Lunar Landing Research Vehicle
|Lunar Landing Research Vehicle (LLRV)
Lunar Landing Training Vehicle (LLTV)
|The Lunar Landing Research Vehicle (LLRV)|
|Role||Experimental VTOL aircraft|
|First flight||30 October 1964|
|Number built||2 LLRVs
The Bell Aerosystems Lunar Landing Research Vehicle (LLRV) was an Apollo Project era program to build a simulator for the Moon landings. The LLRVs were used by the FRC, now known as the NASA Dryden Flight Research Center, at Edwards Air Force Base, California, to study and analyze piloting techniques needed to fly and land the Apollo Lunar Module in the moon's low gravity environment.
The research vehicles were vertical take-off vehicles that used a single jet engine mounted on a gimbal so that it always pointed vertically. It was adjusted to cancel 5/6 of the vehicle's weight, and the vehicle used hydrogen peroxide rockets which could fairly accurately simulate the behaviour of a lunar lander.
Success of the two LLRVs led to the building of three Lunar Landing Training Vehicles (LLTVs) an improved version of the LLRV, for use by Apollo astronauts at the Manned Spacecraft Center in Houston, Texas, predecessor of NASA's Johnson Space Center. One LLRV and two LLTVs were destroyed in crashes, but the rocket ejection seat system recovered the pilot safely in all cases.
The final phase of every Apollo landing was manually piloted by the mission commander. Because of landing site selection problems, Neil Armstrong, Apollo 11 commander, said his mission would not have been successful without extensive training on the LLTVs.
Built of aluminum alloy trusses, the LLRVs were powered by a General Electric CF700-2V turbofan engine with a thrust of 4,200 lbf (19 kN), mounted vertically in a gimbal. The engine lifted the vehicle to the test altitude and was then throttled back to support five-sixths of the vehicle's weight, simulating the reduced gravity of the moon. Two hydrogen peroxide lift rockets with thrust that could be varied from 100 to 500 lbf (440 to 2,200 N) handled the vehicle's rate of descent and horizontal movement. Sixteen smaller hydrogen peroxide thrusters, mounted in pairs, gave the pilot control in pitch, yaw and roll. The pilot had an ejection seat. On activation, it propelled the pilot upward from the vehicle with an acceleration of roughly 14 times the force of gravity for about a half second. From the ground, it was sufficient to propel the seat and pilot to an altitude of about 250 feet where the pilot’s parachute could be automatically and successfully deployed. Manufactured by Weber Aircraft LLC, it was one of the first zero-zero ejection seats, capable of saving the operator even if the aircraft was stationary on the ground - a necessity given the LLRV's low and slow flight envelope.
After conceptual planning and meetings with engineers from Bell Aerosystems, Buffalo, New York, a company with experience in vertical takeoff and landing (VTOL) aircraft, NASA issued Bell a $50,000 study contract in December 1961. Bell had independently conceived a similar, free-flying simulator, and out of this study came the NASA Headquarters' endorsement of the LLRV concept, resulting in a $3.6 million production contract awarded to Bell on February 1, 1963, for delivery of the first of two vehicles for flight studies at the FRC within 14 months.
LLRV#1 was shipped from Bell to FRC in April. LLRV#2 was also shipped at the same time, but in parts. Because of a potential cost overrun, the FRC Director, Paul Bickle, decided to have it assembled and tested at FRC. The emphasis then was on LLTV#1. It was first readied for flight on a tilt table constructed at FRC to evaluate its engine operation without actually flying it. The scene then shifted to the old South Base area of Edwards.
The first three flights of #1 were made on October 30, 1964 by FRC’s senior research test pilot, Joe Walker. He continued to pilot a number of flights through December 1964 after which flights were shared with Don Mallick, also a FRC research pilot, and Jack Kleuver the Army’s senior helicopter test pilot. Familiarization flights were also made by NASA Manned Spacecraft Center (later Johnson Space Center) pilots Joseph Algranti and H.E. Bud Ream.
Modifications were later made to the cockpits of both LLRV’s to better simulate the actual Lunar Module. These included the addition of the LM’s three-axis hand controller and throttle. A Styrofoam cockpit enclosure was also added to simulate the pilot’s restricted view in the LM.
The final LLRV flight at FRC took place on November 30, 1966. In December 1966 vehicle #1 was shipped to Houston, followed by #2 in January 1967. During the preceding two years, a total of 198 flights of LLRV#1 and six flights of LLRV#2 were flown without a serious accident.
The first LLRV flight by Neil Armstrong was made in vehicle #1 on March 27, 1967 from its base at a corner of Ellington Air Force Base, the headquarters for Johnson Space Center’s aircraft operations. Joe Algranti, chief of JSC’s Aircraft Operations Division and test pilot H.E.”Bud” Ream also made flights that month. Both observed, as did Neil and the other astronauts, that if a serious control problem developed, the pilot had little choice but to eject since the vehicle only operated to a maximum of 500 feet altitude.
