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{{More sources|date=September 2024}}{{Short description|American experimental aircraft}}
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{{Infobox aircraft
{{infobox Aircraft
|name = X-23 PRIME
|name = X-23A PRIME
|image = File:X23_PRIME.JPG
|caption = Preserved X-23A PRIME at USAF Museum, Dayton, Ohio
|type = Lifting body
|type = Lifting body
|national_origin = United States
|manufacturer = [[Martin Marietta]]
|manufacturer = [[Martin Marietta]]
|image =Image:X23_PRIME.JPG
|caption = Preserved X-23 PRIME at USAF Museum, Dayton, Ohio
|designer =
|designer =
|first flight = [[21 December]] [[1966 in aviation|1966]]
|first_flight = 21 December 1966
|introduced =
|introduction =
|retired = [[19 April]] [[1967 in aviation|1967]]
|retired = 19 April 1967
|produced =
|produced =
|number built = 3
|number_built = 3
|status = Out of service
|status = Out of service
|unit cost =
|unit cost =
|primary user = [[United States Air Force]]
|primary_user = [[United States Air Force]]
|more users =
|more_users =
|developed from =
|developed_from =
|variants with their own articles = [[Martin-Marietta X-24|Martin X-24]]
|variants = [[Martin Marietta X-24]]
}}
}}


The [[Martin Marietta]] '''X-23A PRIME''' (Precision Reentry Including Maneuvering reEntry) was a small [[lifting body]] [[Atmospheric reentry|re-entry vehicle]] tested by the [[United States Air Force]] in the mid-1960s. Unlike [[ASSET (spaceplane)|ASSET]], primarily used for structural and heating research, the X-23 PRIME was developed to study the effects of maneuvering during re-entry, including [[cross-range]] maneuvers up to 710 statute miles (1143 km) off the ballistic track.
The '''Martin X-23A PRIME''' (Precision Reentry Including Maneuvering reEntry) (SV-5D) is a small [[lifting body|lifting-body]] [[re-entry vehicle]] tested by the [[United States Air Force]] in the mid-1960s. Unlike [[ASSET (spacecraft)|ASSET]], primarily used for structural and heating research, the X-23A PRIME was developed to study the effects of maneuvering during re-entry of [[Earth's atmosphere]], including cross-range maneuvers up to {{cvt|617|nmi|mi km|0}} from the [[Trajectory of a projectile|ballistic]] track.


== Design ==
== Design ==
Each X-23 was constructed from [[titanium]], [[beryllium]], [[stainless steel]], and [[aluminium]] "where appropriate". The craft consisted of two sections — the aft main structure and a removable forward "glove section". The structure was completely covered with a Martin-developed [[ablative]] [[heat shield]] 20 to 70 mm (¾ to 2¾ inches) thick, though the nose cap was constructed of [[carbon-phenolic]].
Each X-23A was constructed from [[titanium]], [[beryllium]], [[stainless steel]], and [[aluminium|aluminum]]. The craft consisted of two sections—the aft main structure and a removable forward "glove section". The structure was completely covered with a Martin-developed [[Ablation|ablative]] [[heat shield]] {{cvt|0.75|to|2.75|in|0}} thick, and the [[Nose cone|nose cap]] was constructed of [[Pyrolytic carbon|carbon]] [[Phenol formaldehyde resin|phenolic]] material.<ref name="NASA">{{cite book |last1=Jenkins |first1=Dennis R. |last2=Landis |first2=Tony |last3=Miller |first3=Jay |title=AMERICAN X-VEHICLES An Inventory—X-1 to X-50 : Monographs in Aerospace History No. 31, SP-2003-4531 |date=June 2003 |publisher=National Aeronautics and Space Administration |location=Washington, DC |page=30}}</ref><ref name=Miller>{{cite book |last1=Miller |first1=Jay |title=The X-planes : X-1 to X-29 |date=1983 |publisher=Speciality Press |location=Marine on St. Croix |isbn=0933424353 |pages=148–149}}</ref>


