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Little Joe II
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Little Joe II
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Little Joe II
Launch of Apollo A-002 escape system test on the third Little Joe II
FunctionApollo launch escape system testing
ManufacturerConvair Division of General Dynamics
Country of originUnited States
Size
Height1,032 inches (26.2 m) with payload
Diameter154 inches (3.9 m)
Width341 inches (8.7 m) at fins
Stages1
Launch history
StatusRetired
Launch sitesLaunch complex 36, White Sands Missile Range, New Mexico
Total launches5
Success(es)4
Partial failure1
First flight28 August 1963
Last flight20 January 1966
Boosters
No. boosters6[N 1]
Powered by1 Thiokol 1.5KS35000 Recruit
Maximum thrust38,000 pounds-force (170 kN)
Total thrust228,000 pounds-force (1,010 kN)[N 1]
Burn time~1.53 s
PropellantSolid
First stage
Powered by1 Aerojet Algol 1-D sustainer[N 2]
Maximum thrust105,100 pounds-force (468 kN)[N 2]
Burn time~40 s
PropellantSolid
[edit on Wikidata]

Little Joe II was an American rocket used from 1963 to 1966 for five uncrewed tests of the Apollo spacecraft launch escape system (LES), and to verify the performance of the command module parachute recovery system in abort mode. It was named after a similar rocket designed for the same function in Project Mercury. Launched from White Sands Missile Range in New Mexico, it was the smallest of four launch rockets used in the Apollo program.

Background

[edit]

Man-rating of the Apollo launch escape system was planned to be accomplished at minimum cost early in the program. Since there were no reasonably priced launch vehicles with the payload capability and thrust versatility that could meet the requirements of the planned tests, a contract was awarded for the development and construction of a specialized launch vehicle. The rocket's predecessor, Little Joe, had been used in testing the launch escape system for the Mercury spacecraft from 1959 to 1960.

The program was originally planned to be conducted at the U.S. Air Force Eastern Test Range at Cape Kennedy, Florida. However, because of a heavy schedule of high-priority launches at that facility, other possible launch sites were evaluated including Wallops Flight Facility, Wallops Island, Virginia, and Eglin Air Force Base, Florida.[1] Launch Complex 36 at White Sands Missile Range, previously used for Redstone missile tests, was selected as the most suitable for meeting schedule and support requirements. White Sands also allowed land recovery which was less costly and complicated than the water recovery that would have been required at the Eastern Test Range or at the NASA Wallops Island facility.

The program was conducted under the direction of the Manned Spacecraft Center (now Johnson Space Center), Houston, Texas, with joint participation by the prime contractors for the launch vehicle (General Dynamics/Convair) and spacecraft (North American Rockwell). The White Sands Missile Range administrative, range, and technical organizations provided the facilities, resources, and services required. These included range safety, radar and camera tracking, command transmission, real-time data displays, photography, telemetry data acquisition, data reduction, and recovery operations.

Design

[edit]

Little Joe II was a single-stage, solid-propellant rocket which used a booster motor developed for the Recruit rocket, and a sustainer motor developed for the Algol stage of the Scout rocket family. It could fly with a variable number of booster and sustainer motors, but all were contained within a single airframe.

Development

[edit]

Fabrication of the detail parts for the first vehicle started in August 1962, and the final factory systems checkout was completed in July 1963. There was an original fixed-fin configuration and a later version using flight controls.

Four Apollo rocket assemblies, drawn to scale: Little Joe II, Saturn I, Saturn IB, and Saturn V.

The vehicle was sized to match the diameter of the Apollo spacecraft service module and to suit the length of the Algol rocket motors. Aerodynamic fins were sized to assure that the vehicle was inherently stable. The structural design was based on a gross weight of 220,000 pounds (100,000 kg), of which 80,000 pounds (36,000 kg) was payload.[citation needed] The structure was also designed for sequential firing with a possible 10-second overlap of four first-stage and three second-stage sustainer motors. Sustainer thrust was provided by Algol solid-propellant motors. The versatility of performance was achieved by varying the number and firing sequence of the primary motors (capability of up to seven) required to perform the mission. Recruit rocket motors were used for booster motors as required to supplement lift-off thrust.

