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Author | : National Aeronautics and Space Administration (NASA) |
Publisher | : Createspace Independent Publishing Platform |
Total Pages | : 46 |
Release | : 2018-07-13 |
Genre | : |
ISBN | : 9781722912598 |
Download Trajectory Optimization for the National Aerospace Plane Book in PDF, ePub and Kindle
The primary objective of this research is to develop an efficient and robust trajectory optimization tool for the optimal ascent problem of the National Aerospace Plane (NASP). This report is organized in the following order to summarize the complete work: Section two states the formulation and models of the trajectory optimization problem. An inverse dynamics approach to the problem is introduced in Section three. Optimal trajectories corresponding to various conditions and performance parameters are presented in Section four. A midcourse nonlinear feedback controller is developed in Section five. Section six demonstrates the performance of the inverse dynamics approach and midcourse controller during disturbances. Section seven discusses rocket assisted ascent which may be beneficial when orbital altitude is high. Finally, Section eight recommends areas of future research. Lu, Ping Unspecified Center NAG1-1255...
Author | : National Aeronautics and Space Administration (NASA) |
Publisher | : Createspace Independent Publishing Platform |
Total Pages | : 130 |
Release | : 2018-07-23 |
Genre | : |
ISBN | : 9781723464409 |
Download Trajectory Optimization and Guidance Law Development for National Aerospace Plane Applications Book in PDF, ePub and Kindle
The work completed to date is comprised of the following: a simple vehicle model representative of the aerospace plane concept in the hypersonic flight regime, fuel-optimal climb profiles for the unconstrained and dynamic pressure constrained cases generated using a reduced order dynamic model, an analytic switching condition for transition to rocket powered flight as orbital velocity is approached, simple feedback guidance laws for both the unconstrained and dynamic pressure constrained cases derived via singular perturbation theory and a nonlinear transformation technique, and numerical simulation results for ascent to orbit in the dynamic pressure constrained case. Calise, A. J. and Flandro, G. A. and Corban, J. E. Unspecified Center DYNAMIC MODELS; FEEDBACK CONTROL; FUEL CONSUMPTION; HYPERSONIC AIRCRAFT; OPTIMAL CONTROL; PERTURBATION THEORY; PRESSURE EFFECTS; SUPERSONIC COMBUSTION RAMJET ENGINES; WIND TUNNEL TESTS...
Author | : National Aeronautics and Space Adm Nasa |
Publisher | : Independently Published |
Total Pages | : 40 |
Release | : 2018-10-17 |
Genre | : Science |
ISBN | : 9781728893075 |
Download Rapid Near-Optimal Aerospace Plane Trajectory Generation and Guidance Book in PDF, ePub and Kindle
Effort was directed toward the problems of the real time trajectory optimization and guidance law development for the National Aerospace Plane (NASP) applications. In particular, singular perturbation methods were used to develop guidance algorithms suitable for onboard, real time implementation. The progress made in this research effort is reported. Calise, A. J. and Corban, J. E. and Markopoulos, N. Unspecified Center NAG1-922
Author | : National Aeronautics and Space Administration (NASA) |
Publisher | : Createspace Independent Publishing Platform |
Total Pages | : 42 |
Release | : 2018-07-13 |
Genre | : |
ISBN | : 9781722912338 |
Download Trajectory Optimization and Guidance for an Aerospace Plane Book in PDF, ePub and Kindle
The first step in the approach to developing guidance laws for a horizontal take-off, air breathing single-stage-to-orbit vehicle is to characterize the minimum-fuel ascent trajectories. The capability to generate constrained, minimum fuel ascent trajectories for a single-stage-to-orbit vehicle was developed. A key component of this capability is the general purpose trajectory optimization program OTIS. The pre-production version, OTIS 0.96 was installed and run on a Convex C-1. A propulsion model was developed covering the entire flight envelope of a single-stage-to-orbit vehicle. Three separate propulsion modes, corresponding to an after burning turbojet, a ramjet and a scramjet, are used in the air breathing propulsion phase. The Generic Hypersonic Aerodynamic Model Example aerodynamic model of a hypersonic air breathing single-stage-to-orbit vehicle was obtained and implemented. Preliminary results pertaining to the effects of variations in acceleration constraints, available thrust level and fuel specific impulse on the shape of the minimum-fuel ascent trajectories were obtained. The results show that, if the air breathing engines are sized for acceleration to orbital velocity, it is the acceleration constraint rather than the dynamic pressure constraint that is active during ascent. Mease, Kenneth D. and Vanburen, Mark A. Unspecified Center NAG1-907...
