Aerospace Archive

Propellant Tanks Pressurization And Venting Saturn V Flight 2

Tue, 17 Jan 2012 04:01:09 GMT

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...

General Description Saturn V Flight 2

Tue, 27 Sep 2011 08:52:55 GMT

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 Saturn Technical Information

Tue, 27 Sep 2011 06:49:35 GMT

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 ProjectGemini

Tue, 27 Sep 2011 04:00:48 GMT

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 RTLSAbort

Tue, 27 Sep 2011 03:22:03 GMT

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 Space Suit Evolution

Tue, 27 Sep 2011 00:44:13 GMT

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 Solid Rocket Motors

Mon, 26 Sep 2011 23:43:20 GMT

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 Lqiuid Rocket Engine Turbopump

Mon, 26 Sep 2011 23:31:19 GMT

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...

SectionPage Wio Flight Director Console

Mon, 26 Sep 2011 18:10:09 GMT

3.2.1 Overview 3.2.2 APU Assembly 3.2.3 Landing Gear 3.2.4 Switch Panel CR YO TK 1 2 3 4 5 MANF1 MANF2 H2 PRESS XXXS XXXS XXXS XXXS XXXS XXXS XXXS 02 PRESS XXXXS XXXXS XXXXS XXXXS XXXXS XXXXS XXXXS HTR T1 XXXS XXXS XXXS XXXS XXXS T2 XXXS tXXXS XXXS XXXS XXXS CR YO TK 1 2 3 4 5 MANF1 MANF2 H2 PRESS XXXS XXXS XXXS XXXS XXXS XXXS XXXS 02 PRESS XXXXS XXXXS XXXXS XXXXS XXXXS XXXXS XXXXS HTR T1 XXXS XXXS XXXS XXXS XXXS T2 XXXS tXXXS XXXS XXXS XXXS EGT SPEED FUEL QTY TK P OUT P TK VLV A A T...

Maneuver Analysis Apollo 11 Mission Report

Mon, 26 Sep 2011 17:55:21 GMT

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 FractureControl

Mon, 26 Sep 2011 16:03:50 GMT

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 Hubble Space Telescope 2

Mon, 26 Sep 2011 15:55:37 GMT

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 DecelaerationSystems

Mon, 26 Sep 2011 15:17:55 GMT

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 Saturn V Flight 2

Mon, 26 Sep 2011 15:16:49 GMT

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...

State Of The Art Solid Rocket Motor Performance

Mon, 26 Sep 2011 15:07:30 GMT

In a solid rocket motor, hot gases generated by the chemical reaction between a fuel and an oxidizer stored within the motor are accelerated to supersonic velocities through a nozzle designed to develop the resultant force. Propulsion thus is achieved by the conversion of the thermal energy of a chemical reaction into the kinetic energy of combustion products. The effectiveness of this process is predicted and assessed by evaluating the reaction thrust developed through the pressure-imparted...

Joe W Waters AuraFacts

Mon, 26 Sep 2011 14:37:04 GMT

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 ExplorationSystems

Mon, 26 Sep 2011 14:05:50 GMT

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...

I Qac Mecury Restone Project

Mon, 26 Sep 2011 06:49:37 GMT

Figure 7-14. Propulsion and Auxiliary Propulsion Panels, Blockhouse 56 instrument compartment test portions of the panel. This switch was de-energized when the function selector switch was positioned in the launch position. The components test switches provided manual control for individually operating all the main valves in the propulsion system. The instrument compartment pressure test switch was provided to manually pressure test the compartment. The 115-volt, 60-cycle LOX valve and the...

Sequence Of Target Of Opportunity Apollo 11 Mission

Mon, 26 Sep 2011 02:58:56 GMT

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 AerospaceProblems

Sun, 25 Sep 2011 23:39:56 GMT

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 RTLSAbort

Sun, 25 Sep 2011 21:48:19 GMT

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 Electrical Power Systems

Sun, 25 Sep 2011 19:05:40 GMT

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...

I Aun Electrical Power Systems

Sun, 25 Sep 2011 19:05:30 GMT

PROJECT GEMINI BIBLIOGRAPHY 1962-1967 UTTl NASA-INDUSTRY Apollo Technical Conference, part 2 COUP National Aeronaut Ics anil Space Administration. Washington. 0. C. 69N71684 RPT NASA TM-X-50045 61 07 20 UT1L Electric power supply system for Apollo AUTH A ALI TN, G. 0. B COLEHOWER. E. W. C SCALES. S. H. CORP Martin Co Baltimore. Md. 69N7I6I9 61 07 20 UTTL Im atm electrical power system AUTH A MOSS. B. W. CORP Be IIcomm. Inc Washington. D. C. 79N72 lt 45 RP T NASA-CR-93015 CNT NASW-417 67 12 20...

