Item Details

Payload Vibration Data Measured During Five Flights of a Two-Stage Solid-Propellant Launch Vehicle

by Sherman A. Clevenson
Format
Book; Government Document; Online; EBook
Published
Washington, [D.C.] : National Aeronautics and Space Administration, 1962.
Language
English
Series
NASA Technical Note
Summary
Since there is a dearth of flight vibration data and because of the current wide interest in solid-propellent, rockets, flight vibration data have been obtained from five vertical test shots of Shotput, the launch vehicle for vertical tests of the 100-foot inflatable sphere. The two-stage vehicle, called Shotput, consisted of a Pollux and two Recruit rocket motors as the first stage and an ABL X-248 rocket motor as the second stage. High vibration levels were obtained near burnout of the second stage of Shotput I, II, and V, whereas only low vibration levels were noted on Shotput III, and IV. The peak flight vibration levels on Shotput I, II, and V occured in the longitudinal direction at a frequency of about 570 cps and were ±45g, and ±24g, respectively. It was found that the flight vibration levels in the normal and transverse directions were considerably less that those in the longitudinal direction. High longitudinal vibration levels were also noted during some of the ground tests of the final stage and are believed to result from a burning instability coupled with the longitudinal acoustical resonance of the rocket motor.
Description
21 p. : ill. ; 26 cm.
Mode of access: Internet.
Notes
  • Document ID: 19620000020.
  • "NASA TN D-963."
  • "Langley Research Center, Langley Air Force Base, Va."
  • "January 1962."
  • Cover title.
  • Includes bibliographical references (p. 8).
Series Statement
NASA technical note ; D-963
Other Forms
Also available via Internet from NASA Technical Reports Server.
Logo for No Copyright - United StatesNo Copyright - United States
Technical Details

  • LEADER 03229nam a2200589Ia 4500
    001 011448733
    003 MiAaHDL
    005 20141009010000.0
    006 m d
    007 cr bn ---auaua
    008 070717s1962 dcua bt f000 0 eng d
    024
    8
      
    a| N6210020
    024
    8
      
    a| 62N10020
    024
    8
      
    a| 19620000020
    035
      
      
    a| sdr-uiuc6395708
    035
      
      
    a| (OCoLC)156250532
    040
      
      
    a| FER c| FER
    049
      
      
    a| UIUU
    100
    1
      
    a| Clevenson, Sherman A.
    245
    1
    0
    a| Payload vibration data measured during five flights of a two-stage solid-propellant launch vehicle / c| by Sherman A. Clevenson.
    260
      
      
    a| Washington, [D.C.] : b| National Aeronautics and Space Administration, c| 1962.
    300
      
      
    a| 21 p. : b| ill. ; c| 26 cm.
    490
      
    0
    a| NASA technical note ; v| D-963
    500
      
      
    a| Document ID: 19620000020.
    500
      
      
    a| "NASA TN D-963."
    500
      
      
    a| "Langley Research Center, Langley Air Force Base, Va."
    500
      
      
    a| "January 1962."
    500
      
      
    a| Cover title.
    504
      
      
    a| Includes bibliographical references (p. 8).
    520
      
      
    a| Since there is a dearth of flight vibration data and because of the current wide interest in solid-propellent, rockets, flight vibration data have been obtained from five vertical test shots of Shotput, the launch vehicle for vertical tests of the 100-foot inflatable sphere. The two-stage vehicle, called Shotput, consisted of a Pollux and two Recruit rocket motors as the first stage and an ABL X-248 rocket motor as the second stage. High vibration levels were obtained near burnout of the second stage of Shotput I, II, and V, whereas only low vibration levels were noted on Shotput III, and IV. The peak flight vibration levels on Shotput I, II, and V occured in the longitudinal direction at a frequency of about 570 cps and were ±45g, and ±24g, respectively. It was found that the flight vibration levels in the normal and transverse directions were considerably less that those in the longitudinal direction. High longitudinal vibration levels were also noted during some of the ground tests of the final stage and are believed to result from a burning instability coupled with the longitudinal acoustical resonance of the rocket motor.
    530
      
      
    a| Also available via Internet from NASA Technical Reports Server.
    538
      
      
    a| Mode of access: Internet.
    650
      
    7
    a| Vibration. 2| nasat
    650
      
    7
    a| Tiros. 2| nasat
    650
      
    7
    a| Solid propellant rocket engines. 2| nasat
    650
      
    7
    a| Scout project. 2| nasat
    650
      
    7
    a| Payloads. 2| nasat
    650
      
    7
    a| Multistage rocket vehicles. 2| nasat
    650
      
    7
    a| Launching. 2| nasat
    650
      
    7
    a| Echoes. 2| nasat
    650
      
    7
    a| Delta rocket vehicle. 2| nasat
    650
      
    7
    a| Argo rocket vehicles. 2| nasat
    710
    1
      
    a| United States. b| National Aeronautics and Space Administration.
    710
    2
      
    a| Langley Research Center.
    974
      
      
    b| UIU c| UIUC d| 20141113 s| google u| uiug.30112106915041 y| 1962 r| pd q| bib

Access online

Google Preview