Propellant Tanks Pressurization And Venting
VENT amp RELIEF VALVE 41.0-45.0 PSIA LIQUID HYDROGEN niMiiiiiri LIQUID OXYGEN GASEOUS OXYGEN SENSE LINE VENT amp RELIEF VALVE 41.0-45.0 PSIA LIQUID HYDROGEN niMiiiiiri LIQUID OXYGEN GASEOUS OXYGEN SENSE LINE pressure through operation of solenoid valves in the lox tank pressure control module 5 . In this manner, lox tank pressurization is maintained during all engine burn periods. An S-IVB lox tank pressure reading becomes available in the command module CM at S-II S-IVB separation. This...
Csm Guidance Control
PROPULSION TORQUE AND FORCE INPUTS TO THE S C -CCW p TCH Y W ROTATION TRANSLATION
General Description
SA TURN V SYSTEM DESCRIPTION 1-1 LA UNCH VEHICLE DESCRIPTION 1-3 RANGE SAFETY AND INSTRUMENTA TION 1-3 L V MONITORING AND CONTR OL 1-9 PERCEPTIBLE PRELAUNCH EVENTS 1-12 The Saturn V system in its broadest scope includes conceptual development, design, manufacture, transportation, assembly, test, and launch. The primary mission of the Saturn V launch vehicle, three-stage-to-escape boost launch of an Apollo Spacecraft, established the basic concept. This mission includes a suborbital start of the...
Fuel Suction Line On Inboard Engines
GASKETS ARE GEO. S. THOMPSON ALLPAX 500 REFERENCE 10413382 EXPANSION JOINT REF MAXIMUM OFF SET - 0.250 FUEL BLEED LINE-10413826-142 BACKUP PLATE-10413075 SWIVEL NUT-4C6BX-SS TUBE-10413826 ORIFICE 10414514 CHECK VALVE-10414014 BOSS 10413067 BACKUP PLATE-10413075 BRACKET ASSY-10418054 REFERENCE BOLT-AN6DD23A WASHER-AN960C616 NUT-79E-064 BACKUP PLATE-10413075 BOSS 10413063 BLEEDER PLUG-AN814-12S GASKET-MS29512- TUBE-10413826 ORIFICE 10414514 CHECK VALVE-10414014 BOSS 10413067 BACKUP...
Sickness to Health
Agena's woes were by now chronic. The Gemini Agena target vehicle GATV was pacing the program by mid-1965, prompting GPO to consider removing the first production model, GATV 5001, from its job as a test vehicle so it could be used in Gemini VIII.2 All such plans went up in smoke with the explosion of GATV 5002, which ignited the most demanding piece of engineering detective work in the entire Gemini program. Efforts to cure Agena's ailments spanned more than four months, much of it on a...
RTLS Overview
If an engine fails during the first 4 minutes of ascent, the shuttle cannot achieve orbit. For the first 3 minutes or so of ascent, it cannot even reach a TAL. The only runway near enough to be reached is one near the launch site. In order to reach this runway, the shuttle must literally reverse course and fly back the way it came. The turn to reverse course is called powered pitcharound PPA , and the timing of PPA is critically important. Since the orbiter is powerless once the main engines...
Ucvginer
IAM1i-lB E lrmttllin lt MLl lOlinntlt-flH r Communications Carrier Assembly CCA The Communications Carrier is a skull cap that interfaces with the Electrical Harness Assembly. It contains a microphone and earphones for voice communications. The skull cap is made of teflon and nylon lycra fabrics. The Hard Upper Torso is a vest-like rigid fiberglass shell which incorporates provisions for Arm, LTA and Helmet attachment. A Water Line and Vent Tube Assembly is fastened to the shell interior and...
Protection From External Heat
Pressure transducers are sensitive to their external environment and often are protected by heat shields or insulation. The pressure transducers shown on figure 4 have been covered with zinc chromate putty to protect them from external heat so that their accuracy will not be impaired. As reported in reference 38, even sunshine on the transducer housing can cause a thermal gradient sufficient to produce a measurable error. For commonly employed strain-gage transducers, about a 1-percent change...
Fluid Thermodynamic Effects
For an ideal fluid, which is as approximated by cold water, hydrocarbon and amine fuels, and other low-vapor-pressure fluids, the limitation on suction performance is always leading-edge cavitation in the inducer. With certain fluids there is observed a thermodynamic suppression head TSH that acts to decrease the critical NPSH requirements of the inducer refs. 1, 6-25 . Among the fluids known to exhibit this effect are liquid hydrogen, liquid oxygen, storable oxidizers such as N2O4, and hot...
