Bristol 164 Brigand torpedo fighter and light bomber

The Bristol Type 164 Brigand was the last in a series of twin piston-engined fighter and bomber designs produced by Bristol in a period just prior to and including the Second World War. The preceding Blenheim, Beaufort and Beaufighter were all successful but the Buckingham was a failure, although a version called the Buckmaster was used as a trainer for the Brigand.

AH-64D Longbow best helicopter on the World

The AH-64D Longbow Apache is structurally very similar to the original Apache – AH-64A. Key improvements include a more powerful engine, improved avionics and navigation systems, and a modern digital cockpit. All AH-64Ds have received the improvements, but only 227 have been fitted with the Longbow radar.

Milan Malpensa Airport Review and History

Milan Malpensa Airport is the largest of the three facilities that serve the Milan metropolitan area. Located 25 miles (40km) north-west of the city centre, the airfield has been associated with aviation for more than 100 years. It all began on May 27, 1910 when the Caproni brothers flew their first flying machine, the Cal biplane, from what was little more than a field. In the years that followed, many prototypes took-off from here and eventually a more formal airfield was established.

Bulgarian Navy AS565MB Panther helicopter

The Bulgarian Navy finally received its long-awaited AS565MB Panther helicopters at the end of 2011. Serial number 901 entered service at the Separate Maritime Helicopter Air Base ‘Chaika’ (Otdelna Morska Vertoletna Avio Basa ‘Chaika’) during an official ceremony that took place at Chaika-Varna on 9 October. The remaining two helicopters (serial numbers 902 and 903) arrived in November and December.

UH-60 Black Hawk utility tactical transport helicopter

The development of UH-60 Black Hawk started in January 1972 as the part of Utility Tactical Transport Aircraft System (UTTAS) program. Helicopter manufacturers were asked to submit proposals for a new machine that would carry heavier loads at greater speeds and over greater distances than the Bell UH-1 Huey. At the same time, the design was to provide better protection and durability than the earlier helicopter.

Boeing AH-64 Apache gunship helicopter – AAH winner

The AH-64 Apache is the US Army’s principal gunship/antitank helicopter. It was the winner in the 1973-76 competition for an Advanced Attack Helicopter (AAH), beating out the Bell YAH-63 entry. The AH-64 is intended primarily for the antitank role, with an all-weather/nigh t operating capability. It is relatively fast and maneuverable, carries a large antiarmor weapons load, has reduced radar and Infrared (IR) signatures, is damage-resistant against most small and medium antiaircraft artillery, and is crashworthy.

Atmospheric Entry Probe Testing

NASA engineers designed Galileo's 4-foot-wide Probe to separate from Orbiter 150 days out from Jupiter and eventually plunge into the planet's atmosphere. It would enter the atmosphere on a shallow trajectory of approximately 9 degrees below horizontal and gradually slow from a velocity of 107,000 mph (48 kilometers per second) to Mach 1. The Probe's thermal heatshield would enclose and protect the scientific instruments during this time. Once Mach 1 was reached, a parachute system would...

Recovery Operations

The Department of Defense provided recovery support in accordance with the mission planning for Apollo 15. Ship support for the primary landing area in the Pacific Ocean was provided by the helicopter carrier USS Okinawa. Active air support consisted of five SH-3G helicopters from the Okinawa and two HC-130 rescue aircraft staged from Hickam Air Force Base, Hawaii.

Fundamental Criteria for Life Chart

Criteria For Oife

Fill in Criteria after the class has made observations and the teacher has grouped the observations. Living Organism Criteria Criteria Criteria Criteria Criteria Activity 2 Part A Looking for Life About This Activity In Activity A students will use research to develop their criteria for life. The class will combine their ideas in a teacher-guided discussion. In Activity B they will then use their definition of life to determine whether there is anything alive in three different soil samples.

