MIT / Lincoln Labs developed, built and prepared for launch the 113 kg, 1.5 meter long ORS-5 SensorSat Space Situational Awareness Small Satellite.  A Flotron CTL-36 Small Satellite Cantilevered Rotation Fixture, part of Flotron’s CTL series, provided the MIT/LL team with ergonomic access during Assembly, Integration and Test operations.  ORS-5 (Sensorsat) is a Low Earth Orbit satellite with optical imaging payload that will monitor potential threats to space assets in the geostationary (GEO) belt.  All of the satellite components (minus the optical imaging payload) were attained from commercial spaceflight hardware suppliers to keep cost down.  ORS-5 utilizes the GeOST (Geometry Optimized Space Telescope) concept, established at MIT Lincoln Labs.  GeOST allows a small detector in low earth orbit to achieve greater imaging sensitivity and discern between celestial objects and resident space objects by pointing the spacecraft’s imager at the GEO Belt at an angle perpendicular to its velocity vector while ensuring that the velocity vectors of both the imager and the space asset are aligned.

Flotron CTL-36 Load Capacity and Design Considerations:
The Flotron CTL-36 load capacity is 3,000 lbs considering a payload CG located at up to 30” out from the interface mounting plate.  Flotron considers a simultaneous dynamic loading condition of 0.5G horizontal (worst case direction) and 1.0G vertical for both stress and stability in addition to SFy = 3 and SFu =5.

Flotron CTL-36 Rotation:
The rotation axis is 36” above the floor and the swing radius is approximately 27.25”.  The gear ratio is 217:1 meaning that 217 turns on the input hand-wheel will result in one 360° rotation of the payload.  This system consists of a geared bearing that is secured to the vertical tower.  The Easy Crank torque of the gear system is approximately 7,200 in-lbs.   “Easy Crank” is a term defined by Flotron and specifies that the input load on the hand-crank is 12 lb or less for ergonomic operation.

Flotron CTL-36 Interface:
The standard interface plate is 24”DIAM and has x20 Ø.531 thru holes on a 22” bolt circle.

Flotron CTL-36 Material, Finish and Lubricant: 
The frame is constructed from carbon steel material.  The frame and tow bar are powder coated gloss white and the gearbox is painted gloss white.  The steel interface plate is electro-less nickel plated.  The caster bodies are finished with satin e-nickel.  All of the fasteners/hardware are stainless steel, e-nickel plated or black oxide.  The caster swivel bearings are lubricated with Braycote 601EF.

Flotron CTL-36 Push Handle, Casters & Other Features:
A push handle is been integrated in the base frame and located at an ergonomic height for an operator to effectively maneuver the Flotron.  The casters have 6”dia phenolic wheels, tread lock brakes & bolt-on swivel locks that allow for safe and ergonomic transport.  A storage box has been integrated on the base frame to store customer tools, fasteners … etc.

A Flotron Satellite Positioner transports the Ball Aerospace and Technologies Corp. (BATC) designed, manufactured and tested JPSS-1 NASA/NOAA next generation Weather Satellite to the launch site at Vandenberg AFB this week. The Flotron will upend the satellite vertically where it will be fueled and integrated with the launch vehicle. BATC will support launch operations and on-orbit checkout. JPSS-1 is currently scheduled to launch in November.

BOULDER, Colorado, September 5, 2017 — Ball Aerospace successfully delivered the Joint Polar Satellite System-1 (JPSS-1), NOAA’s next-generation polar orbiting weather satellite, to Vandenberg Air Force Base in California on Aug. 31, where it is scheduled to launch Nov. 10, 2017. This follows a successful pre-ship review with NASA at Ball’s Boulder, Colorado, manufacturing complex.

“The arrival of the spacecraft at Vandenberg is a tremendous milestone for the program and the culmination of excellent collaboration and hard work by the JPSS-1 team – NOAA, NASA, Ball, Harris, Raytheon and Northrop Grumman,” said Rob Strain, president, Ball Aerospace. “This advanced weather satellite will play a significant role in providing actionable environmental intelligence to decision makers in government and business, and to the general public.”

The JPSS series of polar-orbiting weather satellites will work as the foundation of NOAA’s operational environmental forecasting system for the next 20 years. The JPSS missions are funded by NOAA to provide global environmental data in low-Earth polar orbit. NASA is the acquisition agent for the flight systems, launch services and components of the ground segment.

JPSS data increases the timeliness and accuracy of numerical forecast models three to seven days in advance of severe weather events. These forecasts allow for early warnings and enable agency managers to make informed decisions to protect American lives and property.

The JPSS-1 satellite will host a suite of state-of-the-art instruments: Advanced Technology Microwave Sounder (ATMS – Northrop Grumman), Cross-track Infrared Sounder (CrIS – Harris), Visible Infrared Imaging Radiometer Suite (VIIRS – Raytheon), Ozone Mapping and Profiler Suite (OMPS – Ball), and Clouds and the Earth’s Radiant Energy System (CERES – Northrop Grumman).

Ball designed and built the JPSS-1 spacecraft, the Ozone Mapping and Profiler Suite-Nadir instrument (OMPS), integrated all five of the satellite’s instruments, and is performing satellite-level testing and launch support. JPSS-1 will launch aboard a United Launch Alliance Delta II rocket from Vandenberg Air Force Base.

Following launch, JPSS-1 will join the Ball-built NOAA/NASA Suomi NPP satellite which has served as NOAA’s primary operational satellite for global weather observations since May 2014. Together, the two satellites, each circling the Earth 14 times per day, will provide global observations for U.S. weather and environmental predictions.