Maneuver Analysis
The parameters derived from the best estimated trajectory for each spacecraft maneuver executed during the translunar, lunar orbit, and transearth coast phases are presented in table 7-11. Tables 7-III and 7-IV present the respective pericynthion and free-return conditions after each translunar maneuver. The free-return results indicate conditions at entry interface produced by each maneuver, assuming no additional orbit perturbations. Tables 7-V and 7-VT present the respective maneuver...
Crack Shape Parameter
Flaw types that often go undetected in metallic pressure vessels are the urface and embedded flaws. The flaw size required to cause fracture at a given applied stress level is called the critical size. If the vessel contains an initial flaw which exceeds the critical size at the proof-stress level, catastrophic failure can be expected during proof testing. Failure during service operation will occur when the initial flaw is less than the critical size at the proof-stress level, but grows with...
Instrumentation and Communications Subsystem
This subsystem provides the communications loop between the Telescope and the Tracking and Data Relay Satellites TDRS , receiving commands and sending data through the HGAs and LGAs. All information passes through the Data Management Subsystem DMS . S-Band Single Access Transmitter SSAT . HST is equipped with two SSATs. S-band identifies the frequency at which the science data is transmitted and single access specifies the type of antenna on the TDRS satellite to which the data is sent. is a...
ParachuteDesign Parameters
Typical relationships between various parachute-design parameters and aerodynamic-performance characteristics are illustrated schematically in figure 2. Although wind-tunnel tests have been used to determine force and moment coefficients for some types of parachutes, the preponderance of aerodynamic data available for design is from aerial-drop tests. Consequently, there is a notable lack of data on tangent C-ji. normal lt t. and moment 1 force coefficients and their derivative for some of the...
Laminated Honeycomb Sandwich
Attached to the inner surface of the cylinder are cold plates which serve both as mounting structure and thermal conditioning units for the electrical electronic equipment. Mounting the electrical electronic equipment around the inner circumference of the IU leaves the center of the unit open to accommodate the convex upper tank bulkhead of the S-1VB stage and the landing gear of the Lunar Excursion Module LEM . Cross section A of figure 7-3 shows equipment mounting pads bolted and bonded to...
Joe W Waters
Dr. Joe Waters, the Microwave Limb Sounder Principal Investigator, is a scientist who specializes in the development and implementation of microwave experiments to provide important new information about Earth's atmosphere. He has over 145 refereed publications in his career, with more than 4000 citations. He is a Senior Research Scientist at the California Institute of Technology Jet Propulsion Laboratory JPL , which he joined in 1973 to lead JPL's activities in microwave atmospheric science...
Axisymmetric Capsule Shape Variations
One way to achieve the required L D is to use a nonaxisymmetric shape similar to the AFE shape mentioned previously. A computer-generated shape optimization approach was pursued to attempt to optimize an OML that exhibited some of the desirable characteristics without necessarily being axissymmetric. The investigation of various optimized shapes used the optimization capabilities of the CBAERO computer code. These optimized shapes held the aft-body shape fixed, while the heat shield shape was...
Sequence Of Target Of Opportunity
Component Photographs 6151 6152 6153 Subject This mosaic, which was constructed from the three photographs listed above, presents an oblique view of crater 308, approximately 5 S, 179 E. The scale of photograph 6152 is approximately 27 percent greater than that of 6151 and 6153 also, the tilt angle of 6152 is approximately 65 to the southeast whereas, that of 6151 and 6153 is approximately 55 to the south. These two differences account for the discontinuity on the crater rim between photographs...
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...
Glide Range and Energy
After MECO, the shuttle has a certain amount of energy that determines how far and how long it can glide. This amount of energy is a function of the speed and altitude of the shuttle. The initial energy state, determined by the speed and altitude at the time the SSMEs are shut down, decreases continually during GRTLS, reaching zero at orbiter wheels stop. The horizontal distance or range that the shuttle can glide with a given amount of energy is determined by the vehicle's lift and drag...
Table Manned Apollo Missions
First manned flight test of the command service module First manned test flight of the Apollo Saturn vehicle in lunar orbit To test lunar landing hardware while in earth orbit To test lunar landing hardware while in lunar orbit To undertake the first manned lunar landing Second lunar landing Perform surface experiments Investgigate the remains of Surveyor III Third lunar landing Perform surface experiments Fourth lunar landing Use lunar rover vehicle Fifth Lunar landing Exploration of the...
