Space-Based Countermeasure for Hypersonic Glide Vehicle

The purpose of this thesis is to investigate the effectiveness of a space-based laser weapon system for countering a hypersonic glide vehicle. Hypersonic glide vehicles are an emerging type of weapon system which combine the range of ballistic missiles with the maneuverability of cruise missiles. These systems pose a unique threat to military assets not only for their expanded capabilities but also for the lack of an effective defensive countermeasure. Space-based laser weapon systems may offer a solution to this problem. The dynamics of a space-based laser system defending against a hypersonic glide vehicle are modeled first. The governing equations of motion for the space orbital mechanics and the atmospheric flight mechanics of the two objects, assuming point mass three degree of freedom conditions, are defined. Several variables in the engagement model are allowed to vary including initial conditions for true anomaly and right ascension of the ascending node for the space-based laser system and the velocity ratio, angle of attack, and heading about the ground target for the hypersonic glide vehicle. The motion of each object is propagated from the initial condition forward in time from which the relative motion and lasing along the line of sight are analyzed. A predetermined intercept range for the laser is then compared against the flight path of the hypersonic glide vehicle to determine when a successful intercept of the hypersonic glide vehicle occurs. Finally, the solution set for the intercept of the hypersonic glide vehicle by the laser is examined. Results reveal usable solution sets do exist where a space-based laser system could defensively counter a hypersonic glide vehicle attacking a specific ground target

Intelligent Autonomous Decision-Making and Cooperative Control Technology of High-Speed Vehicle Swarms

This book is a reprint of the Special Issue “Intelligent Autonomous Decision-Making and Cooperative Control Technology of High-Speed Vehicle Swarms”,which was published in Applied Sciences

Optimal Control Methods for Missile Evasion

Optimal control theory is applied to the study of missile evasion, particularly in the case of a single pursuing missile versus a single evading aircraft. It is proposed to divide the evasion problem into two phases, where the primary considerations are energy and maneuverability, respectively. Traditional evasion tactics are well documented for use in the maneuverability phase. To represent the first phase dominated by energy management, the optimal control problem may be posed in two ways, as a fixed final time problem with the objective of maximizing the final distance between the evader and pursuer, and as a free final time problem with the objective of maximizing the final time when the missile reaches some capture distance away from the evader.These two optimal control problems are studied under several different scenarios regarding assumptions about the pursuer. First, a suboptimal control strategy, proportional navigation, is used for the pursuer. Second, it is assumed that the pursuer acts optimally, requiring the solution of a two-sided optimal control problem, otherwise known as a differential game. The resulting trajectory is known as a minimax, and it can be shown that it accounts for uncertainty in the pursuer\u27s control strategy. Finally, a pursuer whose motion and state are uncertain is studied in the context of Receding Horizon Control and Real Time Optimal Control. The results highlight how updating the optimal control trajectory reduces the uncertainty in the resulting miss distance

Aeronautical engineering: A continuing bibliography with indexes (supplement 319)

This report lists 349 reports, articles and other documents recently announced in the NASA STI Database. The coverage includes documents on the engineering and theoretical aspects of design, construction, evaluation, testing, operation, and performance of aircraft (including aircraft engines) and associated components, equipment, and systems. It also includes research and development in aerodynamics, aeronautics, and ground support equipment for aeronautical vehicles

Aeronautical Engineering: A continuing bibliography, supplement 120

This bibliography contains abstracts for 297 reports, articles, and other documents introduced into the NASA scientific and technical information system in February 1980

The Development of Design Requirements and Application of Guided Hard-Launch Munitions on Aerial Platforms

This thesis outlines the potential and need for a paradigm shift that will fundamentally alter the way aerial engagement is carried out in the coming decades. The implementation of guided hard-launch munitions on aerial platforms will effectively allow for greater target versatility while providing a defense system for the aircraft in question. A rearward facing gun barrel equipped with several smaller caliber guided rounds can effectively mitigate air-to-air and surface-to-air missiles from hostile forces, while larger caliber rounds in a traditional forward or side mounted barrel can engage both surface and airborne targets at close and medium-ranges. This study outlines the concept of operations for various mission types implementing these guided munitions from short-range direct fire encounters to long-range indirect fire. A computational model was then established to outline the design requirements for this particular type of munition family. The aerodynamics, structures, and guidance, navigation and controls were considered for each engagement type. A sample guided projectile concept was then applied to three airframes, the F-35A, AC-130U, and A-10, in order to demonstrate basic capability as a retrofit on exiting gunnery systems. The modified system capability was then juxtaposed with existing aerial combat potential

