A New Approach on the Physical Architecture of CubeSats & PocketQubes

The dominant architectural approach in CubeSats and PocketQubes is the use of modular physical units, each hosting (part of the) components of classical (virtual) subsystems. Many of these small satellites, however, also hostsubsystems or experiments with slightly alternative approach, e.g. with cellularization of components or the integration of functions from different virtual subsystems into a single physical unit. These concepts also have beeninvestigated and proposed by some studies on a much more rigorous implementation. Cellularization of complete satellite segments, the implementation of artificial stem cells, a satellite which comprises only of outer panels and plug-and-play technology are examples of these advanced concepts. While they offer promising advantages when implemented smartly as part of a new architecture, their disadvantages become dominant when such a concept isimplemented in a too rigorous and dogmatic manner. A smartly chosen hybrid of several concepts is investigated. An advanced outer but flat panel mixes the cellularized concept and integrates many components which interact with theoutside world. Internally, modular systems are still used, but some classical core subsystems can be integrated towards a single core unit. A lean approach on redundancy and electrical interfaces saves volume (for more payload volumeor smaller satellites) and reduces overall systems complexity. The overall impact on reliability is expected to be positive when taking development and testing time into account, but this requires more in-depth study to be validated

A New Approach on the Physical Architecture of CubeSats & PocketQubes

The dominant architectural approach in CubeSats and PocketQubes is the use of modular physical units, each hosting (part of the) components of classical (virtual) subsystems. Many of these small satellites, however, also host subsystems or experiments with slightly alternative approach, e.g. with cellularization of components or the integration of functions from different virtual subsystems into a single physical unit. These concepts also have been investigated and proposed by some studies on a much more rigorous implementation. Cellularization of complete satellite segments, the implementation of artificial stem cells, a satellite which comprises only of outer panels and plug-and-play technology are examples of these advanced concepts. While they offer promising advantages when implemented smartly as part of a new architecture, their disadvantages become dominant when such a concept is implemented in a too rigorous and dogmatic manner. A smartly chosen hybrid of several concepts is investigated. An advanced outer but flat panel mixes the cellularized concept and integrates many components which interact with the outside world. Internally, modular systems are still used, but some classical core subsystems can be integrated towards a single core unit. A lean approach on redundancy and electrical interfaces saves volume (for more payload volume or smaller satellites) and reduces overall systems complexity. The overall impact on reliability is expected to be positive when taking development and testing time into account, but this requires more in-depth study to be validated

Space Surveillance Network Capabilities Evaluation Mission

The last years saw the diffusion of nano, pico and femto satellite missions launched by multiple entities thanks to the launch cost reduction and the electronics miniaturization. Such missions usually present limited capabilities in terms of precise orbit determination and extremely small radar and optical cross-sections. Often these missions carry one or more laser retro-reflectors for precise orbit determination but precise orbital measurements cannot be found in the literature. Miniaturized GNSS receivers are also often carried out but due to the experimental nature of such missions, the reliability and time span of such measurements is limited, leaving radar tracking as the only reliable tracking method. Due to the size of such satellites, the signal-to-noise ratio of such radar measurements is typically low and satellite identification (when launched on ride-share launches with a hundred or more other satellites) proves difficult and time-consuming.Being these very small satellites at the edge of the radar detection capabilities and not providing independent orbit determination means, their position uncertainty could be quite significant, leading to an increased orbit collision perceived risk.With this paper, we present a dedicated small satellite formation, made by multiple nano and pico satellites to evaluate the space surveillance network tracking capabilities and limits. The formation is made by a 3U CubeSat to be deployed as part of a rideshare launch. The satellite would be equipped with multiple means to track it, including a GNSS receiver, a set of multiple laser retro-reflectors, and LEDs for optical, laser, and radar tracking, allowing to characterize also different detection means in terms of capabilities. Such a satellite is made of two independent smaller satellites that can be un-docked in orbit upon command, reducing the satellite size and cross-section. This would push the detection limit for the space surveillance networks starting from an already acquired object and with limited clutter around it. Independent laser and GNSS tracking would allow ground measurement validation and validate position estimations. Further pico-satellites would be deployed by each sub-satellite to further push the detection limits and validate up to which size objects are trackable (still optically, radar and GNSS), thanks to miniaturized GNSS receivers already flown by several other missions.Sub-satellite separation is implemented upon command to ensure the process can be followed and executed at lower altitudes to limit the orbital lifetime of eventually hard-to-track small objects that could worsen the space debris problem. Ground characterization (in terms of optical and radar properties) will be performed, also including polarimetric measurements used to identify the separate satellites. All these technologies together would contribute to creating a unique tool to estimate the tracking capabilities of multiple instruments, specifically tailored for very small objects, the hardest to track, as compared to other characterization activities performed on much bigger objects.Space Systems Egineerin

