Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722013974
Category :
Languages : en
Pages : 40
Book Description
The class of hypersonic vehicle configurations with single stage-to-orbit (SSTO) capability reflect highly integrated airframe and propulsion systems. These designs are also known to exhibit a large degree of interaction between the airframe and engine dynamics. Consequently, even simplified hypersonic models are characterized by tightly coupled nonlinear equations of motion. In addition, hypersonic SSTO vehicles present a major system design challenge; the vehicle's overall mission performance is a function of its subsystem efficiencies including structural, aerodynamic, propulsive, and operational. Further, all subsystem efficiencies are interrelated, hence, independent optimization of the subsystems is not likely to lead to an optimum design. Thus, it is desired to know the effect of various subsystem efficiencies on overall mission performance. For the purposes of this analysis, mission performance will be measured in terms of the payload weight inserted into orbit. In this report, a trajectory optimization problem is formulated for a generic hypersonic lifting body for a specified orbit-injection mission. A solution method is outlined, and results are detailed for the generic vehicle, referred to as the baseline model. After evaluating the performance of the baseline model, a sensitivity study is presented to determine the effect of various subsystem efficiencies on mission performance. This consists of performing a parametric analysis of the basic design parameters, generating a matrix of configurations, and determining the mission performance of each configuration. Also, the performance loss due to constraining the total head load experienced by the vehicle is evaluated. The key results from this analysis include the formulation of the sizing problem for this vehicle class using trajectory optimization, characteristics of the optimal trajectories, and the subsystem design sensitivities. Lovell, T. Alan and Schmidt, D. K. Unspecified Center NAG1-1540...
A Parametric Sensitivity Study for Single-Stage-To-Orbit Hypersonic Vehicles Using Trajectory Optimization
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722013974
Category :
Languages : en
Pages : 40
Book Description
The class of hypersonic vehicle configurations with single stage-to-orbit (SSTO) capability reflect highly integrated airframe and propulsion systems. These designs are also known to exhibit a large degree of interaction between the airframe and engine dynamics. Consequently, even simplified hypersonic models are characterized by tightly coupled nonlinear equations of motion. In addition, hypersonic SSTO vehicles present a major system design challenge; the vehicle's overall mission performance is a function of its subsystem efficiencies including structural, aerodynamic, propulsive, and operational. Further, all subsystem efficiencies are interrelated, hence, independent optimization of the subsystems is not likely to lead to an optimum design. Thus, it is desired to know the effect of various subsystem efficiencies on overall mission performance. For the purposes of this analysis, mission performance will be measured in terms of the payload weight inserted into orbit. In this report, a trajectory optimization problem is formulated for a generic hypersonic lifting body for a specified orbit-injection mission. A solution method is outlined, and results are detailed for the generic vehicle, referred to as the baseline model. After evaluating the performance of the baseline model, a sensitivity study is presented to determine the effect of various subsystem efficiencies on mission performance. This consists of performing a parametric analysis of the basic design parameters, generating a matrix of configurations, and determining the mission performance of each configuration. Also, the performance loss due to constraining the total head load experienced by the vehicle is evaluated. The key results from this analysis include the formulation of the sizing problem for this vehicle class using trajectory optimization, characteristics of the optimal trajectories, and the subsystem design sensitivities. Lovell, T. Alan and Schmidt, D. K. Unspecified Center NAG1-1540...
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722013974
Category :
Languages : en
Pages : 40
Book Description
The class of hypersonic vehicle configurations with single stage-to-orbit (SSTO) capability reflect highly integrated airframe and propulsion systems. These designs are also known to exhibit a large degree of interaction between the airframe and engine dynamics. Consequently, even simplified hypersonic models are characterized by tightly coupled nonlinear equations of motion. In addition, hypersonic SSTO vehicles present a major system design challenge; the vehicle's overall mission performance is a function of its subsystem efficiencies including structural, aerodynamic, propulsive, and operational. Further, all subsystem efficiencies are interrelated, hence, independent optimization of the subsystems is not likely to lead to an optimum design. Thus, it is desired to know the effect of various subsystem efficiencies on overall mission performance. For the purposes of this analysis, mission performance will be measured in terms of the payload weight inserted into orbit. In this report, a trajectory optimization problem is formulated for a generic hypersonic lifting body for a specified orbit-injection mission. A solution method is outlined, and results are detailed for the generic vehicle, referred to as the baseline model. After evaluating the performance of the baseline model, a sensitivity study is presented to determine the effect of various subsystem efficiencies on mission performance. This consists of performing a parametric analysis of the basic design parameters, generating a matrix of configurations, and determining the mission performance of each configuration. Also, the performance loss due to constraining the total head load experienced by the vehicle is evaluated. The key results from this analysis include the formulation of the sizing problem for this vehicle class using trajectory optimization, characteristics of the optimal trajectories, and the subsystem design sensitivities. Lovell, T. Alan and Schmidt, D. K. Unspecified Center NAG1-1540...
