Irene Budianto - Profile on Academia.edu (original) (raw)
Papers by Irene Budianto
AIAA 98-0302 Constant Dynamic Pressure Trajectory Simulation with POST
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...
37th Aerospace Sciences Meeting and Exhibit, 1999
Most of the analysis codes used in the design of aerospace systems are complex, requiring some ex... more Most of the analysis codes used in the design of aerospace systems are complex, requiring some expertise to set up and execute. POST, which is used in many conceptual design studies to compute space vehicle performance characteristics, often encounters numerical difficulties in solving the defined trajectory problem. Usually POST fails to converge when its control variables are given a bad set of initial guesses, causing the trajectory to remain in the infeasible design region throughout the computations. The user then analyzes the output produced and relies on a set of heuristics, typically gained from experience with the program, to determine the appropriate modification to the problem setup that will guide POST in finding a feasible region and eventually converge to a solution.
Constant dynamic pressure trajectory simulation with POST
36th AIAA Aerospace Sciences Meeting and Exhibit, 1998
with the charter of identifying economically attractive candidate space transfer vehicle systems ... more with the charter of identifying economically attractive candidate space transfer vehicle systems for ferrying components of Space Solar Power (SSP) satellites from Low Earth Orbit (LEO) to Geostationary Earth Orbit (GEO). An aggressive price goal of only 400/kgofpayloadwasestablishedinordertocontrolthecostoftransportationfortheSSPsatellitedeveloper.Amulti−stepdecisionprocesswasemployedtodown−selectfromalargenumberofcandidatesystemstofour.ThefinalfourconceptswereNuclearThermalRocket(NTR),SolarThermalRocket(STR),arotatingtether,andSolarElectricPropulsion(SEP).AdditionalconceptsconsideredwereDual−Mode(Chemical/SEP)andAll−Chemical.Resultsshowthatthemosteconomicalconceptisonewhichishighlyreusable,hasashortturnaroundtime,alongvehiclelife,andsmallpropellantrequirements.Thesecharacteristicsresultinalowfleetsizeandthereforelowerdebtrequirements.ThesecharacteristicsalsolowertheInitialMassinLowEarthOrbit(IMLEO)andthereforelowerdeploymentcosts.Thegoalof400/kg of payload was established in order to control the cost of transportation for the SSP satellite developer. A multi-step decision process was employed to down-select from a large number of candidate systems to four. The final four concepts were Nuclear Thermal Rocket (NTR), Solar Thermal Rocket (STR), a rotating tether, and Solar Electric Propulsion (SEP). Additional concepts considered were Dual-Mode (Chemical/SEP) and All-Chemical. Results show that the most economical concept is one which is highly reusable, has a short turnaround time, a long vehicle life, and small propellant requirements. These characteristics result in a low fleet size and therefore lower debt requirements. These characteristics also lower the Initial Mass in Low Earth Orbit (IMLEO) and therefore lower deployment costs. The goal of 400/kgofpayloadwasestablishedinordertocontrolthecostoftransportationfortheSSPsatellitedeveloper.Amulti−stepdecisionprocesswasemployedtodown−selectfromalargenumberofcandidatesystemstofour.ThefinalfourconceptswereNuclearThermalRocket(NTR),SolarThermalRocket(STR),arotatingtether,andSolarElectricPropulsion(SEP).AdditionalconceptsconsideredwereDual−Mode(Chemical/SEP)andAll−Chemical.Resultsshowthatthemosteconomicalconceptisonewhichishighlyreusable,hasashortturnaroundtime,alongvehiclelife,andsmallpropellantrequirements.Thesecharacteristicsresultinalowfleetsizeandthereforelowerdebtrequirements.ThesecharacteristicsalsolowertheInitialMassinLowEarthOrbit(IMLEO)andthereforelowerdeploymentcosts.Thegoalof400/kg, or 2.5¢/kW-hr, for in-space transportation costs is very aggressive and difficult to achieve.
A collaborative optimization approach to improve the design and deployment of satellite constellations
A collaborative optimization approach to design and deployment of a space based infrared system constellation
2000 IEEE Aerospace Conference. Proceedings (Cat. No.00TH8484), 2000
Design and Deployment of a Satellite Constellation Using Collaborative Optimization
Journal of Spacecraft and Rockets, 2004
Design and Deployment of a Satellite Constellation Using Collaborative Optimization
Journal of Spacecraft and Rockets, 2004
A collaborative optimization approach to improve the design and deployment of satellite constellations
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.
Most of the analysis codes used in the design of aerospace systems are complex, requiring some ex... more Most of the analysis codes used in the design of aerospace systems are complex, requiring some expertise to set up and execute. POST, which is used in many conceptual design studies to compute space vehicle performance characteristics, often encounters numerical difficulties in solving the defined trajectory problem. Usually POST fails to converge when its control variables are given a bad set of initial guesses, causing the trajectory to remain in the infeasible design region throughout the computations. The user then analyzes the output produced and relies on a set of heuristics, typically gained from experience with the program, to determine the appropriate modification to the problem setup that will guide POST in finding a feasible region and eventually converge to a solution.
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.
IEEE P335E A Collaborative Optimization Approach to Design and Deployment of a Space Based Infrared System Constellation
Design and Deployment of a Satellite Constellation Using Collaborative Optimization
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.
