Guidance Concepts for the Interception of an Intermediate Range Ballistic Missile During Its Boost Phase PDF Download
Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download Guidance Concepts for the Interception of an Intermediate Range Ballistic Missile During Its Boost Phase PDF full book. Access full book title Guidance Concepts for the Interception of an Intermediate Range Ballistic Missile During Its Boost Phase by William John Wollenberg. Download full books in PDF and EPUB format.
Author: William John Wollenberg
Publisher:
ISBN:
Category :
Languages : en
Pages :
Get Book Here
Book Description
Author: William John Wollenberg
Publisher:
ISBN:
Category :
Languages : en
Pages :
Get Book Here
Book Description
Author: Florios Bardanis
Publisher:
ISBN: 9781423586302
Category :
Languages : en
Pages : 69
Get Book Here
Book Description
Boost phase interception of ballistic missiles is envisioned as the primary response of the layered defense architecture implemented in the ballistic missile defense system. A limited time frame in which to take action and the necessity to implement hit-to-kill technology in the kill vehicle counterbalances the many advantages of boost phase interception. Direct hit missile technology is constrained by the requirement to minimize miss distance to a negligible amount between the kill vehicle and optimum aim point on the target. This thesis examines kill vehicle effectiveness, which is tantamount to miss distance, as a function of both the kill vehicle maximum acceleration capability and the guidance system time constant necessary to destroy a target. The kill vehicle guidance system is modeled in MATLAB as a fifth-order binomial series with proportional navigation. The simulation examines the effect of an accelerating target attributed to powered flight and aim point displacement caused by a shift in tracking point from the target plume to the payload when resolution occurs. The kill vehicle minimum requirements as indicated by the simulation include a lateral acceleration capability of four times the target acceleration and a guidance system time constant that is less than one-tenth the estimated flight time. (4 tables, 22 figures, 19 refs.)
Author:
Publisher:
ISBN:
Category : Ballistic missiles
Languages : en
Pages : 141
Get Book Here
Book Description
A near-optimal guidance law has been developed using the direct method of calculus of variations that maximizes the kinetic energy transfer from a surface-launched missile upon interception to a ballistic missile target during the boost phase of flight. Mathematical models of a North Korean Taep'o-dong II (TD-2) medium-range ballistic missile and a Raytheon Standard Missile 6 (SM-6) interceptor are used to demonstrate the guidance law2s performance. This law will utilize the SM-62s onboard computer and active radar sensors to independently predict an intercept point, solve the two-point boundary value problem, and determine a near-optimal flight path to that point. Determining a truly optimal flight path would require significant computing power and time, while a near-optimal flight path can be calculated onboard the interceptor and updated in real time without significant changes to the interceptor2s hardware. That near-optimal guidance path is then converted into a set of command functions and fed back into the control computer of the interceptor. By modifying the second and third derivatives of the two-point boundary value problem, the intercept conditions can be varied to study their effects upon the optimal flight path regarding the maximization of kinetic energy upon impact.
Author: Weng Wai Leong
Publisher:
ISBN:
Category : Ballistic missiles
Languages : en
Pages : 117
Get Book Here
Book Description
In recent conflicts, ballistic missiles have been used to achieve military and psychological objectives. With the proliferation of weapons of mass destruction (WMD), the threat of ballistic missiles as delivery platform for WMD is of concern. Defense against such threats becomes important. There are different guidance laws, like pursuit and proportional navigation (PN), for the missile interception of aerial targets. A new guidance algorithm was developed by John A. Lukacs and Prof Yakimenko in 2006 to demonstrate the feasibility of intercepting a ballistic missile during the boost phase. This trajectory-shaping guidance algorithm uses the direct method of calculus of variations that maximizes the kinetic energy transfer from the interceptor to the target. A study was conducted by applying this guidance law and examining the trade-off between the various critical parameters, like intercept geometry, time, altitude and trajectory, in the optimized solution. It provides insights into the feasibility and limitations of this guidance. A literature review of the drag model and comparison with the compensated PN guidance was also conducted. A new induced drag model was developed for future studies. The results verified that the trajectory-shaping guidance is feasible for the interception of ballistic missiles in the boost phase for a wide range of interceptor launch locations with respect to a ballistic missile detection point.