Qrouno Coverage Orbital Workshop 3

Sun, 25 Sep 2011 17:43:52 GMT

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 Solid Rocket Motor Igniters

Sun, 25 Sep 2011 04:55:47 GMT

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 Saturn V Flight 2

Sun, 25 Sep 2011 03:12:34 GMT

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 GOES I-M Facts

Sun, 25 Sep 2011 01:26:07 GMT

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 Solid Rocket Motor Nozzles

Sat, 24 Sep 2011 19:20:16 GMT

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 Solid Rocket Motor Metal Cases

Sat, 24 Sep 2011 18:40:37 GMT

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...

References Apollo 11 Mission

Sat, 24 Sep 2011 05:36:44 GMT

1. Larsen, Paul A. and Otha H. Vaughan, Jr., Survey Report of Lunar Photography Taken during the Apollo 10 Mission, Huntsville, Alabama, October 17, 1969. 2. Apollo 11 Photography Index, 70 mm and 16 mm. Prepared by Mapping Sciences Laboratory, Science and Applications Directorate, Manned Spacecraft Center, Houston, Texas, August 1969 Author unknown . 3. Apollo Target of Opportunity Flight Chart ATO , Apollo 11 Mission, July 16, 1969 Launch Date . Prepared under the direction of the Department...

Apollo Program Electrical Power Systems

Fri, 23 Sep 2011 23:25:49 GMT

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...

I Tvb SA-207 Skylab-3

Fri, 23 Sep 2011 22:12:03 GMT

LONGITUDE. DEGREES MEST OF GREENWICH Figure 4-5. Launch Vehicle Ground Track LONGITUDE. DEGREES MEST OF GREENWICH Figure 4-5. Launch Vehicle Ground Track SECTION 5 S-IVB IU DEORBIT TRAJECTORY All aspects of the S-IVB IU deorbit were accomplished successfully. The propellant dump was modified during real time to establish a reentry traj-jectory that would enable observation by Kwajalein. This modified plan was accomplished. The velocity change obtained for deorbit was very close to the real-time...

Flight Procedures Handbook Publications ApproachLanding

Fri, 23 Sep 2011 21:30:11 GMT

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 Spacecraft Umbilical Systems

Fri, 23 Sep 2011 20:43:46 GMT

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,...

References Space Radiation Effects

Fri, 23 Sep 2011 20:03:51 GMT

1. Blizard, E. P., ed. Shielding. Vol. Ill - Reactor Handbook, Second ed., Part B. Interscience Pub. Co. New York , 1962. 2. Arnold, E. D. Handbook of Shielding Requirements and Radiation Characteristics of Isotopic Power Sources for Terrestrial, Marine, and Space Applications. Rept. ORNL-3576, Oak Ridge National Lab., Apr. 1964. 3. Anon. Synthesis of Calculational Methods for the Design and Analysis of Radiation Shields for Nuclear Rocket Systems. Rept. WANL PR- LL -010, Vol. I, Westinghouse...

References 1 Solid Propellant Selection

Fri, 23 Sep 2011 17:56:49 GMT

1. Anon, Development and Test of High Energy Solid Propellents. AFRPL TR 68204, Allegany Ballistics Laboratory, Nov. 1968. Confidential 2. Allabashi, J. C, Properties of Double-Base Propellants, Unpublished, 1969, Confidential 3. Shorr, M. and Zaehringer, A, J. Solid Rocket Technology, Ch. 2, John Wiley amp Sons, Inc., 1967. 4. Rumbel, K. E, Polyvinyl Chloride Plastisol Propellants. Paper presented at the Symposium on Manufacture, Hazards, and Testing of Propellants, 153rd National Meeting,...

References Interplanetary Particle Models

Fri, 23 Sep 2011 13:11:21 GMT

1. Parker. F.N. Dynamics of the Interplanetary Gas and Magnetic Fields. Astrophysical Journal, Vol. 123, 1958, pp. 664-675. 2. Brandt. J. C. Introduction to the Solar Wind. Freeman, San Francisco. 1970, 199 pp. 3. Bhatnagar, V. P. and Falir, H.J. Solar Wind Fxpansion Beyond the Heliosphere. Planetary Space Science. Vol. 20, No. 4, 1972, pp. 445-460. 4. Axford. W. I. Interaction of the Solar Wind with the Interstellar Medium. NASA SP-308. 1972, pp. 609-660. 5. Brandt, J.C. Interplanetary Gas...

