Figure 4 - uploaded by Clemens Riegler
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Bottom view of the Deployer, showing the ORBC-Box (top right), the GoPro-Box (Bottom), the through holes for all necessary cables and the 6 pyromounts which for the release mechanism
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... However, since 2013, when their work was written, further developments have been made. At JMU the Projects Daedalus 1 [14,15] and Daedalus 2 [16] were implemented. These tested two autorotation vehicles named SpaceSeed v1 and v2, respectively. ...
Humanity is striving to be an interplanetary species more than ever before. Therefore, not only launching but also
landing is a key capability for any future spacecraft. Right now, the state of the art is either landing by parachute or
a propulsive approach. Parachutes are hardly ever reused, hence not a good choice for reusable vehicles. Propulsive
landings do provide reusability but demand fuel and oxidizer, which might only be safe to use for a limited amount
of time, e.g. due to temperature constraints. A viable solution that combines controllability, reusability and does
not require any fuel is available in the form of autorotation. This is not a new technology in itself. Helicopters use
it for landing in case of an engine failure. However, in the context of space flight, this technology has hardly been
investigated. This paper shall present a number of possibilities of theoretical utilization of an autorotation system for
a Venus mission. The focus is on a number of different sized vehicles with different purposes that utilize autorotation.
Furthermore the vehicles will be evaluated upon their deployment method. A mission can be a small atmospheric
probe and deployed by a bigger mission or it can be a lander with direct re-entry. It is important to understand the
advantages and disadvantages of autorotation in these different scenarios. Furthermore, comparison of the viability of
the missions upon different performance parameters is made. This includes TRL, overall complexity and especially in
comparison with other decelerators. The goal is to create a baseline. It shows where missions might be able to benefit
by the utilization of autorotation. The possible limits of the technology are also outlined in this paper.
The Daedalus 2 mission aboard REXUS 29 is a technology demonstrator for an alternative descent mechanism for very high altitude drops based on auto-rotation. It consists of two probes that are ejected from a sounding rocket at an altitude of about 80 km and decelerate to a soft landing using only a passive rotor with pitch control. This type of autonomous, scientific experiment poses great challenges upon the electronics subsystem, which include mechanical stress, power system reliability, sensor redundancy, subsystem communication, and development procedures. Based on the data gathered in Daedalus 1 multiple new approaches were developed to fulfill these requirements, such as redundant communication links, mechanical decoupling of PCBs and fault-tolerant power source selection.
The Daedalus 2 mission aboard REXUS 29 is a technology demonstrator for an alternative descent mechanism for very high altitude drops based on auto-rotation. It consists of two probes that are ejected from a sounding rocket at an altitude of about 80 km and decelerate to a soft landing using only a passive rotor with pitch control.
This type of autonomous, scientific experiment poses great challenges upon the electronics subsystem, which include mechanical stress, power system reliability, sensor redundancy, subsystem communication, and development procedures.
Based on the data gathered in Daedalus 1 [1] multiple new approaches were developed to fulfill these requirements , such as redundant communication links, mechanical decoupling of PCBs and fault-tolerant power source selection.
