Mission Analysis of a Double Unit CubeSat, BeEagleSat

With the advent of the first satellite Sputnik, a new era for mankind has opened. With this new era, the concepts of satellites have become more important than ever for the amenities of the modern civilization that we enjoy today. However, there is still a great need for improvement in satellite technology and this can be best achieved by various Nanosatellite research and deployment programs. Due to its specific nature and its operational dynamics related to its vast application, a Nanosatellite programme can be very efficiently and effectively implemented under a University's R&D programme. Until today, many Nanosatellite have been successfully developed, launched and used by various Universities all across the world and many useful information and experience have come out of these activities. In this particular paper, a case study analysis of an ideal Nanosatellite research and deployment program for universities will be shown. This paper can serve as a fundamental case study of a Nanosatellite program and academic and research organizations can use this as a guideline for their programs. An optimal near polar, low earth orbit is calculated for this Nanosatellite along with its structural configurations. The orbit is calculated keeping in mind certain geographical constraints which defines the basic objectives of the mission. Moreover, different attitude adjustments systems are explored in order to create the most stable configuration in orbit. In addition, possible payload configurations for this particular case study will be analyzed and the corresponding launch systems along with its costs will be explored. The main focus will be on creating the most optimal configuration with the minimum of production and launching costs for the Nanosatellite. Thus, the payload capability as well as the launch configuration along with the orbit will be calculated accordingly. This paper hopes to demonstrate the technical aspects as well as the educational aspects of a University Cubesat project

Space missions in the past were focused on traditional large costly satellites, but are now transitioning to smaller satellites. These satellites include nano-satellites, which is the object of this thesis, becoming one of the most exciting, diverse and fast paced satellites of today. In this study, CubeSats were investigated, focusing on double unit and triple unit CubeSats and deployment effects on CubeSat systems. The deployment effects on CubeSats depend on numerous uncertainties. However, with assumptions for some parameters, analyses can give approximate results. There are also some uncertainties for orbit perturbations such as atmospheric drag, earth gravity and solar radiation pressure which were briefly clarified. The objectives of this thesis are minimizing the risk of collision between CubeSats and deployer and gaining knowledge to optimize the lifetime of CubeSats. To accomplish these objectives specifications of these CubeSats were given and orbital elements were explained. Moreover, each scenario for the cases described reference CubeSats and simulation parameters are briefly explained. Afterwards, with the assumed parameters, some simulations performed. There are two main parts for simulations which are deployment effects to lifetime of CubeSats and collision risks for CubeSats deployment. To accomplish these simulations the two part divided for each part has 2 cases. These cases are altitude effects and ejection time for lifetime prediction part, direction difference and multiple ejection cases for obtaining collision risks part. Deployment altitude effects were explored with taking ballistic coefficient, atmospheric drag, and gravity effects into account. By using STK Lifetime Tool, lifetime for all CubeSats were calculated. Ejection time for CubeSats were changed to observe the effects on them. Solar activity effects are also considered and explained briefly. Deployment directions and multiple ejection cases were investigated with several simulations and some of them are shown. By the help of these simulations, the risk pie for CubeSats deployments were obtained. This thesis proposes knowledge for optimizing lifetime and proper deployment directions which are less risky against collision between CubeSats and deployer. The performed simulations also give some deployment system constraints.

2011 Aerospace Conference, 2011

For a long while, launching satellites for the purpose of research and technology demonstration largely remained with national space agencies and government organizations as the huge funding requirements inhibited the initiation of such projects at university level. It was this idea of providing, at university level, cheap access to space that prompted the design of miniaturized versions of satellites for research purposes. Specifications of cubeSat, a picosatellite, were defined to provide easy access to space for educational and research institutions. The improvement in engineering technologies and miniaturization of physical components has enabled design, development and launch of such small low-cost spacecrafts and to date, more than 60 universities, institutions and research organizations have taken part in cubeSat program since its inception in 1999[1]. Institute of Space Technology (IST) adopted the concept of cubeSat development by initiating the satellite program, ICUBE. ICUBE is the premier student satellite program of any educational institution/university in Pakistan. The first satellite of this program is named ICUBE-1. Successful launch of ICUBE-1 and establishing its communication link with the ground are the primary goals of this mission. The satellite has a passive attitude control system and will carry a CMOS camera for experimental purposes. In this paper, we will discuss in detail the design philosophy of ICUBE-1, followed by the preliminary design and analysis of all its subsystems. The required testing and technical support facilities are discussed before the final conclusions. 12