A simplified design, tooling, and manufacturing concept was used to limit the number of vehicle components, reduce construction time, and hold vehicle cost to a minimum. Because overall weight was not a limiting factor in the design, over designing of primary structural members greatly reduced the number and complexity of structural proof tests. Whenever possible, vehicle systems were designed to use readily available off-the-shelf components that had proven reliability from use in other aerospace programs, and this further reduced overall costs by minimizing the amount of qualification testing required.

The Little Joe II launch vehicle proved to be very acceptable for use in this program. Two difficulties were experienced. The Qualification Test Vehicle (QTV) did not destruct when commanded to do so because improperly installed primacord did not propagate the initial detonation to the shaped charges on the Algol motor case. The fourth mission (A-003) launch vehicle became uncontrolled about 2.5 seconds after lift-off when an aerodynamic fin moved to a hard over position as the result of an electronic failure. These problems were corrected and the abort test program was completed.

Flights

[edit]
Little Joe II flight and capsule launch-escape test.

The Qualification Test Vehicle launch, on 28 August 1963, carried a dummy payload consisting of an aluminum shell in the basic shape of the Apollo command module, with an inert LES attached, and demonstrated the rocket would work for the A-001 launch. This occurred on 13 May 1964, with a boilerplate BP-12 command module, and performed the first successful abort using a live LES. A third launch on 8 December 1964, using BP-23, tested the effectiveness of the LES when the pressures and stresses on the spacecraft were similar to what they would be during a Saturn IB or Saturn V launch. The fourth flight, with BP-22 on 19 May 1965, was designed to test the escape system at a high altitude (although the abort actually occurred at low altitude due to a failure of the Little Joe II booster). The final launch, on 20 January 1966, carried the first production spacecraft, CSM-002.

Minor spacecraft design deficiencies in the parachute reefing cutters, the drogue and main parachute deployment mortar mountings, and the command and service module umbilical cutters were found and corrected before the crewed Apollo flights began. However, all command modules flown achieved satisfactory landing conditions and confirmed that, had they been crewed spacecraft, the crew would have survived the abort conditions.

In addition, two pad abort tests were conducted in which the launch escape system was activated at ground level.

Launch configuration summary

[edit]
Item QTV A-001 A-002 A-003 A-004
Launch date 28 August 1963 13 May 1964 8 December 1964 19 May 1965 20 January 1966
Capsule — BP-12 BP-23 BP-22 CSM-002
Launch weight 57,170 lb (25,930 kg) 57,940 lb (26,281 kg) 94,331 lb (42,788 kg) 177,190 lb (80,372 kg) 139,731 lb (63,381 kg)
Payload 24,224 lb (10,988 kg) 25,336 lb (11,492 kg) 27,692 lb (12,561 kg) 27,836 lb (12,626 kg) 32,445 lb (14,717 kg)
Liftoff thrust 314,000 lbf (1,400 kN) 314,000 lbf (1,400 kN) 360,000 lbf (1,600 kN) 314,000 lbf (1,395 kN) 397,000 lbf (1,766 kN)
Fins controlled No No Yes Yes Yes
Recruit booster motors 6 6 4 0 5
Algol sustainer motors 1 1 2 6 4
Altitude 27,600 ft (8,400 m) 15,400 ft (4,700 m) 15,364 ft (4,683 m) 19,501 ft (5,944 m) 74,100 ft (22,600 m)
Range 48,300 ft (14,700 m) 11,580 ft (3,530 m) 7,598 ft (2,316 m) 17,999 ft (5,486 m) 113,620 ft (34,630 m)

[citation needed]

Surviving examples

[edit]

