scispace - formally typeset
Search or ask a question
Book

Introduction to Rocket Science and Engineering

01 Jan 2009-
TL;DR: In this article, the authors present a review of the history of the development of the modern era of the rocket and its use in space missions, as well as a survey of the current state of the art.
Abstract: What Are Rockets? The History of Rockets Rockets of the Modern Era Rocket Anatomy and Nomenclature Why Are Rockets Needed? Missions and Payloads Trajectories Orbits Orbit Changes and Maneuvers Ballistic Missile Trajectories How Do Rockets Work? Thrust Specific Impulse Weight Flow Rate Tsiolkovsky's Rocket Equation Staging Rocket Dynamics, Guidance, and Control How Do Rocket Engines Work? The Basic Rocket Engine Thermodynamic Expansion and the Rocket Nozzle Exit Velocity Rocket Engine Area Ratio and Lengths Rocket Engine Design Example Are All Rockets the Same? Solid Rocket Engines Liquid Propellant Rocket Engines Hybrid Rocket Engines Electric Rocket Engines Nuclear Rocket Engines Solar Rocket Engines Photon-Based Engines How Do We Test Rockets? The Systems Engineering Process and Rocket Development Measuring Thrust Pressure Vessel Tests Shake 'n Bake Tests Drop and Landing Tests Environment Tests Destructive Tests Modeling and Simulation Roll-Out Test Flight Tests Are We Thinking Like Rocket Scientists and Engineers? Weather Cocking Fuel Sloshing Propellant Vorticity Tornadoes and Overpasses Flying Foam Debris Monocoque The Space Mission Analysis and Design Process Back to the Moon Suggested Reading for Rocket Scientists and Engineers Index A Chapter Summary and Exercises appear at the end of each chapter.
Citations
More filters
Journal ArticleDOI
24 May 2019
TL;DR: The pressure trend of the SRM obtained was also compared to those in well-established literature, thus, the pseudo-numerical approach put forward proves to be effective.
Abstract: To characterize SRM, the motor needs to be tested on a static test rig and certain performers indicators evaluated. In this study, the thrust with time from the SRM was acquired via a Digital Acquisition (DAQ) System and saved in Microsoft Excel® format(.csv). These thrust and time of the tested motor were then imported into MATLAB® for the purpose of computing burn time, maximum thrust, average thrust, total impulse, specific impulse and chamber pressure of the motor. The specific impulse and combustion chamber pressure for the SRM were computed in a novel approach which we call Pseudo-numerical approach (combination of experimental result with numerical computation). In this approach, first, we modelled the depleting propellant mass in the combustion chamber with a novel mathematical expression. This novel expression was then used in computing specific impulse of the SRM. Second, the total surface area of the propellant grain was modelled as a hollow cylinder with depleting dynamics during motor operation, in a similar manner with the propellant mass. Third, multiplying the reciprocal of the propellant grain surface area with the experimental force gave use the pseudo-numerically computed chamber pressure. The pressure trend of the SRM obtained was also compared to those in well-established literature, thus, the pseudo-numerical approach put forward proves to be effective.

5 citations


Cites background from "Introduction to Rocket Science and ..."

  • ...For sounding rockets, typical values for thrust-to-weight ratio is within the range of 3-4 (Taylor, 2009): 705.3 , 9.8 avg w L Thrust T Weight m = = × (1) where, mL is the lift off mass of the rocket....

    [...]

Proceedings ArticleDOI
03 Jan 2022
TL;DR: A review of relaxor piezoelectric single crystal materials, such as PMN-PT, Pb(In 1/2Nb1/2)O3-PbTiO3 (PIN-PMN), PbZn1/3Nb2/3), PZN-PZN, and PZT ceramics can be found in this article .
Abstract: This paper review the developments of relaxor piezoelectric single crystal materials, such as Lead Magnesium Niobate - Lead Titanate (PMN-PT), Pb(In1/2Nb1/2)O3–Pb(Mg1/3Nb2/3)O3–PbTiO3 (PIN-PMN-PT), Pb(Zn1/3Nb2/3)O3-PbTiO3 (PZN-PT), for cryogenic actuators. The relaxor piezoelectric single crystal materials have significant advantages over the common piezoelectric ceramic materials. For instance, more than 80% electrotechnical energy conversion efficiency was approved by several experimental studies. Moreover, the electrotechnical energy conversion efficiency remaining 80% at liquid nitrogen temperature (-197oC). Several of high-performance cryogenic actuators have been developed. These actuators can be applied to lunar and space exploration missions, such as actuators for space robotics and cryogenic valves/injectors for cryogenic fluid managements. The relaxor piezoelectric single crystal-based cryogenic actuators have the potential to make weight/volume reduction down to 20% in comparison with PZT ceramics, which are the popular used piezoelectric materials. The high-performance Cryogenic actuation is also advance other space applications such as primary mirror segment and secondary mirror alignment (position actuators), primary mirror segment figure control (force actuators), deformable mirror control, structure deployment, and many others. The review will provide more choices for aerospace sectors for their future components and system designs.

