Irene Budianto - Academia.edu (original) (raw)
Papers by Irene Budianto
Future space transportation vehicles may well rely on high speed airbreathing propulsion (ramjets... more Future space transportation vehicles may well rely on high speed airbreathing propulsion (ramjets and scramjets) to supply much of their motive power. Because of the tradeoff relationship between engine thrust and vehicle airframe weight, ascent trajectories are typically simulated using a constant dynamic pressure phase during airbreathing acceleration. That is, dynamic pressure is increased to benefit vehicle thrust up to some fixed limit imposed by the vehicle structure. The constant dynamic pressure portion of the trajectory typically begins around Mach 2 or 3 and continues to the maximum airbreathing Mach number or until some convective aeroheating limit is reached. This paper summarizes comparative research on three candidate guidance methods suitable for simulating constant dynamic pressure trajectories. These are generalized acceleration steering, linear feedback control, and cubic polynomial control. All methods were implemented in POST (Program to Optimize Simulated Trajec...
Bookmarks Related papers MentionsView impact
37th Aerospace Sciences Meeting and Exhibit, 1999
Bookmarks Related papers MentionsView impact
36th AIAA Aerospace Sciences Meeting and Exhibit, 1998
Bookmarks Related papers MentionsView impact
Bookmarks Related papers MentionsView impact
Bookmarks Related papers MentionsView impact
2000 IEEE Aerospace Conference. Proceedings (Cat. No.00TH8484), 2000
Bookmarks Related papers MentionsView impact
Journal of Spacecraft and Rockets, 2004
Bookmarks Related papers MentionsView impact
Journal of Spacecraft and Rockets, 2004
Bookmarks Related papers MentionsView impact
This thesis introduces a systematic, multivariable, multidisciplinary method for the conceptual d... more This thesis introduces a systematic, multivariable, multidisciplinary method for the conceptual design of satellite constellations. The system consisted of three separate, but coupled, contributing analyses. The configuration and orbit design module performed coverage analysis for different orbit parameters and constellation patterns. The spacecraft design tool estimated mass, power, and costs for the payload and spacecraft bus that satisfy the resolution and sensitivity requirements. The launch manifest model found the minimum launch cost strategy, to deploy the given constellation system to the specified orbit. Collaborative Optimization (CO) has been previously implemented successfully as a design architecture for large-scale, highly-constrained multidisciplinary optimization problems related to aircraft and space vehicle studies. It is a distributed design architecture that allows its subsystems flexibility with regards to computing platforms and programming environment and, as its name suggests, many opportunities for collaboration. It is thus well suited to a team-oriented design environment, such as found in the constellation design process, and was implemented in this research. Two problems were solved using the CO method related to the design and deployment of a space-based infrared system to provide early missile warning. Successful convergence of these problems proved the feasibility of the CO architecture for solving the satellite constellation design problem. Verification of the results was accomplished by also implementing a large All-at-Once (AAO) optimization. This study further demonstrated several advantages of this approach over the standard practice used for designing satellite constellation systems. The CO method explored the design space more systematically and more extensively, improved subsystem flexibility, and its formulation was more scalable to growth in problem complexity. However, the intensive computational requirement of this method, even with automation and parallel processing of the subsystem tasks, reduced its competitiveness versus the current practice, given today's computing limitations. This thesis also contributed to the current knowledge of the collaborative optimization. To date, CO has been used exclusively with gradient-based optimization scheme, specifically Sequential Quadratic Programming (SQP). This research demonstrated the feasibility of zero-order methods as both system and subsystem optimizers. Finally, with integer variables involved in the problem, CO's flexibility for handling mixed-discrete nonlinear problems was demonstrated.
Bookmarks Related papers MentionsView impact
Bookmarks Related papers MentionsView impact
Bookmarks Related papers MentionsView impact
Bookmarks Related papers MentionsView impact
Bookmarks Related papers MentionsView impact
Journal of Spacecraft and Rockets, 2004
ABSTRACT A study of collaborative optimization as a systematic, multivariable, multidisciplinary ... more ABSTRACT A study of collaborative optimization as a systematic, multivariable, multidisciplinary method for the conceptual design of satellite constellations is presented. Collaborative optimization was selected because it is well suited to a team-oriented environment, such as often found in the constellation design process. The method provides extensive and formal exploration of the multidisciplinary design space and a scalable formulation of the problem without compromising its subsystems' flexibility or eliminating opportunities for collaboration. The feasibility and benefits of the collaborative optimization architecture are highlighted by the successful convergence of an application notional problem to design and deploy elements of a space-based infrared system that provides early missile warning. Furthermore, this study contributes to the existing knowledge of the collaborative optimization method by verifying the feasibility of nongradient optimization algorithms as both system and subsystem optimizers within the architecture. Finally, the demonstrated convergence of this problem, which involves integer variables, also demonstrates the flexibility of the architecture for handling mixed-discrete nonlinear multidisciplinary problems.
