Abstract
Sensor structural feedback and propellant sloshing have an adverse affect on the stability of conventional launch vehicles. Additionally, vehicle flight loads increase due to structural vibrations. However, in the conceptual design phase of a conventional launch vehicle, it is computationally expensive and undesirable to model the aeroelastic effects on its controllability, stability, and flightperformance. Therefore, this paper focusses on the assumed-modes method of analysing aeroelastic effects on a slender-bodied conventional launch vehicle.The general model consists of the structural stiffness and mass properties, discretised over the length of the launcher; flight mechanics, which are simplified to only the pitch-plane equations; and engine swivel, acting as a control (thrust and moment) actuator. The structural representation and flight dynamics are combined in a state-space model with a simple PD controller to evaluate the stability and control of the system, without attempting to optimize for performance. The response to a step-command, with and without turbulence, is examined and compared for rigid, flexible modes, and flexible modes with sloshing effects. Flexible modes and sloshing effects have a destabilising influence, which, if coupled with non-optimal feedback signals, may result in excessive flight loads.
| Original language | English |
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| Title of host publication | Proceedings of the 67th International Astronautical Congress (IAC) |
| Subtitle of host publication | Guadalajara, Mexico |
| Publisher | IAF |
| Number of pages | 15 |
| Publication status | Published - 2016 |
| Event | 67th International Astronautical Congress - Guadalajara, Mexico Duration: 26 Sept 2016 → 30 Sept 2016 Conference number: 37 https://www.iac2016.org/ |
Conference
| Conference | 67th International Astronautical Congress |
|---|---|
| Abbreviated title | 67th IAC |
| Country/Territory | Mexico |
| City | Guadalajara |
| Period | 26/09/16 → 30/09/16 |
| Internet address |