ducted fan
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This manuscript discusses the operation of an electrically driven fan for a hybrid-electric propulsion system for BAe-146 aircraft. The thrust requirement is fed into an integrated cycle and aerodynamic design tool for the sizing of a ducted fan as one of the main propulsors, podded under the wing as a replacement for a turbofan engine. The electric motor design is initiated with the torque and speed requirements and with the dimensional constraints arising from the driven fan geometry. The fan operation and aerodynamic design are derived by changing the fan pressure ratio and hub-to-tip ratio to obtain a 2-D design space. Surface-mounted permanent magnet electric motor designs are mapped on the 2-D fan design space. The design and operational flexibility of the system is investigated through three scenarios. In the first scenario, the aircraft rate of climb is changed to downsize the electric motor. In the second scenario, the electric motor rated frequency is changed to increase the power density and in the third scenario the electric motor current density is changed for the same purpose. The investigated three scenarios provide design and operational guidelines for reducing the weight of the electric motor for a direct drive application.

Abstract On a rocket, control requires monitoring to determine its position and attitude. Rocket stance includes roll, pitch, and yaw angles. Monitoring can be done manually without the help of tools while the object’s position is still within reach. It is difficult to carry out monitoring when the object is moving far and beyond the reach of the operator. This observation requires a monitoring system to monitor the object further. This research applies a telemetry system to a target tracking rocket. The measurement results from the IMU and GPS sensors on the rocket body will be processed by the ATMega 2560 microcontroller and sent via a 2.4 GHz RF signal. to Ground Control Station. The rocket telemetry data that has been sent to the GCS can be viewed by the operator through the GUI system in a computer program using the C# language in Visual Studio. Tests on latitude and longitude are carried out by tracking the trajectory of objects while testing for roll, pitch, and yaw angles is carried out by placing objects according to the reference angle. The results of the position obtained the values of altitude, latitude, and longitude of 0.5364 m, 0.000012°, and 0.000023°, respectively. An attitude tests for roll position, pitch, and compass heading have values of 0.35°, 0.07, and 2.90°, respectively. The telemetry data transmission distance test is still well-received at a distance of 200 with a test speed of 70 KM/hour.

Perkembangan teknologi rudal jelajah sejak era perang dunia ke-II hingga saat ini telah menjadikan negara-negara di dunia saling bersaing menciptakan teknologi rudal yang canggih, sebagai sistem pertahanan negara dan tolak ukur kekuatan suatu negara dalam kepentingan sistem pertahanan dan objek penelitian alutsista. Penelitian ini bertujuan mengetahui pengaruh sudut elevasi terhadap kecepatan rudal mencapai target sasaran 200 meter dengan sistem kendali PID untuk kestabilan gerak. Hasil dari pengujian pada sudut elevasi 50o, 60o, dan 70o didapatkan kecepatan rudal tercepat 25,5 m/s pada sudut elevasi 50o sedangkan sudut elevasi 60o dan 70o hanya mencapai 16 m/s. Hasil simulasi airfoil pada konfigurasi forward swept wing menghasilkan gaya angkat sebesar 2616 N dan gaya drag 1202 N. Sudut elevasi peluncuran 50o mampu diterapkan dengan sistem kendali PID yang didapatkan untuk kestabilan gerak rudal dalam mencapai target sasaran yang optimal. Kata kunci:  EDF, PID, Rudal Jelajah, Wings Forward Swept