SB ALL @ AMSAT $ANS-149.01 Phase 3C In Less Than 2 Weeks HR AMSAT NEWS SERVICE BULLETIN 149.01 FROM AMSAT HEADQUARTERS WASHINGTON, DC May 28, 1988 TO ALL RADIO AMATEURS BT A June 10 launch date is slated for the first flight of Ariane 4 (the V-22 mission) including AMSAT's Phase 3C satellite. If all goes according to plan, the Amateur Radio world's newest and most capable satellite will be launched into a clear morning sky from the Guiana Space Center of the European Space Agency in Kourou, French Guiana, less than two weeks hence. After deployment from the launcher it will become AMSAT OSCAR 13 (AO-13). Phase 3C is a joint project of AMSAT-NA and AMSAT-DL with significant assistance from several affiliated AMSAT organizations. The launch date had been holding at June 8 following the recent successful launch of an Ariane 2 on May 17. Late last week, however, the V-22 mission schedule experienced a two day slip. A routine inspection of a launcher first stage turbine suggested a little deeper look might be appropriate. Consequently, all seven first stage turbines were to be inspected over the weekend. This caused a two day slip from June 8 to June 10. Unofficial sources indicate if the turbines need to be replaced it will take a week. That will push the launch date out to Friday, June 17. The inspections and the reaction to them by Arianespace continue a conservative philosophy of undertaking minimum risk in launch preparations. AMSAT sources expressed no particular concern saying these types of last minute delays are common. AMSAT expects to learn on Monday, May 30, if the additional all seven turbines will be replaced and thus if the launch date will slip from June 10 to June 17. Otherwise, progress towards the launch has been good. On May 26th the upper portion of the payload containing Meteosat and Phase 3C was integrated and enclosed within the fairing. On May 27th the fueling operation of the 3rd stage rocket was begun and completed over night. On Saturday, May 28th, the assembly of the two payload sections consisting of Panamsat in one and Meteosat/AMSAT P3C in the other were mated into the combined payload assembly. The Phase 3C satellite is complete and ready to launch. The Phase 3C safe/arm plug has been swapped so the spacecraft is nearing its fully armed condition. The Third Team's main task is to monitor telemetry until launch to insure all systems are "green". The Phase 3C satellite is in excellent condition and continues to send good telemetry data to the command station location according to Don Moe, DJ0HC/KE6MN who's part of the AMSAT-DL team in Kourou. Elements of the joint "Third Team" from AMSAT-NA and AMSAT-DL arrived Saturday, May 28, to see the satellite through to launch. AMSAT-DL has maintained a small maintenance crew on station throughout the launch preparations. Dave Cowdin, WD0HHU, of AMSAT-NA arrived but his baggage didn't. At last report they were searching for it. The launch windows for June 10 are similar to the prior windows if the launch had gone on June 8. The windows which had been announced for the June 8 launch which were: 11:12 -12:03 UTC and 13:25 - 14:44 UTC. A slight shift in these can be expected for a June 10 launch and an additional shift can be expected if the launch slips to June 17. These times are morning in Kourou. The launch will be broadcast by Arianespace on SPACENET 1. (The transponder has not been identified at this time but V-23 was broadcast on transponder 23). /EX SB ALL @ AMSAT $ANS-149.02 ALINS Coverage Extended HR AMSAT NEWS SERVICE BULLETIN 149.02 FROM AMSAT HEADQUARTERS WASHINGTON, DC May 28, 1988 TO ALL RADIO AMATEURS BT AMSAT Launch Information Network Service (ALINS) coverage will begin a few days before the launch with pre-launch coverage. ALINS pre-launch activity commencement date is now tentatively pegged at Monday, June 6 in a plan drawn up by W0RPK. (See ASR #176). This may slip as the actual