On May 6, 1968 Armstrong was forced to use LLRV #1’s ejection seat from about 200 feet altitude after a control problem, and had about four seconds on his full parachute before landing on the ground unhurt. The accident investigation board found that the fuel for the vehicle’s attitude control thrusters had run out, and that high winds were a major factor. As a result the decision was made by JSC management to terminate further LLRV flights as the first LLTV was about to be shipped from Bell to Ellington to begin ground and flight testing.
Negotiations between JSC and Bell Aerosystems for three LLTV’s, an improved training version of the LLRV, were initiated in October 1966 and a 5.9 million dollar contract for three vehicles was finally signed in March 1967. In June 1968, the first vehicle was delivered by Bell to Ellington to begin its ground and flight testing by JSC’s Aircraft Operations Division. AOD’s head, Joe Algranti was the principal test pilot for its first flight in August 1968. Flight testing continued until December 8 when control was lost by Algranti during a flight to expand the vehicle’s speed envelope. He managed to eject just three-fifths of a second before the vehicle hit the ground, the close call believed to be as a result of his attempt to regain control.
The accident investigation found that the ground controllers had elected not to monitor in real time the attitude thrusters that controlled the vehicle’s yaw motion, and, at the velocity Joe was flying, the thrusters had been overpowered by the LLTV’s aerodynamic forces causing Joe to lose control. Because of the LLRV and LLTV tight cost constraints, no wind tunnel testing had been performed and the decision had been made to rely on careful flight testing for the evaluation of the vehicles’ aerodynamic characteristics. After reviewing the results of the crash investigation, however, it was decided that the third LLTV be loaded into NASA’s “Super Guppy” and flown to NASA’s Langley Research Center in Virginia for testing in its full-scale wind tunnel. Testing was initiated on January 7, 1968 and ended one month later on February 7. It was quickly determined that the cause of the divergence was the Styrofoam cockpit enclosure. As the vehicle's sideslip angle reached minus two degrees, a yawing force rapidly built up that exceeded the ability of the yaw thrusters to counteract. The fix decided on was simply to remove the top of the enclosure thus venting it and eliminating the excessive yawing force. It was also possible from the wind tunnel results to develop a preliminary flight envelope for the LLTV defining its allowable maximum airspeed at various angles of angle of attack and sideslip. All this had to be verified by flight test, however, since it was not possible in the tunnel to obtain good data with the engine running. A high level LLTV Flight Readiness Review Board was appointed on March 5, 1969 by JSC Director Dr. Robert Gilruth. It consisted of himself as chairman with board members Chris Kraft, head of Mission Operations; George Low, head of JSC’s Apollo Program; Max Faget, JSC’s Director of Engineering; and astronaut Deke Slayton, Director of Flight Crew Operations. The Board reviewed the wind tunnel results, and on March 30 gave approval for the resumption of test flights in LLTV#2. The test program of 18 flights, all flown by Bud Ream, was successfully completed on June 2, and the Board finally gave approval on June 30, 1969 for Neil Armstrong to resume LLTV flights. In the 16 days remaining before the Apollo 11 launch Armstrong was able to complete his LLTV flight training. He commented after his return:
“Eagle (the Lunar Module) flew very much like the Lunar Landing Training Vehicle which I had flown more than 30 times at Ellington Air Force Base near the Space Center. I had made from 50 to 60 landings in the trainer, and the final trajectory I flew to the landing was very much like those flown in practice. That of course gave me a good deal of confidence – a comfortable familiarity.”
In Neil Armstrong’s biography, “First Man”, Astronaut Bill Anders is quoted as describing the LLTV as “a much unsung hero of the Apollo Program”. Although Armstrong had to eject from the LLRV, no astronaut ever had to eject from the LLTV, and every Lunar Module pilot through the final Apollo 17 mission trained in the LLTV and flew to a landing on the moon successfully.
LLRV#2 was eventually returned to Dryden, where it is on display as a silent artifact of the Center's contribution to the Apollo program. In January 1971 LLTV#3 was destroyed while testing a major modification to the LLTV's computer system. Its test pilot, Stuart "Stu" Present was able to eject safely. The sole surviving late-model LLTV, NASA 952, is on display at the Johnson Space Center.
