Muriel Richard | EPFL Graph Search

Mrs. Richard got her Masters degree in 1996 from the California Institute of Technology (USA) in Mechanical Engineering. She worked at the NASAs Jet Propulsion Laboratory from 1994 till 2005, early on for the Mars Program, and then for the Advanced Propulsion Technology Group. She becomes a senior engineer in 2001 when she moves to JPLs Mission Architecture Group. In 2005, she was employed by the Space Center EPFL in Switzerland to manage the SwissCube satellite project, and later on to manage the Clean-mE research and technology development program on Active Debris Removal. Since January 2012, she is the Project Manager of the CleanSpace One mission.

Capture system adapted to capture orbital objects, in particular for deorbiting purposes

Pierre-Alain Mäusli, Michaël Pellet, Muriel Richard

There is described a capture system (100) adapted to capture orbital objects (2000), in particular for deorbiting purposes. The capture system (110) comprises (i) a deployable capture structure (110) designed to be deployable between a standby configuration and a fully deployed open configuration, in which the capture structure (110) defines a capture volume with an opening (110A) dimensioned to receive and capture a selected orbital object (2000), (ii) a deployment platform (200) designed to deploy the capture structure (110), and (iii) a closing mechanism (300) designed to close the capture structure (110) around the selected orbital object (2000) located within said capture volume. The capture structure (110) consists of a capture envelope comprising a plurality of foldable sheet-like structures (115, 115.1-115.3) each configured to be reversibly foldable and unfoldable as a function of deployment of the capture structure(110). Each foldable sheet-like structure (115, 115.1-115.3) is designed to take a first configuration, in which the foldable sheet-like structure (115, 115.1-115.3) is folded on itself to form the standby configuration of the capture structure (110), and at least a second configuration, in which the foldable sheet-like structure (115, 115.1-115.3) is unfolded and extended to form the fully deployed open configuration of the capture structure (110). Each foldable sheet-like structure (115, 115.1-115.3) exhibits a fold pattern (MF, VF) defining an alternation of convex and concave sections in the second configuration, which convex and concave sections are adapted to automatically fold one on top of the other upon retracting the capture structure (110).

2020

DEVELOPING A RELIABLE CAPTURE SYSTEM FOR CLEANSPACE ONE

Xavier Collaud, Timothée Robert Sophus Frei, Bastien Gorret, Michel Lauria, Pierre-Alain Mäusli, Camille Sébastien Pirat, Muriel Richard, Régis Voillat

The objectives of the CleanSpace One mission are to raise the awareness of the orbital debris problem, develop and test technologies for non-cooperative rendezvous and as a demonstration, de-orbit the SwissCube satellite. Within this project and over the last few years, several capture systems have been prototyped, from robotic grippers to nets to more conventional capture mechanisms. A major trade-off was performed end of 2014 taking into account system, operational, reliability, functionalities, cost, manufacturability and local expertise criteria. This exercise led to the selection of a deployable “pacman” mechanism. Since then, two iterations of prototypes have been manufactured, with different deployment and closing concepts. This paper describes the latest design. It first presents capture system requirements, including concept of the capture scenario. The capture system trade-offs and selection are then discussed. The main section describes the capture mechanism analyses and design. Analyses especially focus on the cross section and geometry of the elements to ensure successful capture. In the current design, five deployment units unfold bi-stable reeled composite booms. The deployment units use harmonic drives to reduce volume and mass. The synchronized closing of the Pacman is achieved by a closed loop cable linked to a single linear actuator. A complete design of the deployment units has been created to validate the concept. A prototype of one deployment unit has been manufactured. Preliminary tests of the net between the deployable booms have been done. First prototype of the vision-based system that will drive the closing command and confirm capture is discussed. The capture prototypes work well and thus demonstrate the feasibility of the mechanism.

2016

Mission Design and GNC for In-Orbit Demonstration of Active Debris Removal Technologies with CubeSats

Federico Belloni, Volker Gass, Christophe Dominique Paccolat, Camille Sébastien Pirat, Muriel Richard, Reto Wiesendanger

Within the frame of the ESA's General Support Technology Programme, two In-Orbit Demonstration (IOD) missions using CubeSat technologies were studied. These IODs aim at alleviating the technical risk inherent to new technologies required for Active Debris Removal (ADR) of large space objects, by using small and low-cost CubeSat systems. Rendezvous and docking with uncooperative debris has been only partially demonstrated and still raises technological issues. To test technologies such as the navigation and Rendezvous (RV) sensors or capture systems, our studies show that CubeSat missions are appropriate. Already, Guidance, Navigation and Control (GNC), communications and power technologies have successfully been miniaturised and the corresponding equipments are now available to the CubeSat community. This fact extends the range of feasible CubeSat missions from the initial flight of simple sensors to more complex systems. This paper presents two CubeSat ADR experiments and demonstrates how mission design and GNC can serve the verification or navigation sensors performances as well as the validation of uncooperative debris capture using a net. Each mission is composed of a Chaser and a Target. The former being an 8 Units (8U) CubeSat and the latter a 4U, launched together in a 12U deployer. Both satellites are 3-axis attitude controlled. The Chaser has in addition 3 Degrees of Freedom (DoF) translation capability using 1 mN cold gas thrusters. Both CubeSats will carry GNSS receivers to assist in the determination of range and relative-velocity. The global positioning and attitude data or the Target will be transmitted to the Chaser using an inter-satellite link having the additional capacity to measure the corresponding range. This system provides a reference validation for the RV sensors. The relative position and velocity to be controlled are fully observable. Thus a linear quadratic regulator is appropriate to ensure robust and optimal control. Based on the mission design, various close inspection configurations are demonstrated. To emphasise the feasibility of such missions, a system approach will be briefly addressed. Both missions are analysed using a 6 DoF simulator. The performances and absolute errors of the GNC as well as fuel consumption are provided. Power consumption, Telecom capability and thermal aspects will be shown for sake of completeness. Current issues and limitations of the CubeSat GNC will be discussed, as well as conclusions regarding the feasibility of such missions.

Elsevier2016