The development of rockets in Indonesia has long been carried out by the National Aeronautics and Space Agency (LAPAN), which has now been integrated into the National Research and Innovation Agency (BRIN). The Research Centre for Rocket Technology, which is one of the centres within BRIN, has been developing solid propellant-based rockets with a various sizes and types. Solid-propellant rocket technology is commonly used because of their reliability, cost-effectiveness, and simple design. However, this technology is one of the high-risk technologies, whose failure can harm humans, damage the environment and cause huge losses to assets. As a high-risk technology, risk assessment activities must be carried out, starting from the design, manufacturing, testing and up to the launching stage. In this paper, we studied a risk assessment for general Solid-propellant Rocket Motor (SRM). SRM is basically a device that processes chemical energy in solid propellant into thrust (kinetic energy) in a container that functions as a pressure vessel. The risk assessment methods commonly used in this technology are the HAZOP or FMEA methods. The HAZOP is excellent in identifying failure modes systematically through identifying the deviation of physical process parameters but has difficulties in prioritizing the risk. The FMEA has effectiveness in understanding failure mechanisms and establishing necessary countermeasures, but for a product with a lot of components, the worksheet is also complex. By combining these two methods, integrating the superiority of each method, this research can identify modes, causes and effects of failure that may occur in SRM effective and accurately. In addition, this research also proposes corrective or preventive actions for each failure mode. As the objective of the risk assessment, results of the research can be used as input for the designers to improve their design and as inspection and surveillance objects for QC officers.

Unmanned aerial vehicles or often known as Drone / UAV are used for various missions, some of which are for aerial photography, monitoring, load testing, spraying fertilizers and so on. The performance of unmanned aircraft is supported by several aspects, one of which is the propulsion or engine of the aircraft. The Aeronautical Technology Research Center, BRIN, Indonesia has several series of unmanned aerial vehicles used for several missions. To support the missions that must be taken by unmanned aircraft, engine performance is one of the important factors for carrying out missions. In this study, engine testing will be carried out to see the performance of the engine by varying the octane rating of the fuel used. This test used an LSU-04 aircraft engine with a 3W-110i B2 engine type with a capacity of 110 cc and a propeller size of 26x8. Engine tests were carried out using 3 types of fuel with octane ratings of 92, 95 and 98. The data taken is engine speed data (rpm), thrust data and fuel consumption data. Tests and measurements were carried out at the highest rpm value of 6000 rpm and the test was carried out for 1 hour. From the test results, the results were obtained that the performance of the engine that has the largest thrust value is the one that uses fuel with an octane rating of 92, namely with a thrust value of 14.13 kgf, while the thrust value for fuel with an octane rating of 95 is 13.35 kgf, and the thrust produced in fuel with an octane rating of 98 is 13.06 kgf. Then from the results of measuring fuel consumption, the most economical value is an engine that uses fuel with an octane rating of 98, which consumes 1007 ml of fuel, while for fuel consumption with an octane value of 95 of 1028 ml and for an octane value of 92 of 1061 ml.Keywords: UAV, 3W-110i B2 Engine, 92 Octane, 95 Octane, 98 Octane, Engine Performance