Optimization of entry-vehicle shapes during conceptual design

Dirkx, Dominic; Mooij, Erwin

doi:10.1016/j.actaastro.2013.08.006

Cited by 32 publications

(10 citation statements)

References 14 publications

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“…Tudat is applicable to a broad range of topics, and has been used for, among others, simulations of solar system dynamics (Dirkx et al, 2018), interplanetary trajectory design (Musegaas, 2013), planetary system dynamics (Kumar et al, 2015;Dirkx et al, 2016), space debris impact predictions (Ronse and Mooij, 2014) and atmospheric re-entry (Dirkx and Mooij, 2014).…”

Section: Appendix a Relations Between Rotation Representationsmentioning

confidence: 99%

Propagation and estimation of the dynamical behaviour of gravitationally interacting rigid bodies

Dirkx

Mooij

Root

2019

Astrophys Space Sci

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Next-generation planetary tracking methods, such as interplanetary laser ranging (ILR) and same-beam interferometry (SBI) promise an orders-of-magnitude increase in the accuracy of measurements of solar system dynamics. This requires a reconsideration of modelling strategies for the translational and rotational dynamics of natural bodies, to ensure that model errors are well below the measurement uncertainties.The influence of the gravitational interaction of the full mass distributions of celestial bodies, the so-called figure-figure effects, will need to be included for selected future missions. The mathematical formulation of this problem to arbitrary degree is often provided in an elegant and compact manner that is not trivially relatable to the formulation used in space geodesy and ephemeris generation. This complicates the robust implementation of such a model in operational software packages. We formulate the problem in a manner that is directly compatible with the implementation used in typical dynamical modelling codes: in terms of spherical harmonic coefficients and Legendre polynomials. An analytical formulation for the associated variational equations for both translational and rotational motion is derived.We apply our methodology to both Phobos and the KW4 binary asteroid system, to analyze the influence of figure-figure effects during estimation from next-generation tracking data. For the case of Phobos, omitting these effects during estimation results in relative errors of 0.42% and 0.065% for theC 20 andC 22 spherical harmonic gravity field coefficients, respectively. These values are below current uncertainties, but orders of magnitude larger than those obtained from past simulations for accurate tracking of a future Phobos lander, showing the need to apply the methodology outlined in this manuscript for selected future missions.

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Section: Appendix a Relations Between Rotation Representationsmentioning

confidence: 99%

Propagation and estimation of the dynamical behaviour of gravitationally interacting rigid bodies

Dirkx

Mooij

Root

2019

Astrophys Space Sci

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“…The above circumstances may conflict with the adoption of a fully reusable TPS, eventually restricting the choice of insulating materials and penalizing the total mass [5]. However, antithetical requirements between room for the payload, weight, and vehicle operability demand a trade-off between vehicle shape and TPS sizing.…”

Section: Introductionmentioning

confidence: 99%

“…However, antithetical requirements between room for the payload, weight, and vehicle operability demand a trade-off between vehicle shape and TPS sizing. In preliminary design practice, thousands of design configurations are typically evaluated by an optimization algorithm to find the best fit [5][6][7][8][9][10]. As a consequence, a preliminary appraisal of vehicle performances is commonly performed using high-efficiency, low-order fidelity methods that give support to a multidisci-plinary analysis performed with a computational effort which fit the typical timeline of the conceptual design phase [11].…”

Section: Introductionmentioning

confidence: 99%

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Thermal Protection System Design of a Reusable Launch Vehicle Using Integral Soft Objects

Aprovitola

Iuspa

Viviani

2019

International Journal of Aerospace Engineering

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In the present paper, a modelling procedure of the thermal protection system designed for a conceptual Reusable Launch Vehicle is presented. A special parametric model, featuring a scalar field irradiated by a set of bidimensional soft objects, is developed and used to assign an almost arbitrary distribution of insulating materials over the vehicle surface. The model fully exploits the autoblending capability of soft objects and allows a rational distribution of thermal coating materials using a limited number of parameters. Applications to different conceptual vehicle configurations of an assigned thickness map, and material layout show the flexibility of the model. The model is finally integrated in the framework of a multidisciplinary analysis to perform a trajectory-based TPS sizing, subjected to fixed thermal constraints.

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“…This requirement may conflict with the adoption of a fully reusable TPS, either limiting the choice of material category or penalizing the total mass. In preliminary design practice, thousands of design configurations are typically evaluated by an optimization algorithm to find the best fit [5][6][7][8][9][10][11]. Therefore, a preliminary appraisal of vehicle performances is commonly performed using high-efficiency, low-order fidelity methods that give a support to a multidisciplinary analysis performed with a computational effort which fit the typical timeline of the conceptual design phase [11].…”

Section: Introductionmentioning

confidence: 99%

Parametric Integral Soft Objects-based Procedure for Thermal Protection System Modeling of Reusable Launch Vehicle

Aprovitola¹,

Iuspa²,

Viviani³

2019

Hypersonic Vehicles - Past, Present and Future Developments

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The present paper deals with a modeling procedure of a thermal protection system (TPS) designed for a conceptual reusable launch vehicle (RLV). A novel parametric model based on a scalar field created by a set of soft object primitives is used to assign an almost arbitrary seamless distribution of insulating materials over the vehicle surface. Macroaggregates of soft objects are created using suitable geometric supports allowing a distribution of coating materials using a limited number of parameters. Applications to different conceptual vehicle configurations of an assigned thickness map and materials layout show the flexibility of the model.

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Optimization of entry-vehicle shapes during conceptual design

Cited by 32 publications

References 14 publications

Propagation and estimation of the dynamical behaviour of gravitationally interacting rigid bodies

Propagation and estimation of the dynamical behaviour of gravitationally interacting rigid bodies

Thermal Protection System Design of a Reusable Launch Vehicle Using Integral Soft Objects

Parametric Integral Soft Objects-based Procedure for Thermal Protection System Modeling of Reusable Launch Vehicle

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