Parameters adopted in the modeling of TPS configurations of ** Figures 7** and

**.**8

Open access peer-reviewed chapter

Submitted: 22 February 2019 Reviewed: 19 April 2019 Published: 15 May 2019

DOI: 10.5772/intechopen.85603

From the Edited Volume

Edited by Giuseppe Pezzella and Antonio Viviani

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.

- reusable launch vehicles
- reentry aerodynamics
- integral soft objects
- hypersonic flow
- thermal protection system

Currently a number of projects related to the development of reusable launch vehicles (RLV) both single-stage-to-orbit (SSTO) and two-stage-to-orbit (TSTO) are ongoing. This trend relates to objectives of future space missions that demand to improve vehicle operability, reducing at the same time flight costs of putting payload into orbit. Several preliminary studies/experiments related to this design scenario have been carried on. The European Space Agency developed two demonstrators, the EXPERT (European eXPErimental Re-entry Test-bed) program and the Intermediate eXperimental Vehicle (IXV), which performed an atmospheric lifting reentry from orbital speed [1]. Besides, an unmanned lifting body developed by Boeing X-37B has been put in orbit by an Atlas-5 rocket and performed a successful lifting-guided reentry. Furthermore, a growing demand for space tourism has emerged also in recent years [2]; therefore, a great deal of research effort has been put to design RLV as blended wing bodies also allowing a conventional and more comfortable landing on runways. The main requirements currently considered for RLV design are (i) to perform very low-g (nearly 1.5 g) reentry; (ii) to adopt a lightweight (passive), fully reusable thermal protection system (TPS) to withstand several flights without any replacement; and (iii) to provide vehicle autonomy to land at a predefined location for crew rescue [3, 4]. In order to fulfill all those requirements, the duration of reentry flight increases and consequently the integrated heat load absorbed by the structure [3].

The above consideration incidentally demands a trade-off among several nonlinear conflicting design objectives, also satisfying a number of constraint functions. As an example, the design of the TPS of an RLV performing a suborbital lifting reentry requires a mandatory compromise between the maximum allowed peak heating and the integrated heat load. 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]. In current studies, TPS sizing is performed using several simplified assumptions, carrying out a one-dimensional heat conduction analysis with panel thickness modeled using stackups of different materials [12].

The aerothermal environment is a basic design criterion for either TPS sizing or choice of materials [13, 14]. Several works dealing with TPS sizing have been published in literature. Lobbia [8] determined the sizing of a TPS in the framework of a multidisciplinary optimization. Material densities and maximum reuse temperature were computed. TPS mass was estimated assuming the category of materials used for the space shuttle and thickness distribution assigned on a review of HL-20 materials for each component. Trajectory-based TPS sizing has been proposed by Olynick [13] for a winged vehicle concept. The heating peak was determined considering an X-33 trajectory, discretized in a number of fixed waypoints. The resulting aerothermal database was used as an input for a one-dimensional conduction analysis, and several one-dimensional stackups of different materials representative of TPS were consequently sized. Bradford et al. [14] developed an engineering software tool for aero-heating analysis and TPS sizing. The tool is applicable in the conceptual design phase for reusable, non-ablative TPS. The thermal model was based on a one-dimensional analysis, and TPS was modeled considering a stackup of ten different material layers. Mazzaracchio [15] proposed a method to perform the sizing of a TPS depending on the locations of ablative and reusable zone on a TPS considering the coupling between trajectory and heat shield. Multidisciplinary analysis, integrating a procedural NURBS-based shape representation, is adopted for a preliminary design [3]. NURBS parameterization allows a simple control over the aerodynamic shape using a limited number of sensitive design parameters acting as geometrical modifiers.