A New Approach on the Physical Architecture of CubeSats & PocketQubes

The dominant architectural approach in CubeSats and PocketQubes is the use of modular physical units, each hosting (part of the) components of classical (virtual) subsystems. Many of these small satellites, however, also hostsubsystems or experiments with slightly alternative approach, e.g. with cellularization of components or the integration of functions from different virtual subsystems into a single physical unit. These concepts also have beeninvestigated and proposed by some studies on a much more rigorous implementation. Cellularization of complete satellite segments, the implementation of artificial stem cells, a satellite which comprises only of outer panels and plug-and-play technology are examples of these advanced concepts. While they offer promising advantages when implemented smartly as part of a new architecture, their disadvantages become dominant when such a concept isimplemented in a too rigorous and dogmatic manner. A smartly chosen hybrid of several concepts is investigated. An advanced outer but flat panel mixes the cellularized concept and integrates many components which interact with theoutside world. Internally, modular systems are still used, but some classical core subsystems can be integrated towards a single core unit. A lean approach on redundancy and electrical interfaces saves volume (for more payload volumeor smaller satellites) and reduces overall systems complexity. The overall impact on reliability is expected to be positive when taking development and testing time into account, but this requires more in-depth study to be validated.Space Systems EgineeringSpace EngineeringClean Roo

A New Approach on the Physical Architecture of CubeSats & PocketQubes

The dominant architectural approach in CubeSats and PocketQubes is the use of modular physical units, each hosting (part of the) components of classical (virtual) subsystems. Many of these small satellites, however, also host subsystems or experiments with slightly alternative approach, e.g. with cellularization of components or the integration of functions from different virtual subsystems into a single physical unit. These concepts also have been investigated and proposed by some studies on a much more rigorous implementation. Cellularization of complete satellite segments, the implementation of artificial stem cells, a satellite which comprises only of outer panels and plug-and-play technology are examples of these advanced concepts. While they offer promising advantages when implemented smartly as part of a new architecture, their disadvantages become dominant when such a concept is implemented in a too rigorous and dogmatic manner. A smartly chosen hybrid of several concepts is investigated. An advanced outer but flat panel mixes the cellularized concept and integrates many components which interact with the outside world. Internally, modular systems are still used, but some classical core subsystems can be integrated towards a single core unit. A lean approach on redundancy and electrical interfaces saves volume (for more payload volume or smaller satellites) and reduces overall systems complexity. The overall impact on reliability is expected to be positive when taking development and testing time into account, but this requires more in-depth study to be validated.Green Open Access added to TU Delft Institutional Repository ‘You share, we take care!’ – Taverne project https://www.openaccess.nl/en/you-share-we-take-care Otherwise as indicated in the copyright section: the publisher is the copyright holder of this work and the author uses the Dutch legislation to make this work public.Space Systems EgineeringSpace EngineeringClean Roo

Da Vinci Satellite – Roll Of The Dice

The Da Vinci Satellite project is a non-profit initiative started at the Delft University of Technology to inspire and enthuse the youth to learn more about technology and space travel. The team does this by focussing on demystifying space and making it a fun and engaging subject. The non-profit student team is divided into different sub teams, two of which are the technical team and the educational team. The technical team has been building a 2U CubeSat with two payloads that have been designed to support educational packages for children from primary schools and high schools. The educational team works to make these educational modules available for schools all around the world such that children have the opportunity to interact directly with space via The Da Vinci Satellite.Space Systems Egineerin