Bookmarks Related papers MentionsView impact
Future space transportation vehicles may well rely on high speed airbreathing propulsion (ramjets... more Future space transportation vehicles may well rely on high speed airbreathing propulsion (ramjets and scramjets) to supply much of their motive power. Because of the tradeoff relationship between engine thrust and vehicle airframe weight, ascent trajectories are typically simulated using a constant dynamic pressure phase during airbreathing acceleration. That is, dynamic pressure is increased to benefit vehicle thrust up to some fixed limit imposed by the vehicle structure. The constant dynamic pressure portion of the trajectory typically begins around Mach 2 or 3 and continues to the maximum airbreathing Mach number or until some convective aeroheating limit is reached. This paper summarizes comparative research on three candidate guidance methods suitable for simulating constant dynamic pressure trajectories. These are generalized acceleration steering, linear feedback control, and cubic polynomial control. All methods were implemented in POST (Program to Optimize Simulated Trajec...
Bookmarks Related papers MentionsView impact
37th Aerospace Sciences Meeting and Exhibit, 1999
Bookmarks Related papers MentionsView impact
36th AIAA Aerospace Sciences Meeting and Exhibit, 1998
Bookmarks Related papers MentionsView impact
Bookmarks Related papers MentionsView impact
Bookmarks Related papers MentionsView impact
2000 IEEE Aerospace Conference. Proceedings (Cat. No.00TH8484), 2000
Bookmarks Related papers MentionsView impact
Journal of Spacecraft and Rockets, 2004
Bookmarks Related papers MentionsView impact
Journal of Spacecraft and Rockets, 2004
Bookmarks Related papers MentionsView impact
This thesis introduces a systematic, multivariable, multidisciplinary method for the conceptual d... more This thesis introduces a systematic, multivariable, multidisciplinary method for the conceptual design of satellite constellations. The system consisted of three separate, but coupled, contributing analyses. The configuration and orbit design module performed coverage analysis for different orbit parameters and constellation patterns. The spacecraft design tool estimated mass, power, and costs for the payload and spacecraft bus that satisfy the resolution and sensitivity requirements. The launch manifest model found the minimum launch cost strategy, to deploy the given constellation system to the specified orbit. Collaborative Optimization (CO) has been previously implemented successfully as a design architecture for large-scale, highly-constrained multidisciplinary optimization problems related to aircraft and space vehicle studies. It is a distributed design architecture that allows its subsystems flexibility with regards to computing platforms and programming environment and, as its name suggests, many opportunities for collaboration. It is thus well suited to a team-oriented design environment, such as found in the constellation design process, and was implemented in this research. Two problems were solved using the CO method related to the design and deployment of a space-based infrared system to provide early missile warning. Successful convergence of these problems proved the feasibility of the CO architecture for solving the satellite constellation design problem. Verification of the results was accomplished by also implementing a large All-at-Once (AAO) optimization. This study further demonstrated several advantages of this approach over the standard practice used for designing satellite constellation systems. The CO method explored the design space more systematically and more extensively, improved subsystem flexibility, and its formulation was more scalable to growth in problem complexity. However, the intensive computational requirement of this method, even with automation and parallel processing of the subsystem tasks, reduced its competitiveness versus the current practice, given today's computing limitations. This thesis also contributed to the current knowledge of the collaborative optimization. To date, CO has been used exclusively with gradient-based optimization scheme, specifically Sequential Quadratic Programming (SQP). This research demonstrated the feasibility of zero-order methods as both system and subsystem optimizers. Finally, with integer variables involved in the problem, CO's flexibility for handling mixed-discrete nonlinear problems was demonstrated.
Bookmarks Related papers MentionsView impact
Bookmarks Related papers MentionsView impact
Bookmarks Related papers MentionsView impact
Bookmarks Related papers MentionsView impact
Bookmarks Related papers MentionsView impact
Journal of Spacecraft and Rockets, 2004
ABSTRACT A study of collaborative optimization as a systematic, multivariable, multidisciplinary ... more ABSTRACT A study of collaborative optimization as a systematic, multivariable, multidisciplinary method for the conceptual design of satellite constellations is presented. Collaborative optimization was selected because it is well suited to a team-oriented environment, such as often found in the constellation design process. The method provides extensive and formal exploration of the multidisciplinary design space and a scalable formulation of the problem without compromising its subsystems' flexibility or eliminating opportunities for collaboration. The feasibility and benefits of the collaborative optimization architecture are highlighted by the successful convergence of an application notional problem to design and deploy elements of a space-based infrared system that provides early missile warning. Furthermore, this study contributes to the existing knowledge of the collaborative optimization method by verifying the feasibility of nongradient optimization algorithms as both system and subsystem optimizers within the architecture. Finally, the demonstrated convergence of this problem, which involves integer variables, also demonstrates the flexibility of the architecture for handling mixed-discrete nonlinear multidisciplinary problems.
Bookmarks Related papers MentionsView impact