However, derivation of a unique parameterization to describe the overall changes of geometry resulting from a shape optimization is not always possible, and several surfaces are used to parameterize different parts of the geometry. Implicit surfaces are a powerful and alternative tool for creating shapes due to their smooth blending properties enabling creation of arbitrary shape. In the present work, a soft object-derived representation for TPS thickness and material attribution is introduced. According to the legacy formulation of this technique, originally developed in computer graphics for the rendering of complex organic shapes [16], three-dimensional object surfaces are (implicitly) obtained by defining a set of source points (or even more complex varieties) irradiating a potential field that is subsequently tracked according to an assigned isosurface. Following a quite different paradigm developed in [17], the full potential field irradiated by a set of by-dimensional soft objects is congruently mapped on a discretized RLV shape. The methodology is able to create arbitrary TPS distributions seamlessly increasing the thickness where critical heat loads are experienced and dropping out elsewhere. A similar, slightly modified procedure is also applied to create an arbitrary binary map of different TPS materials that may be operated independently (or synchronized) with the thickness distribution. The present formulation is formalized in the framework of a parametric model which exploits simple variations of parameters to perform the soft object mapping over discretized surface. Applications of the developed procedure to different arbitrary vehicle shape show the flexibility of the method.

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## 2. Soft objects definition

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### 2.1 Two-dimensional integral soft object for TPS modeling

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Soft objects constitute a modeling technique which typically represents a domain using a scalar field, namely, a field function F, defined over a three-dimensional space. An implicit surface S defined as

that is, an isosurface S of the field function F specified by the threshold T represents an object instance using a raster conversion algorithm. Soft object modeling overcomes the drawback given by the parametric surfaces; that is, they automatically allow a self-blending between different primitives. Therefore, complex shapes can be modeled defining n ≥ 1 potential field f_{i}, with origin in points _{i}, and the blending among them is formally accounted by the algebraic summation of their potential fields f_{i} [18]:

A commonly adopted notation

composes the distance metric d_{i} (which determines the shape of the objects associated to the key point _{i}), with the field function f_{i}, being ** x** the point of space in which the function is evaluated:

A more powerful representation used in soft object modeling is based on morphological skeleton that synthesizes the morphological properties of a given domain. A skeleton S_{k} can be defined as a basic geometric entity (such as points, segments, and plain closed domains) around which more complex shapes can be created once the distance function is provided. The simplest soft object was introduced by Blinn that originally proposed the “blobby molecule,” an isotropically decaying Gaussian function modulated in strength and radius [16]:

where d is the Euclidean distance (k = 2 in Eq. (4)). Blobby molecule is a soft object defined around a point skeleton, and its field function has an infinite support. This aspect affects the computational effort in a practical implementation, because it has to be evaluated in all points of the space. However, in literature, several finite support potential functions have been proposed for different modeling purposes. Wyvill et al. [19] developed the following field function:

Blanc [18] proposed another field function introducing an internal hardness factor p, which tunes the blending between two different blobs. A higher value of p makes a blob stiffer in the blending, while a low hardness factor generates larger rounded shapes [17]:

The field function * f* used in the present work has a finite support and assumes normalized values in the range between 0 and 1 [18]:

Two-dimensional soft objects preserve self-blending property. Figure 1a, b shows the support and the strength field, respectively, created superposing n = 6 discrete point source blobs with radius r, with origins in key point x_{i}. If δe < 2r, two or more blobs superposes, and the strength of the potential field is obtained summing up the strengths of each blob (see Figure 1b). A set of n blobs represents a too complex entity if used to model a parametric variation of shape (a single blob is characterized by five independent parameters, i.e., scalar coordinates of centers, strength, and radius). Therefore, blobs can be conveniently and easily arranged in macroaggregates with key points placed on a geometric segment (straight or curved) denoted from now on as “sticks.” The point source blobs emulates a segment skeleton with the distance function expressed by Eq. (4) (see Figure 1a). However, a simple algebraic summation of potential fields creates a stick support having “bulges.” Increasing the number of blobs, the shape of the support becomes more regular, but the strength of the field function diverges. The above drawback is overcome modifying the definition of potential field given by Eq. (2) with the relation:

