114 research outputs found
Gadih Ranti" penggarapan komposisi musik untuk orkestra.
No full textPenggarapan komposisi usik ini bertujuan untuk mengekspresikan nilai moral dari cerita rakyat Minangkabau "kabah gadih ranti" dan untuk mewujudkan penggabungan unsur musikal musik tradisional Minangkabau dan musik Barat.Metode yang dipakai dalam komposisi musik ini adalah eksplorasi yaitu menetapkan ide dan judul karya serta improvisasi/eksperimentasi yaitu menemukan integritas dan kesatuan terhadap berbagai percobaan yang dilakukan dan farming (pembentukan
Configuration management in nanosatellites projects: Evalaution of Delfi-C3 and consequent adaption for Delfi-n3Xt
No full textThe Delfi-C3 nano-satellite was launched in April 2008 and the development of its successor, the Delfi-n3Xt, is ongoing. Both of these projects are conducted by students from the Delft University of Technology as a corporation between the Aerospace Engineering Faculty, the Faculty of Electrical Engineering, Mathematics and Computer Science and several industrial partners. This paper provides a description and evaluation of the configuration management that was applied at the Delfi-C3 nano-satellite project. It was done by comparing the initial intentions with the final implementation. More specifically, the interface control, configuration control, requirements management and the documentation management are discussed. An evaluation of the configuration management of the Delfi-C3 project was appropriate, as based on the lessons that were learned an improved configuration management approach for the Delfi-n3Xt project had to be defined. The need for simplification and increased consistency on all the aspects of the configuration management were the main conclusions of this evaluation. Basically, deciding on a configuration-strategy and controlling its consistency as early as possible creates a framework on which the rest of the systems engineering tasks can be build. To provide some insight in the practical implementation of the approach, it will be presented how it was used for the initial design of the Electrical Power System (EPS). Finally, the benefits and remaining issues will be discussed.Space EngineeringAerospace Engineerin
Optimized three-unit cubesat structure for Delfi-n3Xt
No full textFor the Delfi-n3Xt mission, follow-up to CubeSat Delfi-C3 [1] of Delft University of Technology, several concepts concerning the Structural Subsystem (STS) have been analysed. One of the main objectives is to reduce the time needed for assembly, integration and testing, and to improve handling capabilities. Lessons learned from Delfi-C3 have been taken into account in a trade-off between several candidate design options. A brief description of the structure of Delfi-C3 is given. Afterwards the candidate options for the STS of Delfi-n3Xt are discussed, followed by the final structure selection and implementation.Space EngineeringAerospace Engineerin
Mechanical Design and Arrangement of nanosatellite Delfi-n3Xt
No full textDesign of the different elements in the Structural Subsystem of Delfi-n3Xt. This is done by implementation of the lessons learned and solutions to problems encountered with Delfi-C3. First different options for CubeSats are considered and traded. Afterwards the detailed design is treated. Also the arrangement of the different subsystems and payload is discussed, since Delfi-n3Xt has a limited volume.Space Systems EngineeringAerospace Engineerin
Advancing nano-satellite platforms: The Delfi Program
No full textThe Delfi Program aims to launch a nano-satellite every 2.5 years with the objectives to give the best education for space engineering, to test and qualify novel space technology and to enhance the nanosatellite platform to open doors for new applications. With Delfi-C3 in orbit, Delfi-n3Xt in development for a launch in 2010 and preliminary plans for the future, TU Delft wants to put itself at the top level of small satellites engineering. Although the size of nano-satellites puts some constraints on the potential performance and applications, the theoretical limits are still far ahead and nano-satellites might have more potential than typically assumed. This potential can only be made possible if the development goal for each satellite matches the availability of resources and a realistic planning in time.Space EngineeringAerospace Engineerin
Delfi-n3Xt: End-to-end Analysis and Design of the Satellite Communication Links
No full textSystem design of the communication subsystem of the Delfi-n3Xt nanosatellite. Delfi-n3Xt is the successor of the Delfi-C3 nanosatellite.Space Systems EngineeringAerospace Engineerin
Implementation of a reliable date bus for the Delfi nanosatellite programme
No full textThe Delfi-n3Xt nano-satellite is the second Dutch universitysatellite currently being developed at the Delft University of Technology (TUD) as successor of the Delfi-C3 that has been successfully launched in April 2008. Compared to Delfi-C3, the Delfi-n3Xt platform provides significant advancements to the platform: a high-speed downlink, three-axis attitude control and a single-point of failure free battery. In total five payloads will be flown that generate a considerable larger amount of data compared to Delfi-C3that implies, as well, a robust and adequate design for the data handling system that interlinks the various embedded systems on board. This paper examines the design and implementation of a fault tolerant data bus architecture as part of the satellite Command and DataHandling Subsystem (CDHS). Delfi-C3 carries an I2C protocol based implementation that currently experiencesproblems with data corruption and timeouts and is therefore subject of scrutiny andanalysis in this paper. In particular, the relationship between error rates, master-slave speeds and processing overheads is evaluated in detail. After a tradeoff study betweenseveral bus standards for Delfi-n3Xt, the choice is once again an I2Cimplementation, but with significant hardware and software improvements over the previous design. In terms of hardware, shielding and bus protection considerationsare included in the very early stages of design. With respect to software, special care is taken in dealing with the varying clock speeds between slaves and masters, correct data handling and the feasibility of error detection and correction codes, as the amount of data generated by thepayloads of the Delfi-n3Xt is significantly higher. The final result of this research is the selection of the most adequate reliability techniques and their implementation. This I2Cbus targeted middleware is intended for usage in the complete Delfi nanosatelliteprogramme at TUD and for several other space applications in general.Space EngineeringAerospace Engineerin
