Requirements, Design and Prototype of a Virtual User Interface for the AFIT Virtual Spaceplane

The United States Air Force is evaluating the feasibility of designing a military spaceplane capable of accomplishing military objectives from a low earth orbit and atmospheric flight regimes. Current efforts are involved in determining the scientific, operational, and budgetary constraints associated with this concept. This thesis looks at the exploration of new interface techniques associated with the design of a virtual spaceplane and is a subset of the overall virtual spaceplane effort which will assist researchers in determining the feasibility of a military spaceplane. Interface techniques are integrated into a virtual user interface that is designed to accommodate expected operations associated with atmospheric and low earth orbit military operations. We expect these operations to include satellite deployment and recovery reconnaissance, and space station construction and resupply. The focus of the virtual user interface design effort involves the application and integration of current interface design methodologies and virtual environment technologies to support the functionality of a virtual spaceplane

Architecture, Design, and Implementation of a Rapidly Prototyped Virtual Environment for a Military Spaceplane

The new Global Engagement vision places increased emphasis on the Air Force\u27s ability to control and exploit space. A military spaceplane combining reliable access to space, high operational tempos, and multi-mission capabilities is in conceptual stages of development. Virtual environment technology provides an opportunity to investigate system requirements and unconventional interface paradigms for this unique vehicle. A virtual environment architecture and design based on support for a rapid prototyping development process, separation of concerns, and user interface development is presented. The rapid prototyping process allowed management of changing requirements via an evolutionary approach to implementation. Separation of the activities performed by the virtual environment into classes enabled high performance through computational distribution, prevented modifications from rippling through the system and impeding development, and promoted reuse of computation and geometric models. A technique was developed to reduce the flimmer induced by the large spatial extent of the virtual environment. The architecture succeeded in providing a flexible framework for the AFIT Virtual Spaceplane. The Virtual Spaceplane is a large-scale virtual environment within which an immersed user commands a military spaceplane through atmospheric and orbital regimes to complete several simulated missions via an unconventional virtual interface

The Virtual Spaceplane: Integrating Multiple Motion Models and Hypertext in a Virtual Environment

The Air Force is currently investigating the possibility of developing a manned vehicle capable of operating in space. This Military Spaceplane (MSP) will be capable of ascent to low-earth orbit and maneuvering while in orbit. The goal of this research involved creating the Virtual Spaceplane (VSP), a virtual environment (VE) simulator for the MSP. This thesis examines two ideas significant to virtual environments and cockpit design: multiple motion models and hypertext in a VE. Movement in a VE has traditionally been modeled using a single motion model. Little work has been done to allow a change of the motion model used during the simulation. This thesis suggests partitioning simulation entities into two sections: the geometry model and the propagation model. This approach is demonstrated in the VSP using multiple propagation models as it transitions from runway to orbit. This thesis also examines the use of hypertext within a VE. Hypertext has been shown useful for readers to quickly locate information. This thesis will discuss the integration of a hypertext interface into the VSP. The hypertext interface provides checklists, systems status, and consumables status. Hypertext provides the spaceplane pilot with an effective means of referencing large amounts of data

The Spaceplane Equation

Revenue earning space missions for deployment of space solar power satellites are economically competitive only when launch costs are in the region of $100-200 / kg in orbit. Nearly one half the capital cost of a solar power station is attributed to space transportation. To meet the objective of safe, affordable space transportation, an abundance of reusable space vehicle design concepts and programs emerged world-over, from 1985 to the present day. All these have been either abandoned or sub-optimally supported. Their designs emerged by the application of the ideal rocket equation derived in 1903 by Konstantin Tsiolkovsky. It had served as the scientific foundation for the design of multi-stage space rockets and ballistic missiles throughout the 20th century. The rocket equation emerged from a simple systems concept: the expendable space rocket that carries all the oxygen needed from earth for propulsion into space with low fuel efficiency rocket engines. New fully reusable space vehicle concepts use the earth\u27s atmosphere to enhance fuel efficiency and reduce/avoid carrying oxygen on board from earth to orbit. Their shape and aerodynamics call for adopting aircraft design practices. The classical rocket equation is unable to provide a satisfying and adequate theoretical framework to guide design of more complex systems concepts. A modification of the Tsiolkovsky rocket equation is developed here that introduces a mass ratio multiplier factor, which enables a better understanding of spaceplanes. The Spaceplane Equation shows how mass ratios obtainable only by 2-and 3-stage rockets can be realized in a single stage. Novel spaceplane design and technology domains emerge from parametric mapping using the Spaceplane Equation that could synergize more effective design and development of space transportation systems for space solar power missions

Geopolitics of near-space: increasing antional power through spaceplane eployment

With the delimitation of airspace and outer space being a continuous issue, various arguments intend to analyze the viewpoint of the geopolitics of near-space being considered neither as part of Astropolitik, nor the geopolitics of airspace. Consequently, a comparative methodology in regards to the multidimensional objectives of geopolitics is followed: (1) evolving a theoretical military basis of spaceplane deployment; (2) examining the natural background of the geopolitics of near-space; (3) constructing the "history-future" relation of the geopolitics of near-space; and (4) analyzing the increasing of America's national power through spaceplane deployment. Principle results obtained from the theoretical comparative methodology consequently determine the fundamental establishment of the geopolitics of near-space

