Bibliography: p. 196-200. / M.I.T. Project DSR 76094. Contract no. NOW-66-0178-d.

Thesis (MBA)--Stellenbosch University, 2005. / ENGLISH ABSTRACT: OTB, a Division of Denel, is a multi purpose test range specialising in the in-flight testing of guided missile systems and aircraft. Originally established as a launch facility for an ambitious low earth orbit satellite programme, and with a secondary function to support the South African military industry, its raison d'etre stemmed from strategic military considerations. Changes in the political and economical scene, which started in the early nineties, led to the cancellation of the satellite programme and a dramatic downswing in the production of arms in South Africa. This rendered much of the capability of OTB redundant. Although the government signalled its desire to maintain access to the services of a test range in order to support an indigenous arms industry, OTB was structured as a division of Denel at its formation as a company operated for profit. This left OTB faced with the challenge to replace government grant funding with revenues earned in the market place. Furthermore, the drastically lower domestic military spending provided insufficient business to support a test range at the technological level required to serve the demands of modern weapons testing. In order to survive, OTB had to be successful in broadening its client base in a highly competitive commercial environment, a feat only possible with the implementation of an effective marketing strategy. The objective of this study is to formulate a marketing strategy for OTB based on a market orientated approach, bearing in mind that the task at hand is the marketing of a service. The study covers the relevant marketing theory in some depth and employs it as a basis to conduct a situational review followed by the development of an appropriate marketing mix and implementation plan. Even though the development of a marketing strategy for the test range produces some unique issues to address, the applicability and extent of coverage afforded by existing marketing theory suggest that OTB's circumstances show significant commonality with those encountered in other situations and therefore may find broader application. Some of the notable findings are: (1) the integrated marketing effort demanded by the market orientated approach; (2) the distinctive elements contained in the marketing mix of a service organisation; and (3) the possibility and need to retain a strategically founded market while developing a commercially driven market requiring particularly sharp market segmentation and distinctive strategies respectively. / AFRIKAANSE OPSOMMING: OTB, In Divisie van Denel, is 'n multi-aanwendbare toetsbaan wat spesialiseer in die in-vlug toetsing van geleide missiele en vliegtuie. Die toetsbaan is oorspronklik ontwikkel as 'n fasiliteit vir die lansering van lae aardbaan satelliete met, as sekondere funksie, die ondersteuning van die Suid-Afrikaanse militere industrie. Die aanvanklike bestaansreg van die fasiliteit was dus gesetel in militer-strategiese oorwegings. In die vroee neentigs het politieke en ekonomiese veranderinge wat aan die ontwikkel was gelei tot die kansellering van die satellietprogram en 'n drastiese afname in die produksie van krygstuig in Suid-Afrika. Die gevolg was 'n onaanvaarbare onderbenutting van die toetsbaanvermoens en -kapasiteit. Alhoewel die regering aangedui het dat dit van voornemens was om toegang tot 'n funksionerende toetsbaan te verseker ten einde die plaaslike militere industrie te ondersteun, is OTB met die stigting van Denel as 'n divisie daarvan gestruktureer met die doel om winsgewend te opereer. Dit het OTB gelaat met die uitdaging om 'n staatsbefondste begroting met 'n inkomste uit die kommersiele markte te vervang. Voorts het die dramatiese afname in die plaaslike militere spandering tot sodanige verlaging van inkomste uit hierdie bron gelei dat dit nie meer voldoende was om die toetsbaan op die verlangde tegnologiese vlak te onderhou nie. Ten einde te oorleef moes OTB sy klientebasis verbreed in 'n hoogs kompeterende kommersiele omgewing, 'n doelwit wat slegs haalbaar is met die implementering van 'n effektiewe bemarkingstrategie. Die doel van hierdie studie is die formulering van 'n bemarkingstrategie vir OTB gebaseer op 'n markgeorienteerde benadering met inagneming dat die taak voor hande die bemarking van 'n diens is. Die studie dek die relevante bemarkingsteorie tot 'n redelike mate en steun voorts daarop om 'n situasie analise, gevolg deur die ontwikkeling van 'n gepaste bemarkingsamesteliing (marketing mix) en implementeringsplan te ontwikkel. Selfs al lewer die ontwikkeling van 'n bemarkingsplan vir die toetsbaan sommige unieke aspekte op, dui die toepaslikheid van, en die mate waartoe die bestaande teorie die probleme aanspreek daarop dat OTB se omstandighede duidelike ooreenkomste toon met die wat reeds in ander situasies ondervind is. Die bevindinge hier mag dus wyer toepassing hê. Sommige van die noemenswaardige waarnemings is: (1) die geintegreerde bemarkingpoging wat deur die markgeorienteerde benadering vereis word; (2) die onderskeidende elemente wat in die bemarkingsamestelling (marketing mix) vir dienste voorkom; en (3) die moontlikheid en belangrikheid om 'n strategies gefundeerde mark te behou terwyl 'n kommersiele mark ontwikkel word met die skerp marksegmentering en spesifiek gerigte strategie wat per marksegment onderskeidelik nodig is.

