Development of Green Storable Hybrid Rocket Propulsion Technology Using 98% Hydrogen Peroxide as Oxidizer
Abstract
:1. Introduction
2. Technology Development Initiation—The First Steps
3. Materials and Methods Relevant to Hybrid Rocket Motor Hot Fire Testing
3.1. Development Steps and Relevant Methods
3.2. Overview of the Flight Hybrid Rocket Motor of the ILR-33 AMBER
3.3. Overview of the ILR-33 AMBER Suborbital Rocket
4. Results
4.1. Subscale Testing of Fuels for Use with 98% Hydrogen Peroxide
4.2. Full-Scale Testing of the ILR-33 AMBER Hybrid Propulsion System
4.3. In-Flight Test Campaigns
4.4. Other Actions
5. Discussion of Test Firing and Flight Testing Results
- Subscale tests cannot be directly used for full-scale design and analysis (they shall be compensated for scale differences).
- Careful measurement and data analysis is a must for obtaining reliable results for making valuable conclusions and design decisions.
- HTP of 98% concentration allows for safe handling; however, special measures must be taken in order to ensure that organics are not in contact with HTP.
- Hybrid rocket propulsion using 98% HTP can allow for efficient use for space transportation due to its higher performance than in the case of utilizing lower HTP concentrations (performance was verified in flight and extensive system performance data were obtained during in-flight and ground testing; 6-degree-of-freedom flight numerical simulations confirm that for full oxidizer loading of the ILR-33 AMBER 2K vehicle, flights above the Von Karman line will be possible).
6. Conclusions
Author Contributions
Funding
Institutional Review Board Statement
Informed Consent Statement
Data Availability Statement
Acknowledgments
Conflicts of Interest
References
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H2O2 Concentration | Fuel | Motor Thrust 1 | Ignition System | Grain Geometry | Regression Rate Law Following Equation (1) | Injection | Reference |
---|---|---|---|---|---|---|---|
70% | PE | torch | single port | [42] | |||
84% | Paraffin/C (95/5) | 385–661 N | catalytic | single port | 0.0344 Gox0.9593 | [72] | |
70–85% | ABS | arc ignition | [73] | ||||
80–85% | LDPE, HDPE, polymethyl methacrylate | catalytic (consumable bed) | single port | 0.040 Gox0.78 determined for LDPE for Gox in the range of 70–211 kg/(s·m2) at 6.9 bar 0.035 Gox0.52 determined for LDPE for Gox in the range of 70–211 kg/(s·m2) at 13.8 bar 0.041 Gox0.49 determined for LDPE for Gox in the range of 141–492 kg/(s·m2) at 27.6 bar | [74] | ||
87.5% | PE | 300 N (vacuum) | catalytic | single port | catalyst and swirl injector | [49] | |
87.5% | HTPB + C | 30,000 N | catalytic | multiport | [43] | ||
87.5% | HTPB + Al (70/30) | 2400 N | catalytic | telescope (rod-and-tube geometry) | shower-head | [75] | |
88% | PE | catalytic | single port | 0.0535 Gox0.8 | [32] | ||
85–90% | ABS | 140 N | arc-jet ignition (small catalyst bed) | single port | [48] | ||
90% | PE | 4450 N | catalytic | various, including telescope (rod-and-tube geometry) | ~Gox0.45 | [31] | |
90% | PE | 250 N | catalytic | [76] | |||
90% | PE | up to 1250 N | catalytic | single port | [50] | ||
90% | HTPB | single port | 0.04019 Gox0.5623 | shower-head | [77] | ||
90% | Paraffin + PE wax + EVA + SA + C (50/20/18/10/2) | 11,500 N | catalytic | single port | 0.279 Gox0.732 | [78] | |
90% | D: HTPB + Al (40/60)E: HTPB + Al/Mg (40/60) | 90 N | catalytic | single port | 0.014 Gox0.7 (D) 0.029 Gox0.6 (E) | porous injector to cat bed | [58] |
90% | Dicyclopentadiene, HTPB with metal hydrates | catalytic | single port | 0.057 Gox0.49 (DC) 0.060 Gox0.50 (HTPB) 0.019 Gox0.73 (HTPB + NaBH4: 75/25) 0.008 Gox0.90 (HTPB + NaBH4: 50/50) 0.037 Gox0.65 (HTPB + AlH3: 75/25) | [79] | ||
90% | HDPE, PLA, ABS | 250 N | catalytic | single port | shower-head | [45] | |
90% | LDPE | 4000 N | catalytic | 4-port | full cone spray | [80] | |
90% | LiAlH4 + PE (95/5) | [34] | |||||
90% | Paraffin | 1000 N | catalytic | single port | 0.145 Gox0.5 | [81] | |
90% | PP | 400 N | catalytic | single port | swirl | [82] | |
91.5% | HDPE | 300 N | catalytic | single port | provided as function of swirl number | swirl | [82] |