Using Trajectory Optimization to Determine Design Sensitivities for Single-stage-orbit Hypersonic Vehicles
Author: David K. Schmidt
Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Scientific and Technical Aerospace Reports
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1028
Book Description
Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1028
Book Description
Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Monthly Catalog of United States Government Publications
Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1450
Book Description
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1450
Book Description
Configuration Development Study of the Osu 1 Hypersonic Research Vehicle
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722976842
Category :
Languages : en
Pages : 156
Book Description
In an effort to insure the future development of hypersonic cruise aircraft, the possible vehicle configurations were examined to develop a single-stage-to-orbit hypersonic research vehicle (HRV). Based on the needs of hypersonic research and development, the mission goals and requirements are determined. A body type is chosen. Three modes of propulsion and two liquid rocket fuels are compared, followed by the optimization of the body configuration through aerodynamic, weight, and trajectory studies. A cost analysis is included. Stein, Matthew D. and Frankhauser, Chris and Zee, Warner and Kosanchick, Melvin, III and Nelson, Nick and Hunt, William Unspecified Center AIRCRAFT CONFIGURATIONS; HYDROCARBON FUELS; HYDROGEN FUELS; HYPERSONIC VEHICLES; RESEARCH VEHICLES; SINGLE STAGE TO ORBIT VEHICLES; THERMAL PROTECTION; COST ANALYSIS; HYPERSONICS; LIQUID PROPELLANT ROCKET ENGINES; MISSION PLANNING; PROPULSION SYSTEM CONFIGURATIONS; TRAJECTORIES...
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722976842
Category :
Languages : en
Pages : 156
Book Description
In an effort to insure the future development of hypersonic cruise aircraft, the possible vehicle configurations were examined to develop a single-stage-to-orbit hypersonic research vehicle (HRV). Based on the needs of hypersonic research and development, the mission goals and requirements are determined. A body type is chosen. Three modes of propulsion and two liquid rocket fuels are compared, followed by the optimization of the body configuration through aerodynamic, weight, and trajectory studies. A cost analysis is included. Stein, Matthew D. and Frankhauser, Chris and Zee, Warner and Kosanchick, Melvin, III and Nelson, Nick and Hunt, William Unspecified Center AIRCRAFT CONFIGURATIONS; HYDROCARBON FUELS; HYDROGEN FUELS; HYPERSONIC VEHICLES; RESEARCH VEHICLES; SINGLE STAGE TO ORBIT VEHICLES; THERMAL PROTECTION; COST ANALYSIS; HYPERSONICS; LIQUID PROPELLANT ROCKET ENGINES; MISSION PLANNING; PROPULSION SYSTEM CONFIGURATIONS; TRAJECTORIES...
Launch Vehicle Error Sensitivity Study
Author: Richard C. Rosenbaum
Publisher:
ISBN:
Category : Launch vehicles (Astronautics)
Languages : en
Pages : 60
Book Description
Publisher:
ISBN:
Category : Launch vehicles (Astronautics)
Languages : en
Pages : 60
Book Description
Monthly Catalogue, United States Public Documents
Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1484
Book Description
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1484
Book Description
Government reports annual index
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 1686
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 1686
Book Description
Aeronautical Enginnering: A Cumulative Index to a Continuing Bibliography (supplement 312)
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 392
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 392
Book Description
Applied Mechanics Reviews
Author:
Publisher:
ISBN:
Category : Mechanics, Applied
Languages : en
Pages : 338
Book Description
Publisher:
ISBN:
Category : Mechanics, Applied
Languages : en
Pages : 338
Book Description