Uppsatsen diskuterar möjliga lufthot mot Sverige i dag och i framtiden intill ca 2020 ur ett teknisktperspektiv, samt föreslår att kryssningsrobotar samt autonoma substridsdelar från dessa bör varadimensionerande för utformningen av det svenska luftförsvaret.Stridsdelar med såväl konventionella-, massförstörelse-, som möjliga framtida vapen behandlas. Somvapenbärare diskuteras flygplan, helikoptrar, obemannade farkoster (UAV/UCAV), kryssningsrobotar,ballistiska missiler och satelliter. / The composition discusses possible future air- and missile threats against SWEDEN, approximately untilthe year 2020. It suggests that the treat from cruise missiles equipped with autonomous submuntionsshould be dimensioning for the Swedish air-defence. Conventional-, nuclear-, biological-, chemical- andpossible future warheads are discussed. Fixed-wing aircraft, helicopters, unmanned aerial vehicles, cruisemissiles, ballistic missiles and satellites are evaluated as weapon carriers. / Avdelning: ALB - Slutet Mag 3 C-upps.Hylla: Upps. ChP T 00-02

iv ABSTRACT ADAPTIVE CONTROL OF GUIDED MISSILES Tiryaki Kutluay, Kadriye Ph.D., Department of Aerospace Engineering Supervisor: Asst. Prof. Dr. Ilkay Yavrucuk February 2011, 147 Pages This thesis presents applications and an analysis of various adaptive control augmentation schemes to various baseline flight control systems of an air to ground guided missile. The missile model used in this research has aerodynamic control surfaces on its tail section. The missile is desired to make skid to turn maneuvers by following acceleration commands in the pitch and yaw axis, and by keeping zero roll attitude. First, a linear quadratic regulator baseline autopilot is designed for the control of the missile acceleration in pitch axis at a single point in the flight envelope. This baseline autopilot is then augmented with a Direct Model Reference Adaptive Control (DMRAC) scheme using Neural Networks for parameter estimation, and an L1 Adaptive Control scheme. Using the linearized longitudinal model of the missile at the design point, simulations are performed to analyze and demonstrate the performance of the two adaptive augmentation schemes. By injecting uncertainties to the plant model, the effects of adaptive augmentations on the linear baseline autopilot are examined. v Secondly, a high fidelity simulation software of the missile is used in order to analyze the performance of the adaptive augmentations in 6 DoF nonlinear flight simulations. For the control of the missile in three axis, baseline autopilots are designed using dynamic inversion at a single point in the flight envelope. A linearizing transformation is employed during the inversion process. These coarsely designed baseline autopilots are augmented with L1 adaptive control elements. The performance of the adaptive control augmentation system is tested in the presence of perturbations in the aerodynamic model and increase in input gain, and the simulation results are presented.

