This paper focuses on the capabilities of equipment known as Mass Properties Measurement (MPM) to calculate the center of gravity (CG) of a jig or an adaptor, which is used for mounting a structural model of Malaysian satellite, RazakSAT on POI-1000M Spin Balance Machine. The adaptor needs to be designed accurately to precisely accommodate the bolt sizes in both sides of the Device Under Test (DUT) side and the rotary plate side. In other words, the adaptor must be able to act as a good interface plate. A Malaysian research institute, SIRIM Berhad was chosen to undertake the design and manufacturing of the adaptor according to the specifications made by ANGKASA. The list of requirements of MPM should be considered during measurement to have optimum results, so that the satellite fixture onto the rotary table can be preceded for further calculations. Space Electronics (SE), the manufacturer for this MPM machine, has provided the control system for operators to calculate the required measurement such as CG, moment of inertia (MOI) and Product of Inertia (POI). Results confirmed that the simulation and experimental values are successfully obtained.

Reverberation Acoustic Test Facility (RATF) is a one of the mechanical satellite testing facility in the Assembly, Integration and Test Centre at National Space Agency (ANGKASA). This is the reverberation type of chamber with external volume at 999.5m3, has the capability to regenerate high intensity acoustic noise ambiance that will be experienced during the launching stage. This paper will describe on reverberation chamber characteristics, the noise generating system and capabilities, and the chamber configuration for high intensity acoustic testing in empty chamber condition. This paper recommends the measurement setting for three variant spectrum levels in generating high-intensity acoustic noise from 130dB to 155dB with center frequencies from range 31.5Hz to 1250Hz.

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One of the necessary parts of CubeSat’s design is the thermal analysis. It will provide the operating temperatures and their distribution for all devices inside the CubeSat. For decision, which temperature standard can be used for components it is necessary to know the maximum and the minimum value of the temperature. In virtue of these results the position of the all devices must be also optimized. Some methods of the thermal control are also proposed. Contrary to most subsystems the thermal subsystem is not independent of the others. All elements in the spacecraft have an influence on the thermal housekeeping by either emitting or absorbing energy or both respectively. The objective of thermal subsystem is to ensure that the spacecraft operate within the spacecraft operating temperature range. There are two types of thermal control technique; passive and active. Due to the size and power constraint of CubeSat, passive thermal control will be more suitable but analysis must be done in order to know that passive control is sufficient. The FEA methodology would be utilized in order to determine the spacecraft operating temperature within the range. To accomplish this, MSC Nastran Patran software will be used as the FEA modeling tool. The MD Patran will act as preprocessing tool whereas MD Nastran will act as post processing tool. If the simulated thermal range is deviates, temperature sensors and heaters will be mounted on the CubeSat to monitor the deviation. Alternatively, mounting Kapton tape onto the CubeSat structure and laying gold coating would be another method to maintain the desired temperature range. The design of the thermal system shall be based on passive methods. This approach is vital to avoid power consumption in cases where it would not be necessary. As conclusion the thermal subsystem is designed to operate the spacecraft throughout its mission phases without any failure.

This paper focuses on making some review and observation on the performance of equipment named Mass Properties Measurement System (MPMS) which capable to calculate the center of gravity (CG), moment of inertia (MOI) and Product of Inertia (POI) of a satellite. Before approving to receive such a huge machine/equipment consist of mechanical and electronic structure, National Space Agency (ANGKASA) which acts as a Malaysian Government Agency has to go through an Acceptance Test Procedure (ATP) to compare with the factory acceptance result on its performance review. The Factory Acceptance Test (FAT) for this machine has been done earlier in United States (USA) as the equipment is manufactured in Connecticut, USA. This ATP is responsible on determining the requirements of a specification or contract are met or not by conducting test which is commonly applied for engineering and its various subdisciplines and the test have been witnessed by a Malaysian Research Institute; SIRIM Berhad, local and international contractors as well as the principal or manufacturer of the equipment itself and took place in ANGKASA, Banting, Selangor. It may involve chemical tests, physical tests, or performance tests by comparing the results with FAT [1].POI-1000M Rotary table, a rotor, deadweights, a compressor and a beam are the main components to be used for the acceptance performance test assisted by a control system for operators to calculate the desired measurements. Results confirmed that the ATP and FAT results are finally been compared and the equipment is successfully approved.