90%, 95% | HDPE | 250 N | catalytic | single port | 0.0320 Gox0.54 (90% HTP) 0.00737 Gox0.75 (95% HTP) | shower-head | [56] |
95% | Ammonia borane, paraffin wax and hypergolic additives | hypergolic | [52] | ||||
87.5%, 98% | PE | 250 N | catalytic | end-burning | 0.0446 Gox0.3288 (87.5% HTP) | annular ring swirl injection, with six catalyst beds | [38] |
90–98% | HTPB | 9.392 10−2 Gox0.53 (90% HTP) 9.824 10−2 Gox0.53 (98% HTP) | [83] | ||||
98% | HDPE | 4000 N | catalytic | wagon wheel | shower-head | [20] | |
98% | A: HTPB + Al (80/20) B: HTPB + C14H10 + Al (60/20/20) C: HTPB + Al + Mg + C (60/28/10/2) | 1000 N | solid propellant igniter | single port | 3.9388 10−3 Gox1.0433 (A) 4.2938 10−3 Gox1.0336 (B) 2.6676 10−2 Gox0.72493 (C) | shower-head | [84,85] |
98% | HTPB | 100 N | catalytic | single port | shower-head | [86,87] | |
98% | PE | no catalytic bed | single port | annular gap | [51] | ||
98% | ABS, HDPE, PA6 | 200 N | catalytic | wagon wheel | shower-head | [44] |
Development Task | Approach | Outcome |
---|---|---|
fuel candidates down-selection | literature review, use of data of previous in-house test [86,87,99] | high-density polyethylene (2 variants, paraffin, polyamide (PA6) |
fuel regression rate determination | subscale firings of laboratory hybrid rocket motors using 98% HTP and down-selected fuels (Figure 3) | regression rate formulas for each propellant combination |
catalyst development for 98% HTP for burn durations exceeding 40 s and mass flow rates up to 1.5 kg/s | use of earlier verified catalyst technology | use of a catalyst bed using Al2O3 support and MnxOy active phase [86,107,108] |
thermal insulation and low-regression ablative insert degradation characterization | subscale firings of laboratory motors and engines | regression rates of materials in various critical locations within the combustion chamber and nozzle assembly |
feeding system operation and performance validation | ground-testing dynamic characteristics of pressure regulator, valves and measurement devices via feeding water using the helium pressurant | datasets of temperature and pressure in feeding system, particularly with focus on conditions in helium tank and oxidizer tank [20] |
pre-flight motor operation and performance validation | ground firings of full-scale hybrid rocket motors | datasets of pressures, temperatures, mass flows along test-site feeding system and within the motor itself, thrust measurement and extensive data from vision systems (including fast cameras and thermovision) [20] |
in-flight hybrid rocket motor technology verification | suborbital launch of rocket demonstrator | in-flight data of hybrid rocket motor operation 1 [20,63,109] |
Parameter | ILR-33 AMBER | ILR-33 AMBER 2K |
---|---|---|
Launch mass | 160 kg | 270 kg |
Nominal payload mass | 5 kg | 10 kg |
Hybrid rocket motor main core total impulse (sea level) | 150 kNs | 156 kNs |
Hybrid rocket motor main core burn duration | 40 s | 39 s |
Solid rocket motor booster stage total impulse (sea level) | 27 kNs | 176.8 kNs |
Solid rocket motor booster stage burn duration | 2.6 s | 6.1 s |
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Okninski, A.; Surmacz, P.; Bartkowiak, B.; Mayer, T.; Sobczak, K.; Pakosz, M.; Kaniewski, D.; Matyszewski, J.; Rarata, G.; Wolanski, P. Development of Green Storable Hybrid Rocket Propulsion Technology Using 98% Hydrogen Peroxide as Oxidizer. Aerospace 2021, 8, 234. https://doi.org/10.3390/aerospace8090234
Okninski A, Surmacz P, Bartkowiak B, Mayer T, Sobczak K, Pakosz M, Kaniewski D, Matyszewski J, Rarata G, Wolanski P. Development of Green Storable Hybrid Rocket Propulsion Technology Using 98% Hydrogen Peroxide as Oxidizer. Aerospace. 2021; 8(9):234. https://doi.org/10.3390/aerospace8090234
Chicago/Turabian StyleOkninski, Adam, Pawel Surmacz, Bartosz Bartkowiak, Tobiasz Mayer, Kamil Sobczak, Michal Pakosz, Damian Kaniewski, Jan Matyszewski, Grzegorz Rarata, and Piotr Wolanski. 2021. "Development of Green Storable Hybrid Rocket Propulsion Technology Using 98% Hydrogen Peroxide as Oxidizer" Aerospace 8, no. 9: 234. https://doi.org/10.3390/aerospace8090234