4th Symposium on Space Educational Activities, 2022

is a student team of University of Padova with the aim to participate to the ESA Fly Your Satellite! (FYS!) programme and to launch for the first time at University of Padova a CubeSat made by students. The proposed mission has three independent objectives: (1) to collect in-situ measurements of the submm space debris environment in LEO, (2) to study the micro-vibration environment on the satellite throughout different mission phases, (3) to do precise orbit determination through laser ranging and evaluate procedures for fast satellite Pointing, Acquisition and Tracking (PAT) from ground. The proposed technological experiments aim to obtain data that will enrich the current knowledge of the space environment and will provide precious information useful for the further development of some research projects currently performed at University of Padova. In order to reach the objectives, in these years the activities of the teams aimed to develop a 2U CubeSat equipped with three payloads. The first payload is an impact sensor that will be placed on one of the outer faces of the satellite and will be able to count the number of debris impacting the spacecraft thus being able to measure the energy/momentum transferred to the satellite. The second one is a Commercial Off The Shelf (COTS) sensor that measures the micro-vibrations experienced by payloads in a CubeSat in different mission phases. The third one consists in a number of COTS Corner Cube Retroreflectors that will be placed onboard the satellite. Thanks to this, Satellite Laser Ranging (SLR) will be done to collect data on the satellite range and range rate using a facility currently under development at University. This paper presents the mission objectives and motivations. In addition, the mission phases and the preliminary design of the CubeSat reached during the activities of the project are shown. Particular attention is given to the payloads which are the most challenging aspect of this project.

Acta Astronautica, 2014

The paper deals with the mission analysis and conceptual design of an interplanetary 6U CubeSats system to be implemented in the L 1 Earth-Sun Lagrangian Point mission for solar observation and in-situ space weather measurements. Interplanetary CubeSats could be an interesting alternative to big missions, to fulfill both scientific and technological tasks in deep space, as proved by the growing interest in this kind of application in the scientific community and most of all at NASA. Such systems allow less costly missions, due to their reduced sizes and volumes, and consequently less demanding launches requirements. The CubeSats mission presented in this paper is aimed at supporting measurements of space weather. The mission envisages the deployment of a 6U CubeSats system in the L 1 Earth-Sun Lagrangian Point, where solar observations for in situ measurements of space weather to provide additional warning time to Earth can be carried out. The proposed mission is also intended as a technology validation mission, giving the chance to test advanced technologies, such as telecommunications and solar sails, envisaged as propulsion system. Furthermore, travelling outside the Van Allen belts, the 6U CubeSats system gives the opportunity to further investigate the space radiation environment: radiation dosimeters and advanced materials are envisaged to be implemented, in order to test their response to the harsh space environment, even in view of future implementation on other spacecrafts (e.g. manned spacecrafts). The main issue related to CubeSats is how to fit big science within a small package-namely power, mass, volume, and data limitations. One of the objectives of the work is therefore to identify and size the required subsystems and equipment, needed to accomplish specific mission objectives, and to investigate the most suitable configuration, in order to be compatible with the typical CubeSats (multi units) standards. The work has been developed as collaboration between Politecnico di Torino, Sapienza University of Rome, "Osservatorio Astrofisico di Torino-INAF" (Astrophysical Observatory of Torino) and DLR (Deutsches Zentrum für Luft-und Raumfahrt) in Bremen.

