Reliability Analysis of Pyrotechnic Igniter for Hydrogen-Oxygen Rocket Engine with Low Temperature Combustion Instability Failure Mode
Abstract
:1. Introduction
2. Failure Analysis of Low-Temperature Unstable Combustion of the Pyrotechnic Igniter
2.1. Basic Structure and Working Principle
2.2. Failure Mode
3. Deterministic Simulation of Low Temperature of the Pyrotechnic Igniter
3.1. Simulation Model of the Pyrotechnic Igniter
3.2. Simulation Result Compared with Experimented Result
4. Reliability and Reliability Sensitivity Analysis Method of the Igniter
4.1. Kriging Model of the Igniter
4.2. Reliability Sensitivity Analysis
4.3. Reliability Simulation Implementation of the Pyrotechnic Igniter
5. Reliability and Sensitivity Analysis Results
6. Conclusions
- (1)
- The ignition simulation model of the pyrotechnic igniter was established, and the accuracy of the simulation model was verified experimentally. The results show the experimental and analytical results are in good agreement;
- (2)
- The nonlinear implicit function of pyrotechnic igniter is established with ignition impulse as performance parameter;
- (3)
- The Kriging + TLFF + MCS method is verified by analyzing the ignition reliability of the pyrotechnic igniter. The results show that the relative deviations between the Kriging + TLFF + MCS with 81 samples and the MCS are less than 1.2%;
- (4)
- Finally, the sensitivity analysis is performed to quantify the importance ranking of random variables, which offers a valuable insight into reliability-based design and optimization process for the pyrotechnic igniter. The results indicate parameter d is the main factor affecting the ignition reliability of the pyrotechnic igniter, followed by nMLR, ρCMDB and ρBPN. Further improvement measures are presented based on reliability and sensitivity results for the pyrotechnic igniter and the correctness of the improved measures was verified by experiment.
Author Contributions
Funding
Institutional Review Board Statement
Informed Consent Statement
Data Availability Statement
Acknowledgments
Conflicts of Interest
References
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Parameter | Value | Parameter | Value |
---|---|---|---|
Shape characteristic parameter of the CMDB (χ) | 2.5 | Shape characteristic parameter of the BPN (χ) | 4.19 |
Shape characteristic parameter of the CMDB (λ) | −0.3 | Shape characteristic parameter of the BPN (λ) | −1.28 |
Shape characteristic parameter of the CMDB (μ) | 0 | Shape characteristic parameter of the BPN (μ) | 0.25 |
Density of the CMDB particles (ρCMDB) | 1.589 g·cm−3 | Density of the BPN particles (ρBPN) | 1.679 g·cm−3 |
Explosion temperature of the CMDB (Tf) | 3354 K | Explosion temperature of the BPN (Tf) | 3321 K |
Specific heat ratio of the CMDB (k) | 1.87 | Specific heat ratio of the BPN (k) | 1.31 |
Burn rate exponent the CMDB (n) | 0.22 | Burn rate exponent the BPN (n) | 0.31 |
Covolume of the CMDB (αg) | 6.4 × 10−4 m3/kg | Covolume of the BPN (αg) | 1.3 × 10−4 m3/kg |
Convective heat transfer coefficient (h) | 1050 W·m−2·K−1 | Stefan–Boltzmann constant (σs) | 5.67 × 10−8 W·m−2·K−1 |
Absorption rate of the vessel wall (αw) | 0.24 | Net emissivity of the product (Em) | 0.24 |
Temperature of the ignition case (TIC) The diameter of the nozzle (d) | 233.15 K 3.6 mm | Temperature of the main charge chamber (TIC) | 233.15 K |
Parameter | Pm/MPa | Pi/MPa | ts/s | tv/s |
---|---|---|---|---|
Simulation model | 11.07 | 6.17 | 0.16 | 2.14 |
Experiment 1 | 10.76 | 5.38 | 0.15 | 2.17 |
Experiment 2 | 10.48 | 5.60 | 0.14 | 2.23 |
Experiment 3 | 11.49 | 6.81 | 0.13 | 1.91 |
Difference with respect to the average value of exp. Results (%) | 1.35 | 4.04 | 14.28 | 1.90 |
Symbol | Mean | Std. | Distribution Type |
---|---|---|---|
ρBPN (g·cm−3) | 1.679 | 0.02 | Normal |
ρCMDB (g·cm−3) | 1.589 | 0.01 | Normal |
nCMDB | 0.22 | 0.01 | Normal |
d (mm) | 3.6 | 0.007 | Normal |
Name | Type |
---|---|
ρBPN | Input variable |
d | Input variable |
ρCMDB | Input variable |
nCMDB | Input variable |
Imin | Input variable |
MATLAB_input.m | MATLAB input script file |
MATLAB_output | MATLAB output file |
MATLAB | MATLAB execution commands |
I(x) | Output variable |
Display function of the ignition |
Method | Reliability | Reliability Index |
---|---|---|
Kriging + TLFF + MCS (81 samples) MCS (106 samples) | 0.8383 0.8281 | 0.0719 0.0706 |
Variable | Mean Sensitivity | Standard Deviation Sensitivity |
---|---|---|
ρBPN | 0.03 | −0.001 |
nCMDB | 0.411 | −0.011 |
d | −0.900 | −0.006 |
ρCMDB | 0.136 | −0.001 |
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Niu, L.; Liu, Y.; Wang, J.; Tu, H.; Dong, H.; Yan, N. Reliability Analysis of Pyrotechnic Igniter for Hydrogen-Oxygen Rocket Engine with Low Temperature Combustion Instability Failure Mode. Appl. Sci. 2022, 12, 3414. https://doi.org/10.3390/app12073414
Niu L, Liu Y, Wang J, Tu H, Dong H, Yan N. Reliability Analysis of Pyrotechnic Igniter for Hydrogen-Oxygen Rocket Engine with Low Temperature Combustion Instability Failure Mode. Applied Sciences. 2022; 12(7):3414. https://doi.org/10.3390/app12073414
Chicago/Turabian StyleNiu, Lei, Yang Liu, Jingcheng Wang, Hongmao Tu, Haiping Dong, and Nan Yan. 2022. "Reliability Analysis of Pyrotechnic Igniter for Hydrogen-Oxygen Rocket Engine with Low Temperature Combustion Instability Failure Mode" Applied Sciences 12, no. 7: 3414. https://doi.org/10.3390/app12073414
APA StyleNiu, L., Liu, Y., Wang, J., Tu, H., Dong, H., & Yan, N. (2022). Reliability Analysis of Pyrotechnic Igniter for Hydrogen-Oxygen Rocket Engine with Low Temperature Combustion Instability Failure Mode. Applied Sciences, 12(7), 3414. https://doi.org/10.3390/app12073414