Spherical Dampers

Magnetic Damper

Spherical dampers are magnetically coupled to the earth's magnetic field and dissipate the libra-tion energy of the GG spacecraft by either viscous fluid or eddy-current damping see also sect. 2.1.1 2 . Details in addition to those below are given in references 3, 4, 5, and 6. Viscous-Fluid Spherical Damper. Dampers flown on the Gravity Gradient Test Satellite GGTS spacecraft consist of two concentric spheres with a damping fluid contained between the spheres as shown in figure 2. A cylindrical...

Space Shuttle Configuration Evolution

Space Shuttle Configuration Evolution

Figure 3 -J Figure 3 SPACE SHUTTLE PERFORMANCE SPECIFICATIONS (Figure 4) This figure is a summary of the current Level I requirements for the reusable shuttle. The cargo bay is baselined as 15 feet (K.6 m) in diameter by 60 feet (18.3 m) in length. The 60-foot dimension is perhaps the firmest dimension inasmuch as it provides space for rockets such as the Agena and Centaur stages.

Cooling Methods Regenerative and Dump Cooling

Baffles Injectors Liquid Rocket Engine

Baffles usually are cooled with the rocket fuel, although oxidizer and bipropellant cooling occasionally have been used. A typical design, showing coolant passages used on the F- qualification injector, is presented in figure 15. Coolant flowrate through regenerative or dump-cooled baffles is established to satisfy two requirements 1 The total heat absorbed by the coolant must be equal to the integrated gas-side heat flux, and if the coolant is liquid this heat must be absorbed without...

Ring Baffles

The design of ring-baffle slosh-suppression systems is based on selecting baffle width, spacing, and depth of top baffle to give the required damping ratio f as a function of liquid level in the tank. For a flat rigid-ring baffle in a cylindrical tank, the damping ratio as a function of baffle depth d should be estimated from Miles' equation (ref 31) where W is the baffle width rj the maximum slosh-wave height at the wall and 5, the damping factor (or logarithmic decrement). The term in...

For Deltawing Orbiter

X 10 7_ 10' 10 LANGLEY 20-INCH TUNNEL PRESENT TESTS FLIGHT ENVELOPE FOR HIGH CROSS-RANGE ORBITER LANGLEY VARIABL DENSITY TUNNEL AMES 3.5 FOOT TUNNEL (UNPUBLISHED DATA) LANGLEY 22-INCH HELIUM TUNNEL (UNPUBLISHED LANGLEY DATA) 0 1 8 12 M 16 20 24 28 oo CONCLUSIONS Some of the results of an experimental lee-surface heating investigation on a delta-wing orbiter are presented with the following conclusions 1.

Nonpropulsive Venting System Performance

A non-propulsive vent (NPV) system was installed on SA-7, in addition to the main pressure relief LOX and LH2vent systems used on SA-5andSA-6, to obviate the excessive angular rates due to the venting of residual propellants after S-IV cutoff experienced on SA-5 and SA-6 (See Fig. 8-3). The NPV system was designed to keep the angular rates below 6 deg s, the maximum allowable on the Pegasus experiments. The S-IV-7 non-propulsive vent system performed satisfactorily, as indicated by all...

Throat Insert

Segmented Grains Rocket

Six groups of materials have been evaluated as nozzle throat inserts 3 Pyrolytic graphite and pyrolytic graphite codeposited with silicon carbide The first four materials are in common usage, and the carbon carbon composites also called fibrous graphites or prepyrolyzed composites are in advanced development. The ceramics, however, have poor thermal-shock characteristics currently they are not considered by nozzle designers to be suitable for solid rocket application. Only the first five...

Liner Materials

Thermal liners, or flame barriers, are the materials that form the gas-side contour of the nozzle. As noted, throat inserts are either highly-erosion-resistant materials refractories or reinforced plastic. The liners in the remainder of the nozzle usually are reinforced plastics, although, as previously noted, poly crystalline graphites have been used as blast-tube and Elastomers are another group of materials that have also served as liners in some nozzle designs. Elastomeric liners in general...

Nozzletochamber Attachment

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...

