Design and development of a System Drop Test for the validation of Space Rider Descent and Landing mission phase

Paper number

IAC-22,D2,6,2,x74174

Author

Dr. Giuseppe Rufolo, Italy, CIRA Italian Aerospace Research Centre

Coauthor

Mr. Paolo Vernillo, Italy, CIRA Italian Aerospace Research Centre

Coauthor

Mr. Giovanni Cuciniello, Italy, CIRA Italian Aerospace Research Centre

Coauthor

Dr. Francesca Maria Pisano, Italy, CIRA Italian Aerospace Research Centre

Coauthor

Dr. Angelo De Fenza, Italy, CIRA Italian Aerospace Research Centre

Year

2022

Abstract

In the frame of the European Space Agency Space Rider (SR) Program, the Italian Aerospace Research Center (CIRA), under the supervision of the Prime Contractor Thales Alenia Space, is responsible for the design and implementation of a system level test for the in flight verification of the Descent and Landing phase of the mission. 
In that perspective, a dedicated flight test is foreseen to demonstrate the integrated parafoil /GN&C capability to operate in representative flight conditions, ensuring the guidance of the re-entry model under the parafoil up to the achievement of a precision landing.
The test article is a full-scale vehicle model replicating 1:1 the Space Rider Re-entry Module in shape, mass distribution and size; furthermore, it is also representative of some interfaces/layout arrangement and functioning of critical subsystem as Descent System, Landing System, Mechanism, GN&C. The Descent and Landing Test Model will integrate the following items:

\begin{itemize}\item an ad-hoc load-carrying structure able to withstand the foreseen loads of the test scenario;
\item a Flight Model version of the Descent & Landing S/Ss, including the parafoil with winches acting as attitude control actuators and a dedicated control unit, the landing system with nose and main landing gears, some other related Mechanisms. 
\item an ‘ad-hoc’ designed Test Avionic (OBDH, Power, Telecommunication System) replicating Space Rider functionalities for the Descent and Landing Phase.
\end{itemize}

The industrial team lead by CIRA, includes: the Romanian National Institute for Aerospace Research (INCAS), in charge of designing and manufacturing the Space Rider Mock-Up as well as of the procurement of the test site and carrier; and Deimos Space Romania, providing support for the mission analysis. 

The paper describes the strategy being adopted to achieve the qualification of the DLS of Space Rider and provides details over the development process from the analysis of the SR mission constraints, the design of the system and the test campaign, until the validation of all the functions expected to be reproduced.

Abstract document

IAC-22,D2,6,2,x74174.brief.pdf

Manuscript document

(absent)