Bi-elliptic transfer | Wikipedia audio article
Channel: wikipedia tts
Date: 05/10/2019

This is an audio version of the Wikipedia Article:
https://en.wikipedia.org/wiki/Bi-elliptic_transfer


00:01:07 1 Calculation
00:01:16 1.1 Delta-v
00:08:07 1.2 Transfer time
00:09:50 2 Comparison with the Hohmann transfer
00:10:00 2.1 Delta-v
00:13:34 2.2 Transfer time
00:14:41 3 Example
00:14:53 4 See also
00:15:16 5 References
00:15:47 40r0
00:16:37 507 688 km (1.3 times the distance to the Moon) would result in a 1% Δv saving over a Hohmann transfer, but require a transit time of 17 days. As an impractical extreme example, an apogee of 1757r0
00:17:40 See also



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SUMMARY
=======
In astronautics and aerospace engineering, the bi-elliptic transfer is an orbital maneuver that moves a spacecraft from one orbit to another and may, in certain situations, require less delta-v than a Hohmann transfer maneuver.

The bi-elliptic transfer consists of two half-elliptic orbits. From the initial orbit, a first burn expends delta-v to boost the spacecraft into the first transfer orbit with an apoapsis at some point 
  
    
      
        
          r
          
            b
          
        
      
    
    {\displaystyle r_{b}}
   away from the central body. At this point a second burn sends the spacecraft into the second elliptical orbit with periapsis at the radius of the final desired orbit, where a third burn is performed, injecting the spacecraft into the desired orbit.While they require one more engine burn than a Hohmann transfer and generally requires a greater travel time, some bi-elliptic transfers require a lower amount of total delta-v than a Hohmann transfer when the ratio of final to initial semi-major axis is 11.94 or greater, depending on the intermediate semi-major axis chosen.The idea of the bi-elliptical transfer trajectory was first published by Ary Sternfeld in 1934.