International Journal of Computer Applications

CubeSat technology has become a tool to encourage engineering collaboration, to train students providing them with a platform for real-world space exploration. This provides advancements in the aerospace industry as well. These satellites are made for a rather specific purpose than a conventional heavyweight satellite thereby reducing the cost. This paper discusses Cube Satellites, their design, salient features along with different applications and advancements made in the field of CubeSat technology thus providing an overview of a general analysis of CubeSat technology.

Journal of Aerospace Technology and Management, 2017

AbstrAct: Because they are inexpensive platforms for satellites, CubeSats have become a low-cost way for universities and even developing countries to have access to space technology. This paper presents the ITASAT design, particularly the Attitude Determination and Control Subsystem, the Onboard Software, and the Assembly, Integration and Testing program. The ITASAT is a 6U CubeSat nano-satellite in development at the Instituto Tecnológico de Aeronáutica, in São José dos Campos, Brazil. The platform and its subsystems will be provided by industry while the payloads are being designed and developed by the principal investigators. The ITASAT Attitude Determination and Control Subsystem will rely on a 3-axis magnetometer, 6 analog cosine sun sensors, 3-axis MEMS gyroscopes, 3 magnetic torque coils, and 3 reaction wheels. The Attitude Determination and Control Subsystem operating modes, control laws, and embedded software are under the responsibility of the Instituto Tecnológico de Aeronáutica. A Kalman filter shall be employed to estimate the quaternion attitude and gyroscope biases from sensor measurements. The Attitude Determination and Control Subsystem operating modes are the nominal mode, with geocentric pointing attitude control and the stabilization mode, in which only the satellite angular velocity is controlled. The nominal mode will be split into 2 sub-modes: reaction wheel control plus magnetic wheel de-saturation and 3-axis magnetic attitude control. Simulation results have shown that the attitude can be controlled with 1-degree accuracy in nominal mode with the reaction wheels, but these errors grow as much as 20 degrees or higher with the 3-axis magnetic control.

The paper deals with an interplanetary CubeSats mission to Earth-Sun Libration point. CubeSats are an interesting alternative to larger science satellites to accomplish both scientific and technological tasks in deep space, as proved by the growing interest in this kind of application within the scientific community and, most of all, at NASA. Indeed such systems allow less costly missions, due to their reduced sizes and volumes, and consequently less demanding launches requirements.

2018

This work evaluated the power, propulsion, and telecommunications subsystems for CubeSats to support two missions in low earth orbit; a Rendezvous (formation flying) mission and a mission to explore extreme low earth orbit. After selecting a baseline set of hardware for each spacecraft, trade studies were performed to evaluate options. Chemical and electric propulsion options for both primary and attitude control were considered. Thrusters for attitude control were compared with reaction wheels and performance compared for both required maneuvers and disturbance torque compensation. Power subsystem trades considered different solar arrays and battery options. Telecommunication subsystem trades compared data link budgets for different orbit inclinations and receiving station networks. v 3.

1990

On January 22, 1990, Ariane V-35 placed four Microsat spacecraft into orbit. The orbit achieved is nearly perfectly sunsynchronous at 800 km altitude. The satellites, cubic structures measuring only 23 cm per side, were developed by the Radio Amateur Satellite Corporation of North America (AMSAT-NA). The time required to complete the project, from conception to delivery of the four satellites to Kourou, was exactly two years. Each satellite in orbit has a different mission and is performing in accordance with its intended design, although additional software is still being written to enhance the operating characteristics for each mission. This paper reviews the design objectives of the four spacecraft and summarizes their in-orbit performance against these prelaunch technical objectives. The level of technology employed by the Microsat spacecraft is briefly discussed and the software approach taken in implementing a real-time, multitasking operating system is summarized. The paper reviews the AMSAT experience as the first payload user group of the Ariane ASAP structure. Some of the findings regarding the cu"ent technology and how it may be expanded to fulfill other mission needs has been touched upon. 1 Members of the AMSAT-NA Microsat design team.