launch date slips, however. Stay tuned to regular bulletin sources for the latest on ALINS coverage schedules. Stations participating in pre-launch and post-launch coverage on HF include W1AW at ARRL HQ , WA3NAN (at the Goddard Space Flight Center, Maryland) and W6VIO at the Jet Propulsion Lab in Pasadena. W1AW will include ALINS info in its normal bulletin schedule for the pre-launch and post launch days. (See April QST, page 87 W1AW bulletin schedule). WA3NAN will transmit on 7185, 14295 and 21395 kHz at 1600 UTC beaming Europe and 1610 UTC beaming Africa. W6VIO will transmit on 14282 and 21280 from 2015 to 2025 UTC on 20 meters and from 2030 to 2040 on 15 meters. On launch day W1AW will transmit launch activities on all its voice bulletin frequencies. WA3NAN will be on 3860, 7175, 14295, 21395 kHz and 147.45 MHz (FM). W6VIO will be on 14282, 21280, and 3840 (or 7165) kHz and local repeaters. W0RPK will be on 3840 and/or 7165 kHz and local repeaters in Iowa. W5RRR at the Johnson Space Center in Houston will join the network on launch day with transmitters covering 3840 and 7165 kHz as well as local repeater uplinks. The complete and revised ALINS plan will be included in these bulletins before launch and will include the latest updated kick-off date. /EX SB ALL @ AMSAT $ANS-149.03 New OSCAR DX Potential Superb! HR AMSAT NEWS SERVICE BULLETIN 149.03 FROM AMSAT HEADQUARTERS WASHINGTON, DC May 28, 1988 TO ALL RADIO AMATEURS BT With the imminent launch of Phase 3C, analysts have agreed on a general plan to place the new satellite in its final orbit with minimum risk. Meanwhile, potential users are beginning to look at the orbital profiles the new bird will fly once in its final orbit. What they're seeing is fascinating DX scenarios never before attainable. Computer analysis of the visibility contours suggest new breakthroughs in long-awaited DX windows from major user population centers to areas only rarely accessible on earlier birds. The result could be a sharp upsurge in satellite activity according to those now preparing to join the ranks of satellite users. The final orbit, which will be achieved within about 4 weeks of launch and after two or perhaps three burns of the kick motor, has the following approximate characteristics: Apogee: 35,800 km Perigee: 1,500 km Inclination: 57 degrees Argument of perigee: 178 degrees (initial) Period: 656.48 minutes Longitude Increment: 195.4 degrees east/orbit Based on these values, would-be orbital analysts can visualize the characteristics of the FINAL orbit using their tracking programs and the following TEST orbital element set. Please note the following IS NOT FOR TRACKING but merely to demonstrate the general characteristics and viewability of the new satellite. The actual Keplerian element set for the final operational orbit will be available only AFTER the final kick motor burn about 1 month after launch. Name: AO-13 Catalog Number: 000000 Element Set: T1 Ref Epoch: 88183.0 Inclination: 57.0 degrees RAAN: 0.0 degrees Eccentricity: 0.6850 Argument of perigee: 178.0 degrees Mean Anomaly 0.0 Mean Motion: 2.19351693 rev/day Drag: 6.0e-08 rev/day^2 Epoch rev: 48 Based on these values, AO-13's orbital period will be 43 minutes shorter than AO-10's and its inclination will be more than twice that of AO-10. The shorter period is due to AO-13's planned lower perigee of 1500 km compared to 3900 km of AO-10. The shorter period means that one MA "tick" on AO-13 will be 2.564 minutes compared to 2.732 minutes on AO-10; a 6 % reduction. There are 256 MA "ticks" per orbit. Operating activities are scheduled according to the on-board MA clock which determines which transponders are activated and when. The longitude increment of AO-10 is 185 degrees per orbit. This causes footprint positioning (to with 10 degrees of longitude) and coverage patterns to be replicated approximately every 18 days (37 orbits) on average. However, with