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Patent
Thales Alenia and French National Center for Space Studies | Date: 2016-09-16

A dual guidance gyroscopic actuator comprises, a main structure connected to a platform, connected to a satellite, a ring, a U-shaped cradle, having first and second ends and a central part, a flywheel mounted on the central part between the first and second ends, being rotationally mobile with respect to the cradle about a first axis. A first bearing is positioned at the first end and a second bearing is positioned at the second end connecting the ring to the cradle, the first and second bearings rendering the cradle rotationally mobile with respect to the ring about a second axis substantially perpendicular to the first axis. The ring is connected to the main structure. The gyroscopic actuator comprises at least one suspension element limiting microvibrations from the cradle and flywheel and at least one end-stop element limiting travel cradle and of the flywheel with respect to the main structure.


Patent
French National Center for Space Studies | Date: 2015-04-03

The invention relates to a method for transferring a space payload from a first orbit to a second orbit. Said method is characterized in that the space payload, moving about the first orbit, is attached to a removable orbital towing assistance device including at least one fuel pouch. Said method includes the steps of: attaching (E1) an orbital transfer vehicle to the removable orbital towing assistance device; and transferring (E2) the space payload and the removable orbital towing assistance device to the second orbit by means of the orbital transfer vehicle. The invention also relates to a removable orbital towing assistance device intended for a space payload and an orbital transfer vehicle and enabling direct supply of fuel to the vehicle and/or the space payload.


Patent
Snecma and French National Center for Space Studies | Date: 2016-11-10

A feed system for feeding a rocket engine with a liquid propellant includes a feed circuit, and a device to vary a volume of gas in the feed circuit. The device is configured to cause a volume of gas in the feed circuit to vary while the rocket engine is in operation. The device to vary gas volume includes at least one variable-flow-rate gas injector to inject gas into the liquid propellant in the feed circuit. Methods of suppressing a POGO effect are also provided.


Patent
French National Center for Space Studies | Date: 2017-01-11

The invention discloses a receiver of GNSS positioning signals which has embedded computer logic to select between a first operating mode, which uses all available frequencies, and a second operating mode, which uses only part of the available frequencies but in combination with available correction data. The selection is based on a comparison of an index of quality of reception at the receiver and a computed or predicted precision/confidence level of the corrections. A plurality of corrections types are possible, including a type using a local model and a type using collaborative corrections. In some embodiments, a selection and/or a combination of a plurality of local models may be made to optimize the accuracy of the corrections.


Patent
French National Center for Space Studies and M3 Systems | Date: 2017-01-04

A receiver, and associated process, for tracking a GNSS positioning signal comprising a carrier modulated by a subcarrier and a spreading code, the receiver comprising:- at least one tracking loop configured to calculate a first pseudo range from said GNSS positioning signal,- a first discrimination circuit (521) configured to calculate an ambiguous discriminator value from the subcarrier and the spreading code of said GNSS positioning signal,- a calculation circuit (522) configured to calculate a value representative of a tracking error of said tracking loop,- a second discrimination circuit (530) configured to select one of said ambiguous discriminator value and said value calculated by the calculation circuit, and to generate a first non-ambiguous discriminator value, an amplitude of which is based on an amplitude of the selected value, and a sign of which is a sign of said value calculated by the calculation circuit.


Grant
Agency: Cordis | Branch: H2020 | Program: IA | Phase: GALILEO-1-2015 | Award Amount: 4.87M | Year: 2016

The HELIOS project aims at providing a Second Generation range of Beacons (SGB) and associated antennas designed to operate with the full capability of the new Meosar Cospas/Sarsat (C/S) International Programme (a satellite-based Search And Rescue (SAR) distress alert detection and information distribution system), embedded in the Navigation Satellite Systems as GALILEO. The Search & Rescue community is at a turn of its history. New satellite systems develops the MEOSAR constellation of Cospas-Sarsat system, EGNOS improves significantly the performance of localization introducing new capabilities and new operations impossible before, GALILEO unique differentiation with the RLS added to the performance of the system will contribute to save more lives at sea and on land. The key objectives of the HELIOS project are: 1 - Defining, developing Products (beacons and associated antennas) compatible with EGNSS & SAR services and latest end-users requirements. 2 - GALILEO EGNSS & SAR System validation. 3 - Certifications for commercialization. The HELIOS consortium composed of Orolia, Cobham aerospace communications, CNES, SIOEN, Air France, and Airbus, is involved in different relevant international working groups (Cospas-Sarsat, ICAO, EUROCAE), and will ensure that the development phase of the SGB will be in line with the compatibility and interoperability required by the Cospas-Sarsat. Gathering the knowledge of major players recognized in their industry worldwide, the HELIOS partners project will give the vehicle to the European Industry to lead the way for safer, more innovative systems responding to current and evolving market problems.