AIAA 98-0302 Constant Dynamic Pressure Trajectory Simulation with POST
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...
37th Aerospace Sciences Meeting and Exhibit, 1999
Most of the analysis codes used in the design of aerospace systems are complex, requiring some ex... more Most of the analysis codes used in the design of aerospace systems are complex, requiring some expertise to set up and execute. POST, which is used in many conceptual design studies to compute space vehicle performance characteristics, often encounters numerical difficulties in solving the defined trajectory problem. Usually POST fails to converge when its control variables are given a bad set of initial guesses, causing the trajectory to remain in the infeasible design region throughout the computations. The user then analyzes the output produced and relies on a set of heuristics, typically gained from experience with the program, to determine the appropriate modification to the problem setup that will guide POST in finding a feasible region and eventually converge to a solution.
Constant dynamic pressure trajectory simulation with POST
36th AIAA Aerospace Sciences Meeting and Exhibit, 1998
with the charter of identifying economically attractive candidate space transfer vehicle systems ... more with the charter of identifying economically attractive candidate space transfer vehicle systems for ferrying components of Space Solar Power (SSP) satellites from Low Earth Orbit (LEO) to Geostationary Earth Orbit (GEO). An aggressive price goal of only 400/kgofpayloadwasestablishedinordertocontrolthecostoftransportationfortheSSPsatellitedeveloper.Amulti−stepdecisionprocesswasemployedtodown−selectfromalargenumberofcandidatesystemstofour.ThefinalfourconceptswereNuclearThermalRocket(NTR),SolarThermalRocket(STR),arotatingtether,andSolarElectricPropulsion(SEP).AdditionalconceptsconsideredwereDual−Mode(Chemical/SEP)andAll−Chemical.Resultsshowthatthemosteconomicalconceptisonewhichishighlyreusable,hasashortturnaroundtime,alongvehiclelife,andsmallpropellantrequirements.Thesecharacteristicsresultinalowfleetsizeandthereforelowerdebtrequirements.ThesecharacteristicsalsolowertheInitialMassinLowEarthOrbit(IMLEO)andthereforelowerdeploymentcosts.Thegoalof400/kg of payload was established in order to control the cost of transportation for the SSP satellite developer. A multi-step decision process was employed to down-select from a large number of candidate systems to four. The final four concepts were Nuclear Thermal Rocket (NTR), Solar Thermal Rocket (STR), a rotating tether, and Solar Electric Propulsion (SEP). Additional concepts considered were Dual-Mode (Chemical/SEP) and All-Chemical. Results show that the most economical concept is one which is highly reusable, has a short turnaround time, a long vehicle life, and small propellant requirements. These characteristics result in a low fleet size and therefore lower debt requirements. These characteristics also lower the Initial Mass in Low Earth Orbit (IMLEO) and therefore lower deployment costs. The goal of 400/kgofpayloadwasestablishedinordertocontrolthecostoftransportationfortheSSPsatellitedeveloper.Amulti−stepdecisionprocesswasemployedtodown−selectfromalargenumberofcandidatesystemstofour.ThefinalfourconceptswereNuclearThermalRocket(NTR),SolarThermalRocket(STR),arotatingtether,andSolarElectricPropulsion(SEP).AdditionalconceptsconsideredwereDual−Mode(Chemical/SEP)andAll−Chemical.Resultsshowthatthemosteconomicalconceptisonewhichishighlyreusable,hasashortturnaroundtime,alongvehiclelife,andsmallpropellantrequirements.Thesecharacteristicsresultinalowfleetsizeandthereforelowerdebtrequirements.ThesecharacteristicsalsolowertheInitialMassinLowEarthOrbit(IMLEO)andthereforelowerdeploymentcosts.Thegoalof400/kg, or 2.5¢/kW-hr, for in-space transportation costs is very aggressive and difficult to achieve.
A collaborative optimization approach to improve the design and deployment of satellite constellations
A collaborative optimization approach to design and deployment of a space based infrared system constellation
2000 IEEE Aerospace Conference. Proceedings (Cat. No.00TH8484), 2000
Design and Deployment of a Satellite Constellation Using Collaborative Optimization
Journal of Spacecraft and Rockets, 2004
Design and Deployment of a Satellite Constellation Using Collaborative Optimization
Journal of Spacecraft and Rockets, 2004
A collaborative optimization approach to improve the design and deployment of satellite constellations
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.
Most of the analysis codes used in the design of aerospace systems are complex, requiring some ex... more Most of the analysis codes used in the design of aerospace systems are complex, requiring some expertise to set up and execute. POST, which is used in many conceptual design studies to compute space vehicle performance characteristics, often encounters numerical difficulties in solving the defined trajectory problem. Usually POST fails to converge when its control variables are given a bad set of initial guesses, causing the trajectory to remain in the infeasible design region throughout the computations. The user then analyzes the output produced and relies on a set of heuristics, typically gained from experience with the program, to determine the appropriate modification to the problem setup that will guide POST in finding a feasible region and eventually converge to a solution.
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.
IEEE P335E A Collaborative Optimization Approach to Design and Deployment of a Space Based Infrared System Constellation
Design and Deployment of a Satellite Constellation Using Collaborative Optimization
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.