The Study of the Asymmetric Multiple Encounters Problem and Its Application to Obtain Jupiter Gravity Assisted Maneuvers

Table 1

Solutions with Δ𝑉<0.1.

Eccentricity	𝜓 (rad)	True anomaly	Eccentric; anomaly	Velocity; variation
		𝜈 (rad)	𝜂 (rad)	Δ𝑉
𝑒=0	−0.001	1.9990	1.9990	0.000111
	−2.001	0.9990	0.9990	0.000167
	0.933	1.9330	1.9330	0.000179
	−0.099	0.9010	0.9010	0.000195
𝑒=0.1	−0.001	1.9988	1.9986	0.000176
	−2.001	0.9988	0.9986	0.000209
	−0.002	1.9975	1.9973	0.000353
	−2.002	0.9975	0.9973	0.000419
𝑒=0.5	−2.001	0.9965	0.9940	0.008940
	−0.001	1.9965	1.9940	0.008940
	1.999	1.9965	1.9980	0.008946
	1.999	0.9965	0.9980	0.008964
𝑒=0.9	0.000	2.0000	2.0000	0.007984
	2.000	1.0000	1.0000	0.007984
	−2.000	1.0000	1.0000	0.012248
	2.000	2.0000	2.0000	0.012248