Spacecraft Axis And Antenna Locations Apollo 11 Facts

Fri, 23 Sep 2011 09:09:49 GMT

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 Natural Terrestrial Environment

Fri, 23 Sep 2011 04:56:19 GMT

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 Orbital Workshop 3

Fri, 23 Sep 2011 01:21:52 GMT

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 2

Fri, 23 Sep 2011 01:13:10 GMT

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 Solid Rocket Motor Nozzles

Thu, 22 Sep 2011 21:40:14 GMT

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 ApproachLanding

Thu, 22 Sep 2011 20:55:19 GMT

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...

Introduction Liquid Rocket Engine Cimpustion

Thu, 22 Sep 2011 19:55:35 GMT

The problem of combustion instability, or oscillatory combustion, has been encountered in nearly all rocket engine development programs. Combustion instability severely impairs the operation of both the engine and the vehicle system, and considerable effort therefore has been directed toward solving the instability problem. In general, combustion instability results from a coupling of the combustion process and the fluid dynamics of the engine system. By this coupling, the combustion process...

Contents Solid Rocket Thrust Vector

Thu, 22 Sep 2011 18:26:39 GMT

2. STATE OF THE ART 3. DESIGN CRITERIA and Recommended APPENDIX A - Conversion of U. S. Customary Units to SI Units 161 APPENDIX B- NASA Space Vehicle Design Criteria Monographs Issued to Date 185 SUBJECT STATE OF THE ART DESIGN CRITERIA SUBJECT STATE OF THE ART DESIGN CRITERIA Material Adhesive Bond Joint Thermal Mechanical General Design Definitions 2.1.4.1.1 46 Design Safety Flexible-Joint Structural Elastomer Reinforcement Advanced Joint Adhesive Flexible Subscale Test Bench Test...

ENGINE GIMBALLING SYSTEM Gts Saturn launch vehicles

Thu, 22 Sep 2011 17:02:27 GMT

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 Solid Rocket Motor Metal Cases

Thu, 22 Sep 2011 16:34:56 GMT

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 Apollo 9 Facts

Thu, 22 Sep 2011 16:09:44 GMT

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 Solid Rocket Motor Nozzles

Thu, 22 Sep 2011 14:33:36 GMT

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 ThrustExcitation

Thu, 22 Sep 2011 14:09:51 GMT

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 Solid Rocket Thrust Vector

Thu, 22 Sep 2011 13:53:50 GMT

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 SaturnWorkshop

Thu, 22 Sep 2011 13:28:38 GMT

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 Hubble Space Telescope 2

Thu, 22 Sep 2011 12:15:30 GMT

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 Apollo 16 Science Report

Thu, 22 Sep 2011 11:43:05 GMT

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 LaunchVehicle

Thu, 22 Sep 2011 11:32:27 GMT

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 Mars Climate Orbiter

Thu, 22 Sep 2011 06:16:35 GMT

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 Space Vehicle Design

Thu, 22 Sep 2011 05:08:17 GMT

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 GOES I-M Facts

Thu, 22 Sep 2011 04:04:59 GMT

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 AuraFacts

Thu, 22 Sep 2011 03:26:30 GMT

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 Solid Rocket Thrust Vector

Thu, 22 Sep 2011 02:52:43 GMT

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...

Earth Atmosphere Photography Apollo 16 Science Report

Thu, 22 Sep 2011 01:46:05 GMT

Because the Earth is so bright in the lunar sky, special arrangements were made in advance for the commander to take short ILi exposures by interrupting the normal exposure sequence at specified times. Unfortunately, when these interruptions were made, the film was not advanced properly, so that adjacent frames overlap by approximately 30 percent. Figures 13-4, 13-5, and 13-6 are the 1-, 15-, and 60-sec ILi exposures, respectively 105 to 160 nm . These figures show the airglow of the sunlit...

