A Theorem on Space Quantization by Kronig R.

By Kronig R.

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1. 1. Introduction Most future science missions (except for Earth observation) require launching on escape orbits or weakly bound orbits (astronomy). The most effective way to leave the Earth gravity field is to increase the velocity as close to the Earth as possible. 1Rt (altitude: 317–630 km for a mean radius Rt of 6370 km for the Earth). 904 km/s. 5 2 1 − Vper = Vc Rper a where a is the semi-major axis of the orbit. The circular orbit is of particular interest, as it has to be reached by the launcher in a single thrust arc, otherwise the spacecraft will collide with the Earth somewhere on its orbit.

Planetary science covers an enormous range of disciplines, from Earth sciences (internal geophysics, geochemistry, geology, . . ) to atmospheric sciences and space plasma physics (ionized environment and interaction with the solar wind). g. an aeronomy mission, focussing on the ionosphere and environment, a mission focussing on the atmosphere and a surfaceoriented mission). As shown in Fig. 5, this sequence with four stages has been the general trend for all solar system objects apart from the Moon: the Apollo program had mainly political and strategic goals (such as closing the “missile gap” opened by the first Sputnik) and was only marginally (at least as far as the first missions were concerned) dedicated to science.

17 with the insertion of Mars Express. 17. Insertion of Mars Express (25/12/2004); the mass at approach was 1130 kg (the Beagle lander had already been jettisoned); 2200 s of thrust with the 400 N engine were required to brake down to an orbit with a period of 10 days. The insertion delta V was 800 m/s, a gravity loss of only 40 m/s as the whole thrust arc was relatively close to Mars. The 10-day orbit had its pericentre 31◦ away from the subsolar point and it was nearly equatorial. After half an orbit, a plane rotation was performed at apocentre to obtain a near-polar orbit (I = 87◦ ), at a cost of 120 m/s.

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