CERES :: Browsing by Author "Kingston, Jennifer"

Browsing by Author "Kingston, Jennifer"

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Open Access
6U CubeSat design for Earth observation with 6.5m GSD, five spectral bands and 14Mbps downlink
(Royal Aeronautical Society, 2010-11-30T00:00:00Z) Tsitas, S. R.; Kingston, Jennifer
The design of a 6U Cube Sat including spacecraft systems and imagine payload is described for an Earth observation mission. From a Sun synchronous orbit at an altitude of 600km the design enables imaging with a 6.5m GSD, an optical MTF (on axis) of >59% at half Nyquist and >35% at Nyquist, a 26km swath, 12 bit digitisation and SNR of 120-200:one in five spectral bands; blue, green, red, red edge and near infrared. Data can be downlinked at the rate of 14 Mbps to a 3.7m S band ground station. This design allows an 8kg Cube Sat to perform Earth observation missions equivalent to those of current 50-150kg microsatellites, with a corresponding reduction in cost.
Open Access
Challenges in transforming manufacturing organisations into product-service providers
(MCB University Press, 2010-04-01T00:00:00Z) Martinez, Veronica; Bastl, Marko; Kingston, Jennifer; Evans, Stephen
Purpose – The purpose of this paper is to present challenges experienced by UK manufacturing companies undergoing a servitization journey to becoming product- service providers. Design/methodology/approach – The paper uses an exploratory single-case study approach based on semi-structured interviews, and archival data. A total of 22 senior managers were interviewed from the product-service provider and its two suppliers, resulting in more than 400 pages of interview data. Data were analysed through an inductive research analysis by an emergent identification of patterns. Findings – This research identifies critical and frequent challenges experienced by UK manufacturing companies undergoing a servitization journey to becoming product-service system (PSS) providers. They are condensed into five pillars, which constitute the architecture of challenges in servitization. The architecture of challenges in servitization provides a full description of the strategy and operations of PSSs. Research limitations/implications – This is qualitative research based on a single case study. Given the nature of research design, the identified patterns cannot be used as a predictive tool. Practical implications – This research provides a framework to understand, analyse and plan the strategic transformations to more highly servitized organisational forms. Originality/value – This paper contributes to knowledge with a new model called “the architecture of challenges in servitization”. This is the only model that explains the importance of the strategic, operational and social tests that organisations confront when adopting servitization strategies. If companies understand these challenges, they have the potential to create unique sets of values for a variety of s
Open Access
A concurrent engineering framework to explore the servicer-client relationship in on-orbit servicing.
(2018-12) Matos De Carvalho, Tiago; Kingston, Jennifer; Hobbs, Stephen E.
The implementation of On-Orbit Servicing (OOS) in the development and operation of space systems has been pursued to enable inspection, maintenance, repair and assembly of systems in space. Performing such tasks robotically involves the consideration of two sides, a Servicer satellite performing the necessary tasks and a Client satellite receiving it. A critical point for a realistic consideration of OOS demands the concurrent approach of both sides. Despite the current interests towards OOS, there is still a gap in the research into the relationship of Client and Servicer. This research aims to develop and demonstrate a methodology to technically incorporate On-Orbit Servicing, at a system-level, to the mission design process and operation of current and new satellites. The first objective deals with the systematic arrangement of the current available knowledge. A top-down approach is used to provide a taxonomy of servicing, followed by the functional decomposition of the main tasks. This objective clarifies the main issues observed today in OOS, directly related to the Client-Servicer relationship. The second objective is to establish the proposed framework. Agent Based Modelling and Simulation is used to implement the main guidelines and concept of operation, and to output different metrics to allow users (Servicers and/or Clients) to evaluate the attractiveness of various OOS scenarios. The mathematical background for the different metrics is defined and discussed. This is complemented by a solution exploration feature for specific types of OOS. A set of cases is presented based on current interests of operators, providing coverage of potential scenarios to use the framework. The proposed objectives are met, achieving the main research aim. The results help to illustrate the effects of servicing in the systems design and operation. Features of the framework expand the capacity to identify potentially attractive conditions for both sides. Such characteristics are not observed in the current published research and represent a powerful tool to be employed at early stages of design and procurement.