Lunar Sim Mode
There were two distinct modes of flight for the LLRV and LLTV. The basic mode was with the gimbaled engine fixed to the body so that it always pointed downward in relation to the body. But in the gimbaled "Lunar Sim Mode", the engine was allowed to swivel and was kept pointing downward to the earth. This allowed the vehicle to tilt at the far greater angles that would be typical of hovering and maneuvering above the lunar surface. Despite its ungainly appearance, the LLRV was equipped with an astonishingly sophisticated array of early sensor and computational hardware. The system had no specific name, but the effect it produced was called "Lunar Sim Mode". This was the highest degree of hardware-based simulation, and was the purpose of the whole project. This was not a system to unburden the pilot, such as an autopilot does, nor was it meant to introduce any sort of safety or economy. The system's sole intention was to project the illusion of piloting the Lunar Module. So, Lunar Sim Mode can be thought of as a mixture of stability augmentation, recalculation of vertical acceleration according to the lunar gravity constant, all followed by accompanied instantaneous corrective action. The LLRV's Lunar Sim Mode even was able to counter-correct wind gusts within milliseconds, as they definitely would have disturbed the impression of a missing atmosphere. Sensor input for the Lunar Sim Mode was the Doppler radar. The visually significant sign of an engaged Lunar Sim Mode was the free-gimbaled turbofan, always strictly pointing downward toward the ground, regardless the LLRV's current attitude. This unique aircraft represents one of the few hardware simulators that ever became airborne.
FRC test pilot Don Mallick’s comments following the vehicle’s first flight in the lunar simulation mode are instructive:
“As a general statement concerning the translation ability on earth versus the translational ability in the lunar simulation; the vehicle is reduced from a very positive high response vehicle to a very low or weak response vehicle. I’m sure with training and experience the pilot will be able to increase the overall vehicle-pilot performance once he adapts to the low translational accelerations that are available, as well as the lag that follows along with the anticipation that is required to properly control the vehicle. Even with this training the pilot is faced with the situation of about 5/6 of his translational maneuvering performance removed from that on earth which is a marked change.”
Donald "Deke" Slayton, then NASA's chief astronaut, later said there was no other way to simulate a moon landing except by flying the LLRV.
- Crew: one, pilot
- Length: 22.5 ft (6.85 m)
- Wingspan: 15.08 ft (4.6 m)
- Height: 10.0 ft (3.05 m)
- Empty weight: 2,510 lb (1,138 kg)
- Loaded weight: 3,775 lb (1,712 kg)
- Max. takeoff weight: 3,925 lb (1,780 kg)
- Powerplant: 1 × General Electric CF-700-2V jet, 4,200 lbf (19 kN)
- Maximum speed: 40 mph
- Service ceiling: 6,000 ft (1,800 m)
- Rate of climb: 3,600 ft/min (17.9 m/s)
- Thrust/weight: 1.07
- Secondary Engine: 2 x hydrogen peroxide lift rockets with 500 lbf (2,200 N) each
- Endurance: 10 minutes
|This section needs additional citations for verification. (July 2011)|
The electronic control system for the Lunar Landing Training Vehicle was developed for NASA by Bell Aerosystems, Inc. which had engineering facilities located in Niagara Falls, New York. The LLTV was a second generation vehicle, after the Lunar Landing Research Vehicle, used by NASA Apollo Program astronauts to develop piloting skills. The LLTV provided Apollo program commanders the opportunity to experience the flight characteristics associated with the 1/6 gravity conditions on the moon. The first LLTV vehicle was assembled at Ellington Airforce Base in Houston, Texas in 1967. A total of 3 LLTV vehicles were eventually delivered to Ellington AFB. The last remaining of the three LLTV vehicles is on display at the Johnson Spacecraft Center in Houston, Texas.
The electronic control system was designed with redundant channels that used 2 of 2 logic. The outputs of each primary channel were compared on a continuous basis. If a fault was detected in the primary control system, then control was automatically switched to an identical backup channel and the pilot immediately took measures to bring the vehicle to the ground. All the controls were analog circuits utilizing Burr-Brown transistor amplifier modules and other analog components. Unlike modern digital control circuits, in 1967 the technology available was limited to discrete transistors.
- Aircraft of comparable role, configuration and era
- Related lists
- Unconventional, Contrary, and Ugly: The Lunar Landing Research Vehicle Gene J. Matranga, C. Wayne Ottinger, and Calvin R. Jarvis with C. Christian Gelzer Monograph is Aerospace History #35 NASA SP-2004-4535, 2005
- NASA Dryden Technology Facts - Lunar Landing Research Vehicle
- www.jsc.nasa.gov/oral history/James P. Bigham
- Bell Aerosystems, LLRV Flight Manual. Report No. 7161-954005, 1964, p. 311-313.
- Mallick, Donald, LLRV Flight Notes,Flight 1-28-87F, September 16, 1965
|Wikimedia Commons has media related to Lunar Landing Research Vehicle.|
- Lunar Landing Research Vehicle landing dynamics - NASA report (PDF format)
- Lunar Landing Terminal descent study using LLRV - NASA report (PDF format)
- Lunar Landing Research Vehicle - LM technology - NASA report (PDF format)
- LLRV/TV flight summary (sci.space.history post)
- LLTV FRRB transcript, Jan 12, 1970
- http://grin.hq.nasa.gov/ABSTRACTS/GPN-2000-001901.html Pictures
- http://www.hq.nasa.gov/alsj/LLTV-952.html Pictures
- Conference video from meeting where 4 moonwalkers discuss the value of the LLTV
- Neil Armstrong presentation on LLRV/TV (video from the 51st SETP Symposium)