Msfc Program Evolution 1
2. Evolution Creativity Innovation. During the Jupiter and Redstone programs, there was a struggle trade of how best to deal with aerodynamically unstable missile systems, including performance loss due to winds, guidance, and loads. The aerodynamic stability question could be solved by putting large static aerodynamic fins on the aft end, and optimizing the external shapes and mass distributions propellant tank locations . In many cases, the fins were too large, thus thrust vectoring was...
On
Figure 122. Spacelab module configuration continued . Figure 122. Spacelab module configuration continued . Figure 122. Spacelab module configuration continued . Figure 122. Spacelab module configuration continued . Figure 123. Spacelab typical pallet configuration. Figure 123. Spacelab typical pallet configuration. Figure 124. Spacelab module and pallet combination. Figure 124. Spacelab module and pallet combination. Spacelab, as a laboratory, has emphasized microgravity science, life...
Info Asc
The next section will deal with the shuttle elements. 2. Space Shuttle Main Engine. The following section is a collection of materials, data, charts, etc., from several sources associated with the SSME. These sources are 1 MSFC and Rocketdyne failure investigation reports, 2 Rocketdyne presentations, 3 MSFC Rocketdyne special problem resolution teams, 4 MSFC and Rocketdyne studies and reports, and 5 MSFC and Rocketdyne technical society papers and professional journal articles. The engine...
R Uyv
Designing the SRB SRM to maximum minimum loads instead of time-consistent loads was an approach that saved redesigns and cost as the shuttle system evolved and loads increased. This approach early in the program was optimal since the dry weight of the SRM SRB to payload to orbit was approximately 8 to 1. This meant that approximately 8 lb of structural weight would only penalize the performance 1 lb. Late in the development program as loads increased, time consistent loads could be used to...
Rpl
Figure 50. SSME propellant flow diagram. Figure 50. SSME propellant flow diagram. Many other innovations were apparent as various problems occurred. The numerous major hot-fire development problems were studied and resolved using Government contractor concurrent engineering teams, usually called failure investigation boards. Although the word concurrent engineering was not in vogue, the operating approach and team makeup were part of the characteristics of the current definition. See reference...
Tup
3 Bathtub Fittings. The original design had bathtub fittings at the fine guidance sensor, and the radial scientific instruments SI's points B and C latch locations the focal plane side of each of these points, i.e., the fixed half of the latch were bolted to these bathtub fittings. All of the fittings failed three were tested well below the design load. The failures were all in the length of the edge of the fitting fig. 120 . The failure was due to the fact that the design did not place any...
Tps 1
Minimize SOFI thickness on tank sidewalls Al Li 2090, 2195 Other Redesigned Parts No Change Figure 102. ET SLWT lox tank changes. As stated previously, the tank is a prime part of the liquid propulsion system in that it contains level sensors, the pressurization system, etc., as shown on figure 103. It also contains the tumble valve for ensuring that the ET tumbles and breaks up as it enters the atmosphere and that resulting pieces stay within a safe footprint in the Atlantic Ocean and do not...
Sic
-Reaction Motors -Propellant Tank -Helium Tank - Service Module Propulsion Engine Nozzle
Electrodynamic Tether String Mode Excitation
Although as illustrated the tether forces are in-plane this is not the general case and excitation usually occurs in both planes. Figure 144. Electrodynamic tether properties. Figure 144. Electrodynamic tether properties. Figure 145. Dynamic modes of a tethered satellite. complicated by the difficulty of sensing the amplitude, phase, and frequency of the skiprope dynamics. It can be inferred by the dynamics it introduces into the satellite, by visual observations from the orbiter, or by some...
Hpftp
Rotating unbalance of turbine disk phase I HPFTP The first-stage blades were coated with zirconium zirconium has poor adhesion characteristics loss of coating caused rotating unbalance Changed to Nicraly coating only on blades First- and second-stage turbine disks curvic teeth after gold plating, excess gold was frequently found on the load flats of the curvic teeth upon excess gold removal, damage occurred to the fillet region of the curvic teeth on several disks Excess gold occurred due to...