Equation (9) where F0(P) = 0 expresses the global potential field F_{j}(P) irradiated by a set of j blobs at a generic point P of space placed at a distance d from the key points, as the max between the previous j − 1 potentials accounted by the assembly layer F_{j − 1}(P) and the current potential G_{j} over the plane disk of radius r:

Figure 2a, b shows the support and the strength field of a two-dimensional stick primitive obtained with n_{blob} = 6 and 20, respectively, computed with Eq. (8). By increasing the number of blob on a stick, the strength of F is still bounded to a maximum unit value. Figure 2c, d shows the same behavior for a tapered primitive having a linear variation of the blob radius along the axis of stick. Therefore, a seamlessly blending of blobs, with a bounded strength, is obtained adopting Eq. (9). The procedure proposed here relies on a similar idea to the one developed in [17] to generate self-stiffened structural panels. Specifically, rather than modeling an object tracking an iso-contour of its potential field, the full integral field generated by a set of blobs spatially arranged on a two-dimensional grid generates a smoothly varying field.

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## 3. RLV shape modeling

A generic shape of an RLV is represented by a grid formed by a quadrangular and/or by either degenerated triangular panel grid. Grid points are obtained using a proprietary procedure that authors fully detailed in [20, 21]. Without going into details of the shape model, we remark that the mesh arrangement over the RLV surface is obtained with no NURBS support surface: a three-dimensional parametric wireframe is created using cubic rational B-splines [22] and used to reconstruct computational surface grid. The control parameter allows a wide range of shape variations to handle different design objectives (thermal or dynamical) for a reentry mission. Grid topology is equivalent to a spherical surface with no singularities (open poles) and allows a mapping of the points in UV coordinates over an equivalent cylindrical surface. The above considerations ensure a topologically invariant shape.

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## 4. Soft object design of TPS

### 4.1 Rationale

The modeling procedure for the TPS is defined starting from the definition of a set of soft objects which are represented on the topological map associated with the current morphology of the object, as shown in Figure 3. Consequently, the supports of the sticks are adjusted according to the normalized dimensions relative to this map. The topological map is emulated introducing a two-dimensional grid (from now, denoted as B-grid) having the same topology tree than the vehicle open grid (number of points, panels, and connectivity) but unit size. A geometric mapping between the B-grid and the vehicle grid is established, and elements of B-grid are univocally mapped onto corresponding elements of the vehicle surface (see Figure 3). Therefore, each centroid of panels which belong to topological map has the same neighboring points either on the topological or morphological map. Several stick primitives are emulated on B-grid placing a number of n equally spaced isotropic blobs, with radius r and length l, respectively, in a normalized unit. Stick emulation is performed by overlapping n blobs using the special formulation reported in [17] that ensures a convergent envelope of the finite support and a limited value of the blob strength. An exemplificative spatial distribution of sticks on the B-grid is shown in Figure 3.

Position and orientation of each stick are determined by assigning coordinates of centers C_{i} and precession angles θ_{i}, respectively, with respect to a Cartesian frame of reference Oxz oriented as in Figure 3. Therefore, a generic distribution of sticks created on vehicle grid is equally mapped on the vehicle surface whatever is the morphological map considered. In the present case, gray-colored regions (1) denote points of the B-grid mapped on the windward side of RLV shape (see Figure 3), while white regions (2) relate to leeward regions of the vehicle. Regions of vehicle surface mainly subjected to heating peaks during the reentry maneuver are (i) nose, (ii) leading edge, and (iii) tail. The global potential field generated by the sticks onto the B-grid is adjusted in a suitable dimensional scale and subsequently mapped on the mesh panels of the vehicle surface grid to obtain an easy and powerful control of the thickness distribution. The proposed methodology is able to create virtually arbitrary TPS distributions and can be easily tuned up to locally increase the thickness where critical heat loads are expected and dropping out elsewhere. A similar, slightly modified procedure is also applied to create an arbitrary binary map distribution of different TPS materials that may be operated independently of the thickness distribution. Figure 4 shows an arbitrary distribution of stick primitives (not suitable for application purposes) created over the topological map.