References 1 Gemini 7 Program

Thu, 22 Sep 2011 00:41:12 GMT

1, Gemini Mission Evaluation Team Gemini Program Mission Report for Gemini-Titan I GT-l . MSC-R-G-64-1, NASA Manned Spacecraft Center, May 1964. 2, Gemini Mission Evaluation Team Gemini Program Mission Report GT-2, Gemini 2. MSC-G-R-65-I, NASA Manned Spacecraft Center, Feb. 1965. 3, Gemini Mission Evaluation Team Gemini Program Mission Report GT-3, Gemini 3. MSC-G-R-65-2, NASA Manned Spacecraft Center, April 1965. 4., Gemini Mission Evaluation Team Gemini Program Mission Report, Gemini IV....

Coming Events Little Joe II

Wed, 21 Sep 2011 20:19:24 GMT

Convair personnel to visit NASA-MSC to negotiate contract changes. Messrs. M. E. Dell and P. S. Jaschke, NASA-MSC, will visit Convair for the purpose of program review. Convair will attend the FRR at WSMR. Launch of Mission A-002 Little Joe II 12-51-1 BP-23 . 1. Amendment No. 13 dated 9 November 1964 incorporated CCP No. 138, 139, 143, 148, 150, 152 through 159, 161 and 162 into the contract at an increase in program price of 868,443, including a fixed fee of 52,400. This amendment increased...

Burning Rate Solid Rocket Motor Performance

Wed, 21 Sep 2011 19:53:17 GMT

mended in section 3.3.3.1. Th'i recommended techniques to be used in determining augmented rates are presented in section 3.3.3.2. 3.3.3.1 Linear Burning-Rate Characteristics Prediction of full-scale-motor propellant linear burning rates shall be based on the characteristics demonstrated in small-ballistic-evaluation-motor tests. Linear burning rates of solid pmpellants depend primarily on formulation, chambcr pressure, and temperature of the propellant grain. To provide burning-rate data for...

Auxiliary Propulsion System Control Module Saturn V Flight 2

Wed, 21 Sep 2011 15:32:28 GMT

modules are detachable and are easily checked or replaced. Each module contains four engines three 150-pound thrust control engines figure 6-15 and one 70-pound thrust ullage engine figure 6-16 . Each module contains its own oxidizer, fuel, and pressurization systems. A positive expulsion propellant feed subsystem is used to ensure that hypergolic propellants are supplied to the engine under zero or random gravity conditions. This subsystem consists of separate fuel and oxidizer propellant tank...

CH Iru Spacecraft Umbilical Systems

Wed, 21 Sep 2011 15:32:22 GMT

Figure 5-9. S-IC Intermediate Service Arm Umbilical Carrier, Lock, Retract and Reconnect Mechanism Preliminary The umbilical carrier figure 5-10 is the same as that used for the Saturn I Block II, number 1 swing arm. The carrier provides for connection of eight electrical cables, seven pneumatic lines, a liquid nitrogen line, and two air-conditioning ducts. The carrier connects to the vehicle with a pneumatically released ball-lock mechanism. Primary release of the umbilical carrier is...

Nasa Apollo Saturn1b Saturn 1B Mission 2

Wed, 21 Sep 2011 12:40:23 GMT

Sta 962.304 3-2301 A Access Door Sta 962.304 3-2301 A Access Door Figure 2. S-IB Stage Inboard Profile Water Quench amp Tail Heater Firewall Figure 2. S-IB Stage Inboard Profile

A Jux Saturn 1B Mission 2

Wed, 21 Sep 2011 12:21:04 GMT

Figure 3. S-IVB Stage Inboard Profile Figure 4. Instrument Unit Arrangement Figure 5. Saturn IB Payload SA-201 through SA-205 Figure 5. Saturn IB Payload SA-201 through SA-205 Figure 6. Saturn IB Operational Sequences SA-201 Figure 6. Saturn IB Operational Sequences SA-201

Info Dpr Electrical Power Systems

Wed, 21 Sep 2011 10:47:30 GMT

UTTL Voyager capsule phase 8. Volume III - Surface laboratory system. Part CI - Subsystem functional descr ipt Ion Final report UNOC Voyager capsule surface laboratory system - subsystem functional descriptions CORP Jet Propulsion Lab California lot.I. of Tech., Pasaoena. McDonnell Aircraft Co., St. Louis, Mo. 67N40585 RPT NASA-CR-89695 F694, VOL. III. PT. CI CNT NAS7-I00 JPL-952000 67 08 31 VOYAGER MISSION BIBLIOGRAPHY 1962-1967 PR I Nf 23 4 1 -20 T ERMI NALS 73 UTIL Electrical power system...

