Advanced Radar Absorbing Ceramic-Based Materials for Multifunctional Applications in Space Environment
Abstract
:1. Introduction
2. Materials and Methods
2.1. Carbon/Carbon Shell as a Thermal Protection System
- Thermal expansion compatibility between materials to avoid internal stresses due to the increasing temperature;
- Oxidation resistance for the plasma exposed layer;
- Great heat capacity for the core material to put down the temperature;
- Mechanical properties not degrading at high temperatures;
- High emissivity of the external layer in order to allow as much heat emission as possible;
- Low thermal conductivity of the inner layers in order to maintain a low temperature in the cold structure of the vehicle;
- Low catalycity of the plasma exposed surface in order to limit the surface heat flux: in fact, the outer structure could catalyze the exothermic recombination of disassociated species present in the hypersonic flow, thus resulting in heat flux increasing.
2.2. Multilayered Carbon Micro-/Nano-composite as an EM Shielding System
3. Results
3.1. Process Methodology
- Tile for cube-sat faces—The external surface is the EM impinged layer of the optimized carbon nanocomposite multilayered plate-shaped structure, aimed at microwave shielding, i.e., the satellite’s radar cross section reduction; the inner ceramic C/C bulk is imposed as a thermo-structural component to preserve the integrity and the correct working of the internal instrumentation from the severe thermo-mechanical stress experienced by the satellite during in orbit operations (see Figure 7).
- b. Shell for leading edge of sub-orbital aircraft—The C/C coating is externally exposed to the space conditions as TPS, and it is dimensioned to be totally eroded during the critical re-entry phase; the underlying nanocomposite-based lamination then acts as stealth component during the orbital operations (see Figure 8).
3.2. C/C Morphological and Thermo-Mechanical Analysis
3.3. Multilayers Absorbing Cross Section Evaluation
3.4. Numerical Simulation of Hybrid TPS/Stealth Structures
4. Conclusions
Author Contributions
Funding
Conflicts of Interest
References
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Property | Temperature, °F (°C) | |||
---|---|---|---|---|
70 (21) | 1500 (816) | 3000 (1649) | 3500 (1927) | |
Tensile strength-warp longitudinal direction, psi (MPa) | 48.0 × 103 (331) | 54.0 × 103 (372) | 60.0 × 103 (414) | 62.0 × 103 (427) |
Tensile strength-fill transverse direction, psi (MPa) | 40.0 × 103 (276) | 45.0 × 103 (310) | 50.0 × 103 (345) | – |
Modulus-warp longitudinal direction, psi (GPa) | 16.5 × 106 (114) | 16.5 × 106 (114) | 15.0 × 106 (103) | 12.5 × 106 (86) |
Modulus-fill transverse direction, psi (GPa) | 15.8 × 106 (109) | 15.8 × 106 (109) | 14.4 × 106 (99) | 12.0 × 106 (83) |
Compressive strength-warp longitudinal direction, psi (MPa) | 26.0 × 103 (179) | 33.0 × 103 (228) | 40.0 × 103 (276) | – |
Compressive strength-fill transverse direction, psi (MPa) | 26.0 × 103 (179) | 30.0 × 103 (207) | 35.0 × 103 (241) | – |
Item | Fiber Yarn & D-Stitch | Thickness (mm) | Density (g/cm3) |
---|---|---|---|
Antares | 12 K/3D | 30–36 | 1.52 |
Aldebaran | 12 K/4D | 30–36 | 1.46 |
Item | Sample Number | Weight before Cycle (g) | Weight after Cycle (g) | Total Mass Loss (%) |
---|---|---|---|---|
Antares | 1 | 37.30 | 37.25 | 0.13 |
2 | 36.51 | 36.44 | 0.19 | |
3 | 36.70 | 36.65 | 0.14 | |
4 | 37.56 | 37.51 | 0.13 | |
Aldebaran | 1 | 35.00 | 34.94 | 0.17 |
2 | 26.45 | 26.40 | 0.19 | |
3 | 34.65 | 34.61 | 0.12 | |
4 | 38.67 | 38.60 | 0.18 |
Temperature (°C) | Average Value of Pre-Treatment (10−6/K) | Average Value of Post-Treatment (10−6/K) | Difference (%) |
---|---|---|---|
400 | 1.60 | 1.60 | 0 |
500 | 1.60 | 1.60 | 0 |
600 | 1.60 | 1.70 | 6.25 |
700 | 1.60 | 1.70 | 6.25 |
800 | 1.70 | 1.80 | 5.88 |
900 | 1.70 | 1.90 | 11.76 |
1000 | 1.70 | 2.00 | 17.65 |
1100 | 1.80 | 2.00 | 11.11 |
1200 | 1.90 | 2.10 | 10.53 |
1300 | 1.90 | 2.10 | 10.53 |
1400 | 1.90 | 2.20 | 15.79 |
1500 | 1.90 | 2.20 | 15.79 |
Frequency (MHz) | ACS-Panel 1 (m2) | ACS-Panel 2 (m2) |
---|---|---|
2200 | 0.020 | 0.020 |
2250 | 0.025 | 0.030 |
2500 | 0.027 | 0.032 |
2750 | 0.025 | 0.026 |
3000 | 0.017 | 0.019 |
3250 | 0.021 | 0.031 |
3500 | 0.022 | 0.026 |
3750 | 0.026 | 0.027 |
4000 | 0.017 | 0.022 |
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Delfini, A.; Albano, M.; Vricella, A.; Santoni, F.; Rubini, G.; Pastore, R.; Marchetti, M. Advanced Radar Absorbing Ceramic-Based Materials for Multifunctional Applications in Space Environment. Materials 2018, 11, 1730. https://doi.org/10.3390/ma11091730
Delfini A, Albano M, Vricella A, Santoni F, Rubini G, Pastore R, Marchetti M. Advanced Radar Absorbing Ceramic-Based Materials for Multifunctional Applications in Space Environment. Materials. 2018; 11(9):1730. https://doi.org/10.3390/ma11091730
Chicago/Turabian StyleDelfini, Andrea, Marta Albano, Antonio Vricella, Fabio Santoni, Giulio Rubini, Roberto Pastore, and Mario Marchetti. 2018. "Advanced Radar Absorbing Ceramic-Based Materials for Multifunctional Applications in Space Environment" Materials 11, no. 9: 1730. https://doi.org/10.3390/ma11091730