Lockheed L-301

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L-301
X-24C configuration images circa January 1977
Role	Hypersonic research project
National origin	United States
Manufacturer	Lockheed
Status	Cancelled project
Number built	None

Lockheed L-301 (sometimes called the X-24C, though this designation was never officially assigned) was an experimental air-breathing hypersonic aircraft project. It was developed by the NASA and USAF organization National Hypersonic Flight Research Facility^[1] (NHFRF or NHRF^[2]), with Skunk Works as the prime contractor. In January 1977, the program was "tentatively scheduled to operate two vehicles for eight years and to conduct 100 flights per vehicle."^[3] NASA discontinued work on L-301 and NHRF in September 1977 due to budget constraints and lack of need.^[1]

Development

The L-301 HGV was intended to be a follow-on to the X-15 and X-24 (specifically the X-24B) programs, to take lessons learned from both and integrate them into an airframe capable of at least reaching Mach 8 and engaging in hypersonic skip-glide maneuvers for long range missions. While the NASA program, one of several to use the tentative X-24C designator, was ostensibly canceled in 1977, it was only canceled at the time because of USAF disclosures of duplicate black programs with the same contractors for similar vehicles. The vehicle used both air breathing ram or scramjet propulsion as well as a rocket engine, carrying both RP-1 and LH2 propellant as well as on board stores of LOX.
It is presently undetermined whether the black program ever resulted in flight tests, however wind tunnel models are well documented online by both Lockheed and USAF websites,^[4] while Lockheed drawings have appeared on the web,^[5] particularly on the sites of modelers producing models of this vehicle. Aviation historian Rene Francillion believes Lockheed did fly a testbed aircraft in 1982.^{[citation needed]}

Design

Propulsion

Originally intended to carry the same XLR-99 engine used by the X-15, the primary engine was changed to the LR-105, which was the sustainer engine used on the Atlas launcher. This rocket engine, burning RP-1 and LOX, was intended to accelerate the X-24C to hypersonic speeds in order to ignite the hydrogen fueled, air breathing ram/scramjet mounted in the belly of the airframe with which it would attain cruise speeds of at least Mach 6 and peak velocities of Mach 8+ at altitudes of 90,000 feet or more.
As such, this vehicle was plainly not intended to reach orbit, but may have served as a technology testbed for development of later black orbiter programs such as COPPER CANYON, HAVE SPACE, HAVE REGION, among others, perhaps even the purported Blackstar project. It may also have served as an intermediate stage for an expendable upper stage capable of putting a small payload in orbit.

Airframe

Design of the aircraft in various wind tunnel models and contractor drawings seems to follow variations of the FDL-5 and FDL-8 lifting body shapes originally developed by the USAF Flight Dynamics Laboratory in the 1950s, which were used in the earlier X-23 and X-24A/B programs. With a radically swept delta wing, and 2, 3, or 4 vertical stabilizers, as well as several body flaps (depending on the model), the vehicle did not lack for control surfaces. The vehicle measured 74 feet 10 inches long, 24 ft, 2 in wingspan, and 20 ft, 7 in height.
Various drawings show a payload bay twelve feet long and perhaps five feet diameter. This would certainly have been sufficient for delivering military ordnance on a transcontinental skip-glide strike mission. It may also have been large enough to carry an upper stage and a small satellite for a surprise orbiting which would eliminate the problem spy satellites have of having their ephemerides predicted and used by enemy nations to hide sensitive observation targets.