Specifications

[edit]
  • Little Joe II
    • Thrust: 49 to 1,766 kN
    • Length: 10.1 m without CM/SM/LES
    • Length: 26.2 m with CM/SM/LES
    • Diameter: 3.9 m body
    • Fin span: 8.7 m
    • Weight: 25,900 to 80,300 kg
    • Propellant: solid
    • Burn time: ~50 s
  • Algol motor
    • Thrust: 465 kN each
    • Length: 9.1 m
    • Diameter: 1 m
    • Weight full: 10,180 kg
    • Weight empty: 1,900 kg
    • Propellant: solid
    • Burn time: 40 s
  • Recruit motor (Thiokol XM19)
    • Thrust: 167 kN
    • Length: 2.7 m
    • Diameter: 0.23 m
    • Weight: 159 kg
    • Propellant: solid
    • Burn time: 1.53 s

Notes

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References

[edit]
[edit]
Revisions and contributorsEdit on WikipediaRead on Wikipedia

Little Joe II

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from Grokipedia
Little Joe II was an American developed by ' division for the , used from 1963 to 1966 to perform five uncrewed test flights that evaluated the (LES) of the under simulated launch failure conditions. The rocket represented an enlarged adaptation of the earlier Little Joe vehicle from the Mercury program, selected for development in May 1962 to accelerate testing of the Apollo spacecraft's emergency abort capabilities, including pad aborts, aborts, and high-altitude aborts. Standing approximately 26.2 meters (86 feet) tall with a diameter of 3.96 meters (13 feet) and a gross mass of 63,300 kilograms (139,550 pounds), Little Joe II featured a clustered configuration of up to nine solid rocket motors, including and Recruit engines, to achieve velocities simulating various abort scenarios and reach apogees of up to 23 kilometers (14 miles). Constructed with corrugated aluminum panels for its , the vehicle launched boilerplate Apollo capsules from in , verifying the LES's ability to separate the crew module from the and deploy parachutes for safe recovery. All five flights—the Qualification Test Vehicle (QTV) and A-001 through A-004—successfully demonstrated the LES's despite some anomalies, such as structural failures during ascent, contributing essential data to ensure safety during potential launch emergencies and paving the way for crewed Apollo missions. The program concluded in January 1966 after the final high-altitude abort test, with surviving hardware, including a full-scale example, preserved at institutions like the Smithsonian's and the New Mexico Museum of Space History.

Background

Apollo Program Context

Following the success of NASA's Mercury program, which demonstrated human spaceflight capabilities, and the Gemini program, which advanced orbital rendezvous and extravehicular activities, the was established in 1961 with the ambitious goal of landing astronauts on the and returning them safely to by the end of the decade. This escalation required developing a new spacecraft and the massive launch vehicle, introducing significant uncertainties in performance, structural integrity, and emergency scenarios that necessitated rigorous testing of the (LES) to protect the crew during potential failures. Apollo development accelerated from 1961, with early emphasis on uncrewed tests to qualify the and LES under simulated launch conditions, including maximum (max-Q) and high-altitude aborts, to mitigate risks from the unproven such as thermal overloads and booster malfunctions. By 1963, the program shifted to a series of dedicated abort tests using boilerplate capsules, prioritizing suborbital flights to replicate critical failure points without endangering lives or requiring full orbital insertions. Launches for these tests were scheduled to begin at (WSMR) in 1963, selected over Cape Kennedy due to scheduling conflicts with manned programs and the site's advantages for land-based recovery of test articles, facilitated by its 4,000-foot elevation and existing facilities. The first qualification flight occurred there on August 28, 1963, marking the start of operational testing. Program oversight was provided by NASA's Manned Spacecraft Center (now ), which coordinated development and integration. General Dynamics/Convair served as the prime contractor for the Little Joe II rocket under a $6.32 million definitive contract signed February 18, 1963, while handled the boilerplate Apollo command module and LES integration.