Open Access
The design of beyond LEO mission scenario for a biological payload with a cubesat.
(2019-06) Pratnekar, Marko; Cullen, David C.; Kingston, Jennifer
CubeSat technology has been well established in the area of space engineering for almost two decades. Because of standardisation of components and procedures, development and launch costs of space missions are greatly reduced and space based experiments become more affordable for the broader community. Up to now, all CubeSat missions except for one have been launched in Low Earth Orbit. With recent developments and new launch opportunities, sending CubeSat missions with various on board experiments beyond Low Earth Orbit into interplanetary space becomes possible. Major space agencies have ambitious plans to send human space missions to Mars and other bodies in the Solar System. Traveling beyond Earth’s orbit, living cells in the human body will be exposed to harmful effects of space radiation. Therefore, before such interplanetary mission takes place, detailed study of effects of space radiation on human like mammalian cells should be conducted. An interplanetary mission based on the CubeSat platform would be the most affordable way of conducting such experiment. The main aim of the reported research work is to investigate if adequate space radiation protection and strict thermal environment requirement can be achieved and maintained for biological payload with higher forms of living cells, within a CubeSat spacecraft platform during interplanetary flight. This thesis is divided into a theoretical part – the literature review and methodological part – numerical simulations which are for space radiation performed by NASA developed software OLTARIS and for thermal analysis of the spacecraft and installed components with ESATAN –TMS modelling software. From the performed research work it can be concluded that adequate radiation protection can be implemented within the CubeSat payload compartment, so as not to exceed the acute dose limit set even during long duration interplanetary space flight, while at the same time leaving enough payload volume for the installation of the experimental biological payload and experimental instrumentation within the extra installed radiation protection. In maintaining the thermal environment inside the payload bay with biological material as well as in maintaining the survival temperature of some electronic components, careful heat management and active thermal control – additional electrical heating is required. There was no requirement for active cooling in the realistic mission scenarios considered.
Open Access
Drag augmentation systems for space debris mitigation
(Elsevier, 2021-06-01) Serfontein, Zaria; Kingston, Jennifer; Hobbs, Stephen; Holbrough, Ian E.; Beck, James C.
Space debris is a critical threat to future and on-going missions. The commercialisation of the space sector has led to a rapid growth in the number of small satellites in recent years, which are adding to the already high number of objects currently in low-Earth orbit (LEO). Low-cost small satellites operators are under increasing pressure to comply with debris mitigation guidelines as part of the application process for a launch licence. Drag augmentation systems are a potential low-cost and low-impact solution for small satellites. By increasing the effective area of a satellite, and therefore its drag, these sails reduce the de-orbit period of a satellite, subsequently reducing the probability of significant collisions and supporting the sustainable use of space. Cranfield University are developing a family of drag augmentation systems (DAS) to assist in the long-term conservation of the space environment. The DAS are lightweight, cost-effective, reliable sails deployed at end of mission. Currently three of the drag sails designed, manufactured, and tested at Cranfield University are in orbit and two of the devices have successfully deployed their sails. This paper will discuss these sails and will highlight results from recent studies; examining the scalability of the system, the vehicle dynamics after sail deployment, the medium-term impact of the sail on the host satellite's ability to continue operations, and the long-term effect of the sail on the demisability of the satellite. The DAS technology has a strong enabling potential for future space activities, allowing satellites to operate responsibly and sustainably.
Open Access
Drag augmentation systems for space debris mitigation
(International Astronautical Federation, 2020-10) Serfontein, Zaria; Kingston, Jennifer; Hobbs, Stephen; Holbrough, Ian E.; Beck, James C.
Space debris is recognised as a critical threat for the space industry. The proliferation of small satellites has invited commercialisation and subsequently, the growing number of satellites are adding to the already high number of objects currently in low-Earth orbit (LEO). Low-cost small satellites are under increasing pressure to meet debris mitigation guidelines and failure to comply could result in a launch licence being denied. Drag augmentation systems increase the drag area of a spacecraft, minimising the de-orbit period and thus reducing the probability of significant collisions and supporting the sustainable use of space. In response to the growing number of small satellites (10-500 kg) unable to de-orbit from low-Earth orbit within 25 years, Cranfield University has developed a family of drag augmentation systems (DAS). The DAS are lightweight, cost-effective sails deployed at end of mission and are reliable solutions for deorbiting small satellites, assisting in the conservation of the space environment. Three drag sails designed, manufactured and tested at Cranfield University are currently in orbit, with two sails already successfully deployed. This paper details the sails and will discuss findings from recent studies; examining the system’s scalability, the post-deployment vehicle dynamics, the medium-term impact of the sail on the satellite’s ability to conduct science and the long-term effect of the sail on the satellite’s re-entry and demise. The DAS technology have a strong enabling potential for future space activities, allowing satellites to operate responsibly and sustainably.