Author | : |
Publisher | : |
Total Pages | : 0 |
Release | : 1989 |
Genre | : Aerospace planes |
ISBN | : |
Download Trajectory Optimization and Guidance for an Aerospace Plane Book in PDF, ePub and Kindle
Author | : National Aeronaut Administration (Nasa) |
Publisher | : Createspace Independent Publishing Platform |
Total Pages | : 62 |
Release | : 2018-07-10 |
Genre | : |
ISBN | : 9781722681968 |
Download Optimal Trajectories for an Aerospace Plane. Part 1 Book in PDF, ePub and Kindle
The optimization of the trajectories of an aerospace plane is discussed. This is a hypervelocity vehicle capable of achieving orbital speed, while taking off horizontally. The vehicle is propelled by four types of engines: turbojet engines for flight at subsonic speeds/low supersonic speeds; ramjet engines for flight at moderate supersonic speeds/low hypersonic speeds; scramjet engines for flight at hypersonic speeds; and rocket engines for flight at near-orbital speeds. A single-stage-to-orbit (SSTO) configuration is considered, and the transition from low supersonic speeds to orbital speeds is studied under the following assumptions: the turbojet portion of the trajectory has been completed; the aerospace plane is controlled via the angle of attack and the power setting; the aerodynamic model is the generic hypersonic aerodynamics model example (GHAME). Concerning the engine model, three options are considered: (EM1), a ramjet/scramjet combination in which the scramjet specific impulse tends to a nearly-constant value at large Mach numbers; (EM2), a ramjet/scramjet combination in which the scramjet specific impulse decreases monotonically at large Mach numbers; and (EM3), a ramjet/scramjet/rocket combination in which, owing to stagnation temperature limitations, the scramjet operates only at M approx. less than 15; at higher Mach numbers, the scramjet is shut off and the aerospace plane is driven only by the rocket engines. Under the above assumptions, four optimization problems are solved using the sequential gradient-restoration algorithm for optimal control problems: (P1) minimization of the weight of fuel consumed; (P2) minimization of the peak dynamic pressure; (P3) minimization of the peak heating rate; and (P4) minimization of the peak tangential acceleration. Miele, Angelo and Lee, W. Y. and Wu, G. D. Unspecified Center...
Author | : H. D. Froning |
Publisher | : |
Total Pages | : |
Release | : 1996 |
Genre | : |
ISBN | : |
Download Aerospace Plane Trajectory Optimization for Sub-orbital Boost Glide Flight Book in PDF, ePub and Kindle
Author | : Bruce A. Conway |
Publisher | : Cambridge University Press |
Total Pages | : 313 |
Release | : 2010-08-23 |
Genre | : Technology & Engineering |
ISBN | : 113949077X |
Download Spacecraft Trajectory Optimization Book in PDF, ePub and Kindle
This is a long-overdue volume dedicated to space trajectory optimization. Interest in the subject has grown, as space missions of increasing levels of sophistication, complexity, and scientific return - hardly imaginable in the 1960s - have been designed and flown. Although the basic tools of optimization theory remain an accepted canon, there has been a revolution in the manner in which they are applied and in the development of numerical optimization. This volume purposely includes a variety of both analytical and numerical approaches to trajectory optimization. The choice of authors has been guided by the editor's intention to assemble the most expert and active researchers in the various specialities presented. The authors were given considerable freedom to choose their subjects, and although this may yield a somewhat eclectic volume, it also yields chapters written with palpable enthusiasm and relevance to contemporary problems.
Author | : Angelo Miele |
Publisher | : |
Total Pages | : 42 |
Release | : 1959 |
Genre | : Jet planes |
ISBN | : |
Download Approximate Solutions to Optimum Flight Trajectories for a Turbojet-powered Aircraft Book in PDF, ePub and Kindle
Author | : Runqi Chai |
Publisher | : Springer |
Total Pages | : 207 |
Release | : 2019-07-30 |
Genre | : Technology & Engineering |
ISBN | : 9811398453 |
Download Design of Trajectory Optimization Approach for Space Maneuver Vehicle Skip Entry Problems Book in PDF, ePub and Kindle
This book explores the design of optimal trajectories for space maneuver vehicles (SMVs) using optimal control-based techniques. It begins with a comprehensive introduction to and overview of three main approaches to trajectory optimization, and subsequently focuses on the design of a novel hybrid optimization strategy that combines an initial guess generator with an improved gradient-based inner optimizer. Further, it highlights the development of multi-objective spacecraft trajectory optimization problems, with a particular focus on multi-objective transcription methods and multi-objective evolutionary algorithms. In its final sections, the book studies spacecraft flight scenarios with noise-perturbed dynamics and probabilistic constraints, and designs and validates new chance-constrained optimal control frameworks. The comprehensive and systematic treatment of practical issues in spacecraft trajectory optimization is one of the book’s major features, making it particularly suited for readers who are seeking practical solutions in spacecraft trajectory optimization. It offers a valuable asset for researchers, engineers, and graduate students in GNC systems, engineering optimization, applied optimal control theory, etc.