Tower Separation Mechanism Apollo Events Control

Wed, 21 Sep 2011 08:23:01 GMT

Figure 4-9. The Tension Tie Plate is common to a bolt which screws up into the CM structure and another bolt which screws down into the CM support structure on top of the SM as shown in figure 4-10. After the CM has been bolted down to the SM under tension, an FLSC Cutter Assembly is installed on each of the 3 Tension Tie Plates in the manner shown in figure 4-11. Note the face-to-face mounting of the FLSC onto the Tension Tie Plate and a Detonator provided for each. When CM - SM Separation is...

Project Gemini Electrical Power Systems

Wed, 21 Sep 2011 04:21:39 GMT

Experience from Project Mercury demonstrated that failure propagation can occur when the systems are designed such that there is an interdependency or when systems are installed in a stacked fashion with common interfaces. In order to remove this constraint, Gemini development program emphasized rigorous . Component Testing . Subsystem Testing . Integrated Systems Testing The Gemini systems were almost exclusively installed In a modular structure outside the inner pressure vessel and were...

Rotation Control Apollo Training Guidance 2

Wed, 21 Sep 2011 03:35:42 GMT

TRAVEL PRIOR TO SWITCH ACTUATION TRAVEL TO HARDSTOP MAXIMUM TORQUE 8.0 MIN 25.0 MAX 1.0 POUND INCHES BREAKOUT SWITCH ACTUATION CONTROLLER LOCK TO ARM DISPLACEMENT 1L 5 0.50 IL 0 10 1 1.5 0.5 5tt 0 DIRECT RCS SOLENOIDS amp RJ EC AUTO RCS LOGIC HARD STOP, DETENT amp SWITCH CLOSURE FORCE INTO DETENT OUT OF DETENT TRANSLATION CONTROL MOTION LIMITS OR - COMMANDS MECHANICAL STOP - a 5 0.075 ARC INCHES SWITCH CLOSURE - a375 ARC INCHES v - r ' 17 scs ENABLE 3K1 - RATE I IGN 2 J SCS AUTO CW SCS RATE CMD...

Saturn V Launch Vehicle 1 Apollo 8 Facts

Tue, 20 Sep 2011 18:46:37 GMT

The white Saturn V launch vehicle, with the Apollo spacecraft and launch escape system mounted atop, towers 363 feet above the launch pad. The three propulsive stages and the instrument unit have a combined height of 281 feet. The vehicle weighs 6,219,760 pounds at ignition. Marked with black paint in sections for better optical tracking, identified with huge red lettering, and wearing the United States Flag on the first stage, the giant vehicle is capable of hurling 285,000 pounds into low...

Cruciform Baffles and Other Suppression Devices SloshSuppression

Tue, 20 Sep 2011 17:43:35 GMT

Cruciform baffles and suppression devices other than ring baffles are not recommended for general use. Cruciform baffles may, however, be useful in nearly empty tanks, and other specific applications may indicate their desirability, in which case their effectiveness should be verified by experimental measurements. Although studies of the influence of flexible diaphragms on liquid sloshing in spherical tanks show that significant damping of slosh forces could be achieved, such devices are...

Radio sounding of the neutral atmosphere and ionosphere Science Objectives MarsExpress

Tue, 20 Sep 2011 16:27:31 GMT

The modern value for the surface pressure of Mars was first determined in 1965 by using the radio occultation method with Mariner-4 Kliore et al., 1965 . Prior to that, the literature indicated a consensus that the surface pressure was of the order 100 mbar about 10 of Earth's , based on spectroscopic observations from the ground, with many believing that oxygen was a likely major constituent. A more accurate value was needed in support of martian landers being studied by NASA teams lead by...

Physical Description Hubble Space Telescope 2

Tue, 20 Sep 2011 16:01:03 GMT

ACS will reside in an axial bay behind the HST main mirror. It is designed to provide HST with a deep, wide-field survey capability. The primary design goal of the ACS WFC is to achieve a factor of 10 improvement in discovery efficiency compared to WFPC2. Discovery efficiency is defined as the product of imaging area and instrument throughput. Grism spectroscopy low resolution R 100 wide-field spectroscopy from 5500 to 11,000 A, available in both the WFC and the HRC. Objective prism...