The field of guided projectile research has continually grown over the past several decades. Guided projectiles, typically encompassing bullets, mortars, and artillery shells, incorporate some sort of guidance and control mechanism to generate trajectory alterations. This serves to increase accuracy and decrease collateral damage. Control mechanisms for smart weapons must be able to withstand extreme acceleration loads at launch while remain simple for cost and reliability reasons. One type of control mechanism utilizes controllable internal translating masses (ITM's) that oscillate within the projectile to generate control forces. Several techniques for using internal translating masses for smart weapon flight control purposes are explored here. Specifically, the use of ITM's as direct control mechanisms, as a means to increase control authority, and as a means to protect the smart weapons sensor suite are examined. It is first shown that oscillating a mass orthogonal to the projectile axis of symmetry generates reasonable control force in statically-stable rounds. Trade studies examine the impact of mass size, mass offset from the center of gravity, and reductions in static stability on control authority. Then, the topic of static margin control through mass center modification is explored. This is accomplished by translating a mass in flight along the projectile axis of symmetry. Results show that this system allows for greater control authority and reduced throw-off error at launch. Another study, aimed at examining shock reduction potential at launch rather than static margin alteration, also considers ITM movement along the projectile centerline. In these studies, the ITM is comprised of sensitive electronic sensors, and is configured as a first-order damper during launch. Trade study results show that although the mechanism cannot substantially reduce the magnitude of launch loads, it is successful at dampening harmful structural vibrations typically experienced after muzzle exit. Finally, an active control system is developed for the ITM control mechanism using sliding mode methodology. Example cases and Monte Carlo simulations incorporating model uncertainties and sensor errors show that ITM control of projectiles can substantially reduce dispersion error. Furthermore, the novel sliding mode control law is shown to be highly robust to feedback disturbances. In a final study, combined ITM-canard control of projectiles is explored, concluding that ITM mechanisms can serve as a useful supplement in increasing the efficiency of currently-deployed control mechanisms.

A satellite launch vehicle not subjected to any perturbations, external or internal, could be guided along a trajectory by following a stored, pre-computed steering program. In practice, perturbations do occur, and in order to take account of them and to achieve an accurate injection, a closed loop guidance system is required. Guidance algorithm is developed by solving the optimal control problem. Closed form solution is difficult because the necessary conditions are in the form of Two Point Boundary Value Problems (TBVP) or Multi Point Boundary Value Problems (MPBVP). Development of non-iterative guidance algorithm is taken as a prime objective of this thesis to ensure reliable on-board implementation. If non-iterative algorithms are required, the usual practice is to approximate the system equations to derive closed form solutions. In the present work, approximations cannot be used because the algorithm has to cater to a wide variety of vehicles and missions. Present development adopts an alternate approach by splitting the reconfigurable algorithm development in to smaller sub-problems such that each sub-problem has closed form solution. The splitting is done in such a way that the solution of the sub-problems can be used as building blocks to construct the final solution. By adding or removing the building blocks, the algorithm can be configured to suit specific requirements. Chapter 1 discusses the motivation and objectives of the thesis and gives a literature survey. In chapter 2, Classical Flat Earth (CFE) guidance algorithm is discussed. The assumptions and the nature of solution are closely analyzed because CFE guidance is used as the baseline for further developments. New contribution in chapter 2 is the extension of CFE guidance for a generalized propulsion system in which liquid and solid engines are present. In chapter 3, CFE guidance is applied for a mission with large pitch steering angles. The result shows loss of optimality and performance. An algorithm based on regular perturbation is developed to compensate for the small angle approximation. The new contribution in chapter 3 is the development of Regular Perturbation based FE (RPFE) guidance as an extension of CFE guidance. RPFE guidance can be configured as CFE guidance and FEGP. Algorithms presented up to chapter 3 are developed to inject a satellite in to orbits with unspecified inertial orientation. Communication satellite missions demand injection in to an orbit with a specific inertial orientation defined by argument of perigee. This problem is formulated using Calculus of Variations in chapter 4. A non-iterative closed form solution (Predicted target Flat Earth or PFE guidance) is derived for this problem. In chapter 5, PFE guidance is extended to a multi-stage vehicle with a constraint on the impact point of spent lower stage. Since the problem is not analytically solvable, the original problem is split in to three sub-problems and solved. Chapter 6 has two parts. First part gives theoretical analysis of the sub-optimal strategies with special emphasis to guidance. Behavior of predicted terminal error and control commands in presence of plant approximations are theoretically analyzed for a class of optimal control problems and the results are presented as six theorems. Chapter 7 presents the conclusions and future works.

My research provides a historical and archaeological context for this thesis, in which I argue the JB-2 missile is historically significant as a unique example of the rapid duplication of enemy technology for both physical and psychological retaliation, as a crucial link in the chain of development for America’s cruise missile program, and for its role in early Cold War deterrence. Jet Bomb model number 2 (JB-2), America’s first operationally successful, mass produced cruise missile, developed as a direct copy of the German V-1, with slight variation in manufacture due to differences between German and American components, machinery and tooling. Continuing modifications of the JB-2 during its service life led to improvements in performance, control, and accuracy. From 1944 to 1953, the JB-2 transitioned from a weapon quickly prepared for wartime deployment to an essential test vehicle for the United States Army, Air Force and Navy while supporting the U.S. policy of containment during the early Cold War.