AO-13, footprint positioning and coverage patterns will be replicated much more frequently. With a longitude increment of 195 degrees east per orbit, similar visibility patterns (to within 10 degrees of longitude) return after only 5 days (11 orbits); more than 3 times more frequently than has been the experience with AO-10. How this will affect operating habits is open to debate. Moreover, for users all over the world, for the first several months of operation, AO-13 at apogee will give nearly precisely the coverage of a geosynchronous satellite since it will have its apogee right over the equator. AO-13's planned apogee of 36,000 km is the altitude of geosynchronous satellites. Thus its footprint at apogee will be exactly the same as a geo-synch bird. The difference is, of course, that a Molniya orbit such as that into which AO-13 will be placed, is elliptical. So after a few hours at very high altitude, AO-13 will dive towards perigee and then make its way up to an apogee nearly half an earth away. Satellite footprints from geo altitude are exhilarating. With satellite longitude of 100 degrees West, for example, all of the Western Hemisphere is in the footprint except for parts of Greenland. Moved to 15 degrees West longitude, all of the U.S. and Canada east of the Mississippi, all of South America, Africa, Europe and the Middle East are in view! With DX windows like this, AO-13 is bound to become the most popular satellite of all time by far. /EX SB ALL @ AMSAT $ANS-149.04 Phase 3C Deployment Plans HR AMSAT NEWS SERVICE BULLETIN 149.04 FROM AMSAT HEADQUARTERS WASHINGTON, DC May 28, 1988 TO ALL RADIO AMATEURS BT The stack of three satellites carried by Ariane 4 is mounted on and within a large egg-shaped composite enclosure called a SPELDA which rides high atop the launcher above the third stage. This is shown in Amateur Satellite Report (ASR) #169. The payload stack consists of, top-to-bottom, Meteosat P2, AMSAT Phase 3C and Panamsat. The deployment sequence has Meteosat pop off the top of the stack first at about 20 minutes after launch. The fairing had been detached and the launcher had been oriented and spun up to about 5 rpm with small rocket (vernier) motors. Next, the carrying structure on which Meteosat had been mounted and within which Phase 3C is enclosed, is separated. This happens 5 seconds after Meteosat is separated or just over 20 minutes into the launch. Phase 3C will remain within the structure for a full hour more. At about 21 minutes after launch, the top of the egg-like SPELDA is separated revealing Panamsat within it. Two minutes later, at 23 minutes into the mission, Panamsat is separated from the lower SPELDA section. Finally, at 80 minutes after launch and 60 minutes after Meteosat deployment, Phase 3C, contained in the carrying structure, is deployed marking the birth of AMSAT OSCAR 13. At the moment of birth, AO-13 will be over the eastern Indian Ocean south of Sumatra at an altitude just over 14,000 km. Stations in Australia, Japan and India will have an excellent opportunity to hear AO-13 as it's born one hour and twenty minutes after launch. The General Beacon should be heard on 145.812 MHz by stations in range. South Africa may get a look too. At birth, AO-13 will be only 4 degrees above the eastern horizon at Johannesburg. New Zealand stations will get their first glimpse about 10 minutes later at about "Launch + 90 minutes". European stations will get their first AO-13 Acquisition of Signal (AOS) later with Munich having AOS at launch plus 5 hours, 19 minutes; London, 6 hours, 48 minutes. First AOS in the Western Hemisphere will occur when coastal Mexico sees AO-13 for the first time at 11 hours and 2 minutes after launch. The U.S. will gain AOS simultaneously in southern Texas and California at launch plus 11 hours and 6 minutes. Other AOS times on the first orbit include: Buenos Aires: L + 11:11 (launch plus hours and