KEYWORDS: Systems modeling, Error analysis, Space telescopes, Mirrors, Telescopes, Finite element methods, Spatial frequencies, Observatories, Integrated modeling, Thirty Meter Telescope
Simulation models of new opto-mechanical systems are often based on engineering experience with older, potentially
dissimilar systems. This can result in inaccuracies in the model prediction. A method is needed to gauge the fidelity of
new system models in the initial design phases, often in the absence of hardware data. The Nyquist criterion is used to
develop a quantitative measure of model fidelity, called the Nyquist fidelity metric. The spatial Nyquist fidelity method
is presented which uses the Nyquist fidelity metric to both assess the fidelity of existing complex models and to
synthesize new multi-component models starting from architectural considerations such as geometric and material
properties of the system. This method also estimates the error bound on the output figures of merit based on the fidelity
levels and sensitivity analysis. The Nyquist fidelity method is applied to the Modular Optical Space Telescope (MOST),
the Thirty Meter Telescope, and the Stratospheric Observatory for Infrared Astronomy. It is shown in the MOST case
study that the Nyquist fidelity method provides a 40% improvement in computational time while assuring less than 5%
modal frequency error, and less than 2.2% error in the output figure of merit.
KEYWORDS: Systems modeling, Telescopes, Finite element methods, Chemical elements, Space telescopes, Device simulation, 3D modeling, Spatial frequencies, Optical instrument design, Signal processing
Analysis of complex interdisciplinary systems such as large telescopes is usually performed using simulation models due to the expense of hardware testbeds. The level of fidelity of these simulation models, or the relative closeness to which the model simulates reality for the behavior under investigation, is often not assessed in a quantitative manner. Rather, the model is described qualitatively as being of either "low" or "high" fidelity, often progressing from lower to higher fidelity models as the candidate designs are down-selected. This paper provides a quantitative assessment of fidelity for structural subsystems for large telescope models based on the Nyquist criterion, shows how it influences simulation accuracy, and applies it to a space telescope model. This metric will be useful for assessing the fidelity of an existing structural finite element telescope model or in creating a new model having sufficient fidelity (sufficient accuracy).
KEYWORDS: Systems modeling, Integrated modeling, Mirrors, Telescopes, Optical instrument design, Space telescopes, Motion models, Observatories, Control systems, Thirty Meter Telescope
In the conceptual design phase for a large ground-based observatory, it is often necessary to make major design decisions affecting output figures of merit before sufficiently detailed models are available for predicting results. While a single "point design" may be selected based on expert opinion, for new and complex structures the optimal design that meets both cost and science requirements may not be obvious without analysis of many models. One solution to evaluating different designs early in the design process is to create a parametric model of the telescope structure and predict the dynamic behavior using an integrated model. An integrated model is an environment where the major disciplines of disturbance, optics, controls and structures are modeled. In this way a large tradespace across different design configurations and parametric values can be rapidly evaluated using metrics such as image motion and estimated system cost. This paper describes the steps taken by the MIT Space System Laboratory (MIT SSL) for large ground-based observatory preliminary design using a parametric integrated model. The parametric finite element structural model is described and representative results are shown. In particular, this paper will describe lessons learned about the advantages and challenges
encountered during development and implementation of the parametric integrated model such as the usefulness of a visualization tool and the importance of subsystem model modularity.
KEYWORDS: Mirrors, Space telescopes, Optical instrument design, Systems modeling, Lightweight mirrors, Actuators, Performance modeling, Finite element methods, Space mirrors, Space operations
Development of low-cost, lightweight space imaging systems requires a combination of technologies including
lightweight optics to reduce the areal density of the mirrors and application of controls-structures technologies to
compensate for the increased flexibility of these systems. These new design technologies have led to many new
possibilities for architectures of large space telescopes, creating a necessity for new design tools during the conceptual
design phase. The MIT Space Systems Laboratory (MIT-SSL) is examining alternative architectures for a Modular
Optical Space Telescope (MOST) by developing a tool to automatically generate unique realizations of a spacecraft
based upon parametric inputs to the model. This tool allows system metrics to be evaluated across combinations of
design variables so that promising architecture families utilizing different technologies can be identified on the basis of
system performance. This paper will describe advances to the structural components of the MOST model, particularly
the primary mirror and secondary support tower. Lightweight, rib-stiffened mirrors and a variety of geometries for a
lightweight secondary support tower have been modeled. Both of these parameterized sub-components can be analyzed
to determine the effects of changing geometries on the structural stiffness. These advanced components can then be
used in the system in order to more fully understand the effects of lightweight structures on the system performance
metrics.
KEYWORDS: Systems modeling, Data modeling, Integrated modeling, Sensors, Optimization (mathematics), Aluminum, Performance modeling, Control systems, Process modeling, Error analysis
High quality multi-disciplinary integrated models are needed for
complex opto-mechanical spacecraft such as SIM and TPF in order to
predict the system's on-orbit behavior. One major activity in
early design is to examine the system's behavior over multiple
configurations using an integrated model. A three step procedure
for model tuning is outlined that consists of (1) applying
engineering insight to the model so that all physical systems are
present in the model, (2) using optimization to automatically
update system parameters that are uncertain in the model, and (3)
evaluating the model at several configurations using the updated
parameters. The key contribution of this work is the systematic
checking of the validity of the updated parameters by evaluating,
both in the model and the experiment, the system at different
configurations (step three). It is hypothesized that if the
simulation model and experimental data of the additional
configurations match well then the tuned system parameters were
indeed updated in a way that physically represents the system.
This three step process is applied to a testbed at the MIT Space
System Laboratory.
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