Aeronautical Engineering: A continuing bibliography with indexes (supplement 175)

This bibliography lists 467 reports, articles and other documents introduced into the NASA scientific and technical information system in May 1984. Topics cover varied aspects of aeronautical engineering, geoscience, physics, astronomy, computer science, and support facilities

Large Scale Constrained Trajectory Optimization Using Indirect Methods

State-of-the-art direct and indirect methods face significant challenges when solving large scale constrained trajectory optimization problems. Two main challenges when using indirect methods to solve such problems are difficulties in handling path inequality constraints, and the exponential increase in computation time as the number of states and constraints in problem increases. The latter challenge affects both direct and indirect methods. A methodology called the Integrated Control Regularization Method (ICRM) is developed for incorporating path constraints into optimal control problems when using indirect methods. ICRM removes the need for multiple constrained and unconstrained arcs and converts constrained optimal control problems into two-point boundary value problems. Furthermore, it also addresses the issue of transcendental control law equations by re-formulating the problem so that it can be solved by existing numerical solvers for two-point boundary value problems (TPBVP). The capabilities of ICRM are demonstrated by using it to solve some representative constrained trajectory optimization problems as well as a five vehicle problem with path constraints. Regularizing path constraints using ICRM represents a first step towards obtaining high quality solutions for highly constrained trajectory optimization problems which would generally be considered practically impossible to solve using indirect or direct methods. The Quasilinear Chebyshev Picard Iteration (QCPI) method builds on prior work and uses Chebyshev Polynomial series and the Picard Iteration combined with the Modified Quasi-linearization Algorithm. The method is developed specifically to utilize parallel computational resources for solving large TPBVPs. The capabilities of the numerical method are validated by solving some representative nonlinear optimal control problems. The performance of QCPI is benchmarked against single shooting and parallel shooting methods using a multi-vehicle optimal control problem. The results demonstrate that QCPI is capable of leveraging parallel computing architectures and can greatly benefit from implementation on highly parallel architectures such as GPUs. The capabilities of ICRM and QCPI are explored further using a five-vehicle constrained optimal control problem. The scenario models a co-operative, simultaneous engagement of two targets by five vehicles. The problem involves 3DOF dynamic models, control constraints for each vehicle and a no-fly zone path constraint. Trade studies are conducted by varying different parameters in the problem to demonstrate smooth transition between constrained and unconstrained arcs. Such transitions would be highly impractical to study using existing indirect methods. The study serves as a demonstration of the capabilities of ICRM and QCPI for solving large-scale trajectory optimization methods. An open source, indirect trajectory optimization framework is developed with the goal of being a viable contender to state-of-the-art direct solvers such as GPOPS and DIDO. The framework, named beluga, leverages ICRM and QCPI along with traditional indirect optimal control theory. In its current form, as illustrated by the various examples in this dissertation, it has made significant advances in automating the use of indirect methods for trajectory optimization. Following on the path of popular and widely used scientific software projects such as SciPy [1] and Numpy [2], beluga is released under the permissive MIT license [3]. Being an open source project allows the community to contribute freely to the framework, further expanding its capabilities and allow faster integration of new advances to the state-of-the-art

Aeronautical Engineering: A continuing bibliography with indexes (supplement 161)

This bibliography lists 375 reports, articles and other documents introduced into the NASA scientific and technical information system in April 1983

On the frontier: Flight research at Dryden 1946-1981

The history of flight research at the NASA Hugh L. Dryden Flight Research Center is recounted. The period of emerging supersonic flight technology (1944 to 1959) is reviewed along with the era of flight outside the Earth's atmosphere (1959 to 1981). Specific projects such as the X-15, Gemini, Apollo, and the space shuttle are addressed. The flight chronologies of various aircraft and spacecraft are given