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Flight Performance Data from the Scout X-258 Rocket Motor

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Flight Performance Data from the Scout X-258 Rocket Motor r" NASA TECHNICAL NOTE NASA TN D-2756 *o rr) h cy d r. I 'i UCCtSSION NUHOER) a c 4 r/) 4 z GPO PRICE $ OTS PRICE(S) $ Hard copy (HC) Microfiche (MF) sa FLIGHT PERFORMANCE DATA FROM THE SCOUT X-258 ROCKET MOTOR by James A. Nagy Godlard Spuce Fl@t Center Greenbelt, Mal NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON, D. C. MAY 1965 . NASA TN D-2756 FLIGHT PERFORMANCE DATA FROM THE SCOUT X-258 ROCKET MOTOR - By James A. Nagy Goddard Space Flight Center Greenbelt, Md. NATIONAL AERONAUTICS AND SPACE ADMINISTRATION For sale by the CLearinghouse for Federal Scientific and Technicol Information Springfield, Virginia 22151 - Price 53.00 FLIGHT PERFORMANCE DATA FROM THE SCOUT X-258 ROCKET MOTOR by James A. Nagy Goddard Space Flight Center SUMMARY Nine channels of performance data were obtained during the flight of the Scout launch vehicle (S-122)on December 19, 1963. This vehicle was used to place the Langley Research Center satellite Explorer XIX into earth orbit from Point Arguello, California. Shock and vibration data were obtained from the forward motor shoulder (payload attach point) of the fourth stage X-258 from liftoff through fourth-stage motor burnout. Low-level random vibrations (be- low 0.0016 g*/cps) were recorded during first-stage burning and are the subject of detailed analysis in this report. First-stage motor burn- ing irregularities which caused increases in vibrationlevel at the pay- load also are analyzed, as well as transients recorded during first- and third-stage burning. No appreciable vibrations were apparent during fourth-stage burning; this correlates with results obtained during a simulated high-altitude static firing of an X-258. There was no indi- cation of X-258 chuffing; however, the tailoff was exceedingly long. Low-frequency accelerometers included in the experiment meas- ured lateral bending frequencies and low-frequency vehicle pitching and yawing motions during the first three stages of burning. Spin rate and gyroscopic motions during fourth-stage burning were recorded, as well as axial steady-state acceleration for all four stages. The experiment also measured X-258 headcap pressure. The X-258 forward dome tem- perature is presented for the first 2 hours after fourth-stage ignition. iii " CONTENTS Summary. i INTRODUCTION . 1 DESCRIPTION OF PAYLOAD. 2 INSTRUNLEE.rl'ATION . 4 DATA REDUCTION . 5 FLIGHTTIMEHISTORY.. 9 DISCUSSION AND RESULTS . 9 Discussion. 9 Random Vibrations . 9 Transient Vibrations . 12 Low-Frequency Oscillations . 13 Acceleration, Pressure, Temperature, and Spin Rate . 14 CONCLUDING REMARKS . 15 References and Bibliography . 15 V i- FLIGHT PERFORMANCE DATA FROM THE SCOUT X-258 ROCKET MOTOR by James A. Nagy Goddard Space Flight Center INTRODUCTION The development program of the NASA Langley Research Center to improve the performance of the Scout launch vehicle has led to a new fourth-stage solid rocket motor, the X-258. Instru- mented ground firings at sea level and at simulated high altitude have shown that the X-258 ex- hibits no oscillatory burning and that practically no vibrations exist at the X-258 payload attach point. * To confirm the static firing results and to establish laboratory vibration test specifications for X-258 payloads, it was considered necessary to measure the in-flight vibrations. Prior to this, no in-flight measurements had been made on the X-258. In addition to the vibration meas- urements, transducers were included in the experiment to measure the following X-258 per- formance parameters: steady accelerations, spin rate, temperature, headcap pressure, tipoff, coning, and chuffing. The experiment also telemetered a signal to verify that the spacecraft sepa- ration sequence of events had occurred. The performance experiment was implemented by Goddard Space Flight Center (GSFC) at the request of Langley Research Center as a secondary experiment. The primary experiment was the Langley Air Density Satellite, Explorer XM (1963 53A). The Scout vehicle (S-122) was launched by the Air Force Space Systems Division from the Probe Launch Complex, Naval Missile Facility, Point Arguello, California, on December 19, 1963. The vehicle followed a nominal tra- jectory and placed the satellite in an earth orbit. The purpose of this report'is to present the in-flight shock and vibration data. Although data from the other transducers are presented, no attempt is made to analyze X-258 or Scout vehicle performance. As a reference for the data, the vehicle is described and typical time histories of flight per- formance, as well as the times of significant events, are presented. *See Tereniak, 8. B., "X-258 Development Motor Static Firing Vibration Data," Goddard Space Flight Center Memorandum Report 631- 184, December 4, 1963. It should be noted that the X-258's predecessor, the 5-248, did exhibit oscillatory burning. 