
Test & Measurement
Products
The NS1310 is a robust, compact data server and storage unit specifically designed for the challenging conditions of airborne environments.
This versatile system functions as a Network Attached Storage (NAS) unit and is equipped with a high-capacity Removable Memory Module (RMM).
The ENERTEC™ mission data processing and distribution units offer cost-effective and dependable solutions for field and mission data tasks, such as data acquisition, processing, storage, exploitation, and distribution. These units are suitable for use on both manned and unmanned ground, air, and sea vehicles. They undergo rigorous validation and formal qualification testing, adhering to standard test methods like DO-160 and MIL-STD-810.
The PPS®1350 Hall Effet plasma thruster draws on Safran’s long experience with electric propulsion. It is designed for orbital transfer, station keeping and deorbiting satellites and other spacecraft. In particular, the PPS 1350 was the primary engine on ESA’s lunar probe, Smart-1, launched in 2003 by an Ariane 5 rocket. This mission was completed in September 2006.
The PPS®5000, produced by Safran Spacecraft Propulsion, is a Hall Effect Thruster purposely designed for “all-electric” satellites. It can operate in high-thrust or high specific impulse mode,and offers an operating lifespan of about 20,000 hours. This means it can handle orbital positioning and station-keeping duties for a wide range of telecom and navigation satellites, as well as exploration spacecraft. The PPS®5000 was fully qualified in 2021.
The PPS®X00 plasma thruster (Hall effect) takes benefit of Safran’s long experience with electric propulsion to propose a very efficient product. PPS®X00 was designed to address the specific requirements inherent in the “New Space” market environment. With a lifespan exceeding 5,000 hours and very high specific impulse, the PPS®X00 is an extremely versatile thruster, making it ideal for all types of applications in its core market: low Earth orbit (LEO).
The RMM Manager utility software offers convenient, user-friendly pre-mission or post-mission access to SC1450-series Removable Memory Modules (RMM) for use with VS-Series video & data recorder/server, in PC/Windows® environment.
The SafeLaunch-FTR is based on more than 20 years of skills and experience. Such Flight Termination Receivers equip air to air, ground to air and air to ground missiles as well as UAV, target drones and Launch Vehicles. They are qualified under MIL-STD-810F and MIL-STD-461E standards, and comply to RCC-319. The compact and optimized package is consistent in size and weight with the most severe requirements of missile platforms. The electronical design, based on the latest generation of Software Defined Radio (SDR) components, brings to SafeLaunch-FTR high reliabilty and evolutivity.
Safran’s SEEING™ 130 Wide includes a unique medium focal length catadioptric optics, limited by diffraction only and with ultra-low distortion, offering perfect imaging over 35 mm full-frame image format. It is fitted with a 10megapixel sensor.
SEEING™ 130 Wide enables high Signal to Noise Ratio for multispectral (MS), hyperspectral (HS) and low light level imaging. SEEING™ 130 Wide includes a spectral filter with 23 bands covering Blue, Green, Red, Near InfraRed and Red Edge MS, for a broad spectral range between 475 and 900nm. SEEING™ 130 Wide has a large Field of View of 6.3° x 4.3° / 54 x 36 km2 from a 500km/310 miles orbit.
In addition to its a thermal design within a robust structure, SEEING™ 130 Wide has a low SWaP, saving launch and operational costs.
Acquire high quality images with accurate radiometry for LEO (Low Earth Observation) earth observation applications with 65 MP focal plane and control electronics. From a 500 km orbit, SEEING™ 230 Ident has 9 x 6 km2 swath, offering a 1.03m native Ground Sample Distance (GSD), and features a super-resolution optional mode providing 70cm GSD. Thanks to its unique design, SEEING™ 230 Ident has an ultra-low SWaP factor. It is made of advanced ceramic material for strength during launch and stability during operation in space. It is athermalized and gradient insensitive between -10°C to +50°C. It has a low mass, below 8kg, saving both platform and launch costs.