An adaptive, semi‑analytical, and geometrically clear method for synthesis of sequences of Venusian gravity‑assist maneuvers setting the desired inclination of a spacecraft orbit is proposed. The geometric constraint on the maximum possible inclination of a spacecraft orbit, which depends on the asymptotic spacecraft velocity relative to Venus, and the dynamic constraint (arising when a gravity‑assist maneuver is performed) on the angle of rotation of the vector of asymptotic velocity relative to Venus are considered simultaneously.
Abstract
This study discusses the usage of Venus gravity assist in order to choose and reaching any point on Venusian surface. The launch of a spacecraft to Venus during the launch windows of 2029 to 2031 is considered for this purpose. The constraints for the method are the re-entry angle and the maximum possible overload. The primary basis of the proposed strategy is to use the gravitational field of Venus to transfer the spacecraft to an orbit resonant to the Venusian one – with the aim of expanding accessible landing areas. Results of the current research show that this strategy provides an essential increase in accessible landing areas and, moreover, may provide an access to any point on the surface of Venus with a small increase in ∆V required for launch from the Earth and in the flight duration. The comparison with the landing without using gravity assist near planet is also given.
Synthesizing spacecraft orbits with high inclinations using Venusian gravity assists