Rationale and Objectives

The development of Little Joe II addressed the Apollo program's urgent need for a rapid, low-cost testing platform to evaluate the (LES) under realistic dynamic abort conditions, replicating essential Saturn V ascent profiles without the expense and complexity of a full-scale orbital . This approach enabled efficient validation of crew safety mechanisms during emergencies, such as engine failures or structural issues shortly after liftoff, while aligning with the program's aggressive schedule. Approved by in March 1962, the initiative responded to timeline pressures aiming for the first manned Apollo flight by late 1967, allowing for accelerated qualification ahead of crewed missions. A key factor in its selection was the adoption of a solid-propellant architecture, which provided superior turnaround speed and operational reliability compared to liquid-fueled alternatives, facilitating frequent test iterations with minimal logistical demands. By incorporating off-the-shelf components from the U.S. Navy's —specifically Aerojet-General first-stage motors and Recruit upper-stage motors—NASA avoided the development delays and safety risks inherent in custom liquid propulsion systems. This strategic reuse not only reduced costs but also leveraged mature, battle-proven to ensure dependable performance in high-stress environments, with the program's initial 1962 budget programmed at $1.25 million after congressional adjustments. The core objectives centered on demonstrating the LES's ability to separate the command module from the , deploy parachutes for controlled descent, and enable boilerplate capsule recovery, all under simulated abort scenarios reaching altitudes of up to 100,000 feet and speeds near Mach 1. Particular focus was placed on maximum (max-Q) conditions—where aerodynamic loads peak during ascent—and launch escape tower jettison to confirm structural integrity and aerodynamic stability at these regimes. These tests collectively qualified the LES for operational use, prioritizing crew survivability without exposing full hardware to unnecessary risks.

Design

Airframe and Stability Features

The Little Joe II employed a non-aerodynamic cylindrical to support short-duration abort tests, constructed primarily from corrugated aluminum skin panels reinforced by internal ring frames for structural integrity. The overall structure incorporated aluminum as the main material, with select elements in high-stress areas such as attachments, enabling a lightweight yet robust design capable of withstanding launch loads up to a gross weight of 220,000 pounds. With the integrated, the total vehicle height measured approximately 85 feet 7 inches (26.1 meters), and the diameter aligned with that of the Apollo service module for seamless interface compatibility. Passive stability was achieved through four clipped triangular cruciform fins mounted at the base, each featuring a 45-degree sweepback to provide aerodynamic restoring moments during ascent. These fins, canted slightly for roll control, included trailing-edge control surfaces in the production configuration to enhance across subsonic to supersonic speeds, as verified in testing. The design emphasized inherent stability without reliance on active guidance for the brief flight profiles. The payload interface centered on mounting a boilerplate Apollo command module, such as the BP-22 or BP-23 series, directly atop the (LES) via an adapter that ensured secure attachment during powered flight. A destruct system was integrated into the and LES, allowing remote command detonation to mitigate hazards over the . Launches occurred vertically from Launch Complex 36, supported by a launch stand and rail adapter that provided initial guidance and acceleration. To support varying mission requirements, the featured modular and skirt assemblies, enabling configurations with up to 6 main booster motors or equivalent combinations of units without core structural modifications. This adaptability allowed the same basic vehicle to simulate different abort scenarios by adjusting the cluster while maintaining stability characteristics.

