For these tests the gps receiver should be simulated

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For these tests, the GPS receiver should be simulated in motion from the "Initial Location" at the beginning of the test and should then move along a great circle route with the specified "Ground Speed" toward the "Final Location". The receiver should be positioned at the appropriate geometric altitude with the specified pressure altitude input at the beginning of the test. These altitudes are either maintained or reduced as specified by the "Altitude Profile". The geometric altitude and the pressure altitude input should begin to be reduced at the "Time of Top of Descent" and should be reduced to the specified altitude at the "Time of Bottom of Descent". The initial conditions for these tests are as follows: Test No. Initial Location (Lat/Long ) Altitude Profile (Feet) Time of Top of Desce nt Time of Botto m of Desce nt Integri ty Alarm Limit (nm) Faile d SV Initial SV Errors* (Meters) Initial Altitude Error** (Meters) Groun d Speed (Knots ) 1 34 ° N /118 ° W 40,000 Descend to 5,000 21:30 22:20 1.0 SV3 SV6,SV1 0 & SV21: +33 SV8: -33 +150 600 2 34 ° N /118 ° W 40,000 Descend to 5,000 21:30 22:20 1.0 SV3 SV6, SV10 & SV21: +33 SV8 & SV13: -33 0 600 3 34 ° N /118 ° W Level at 500 NA NA 1.0 SV3 SV6, SV10 & SV21: +33 SV8 & SV13: -33 0 600 4 34 ° N /118 ° W 6,000 Descend to 500 22:15 22:55 2.0 SV3 SV6, SV10, SV21: +33 SV8: -33 +150 600 1Page 23
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TSO-C129a * A positive SV error causes a pseudorange which is smaller than the actual distance from the receiver to the SV. ** A positive altitude error causes a barometric altitude which is higher than the geometric altitude. a. For these tests the SVs change their orbital positions and the identified "Failed SV" must not provide any signals to the receiver for the duration of the tests. If an initial error is not specified for a space vehicle (SV) pseudorange measurement, the error for the test for those SVs should be set to zero. Data should be recorded for each test during the specified "Period of Test" to determine the time at which the RAIM integrity limit alarm is activated. For a successful test, this alarm must not occur during the time from the start of the test to the time identified as the "Earliest Alarm Time", but must occur between the time identified as the "Earliest Alarm Time" and the "Latest Alarm Time". As shown below a positive error rate in meters per minute is induced in either the identified SV pseudorange value or the pressure altitude input beginning at the "Start Time of Ramp Error" and continuing until the end of the test. The magnitude of the error rate is specified by the "Error Rate". Test No. Period of Test Error Source Start Time of Ramp Error Error Rate (Meters/Min ) Earliest Alarm Time Latest Alarm Time Final Position (Lat/Long) 1 21:05 to 22:43 SV13 22:12 30 22:31:10 22:38:5 7 33 ° N/ 97 ° W 2 21:05 to 22:44 Altimeter 22:12 72 22:31:07 22:35:3 1 33 ° N/ 97 ° W 3 21:20 to 22:59 Altimeter 22:10 40 22:38:12 22:55:5 6 33 ° N/ 97 ° W 4 21:20 to 22:57 SV13 22:22 27 22:35:25 22:43:1 7 33 ° N/ 97 ° W Page 24    (a)(3)(vii)  
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TSO-C129a NOTE 1: All tests in Section 2.5.2.5.3.8 apply to RAIM algorithms that incorporate the altitude measurement as described in Section (a)(3)(xxi). For the tests of RAIM with altitude data
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