Aircraft are currently quite popular transportation, due to its ability to utilize air space as a flight path, so that it can be efficient in mileage. To support the safety of airplane passengers, every component on the aircraft must pass the test. One of them in the aircraft windshields that are prone to collisions with other objects. In accordance with the regulations in the Civil Aviation Safety Regulation (CASR) the windshield must withstand the impact load of a 0,91 kg bird. In this simulation, the material shape of the bird uses the EOS Tabular type. For modeling windshields, frame¸ gaskets and birds use a general method for solid materials, namely the Lagrangian method. Rubber used as gasket material with mooney rivlin for modeling material behavior. the polymethyl methacrylate and aluminum alloy 7075 T6 material is used in the windshield and frame. Numerical modeling is validated using analytical results. The gasket thickness of 2 mm produces the most optimum energy absorption. The use of gaskets on the windshield does not have a significant effect on the windshield because the gasket on average is only able to absorb 5% of the total energy absorbed by all windshield parts. The collision parameter that produces the greatest failure occurs at a speed of 87,5 m/s with -15o angle. The area that is most prone to material failure is in the area of the upper bolt hole.

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-. This research was conducted based on data obtained during testing at LAPAN (Lembaga Antariksa dan Penerbangan Nasional), where there was a case that became a concern. The test is about the free fall test, which results in a deflection that is considered too large. From these results it was decided to investigate further. This free fall test uses impact testing where a material is measured for its shock load resistance. Impact testing simulates the operating conditions of a material where the loading that occurs is not only in static conditions but also occurs in dynamic conditions. In the free fall test, a test was carried out to measure and see the resistance of the landing gear and crash box in receiving dynamic loads, when the aircraft landed. The main purpose of simulating this tool is for research and development of the free fall test equipment itself, as well as the design of the landing gear of the LSU (Lapan Survaillance UAV) drone in the future. The impact platform on the free fall test equipment plays an important role in impact testing, where the deformation of the plate holder will be converted by the load cell, into a signal received by the acquisition system. So it is designed to fit the existing needs. In this test equipment, the test object is given a load (50 kg and 200 kg), height (4.72 m and 1,204 m), so that it reaches a velocity (9,623 m/s and 4,861 m/s) with impactor crash box geometry and main landing gear as well as plate holder design based tools in the field. Based from testing, impact, and analysis using the finite element method in this study, it was found that the deflection value was 1.771 mm which reduced 94.61% for the crash box case and the deflection value was 2.696 mm with a reduction value of 87.85 % for the main landing gear case from the existing initial design. Keywords: Free fall test equipment, impact platform, landing gear, plate mount, main landing gear, crash box, finite element method, LSU.

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