectives with
inte s for band-limited noise-like signals cified in Table B-84. minal area and enrou
igation operations, and for initial acquisiti e GLONASS signals prior y-state navigation,
the ited noise-like signals shall be 6 dB less than those specified in Table B-85.
Note.— For the approach phase of flight it is assumed that the receiver operates in tracking mode and acquires no new
tellites.
3.7.3.3 Pulsed interference. After steady-state navigation has been established, the receiver shall meet the performance
objectives while receiving pulsed int th characteristics according to Table B-86 where the interference
threshold is defined at the antenna por
3.7.3.4 SBAS and GBAS receivers shall output misleading information in the presence of interference including
interference levels above those specified in 3.7
Note.— Guidance material on this requirement is given in Attachment D .6.
3.8 GNSS aircraft satellite receiver antenna
3.8.1 Antenna coverage. The GNSS antenna shall meet the performance requirements for the reception of GNSS
satellite signals from 0 to 360 degrees in azimuth and from 0 to 90 degrees in elevation relative to the horizontal plane of an
aircraft in level flight.
3.8.2 Antenna gain. The minimum antenna gain shall not be less than that shown in Table B-87 for the specified
elevation angle above the horizon. The maximum antenna gain shall not exceed +7 dBic for elevation angles above 5 degrees.
established, GPS and SBAS receivers used for the
rference thresholds specified in Table B-84 and Figure B-17 and with the desired sign
a
ceivers used for non-precision approach shall meet th
erations and for initi nd SBAS signals pr
ited noi
tellite comm
g signals in the frequency band fk ±Bwi/2, with power levels at
n Table B-85 and with a desired signal level of –165.5 dBW at t
with f = 1
andwidth of the interferenc ignal.
3.7.3.2.2 GL ision approach s
3 dB an spe
rformance
rference threshold
e steady-state nav
less th
on of th
For ter
t to stead
interference thresholds for band-lim
sa
erference signals wi
t.
not
.
, 10
APP B-123 23/11/06
Annex 10 — Aeronautical Communications Volume I
3.8.3 Polarization. The GNSS antenna polarization shall be right-hand circular (clockwise with respect to the direction
of propagation).
3.9 Cyclic redundancy check
Each CRC shall be calculated as the remainder, R(x), of the Modulo-2 division of two binary polynomials as follows:
k
mod 2
[x M(x)] Q(x) R(x)
G(x) G(x)
⎧ ⎫
⎨ ⎬ = +
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