Propulsion System

The propulsion system of the Little Joe II launch vehicle featured a variable cluster of solid-propellant motors configured to deliver high initial acceleration followed by sustained thrust, enabling simulation of critical abort conditions during Apollo spacecraft launches such as pad aborts, maximum dynamic pressure (max Q) aborts, and high-altitude aborts. The system typically included 1 to 6 Algol 1-D sustainer or booster motors, adapted from the Thor/Able upper stage, each generating 103,200 pounds (459 kN) of thrust over approximately 42 seconds. These motors provided primary propulsion, with numbers and firing sequences adjusted per mission to achieve desired velocities and apogees. Complementing the Algol motors were 0 to 6 Recruit solid-fuel boosters, each producing 33,395 pounds (149 kN) of thrust for about 1.5 seconds. These boosters, manufactured by Thiokol Chemical Corporation, were arranged around the core motors to augment liftoff thrust and replicate varying dynamic loads akin to Saturn V ascent profiles. Configurations varied by mission: for instance, one Algol with six Recruit boosters delivered peak initial thrust for pad abort tests, while six Algol motors without Recruits supported maximum dynamic pressure tests, achieving total thrust exceeding 600,000 pounds (2,700 kN). This flexibility allowed the vehicle to mimic diverse failure scenarios, such as engine-out conditions early in launch. Ignition occurred simultaneously for all motors via ground command, using pyrotechnic squibs to ensure reliable light-off under launch pad conditions. The Recruit boosters burned out shortly after liftoff, after which they were jettisoned through pyrotechnic separation systems, transitioning the vehicle to -only propulsion and reducing mass for the abort trajectory. The motors, produced by Aerojet-General Corporation, continued firing until test objectives were met or destruct systems were activated. Overall integration and vehicle assembly were handled by / as the prime contractor. This arrangement emphasized rapid response and , critical for validating the Apollo launch escape system's across simulated profiles.

Development

Manufacturing Process

The manufacturing of the Little Joe II vehicles began in early 1963 at the Convair facility in San Diego, California, following the contract award in May 1962, under the direction of General Dynamics/Convair, which served as the primary contractor responsible for the airframe design, construction, and overall system integration. Aerojet-General Corporation supplied the main Algol solid-propellant motors, while Lockheed provided the auxiliary Recruit motors, with NASA providing oversight and coordination at the White Sands Missile Range (WSMR) in New Mexico. The initial plan included one Qualification Test Vehicle (QTV) to validate the design, though adaptations were made to configure specific units for pad abort and high-altitude missions as requirements evolved. Fabrication progressed modularly, with motor clusters assembled first by securing up to seven and additional Recruit motors within the thrust bulkhead structure at the plant, followed by attachment of the aerodynamic fins for stability. Electrical systems and instrumentation were then integrated before the vehicles were disassembled for shipment to WSMR, where final steps included reassembly, fin verification, and mating of the boilerplate Apollo command module payloads to the adapters. This site-based completion allowed for test-specific customizations, such as varying motor configurations (e.g., 6-1-0 or 4-2-0 clusters) to simulate different abort scenarios. The first Little Joe II vehicle was completed in July 1963 and shipped to WSMR shortly thereafter for qualification testing. In total, seven vehicles were built: five for flight tests (including the qualification vehicle) and two dedicated to pad abort evaluations, reflecting the program's emphasis on rapid production to meet Apollo's aggressive development schedule.

Pre-Flight Testing and Modifications

Pre-flight testing for the Little Joe II vehicles began with factory-level validations at the General Dynamics/Convair facility in , , where calibration, system checks, and assembly using dummy motors were conducted from to July 1963 to verify thrust profiles and separation mechanisms. These efforts ensured the clustered solid-propellant motors—for the QTV, comprising one and six Recruit units—met performance criteria before shipment to (WSMR) in . Configurations varied across vehicles. Integration trials at WSMR followed in July 1963, involving full-vehicle rehearsals that included boilerplate capsule mating, (LES) jettison simulations, and parachute deployment packing, culminating in completion by August 1963. Structural load tests during this phase measured stresses at key stations, confirming values within 13% of design limits under simulated flight conditions. The dual-command destruct , featuring two receivers and primacord trains, underwent pre-launch functional checks to validate reliable activation. Early aerodynamic simulations at NASA's identified instability in the Little Joe II configuration, prompting a redesign with larger booster fins to enhance roll stability and overall control authority. This modification, incorporated via a contract amendment on October 18, 1963, also added attitude control subsystems to the fins, addressing limitations observed in data. By late 1963, enhanced packages—totaling 27 channels across three units—were integrated and checked out pre-launch to capture detailed abort sequence data, including acceleration and separation events. Further ground evaluations, including structural and systems assessments at WSMR and , , occurred from October 1965 to January 1966, supporting iterative improvements ahead of subsequent missions. In June to December 1965, post-test feedback led to booster modifications at , , refining clamp mechanisms for secure payload attachment and release.

