European Recovery System (ERS)

Up to the TEXUS-44 microgravity research mission, successfully launched in February 2008, the payloads of the TEXUS vehicles were exclusively equipped with the Magellan (former Bristol Aerospace Ltd.) ORSA recovery system, integrated into the ogive nose cone. With the intention to gain more independency from the North American market and the inherent procurement and ITAR regulations problems, the European Space Agency (ESA) has taken initiative to contract industry for the development and built-up of a new European Recovery System (ERS) in 2006. For the design, manufacturing and qualification task sharing, a cooperation of DLR Moraba and the Kayser-Threde GmbH has been initialized. The ERS is designed to recover payloads of up to 450 kg mass and 17 inch (438 mm) diameter by a two-stage subsonic parachute system. It features a separating ogive nose tip with a forward deploying recovery parachute. The assembly incorporates a 3:1 fineness ratio ogive which forward portion is ejected exo-atmospherically to permit subsequent parachute recovery system operation. The aft ogive houses the parachute system, autonomous redundant pyrotechnic ignition system, housekeeping electronics, TM interface, beacon system, camera system and pyrotechnic and electronic batteries. The parachute system activation is controlled by barometric switches on the descent trajectory at a nominal altitude of 15 kft (4.6 km) in the combination of an electronic timing activation unit (ignition unit). Together with the heat shield ejection the drogue parachute is deployed and the payload is mainly stabilized from flat spin and decelerated. After complete stabilization the drogue parachute is separated and extracts the main parachute out of the deployment bag. At fully opened main parachute the final sink rate is around 8 m/sec

New Techniques and Instrumentation – TEXUS Service Module (TSM)

Until the TEXUS-42 (EML-1) project, successfully launched in Dec. 2005, the payload of the TEXUS and the MAXUS were equipped with the former Kayser-Threde 12 bit based PCM data acquisition system. To fulfill experimental requirements for higher data resolution and the intention to reduce weight and also to improve the performance of the service module, ESA has taken initiative to contract industry for the development and built up of a new data acquisition system and the new TEXUS Service Module (TSM) in 2004. For the design, manufacturing and qualification task sharing, a cooperation of DLR Moraba and the Kayser-Threde GmbH has been initialized. With respect to the compatibility of already existing experiment modules, Kayser-Threde has developed, manufactured and qualified the decentralized 16 bit CTS 3000 (Compact Telemetry System) data acquisition system and together with DLR Moraba the TSM. In order to improve existing systems and to comply with new requirements the DLR/Moraba has designed a new power distribution and a GPS system. The TSM is incorporating all known standard features, modern technologies and is capable of serving actual and future experiment requirements. The TSM provides flexibility for future implementation of up to two digital TV respectively TM down links besides the three standard analog TV down links. The design implies economic technical concepts consuming a minimum of service module mass and length. The service module acquires and transmits all experimental and service system housekeeping data via telemetry transmitter to ground. Commands to the service system and for experiment control are received with a dedicated diversity system from the ground station and distributed onboard. Furthermore three TV down links, 3-axis micro-g and acceleration measurement as well as a rate control (RCS) and a GPS system are incorporated. The TSM is integrated within a standard TEXUS cylindrical structure with Radax flanges on both ends. Most of the components are assembled on the instrumentation deck, which is fixated via shock mounts to the outer structure. All electronic boards for TM/TC, RCS, power switching, sequencing, μ-g measurement and housekeeping are integrated and wired within one

Results of the GNSS Receiver Experiment OCAM-G on Ariane-5 flight VA 219

The fifth Automated Transfer Vehicle (ATV) was launched on July 29, 2014 with Ariane-5 flight VA 219 into orbit from Kourou, French Guyana. For the first time, the ascent of an Ariane rocket was independently tracked with a Global Navigation Satellite System (GNSS) receiver on this flight. The GNSS receiver experiment OCAM-G was mounted on the upper stage of the rocket. Its receivers tracked the trajectory of the Ariane-5 from lift-off until after the separation of the ATV. This paper introduces the design of the experiment and presents an analysis of the data gathered during the flight with respect to the GNSS tracking status, availability of navigation solution and navigation accuracy