![An Optimal T-[Delta]v Guidance Law for Intercepting a Boosting Target PDF](https://books.google.com/books/content/images/frontcover/SzHRjwEACAAJ?fife=w80-h100)
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages :
Get Book Here
Book Description
Lawrence Livermore National Laboratory (LLNL) have developed a new missile guidance law for intercepting a missile during boost phase. Unlike other known missile guidance laws being used today, the new t-[Delta]v guidance law optimally trades an interceptor's onboard fuel capacity against time-to-go before impact. In particular, this guidance law allows a missile designer to program the interceptor to maximally impact a boosting missile before burnout or burn termination and thus negating its ability to achieve the maximum kinetic velocity. For an intercontinental range ballistic missile (ICBM), it can be shown that for every second of earlier intercept prior to burnout, the ICBM ground range is reduced by 350 km. Therefore, intercepting a mere 15 seconds earlier would result in amiss of 5,250 km from the intended target or approximately a distance across the continental US. This paper also shows how the t-[Delta]v guidance law can incorporate uncertainties in target burnout time, predicted intercept point (PIP) error, time-to-go error, and other track estimation errors. The authors believe that the t-[Delta]v guidance law is a step toward the development of a new and smart missile guidance law that would enhance the probability of achieving a boost phase intercept.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 50
Get Book Here
Book Description
Boost-phase intercept of a threat intercontinental ballistic missile (ICBM) is the first layer of a multilayer missile defense strategy. Space-based interceptors possess certain kinematic advantages over ground-based interceptors in defeating an ICBM threat during boost phase. This paper explores the performance of various guidance laws that might be used by an exo-atmospheric kill vehicle (EKV) launched from a space platform to defeat a hostile, ground-launched ICBM during boost phase. Proportional navigation guidance, bang-bang guidance and predictive guidance are all investigated using simulated missile and EKV trajectories. Performance results are presented with respect to miss distance, intercept time, launch envelope, and total control effort. The total control effort is directly related to fuel consumption, and smaller values translate to less weight in fuel or longer potential intercept ranges. Large launch envelopes mean fewer required EKV carriers. In general, the predictive guidance algorithm outperformed the other guidance algorithms in these simulations, but it did prove to be sensitive to timeto- go errors.
Author: Kubilay Uzun
Publisher:
ISBN: 9781423520115
Category :
Languages : en
Pages : 163
Get Book Here
Book Description
The objective of this thesis is to investigate the requirements and limitations of boost phase ballistic missile intercept systems that contain interceptor and its guidance sensors (both radar and infrared). A three- dimensional computer model is developed for a multi-stage target with a boost phase acceleration profile that depends on total mass, propellant mass and the specific impulse in the gravity field. The radar cross-section and infrared radiation of the target structure are estimated as a function of the flight profile. The interceptor is a multi-stage missile that uses fused target location data provided by two ground-based radar sensors and two low earth orbit infrared sensors. Interceptor requirements and limitations are derived as a function of its initial position from the target launch point and the launch delay. Sensor requirements are also examined as a function of the signal-to- noise ration during the target flight. Electronic attack considerations within the boost phase are also addressed including the use of decoys and noise jamming techniques. The significance of this investigation is that the system components within a complex boost phase intercept scenario can be quantified and requirement for the sensors can be numerically derived.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 9
Get Book Here
Book Description
Finding guidance methods that efficiently and effectively handle the problem of directing the boost-phase portion of an exoatmospheric tactical ballistic missile interceptor is an active area of research. This paper presents a candidate method that is a hybrid combination of three algorithms. The chief method, used throughout the majority of the flight, is a minimum-time neighboring optimal control scheme. As demonstrated through Monte Carlo simulations, perturbations in the predicted intercept point (caused by boost-phase updates of the target state estimate received from an exogenous radar) are corrected for in a smooth manner which preserves performance. Even large corrections are handled with low angles of attack, and less than one percent changes in burnout velocity relative to theoretical open-loop optimal control values. Near the end of the booster burn, the guidance scheme switches over to two Lambert-based guidance methods, which have the effect of taking out residual velocity errors, thus putting the interceptor on a nearly exact intercept path to the latest estimate of the target trajectory. The total scheme, while being somewhat computationally complex in pre-deployment development, is actually computationally simple for on-board computations, and has a small computer memory requirement. Therefore, the robust performance combined with the light computational burden provided by this hybrid algorithm make it a competitive candidate for boost-phase interceptor guidance.
Author: Department Of Defense
Publisher: Independently Published
ISBN: 9781794441101
Category : History
Languages : en
Pages : 108
Get Book Here
Book Description
2019 Missile Defense Review - January 2019 According to a senior administration official, a number of new technologies are highlighted in the report. The review looks at "the comprehensive environment the United States faces, and our allies and partners face. It does posture forces to be prepared for capabilities that currently exist and that we anticipate in the future." The report calls for major investments from both new technologies and existing systems. This is a very important and insightful report because many of the cost assessments for these technologies in the past, which concluded they were too expensive, are no longer applicable. Why buy a book you can download for free? We print this book so you don't have to. First you gotta find a good clean (legible) copy and make sure it's the latest version (not always easy). Some documents found on the web are missing some pages or the image quality is so poor, they are difficult to read. We look over each document carefully and replace poor quality images by going back to the original source document. We proof each document to make sure it's all there - including all changes. If you find a good copy, you could print it using a network printer you share with 100 other people (typically its either out of paper or toner). If it's just a 10-page document, no problem, but if it's 250-pages, you will need to punch 3 holes in all those pages and put it in a 3-ring binder. Takes at least an hour. It's much more cost-effective to just order the latest version from Amazon.com This book includes original commentary which is copyright material. Note that government documents are in the public domain. We print these large documents as a service so you don't have to. The books are compact, tightly-bound, full-size (8 1/2 by 11 inches), with large text and glossy covers. 4th Watch Publishing Co. is a HUBZONE SDVOSB. https: //usgovpub.com
Author: Tetsuya Takehira
Publisher:
ISBN:
Category :
Languages : en
Pages : 554
Get Book Here
Book Description