External Tank Separation 1
Figure 42. Space shuttle typical mission profile. Figure 42. Space shuttle typical mission profile. Figure 43. Space shuttle typical ascent and descent trajectory profiles. Figure 43. Space shuttle typical ascent and descent trajectory profiles. b. Evolution Creativity Innovation. The development of such a complex machine required the best in engineering innovation, creativity, and common sense. Management of such a complex government-industrial teaming also required the same innovation, etc....
Srb Aft Skirt Dimensions
0 20 40 60 80 100 120 140 160 180 DEGREES FROM Y SRB AXIS 50 RADIAL 100 RADIAL o 150 RADIAL Figure 91. SRB radial load sensitivity. the symmetrical skirt showing the large peak at the weld for different load variations. Figure 92 is a detailed finite element stress analysis localized around the weld failure point, showing the large stress intensity at the weld near the bottom of the skirt. Part of the loads sensitivity of the aft skirt is due to the holddown mechanism, which is composed of the...
Info Srr
Jet ring cup washer high-cycle fatigue cracks Flow environment caused high 40 kHz frequency high-cycle fatigue cracks First- second-stage turbine nozzle cracks cracks are on leading edges of vanes and inner and outer shrouds cracks initiate at low and high time Low-cycle fatigue caused by thermal transient start Modified start sequence to reduce thermal transients cracks are shallow and monitored by borescope and dye penetrant inspections Failures not function of starts, time, or power level...
High Pressure Fuel Turbopump Coolany Liner Pressure 1
00 HIGH PRESSURE f OXIDIZER TURBOPUMP INTERMEDIATE SEAL PURGE PRESSURE Figure 55. SSME schematic with failures. Figure 55. SSME schematic with failures. 1 SSME 4,000 Hz. Flow instabilities have been the classical problem of structural systems. They have taken many forms, occurring unexpectedly, taking human life. Many textbooks and technical papers focus on the phenomenon aircraft flutter garners the bigger emphasis. Internal flow in fluid systems experiences the same instabilities. An...
HPOTP Gcx
PBP ball bearings No. 1 and No. 2 experienced spalling In-housing rotor balancing with inadequate lubrication cooling Thermal growth of ball bearings caused balls to expand to the point of detrimental rubbing with the race the inner race diametral bearing clearance was increased in conjunction with elongated cage pockets eliminated in-housing rotor balancing PBP bearing springs between bearings No. 1 and No. 2 were softened to reduce the axial load on the bearings bearing preload the bearings...
Info Yqa
RSS panel failed in random vibration test Lightweight replacement composite nose cone failed during development test Missed coefficient of thermal expansion and inadequate design of mating bolt holes breakdown in system requirements Redesigned unit to proper systems requirements Concern over crack acceptance criteria after Challenger accident Formed Blue Ribbon Panel of fracture experts to review approach and make recommendations Criteria and procedures were changed supported by detailed analog...
Info Vsy
Safety concerns with fully assembled international module cluster having high likelihood of penetration Growth of debris and exposed size of module cluster taken as a whole Developed analytical tool to quantify and maximize crew survivability following orbital debris penetration verified via internal module impact effects testing, hazards effects analysis, including cooperation with DOD in crew survivability implemented improved crew operations with JSC astronaut office and Russian station...
Iv Space Shuttle Systems
If the space shuttle taught one lesson, it was that the system effects predominated the vehicle characteristics and the problems experienced. Therefore, system requirements and integration are key elements for aerospace systems quality and, thus, success. It clearly taught a second lesson that the higher the performance requirements, the higher the sensitivities to system interactions, environments, uncertainties, manufacturing tolerances, and operational complexity. The matrix of problems,...
Ocad 1
Flight Restrictions Result In Lower Launch Probability L.P. OMS POD M 1.55 OMS Deck M 1.05 Complete Set of Flight Restrictions Will Be Defined In SODB Structural Constraints Document - June 18 Figure 46. Space shuttle Mach 1.25 squatcheloid. Figure 47. Space shuttle family of squatcheloids. Figure 47. Space shuttle family of squatcheloids. These resulted in weld problems. To save cost, formal fracture control was initially not a design requirement following the pattern of the Saturn engines,...