Open Access
Effects of long-term exposure to the low-earth orbit environment on drag augmentation systems
(IAF, 2020-10-14) Serfontein, Zaria; Kingston, Jennifer; Hobbs, Stephen; Holbrough, Ian E.; Beck, James C.; Impey, Susan A.; Aria, Adrianus Indrat
Spacecraft in low-Earth orbit are exposed to environmental threats which can lead to material degradation and component failures. The presence of atomic oxygen and collisions from orbital debris have detrimental effects on the structures, thus affecting their performance. Cranfield University has developed a family of drag augmentation systems (DAS), for end-of-life de-orbit of satellites, addressing the space debris challenge and ensuring that satellites operate responsibly and sustainably. Deorbit devices are stowed on-orbit for the duration of the mission lifetime and, once deployed, the devices must withstand this harsh low-Earth environment until re-entry; a process which can take several years. The DAS’ deployable aluminised Kapton sails are particularly susceptible to undercutting by atomic oxygen. In preparation for commercialising the DAS, Cranfield University and Belstead Research Ltd. have submitted several joint proposals to better understand the degradation process of the drag sail materials and to qualify the materials for the specific application of drag sails in low Earth Orbit (LEO). This paper will outline the proposals and the expected benefits from the projects. Additionally, collisions with debris could accelerate the degradation of the system and generate additional debris. This paper will discuss a future ESABASE2 risk assessment study, aiming to quantifying the probability of collisions between the deployed drag sail and orbital debris. The atmospheric models required to simulate the aforementioned risks are complex and often fail to accurately predict performance or degradation observed in the space environment. A previous UKSA Pathfinder project highlighted this issue when different atmospheric models with varying levels of solar activity yielded drastically different re-entry times. Since Cranfield University has two deployed drag sails in orbit, previous de-orbit analysis performed using STELA and DRAMA will be updated and the simulations will be compared to actual data. This paper will conclude in a summation of the different on-going research projects at Cranfield University related to commercialising the DAS family. This research will benefit the wider space community by expanding the understanding of the effects of long-term exposure on certain materials, as well as improving the validity of future low Earth atmospheric models.
Open Access
Effects of long-term exposure to the low-earth orbit environment on drag augmentation systems
(Elsevier, 2021-06-10) Serfontein, Zaria; Kingston, Jennifer; Hobbs, Stephen; Impey, Susan A.; Aria, Adrianus Indrat; Holbrough, Ian E.; Beck, James C.
Spacecraft in low-Earth orbit are exposed to environmental threats which can lead to material degradation and component failures. The presence of atomic oxygen and collisions from orbital debris have detrimental effects on the structures, thus affecting their performance. Cranfield University has developed a family of drag augmentation systems (DAS), for end-of-life de-orbit of satellites, addressing the space debris challenge and ensuring that satellites operate responsibly and sustainably. De-orbit devices are stowed on-orbit for the duration of the mission lifetime and, once deployed, the devices must withstand the harsh low Earth environment until re-entry; a process which can take several years. The DAS’ deployable aluminised Kapton sails are particularly susceptible to undercutting by atomic oxygen. In preparation for commercialising the DAS, Cranfield University are investigating the degradation process of the drag sail materials, with the end goal of qualifying the materials for the specific application of drag sails in low Earth orbit (LEO). This paper will outline the proposed research and the expected benefits from the projects. This paper will conclude in a summation of the different on-going research projects at Cranfield University related to commercialising the DAS family. This research will benefit the wider space community by expanding the understanding of the effects of long-term exposure on certain materials, as well as improving the validity of future low Earth atmospheric models.