Flights

Pad Abort Tests

The pad abort tests were ground-based demonstrations of the Apollo (LES), conducted without igniting the Little Joe II boosters to simulate a on the prior to liftoff. These tests used pyrotechnic devices to mimic a launch anomaly, activating the LES solid-propellant motor to separate the boilerplate command module from the service module adapter and structure. The primary goals were to validate LES performance in a zero-velocity environment, assess capsule stability and tower jettison, and verify recovery sequencing for . Both tests employed boilerplate capsules at Launch Complex 36, , , providing data that shaped manned Apollo abort procedures. The first pad abort test, designated Pad Abort Test 1 (PA-1), occurred on , 1963, using boilerplate BP-6. The LES motor ignited successfully, lifting the capsule to an apogee of approximately 4,000 feet while validating tower jettison and initial stability. parachutes deployed at about 4,100 feet, followed by main parachutes, resulting in a stable descent and soft landing 1.6 miles downrange with no structural damage to the capsule. Minor oscillations in parachute deployment were observed, attributed to wind conditions, but all primary objectives were met, confirming the LES could extract the crew from a pad . Modifications addressed the oscillation issue by refining parachute risers and sequencing timers before the second test. Pad Abort Test 2 (PA-2), conducted on June 29, 1965, utilized an updated LES configuration with boilerplate BP-23A to simulate a Block I command module. The system propelled the capsule to 5,200 feet, demonstrating improved stability during ascent and zero-velocity abort conditions. parachutes opened at 5,100 feet, initiating main chute deployment without significant sway, and the capsule landed intact 4.5 miles away after a 177-second flight. This test confirmed reliable parachute sequencing and LES reliability, with telemetry data informing refinements for subsequent Little Joe II high-altitude aborts.

High-Altitude Abort Tests

The high-altitude abort tests of the Little Joe II program consisted of four powered flights conducted at in , designed to evaluate the (LES) under dynamic flight conditions simulating various failures. These tests focused on abort initiation at specific altitudes and speeds to verify the LES's ability to separate the Apollo command module boilerplate from the booster, stabilize the capsule, deploy recovery systems, and ensure safe landing. The first, designated A-001 and launched on May 13, 1964, was intended to simulate a abort but experienced a ground command failure that prevented the abort signal from being sent. The LES did not fire, and the vehicle reached an apogee of approximately 1,200 meters (4,000 feet) before range safety destructed it at 20 seconds. The boilerplate BP-12 separated due to the explosion, stabilized, and was recovered on land about 8 miles downrange with minor damage. Although the primary LES activation objective was not met, the test provided valuable data on structural loads during ascent and confirmed capsule recovery procedures. Launched on December 8, 1964, A-002 simulated a maximum (Max-Q) abort at approximately 1,500 meters (5,000 feet) and 40 seconds into flight using boilerplate BP-23. The LES fired successfully, pulling the command module away from the booster without recontact. The capsule reached an apogee of 4,700 meters (15,400 feet), with canards deploying for stability, followed by drogue and main parachutes for a 9 miles downrange. This test validated LES performance during the aerodynamically stressful Max-Q phase. A-003, launched on May 19, 1965, aimed to assess high-altitude LES operation at around 24 kilometers (80,000 feet) with boilerplate BP-22 but encountered a partial due to loss of roll control shortly after liftoff, leading to vehicle tumbling and structural breakup at 26 seconds and 8,500 meters (28,000 feet). The LES activated automatically in response to the anomaly, separating the capsule safely from the disintegrating stack at low altitude. Despite ineffective canard deployment due to high spin rates, the command module stabilized, and recovery systems deployed successfully for a landing 5 miles downrange, demonstrating LES robustness in unplanned conditions. The program's final test, A-004, launched on January 20, 1966, evaluated a high-altitude tumbling abort using a Block I production command module (S-C002) to simulate instability. The abort was initiated at 35 seconds and 21 kilometers (70,000 feet), with the LES separating the capsule effectively. The escape tower was jettisoned at apogee over 22 kilometers (72,000 feet), and the module descended under and main parachutes for recovery 18 kilometers (11 miles) downrange. All objectives were met, confirming the LES for manned flights despite not fully achieving targeted structural loads. With the series providing essential data across nominal and off-nominal scenarios—all capsules recovered intact—the LES was certified for crewed Apollo missions.