Grant
Agency: Cordis | Branch: H2020 | Program: CSA | Phase: SPACE | Award Amount: 9.02M | Year: 2016

This 3SST2015 project is aimed at supporting the emergence of a European SST service built on a network of existing SST assets, notably sensors (radar, laser and telescopes) owned by SST Consortium Member States. This will require the commitment of Consortium Member States owing relevant assets to cooperate and provide an anti-collision, fragmentation and re-entry service at European level in order to increase the autonomy of Europe concerning the operational objectives derived from the SST decision, which will be partially fulfilled by the operation of the initial European SST system. Given that this system is mainly based on national systems, at the initial stage many of the activities will be based at national level. At the same time, and in order to achieve the convergence within a joint action that will allow the minimum desirable level of performance, an appropriate degree of coordination between SST Consortium Member States is needed. The project is following a shared working approach between the key players within the field of SST in Europe. Following the guidelines given by the implementing decision of the European Commission (C(2014)6342 final of the 12.09.2014), the backbone of the planned activity is formed by a set of SST committees forming the decision platform of the SST Consortium, composed of the five designated national entities in cooperation mechanisms with the EU SatCen. Three Committees are foreseen for the governing structure of the SST Consortium: the Steering Committee as the decision platform, the Technical Committee as the professional motor and to the Security Committee dealing with bi- and multilateral aspects of security constraints and issues. The main activities are addressed in terms of: Performance assessment and architecture of SST, an SST Action Plan and the Priority upgrading of existing sensors owned by the Member States member of the SST consortium.


Grant
Agency: Cordis | Branch: H2020 | Program: CSA | Phase: SPACE | Award Amount: 3.20M | Year: 2016

The main objectives of 2SST2015 are the initial networking of SST assets and preparation of the establishment of a European SST Service provision function. The project is the first of a series in the upcoming years and has to be seen in context with two parallel projects for initial service provision and for SST roadmapping and infrastructure.


Grant
Agency: Cordis | Branch: H2020 | Program: IA | Phase: GALILEO-1-2015 | Award Amount: 2.78M | Year: 2016

Recent drama in civil aviation leading to losses of several aircrafts (AF447, MH370, etc) have shown first an incapacity of quickly dispatching rescue means for potential survivals, and second, a surprising incapacity of determining the position of the aircrafts wreck, generating major researches expenses. This situation led to the creation of a joint RTCA/Eurocae working area in SC229/WG98 group; Its objective: define new solutions to cope with the current situation. It mirrors the ICAO recommendations from the Second High-Level Safety Conference (HLSC 2015) in Montreal. The conference raised key improvement areas and paved the way for the development of an integrated Global Aeronautical Distress and Safety System (GADSS) addressing all the flight phases. Based on these initiatives, a regulation will impose in-flight activations of aircraft S&R beacons for 2021. Aligned with GADSS perspectives and H2020 Galileo Topic 1, GRICAS proposes to develop a safety concept based on an innovative use of Galileo SAR service for a maximum rescue effectiveness. It includes the development of NG Beacons, innovative MEOLUT that optimizes the position accuracy even for high dynamic beacons, a new RLS employment concept, and associated In-flight beacon activations triggers when detecting abnormal flight situations. Based on key regulation S&R players within the consortium (CNES, BEA, DGAC), GRICAS is a unique opportunity to bring to the fore one of the essential Galileo differentiator compared to other GNSS, e.g. a rich S&R service with a unique Return link service, decisively contributing to the aviation safety. The technological developments are supported by rich In-flight experimentations and demonstrations, relayed by a strategic dissemination plan irrigating the aeronautical regulation ecosystem, as well as the end users (airliners). With the innovations developed in GRICAS, Galileo will get a recognized service differentiator for the European Citizen Safety in aircrafts.


Grant
Agency: Cordis | Branch: H2020 | Program: RIA | Phase: COMPET-02-2015 | Award Amount: 3.97M | Year: 2015

ALTAIRs strategic objective is to demonstrate the feasibility of a new cost effective and reliable space launch system for the access to Low-Earth Orbit (400-1000 km) of small satellites ranging from 50 to 150 kg. The ALTAIR launch system aims to be the expected answer to the needs of small satellites users, providing an affordable and adapted access to space service, without the constraints of current rideshare launch options. ALTAIR will boost space applications to the benefit of an increased spectrum of users, from classic satellite operators to academics and research centres. To support this ambitious goal, the ALTAIR system combines an innovative semi-reusable concept and the integration of relevant technologies in all parts of the system. ALTAIR is an innovative air-launch system using a reusable unmanned aircraft carrier optimised specifically for this mission. The expendable rocket launch vehicle, which is released at high altitude, associates green propellant hybrid propulsion, lightweight composite structure, innovative avionics and a versatile upper-stage, providing mission flexibility. Cost-effective ground operations are obtained through innovative ground systems architecture. ALTAIR will pave the way for a feasible system ready to address the markets need through an original approach associating a cost-oriented preliminary design of the whole system (carrier vehicle, launch vehicle and ground segment) using advanced Multidisciplinary Design Optimisation techniques, and the definition of a credible development roadmap and business model, supported by market analyses. The design will be supported by flight experimentations for key technologies using the existing small scale demonstrator EOLE. The 36-month ALTAIR project benefits from a solid and proven heritage, and gathers the experience of 8 partners from 6 countries (including industrial companies, research centres and a technical centre of a space agency), for a total EC contribution of 3.5 M.

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