Flight Test Results of an Adaptive Guidance System for Reusable Launch Vehicles - read free eBook in online reader or directly download on the web page. Select files or add your book in reader. Download and read online ebook Flight Test Results of an Adaptive Guidance System for Reusable Launch Vehicles write by John D. Schierman. This book was released on 2004. Flight Test Results of an Adaptive Guidance System for Reusable Launch Vehicles available in PDF, EPUB and Kindle. To enable autonomous operations in future Reusable Launch Vehicles (RLVs), reconfigurable control and adaptive guidance will often be required to facilitate recovery of the mission following a major anomalous event such as an effector failure. An adaptive guidance system that works in conjunction with a reconfigurable controller and an autonomous trajectory command reshaping algorithm is presented. The guidance law utilizes a backstepping architecture to generate pitch rate commands that drive the inner-loop control system. Under extreme failure conditions the control surfaces can saturate in an attempt to meet commanded moments. In these cases, the guidance feedback gains are reduced to preserve stability margins in the guidance loops. A case study is presented that shows the benefits of the guidance gain adaptation. Without adjusting the gains, the guidance loops go unstable, whereas stability is maintained with gain reduction.
Adaptive Guidance Systems for Hypersonic Reusable Launch Vehicles
Adaptive Guidance Systems for Hypersonic Reusable Launch Vehicles - read free eBook in online reader or directly download on the web page. Select files or add your book in reader. Download and read online ebook Adaptive Guidance Systems for Hypersonic Reusable Launch Vehicles write by . This book was released on 2001. Adaptive Guidance Systems for Hypersonic Reusable Launch Vehicles available in PDF, EPUB and Kindle. This paper presents an adaptive guidance system approach applied to hypersonic Reusable Launch Vehicles (RLVs). After an effector failure, it is assumed that the inner-closed-loop system utilizes a reconfigurable control algorithm to recover nominal maneuvering capabilities to the extent possible. However, nominal performance will typically not be fully recovered for RLVs, and the outer-loop guidance system must account for the degraded vehicle response. Two main approaches for the adaptive guidance system are presented. The first approach augments the existing production guidance system by adding adaptation capabilities. A case study shows that stability is maintained following a primary pitch effector failure. This is achieved by adapting gains in the guidance feedback loops. However, it is shown that the trajectory commands to the guidance loops must also be re-targeted in order to achieve a safe landing. The second approach employs an on-line optimal trajectory re-targeting algorithm. Here, the calculus of variations is used to generate a database of admissible neighboring extremals. This database is then encoded in an efficient manner to generate mappings between the current states and vehicle capabilities and the costates defining the admissible optimal trajectories. These mappings are interrogated on-line at regular intervals to obtain the optimal guidance commands. A proof-of-concept case study of this approach shows that the final landing conditions are achieved following a primary speed control effector failure.
Reusable Booster System
Reusable Booster System - read free eBook in online reader or directly download on the web page. Select files or add your book in reader. Download and read online ebook Reusable Booster System write by National Research Council. This book was released on 2013-01-10. Reusable Booster System available in PDF, EPUB and Kindle. On June 15, 2011, the Air Force Space Command established a new vision, mission, and set of goals to ensure continued U.S. dominance in space and cyberspace mission areas. Subsequently, and in coordination with the Air Force Research Laboratory, the Space and Missile Systems Center, and the 14th and 24th Air Forces, the Air Force Space Command identified four long-term science and technology (S&T) challenges critical to meeting these goals. One of these challenges is to provide full-spectrum launch capability at dramatically lower cost, and a reusable booster system (RBS) has been proposed as an approach to meet this challenge. The Air Force Space Command asked the Aeronautics and Space Engineering Board of the National Research Council to conduct an independent review and assessment of the RBS concept prior to considering a continuation of RBS-related activities within the Air Force Research Laboratory portfolio and before initiating a more extensive RBS development program. The committee for the Reusable Booster System: Review and Assessment was formed in response to that request and charged with reviewing and assessing the criteria and assumptions used in the current RBS plans, the cost model methodologies used to fame [frame?] the RBS business case, and the technical maturity and development plans of key elements critical to RBS implementation. The committee consisted of experts not connected with current RBS activities who have significant expertise in launch vehicle design and operation, research and technology development and implementation, space system operations, and cost analysis. The committee solicited and received input on the Air Force launch requirements, the baseline RBS concept, cost models and assessment, and technology readiness. The committee also received input from industry associated with RBS concept, industry independent of the RBS concept, and propulsion system providers which is summarized in Reusable Booster System: Review and Assessment.
Guidance, Navigation and Control Design Overview and Flight Test Results from Nasa's Max Launch Abort System
Guidance, Navigation and Control Design Overview and Flight Test Results from Nasa's Max Launch Abort System - read free eBook in online reader or directly download on the web page. Select files or add your book in reader. Download and read online ebook Guidance, Navigation and Control Design Overview and Flight Test Results from Nasa's Max Launch Abort System write by Nasa Technical Reports Server (Ntrs). This book was released on 2013-07. Guidance, Navigation and Control Design Overview and Flight Test Results from Nasa's Max Launch Abort System available in PDF, EPUB and Kindle. The National Aeronautics and Space Administration Engineering and Safety Center designed, developed and flew the alternative Max Launch Abort System (MLAS) as risk mitigation for the baseline Orion spacecraft launch abort system already in development. The NESC was tasked with both formulating a conceptual objective system design of this alternative MLAS as well as demonstrating this concept with a simulated pad abort flight test. Less than 2 years after Project start the MLAS simulated pad abort flight test was successfully conducted from Wallops Island on July 8, 2009. The entire flight test duration was 88 seconds during which time multiple staging events were performed and nine separate critically timed parachute deployments occurred as scheduled. This paper provides an overview of the guidance navigation and control technical approaches employed on this rapid prototyping activity; describes the methodology used to design the MLAS flight test vehicle; and lessons that were learned during this rapid prototyping project are also summarized.
Onboard Trajectory Generation for the Unpowered Landing of Autonomous Reusable Launch Vehicles
Onboard Trajectory Generation for the Unpowered Landing of Autonomous Reusable Launch Vehicles - read free eBook in online reader or directly download on the web page. Select files or add your book in reader. Download and read online ebook Onboard Trajectory Generation for the Unpowered Landing of Autonomous Reusable Launch Vehicles write by André René Girerd. This book was released on 2001. Onboard Trajectory Generation for the Unpowered Landing of Autonomous Reusable Launch Vehicles available in PDF, EPUB and Kindle.
