Timeline for How will the RADARSAT Constellation Mission (RCM) satellites achieve their final orbital spacing?
Current License: CC BY-SA 4.0
14 events
| when toggle format | what | by | license | comment | |
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| S Jan 28 at 22:02 | history | bounty ended | CommunityBot | ||
| S Jan 28 at 22:02 | history | notice removed | CommunityBot | ||
| Jan 28 at 3:58 | comment | added | uhoh | @Woody I don't think there's a situation or a problem, just a question. About the area, the SAR array is probably much larger than the solar panel. | |
| Jan 28 at 2:45 | comment | added | Woody | @uhoh ... Dispersion after release from second stage was 5 days. This can be accomplished with 30m/sec difference in orbital speed. The satellites have lots of thrusters and 50 l of hydrazine. The bus is a standard design with the design's usual solar panels. Doesn't sound like a" very large cross section". I think I understand the situation but I'm having trouble seeing the problem. | |
| Jan 28 at 1:37 | answer | added | Woody | timeline score: -1 | |
| Jan 27 at 23:45 | comment | added | uhoh | @Woody While the bounty is now invisible, there's still 21+ hours left on the 24 hour grace period It ends at 01-28 at 20:44 UTC. | |
| Jan 27 at 23:41 | comment | added | uhoh | @Woody last sentence "I'm looking for an authoritative answer backed up by references, not speculative 'probably' or 'potentially' worded answers." From space.skyrocket.de/doc_sdat/radarsat-constellation.htm it seems they have very large cross-sectional area. Did they use thrusters, or differential drag for example? Did they achieve it quickly, or do it slowly to conserve propellants? | |
| Jan 21 at 4:02 | comment | added | Woody | Is there a reason this is other than a standard orbit phasing exercise? en.wikipedia.org/wiki/Orbit_phasing. If so, it would be interesting if this were edited into the OP | |
| S Jan 20 at 20:44 | history | bounty started | uhoh | ||
| S Jan 20 at 20:44 | history | notice added | uhoh | Draw attention | |
| Aug 5, 2019 at 20:16 | comment | added | Mefitico | Then again, an autonomous orbit maintenance system could achieve whatever final orbit by doing its thing. You'd see that by noting slow changes in the TLE's mean motion field. Either case, it wouldn't be conclusive. | |
| Aug 5, 2019 at 20:14 | comment | added | Mefitico | I seriously doubt you'd get access to the maneuvering plan/report that the operation team develops. And that would be the only truly "authoritative" answer you could get. But then, why do you need to do that? An option you have downloading TLEs for both satellites from launch until they're in their final orbit. This should allow testing some hypothesis. The basic one being that they'll probably launch the satellites with different semi-major axes, which cause a phasing difference, and upon orbit correction, they'll maneuver into the final orbit. | |
| Jun 27, 2019 at 17:20 | comment | added | asdfex | So you're looking for a precise plan for propulsive maneuvers of the three satellites? In the end it should be as simple as accelerating by ~10 m/s and waiting a couple of days.... | |
| Jun 27, 2019 at 14:52 | history | asked | Organic Marble | CC BY-SA 4.0 |