ERS-1 processing chain development and product support by the EODC science team, the algorithm development facility and the calibration and validation facility
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Abstract The Earth Observation Centre (EODC), located at Farnborough, has been developed to serve the needs of users of data from Earth remote sensing missions, beginning with the European Space Agency's ERS-1 spacecraft. To this end, the facilities of the ESA Processing and Archiving Facility (PAF) for ERS-1 reside within the EODC. With the exception of the core Synthetic Aperture Radar processing algorithms, the majority of the scientific processing chains for exploitation of data from ERS-1 at the EODC were designed and specified by a Science Team, consisting of specialists from UK universities, industry, and government research institutes. These designs were implemented by an industrial consortium. The Science Team was supported by an Algorithm Development Facility (ADF) during the processing chain development. The Science Team currently provide operational support using the EODC Calibration and Validation Facility (CVF). This consists of the verification, calibration, validation, and continuous assessment of products. This paper describes the work and structure of the Science Team, the ADF and the CVF. The methodology adopted is evaluated, and implications for future projects of this kind are considered in the light of the lessons learned.Keywords:
Data Processing
Spacecraft payloads are the sensing components that remain active over time and ensure Spacecraft's capability to perform multiple operations. It determines the rate of mission extension and the amount of scientific return based on extended performance. But it degrades over time due to the continuous process of operation and several space environmental factors. This paper has estimated payload mass fraction using the Spacecraft's data to relate it to the lifetime of orbital Spacecraft. Our prime intent is to check whether the spacecraft payload mass fraction affects the Spacecraft's lifetime concerning the initial hypothesis that the spacecraft mass greatly influences spacecraft lifetime. We derive some mathematical relation and establish a relationship between spacecraft payload mass fraction and lifetime. Finally, to verify our relation, we employ spacecraft data to investigate and interpret reliability behavior based on payload fraction and lifetime relation.
Payload (computing)
Spacecraft design
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This paper presents an implicit algorithm for spacecraft onboard instrument calibration, particularly to onboard gyro calibration. This work is an extension of previous work that was done where an explicit gyro calibration algorithm was applied to the AQUA spacecraft gyros. The algorithm presented in this paper was tested using simulated data and real data that were downloaded from the Microwave Anisotropy Probe (MAP) spacecraft. The calibration tests gave very good results. A comparison between the use of the implicit calibration algorithm used here with the explicit algorithm used for AQUA spacecraft indicates that both provide an excellent estimation of the gyro calibration parameters with similar accuracies.
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Facing the increasingly crowded orbital space and the gradually increasing space threats, more attention needs to be paid to spacecraft safety in space. In order to address the problem of non-cooperative spacecraft's approach interference to our spacecraft, the process of non-cooperative spacecraft's approach to our spacecraft by using Hohmann transfer is given by Satellite Tool Kit (STK) software, and the whole process of spacecraft's abnormal orbital maneuvering to approach our spacecraft is identified and judged by the method based on long short-term memory (LSTM) network. The simulation verifies that the LSTM network achieves good results.
Orbit (dynamics)
Orbital maneuver
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Spacecraft charging
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Synthetic Aperture Radar (SAR) is a high resolution microwave active imaging sensor with all-weather, day or night time observation capability. SAR has an information aquisition capability that differs from that obtained by optical sensors. Because a very large number of operations are required in SAR data processing, the authors have applied a non-von Neumann type high speed computer (data-flow computer) called NEDIPS to SAR data processing, and have realized one of the highest speed SAR data processing systems. In this paper, the characteristics of SAR data processing and an outline of the SAR data processing system using NEDIPS are introduced. Finally, the high speed SAR data processing techniques used in the system are discussed.
Data Processing
Data processing system
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Large spacecraft missions have both technical and financial needs. Technical needs drive the inclusion of numerous subsystems, which must be configured or deployed. Financial needs, for many spacecraft, are filled through generating public support, which is enhanced by being able to show the spacecraft in operation. This paper presents DeSCJOB, a small satellite that is deployed from a larger spacecraft. It launches from the parent spacecraft, captures images of whatever is desired (moving around the larger spacecraft, if desired) and then retracts back to its docking point automatically. Its utility for operational and public relations imaging is discussed.
Spacecraft design
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Because very large spacecrafts are being proposed for future missions, spacecraft designers will face new problems related to spacecraft interactions with the environment. Two categories of spacecraft-environmental interactions are discussed. These are spacecraft passive, where the charged-particle environment acts on spacecraft surfaces/ and spacecraft active, where the spacecraft or its systems cause the interaction. Motion induced mechanical stresses in large spacecrafts, and high voltage, large power system interactions are considered. (5 diagrams, 13 graphs, 1 photo, 27 references)
Spacecraft design
Spacecraft charging
Space environment
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Spacecraft-environment interactions are defined as the responses of a spacecraft surface to a charged-particle environment. This response can influence spacecraft system performance. Interactions can be divided into two broad categories: spacecraft passive, in which the environment acts on the spacecraft; and spacecraft active, in which the spacecraft causes the interaction. Passive interactions include the spacecraft-charging phenomenon. Active interactions include the relatively new interactions arising from the use of very large spacecraft and space power systems in future missions. To illustrate active interactions, a large power system operating at elevated voltages is considered. Possible interactions are described, available experimental data are reviewed, and the effect on power system performance is estimated.
Spacecraft design
Spacecraft charging
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Spacecraft charging is a major topic of space-weather research since charging can lead to spacecraft anomalies, ranging from inconsequential to catastrophic. Spacecraft surface charging calculations use sophisticated numerical codes and are typically performed with a direct (forward) approach: the local properties of the space environment, the spacecraft geometry, and the spacecraft material properties are the input, while the electric field on and around the spacecraft and the corresponding plasma particle distributions are the output. This approach can be limited or highly inaccurate when some of the critical input parameters are either unknown or have large uncertainties. For instance, the Van Allen Probes spacecraft, also known as RBSP, is an example of a modern spacecraft with state-of-the-art measurements. Predicting the RBSP spacecraft potential requires knowledge of the cold and warm plasma populations which dominate surface charging. However, the cold plasma properties (particularly temperature) are not well characterized. In addition, the material properties are known from measurements in laboratory "clean" conditions but how materials age in space due to their interaction with the environment is not well understood. To mitigate these limitations, we developed an inverse approach to use available spacecraft-charging data to infer some of the unknown properties of the space environment around the spacecraft and spacecraft material degradation. Our inversion is composed of an ensemble of constrained optimization solutions that provide an estimate of the parameter values of interest. Our approach is validated with an analytical model of spacecraft charging, based on the orbital-motion-limited theory, together with a quasi-Newton optimization method. Our results show convergence and the ability to estimate the correct parameters in synthetic observation experiments.
Spacecraft charging
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Spacecraft charging (surface and internal) is complex physical phenomena that can have serious ramifications on mission success. The degree of spacecraft charging a spacecraft may experience is heavily dependent on both the surrounding space environment and spacecraft geometry (more specifically, the geometry and material makeup of the spacecraft). We will present a study focusing on the effects of using good design and materials to help mitigate risks due to spacecraft charging. We will review the important considerations and good design practices to ensure mission success.
Spacecraft design
Spacecraft charging
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