MISSILE DATCOM User's Manual - 2011 Revision

Rosema, Christopher; Doyle, Joshua; Auman, Lamar; Underwood, M. L.; Blake, William

doi:10.21236/ada548461

Cited by 33 publications

(11 citation statements)

References 0 publications

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“…In previous studies an aerodynamic reference database for the SpaceLiner has been defined which determines the longitudinal aerodynamic coefficients for multiple flight conditions based on CFD calculations and empirical methods [13]. For the aerodynamic model of the SpaceLiner this dataset has been complemented by estimations of lateral and dynamic derivatives of the aerodynamic coefficients [14]. All coefficients and derivatives have been considered with respect to the Mach regime and the vehicle's angle of attack as it is visualized in FIG 9 for the lift-to-drag ratio.…”

Section: Aerodynamics Modelmentioning

confidence: 99%

Effects of the rotational vehicle dynamics on the ascent flight trajectory of the SpaceLiner concept

Krummen

Sippel

2018

CEAS Space J

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During the preliminary design of space transportation systems the vehicle dynamics are commonly reduced to a pointmass model for definition of the flight trajectory. While this approach effectively reduces the number of model parameters in the design process, it neglects the rotational dynamics of the vessel completely. Since the rotational degrees of freedom (DOF) have a significant influence on the vehicle's controllability, a sole analysis of the translational dynamics is insufficient to assess the general feasibility of the concept. This study investigates the ascent flight trajectory of the SpaceLiner vehicle, a concept for a hypersonic suborbital space plane, based on a newly developed 6-DOF flight dynamics simulation to determine the influence of the rotational dynamics on the vehicle's controllability and performance. The first part of this paper will focus on the developed vehicle model which features a transient inertia model as well as an algorithmic-designed flight control system. The second part will present several simulations of nominal and off-nominal ascent trajectories. Based on the results it will be shown that SpaceLiner's thrust vector control system is sufficiently dimensioned for the investigated mission scenarios, while the vehicle performance is only slightly influenced by the rotational dynamics.

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Section: Aerodynamics Modelmentioning

confidence: 99%

Effects of the rotational vehicle dynamics on the ascent flight trajectory of the SpaceLiner concept

Krummen

Sippel

2018

CEAS Space J

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“…The second path constraint is finally Γ( ) ≤ Γ , with no need to specify the absolute value because Γ is defined positive by Eq. (8).…”

Section: B Second Phase: First Burnmentioning

confidence: 99%

Trajectory Optimization for a Mars Ascent Vehicle

Benito

Johnson

2016

AIAA/AAS Astrodynamics Specialist Conference

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The trajectory design, propellant loading, and staging of a Mars Ascent Vehicle (MAV) can be accomplished via the solution of the associated optimal control problem under given vehicle, mission, path and control constraints. This paper presents the implementation of this optimization using Gauss Pseudospectral OPtimization Software (GPOPS-II) in combination with a Sparse Nonlinear OPTimizer (SNOPT) as the nonlinear programing solver. The solution obtained is an input to the propulsion, Guidance Navigation and Control, mechanical design, aerodynamic and thermal analysis teams, which use it to size systems, tune algorithms and update models. Optimal solutions are obtained for a variety of MAV architectures, which can be grouped in categories according to the number of stages (one or two) and the propulsion technology (solid, liquid or hybrid). A sensitivity analysis of variables of interest, like launch conditions, target orbit, stage and payload mass is presented.

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“…We obtained aerodynamic data with Missile DATCOM, a conventional missile aerodynamic design tool [5]. Motor off and on flight conditions were simulated over a wide range of dynamic pressures ranging on the order of kilo to mega Pascals.…”

Section: Missile Modelmentioning

confidence: 99%

Robust and adaptive control of a rocket boosted missile

Dickinson

Nivison

Hart

et al. 2015

2015 American Control Conference (ACC)

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This paper is an exposition on the design of robust observer-based adaptive autopilots for aerospace systems. Using a rocket boosted missile as an example, we will discuss systematic design principles to meet closed-loop autopilot robustness and performance criteria. The controller consists of decoupled lateral and longitudinal linear gain scheduled optimal baseline designs with servomechanism acceleration tracking and observer-based adaptive augmentation. We will demonstrate improved robustness with observer-based adaption to various uncertainties including significant discrepancies in aerodynamic coefficients, center of gravity shifts, and actuator failures. These results support the practicality of observerbased adaptive output feedback laws for the control design of uncertain aerodynamic systems.

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MISSILE DATCOM User's Manual - 2011 Revision

Cited by 33 publications

References 0 publications

Effects of the rotational vehicle dynamics on the ascent flight trajectory of the SpaceLiner concept

Effects of the rotational vehicle dynamics on the ascent flight trajectory of the SpaceLiner concept

Trajectory Optimization for a Mars Ascent Vehicle

Robust and adaptive control of a rocket boosted missile

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