Launch Configuration Summary

The Little Joe II program involved the launch of seven vehicles with configurations tailored to specific test objectives, including variations in the number of solid-propellant motors to achieve desired thrust profiles and abort conditions. Pad abort tests omitted main entirely, while high-altitude tests incorporated combinations of Recruit boosters and sustainers; all vehicles included telemetry pods for transmission and destruct charges for .
Flight DesignationDateNumber of Recruit BoostersAlgol Sustainer UseBoilerplate ModelAbort Mode
QTVAugust 28, 19636Yes (1)None (dummy payload)None (qualification test)
Pad Abort Test 1November 7, 19630NoBP-6Pad
A-001May 13, 19646Yes (1)BP-12Transonic
A-002December 8, 19644Yes (2)BP-23Max-Q
A-003May 19, 19650Yes (6)BP-22Low-altitude
Pad Abort Test 2June 29, 19650NoBP-23APad
A-004January 20, 19665Yes (4)S-C002 (Block I)Tumbling

Specifications

Physical Characteristics

The Little Joe II launch vehicle featured a slender airframe designed for fin-stabilized flight, with a height of approximately 10 (33 ft) in its standard configuration without payload, extending to 26.2 (86 ft) when mated to an Apollo boilerplate capsule and (LES). The main body had a of 3.96 (13 ft), while the four canted fins provided a total span of 8.2 (27 ft) to ensure aerodynamic stability during ascent. In the 4-booster configuration (4 Recruit + 2 ), the vehicle's gross liftoff weight reached approximately 25,940 kg (57,165 lb), encompassing the , clustered solid-propellant motors, and structural reinforcements, while the empty weight—excluding propellants—was approximately 2,700 kg (6,000 lb). The consisted primarily of lightweight aluminum structures for the central tube and fin assemblies, complemented by robust casings on the booster motors to withstand high-pressure . The payload interface incorporated a dedicated 3.9 m (12 ft 10 in) diameter mount to securely attach the LES to the boilerplate command module, facilitating seamless integration during ground handling and . Launches occurred from a specialized setup at the (WSMR), employing a 6 m (20 ft) launch rail mounted on a pivotable steel tower to accommodate elevation angles up to 90 degrees and precise alignment. This configuration allowed for vertical or near-vertical trajectories essential to simulating abort scenarios without requiring extensive site modifications.

Performance Data

The Little Joe II launch vehicle achieved a total maximum of 1,133 kN (254,500 lbf) in the 4-booster configuration, utilizing two motors augmented by four Recruit motors to simulate early-flight dynamic pressures comparable to those experienced by the . Configurations varied, with up to approximately 1,500 kN (337,000 lbf) in fuller setups. The motor delivered 465 kN (104,500 lbf) of over a nominal burn duration of 40 seconds, serving as the primary sustainer stage, while each Recruit motor produced 167 kN (37,500 lbf) for 1.53 seconds to provide initial boost acceleration. In terms of trajectory performance, the full configuration reached a peak altitude of approximately 23 km (75,000 ft), with velocities attaining up to Mach 1.2 during ascent, and burnout occurring between 50 and 60 seconds after liftoff. These parameters allowed the vehicle to replicate suborbital profiles relevant to Apollo abort scenarios without exceeding the structural limits of the test hardware. The for the motor was around 235 seconds, and for the Recruit motors approximately 200 seconds at , reflecting the efficiency of their solid propellants under operational conditions. The design emphasized abort simulation capabilities from 0 to 30 seconds post-liftoff, aligning with the Saturn V's maximum (max-Q) phase at roughly 1.2 g , ensuring the could be tested under representative aerodynamic and structural loads.
ConfigurationMotorsGross Mass (kg)Thrust (kN)Max Altitude (km)
QTV (4-booster)4 Recruit + 2 25,9401,133~23
Full (e.g., 6-1-0)6 Recruit + 1 63,300~1,500Up to 23
0-3-36 VariesUp to 2,800Varies