OTA Equipment Section Hubble Space Telescope 2

Tue, 20 Sep 2011 15:08:37 GMT

The OTA Equipment Section is a large semicircular set of compartments mounted outside the spacecraft on the forward shell of the SSM see Fig. 5-25 . It contains the OTA Electrical Power and Thermal Control Electronics EP TCE System, Fine Guidance Electronics FGE , Actuator Control Electronics ACE , Optical Control Electronics OCE and the fourth DMS DIU. The OTA Equipment Section has nine bays seven for equipment storage and two for support. All bays have outward-opening doors for easy astronaut...

dimensions Units and conversion factors MagneticFields

Tue, 20 Sep 2011 14:47:04 GMT

Several systems of. units have been commonly used to describe the characteristics of magnetic fields. The system of electrostatic units esu uses Coulomb's law and the system of electromagnetic units emu uses the law of attraction between currents. The Gaussian system'expresses magnetic quantities in.emu and electric quantities in esu. In the Gaussian system, the magnetic flux density B and the magne.ic field intensity H are used interchangeably. This interehangeability is based on the fact that...

Nozzletochamber Attachment Solid Rocket Motor Nozzles

Tue, 20 Sep 2011 14:03:06 GMT

Four methods for attaching the nozzle to the chamber are in common use for flightweight production design fig. 36 . A bolted joint is most common because it is positive and rigid, provides means for accurate thrust alignment, disassembles freely, and is not size limited. Entrance thermal liner and insulation carbon phenolic tape Entrance thermal liner and insulation carbon phenolic tape a Boot alone boot folds as nozzle pivots Attach insulation ____ silica phenolic tape a Boot alone boot folds...

Spacecraftmission Mir PE Walking to Olympus

Tue, 20 Sep 2011 12:19:18 GMT

Crew Yuri Romanenko, Alexander Laveikin Spacewalkers Yuri Romanenko, Alexander Laveikin Purpose Contingency EVA to investigate cause of Kvant module hard docking difficul- The first Mir space station EVA - only the 19th of the Soviet space program - was a contingency spacewalk to permit Kvant, the station's first expansion module, to complete docking. One of its participants, Yuri Romanenko, took part in the first Soviet space station EVA aboard Salyut 6 in 1977, which also involved a docking...

Countdown 1 Skylab 4 Facts

Tue, 20 Sep 2011 02:35:21 GMT

After the July 28 launch of the second crew to man Skylab, the mobile launcher was brought back to the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida. The stages of the next Saturn IB launch vehicle and a boilerplate Command Service Module CSM were erected on the mobile launcher on July 31 and August 1. Starting August 2, the impact of problems with two of the four control engine quadrants in the docked service module's attitude control system and the possibility of a...

r Kgz Saturn V Flight

Tue, 20 Sep 2011 01:29:41 GMT

Plight Control System, Saturn S-1I February 1, 1965 SID 62-140. Flight Dynamics Analysis, Saturn V Launch Vehicle, AS-507 July 24. 1969 Boeing Report DS-lSS09 F -7. Flight Manual, Saturn V, SA-506 June 10, 1969 MSFC-MAN-506. Flight Manual, Saturn V, SA-507 August IS, 1969 M8FC-MAN-S07. Flight Operations Planning and Preparation for Manned Orbital Missions John H. Boynton and Christopher C. Kraft, Jr. AIAA Paper No. 66-904. Flight Performance Handbook for Powered Flight Operations Space...

r Enu Apollo 12 Saturn V

Tue, 20 Sep 2011 01:26:27 GMT

Plight Control System, Saturn S-1I February 1. 1965 SID 62-140. Flight Dynamics Analysis, Saturn V Launch Vehicle, AS-507 July 24. 1969 Boeing Report D5-lS509 F -7. Flight Manual, Saturn V, SA-506 lune 10, 1969 MSFC-MAN-506. Flight Manual, Saturn V, SA-507 August IS, 1969 MSFC-MAN-507. Flight Operations Planning and Preparation for Manned Orbital Missions John H. Boynton and Christopher C. Kraft, Jr. AIAA Paper No. 66-904. Flight Performance Handbook for Powered Flight Operations Space...

Should the HGA Anomaly Have Been Prevented GalileoProject

Mon, 19 Sep 2011 23:08:32 GMT

An analysis of the HGA anomaly by John F. Kross in the periodical Ad Astra concluded that human error led to the antenna's failure to open. The problem should have been anticipated, Kross wrote. After all, the molybdenum disulfide lubricant was applied just once, nearly a decade before launch. Travel is notoriously fraught with risk When asked if this excess travel was ever addressed as a potential problem, project manager William O'Neil claims, 'I believe that the travel induced lubricant...