Open Access
Establishing a framework to explore the Servicer-Client relationship in On-Orbit Servicing
(Elsevier, 2018-10-26) Matos de Carvalho, Tiago Henrique; Kingston, Jennifer
On-Orbit Servicing (OOS) is becoming more extensively discussed in research and commercial developments. The key point of servicing relies on the relation between two systems, the Servicer executing the tasks and the Client being serviced. With the increase of interest in OOS applications, the exploration of the Client-Servicer relationship in different scenarios becomes a necessary step in servicing implementation. Exploring such a relationship involves translating the information available about OOS into useful inputs for spacecraft design, a challenging task due to the variety of applications and possible interactions between both sides. Then, different modelling and simulation techniques can be used to model and to explore the interaction of such complex systems for different scenarios of servicing. This paper presents an agent-based framework to explore the relations of Servicer and Client for applications of On-Orbit Servicing. To do so, the case for a hypothetical satellite operator is explored, under a specific set of requirements and conditions for different servicing solutions. First, the Agent Based Modelling and Simulation (ABMS) is established based on a specific set of rules, definition metrics and operation characteristics relating Servicer and Client. Then, the basic assumptions of Client, Servicer and servicing operations are discussed and the initial simulation parameters are defined. The ABMS is used to simulate OOS for a fleet of geostationary communication satellites for the cases of Lifetime Extension, Refuel and Rescue and Recover. In the end, the ABMS outputs are used to explore the design aspects of the Servicer and Client satellites at systems level. The results highlight the advantages of having this type of framework for early assessment of OOS under different types of context for both Servicer and Client. The paper concludes with directions of how the framework can be used to explore more complex and realistic scenarios of OOS, and assess their potential benefits.
Open Access
Failure analysis of satellite subsystems to define suitable de-orbit devices
(Elsevier, 2016-07-14) Palla, Chiara; Peroni, Moreno; Kingston, Jennifer
Space missions in Low Earth Orbit (LEO) are severely affected by the build-up of orbital debris. A key practice, to be compliant with IADC (Inter-Agency Space Debris Coordination Committee) mitigation guidelines, is the removal of space systems that interfere with the LEO region not later than 25 years after the End of Mission. It is important to note that the current guidelines are not generally legally binding, even if different Space Agencies are now looking at the compliance for their missions. If the guidelines will change in law, it will be mandatory to have a postmission disposal strategy for all satellites, including micro and smaller classes. A potential increased number of these satellites is confirmed by different projections, in particular in the commercial sector. Micro and smaller spacecraft are, in general, not provided with propulsion capabilities to achieve a controlled re-entry, so they need different de-orbit disposal methods. When considering the utility of different debris mitigation methods, it is useful to understand which spacecraft subsystems are most likely to fail and how this may affect the operation of a de-orbit system. This also helps the consideration of which components are the most relevant or should be redundant depending on the satellite mass class. This work is based on a sample of LEO and MEO satellites launched between January 2000 and December 2014 with mass lower than 1000 kg. Failure analysis of satellite subsystems is performed by means of the Kaplan–Meier survival analysis; the parametric fits are conducted with Weibull distributions. The study is carried out by using the satellite database SpaceTrak™ which provides anomalies, failures, and trends information for spacecraft subsystems and launch vehicles. The database identifies five states for each satellite subsystem: three degraded states, one fully operational state, and one failed state (complete failure). The results obtained can guide the identification of the activation procedure for a de-orbit strategy and the level of integration it should have with the host satellite in order to be activated before a total failure. At Cranfield Space Research Centre two different solutions have already been developed as de-orbit sail payloads for microsatellites (Icarus-1 on TechDemoSat-1 and Icarus-3 on Carbonite-1 currently on-orbit, DOM for future ESA ESEO mission). This study will provide a useful input to improve and refine the current de-orbit concepts for future satellite missions.
