b'Aerospace | Engineer InnovationHydrogen 4: OHOxygen 5: 06: HDiphasic fluid definition 7: HO2Fairing Second StageGas Mixture - Gaseous phasesLinear AnalysisSecond StageLH 2Tank SimcenterGas Jet SystemSecond Stage LQG/LTR Controller modelLox TankLE-5B-3Second StageEngine LE-5B-3First StageLox TankCo-simulation (MiL)First StageFirst StageLH 2Tanksimulation results will remain reusableLE-9 Control design flow using and accessible to anyone in the designSimcenter Amesimteam. Developing a LQG/LTR controller for the LE-9 engine requires:The LE-5B-2 engine model results were compared with existing results, showing a a simulation environment able to SRB-3good agreement with both the in-housegenerate a state-space representation Solid Rocket simulation tool results and firing tests. of the engine, andBoosterSRB-3a co-simulation capability with the Modern control design for the firstcontroller development environment.stage engine LE-9The engines currently in operation useSimcenter Amesim provides these H3-32L First stage Engine LE-9 Proportional-IntegraI control as acapabilities. The state-space baseline. It has limitations. representation can be obtainedOne of the MHIs older engine designautomatically thanks to the Linear required one hundred tests and three Interactions between fuel-oxidizerAnalysis tools. And the Simcenter Amesim years duration to fix the start/stopMixture Ratio (MR) control loops and- MATLAB/Simulink standard interface sequence, and the thrust generated are observed inallows the co-simulation with models ofAs experienced workers leave thefiring tests. It requires additional workthe controller, in a Model-in-the-Loop organization, they take with themto add decoupling and cancel them. (MiL) configuration. MiL allows fast accumulated knowledge and skills, There is no control during flightdevelopment as you can make changes to making it difficult to maintain andbecause some quantities, such as thethe control model and immediately test upgrade legacy simulation tools. MR, are difficult to measure. the system. The engine must accommodate a Simcenter Amesim was selected towide range of operating points. ThisConclusionsdevelop the transient simulation model ofis due to variation in the launchersSiemens, MHI and Churyo Engineering the LE-5B-2 engine. When usingacceleration, which changes thehave developed in close collaboration a Simcenter Amesim the engineers benefitengine operating point, and run-to-runframework for rocket engine transient from the latest development of Simcentervariation. analysis and control development. The Amesim liquid propulsion solution (andmethodology is now mature enough to the associated libraries, Two-Phase flowA more robust control strategy, the Linearbe applied on current developments and and Gas Mixture). Quadratic Servo Control (LQG/LTR), isshould support MHI objective of a launch selected. With this approach it is easier toservice price reduced by half compared to Building engine models in the Simcenterdecouple interactions and it provides aHII family and aims to be on par with Amesim environment ensures thatMR estimator during the flight. SpaceXs Falcon 9. n33'