Qrouno Coverage
fffMT 2J.11 J JO SC-1 REFRIGERATION VIT EM DATA LAUNCH HOURS O.E.T Evaluation of this flight data from lift-off to approximately b hours GET indicates nominal refriqeration system performance. While the radiator plume shield jettison time could not be determined precisely from tne available fliqht data, there was verification that the M command for shield jettison was sent at the nominal prescribed t1mo uu 0y gt 7.4 ul . Refrigeration system temperature djta indicates the shield was jettisoned...
Basic Requirements Heat Flux and Pressure
The energy release system shall provide the heat flux to the motor propellant and the pressure in the motor chamber necessary to ignite the propellant and produce sustained combustion within the required time limit. Because pyrogen and pelleted pyrotechnic igniters comprise the bulk of igniters currently used in operational motors, the major portion of this section on recommended practices is devoted to these types. References are provided for other systems considered of potential value for...
Sivb Aft Skirt Environmental Control
The electrical electronic equipment in the S-IVB forward skirt area is thermally conditioned by a heat transfer subsystem using a circulating coolant for the medium. Principal components of the system, located in the S-IVB stage forward skirt area, are a fluid distribution subsystem and cold plates. The coolant is supplied to the S-IVB by the IU thermoconditioning system starting when electrical power is applied to the vehicle and continuing throughout the mission. For a description of this...
Image Navigation and Registration
In addition to the acquisition of imaging and sounding data, the GOES I-M system is capable of registering to a high degree of accuracy the earth's latitude and longitude locations of each picture element pixel within an image. This accurate determination of pixel location is accomplished by a ground computer in the operations ground equipment OGE , which processes star and landmark data obtained by the Imager and Sounder. Working in conjunction with the spacecraft attitude and orbit control...
Nozzle Quality Assurance
Nozzle quality is assured by good process controls, nondestructive testing, destructive sample testing of components, and leak testing of the nozzle assembly. In addition, movable nozzles are vectored while pressurized. Nondestructive testing such as X-ray, alcohol wipe, ultrasonic, dye penetrant, and hardness testing generally is performed on all components. Reinforced-plastic composites usually are subjected to X-ray tangential and alcohol wipe no cracks are allowed, and delaminations and...
Nondestructive Testing Inspection Plan
In each new motor program, there are normally two methods for controlling motor case reliability. One method is to accumulate and analyze data on failures that occur during hydrostatic proof tests and motor static and service firings, then modify the design according to the results of the failure analysis. The other approach, used in combination with the method above, is to employ a detailed and comprehensive program of material and fabrication-process control throughout material procurement...
Apollo Program
The first Apollo mission launch date was October 27, 1961 and it verified the Saturn I's aerodynamic and structural design. A series of five more launches were conducted before the first manned Apollo launch was made on October 11, 1968. See Table 4.1 for details of Apollo missions 1 . On July 16, 1969, man landed on the moon Apollo 11 mission followed by five more moon landings. The last launch was on December 7, 1972. See Table I for The Apollo command and service module electrical power...
Flight Procedures Handbook Publications
The following is a list of the Integrated Flight Procedures Handbooks of which this document is a part. These handbooks document integrated and or flight procedural sequences covering major shuttle crew activity plan phases. OMS RCS On-Orbit Operations 10588 Inertial Measurement Unit Alignment 12842 Ascent Orbit Entry Pocket Checklists, Ascent Entry Systems 16873 Procedures and Cue Cards with Rationale Update document through OI-28, including Updated nose wheel steering section New single APU...
Lox Fueling Coupler
alcohol valve and flowed into the alcohol manifold surrounding the -thrust chamber. The inert fluid provided lor smoother ignition. After the lithium chloride had been loaded and the main alcohol valve had been closed, the connection from the lithium chloride tank and pump was disconnected and the alcohol filling operation began. The alcohol was metered as it was pumped into the missile. In addition to filling the missile with alcohol, an igniter alcohol container located on the launcher,...
Spacecraft Axis And Antenna Locations
Stee rabie S-band 2-GHz high gain antenna Stee rabie S-band 2-GHz high gain antenna Two scimitar VHF omni antennas on SM 180 deg. apart 2 VHF Recovery antennas under forward heat shield Not Shown Two scimitar VHF omni antennas on SM 180 deg. apart VHF inflight antenna 2 S-band steerable antenna 2 VHF Recovery antennas under forward heat shield Not Shown VHF inflight antenna 2 S-band steerable antenna
Terrestrial Environment Issues
Experience gained in developing terrestrial environment design criteria for previous aerospace vehicle programs has proven that to be most effective, the terrestrial environment design criteria for a new launch vehicle should be a Available at the inception of the program and based on the desired operational performance for the launch vehicle. b Issued under the signature of the program manager and be part of the controlled program definition and requirements documentation. c The design...