Aerodynamic control was provided by a pair of 12-inch (30 cm) square lower flaps, and fixed upper flaps and rudders. A [[nitrogen]] gas [[reaction control system]] was used outside the atmosphere. At Mach 2 a [[drogue]] [[ballute]] deployed and slowed the vehicle's descent. As it deployed, its cable sliced the upper structure of the main equipment bay, allowing a 47-foot (16.4 m) recovery chute to deploy. It would then be recovered by a specially-equipped [[C-130 Hercules|JC-130B]] Hercules.
[[Aerodynamic]] control was provided by a pair of {{cvt|12|x|12|in|0}} lower [[Flap (aircraft)|flaps]], and fixed upper flaps and [[Rudder#Aircraft rudders|rudder]]s. A [[nitrogen]]-gas [[reaction control system]] was used outside the atmosphere. At [[Mach number|Mach 2]] a [[drogue]] [[ballute]] deployed and slowed the vehicle's descent. As it deployed, its cable sliced the upper structure of the main equipment bay, allowing a {{cvt|47|ft|0}} recovery [[Parachute|chute]] to deploy. It would then be [[Mid-air retrieval|recovered in midair]] by a specially-equipped [[Lockheed C-130 Hercules|JC-130B]] Hercules aircraft.<ref name="NASA"/><ref name=Miller/>


== Flight testing ==
== Flight testing ==
The first PRIME vehicle was launched from [[Vandenberg AFB]] on [[21 December]] [[1966 in aviation|1966]] atop an [[Atlas missile|Atlas launch vehicle]]. This mission simulated a low-earth orbit reentry with a zero cross-range. The ballute deployed at 99,850 feet (30.43 km), though the recovery parachute failed to completely deploy. The vehicle crashed into the Pacific.
The first PRIME vehicle was launched from [[Vandenberg AFB]] on 21 December 1966 atop an [[Atlas SLV-3]] [[launch vehicle]]. This mission simulated a [[low Earth orbit]] reentry with a zero cross-range. The ballute deployed at {{cvt|99850|ft|0}}, though the recovery parachute failed to completely deploy. The vehicle crashed into the Pacific Ocean.<ref name="NASA"/><ref name=Miller/>


The second vehicle was launched on 5 March 1967. This flight simulated a 654-mile (1053-kilometre) cross-range reentry, and banking at hypersonic speeds. The recovery parachute deployed properly and was located by two of the deployed recovery aircraft. During an inspection fly-by of the descending parachute system it was seen that reefing cutters had failed to actuate. These cutters are on the harness suspending the vehicle from the parachute to ensure stability of the vehicle behind the JC-130B recovery aircraft during reel-in, and permit safely boarding the vehicle. As a result, the parachute and vehicle were allowed to descend to the sea. Subsequently, the vehicle separated from its flotation "balloon" in the rough seas and, with the parachute, sank before a nearby ship could arrive to retrieve it from the ocean.<ref name="NASA"/><ref name=Miller/>
The second was launched on [[5 March]] [[1967]]. This flight simulated a 654-mile (1053 km) cross range re-entry, and banking at hypersonic speeds. Several stringers on the main parachute failed to cut, preventing a successful recovery. It too was lost in the Pacific.


The final PRIME mission was flown on [[19 April]] [[1967]], and simulated reentry from low-earth orbit with a 710 mile (1143 km) cross-range. This time, all systems performed perfectly, and the X-23 was successfully recovered. An inspection by a USAF-Martin team reported the craft "ready to fly again", although no later missions were carried out. The third X-23 is now on display at the [[National Museum of the United States Air Force]] at [[Wright-Patterson AFB, Ohio|Wright-Patterson]] Ohio.
The final PRIME mission was flown on 19 April 1967, and simulated re-entry from low Earth orbit with a {{cvt|617|nmi|mi km|0}} cross-range. This time, all systems performed perfectly, and the X-23A was successfully recovered. An inspection by a USAF-Martin team reported the craft "ready to fly again", although no later missions were carried out. The third X-23A is now on display at the [[National Museum of the United States Air Force]] at [[Wright-Patterson Air Force Base]] in Ohio.<ref name="NASA"/><ref name=Miller/>


