Trajectory options to Pluto via gravity assists from Venus, Mars, and Jupiter

Transcription

1 Copyright 1996, American Institute of Aeronautics and Astronautics, Inc. AIAA Meeting Papers on Disc, 1996, pp A , NGT-51129, AIAA Paper Trajectory options to Pluto via gravity assists from Venus, Mars, and Jupiter Jon A. Sims Purdue Univ., West Lafayette, IN Andrew J. Staugler Purdue Univ., West Lafayette, IN James M. Longuski Purdue Univ., West Lafayette, IN AIAA/AAS Astrodynamics Conference, San Diego, CA, July 29-31, 1996, Collection of Technical Papers (A ), Reston, VA, American Institute of Aeronautics and Astronautics, 1996, p We use analytic and numeric techniques to assess trajectory options for the Pluto Express science spacecraft to be launched early in the next decade. These techniques have been shown to be highly efficient and thorough. The constraints placed on the Pluto Express trajectory for this study are severe (total flight time to Pluto of 12 years or less using a Delta-class launch vehicle with no upper stage). In addition, no gravity assists involving the Earth are permitted. Using the aforementioned techniques, we found suitable trajectories with launch windows before, near, and after the date of the baseline launch. We also discovered several asteroid flyby opportunities for the baseline mission and for a backup trajectory. (Author) Page 1

2 AIAA CP TRAJECTORY OPTIONS TO PLUTO VIA GRAVITY ASSISTS FROM VENUS, MARS, AND JUPITER Jon Andrew Sims* Andrew James Staugler,t and James Michael Longuski* School of Aeronautics

3

4 reached at which a single flyby can no longer turn the Voo parallel to Vv, and the single flyby curve in Figure 1 leaves the solid curve. The final aphelion radius then reaches a maximum and decreases. Multiple (n) Venus flybys increase

5 Vinf(km/a): a /10/09 : O3/09/ 11 : 03/08/14 : 03/07/ 17 - ^03/06J 19 : : (d 03/05/22 : T3

6 be due to the inability of STOUR to do VOQ leveraging.

7 Table 1 Trajectory Characteristics Table 1 Trajectory Characteristics (continued) Trajectory Launch Perihelion Perihelion Venus 1 Manuever Perihelion Venus 2 Jupiter Pluto I EVVJP 4/3/2002 8/10/2002 5/23/2003 6/15/2003 1/14/2004 9/11/ /2/2004 2/7/2006 4/3/2014 [2+AV-VGA] C 3 = km 2 /s AU 0.696

8 Table

9 Table 2 Trajectories to Pluto Using the Delta 7925 (Flight Time: 12 years) Trajectory Number Trajectory Type Launch Date C 3 (km 2 /s 2 ) AVp L (km/s) AVjjAV (m/s) Injection Margin (kg) I II III IV V VI VII VIII IX X VVJ VVJ VVJ VVJ VVJ VVVJ VVVJ VMVVJ VMVVJ VVVJ 4/3/2002 4/3/2002 5/11/2002 5/13/2002 7/17/2002 7/20/2002 7/29/2002 8/9/2002 8/14/2002 8/23/ Earlier Launch Dates Having found trajectories satisfying our initial constraints,

10 Table 3 Examination of Flight Time to Pluto Table 5 Baseline Trajectory Characteristics Traj. No. Launch Date TOF (yrs) C 3 (W/s 2 ) AV PL (km/s) Rad. a (flj) Baseline EVVVJP [2+ A V- VGA, 4+ A V- VGA] I II III 4/3/02 4/3/02 4/5/02 4/3/02 4/5/02 4/6/02 5/11/02 5/12/02 5/13/ , ,82 4.,32 3.,60 4.,02 4.,68 3., ,, Launch Perihelion Venus 1 Maneuver Perihelion Venus 2 Maneuver Perihelion Venus 3 Jupiter 3/9/2001 7/21/2001 8/29/2001 3/20/ /6/ /25/2002 1/23/2004 5/14/2005 6/1/2005 7/11/2006 C 3 = km 2 /s AU (min) Voo = 8.72 km/s AV IV 5/13/02 5/14/02 5/15/ ,.45 3, Pluto 3/10/2013 V 7/17/02 7/19/02 7/20/02 7/19/ , IX 8/14/02 8/14/02 8/14/

11 Table 7 Potential Asteroid Flybys on the Final Venus-Venus

12 trajectory has a launch date in July 2002 (sixteen months after the baseline), and an excellent launch opportunity exists