Space Transportation: A Systems Approach to Analysis and Design

Hammond, Walter E.

doi:10.2514/4.862380

Cited by 33 publications

(13 citation statements)

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“…Next, an independent review team will validate that the CRM Figure 6. The Space Systems Working Group (SSWG)-CubeSat reference model (based on [32,33]).…”

Section: Engineering Methodology For University-class Cubesatsmentioning

confidence: 99%

Engineering Methodology for Student-Driven CubeSats

Alanazi

Straub

2019

Aerospace

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CubeSats are widely used by universities and research institutions all over the world. Their popularity is generally attributed to the use of low-cost components, free student labor and simple design. They have been shown to encourage Science, Technology, Engineering and Math (STEM) students to become involved in designing, implementing and testing a real functioning spacecraft system. Projects like this encourage students from different disciplines to team up to design and build CubeSats, providing interdisciplinary work experience. Participating students vary in their expertise in developing such systems. Some will work on the project for years while others are not willing to spend two or three consecutive semesters developing a CubeSat project. Despite their simplicity in design and low cost, CubeSats are considered great engineering systems for exploring space. Nevertheless, a large number of CubeSat projects fail due to having an unclear mission, ambiguous system requirements and a lack of documentation. Students need to have a clear vision of how to build a real CubeSat system that can be launched and that can function in space. Thus, this paper proposes engineering methodologies and tools to help students develop CubeSat systems. These tools can help students with planning, collecting, eliciting and documenting the requirements in a well-defined manner. This paper focuses on student-driven CubeSat projects designed by students and faculty members. Additionally, data is presented in this paper to identify the challenges and needs of CubeSat developers. Plans for future work are also discussed.

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“…Next, an independent review team will validate that the CRM Figure 6. The Space Systems Working Group (SSWG)-CubeSat reference model (based on [32,33]).…”

Section: Engineering Methodology For University-class Cubesatsmentioning

confidence: 99%

Engineering Methodology for Student-Driven CubeSats

Alanazi

Straub

2019

Aerospace

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“…Such spaceplanes could be used as space-taxi to transport people and materials to and from orbiting space stations (space tourism) and as emergency escape vehicle. A comprehensive analysis of space transportation systems including their design and cost analysis is given in Hammond (1999). The author also briefly discusses future NASA's fully reusable RBCC SSTO vehicles as a means to significantly reduce launch costs and provides figure (an overly optimistic in our view) of $300-$600 per pound (in late 1990's US$).…”

Section: Cost Analysismentioning

confidence: 99%

High-elevation equatorial catapult-launched RBCC SSTO spaceplane for economic manned access to LEO

Daidzic¹

2016

IJAAA

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“…The affordability of expendable launch vehicles is largely determined by the development and production costs of liquid rocket engines [1,2]. The major part of the development cost is spent on development test hardware subjected to hot-fire tests in order to sufficiently demonstrate design maturity/robustness and to qualify/ certify the liquid rocket engines for a successful flight operation [3].…”

Section: Nomenclaturementioning

confidence: 99%

Reliability as an Independent Variable Applied to Liquid Rocket Engine Hot Fire Test Plans

Strunz¹,

Herrmann²

2011

Journal of Propulsion and Power

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Manufacturers lack an adequate method to balance performance, reliability, and affordability. The reliability-asan-independent-variable methodology is the solution proposed by expressing quantitatively the reliability trade space as ranges of a number of hardware sets and a number of hot-fire tests necessary to develop and qualify/certify a liquid rocket engine against a stated reliability requirement. Therefore, reliability-as-an-independent-variable becomes one of the key decision parameters in early tradeoff studies for liquid rocket engines because the reliability trade space directly influences the performance requirements and, as a result, the affordability. The overall solution strategy of reliability-as-an-independent-variable is based on the Bayesian statistical framework using either the planned or actual number of hot-fire tests. The planned hot-fire test results may include test failures to simulate the typical design-fail-fix-test cycles present in liquid rocket engine development programs in order to provide the schedule and cost risk impacts for early tradeoff studies. The reliability-as-an-independent-variable methodology is exemplarily applied to the actual hot-fire test history of the F-1, the space shuttle main engine, and the RS-68 liquid rocket engine, showing adequate agreement between computed results and actual flight engine reliability.Nomenclature Beta = Beta probability density function Bi = Binomial probability density function C = level of confidence (credibility bound) c = number of cycles CTD = cumulated test duration, s F X = cumulative density function HW = number of hardware L = likelihood function n = number of trials, i.e., hot-fire tests p = probability of success q = failure fraction q ind = candidate probability density function R = reliability r = number of failures t = hardware life, s tp = hot-fire test proportion T 50 = median lifetime, s w = weighting factor x = number of successes, i.e., hot-fire tests = shape parameter 1 , 2 = weighting factors = shape parameter = median regression coefficients = integration domain = parameters to be estimated = acceptance rate = Gamma function = parameter of Poisson probability mass function = probability of success of a functional node = posterior probability 0 = prior probability = standard deviation

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Space Transportation: A Systems Approach to Analysis and Design

Cited by 33 publications

References 0 publications

Engineering Methodology for Student-Driven CubeSats

Engineering Methodology for Student-Driven CubeSats

High-elevation equatorial catapult-launched RBCC SSTO spaceplane for economic manned access to LEO

Reliability as an Independent Variable Applied to Liquid Rocket Engine Hot Fire Test Plans

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