Water Dispenser Wash Cloth Squeezer
Figure 2.2.11.3 . WMC Water Dispenser Squeezer Figure 2.2.11.3 . WMC Water Dispenser Squeezer per month were allocated for compartment and trash disposal airlock cleaning. Each soap bar measured 1 by 2 by 3 in. 25 by 50 by 75 mm and contained Neutrogena, which acts as a mild antibacterial agent. Imbedded in the center of each soap bar was a stainless steel disc which provided a restraining mechanism for the soap when mated with the magnetic soap holders in the handwasher. The handwasher...
Hst Operations
Hubble Space Telescope operations comprise 1 science operations and 2 mission operations. Science operations plan and conduct the HST science program observing celestial objects and gathering data. Mission operations command and control HST to implement the observation schedule and maintain the Telescope's overall performance. These two types of operations often coincide and interact. For example, a science instrument may observe a star and calibrate incoming wavelengths against standards...
Appendix A Glossary
The nomenclature used in the preceding text basically is that presented in Solid Propulsion Nomenclature Guide ref. 135 . The guide should be reviewed for complete coverage of recommended solid propulsion symbols and subscripts only those used in this monograph are presented below. Symbol Definition Appears in A 1 empirical constant eq. 4 a blowing rate constant eq. 8 B empirical constant eq. 4 B' blowing rate parameter eq. 8 Cp del delivered thrust coefficient eq. 2 C f vac vacuum thrust...
Appendix B Flare And Shallow Glide Slope
In the early design of the FSGS geometry, it was decided to use a two-flare approach instead of one flare. The one flare design was more sensitive to trajectory and vehicle disturbances near the ground, and it provided no stable flight time just prior to T D. Using an initial pullup circle for a reference profile minimizes the maximum load factor and eases the monitoring task because the pullup g's are nearly constant. Also, using an IGS before an FF provided a stable flight time, which was...
ENGINE GIMBALLING SYSTEM Gts
The Saturn V engine gimballing system positions the gimballed engines of the active stage to provide the thrust vectors required for vehicle control. In performing this function, the gimballing system is controlled by commands initiated by the attitude control and stabilization function. Refer to Paragraph 20-35. The engine gimballing system steers the vehicle along its trajectory by providing engine thrust vectors for pitch, yaw, and roll control except for the S-IVB stage . The system is...
Motor Case Loads 1
The case-loading profile shall include all individual design loads or the worst combination of design loads. The loading profile shall be determined by evaluation of any and all of the following loads. All axisymmetric and local design loads for definition of design load, see sec. 2.3.1.1 , including dynamic loads sec. 3.3.7 , should be resolved into membrane loads to determine the critical design loading condition. The critical case loading condition, or worst critical combination loading,...
Atlantic Splashdown
Stage measurements evolved from research and development to operational status, and instrumentation measurements were reduced from 342 to 280. In the instrument unit, the rate gyro timer, thermal probe, a measuring distributor, tape recorder, two radio frequency assemblies, a source follower, a battery and six measuring racks have been deleted. Instrumentation measurements were reduced from 339 to 221. During the Apollo 9 mission, communications between the spacecraft and the Mission Control...
Basic Nozzle Structure
The basic structure of both external and submerged nozzles fig. 1 is subjected to internal pressure loads and flight loads. The internal pressure load is divided into an axial ejection blowout load and an opposing axial thrust load the flight loads include aerodynamic loads, inertial loads, and vibration loads. In addition to these loads, the submerged structure of a submerged nozzle is subjected to chamber pressure loads. If the nozzle is used with an attached TVC system, the nozzle structure...
SolidPropellant Vehicles
Solid-propellant vehicles have a compact structural design and have been modeled by both the lumped-parameter and continuous-model methods. In solid-propellant vehicles, the propellant is usually bonded to the case wall. Simulation of the Tank wall and dome, interstage and engine Simplified longitudinal dynamic model of space vehicle held to launch stand longitudinal elastic properties of this composite structure is difficult, in part because of the effects of dynamic interaction between the...
