The Space Launch System is a Shuttle-derived heavy-lift vehicle currently in development to serve as NASA’s premiere launch vehicle for space exploration. The Space Launch System is a multistage rocket with two Solid Rocket Boosters and multiple payloads, including the Multi-Purpose Crew Vehicle. Planned Space Launch System destinations include near-Earth asteroids, the Moon, Mars, and Lagrange...

Collaborative optimization is a new design architecture speci cally created for large-scale distributed-analysis applications. In this approach, a problem is decomposed into a user-de ned number of subspace optimization problems that are driven towards interdisciplinary compatibility and the appropriate solution by a system-level coordination process. This decentralized design strategy allows d...

A method for solving finite-horizon optimal control of nonlinear systems has been developed in this paper and used for an online path planning problem. The new controller synthesis is motivated by the state-dependent Riccati equation (SDRE) technique that was developed for solving regulator and tracking problems. However, finite-time problems need to meet specified boundary conditions for the a...

Abstract In this paper, the ascent trajectory optimization of a lifting body Single-Stage To Orbit (SSTO) reusable launch vehicle is investigated. The work carried out using Direct Multiple Shooting method to solve Optimal Control problem. crucial initialisation optimisation process performed by combination two evolutionary algorithms, namely Multi-Objective Parzen-based Estimation Distribution...

Abstract In the last decade, rapid and successful development of reusable launch systems such as SpaceX’ Falcon 9 demonstrated both operational feasibility launchers their economic viability. The objective recovering a launcher or launcher’s booster requires to safely return vehicle from orbital sub-orbital conditions soft landing. To increase reusability, decrease turnaround time reduce costs,...

For the safe operation of a complex system like a (manned) launch vehicle, real-time information about the state of the system and potential faults is extremely important. The on-board FDDR (Failure Detection, Diagnostics, and Response) system is a software system to detect and identify failures, provide real-time diagnostics, and to initiate fault recovery and mitigation. The ERIS (Evaluation ...

Abstract The assessment of thermal loads occurring on reusable launch vehicles during the entire trajectory is essential for correct dimensioning protection system. Due to costs and limitations ground-based testing large-scale vehicles, these predictions rely intensively numerical simulations (CFD). need aero-thermal databases, as a fast-response surrogate model aero-thermodynamic heating, aris...

Current methods for defining the operational support requirements of new systems are data intensive and require significant design information. Methods are being developed to aid in the analysis process of defining support requirements for new launch vehicles during their conceptual design phase that work with the level of information available during this phase. These methods will provide supp...

1 0-7803-6599-2/01/$10.00 © 2001 IEEE. Abstract— This paper presents an adaptive guidance system approach applied to hypersonic Reusable Launch Vehicles (RLVs). After an effector failure, it is assumed that the inner-closed-loop system utilizes a reconfigurable control algorithm to recover nominal maneuvering capabilities to the extent possible. However, nominal performance will typically not b...

Flexible inhibitors are generally used in solid rocket motors (SRMs) as a means to control the burning of propellant. Vortices generated by the flow of propellant around the flexible inhibitors have been identified as a driving source of instabilities that can lead to thrust oscillations in launch vehicles. Potential coupling between the SRM thrust oscillations and structural vibration modes is...