Gespeichert in:
| Hauptverfasser: | , , |
|---|---|
| Format: | Recurso digital |
| Sprache: | Englisch |
| Veröffentlicht: |
Zenodo
2023
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| Schlagworte: | |
| Online-Zugang: | https://doi.org/10.5281/zenodo.7528735 |
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Inhaltsangabe:
- <p>Unmanned Air Vehicles (UAVs) have made substantial progress in research over the last decade, as a result of its capability to enhance tactical spatial awareness in combat activities and a wide range of other areas that might be hazardous or demanding for human engagement. Researchers are interested in Cyclocopters because of their ability to execute reconnaissance and sensing tasks that cannot justify the expense of space satellites due of their short mission lifetime. Hybrid Cyclocopters with longer endurance needs to have higher hover time than conventional counterparts which can be achieved using a Cyclorotor that can generate forward thrust even at lower wind speeds. But Hybrid Cyclocopters also need more power to sustain the long fight without increasing the battery size and weight. A fuel cell can satisfy this hurdle by generating electrical energy on-board using electro-chemical process. This report explores the feasibility of integrating cyclorotor and fuel cell into hybrid Cyclocopter to improve its endurance and support surveillance missions. Numerical analysis of the design show that the presence of cyclorotor decreases the sinking rate of cyclocopter by 1.4 times in comparison to the conventional model. It also shows that a 5-hr journey for a hybrid cyclocopter at endurance level requires 36.2 g of H2 or 402 Liter of H2 at NTP conditions</p>