The resulting potential field created by the superposition of sticks modulates y-coordinate of grid points as shown in Figure 4.

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## 5. Parametric model of thermal protection system

### 5.1 Thickness modeling

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### 5.2 Material modeling

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As demonstrative example, a parametric representation of TPS is obtained using a limited set of sticks primitive (n_{stick} = 5), oriented as shown in Figure 5. Skin sticks characterized by a large radius and limited strength are spread over the skin surface in longitudinal direction in order to provide a thickness graded baseline. A constant minimum thickness is superposed in all remaining points of B-grid, ensuring a nonzero value in any point of the grid. Furthermore, additional parametric sticks, specifically positioned and oriented to affect thickness in critical regions as nose, leading edge, and trailing edge, complete the support for TPS and create a rational distribution of insulating material suitable with a reentry mission. Parametric position of sticks and axis of orientation are defined by assigning centroid coordinates xc,zc and angle θ_{th}, measured with respect to the system of reference reported in Figure 5. Length (l) and strength (th) are expressed with the parametric relations

Skin (q = 1, 2) and nose sticks (q = 3) have a tapered support obtained imposing a linear variation of point source blob radius. Conversely, a constant radius is adopted for the leading edge (q = 4) and trailing edge (q = 5) sticks.

A similar but completely independent stick-based parameterization has been also defined to model a dynamic distribution map of different insulating materials, denoted here generically as material 1 and material 0 represented with red and blue colors, respectively. We assume that material 1 outperforms material 0. Therefore, material 1 is adopted on the nose, leading edge, and trailing edge, respectively. Differently than sticks used for thickness distribution, this additional set of primitives returns just binary values used to define specific materials. In this case the field function mth (see relation (12)) assumes a constant value equal to one inside the finite support of a stick and zero elsewhere. The parametric equations which describe material assignments are

with normalized parameters reported in Table 1.

Parameter | Value | Parameter | Value |
---|---|---|---|

st_{1}, ad |
0 | mt_{1}, ad |
1 |

st_{2}, ad |
0.01 | mt_{2}, ad |
0.01 |

st_{3}, ad |
0.05 | mt_{3}, ad |
0.05 |

st_{4}, ad |
1 | mt_{4}, ad |
1 |

st_{5}, ad |
0.8 | mt_{5}, ad |
0.8 |

lt_{1}, ad |
1 | mlt_{1}, ad |
1 |

lt_{2}, ad |
0.1 | mlt_{2}, ad |
0.1 |

lt_{3}, ad |
1 | mlt_{3}, ad |
1 |

lt_{4}, ad |
1 | mlt_{4}, ad |
1.2 |

lt_{5}, ad |
1 | mlt_{5}, ad |
1 |

pt_{1}, ad |
1 | _ | _ |

pt_{2}, ad |
0.2 | _ | _ |

pt_{3}, ad |
0.5 | _ | _ |

pt_{4}, ad |
0.2 | _ | _ |

pt_{5}, ad |
0.6 | _ | _ |

d_{1min}, ad |
0.5 | d_{1max}, ad |
1 |

d_{2inin}, ad |
0.01 | d_{2max}, ad |
0.3 |

d_{3min}, ad |
0.09 | d_{3max}, ad |
1 |

d_{4min}, ad |
0.1 | d_{4max}, ad |
0.5 |

d_{5min}, ad |
0.02 | d_{5max}, ad |
0.5 |

th^{’}_{min}, ad |
0.07 | th^{’}_{max}, ad |
0.12 |

th^{”}_{min}, ad |
0.132 | th^{”}_{max}, ad |
0.25 |

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## 6. TPS modeling capabilities

The previously introduced modeling procedure has been applied on a conceptual RLV shape created with the model described in Section 4 and detailed in [20, 21]. Figure 6 shows a topological map obtained for an arbitrarily chosen distribution of stick primitives.