4 citations

09 Oct 2011
TL;DR: This project aims to enhance the real time surveillance capability of RAN small teams in the littoral environment by designing and developing the launching device (LD) for the SeaEagle fixed wing UAV from the RAN Armidale Class Patrol Boats.
Abstract: Royal Australian Navy (RAN) Armidale Class Patrol Boats (ACPB) currently provide a seaborne surveillance capability incorporating border protection and fisheries patrols in the North Australian Exclusive Economic Zone. This project aims to enhance the real time surveillance capability of RAN small teams in the littoral environment. Unmanned Aerial Vehicles (UAV) can be used to detect, locate, track and identify targets of interest. Integrating a quick launch and recover UAV from patrol boats would enable the local commander greater flexibility, increasing the range of the ships surveillance capability. Currently no ship-borne UAV is used in the RAN. This project starts the process of designing and developing the launching device (LD) for the SeaEagle fixed wing UAV from the RAN Armidale Class Patrol Boats. To this extent, a feasibility design and development process, incorporating the operational requirements analysis has been undertaken. Customer requirements have been achieved through interviewing potential customers and assessing current commercially available LD in production to determine a gap in the market. Analysis of the customer requirements was determined through the use of Quality Function Deployment (QFD) methodology to produce a functional specification baseline for the design process. The conceptual design phase was based on a modification to the design process outlined by Dr. Daniel Raymer. Using the functional baseline achieved, a number of possible designs were produced to resolve the LD requirements. Through the design selection process, a conceptual design concept was determined, employing elastic bungee cords for launch. The LD was validated to confirm to the functional baseline and in some instances, exceed the customer requirements. These results were validated against current production systems of similar design. Results obtained provide the RAN with the potential for further enhancing future seaborne surveillance capability.

3 citations


Cites background from "Introduction to Rocket Science and ..."

  • ...Ullman (1992) describes the relationship as: 9 = Strong Relation 3 = Medium Relation 1 = Weak Relation Blank = No Relation The relationship of customer requirements to both engineering performance specifications and geometry and description specifications is attached at appendix C6-1 and C6-2 respectively....

    [...]

Proceedings ArticleDOI
28 Jul 2014
TL;DR: The design analysis of a printed hybrid thruster for use in a nanoscale satellite propulsion module uses nitrous oxide and a nylon based fuel propellant combination.
Abstract: Nanoscale satellites have emerged as an area of interest to a variety of entities. Due to their small volume and weight, nanoscale satellites can easily travel as secondary payloads on a launch vehicle, but they are typically limited in orbit selection due to the target orbit of the primary payload. This orbit selection limitation can be mitigated through the addition of a propulsion system to a nanoscale satellite. This paper details the design analysis of a printed hybrid thruster for use in a nanoscale satellite propulsion module. The thruster design uses nitrous oxide and a nylon based fuel propellant combination. The analysis predicts an average thrust of 65 N and a specific impulse of 217 s for the thruster. Future work will include experimental testing at the University of Alabama in Huntsville Propulsion Research Center to provide validation of the analysis for use in design of a propulsion module.

3 citations

Journal ArticleDOI
TL;DR: In this paper, the authors compare Earth to the most common type of exoplanet, the super-Earth, with respect to interplanetary space travel and show that the typical super-earth should have higher gravity and atmospheric pressure at its surface.
Abstract: Here, we compare Earth to the most common type of exoplanet, the super-Earth, with respect to interplanetary space travel. The typical super-Earth should have higher gravity and atmospheric pressure at its surface. These factors pose significant challenges to rocket launches and to reentering spacecraft. In addition, the Solar System is compared to exoplanetary systems with respect to interstellar travel. It is easier to launch an interstellar spacecraft from a planet in the circumstellar habitable zone of the Sun than from planets in the circumstellar habitable zones of less massive stars. In the larger context of the Milky Way galaxy, our Solar System is in the best location to initiate interstellar missions. In summary, we here confirm and expand upon recent studies that argue that the Earth and the Solar System are rare in the degree to which they facilitate space exploration.

3 citations


Cites methods from "Introduction to Rocket Science and ..."

  • ...Escape from the planet The Tsiolkovsky equation [7, 8] gives the maximum change in velocity (delta-V) applicable to a simple single stage rocket or a single stage in a multistage rocket: (1)...

    [...]