A General Integrated Method for Design Analysis and Optimization of Missile Structure
Abstract
:1. Introduction
2. Theory
2.1. CST Parameterization Method
2.2. Augmented Fourier Series-Based Polynomial Surrogate Model
3. Design of Module
3.1. Design of Parametric Modeling Module
3.2. Design of Analysis Module
4. Optimation Strategy
5. Validation Examples
5.1. Parametric Modeling
5.2. Parametric Structure Analysis
5.3. Structure Optimation
6. Conclusions
- (1)
- The CST parameterization methodology is derived, which can accurately model any airfoil in the entire design space with fewer variables;
- (2)
- The parametric modeling and analysis module of the missile is developed in C/C++ language on the basis of the CST parametric method and UG secondary development technology. Moreover, several various examples are presented to verify the validity and the versatility of this module;
- (3)
- By introducing a linear polynomial, a novel Augmented Fourier series-based polynomial surrogate model can be obtained. It can more accurately reflect the mathematical relationship between input and output data, which has the advantages of efficiency, transparency, and conceptual simplicity, especially for strong non-linear problems;
- (4)
- A novel surrogate model-based optimation strategy is designed to obtain a relatively light mass missile structure under the existing shape size, and satisfactory results are obtained when applied the structure optimation procedure to a missile example;
- (5)
- Compared with the traditional manual method, the parametric modeling and analysis method proposed in this paper can significantly improve the design efficiency of the missile, and shorten the design cycle, which provides a method with great value in engineering;
- (6)
- Subsequently, a comprehensive analysis platform of the missile can be established by using the parametric modeling module and the parametric analysis module developed in this paper, and other analysis modules, such as aerodynamic analysis module and stealth performance analysis module, which would provide a comprehensive method to realize the multidisciplinary optimization design of missiles.
Author Contributions
Funding
Conflicts of Interest
References
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Part | Parameter Names | Variables | Part | Parameter Names | Variables |
---|---|---|---|---|---|
Body | Total Length | Len | Wing | Wingroot Shape | Swroot[ ] |
Nose Fineness Ratio | Rnd | Wingtip Shape | Swtip[ ] | ||
Nose Length | Lnose | Sweep Angle | Awsweep | ||
Boattail Length | Ltail | Wingspan | Lwspan | ||
Nose Shape | Snose[ ] | Wing Position | Pwing[ ] | ||
Projectile Body Shape | Spb_1[ ] | Installation Angle | Ains | ||
Boattail Shape | Stail[ ] | Number of Wings | Nass |
Part | Parameter | Variables | Part | Parameter | Variables |
---|---|---|---|---|---|
Cabin | Number | Num_C | Wing | Type | Type |
position | Pos_C[ ] | Size | Siz_W | ||
thickness | Thick | Material property | Mat_W[ ] | ||
length | Len | Number | Num_W | ||
Material | Mat_E[ ] | Loads | Position | Pos_L[ ] | |
Components | Position | Pos_E[ ] | Magnitude | Mag | |
Size | Size_E[ ] | Direction | Dir[ ] |
Objects | Modeling Process | Analysis Process |
---|---|---|
Traditional manual | 1 h | 2 h |
Parametric method | 20 s | 100 s |
Saving time | 99.44% | 98.61% |
Index | Parameter | Description |
---|---|---|
1 | t1 | Thickness of cabin 1 |
2 | t2 | Thickness of cabin 2 |
3 | t3 | Thickness of cabin 3 |
4 | t4 | Thickness of cabin 4 |
5 | t5 | Thickness of cabin 5 |
6 | t6 | Thickness of cabin 6 |
7 | t7 | Thickness of wing |
Objects | Optimum Value |
---|---|
Thickness of cabin 4 (mm) | 7.96 |
Thickness of wing (mm) | 6.94 |
Weight (kg) | 100.58 |
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Wang, X.; Yang, J.; Guo, J.; Guo, J. A General Integrated Method for Design Analysis and Optimization of Missile Structure. Algorithms 2019, 12, 257. https://doi.org/10.3390/a12120257
Wang X, Yang J, Guo J, Guo J. A General Integrated Method for Design Analysis and Optimization of Missile Structure. Algorithms. 2019; 12(12):257. https://doi.org/10.3390/a12120257
Chicago/Turabian StyleWang, Xiaoguang, Jun Yang, Jian Guo, and Jun Guo. 2019. "A General Integrated Method for Design Analysis and Optimization of Missile Structure" Algorithms 12, no. 12: 257. https://doi.org/10.3390/a12120257
APA StyleWang, X., Yang, J., Guo, J., & Guo, J. (2019). A General Integrated Method for Design Analysis and Optimization of Missile Structure. Algorithms, 12(12), 257. https://doi.org/10.3390/a12120257