| dc.creator |
Zare Shahneh, Amir |
|
| dc.date |
2018-09-12T13:34:53Z |
|
| dc.date |
2018-09-12T13:34:53Z |
|
| dc.date |
2018-09-11 |
|
| dc.date.accessioned |
2022-05-25T16:38:27Z |
|
| dc.date.available |
2022-05-25T16:38:27Z |
|
| dc.identifier |
Amir Zare Shahneh. Compound actuation system design for an advanced space transportation reusable orbiter. Aeronautics and Aerospace Open Access Journal, 2018, Volume 2, Issue 5, pp264-268 |
|
| dc.identifier |
2576-4500 |
|
| dc.identifier |
https://doi.org/10.15406/aaoaj.2018.02.00059 |
|
| dc.identifier |
http://dspace.lib.cranfield.ac.uk/handle/1826/13479 |
|
| dc.identifier.uri |
http://localhost:8080/xmlui/handle/CUHPOERS/182336 |
|
| dc.description |
The SL-12 is a reusable space orbiter which offers the capability to go beyond the
notion of a second generation space shuttle, and is targeted to be in operation in the
year 2020. SL-12 Orbiter utilizes gimballing of the main rocket engines for control
during ascent and typical aerodynamic surfaces for control during re-entry, approach,
and landing. Power by wire (PBW) Actuation system is used for SL-12 based on All
Electric Aircraft (AEA) approach. Electro Hydrostatic Actuators have been used for
Primary Flight Control surfaces (Elevon, Body Flap and Rudder) and Thrust Vector
Control for Main Engine Module, Electro Mechanical actuators have been used for
Thrust Vector Control of Orbital Maneuvering System and Payload bay door. Dual
redundant electric power supply channels are used for redundancy. Actuation System
Safety and Reliability analysis has been done to ensure compliance and specification
requirements. |
|
| dc.language |
en |
|
| dc.publisher |
MedCrave Group |
|
| dc.rights |
Attribution-NonCommercial 4.0 International |
|
| dc.rights |
http://creativecommons.org/licenses/by-nc/4.0/ |
|
| dc.title |
Compound actuation system design for an advanced space transportation reusable orbiter |
|
| dc.type |
Article |
|