CATENI INC — Department of Defense STTR Phase I: AFX20D-TCSO1

Description

Cateni has identified a market opportunity for the development of a low-cost, low-SWaP attitude control solution for CubeSat-class missions.  Existing 3-axis stabilization solutions for CubeSats perform well but are over-kill for a large segment of missions that have modest requirements associated with nadir or inertial pointing.  A pitch momentum bias (PMB) solution can satisfy such requirements for <33% of the SWaP and <25% of the cost --by eliminating the need for a star camera and eliminating all but one wheel.  The inertial stiffness and torque capability from the single pitch-wheel provides stability in roll and yaw along with agility in pitch, and adequate attitude estimation can be provided with magnetic field and sun-angle measurements (magnetic field only during eclipse) without the need for a star camera.  B-field, sun-vector and nadir vector models are sufficiently accurate based on propagation from daily TLE (two-line-elements --Keplerian orbital elements) uploads and a modest accuracy onboard clock --eliminating the need for onboard GPS.  Momentum steering and unloading is performed via magnetic torqueing. PMB is proven technology and key members of the technical team have experience with it from prior programs.  The intent of the project is to develop a MOSA, scalable implementation suitable for 1U, 2U, 3U, 6U, 12U, 18U and 27U CubeSat configurations as well as non-CubeSat small/micro-sats.  The proposed solution leverages the existing CubeSat and SmallSat industrial-base, using commercially available momentum/reaction wheels, magnetic torquers, and sensors (inertial measurement units, magnetometers, sun sensors), and providing value-added with a high-reliability, low-SWaP GN&C processor board and associated GN&C flight software.  The processor board is a derivative of a previously developed CubeSat flight processor and all critical components have good flight heritage.  The core team has >100 years of experience in GN&C system, avionics and flight software development, and are all also experienced with MOSA systems and CubeSat interfaces.   The research institution, Cornell University, and more specifically Dr. Mason Peck's Space System Design Studio (SSDS) laboratory, bring tremendous value to the project.  Dr. Peck is a renowned expert in spacecraft momentum control systems and coauthored a recent book on the topic.  His research group has extensive relevant simulation and test capabilities and has recent/current experience with a 3U platform, Pathfinder for Autonomous Navigation (PAN), which could be an excellent core platform for a 3U-class flight demonstration as part of Phase II.  In Phase I, the Cornell team will conduct a parallel design/development for a 3U class solution in addition to supporting independent verification and validation of the Cateni developed algorithms and filters.