Open Access
Forecast analysis on satellites that need de-orbit technologies: future scenarios for passive de-orbit devices
(Springer Verlag, 2016-05-10) Palla, Chiara; Kingston, Jennifer
Propulsion-based de-orbit is a space-proven technology; however, this strategy can strongly limit operational lifetime, as fuel mass is dedicated to the de-orbiting. In addition previous reliability studies have identified the propulsion subsystem as one of the major contributors driving satellite failures. This issue brings the need to develop affordable de-orbit technologies with a limited reliance on the system level performance of the host satellite, ideally largely passive methods. Passive disposal strategies which take advantage of aerodynamic drag as the de-orbit force are particularly attractive because they are independent of spacecraft propulsion capabilities. This paper investigates the future market for passive de-orbit devices in LEO to aid in defining top-level requirements for the design of such devices. This is performed by considering the compliances of projected future satellites with the Inter Agency Space Debris Coordination Committee de-orbit time, to quantify the number of spacecraft that are compliant or non-compliant with the guidelines and, in this way, determine their need for the previously discussed devices. The study is performed by using the SpaceTrak™ database which provides future launch schedules, and spacecraft information; the de-orbit analysis is carried out by means of simulations with STELA. A case study of a passive strategy is given by the de-orbit mechanism technological demonstrator, which is currently under development at Cranfield University and designed to deploy a drag sail at the end of the ESEO satellite mission.
Open Access
System-in-use methodology : a methodology to generate conceptual PSS (Product-Service Systems) and conventional designs using systems-in-use data
(Cranfield University, 2013-03) Hussain, Romana; Lockett, Helen L.; Kingston, Jennifer; Alcock, Jeffrey R.
Industries want to add value to their offerings but to do this, rather than just accepting customer requirements, they now need to know how their products and/or services have been embedded within their customer’s process to achieve a goal that the customer has; any gaps within the process then present an opportunity for the provider to fill these gaps. The System-In-Use (SIU) Methodology presented in this thesis facilitates customer issues in “pulling” the supply chain into creating new solutions as well as the supply chain “pushing” new value propositions into improving customer processes. It does this by drawing on a detailed theory of value and capability which was developed as part of this research. The method has been applied in five industries in processes encompassing high value-assets with very positive outcomes for each of the stakeholders involved: notably, three solutions have been adopted in industry for which a KT-Box award was granted by Cambridge University. Cont/d.
Open Access
Towards drop your thesis 2018: 4.7 seconds of microgravity conditions to enable future CubeSat landings on asteroids
(International Astronautical Federation, 2018-10-05) Sanchez Cuartielles, Joan Pau; Sitepu, Elioenai; Le Blay, Carole; Kersey, George; Ogborne, Stuart; Durrani, Daniyal Ahmad; Zanotti Fragonara, Luca; Gautier, Florian; Kingston, Jennifer
An increasing number of interplanetary missions are aiming at visiting asteroids and other small bodies, since these may provide clues to understand the formation and evolution of our Solar System. CubeSats allow a low-cost solution to land on these objects, as opposed to risking a much more expensive mothership. The weak gravitational field on these small bodies may also enable the possibility of simply dropping a CubeSat from afar (i.e. ballistic landing). However, ballistic landing of an unpowered spacecraft may be feasible solely within certain asteroid locations, and only if sufficient energy can be dissipated at touchdown. If such conditions are not met, the spacecraft will rebound off the surface. It is likely that the necessary energy dissipation may already occur naturally due to energy loss expected through the deformation of the regolith during touchdown. Indeed, previous low-velocity impact experiments in microgravity seem to indicate that this is exactly the case. However, data from past asteroid touchdowns, Hayabusa and Philae, indicate the contrary. This paper describes the development of an experiment which aims to bridge the aforementioned disagreement between mission data and microgravity experiment; to understand the behaviour of CubeSat landing on asteroids. The experiment will also test a novel damping system made by origami paper that should increase the dissipated energy at touchdown. The experiment will take place at the ZARM Drop Tower in Bremen in November 2018. With the constraint of 5 drops, the experiment will measure the coefficient of restitution during an available time window of 4.74 seconds of microgravity conditions. A 1UCubeSat mock-up will be used to represent a future asteroid lander. In order to mimic the landing of actual missions, the mock-up will have a mass of about 4 kg and it will be given a velocity of 15 cm/s with minimal rotation. This will be achieved by an automated spring-based release mechanism. An asteroid simulant, ESA03-A KM Bentonite Granules will be used to replicate an asteroid mechanical properties at the surface. This paper reviews the final design and the engineering challenges of the experiment.

Browsing by Author "Kingston, Jennifer"

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