Preface

This book is a collection of reviewed and relevant research chapters, concerning the developments within the Aerospace Engineering field of study. The book includes scholarly contributions by various authors, edited by an expert in the engineering field. Each contribution is a separate chapter but each is directly related to the book's topic and objectives.

The book includes nine chapters dealing with the following topics: Green Comparable Alternatives of Hydrazines-Based Monopropellant and Bipropellant Rocket Systems, High Strain Rate Characterization of Thermoplastic Fiber-Reinforced Composites under Compressive Loading, Matrix Converter for More Electric Aircraft, Turbine Engine Lubricant and Additive Degradation Mechanisms, The Evolution of the Composite Fuselage: A Manufacturing Perspective, Robotic Autonomous Spacecraft Missions: Cassini Mission-To-Saturn Example, Advanced Nonlinear Modeling of Gas Turbine Dynamics, Effect of Microstructure on Microhardness and Electrochemical Behavior in Hypereutectic Al-Fe Alloy Processed by Laser Surface Remelting, and Optimal Control of Fuzzy Systems with Application to Rigid Body Attitude Control.

The target audience comprises scholars and specialists in the field.

**II**

Control

*by Yonmook Park*

**Chapter 9 191**

Optimal Control of Fuzzy Systems with Application to Rigid Body Attitude

**IntechOpen**

**1**

**Chapter 1**

*and Moti Elyashiv*

characteristic velocity efficiency exceeding 98%.

kerosene, hydrazines

**1. Introduction**

**Abstract**

Green Comparable Alternatives of

Hydrazines-Based Monopropellant

and Bipropellant Rocket Systems

Concepts are presented for "green" (with reduced hazards) replacements for monopropellant hydrazine propulsion systems and for hypergolic bipropellant systems while maintaining similar performance. At the onset of the "green propulsion" age, "green" alternatives to hydrazine propulsion have been emerging. The introduction rate of these into space systems is very slow due to the conservatism of the space propulsion industry. The concept presented here for monopropellant hydrazine systems offers gradual conversion to "green propellants" by dual capability of conventional hydrazine systems and ammonium dinitramide (ADN)-based systems. An initial risk reduction program has been carried out for materializing the concept. It includes proof of concept of dual use of all propulsion system parts. Materials compatibility and actual operation have been demonstrated. For bipropellants, we present the emerging "green" hypergolic system based on kerosene and peroxide, similar in performance to MMH/N2O4. Results of the proof-of-concept and development model systems are presented. The experimental results of various engine types demonstrate the capability to operate in both pulse and steady-state modes and the ability to produce different thrust levels. The fuel and oxidizer show very robust hypergolicity and short ignition delay times, as well as

**Keywords:** green propulsion, hypergolic, space propulsion, rocket, thruster, H2O2,

The use of chemical propulsion systems for rocket engines is quite common for over half a century. Hydrazines are the major chemical space propellants of choice due to their good performance and reliable track record. A majority of low earth orbit (LEO) satellite propulsion systems are based on monopropellant hydrazine thrusters. The Israeli Offek LEO satellites employ such a hydrazine system [1–3]. **Figure 1** depicts the Offek satellite top plate with monopropellant hydrazine thrusters, being the space facing part of the propulsion module. **Figure 2** depicts the propulsion system module and its schematic, which identify the construction and major parts and components of a typical monopropellant space propulsion system.

*Dov Hasan, Dan Grinstein, Alexander Kuznetsov,* 

*Benveniste Natan, Zohar Schlagman, Avihay Habibi*
