Free-Space Optics (FSO) for optical communication request new compact low-power high-stroke high-bandwidth Fast Steering Mirrors (FSM). To address this need, CEDRAT TECHNOLOGIES has developed a Magnetically-actuated Fast Steering Mirror called M-FSM, taking heritage of its MICA™ actuators. This FSM offers Rx Ry strokes larger than +/- 2° with a 250Hz bandwidth when tilting a 31mm diam mirror. Requested power is minimized leading to low heating. Vibration tests have been performed to define first limits and conditions for the M-FSM to bear external vibrations. Large bandwidth closed loop control is achieved using integrated eddy current sensor and a state feedback-based controller.
Many applications and more specifically space projects show need for a stable sub-micrometre positioning actuator. In order to meet this need, Cedrat Technologies has designed the new FSPA brand. This linear stepping actuator offers sub-micrometric positioning resolution along 5mm stroke combined with high actuation force (>100N) and the ability to hold its position without power. The IASI-NG instrument is one of the key payload on-board METOP-SG which is a new meteorological satellite for Europe. The instrument is based on a Mertz interferometer and requires a very precise positioning of an optical blade used to separate the interferometer’s branches. A dedicated version of the FSPA, the Beam Splitter Mechanisms Actuator (BSMA) is then developed to achieve this nanometric positioning which is a key parameter for the overall instrument performance. This paper firsts present the internals of both FSPA and BSMA actuators. Major design differences and their respective impact on the resulting performances are detailed. Results from the acceptance and qualification test campaigns are also presented.
A reed valve compressor technology for future science spacecraft application, is being developed by CEDRAT TECHNOLOGIES (CTEC), based on the very compact and high-power MICA300CM actuator (Moving Iron Controllable Actuator). The present publication details the compressor breadboard design and test results, manufactured in the frame of an ESA Technological Research Program (TRP), for the testing of a Zero Boil Off Hydrogen storage demonstrator. The test results presented have been realized at compressor level with Helium gas at CTEC facilities, and the full 20K Hydrogen storage demonstrator is soon to be tested.
High Power Synthetic Jet Actuator (SJA) based on compact piezoelectric actuators, have been developed and tested by CEDRAT TECHNOLOGIES (CTEC) and ONERA, under French National funding RAPID from DGA. This publication presents the modelling approach with early breadboarding results, the final design chosen for integration onto an aircraft airfoil mock-up, the performance test results on the SJA device prior integration, and the final aerodynamic performance test demonstration achieved at ONERA wind tunnel test facility.
In many in-situ instruments information about the mass of the sample could aid in the interpretation of the data and portioning instruments might require an accurate sizing of the sample mass before dispensing the sample. In addition, on potential sample return missions a method to directly assess the captured sample size would be required to determine if the sampler could return or needs to continue attempting to acquire sample.
This paper presents a piezoelectric motor which provides linear motion and very high resolution (40 nm steps). First, the space application (IASI-NG instrument onboard METOP-SG satellite) and associated performance requirements are presented. The internal architecture of the motor and its main components are then explained. A first focus is done on the experimental verification of the threaded interface lifetime which is a key element of the mechanism. A second focus is on the nanometric position test bench. Achieved results are provided for resolution, motion quality and position stability. Finally, results from the vibration test campaign are presented
This paper presents an overview of the preliminary design process and findings aimed at morphing of trailing edge (TE) control surfaces for rotorcraft. A design methodology for a camber morphing control surface is presented, although twist can also be induced by applying differential camber of the morphing section span. The concept investigated relies on utilizing conventional aircraft structures and materials for morphing purposes; thus, in essence, has the potential to fulfil the conflicting requirements of lightweight, flexibility and strength at the same time. Based on this concept, the preliminary design work shows that an active trailing edge camber morphing mechanism can be designed after careful considerations of design and actuation requirements. The numerical results presented also indicate that such a morphing scheme increases the 2D aerodynamic efficiency.
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