Boeing X-40
| Boeing X-40A | ||
|---|---|---|
| ||
| Description | ||
| Role | Glide Test Vehicle | |
| Crew | 0 | |
| First Flight | March 14, 2001 (dropped by CH-47) | |
| Manufacturer | Boeing | |
| Dimensions | ||
| Length | 21ft 5in | 6.5 m |
| Wingspan | 11ft 6in | 3.5 m |
| Height | 7ft 5in | 2.3 m |
| Wing area | ft² | m² |
| Weights | ||
| Empty | lb | kg |
| Performance | ||
| Maximum speed | 300 mph | 480 km/h |
| Avionics | ||
| Avionics | Honeywell 12-channel Space Integrated GPS/INS (SIGI) system. | |
The Boeing X-40A Space Maneuver Vehicle was part of the X-37 Future-X Reusable Launch Vehicle project. Built to 85 percent scale, in 2001 it successfully demonstrated the glide capabilities of the X-37's fat-bodied, short-winged design and validated the proposed guidance system.
See also
External link
- NASA Dryden X-40A SMV Photo Collection (http://www.dfrc.nasa.gov/gallery/Photo/X-40A/index.html)
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