1 DESCRIPTION OF THE VEHICLE AND PAYLOAD The Scout vehicle is a ?%foot, multistage, solid fuel research missile developed by Langley Research Center (Figure 1). Four solid rocket motors are joined by airframe assemblies called transition sections. Ad- ditional airframe assemblies include a base section, heat shield, and wiring tunnels. Each tran- sition section is divided into upper and lower portions at the stage separation plane. Frangible "blowout" diaphragms join the first and second and the second and third stages. The diaphragms form an internal clamp by the threaded periphery that engages two structural threaded rings at the separation plane. Blast pressure of the upstage motor ruptures the diaphragm, disengages the periphery, and allows the stage to separate. The third and fourth stages are joined by a "cold- separation" arrangement of springs held compressed by a clamp retainer flange. Explosive bolt clamps release the flanges, effecting separation by spring-loaded ejection force. Base section A, shown in Figure 2, con- tains electrohydraulic actuators used to con- COLD SEPARATION trol a combinationof jet vanes and aerody- namic tip control surfaces for guidance control SPINUP MOTORS SPIN BEARING Transition Section D It3l HzOz ATTITUDE CONTROL SEPARATION DIAPHRAGM Transition Section C H202 ATTITUDE CONTROL Transition Section B HYDRAULIC CONTROLS ,FINS \ / '\/' Base Section A Figure 1-The Scout vehicle on its launch pad. Figure 2-General arrangement of vehicle. 2 throughout the entire first-stage burning period. Transition B section (between first and second stage) and transition C section (between second and third stage) contain second- and third-stage control systems of hydrogen peroxide reaction jet motors. Transition lower D section contains the guidance system and the fourth-stage spinup system. Transition upper D section, where the performance experiment antennas are located, is attached to the fourth-stage aft motor shoulder. The payload, consisting of four sections, was attached to the forward motor shoulder of the X-258 as depicted in Figures 3 and 4. The lower extension contains a beacon transmitter and its antennas, payload umbilical, and piezoelectric accelerometers. The upper extension contains four low-frequency accelerometers and the performance telemeter. Satellite timers and batteries for pyrotechnics are located on the frustum, and attached to the frustum is a canister which accommo- dates the folded 12-foot-diameter inflatable satellite. A 34-inch-diameter clamshell-type heat shield protects the payload during ascent. The heat shield is ejected when the vehicle is out of the sensible atmosphere by latch-contained springs, after release of latches and clamps effected by a ballistic actuator and drawbar. The total payload weight, including ballast, amounted to 138.50 pounds. Changes made in the vehicle for this flight were: (1) The first stage had a modified Figure 3-Fourth-stage arrangement. Algol IIA nozzle; (2) a heat shield was in- stalled in transition upper C section to re- duce heat transferred from the x-259 motor nozzle to the hydrogen peroxide system, and insulation was added in localized areas to further protect the system; (3) additional instrumentation was installed in C section to provide more performance and environmental data on the control system; (4) the X-258 rocket motor case was overwrapped with 0.20-inch-thick filament; and (5) the X-258 dome was covered with an insulating blanket for thermal protection of the performance experiment, as shown in Figure 5. Figure 5-X-258 forward dome blanket (shown partially installed). Table 1 lists the nominal dimensions and predicted performance characteristics of the four motors. Table 1 Nominal Dimensional and Predicted Performance Characteristics of the Four Rocket Motors ~ ~~~ ~~ Stage I Stage II Stage III Stage IV Characteristics Algol IIA Castor XM33-E5 Antares X259-A3 Altair X258-B1 S/N 21 S/N 152 S/N HPC-134 S/N 61 ~ ~~ RH Motor temperature (OF) 70 70 70 70 Overall length (in.) 357.6 244.1 113.7 58.4 Principal diameter (in.) 40.0 31.0 30.05 18.05 Propellant weight (lb) 21,087 7,326 2,580 504.8 Loaded motor weight (lb) 23,583 8,867 2,818 574.5 Burnout motor weight (lb) 2,212 1,435 *213 63.3 Consumed weight (lb) 21,371 7,432 2,605 511.2 Propellant specific impulse, vacuum (lb -sec/lb,) 258.29 273.21 278.72 281.88 Total impulse, vacuum (lb-sec) 5,446,605 2,001,536 719,098 142,292 Average thrust, based on total burntime (lb) 79,862.2 47,106.1 21,529.9 5472.8 Total burntime (sec) 68.2 42.49 33.4 26.0 Nozzle expansion ratio 7.32 15.61 17.93 25.80 Exit area (sq ft) 5.648 8.083 4.346 1.367 *This weight includes 13.8 Ib Thennolag, 8 Ib of which is consumed during first- and second-stage operation. INSTRUMENTATION To determine the primary experimental objective of X-258 motor performance, the experi- ment was installed in the upper extension illustrated in Figure 6.
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