minutes) Chicago: L + 11:12 Sao Paulo: L + 11:13 Washington: L + 11:14 New York: L + 11:16 Boston: L + 11:17 Montreal: L + 11:18 | Initial GTO apogees occur at: | If launch @ 11:12 UTC, | |(Launch plus hours and minutes)| | June 10, then apogee at: | |---------------------------------|--------------------------| | #1 L + 5:34 @ 0.3 S 86.0 E | June 10 16:45 UTC | | #2 L + 16:11 @ 0.2 S 73.5 W | June 11 03:23 UTC | | #3 L + 26:48 @ 0.2 S 126.9 E | June 11 14:00 UTC | | #4 L + 37:25 @ 0.1 S 32.7 W | June 12 00:38 UTC | | #5 L + 48:03 @ 0.1 S 167.7 E | June 12 11:15 UTC | For later GTO apogees, add the GTO anomalistic period of 10:37 and 200.4 degrees eastward movement per orbit. The Keplerian elements used to develop these predictions were derived from the latest estimated launcher performance and time line and processed through a BASIC program developed by James Miller, G3RUH. The program is available as a BASIC listing on the W0RPK bulletin board. The resulting Keplerian elements are: Set Name: P3C GTO Ref Epoch: 88162.52220000 Inclin: 9.996 deg RAAN: 238.5 deg Ecc: 0.73099023 Arg Per: 178.155 deg Mean Anomaly: 36.51014 deg Mean Motion: 2.259879 rev/day Drag: 0 Rev at epoch: 0 SMA: 24528.91 km (If needed) Please carefully note that this Keplerian element set makes a significant assumption: It assumes the launch occurs exactly on June 10 at 11:12 UTC. Chances are it will not. Consequently, the actual Keplerian elements for the transfer ellipse orbit will be different. The reference epoch, RAAN and MA will change if the launch time changes. However, for relative timing of AOS/LOS (referenced to launch time) other similar planning exercises, this element set should suffice. The ground track resulting corresponds nicely with one circulated by DB2OS late last year. /EX SB ALL @ AMSAT $ANS-149.05 Phase 3C Launch Time Lines HR AMSAT NEWS SERVICE BULLETIN 149.05 FROM AMSAT HEADQUARTERS WASHINGTON, DC May 28, 1988 TO ALL RADIO AMATEURS BT Abbreviated Ariane V-22 Launcher and Payload Deployment Time Line Count Time (sec) Event H0 0 Opening of command valves of the first stage and ignition of liquid boosters 3.0 Ignition of solid strap-on boosters 3.4 Lift off H1 209.4 End of main thrust phase of first stage 214.3 First stage separation 217.2 Beginning of second stage main thrust phase 286.6 Jettison of fairing H2 339.9 End of main thrust phase of second stage 344.8 Second stage separation 349.9 Beginning of third stage main thrust phase H3 1062.4 End of main thrust phase of third stage H4 1064.4 Begin composite orientation to separation attitude H4.1 1195.4 METEOSAT P2/Ariane separation H4.2 1200.4 Carrying structure separation H4.3 1273.4 SPELDA top separation H4.4 1379.4 PANAMSAT separation H5 1594.4 Ariane end of mission 4800.4 AMSAT Phase 3C carrying structure separation The transfer orbit elements are: Time = H0 + 1063.8 sec Perigee altitude Zp = 219.95 km Apogee altitude Za = 36290 km Inclination i = 9.999 deg. Argument of perigee w = 178.004 deg (earth equatorial radius= 6378.135 km) The other orbit parameters (longitude of ascending node and true anomaly) are fixed by the launch vehicle flight plan. Ascending node longitude: -135.690 deg (ref is KRU meridian at H0-9sec) True anomaly : 12.532 degrees The derived AMSAT Phase 3C orbit parameters are: Perigee 222.53 km Apogee 36079.0 km Inclination 9.996 deg Perigee arg. 178.155 deg Ascending node longitude -135.783 deg True anomaly 127.571 deg Separation time after H0 4800.4 sec Use these with the G3RUH program available on the W0RPK BBS, 515-961-3325 /EX SB ALL @ AMSAT $ANS-149.06 Phase 3C Kick Motor Burn Plan HR AMSAT NEWS SERVICE BULLETIN 149.06 FROM AMSAT HEADQUARTERS WASHINGTON, DC May 28, 1988 TO ALL RADIO AMATEURS BT After months of planning, AMSAT engineers and scientists in several nations have jointly determined what they believe to be an optimal series of maneuvers to change AO-13's orbit from its initial value