A New Electrical Power System Architecture For Delfi-PQ

Due to strict constraint regarding the volume of a PocketQube (50x50x50 mm) it is crucial to reduce the space that is consumed by the satellite bus subsystems. This paper focuses on a new architecture for the electrical subsystem in order to reduce its volume and increase the usage of empty surfaces inside the satellite. This increment in volume efficiency is going to be achieved by splitting the electrical power system on different surfaces and reducing the number of required voltage regulators. This modular approach is going to be realized by two main steps. First, removing the regulated bus from the satellite and delivering an unregulated bus to the subsystems. This will also give flexibility to other subsystems to use a voltage level which are more suitable for their requirements. Secondly, the internal side of the solar panels’ are going to be used for MPPT (maximum power point tracking) circuits, actually achieving a distributed power generation system, similar to ground-based solar power generation systems. The battery board is going to be a separate board with its dedicated communication lines and will also act as an interface between the solar panels and power distribution board via simple spring loaded connectors. This latter solution helps reducing dramatically the number of cables in the satellite,thus simplifying integration. The main objective of this work is turning the EPS (electrical power system) into a more flexible, scalable and volume-efficient system by a physical relocation of its components and a lean approach. The new EPS will be functionally and environmentally tested in a flight representative satellite model with the aim to verify its simplification in integration, assess its true performance as well as its reliability during launch vibration which especially includes spring-loaded connectors.Clean RoomSpace Systems EgineeringSpace Engineerin

Delfi-PQ: The first pocketqube of Delft University of Technology

Delft 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 Surveillance Network Capabilities Evaluation Mission

The last years saw the diffusion of nano, pico and femto satellite missions launched by multiple entities thanks to the launch cost reduction and the electronics miniaturization. Such missions usually present limited capabilities in terms of precise orbit determination and extremely small radar and optical cross-sections. Often these missions carry one or more laser retro-reflectors for precise orbit determination but precise orbital measurements cannot be found in the literature. Miniaturized GNSS receivers are also often carried out but due to the experimental nature of such missions, the reliability and time span of such measurements is limited, leaving radar tracking as the only reliable tracking method. Due to the size of such satellites, the signal-to-noise ratio of such radar measurements is typically low and satellite identification (when launched on ride-share launches with a hundred or more other satellites) proves difficult and time-consuming.Being these very small satellites at the edge of the radar detection capabilities and not providing independent orbit determination means, their position uncertainty could be quite significant, leading to an increased orbit collision perceived risk.With this paper, we present a dedicated small satellite formation, made by multiple nano and pico satellites to evaluate the space surveillance network tracking capabilities and limits. The formation is made by a 3U CubeSat to be deployed as part of a rideshare launch. The satellite would be equipped with multiple means to track it, including a GNSS receiver, a set of multiple laser retro-reflectors, and LEDs for optical, laser, and radar tracking, allowing to characterize also different detection means in terms of capabilities. Such a satellite is made of two independent smaller satellites that can be un-docked in orbit upon command, reducing the satellite size and cross-section. This would push the detection limit for the space surveillance networks starting from an already acquired object and with limited clutter around it. Independent laser and GNSS tracking would allow ground measurement validation and validate position estimations. Further pico-satellites would be deployed by each sub-satellite to further push the detection limits and validate up to which size objects are trackable (still optically, radar and GNSS), thanks to miniaturized GNSS receivers already flown by several other missions.Sub-satellite separation is implemented upon command to ensure the process can be followed and executed at lower altitudes to limit the orbital lifetime of eventually hard-to-track small objects that could worsen the space debris problem. Ground characterization (in terms of optical and radar properties) will be performed, also including polarimetric measurements used to identify the separate satellites. All these technologies together would contribute to creating a unique tool to estimate the tracking capabilities of multiple instruments, specifically tailored for very small objects, the hardest to track, as compared to other characterization activities performed on much bigger objects