Improved command and data handling system for the Delfi-n3Xt nanosatellite
No full textThe Delfi-C3 nanosatellite successor, Delfi-n3Xt, is currently under development at Delft University of Technology. This nanosatellite based on a three-unit CubeSat form factor has been improved through the implementation of a high-speed downlink, three-axis active attitude control and a single-point-failure free implementation of batteries in the electrical power system. Failure of the batteries will therefore not lead to failure of the primary mission as has, in the past, been the case with many other nanosatellite missions. The functional analysis and design of the command and data handling system (CDHS) of Delfi-C3 and the improved CDHS architecture of Delfi-n3Xt are presented in this paper. The main design drivers for the CDHS of Delfi-C3 were the available technology and the absence of batteries. These design drivers enforced specific hardware components which, however, resulted in undesired behavior during integration and testing. In particular low-speed devices on the bus were suppressing the performance of the CDHS and the high-speed systems of Delfi-C3. Delfi-n3Xt requires a higher performance since much more data will be produced by the five payloads, stored and sent down with a high-speed downlink. The architecture presented in this paper complies with this, while it is based on the architecture of Delfi-C3.Space EngineeringAerospace Engineerin
Delfi-PQ: The first pocketqube of Delft University of Technology
No full textDelft University of Technology has embarked on PocketQubes to showcase as the next class of miniaturized satellites. In the past decade, CubeSats have grown towards a successful business with mature capabilities. PocketQubes, however, are still in their infancy. The small size of the PocketQubes will trigger innovations in miniaturization and will force one to think differently about space technology. It is not sufficient to simply down-scale existing concepts used in CubeSats, there is a necessity to develop and qualify completely new components through which new applications can be enabled in the future.The new satellite platform, called Delfi-PQ, inspired by the success of previous Delfi satellite projects is seen as an opportunity for innovation and offers research challenges in the miniaturization field of systems and components. The focus of this paper is to highlight those innovations and challenges, and to communicate the progress that has been made with respect to building a core platform and standardized bus.The mission of Delfi-PQ is to demonstrate a reliable core bus and outer structure for a three unit PocketQube that shall be tested in flight as a first iteration of a series of PocketQubes to be developed by Delft University of Technology. The core bus shall fit in one unit - 1P (50x50x50mm), having as aim that after further miniaturization and optimization, the second unit shall contain an advanced subsystem (e.g. advanced Attitude Determination and Control System - ADCS) and the third unit shall consist of a scientific payload (e.g micro-propulsion, lensless camera). For Delfi-PQ, the focus was on the miniaturization process and on the structure of the PocketQube. The core platform of the first Delfi-PQ consists of the Electrical Power System (including two 3.7V batteries and solar panels with two cells/each X-Y face), On-board Computer, Communications System, ADCS (including two magnetorquers and three magnetometers), as well as: temperature sensors and two different sensors for assessing the rotational speed of the PocketQube.Space Systems EgineeringClean RoomSpace Engineerin
Design status of the Delfi-Next nanosatellite project
No full textDelfi-Next is the second project within the Delfi nanosatellite development program of Delft University of Technology. It will provide students hands-on experience, facilitate technology demonstration for innovative miniaturized space technology from the Dutch space sector and allow advancements in satellite bus performance compared to its predecessor Delfi-C3. This paper will describe the mission and provides insight in the design status and trade-offs of each bus subsystem at September 2010. A micropropulsion system from TNO, an in-orbit configurable radio from ISIS BV and amorphous silicon solar cells will be demonstrated onboard Delfi-Next. The electrical power subsystem consists of deployable solar panels, a central power management unit, a battery system and local power regulation units on each printed circuit board. The central power management unit uses redundant maximum power point trackers for each solar panel and distributes the acquired power to a standard system bus on a fixed single supply voltage of 12V, the battery system and a shunt for excessive power. The communication subsystem consists of two redundant radios transmitting a continuous 1.2 9.6 kbps signal on a 145 MHz carrier frequency, a high data rate S-band transmitter, a receiver and a set of deployable antennae in a turnstile configuration. The downlink is received by a global distributed ground station network consisting of several universities and radio amateurs. Onboard data handling is performed by a hot redundant onboard computer, which manages and acquires measurement data from local subsystem microcontrollers by means of an I2C data bus. Because the standard implementation of I2C lacks failure tolerance it is supplemented with bus buffers on each local system which will isolate malfunctioning nodes from the main bus when necessary. A custom designed spacecraft structure optimized for accessibility will provide the basis for all physical subsystems which are made compliant to a standardized form factor. The structure complies with the outer dimensions of a triple-unit CubeSat. Passive thermal control based on heat sinks and optical properties of surface materials will keep components and subsystems within the required thermal range. Attitude determination and control will be performed by a suite of sensors, actuators and processing algorithms to demonstrate active attitude control functionality as a baseline for future Delfi missions. Future Delfi missions to demonstrate formation flying capabilities are foreseen, potentially within the QB-50 network for thermospheric research or demonstration missions for the OLFAR moon-orbiting radio telescope.Space EngineeringAerospace Engineerin
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