Odyssey Space Research, LLC is a small business based in Houston, Texas near NASA Lyndon B. Johnson Space Center providing engineering research and analysis services. This start-up in the space industry founded in November 2003 has already won major contracts and is the only private company working on the 5 next human-rated spacecraft . Wikipedia.
Senent J.S.,Odyssey Space Research
Advances in the Astronautical Sciences | Year: 2010
If a pure numerical iterative approach is used, targeting entry interface (EI) conditions for nominal and abort return trajectories or for correction maneuvers can be computationally expensive. This paper describes an algorithm to obtain an optimal impulsive maneuver that generates a trajectory satisfying a set of EI targets: inequality constraints on longitude, latitude and azimuth and a fixed flight-path angle. Most of the calculations require no iterations, making it suitable for real-time applications or large trade studies. This algorithm has been used to generate initial guesses for abort trajectories during Earth-Moon transfers. Source
Brunner C.W.,Odyssey Space Research |
Lu P.,Iowa State University
Journal of the Astronautical Sciences | Year: 2012
The dramatic increase incomputational power since the Apollo program has enabled the development of numerical predictor-corrector (NPC) entry guidance algorithms that allow on-board accurate determination of a vehicle's trajectory. These algorithms are sufficiently mature to be flown. They are highly adaptive, especially in the face of extreme dispersion and off-nominal situationscompared with reference-trajectory following algorithms. The performance and reliability of entry guidance are critical to mission success. This papercompares the performance of a recently developed fully numerical predictor-corrector entry' guidance (FNPEG) algorithm with that of the Apollo skip entry guidance. Through extensive dispersion testing, it is clearly demonstrated that the Apollo skip entry guidance algorithm would be inadequate in meeting the landing precision requirement for missions with medium (4000-7000 km) and long (>7000 km) downrange capability requirements under moderate dispersions chiefly due to poor modeling of atmospheric drag. In the presence of large dispersions, a significant number of failures occur even for short-range missions due to the deviation from planned reference trajectories. The FNPEG algorithm, on the other hand, is able to ensure high landing precision in all cases tested. All factors considered, a strong case is made for adopting fully numerical algorithms for future skip entry missions. Source
Agency: National Aeronautics and Space Administration | Branch: | Program: SBIR | Phase: Phase I | Award Amount: 69.95K | Year: 2005
The innovations of the Fusion of Inertial Navigation and Imagery Data are the application of the concept to the dynamic entry-interface through near-landing phases, the autonomy and (near) real-time requirements of the system, and the focus on satisfying the stringent requirements for reliability and verification for spaceflight. This innovation will allow spacecraft to navigate autonomously, precisely and safely from entry-interface to near-landing. The plan is to develop automated techniques suitable for onboard software that incorporate recognized objects from imagery data into the vehicle's navigated solution. We will use image processing techniques to compare the imagery with expected views, pattern recognition techniques to identify known objects in the comparison, mechanisms for locating known objects using the navigated state, and filtering techniques to update the navigated state with the errors between the observed and expected results. To qualify as flight software, the proposed solution will be reliable and verifiable, and will satisfy limitations of the onboard equipment. No existing techniques solve all of these problems. Current techniques for incorporating imagery data into navigated solutions use sensors that have significantly shorter ranges, rely on registration markers placed on the target, use ground-based computational equipment, or require human intervention to arrive at a solution.
Agency: National Aeronautics and Space Administration | Branch: | Program: SBIR | Phase: Phase I | Award Amount: 99.98K | Year: 2011
Odyssey Space Research proposes to develop a modular navigation software package to provide precise state information for offline analysis and real-time applications. This navigation package will use particle filter methodology to process discrete observation data and maintain an accurate state. This navigation system will leverage several NASA products to rapidly prototype and demonstrate the feasibility of this software during Phase I, including the General Mission Analysis Tool (GMAT) and Trick, taking it from TRL 2 past TRL 3. Phase II will deliver an expanded modular software product integrated into several other software packages demonstrating different estimation capabilities (TRL 5-6). This system will function as a standalone estimation package that can be easily integrated into other software packages, or as the basis for embedded flight software algorithms.This navigation package will be designed to meet the position, velocity, and time estimation requirements for space missions. It will contain an expanded state vector used to estimate non-Gaussian forcing functions perturbing the vehicle's dynamics. This navigator will integrate the measurements from diverse sensors running at different rates. And it will demonstrate accurate estimation of uncertain dynamics parameters that are affecting the vehicle's state such as the gravitation field of small bodies.
Agency: National Aeronautics and Space Administration | Branch: | Program: SBIR | Phase: Phase I | Award Amount: 125.00K | Year: 2015
Odyssey proposes a new fault management planning and design tool and methodology that uses state-based simulations with programmable dynamic state definitions to provide early assessments of fault management system scope and cost. The tool will utilize models developed in SysML to capture system characteristics and relationships between system components as well as mapping of functionality to requirements and mission objectives, and a probabilistic state-based simulation to determine requirements compliance, fault probabilities, and the number of fault paths in the system. The tool will provide useful visualization of the FM design and fault paths, including the dynamic aspect of the system, as well as visual representations of system complexity. In addition, the tool will provide automated means to estimate the complexity of the FM design based on system characteristics and simulation results. The tool will provide engineers and managers with the ability to scope the fault management (FM) effort from requirements development through verification at a point early in the design process. Phase I will focus on proof of concept and demonstration of key aspects of the tool, with full tool development and scaling to complex systems in Phase II.