### Abstract

A transient inverse heat conduction analysis enables the identification of the unknown boundary heat flux from finite number of temperature data obtained, e.g., in the high temperature structural tests or in the actual operation. Since the prediction of thermal load (heat flux) is difficult, the inverse analysis is expected to improve structural design of high temperature components. The present study develops a computational method of transient inverse heat conduction analysis. The developed code is applied to problems of a simple two-dimensional plate and of an atmospheric reentry capsule. Sequential Function Specification (SFS) method and Truncated Singular Value Decomposition (TSVD) are employed to improve the stability of the inverse analysis. Effects of these regularization methods are numerically discussed.

Original language | English |
---|---|

Pages (from-to) | 48-55 |

Number of pages | 8 |

Journal | Aerospace Science and Technology |

Volume | 38 |

DOIs | |

Publication status | Published - 2014 |

### Fingerprint

### Keywords

- Pseudo-inverse matrix
- Reentry capsule
- Sequential function specification
- Transient inverse heat conduction analysis
- Truncated singular value decomposition

### ASJC Scopus subject areas

- Aerospace Engineering

### Cite this

*Aerospace Science and Technology*,

*38*, 48-55. https://doi.org/10.1016/j.ast.2014.07.015

**Inverse analysis for transient thermal load identification and application to aerodynamic heating on atmospheric reentry capsule.** / Nakamura, Toshiya; Kamimura, Yukihiro; Igawa, Hirotaka; Morino, Yoshiki.

Research output: Contribution to journal › Article

*Aerospace Science and Technology*, vol. 38, pp. 48-55. https://doi.org/10.1016/j.ast.2014.07.015

}

TY - JOUR

T1 - Inverse analysis for transient thermal load identification and application to aerodynamic heating on atmospheric reentry capsule

AU - Nakamura, Toshiya

AU - Kamimura, Yukihiro

AU - Igawa, Hirotaka

AU - Morino, Yoshiki

PY - 2014

Y1 - 2014

N2 - A transient inverse heat conduction analysis enables the identification of the unknown boundary heat flux from finite number of temperature data obtained, e.g., in the high temperature structural tests or in the actual operation. Since the prediction of thermal load (heat flux) is difficult, the inverse analysis is expected to improve structural design of high temperature components. The present study develops a computational method of transient inverse heat conduction analysis. The developed code is applied to problems of a simple two-dimensional plate and of an atmospheric reentry capsule. Sequential Function Specification (SFS) method and Truncated Singular Value Decomposition (TSVD) are employed to improve the stability of the inverse analysis. Effects of these regularization methods are numerically discussed.

AB - A transient inverse heat conduction analysis enables the identification of the unknown boundary heat flux from finite number of temperature data obtained, e.g., in the high temperature structural tests or in the actual operation. Since the prediction of thermal load (heat flux) is difficult, the inverse analysis is expected to improve structural design of high temperature components. The present study develops a computational method of transient inverse heat conduction analysis. The developed code is applied to problems of a simple two-dimensional plate and of an atmospheric reentry capsule. Sequential Function Specification (SFS) method and Truncated Singular Value Decomposition (TSVD) are employed to improve the stability of the inverse analysis. Effects of these regularization methods are numerically discussed.

KW - Pseudo-inverse matrix

KW - Reentry capsule

KW - Sequential function specification

KW - Transient inverse heat conduction analysis

KW - Truncated singular value decomposition

UR - http://www.scopus.com/inward/record.url?scp=84906717392&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=84906717392&partnerID=8YFLogxK

U2 - 10.1016/j.ast.2014.07.015

DO - 10.1016/j.ast.2014.07.015

M3 - Article

AN - SCOPUS:84906717392

VL - 38

SP - 48

EP - 55

JO - Aerospace Science and Technology

JF - Aerospace Science and Technology

SN - 1270-9638

ER -