A local thickness is assigned on the nose, the leading edge, and the trailing edge. The topological map shown in Figure 6 creates a morphologically adaptive TPS on two RLV shapes with different dimensions: (RLV-1) with length ltot = 9.8 m, wingspan ws = 5.6 m, cabin height h = 1.6 m, and (RLV-2) with length ltot = 15 m, wingspan ws = 9.2 m, and cabin height h = 2 m. The parameters characterizing the distribution of thickness and of the materials are reported in Table 1. Figure 7a, b shows the application of TPS modeling over the first configuration (RLV-1), on leeward (a) and windward (b) surface, respectively. Different colors denote different values of thickness and are represented in a dimensional scale.

It can be observed that the thickness map can be easily tuned up for best covering of regions where maximum heat loads occur (i.e., the nose and leading edge). Figure 7 shows the capability to create arbitrary seamless thickness distribution up to the value of the baseline thickness which has been arbitrarily set equal to th_{min} = 0.05 m (denoted in blue color). This corresponds to a region of the leeward surface not covered by the skin stick. Figure 7c, d shows the map of two different insulating materials created with Eq. (7). Red colors indicate material 1, which is placed on regions of the vehicle subjected to higher heat loads. Comparisons between Figure 7a, b and Figure 7c, d also exhibit the capability of the model to handle independently both the thickness and material distribution. Finally, Figure 8a, b and Figure 8c, d show the same blob distribution adopted either for thickness or material modeling applied on a different RLV configuration (RLV-2). The procedure creates, as it was expected, the same TPS distribution both for thickness or materials on two different shapes and is completely independent by their morphology.

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## 7. Conclusions

In the present paper, a special modeling procedure of the TPS designed for a conceptual RLV has been developed. A set of macroaggregates of point source blobs organized in envelopes of finite supports, and with a bounded strength, has been successfully created on the topological map associated with the computational grid. Applications of the modeling procedure to different design configurations highlighted the sensitivity and powerful control to radically change the TPS using a limited number of parameters. The promising capabilities of the developed modeling procedure suggest that the present methodology can give support to a multidisciplinary analysis optionally included in a conceptual design framework. Further developments of the considered procedure are about to be integrated in a companion paper by the authors [23].

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## Acknowledgments

This work was supported by the Universitá della Campania: “Luigi Vanvitelli.”

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## Conflict of interest

The authors declare that there is no conflict of interest regarding the publication of this chapter.