to a stable, useful one. They will achieve this, they say, with minimum risk given the anticipated engine performance. To accomplish this involves close measurement of the orbit, careful calculation of the motor performance and timely execution of at least two kick motor burns. The Ariane 4 launcher will place the three payload satellites in a so-called GTO or geosynchronous transfer orbit. With a perigee height of only 222 km (137 miles), it is necessary to use the kick motor to boost the perigee as soon as possible. Each of the three satellites in the stack employs its own kick motor. Initially AMSAT will rely on European Space Agency and NASA tracking data for the orbital data. During the first few days AMSAT will employ its own tracking system for calibration only. AMSAT's technique depends on active ranging using round-trip delay time measurements to the satellite. Then, after kick motor burn, AMSAT will do its own orbit determination. Because of the small radar cross-section of AO-13, it is very difficult to find at 36,000 km. In a general sky-search using even the most power ground-based radars it could not be located. However, given a fairly small vicinity in which to search, the large government radars can track with precision thereafter. AMSAT will thus narrow the search range using its own equipment and ranging techniques to provide vital hints to officials operating the radars. The initial orbit as provided by the Ariane will have a 222 km perigee; 36,000 km apogee; 10 degree inclination. The desired final orbit has perigee at 1500 km; apogee at about 36,000 km and inclination at 57 degrees. The first kick motor burn will be accomplished as soon as possible; within a week of launch is likely. Atmospheric drag would cause the satellite to fall from orbit in a few weeks if nothing were done to raise the perigee. The strategy worked out by KA9Q, N4HY and G3RUH is a conservative one which, according to KA9Q, uses the first burn to "make the second one safe. That is," he says, "the first burn should be just long enough so that at no time during the second burn will the instantaneous perigee decrease below a safe value of 500 km." Thus, the plan calls for a first burn yielding a delta V (change in velocity) of 453.735 m/sec, giving an intermediate orbit of 856 km x 36086 km with inclination of 26 degrees. Then, burn #2 would require a delta V of 903.899 m/sec giving a final orbit of 1500 km x 36086 km inclined 57 degrees. The first burn gives an opportunity to calibrate the motor performance by analyzing the actual intermediate orbit. Using available orbital data, DJ4ZC at AMSAT-DL will execute the first burn from Marburg, West Germany. KA9Q and N4HY in New Jersey will then carefully determine the intermediate orbit and estimate the delta V of the satellite. This will calibrate the motor performance during the first burn. With this data in hand, a precise second burn can be planned and executed perhaps within two or three weeks of the initial burn. Quick and accurate ranging during this period will be essential. If the burn is a little short, another one with the same orientation can be accomplished to make up the difference. "If it is a little long," says KA9Q, "we will be taking more of a `insurance dogleg' than is necessary but we'll probably still make it to the final orbit. Clearly it would be better to err on the short side." The plan calls for all burns to be done at apogee. No attempt will be made to change the argument of perigee. With an initial setting at 178 degrees, apogee will occur nearly over the equator. Apogee will move north such that 3.5 years after launch, apogee will occur at 57 degrees North latitude. In another 3.5 years, apogees will return to the equator. Thus, apogee will remain in the Northern Hemisphere for the first 7 years of the satellite's operation and in the Southern Hemisphere for the second 7 years. /EX SB ALL @ AMSAT $ANS-149.07 Phase 3C Operating Frequencies HR AMSAT NEWS SERVICE BULLETIN 149.07 FROM AMSAT HEADQUARTERS WASHINGTON, DC May 28, 1988 TO ALL RADIO AMATEURS BT As previously announced, here are the Phase 3C operating frequencies. Frequencies of Phase 3C operation have been published in ASR #173 and the upcoming ASR Special Edition #177. The frequencies also appear in June QST, page 22. The operating bandplan and schedule will be announced after launch. Mode B: Uplink: 435.420 - 435.570 MHz Downlink: 145.975 - 145.825 MHz GB: 145.812 MHz EB: 145.985 MHz Mode JL: L Uplink: 1269.620 - 1269.330 MHz J Uplink: 144.425 - 144.475 MHz RUDAK up: 1269.710 MHz L Downlink: 435.715 - 436.005 MHz J Downlink: 435.990 - 435.940 MHz RUDAK down: 435.677 MHz GB: 435.651 MHz Mode S: Uplink: 435.601 - 435.637 MHz Downlink: 2400.711 - 2400.747 MHz Beacon: 2400.325 MHz /EX SB ALL @ AMSAT $ANS-149.00 SKITREK Progress Report #18 HR AMSAT NEWS SERVICE BULLETIN 149.08 FROM AMSAT HEADQUARTERS WASHINGTON, DC May 28, 1988 TO ALL RADIO AMATEURS BT The Amateur Radio supported Transpolar Skitrek Expedition moved toward a close last week as the skiers reached a point just 71 km away from the Canadian shore on Saturday, May 28th. They will be making landfall at Ward Hunt Island which has a latitude of 83 degrees 6 minutes North. A 10 km wide lead awaits them in the next few days which they will cross in large inflatable rafts brought by Twin Otter aircraft from Resolute Bay. The rafts the skiers have carried with them are small, single person units, that are impractical to use on large bodies of water such as the lead the skiers face. The Soviet skiers have requested and will receive a final resupply just before crossing the lead. The weather and ice conditions of late have made for slow progress. Fog, rough ice with water on it, pressure ridges and many small open leads have limited the skiers movement to about 22 km per day. Moderating temperatures (between -10 and -6 Celsius) are causing much of the ice problems along with a rapid (as much as 12 km/day) southward drift of the ice pack. If progress continues at the current rate, and the large lead does not slow them down, the skiers should make Ward Hunt Island between June 1st and 3rd. The Soviet Ice Island NP-28 has not experienced any further damage due to ice fracturing since the loss of communications gear last week. Barry Garratt, 4K0DX/VE3CDX planned to leave the island May 29th and is returning to Canada via the Soviet Union. The Royal Canadian Air Force has joined the Skitrek communications team with their amateur station VE8RCS located at Alert on Ellesmere Island. A special supplement to this report will be issued on Tuesday, May 31st, prior to the Wednesday (UTC) North America Nets. Skitrek Report #19 will be issued on the day the trek ends. This report has been prepared by Rich Ensign, N8IWJ, AMSAT Science Education Advisor For Use With The AMSAT Teachers' Guide "Exploring The High Arctic From Your Classroom". /EX SB ALL @ AMSAT $ANS-149.09 Short Bursts HR AMSAT NEWS SERVICE BULLETIN 149.09 FROM AMSAT HEADQUARTERS WASHINGTON, DC May 28, 1988 TO ALL RADIO AMATEURS BT Here is the AO-10 operating schedule per ZL1AOX: From May 14 thru May 31: MA 20 through MA 220 From June 01 thru June 14: MA 25 through MA 225 From June 15 thru June 30: MA 30 through MA 230 Please use minimum power required for communications. Here is the FO-12 operating schedule for the next month Mode From (UTC) ---------------- D May 30 0217 JA = Analog mode JD Jun 04 0353 JD = Digital mode DI 05 0259 D = All systems off JD 07 0110 DI = Systems off except CPU and memory DI 08 0218 JD 11 0546 DI 12 0654 JD 14 0505 DI 15 0613 JD 18 0533 D 19 0439 JA 22 0156 D 23 0304 JA 25 0318 D 27 0131 JA 29 0143 D Jun 30 0049 The transponders will be off at other times. The actual operating schedule may change due to unexpected situations such as variations in available power. /EX