== Specifications (X-23) ==
== Specifications (X-23A) ==
{{aero-specs}}
{{Aircraft specs
|ref=The X-planes : X-1 to X-29<ref name=Miller/><ref>{{cite web |url=https://www.researchgate.net/publication/276294924 |url-status=dead |archive-url=https://web.archive.org/web/20210501004337/https://www.researchgate.net/publication/276294924_Martin_X-24A_Lifting_Body |archive-date=2021-05-01 |title=Martin X-24A Lifting Body}}</ref>
{{aircraft specifications
|prime units?=kts
|plane or copter?=plane
|length ft= 6
|jet or prop?=jet
|length in= 8
|ref=
|span ft= 3
|crew=None
|span in= 10
|capacity=
|height ft= 2
|payload main=
|height in= 10
|payload alt=
|gross weight lb= 894
|length main= 6 ft 9 in
|eng1 name=[[Nitrogen]] gas [[Reaction control system|reaction control thruster]]s
|length alt= 2.07 m
|max speed kts=14388
|span main= 3 ft 10 in
|max speed note=
|span alt= 1.16 m
|max speed mach=25
|height main= 2 ft 1 in
|range miles=
|height alt= 0.64 m
|area main=
|range km=
|area alt=
|airfoil=
|empty weight main=
|empty weight alt=
|loaded weight main= 890 lb
|loaded weight alt= 405 kg
|useful load main=
|useful load alt=
|max takeoff weight main=
|max takeoff weight alt=
|more general=
|engine (jet)=Nitrogen-gas reaction control thrusters
|type of jet=
|number of jets=
|thrust main=
|thrust alt=
|thrust original=
|afterburning thrust main=
|afterburning thrust alt=
|max speed main=Mach 25
|max speed alt=
|cruise speed main=
|cruise speed alt=
|stall speed main=
|stall speed alt=
|never exceed speed main=
|never exceed speed alt=
|range main= 710 miles
|range alt= 1,143 km
|ceiling main=
|ceiling alt=
|climb rate main=
|climb rate alt=
|loading main=
|loading alt=
|thrust/weight=
|power/mass main=
|power/mass alt=
|more performance=
|more performance=
* '''Hypersonic L/D Ratio:''' 1:1
* '''Hypersonic L/D Ratio:''' 1:1{{citation needed|date=December 2020}}
|armament=
|avionics=
|avionics=
}}
}}
Line 98: Line 61:
{{aircontent|
{{aircontent|
|related=
|related=

|similar aircraft=
|similar aircraft=
[[BOR-4|Molniya BOR-4]]<br>
*[[BOR-4|Molniya BOR-4]]
[[ASSET (spaceplane)|ASSET]]
*[[ASSET (spacecraft)|ASSET]]
|sequence=
[[X-20 Dyna-Soar|X-20]] -
[[Northrop X-21|X-21]] -
[[Bell X-22|X-22]] -
'''X-23''' -
[[Martin-Marietta X-24|X-24]] -
[[Bensen X-25|X-25]] -
[[X-26 Frigate|X-26]]

|lists=
|lists=

|see also=
|see also=
{{X-planes}}
}}
}}
{{aviation lists}}


== References==
[[Category:Glider aircraft]]
{{reflist}}
[[Category:Lifting body aircraft]]

==External links==
{{commons category|Martin Marietta X-23}}
*[https://web.archive.org/web/20090212224747/http://astronautix.com/craft/prime.htm Encyclopedia Astronautica]
*[https://www.youtube.com/watch?v=gDAPjumZA1s Video] Atlas X-38 Prototype Arrival (PRIME/X-23), Unloading, Mating and Launch

{{Martin aircraft}}
{{X-planes}}

{{DEFAULTSORT:Martin X-23 Prime}}
[[Category:United States military gliders]]
[[Category:Lifting bodies]]
[[Category:Spaceplanes]]
[[Category:Spaceplanes]]
[[Category:United States experimental aircraft 1960-1969]]
[[Category:1960s United States experimental aircraft]]
[[Category:UAVs and drones]]
[[Category:Unmanned aerial vehicles of the United States]]
[[Category:Martin aircraft|X-23]]

[[Category:Aircraft first flown in 1966]]
[[de:Martin-Marietta X-23]]
[[Category:Twin-tail aircraft]]

Latest revision as of 02:25, 25 November 2024

X-23A PRIME
Preserved X-23A PRIME at USAF Museum, Dayton, Ohio
General information
TypeLifting body
National originUnited States
ManufacturerMartin Marietta
StatusOut of service
Primary userUnited States Air Force
Number built3
History
First flight21 December 1966
Retired19 April 1967
VariantsMartin Marietta X-24

The Martin X-23A PRIME (Precision Reentry Including Maneuvering reEntry) (SV-5D) is a small lifting-body re-entry vehicle tested by the United States Air Force in the mid-1960s. Unlike ASSET, primarily used for structural and heating research, the X-23A PRIME was developed to study the effects of maneuvering during re-entry of Earth's atmosphere, including cross-range maneuvers up to 617 nmi (710 mi; 1,143 km) from the ballistic track.