The Student Aerospace Challenge: a european multidisciplinary contest and tertiary educational programme

Inspired by the first successful tests of a private manned spaceplane in 2004, the Student Aerospace Challenge was created in 2006 by the European Astronaut Club and its partners - Dassault Aviation, the European Space Agency, the International Astronautical Federation, Safran and Thales at the time - to allow European university students to explore some aspects of manned suborbital vehicles. Until 2020, the Challenge focused on a local reusable vehicle reaching Mach 3.5 and an altitude of 100 km. Since the 15th edition, to better respond to the evolution of the sector, a second vehicle is proposed: a hypersonic vehicle dedicated to point-to-point transportation taking, for example, less than two hours to travel from Barcelona to Tokyo. Each year, the Steering Committee defines several work packages corresponding to a large variety of study domains realistically related to this type of innovative vehicles like aerodynamic and flight control, structure, reusable propulsion, airworthiness, promotion, market analysis, legal frame & medicine. The introduction of a second vehicle having a quite different mission led the Committee to introduce dedicated topics. In addition, for the current edition, a new work package was proposed to cover potential applications of suborbital flights other than carrying passengers. In function of their background and interest, European University students have the opportunity to work, during several months, on a topic related to one of the work packages and to explore new solutions. Proposed projects should be technically realistic, economically viable and environmentally friendly. Reports and posters issued by student teams are evaluated by the Steering Committee some weeks before the “Suborbital Day”, a dedicated event organised like a mini-symposium, usually on-site where students present orally their projects and meet representatives of the different partners. The best-quoted projects are rewarded with prizes, among them, the ESA Grand Prize offering the winner team the unique opportunity to present their project in an appropriate European space-related event. To date, 216 teams and 998 University students coming from all over Europe already took part in the Student Aerospace Challenge, a motivating and ambitious multidisciplinary educational programme. Their participation allowed them to complement their knowledge, learn new skills and enlarge their network in the space secto

A space odyssey

Space Tourism: opportunities and challenges of an emerging industr

The Reality of Functionally Graded Material Products

Rapid Manufacturing utilizes the application of different materials in parts by stacking a sequence of layers. Based on the requirements of the part, mixtures of materials, so-called Functionally Graded Materials, can be used to compose the product functionality. This process depends completely on the availability of CAD information of the part geometry. Unfortunately, commercially available CAD-systems do not allow the design of graded material structures. TNO developed a computer tool which enables the user to specify Functionally Graded Materials. The system is based on a new approach to define the material composition at any point in the solid.Mechanical Engineerin

Comparative analysis of new configurations of aircraft aimed at competitiveness, environmental compatibility and safety

This Ph.D. Thesis aims at suggesting a proper integrated and multidisciplinary design methodology to improve the current conceptual and preliminary design phases of breakthrough innovative aerospace products. The methodology, based on a Systems Engineering approach, is presented together with an envisaged toolchain, consisting of both commercial and ad-hoc developed software, integrated in a Model-Based Systems Engineering perspective. In addition, for the sake of clarity and for validation purposes, a specific case study has been selected and developed all along the document. The reference case-study is inspired to a real pre-feasibility study in which the research group of Politecnico di Torino, which the author of this Thesis belongs to, has been involved. The project aims at developing a suborbital vehicle able to perform parabolic flights for both scientific and touristic purposes. This kind of initiatives paves the way for the future hypersonic vehicles, because it allows to crucial enabling technologies to be tested and validated in relevant environment but with lower performances’ requirements. The Thesis is articulated in seven Chapters with an introduction and conclusion sections and in each Chapter a balanced mix between theoretical investigation, mathematical model development, tool selection or development and application to the selected case study is guaranteed. This document starts reporting the major reasons why an innovative design methodology should be envisaged to deal with the increasing level of complexity in the aerospace domain. In particular, in the first Chapter, a brief overview of existing or underdevelopment initiatives related to hypersonic is reported, together with the description of the different types of mission in which the new hypersonic vehicles will be exploited. Moreover, the major issues related to the infrastructures required to operate these transportation systems are summarized. As far as operations are concerned, a short section makes the readers aware of the current under-development regulatory framework. Then, the integrated multidisciplinary design methodology is presented starting from the very high level analyses up to the sizing of the different components of the transportation system. All along the document, crucial role is played by requirements, whose management can allow a complete traceability of the different design characteristics during the overall product life-cycle. Furthermore, proper algorithms allowing to move from purely qualitative to quantitative trade-offs, are presented, with a noticeable advantage in terms of traceability and reproducibility. Eventually, further improvements of both the tool-chain and the reference case studies are envisaged for future developments

A Comparison Of Different Technologies For Thrust Vectoring In A Linear Aerospike

The aerospike nozzle represents an interesting technology for Single-Stage-To-Orbit vehicles because of its self-adapting capability. It is possible to get thrust vectoring capabilities in different ways. A straightforward solution consists in applying differential throttling to multiple combustion chambers which feed the nozzle. An alternative technology, which can be used in the presence of a common combustion chamber, is represented by fluidic thrust vectoring which requires the injection of a secondary flow from a slot on the wall. In this work, the flow field in a linear aerospike nozzle is numerically investigated by means of RANS simulations and both differential throttling and shock vectoring are studied. A parametric study is performed to evaluate the potential of the two technologies