Introduction CompartmentVenting

Mon, 19 Sep 2011 20:52:18 GMT

Space vehicles contain many compartments whose walls may be subjected to critical loads imposed by pressure differentials across them. These compartments include not only such obvious enclosures as interstages, payload shrouds, and fairings, but also enclosures such as heat shields, insulation panels e.g., multilayer blankets and foam , honeycomb and corrugated sandwich structure, and housings for electronic equipment and conduits. Pressure differentials cause bursting or crushing loads which...

Info Asc AerospaceProblems

Mon, 19 Sep 2011 17:25:56 GMT

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...

Test Facility Description Atmosphere Revitalization 2

Mon, 19 Sep 2011 16:46:42 GMT

The Phase III IART was conducted in the Core Module Simulator CMS , a 175-m3 6,180-ft3 sealed chamber that provides a closed working volume and connections to facility power and consumable resources. Test control, data acquisition and management, and process monitoring capabilities are also provided by the facility. The entire test facility, called the Core Module Integration Facility CMIF , includes the CMS, resource distribution network, and control room. Bench test stands that support...

Block Fields Lunar Surface Models

Mon, 19 Sep 2011 14:35:35 GMT

Studies H. J. Moore of dense block fields indicate the distributions may be higher than those shown in figure 9. However, Moore's data also show that there are often paths 50 meters or wider through even dense block fields which are relatively free of blocks. Figure 7. - Cumulative number of blocks in intercrater region of smooth Mare, rough Mare, and Upland terrains. Figure 7. - Cumulative number of blocks in intercrater region of smooth Mare, rough Mare, and Upland terrains. Figure 8. -...

REPRODUCIBILITY OF THE ORIGINAL PAGMf IS POOR Apollo Spacecraft 1964 - 1966

Mon, 19 Sep 2011 13:09:30 GMT

1965 A LEM CSM interface meeting uncovered a number of design problems April and reierred them to the Systems Engineering Division SED for evaluation the requirement for ground verification of panel deployment prior to LEM 7 withdrawal the requirement for panel deployment in earth orbit during the SA-206 flight the absence of a backup to the command sequencer for jettisoning the CSM Flight Projects Division FPD urged such a backup signal and Grumman's opposition to a communications link with...

Bailout Crew Escape System

Mon, 19 Sep 2011 11:50:24 GMT

The prescribed order of bailout will be 1 Attach D-ring on parachute riser to snap hook on lanyard before releasing snap hook from magazine . 2 Release lanyard from magazine. 4 Bail out, forcibly rolling out of hatch remaining tucked. Mode 8 bailout Figure 4.7-1 shows the CDR PLT and MS versions of the Mode 8 bailout cue REPORT POSITION MACH lt .95, OPS 305 603 SB - AUTO BF - AUTO FLY 185-195 KEAS, F 0o ABORT MODE - ATO ABORT PBI - PUSH P,R Y - AUTO FLT CNTLR PWR two - OFF 50K FT TABS - RELEASE...

SYSTEMS DATA Gti Apollo Environmental Control

Mon, 19 Sep 2011 09:08:33 GMT

continues through recovery. The following paragraphs describe the operating modes and the operational characteristics of the ECS from the time of crew insertion to recovery. 2.7.2.1 Spacecraft Atmosphere Control. During prelaunch operations the SUIT CIRCUIT RETURN VALVE is closed and the DIRECT O valve is opened slightly approximately 0.2 pound per hour flowrate to provide an oxygen purge of the PSC. Just before prime crew insertion the O flowrate is increased to 0.6 pound per hour. This flow...

Blunt Bodies Versus Slender Bodies Trade ExplorationSystems

Mon, 19 Sep 2011 04:54:11 GMT

The shape study trade was initiated between major vehicle classes. The primary classes considered were capsules blunt bodies , slender bodies, lifting bodies, and winged vehicles. Winged bodies and lifting bodies such as X-38, X-24, HL-10, etc. were eliminated at the outset due to several factors, including 1 the extreme heating especially on empennages these would encounter on lunar return entries, 2 the additional development time required due to multiple control surfaces, and 3 the increased...

Spacecraft Axis And Antenna Locations 1 Apollo 11 Facts

Mon, 19 Sep 2011 02:33:43 GMT

Reaction Control System RCS The command module and the service module each has its own independent system. The SM RCS has four identical RCS quads mounted around the SM 90 degrees apart. Each quad has four 100 pound-thrust engines, two fuel and two oxidizer tanks and a helium pressurization sphere. The SM RCS provides redundant spacecraft attitude control through cross-coupling logic inputs from the stabilization and guidance systems. Small velocity change maneuvers can also be made with the SM...