Design

[edit]

Each X-23A was constructed from titanium, beryllium, stainless steel, and aluminum. The craft consisted of two sections—the aft main structure and a removable forward "glove section". The structure was completely covered with a Martin-developed ablative heat shield 0.75 to 2.75 in (19 to 70 mm) thick, and the nose cap was constructed of carbon phenolic material.[1][2]

Aerodynamic control was provided by a pair of 12 in × 12 in (305 mm × 305 mm) lower flaps, and fixed upper flaps and rudders. A nitrogen-gas reaction control system was used outside the atmosphere. At Mach 2 a drogue ballute deployed and slowed the vehicle's descent. As it deployed, its cable sliced the upper structure of the main equipment bay, allowing a 47 ft (14 m) recovery chute to deploy. It would then be recovered in midair by a specially-equipped JC-130B Hercules aircraft.[1][2]

Flight testing

[edit]

The first PRIME vehicle was launched from Vandenberg AFB on 21 December 1966 atop an Atlas SLV-3 launch vehicle. This mission simulated a low Earth orbit reentry with a zero cross-range. The ballute deployed at 99,850 ft (30,434 m), though the recovery parachute failed to completely deploy. The vehicle crashed into the Pacific Ocean.[1][2]

The second vehicle was launched on 5 March 1967. This flight simulated a 654-mile (1053-kilometre) cross-range reentry, and banking at hypersonic speeds. The recovery parachute deployed properly and was located by two of the deployed recovery aircraft. During an inspection fly-by of the descending parachute system it was seen that reefing cutters had failed to actuate. These cutters are on the harness suspending the vehicle from the parachute to ensure stability of the vehicle behind the JC-130B recovery aircraft during reel-in, and permit safely boarding the vehicle. As a result, the parachute and vehicle were allowed to descend to the sea. Subsequently, the vehicle separated from its flotation "balloon" in the rough seas and, with the parachute, sank before a nearby ship could arrive to retrieve it from the ocean.[1][2]

The final PRIME mission was flown on 19 April 1967, and simulated re-entry from low Earth orbit with a 617 nmi (710 mi; 1,143 km) cross-range. This time, all systems performed perfectly, and the X-23A was successfully recovered. An inspection by a USAF-Martin team reported the craft "ready to fly again", although no later missions were carried out. The third X-23A is now on display at the National Museum of the United States Air Force at Wright-Patterson Air Force Base in Ohio.[1][2]

Specifications (X-23A)

[edit]

Data from The X-planes : X-1 to X-29[2][3]

General characteristics

  • Length: 6 ft 8 in (2.03 m)
  • Wingspan: 3 ft 10 in (1.17 m)
  • Height: 2 ft 10 in (0.86 m)
  • Gross weight: 894 lb (406 kg)
  • Powerplant: × Nitrogen gas reaction control thrusters

Performance

  • Maximum speed: 14,388 kn (16,557 mph, 26,647 km/h)
  • Maximum speed: Mach 25
  • Hypersonic L/D Ratio: 1:1[citation needed]

See also

[edit]

Aircraft of comparable role, configuration, and era

References

[edit]
  1. ^ a b c d e Jenkins, Dennis R.; Landis, Tony; Miller, Jay (June 2003). AMERICAN X-VEHICLES An Inventory—X-1 to X-50 : Monographs in Aerospace History No. 31, SP-2003-4531. Washington, DC: National Aeronautics and Space Administration. p. 30.
  2. ^ a b c d e f Miller, Jay (1983). The X-planes : X-1 to X-29. Marine on St. Croix: Speciality Press. pp. 148–149. ISBN 0933424353.
  3. ^ "Martin X-24A Lifting Body". Archived from the original on 2021-05-01.
[edit]
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