Preservation

Surviving Hardware

Following the end of the Little Joe II program in 1966, the majority of vehicles and components were scrapped or disassembled at the , with no flown examples preserved intact. The surviving hardware consists primarily of qualification test vehicles (QTVs) assembled from surplus parts for ground-based evaluations of the and structural integrity. Two full Little Joe II vehicles are known to survive. One is preserved at the New Mexico Museum of Space History in . This 86-foot-tall specimen, weighing approximately 41,000 pounds, features the characteristic corrugated aluminum skin and clustered solid-propellant motors; it was transferred to the museum in 1985 from the . The other full vehicle, unflown and complete with boilerplate Apollo capsule BP-22 and escape tower, is on outdoor display at the Johnson Space Center's Rocket Park in Houston, Texas, mounted on its launch pedestal adjacent to the rocket exhibit. Additionally, the National Air and Space Museum (NASM) in Washington, DC, holds a Little Joe II QTV, transferred from NASA in 1974. Approximately 86 feet in height with a fin span of 27 feet, it includes motor casings, launch escape system tower, and boost protective cover, though it remains in storage and is not on public display.

Recent Restoration Efforts

In 2025, the New Mexico Museum of Space History, in collaboration with the Smithsonian Institution, launched a major restoration project for its Little Joe II rocket, one of two surviving full examples of the vehicle. The initiative began with the temporary closure of Rocket Park and the adjacent playground on November 6, 2025, to ensure public safety during the work, which is expected to last up to 90 days. Restoration specialists from Blast Off, Inc. are addressing structural degradation caused by over 40 years of outdoor exposure in the harsh desert environment since the rocket's transfer to the museum in 1985, particularly focusing on its corrugated aluminum body. At the Smithsonian Institution's , the QTV—transferred from in 1974—remains in archival storage with no active restoration underway. The museum's Preservation and Restoration Unit conducts periodic inspections and maintenance on stored artifacts like this solid-propellant test vehicle to prevent deterioration, emphasizing controlled environmental conditions over public display. This approach prioritizes long-term conservation without recent interventions specific to the Little Joe II. These preservation activities underscore the enduring historical significance of Little Joe II in the Apollo program's development, particularly its role in validating the launch escape system's safety features through uncrewed abort tests from 1963 to 1966. Efforts align with broader post-50th anniversary initiatives to educate on Apollo-era innovations, as seen in NASA's 2019 restorations of related sites like the Apollo , potentially paving the way for enhanced public exhibits on early spacecraft recovery systems. Key challenges include combating environmental weathering from prolonged outdoor placement, which has accelerated material fatigue on exposed components.

References

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  13. https://www.nasa.gov/wp-content/uploads/2023/03/sp-4009vol2.pdf
  14. https://ntrs.nasa.gov/api/citations/19790076764/downloads/19790076764.pdf
  15. https://www.nasa.gov/history/alsj/a001/a001.html
  16. https://www.drewexmachina.com/2021/05/19/a-successful-failure-the-flight-of-apollo-little-joe-ii-a-003/
  17. https://ntrs.nasa.gov/api/citations/19670022649/downloads/19670022649.pdf
  18. https://nmspacemuseum.org/2025/11/06/rocket-park-temporarily-closed-for-little-joe-ii-restoration/
  19. https://www.american-spacecraft.org/boosters/little-joe-2-jsc.html
  20. https://www.collectspace.com/news/news-111425a-little-joe-II-rocket-restoration-new-mexico-museum-space-history.html
  21. https://airandspace.si.edu/about/organization/departments-staff/preservation-and-restoration-unit
  22. https://www.nasa.gov/podcasts/houston-we-have-a-podcast/restoring-the-apollo-mission-control-center/
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