Chapter Apollo 1 Crew

Sun, 18 Sep 2011 22:27:47 GMT

1. Much of this chapter is based of Report of Apollo 204 Review Board to the Administrator, National Aeronautics and Space Administration Washington, 1967 -- Floyd L. Thompson, chairman, 5 April 1967, with appendixes A through G hereafter cited at RARB . Also basic are Senate Committee on Aeronautical and Space Sciences, Apollo Accident Hearings, 8 parts, 90th Cong., 1st and 2d sess., 7 Feb. 1967 to January 1968, and House Committee on Science and Astronautics, Subcommittee on NASA Oversight,...

Launch Escape System Apollo 7 Facts

Sun, 18 Sep 2011 19:51:13 GMT

launch escape motor thrust alignment fitting launch escape motor thrust alignment fitting power systems amp instrumentation wire harness power systems amp instrumentation wire harness boost protective CWER apex section

Mobile Launcher Saturn V Flight 2

Sun, 18 Sep 2011 12:00:22 GMT

HNgSCU Flow Control Valve Box W Selects either GSCU for operation of one unit while the other recirculates. 2 gt Ground Support Cooling Unit f Supplies water-methanol to the heat exchanger in the IU thermal conditioning system to absorb heat in the IU generated by electronic equipment. p s-IVB Pneumatic Console A amp B r Regulates and controls helium and nitrogen gases for leak testing, functional checkout, propellant loading, purge, and propell ant unloading. As-IVB APS Pneumatic Console y...

High Accuracy Sun Sensor GOES I-M Facts

Sun, 18 Sep 2011 11:34:08 GMT

The pointing knowledge required of the SXI is 10 arcsec, which is met by the HASS. The HASS consists of a Sun sensor head and a Sun sensor electronics box. Various reticles and associated solar cells form the optics of the sensor head. The electronics package provides multiplexed processors for the coarse and fine Sun data, and for detecting Sun presence. The Sun angle output signals are passed through shift registers. The HASS output to the data electronics box is digital. Serial data...

Data Management Subsystem Hubble Space Telescope 2

Sun, 18 Sep 2011 09:08:19 GMT

The DMS receives communications commands from the STOCC and data from the SSM systems, OTA and science instruments. It processes, stores and sends the information as requested see Fig. 5-10 . 3. Scientific data from the SI C amp DH unit 4. Telescope engineering status data for telemetry 5. System outputs, such as clock signals and safemode signals. Advanced Computer. The Advanced Computer is a general-purpose digital computer for onboard engineering computations. It executes stored commands,...

Nozzle Configuration And Construction Solid Rocket Motor Nozzles

Sun, 18 Sep 2011 05:38:47 GMT

Nozzle design is a dynamic, iterative process, as evidenced by the estimate of nozzle designers that they average three major iterations before release of a design. Interation occurs because of 1 interactions between nozzle and total propulsion systems and 2 interactions between the design and analysis tasks fig. 22 . The initial values of the design parameters e.g., throat area, expansion ratio for the design of the nozzle are based on estimates of the weight, peformance, envelope, and...

Maneuvering Characteristics Hubble Space Telescope 2

Sun, 18 Sep 2011 04:51:23 GMT

The Telescope changes its orientation in space by rotating its reaction wheels, then slowing them. The momentum change caused by the reaction moves the spacecraft at a baseline rate of 0.22 degree per second or 90 degrees in 14 minutes. Figure 6-2 shows a roll-and-pitch maneuver. When the Telescope maneuvers, it takes a few minutes to lock onto a new target and accumu V1 Roll Maneuver Viewing Away From Sun V1 Roll Maneuver Viewing Away From Sun V2 Pitch Maneuvers Maneuver plane contains Sun V2...

Appendix Nasa Centers And Other Government Agencies Participating In The Gemini Program Project Gemini Technology

Sun, 18 Sep 2011 04:32:07 GMT

NASA Headquarters, Washington, D.C., and the following NASA centers Ames Research Center, Moffett Field, Calif. Electronics Research Center, Cambridge, Mass. Flight Research Center, Edwards, Calif. Goddard Space Flight Center, Greenbelt, Md. Kennedy Space Center, Cocoa Beach, Fla. Langley Research Center, Langley Station, Hampton, Va. Lewis Research Center, Cleveland, Ohio Manned Spacecraft Center, Houston, Tex. Marshall Space Flight Center, Huntsville, Ala. Department of Defense, Washington,...