- 1.
Sziroczak D, Smith H. A review of design issues specific to hypersonic flight vehicles. Progress in Aerospace Sciences. 2016; 84 :1-28. DOI: 10.1016/j.paerosci.2016.04.001 - 2.
DePasquale D, Charania AC, Olds JR. The emerging orbital space tourism industry: New insight into demand and prospect for success. Space 2006. AIAA Paper No. 2006-7478 - 3.
Hirschel E, Weiland C. Selected Aero-Thermodynamic Design Problem of Hypersonic Flight Vehicles. Springer-Verlag/AIAA; 2009. DOI: 10.1007/978-3-540-89974-7 - 4.
Dirkx D, Mooij E. Conceptual Shape Optimization of Entry Vehicles Applied to Capsules and Winged Fuselage Vehicles, Springer Aerospace Technology. Switzerland: Springer International Publishing; 2017. DOI: 10.1007/978-3-319-46055-0 - 5.
Dirkx D, Mooij E. Optimization of entry-vehicle shapes during conceptual design. Acta Astronautica. 2014; 94 (1):198-214. DOI: 10.1016/j.actaastro.2013.08.006 - 6.
Ridolfi G, Mooij E, Dirkx D, Corpino S. Robust multi-disciplinary optimization of unmanned entry capsules. 2012. AIAA Paper No. 2012-5006 - 7.
Rowell RF, Braun RD. Multidisciplinary conceptual design optimization of space transportation systems. Journal of Aircraft. 1999; 35 (1):218-226 - 8.
Lobbia MA. Multidisciplinary design optimization of waverider-derived crew reentry vehicles. Journal of Spacecraft and Rockets. 2017; 54 (1):233-245. DOI: 10.2514/1.A33253 - 9.
Di Giorgio S, Quagliarella D, Pezzella G, Pirozzoli S. An aerothermodynamic design optimization framework for hypersonic vehicles. Aerospace Science and Technology. 2019; 84 :339-347 - 10.
Zhang T-t, Wang Z-g, Huang W, Yan L. Parameterization and optimization of hypersonic-gliding vehicle configurations during conceptual design. Aerospace Science and Technology. 2016; 58 :225-234. DOI: 10.1016/j.ast.2016.08.020 - 11.
Hinman WS, Johansen CT. Rapid prediction of hypersonic blunt body flows for parametric design studies. Aerospace Science and Technology. 2016; 58 :48-59. DOI: 10.1016/j.ast.2016.08.007 - 12.
Kumar S, Mahulikar SP. Design of thermal protection system for reusable hypersonic vehicle using inverse approach. Journal of Spacecraft and Rockets. 2017; 54 (2):436-446. DOI: 10.2514/1.A33688 - 13.
Olynick D. Trajectory-based thermal protection system sizing for an X-33 winged vehicle concept. Journal of Spacecraft and Rockets. 1998; 35 (3):249-256. DOI: 10.2514/2.338 - 14.
Bradford JE. Thermal protection system sizing and selection for RLV using the sentry code. 2006. AIAA Paper No. 2006-4605 - 15.
Mazzaracchio A. Thermal protection system and trajectory optimization for orbital plane change aeroassisted maneuver. Journal of Aerospace Technology and Management. 2013; 5 (1):49-64 - 16.
Blinn JF. A generalization of algebraic surface drawing. ACM Transactions on Graphics. 1982; 68 (3):123-134 - 17.
Iuspa L. Free topology generation of self-stiffened panels using skeleton-based integral soft objects. Computers and Structures. 2015; 158 :184-210. DOI: 10.1016/j.compstruc.2015.06.013 - 18.
Blanc C, Schlick C. Extended field functions for soft objects. In: Proceedings of the Implicit Surface’95; Grenoble, France; 1995. pp. 21-32 - 19.
Wyvill G, Pheeters C, Wyvill B. Data structures for soft objects. The Visual Computer. 1986; 2 :227-234 - 20.
Viviani A, Iuspa L, Aprovitola A. An optimization-based procedure for self-generation of re-entry vehicles shape. Aerospace Science and Technology. 2017; 68 :123-134. DOI: 10.1016/j.ast.2017.05.009 - 21.
Viviani A, Iuspa L, Aprovitola A. Multi-objective optimization for re-entry spacecraft conceptual design using a free-form shape generator. Aerospace Science and Technology. 2017; 71 :312-324. DOI: 10.1016/j.ast.2017.09.030 - 22.
Florez H, Borges B. Scalar and Parametric Spline Curves and Surfaces. Rijeka, Croatia: Intech Open; 2018. DOI: 10.5772/intechopen.74929 - 23.
Aprovitola A, Iuspa L, Viviani A. Thermal protection system design of a reusable launch vehicle using integral soft objects. International Journal of Aerospace Engineering. 2019:(3). DOI:10.1155/2019/6069528

Submitted: 22 February 2019 Reviewed: 19 April 2019 Published: 15 May 2019

© 2019 The Author(s). Licensee IntechOpen. This chapter is distributed under the terms of the Creative Commons Attribution 3.0 License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.