Subscale Test Program
The subscale test program is conducted to measure mechanical properties of the elastomer and of the bond between elastomer and reinforcement and to evaluate aging characteristics of the elastomer. In the preparation of test specimens, the surfaces of the test plates must be prepared in the same manner as the surfaces of the reinforcements in the joint if possible, the test specimen is fabricated in the manner used for manufacture of the joint. The most important properties of the elastomer used...
Laboratory Thermal Control
Insulation, surface coatings, and other passive elements perform a major role in keeping temperatures within the laboratory at acceptable values. The basic insulating materials are fiberglass reinforced polyurethane foam, fiberglass, and multilayer insulation fig. 8-1 . Fiberglass curtains on the airlock both Insulate it and protect against penetration by micrometeoroids. The mete-oroid curtain has an off-white fiberglass cloth exterior facing and is gold coated on the other facing. Emittance...
Electrical Power Subsystem
Power for the Telescope and science instruments comes from the Electrical Power Subsystem EPS . The major components are two SA wings and their electronics, six batteries, six Charge Current Controllers CCC , one Power Control Unit PCU and four Power Distribution Units PDU . All except the SAs are located in the bays around the SSM Equipment Section. During the servicing mission, the Shuttle will provide the electrical power. After deployment, the SAs will begin converting solar radiation into...
Visual Light Flash Phenomenon
Richard E. Bensona and Lawrence S. Pinskya Beginning with the Apollo 11 lunar mission, crewmen have reported seeing flashes of light while they were relaxing in the darkened command module or wearing light-tight eyeshades. These events have been described as colorless starlike flashes, narrow streaks of light, or diffuse light flashes and have been observed during translunar coast, in lunar orbit, on the lunar surface, and during transearth coast. At the times of the observations, the crewmen...
Titan Eagena B Modi
Dxts vehicle has been studied by Lockheed Aircraft Company. Though not currently under development, performance estimates are presented. The Titan ascent trajectory used is similar to that of the Atlas until first stage separation. However, after ignition of the second stage, the trajectory consists of a phase of constant attitude rate in lnertlal space rather than a consta attitude path in local space. This continues throughout the remainder of the boost and Agena phase of powered flight,...
Orbiters Delta II launch vehicle
Fairing jettison Time 282.0 seconds . . . Velocity 19,433 km h 12,07S mph Second-stage ignition 1 v r ' Altitude a 122 km 6S.9 naut mi Main engine cutoff Time a 264.0 seconds Altitude a 112.4 km 60.7 naut mi Velocity a 19,404 km h 12,0S7 mph Second-stage engine cutoff 51 Time a 677.S seconds Altitude a 188.7 km 101.9 naut mi Velocity a 28,067 km h 17,440 mph Solid rocket jettison 2 2 Time 66.0 amp 67.0 seconds Altitude 21.1 21.7 km 11.4 11.7 naut mi Velocity 3,881 3,899 km h 2,412 2,423 mph...
Burndown Weld 1
b End construction for smal 1-diameter braided metal hose temperatures above 400 F c End construction for braided metal hose 3-tn. 10 and over temperatures from cryogenic to 1 00 F Figure 44, Braided-hose end construction for specific applications. A common problem, especially with small ii-in. diam. hoses, is the overangulation and subsequent braid bulging at the ends of the hose. A solution widely used with commercial clastomeric hoses is the placing of external coil springs over the braid...
Image Navigation
Pixel navigation for the Imager and Sounder is independently established by orbit and attitude determination of each unit's optical line of sight. This computation, performed every 24 hours, is based on ranging data, landmark observations, and star observations made by each instrument. Orbit determination is accomplished primarily from range data and landmark observations. The ranging measurements are obtained by using the processed data relay PDR link and computing the round trip propagation...
Mike Tanner
Mike Tanner is the Aura Program Executive from the Office of Earth Science at NASA Headquarters. Mike is directly responsible for providing overall guidance, direction and oversight for the development of the Aura project. As Program Executive, Mike provides policy and programmatic guidance, responds to inquiries and serves as the point of contact for domestic and international partnering organizations. Serves as a strategic mission architect for the Enterprise working with the science,...
Liquid Injection Thrust Vector Control
Thrust vectoring by LITVC is accomplished by injecting a liquid into the supersonic exhaust of a rocket motor through holes in the wall of the nozzle exit cone. The injection produces side thrust by a combination of effects that include the thrust of the injectant jet itself, pressures on the nozzle wall from shock waves, and pressures on the nozzle wall resulting from addition of mass and energy to the exhaust flow. These effects are illustrated in figures 23, 24, and 25. Liquid injection TVC...