Design Requirements And Constraints

Nozzle design requirements and constraints are imposed specifcally by contract, are specified by propulsion or vehicle system analysis, or are left to the discretion of the nozzle designer. Requirements from system analyses are, in part, based on estimated nozzle weight, performance, and envelope. An iterative process therefore is involved, and nozzle design parameters can be expected to change during a design effort. The nozzle designer is better prepared to respond to changes when he is...

Figures of Merit Safety and Reliability

The same probabilistic techniques used in previous analysis cycles, and described in Section 8, Risk and Reliability were repeated for the final set of mission modes and technology options. Three mission modes were analyzed, with three different propulsion technologies applied. In addition to the LOR, EOR-LOR 2-launch, and EOR-LOR 1.

LSAM Reference Design

The ESAS team examined the unique architecture of the lunar lander, or LSAM. Other architecture element designs and trade studies were also accomplished by the team. The reference LSAM concept, shown in Figure 1-16, for the ESAS 1.5-launch EOR-LOR architecture is a two-stage, single-cabin lander similar in form and function to the Apollo LM. The LSAM ascent stage, in conjunction with the descent stage, is capable of supporting four crew members for 7 days on the lunar surface and transporting...

Design Reference Missions

A series of DRMs was established to facilitate the derivation of requirements and the allocation of functionality between the major architecture elements. Three of the DRMs were for ISS-related missions transportation of crew to and from the ISS, transportation of pressurized cargo to and from the ISS, and transportation of unpressurized cargo to the ISS. Three of the DRMs were for lunar missions transportation of crew and cargo to and from anywhere on the lunar surface in support of 7-day...

Lunar Architecture Recommendations

The lunar architecture defined by the ESAS integrates mission mode analysis, flight element functionality, and the activities to be performed on the lunar surface. An integrated analysis of mission performance, safety, reliability, and cost led to the selection of a preferred mission mode, the definition of functional and performance requirements for the vehicle set, and the definition of lunar surface operations. Additionally, the analysis looked back to examine how the CEV and CLV would be...

Nozzle Misalignment

Thrust Vectoring For Model Rockets

Axial deflection causes a vectoring misalignment of the nozzle. When the actuator attachment points are a fixed distance apart, as in the case just after booster launch before the guidance system begins to control the vehicle, the nozzle is not free to translate aft as the motor pressure increases. An actuator length that holds the movable components aligned to the fixed components at zero motor pressure would be too short at operating pressure. The nozzle at pressure would vector as though the...

Attitude Hold

The chief purpose of the attitude hold phase is to reduce the maximum loads that are imposed on the main landing gear. The attitude of the orbiter at T D is held constant until the EAS decreases to a specified value. This value is selected to achieve a compromise between the maximum load on the main gear and the maximum load on the nose gear. The peak load on the main gear decreases as the derotation is delayed, but the peak load on the nose gear increases.

Through Bulkhead Initiators

As is frequently the case in the ignition field, the application of a through-bulkhead initiator TBI has preceded a comprehensive theoretical explanation of the behavior of the components involved. However, some success has been reported in relating the detonation-to-deflagration transition to the detonating velocity and resulting shock pressure. A simplified illustration of a TBI is provided in figure 6. Acceptor charge 5 8 - 18 UNF-2A Closure Sealant Ignition charge Integral diaphragm Figure...

Pelleted Pyrotechnics

Solid Rocket Motor Igniters

In the broadest sense, the term pyrotechnic describes a large variety of igniter types. For purposes of this monograph, however, this group of igniters is limited to pyrotechnics in the form of pellets or large grains. Examples of these types are shown in figures 8 and 9. Figure 8. Pyrodyne igniter. Igniter body Booster charge Figure 8. Pyrodyne igniter. Igniter body Booster charge In the pelleted pyrotechnic, the pellets are retained for the bulk of their burning time by either a wire mesh or...

Burning Rate

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...

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...

To Cabin Pressure Switch

Cabin Repressurization and Emergency Oxygen Valve - Functional Schematic maintain cabin pressure at 3. 5 psia for at least 2 minutes, allowing the astronauts to return to a closed-suit environment. The valve is controlled by a three-position handle on the oxygen control module. When the AUTO position is selected, valve operation is controlled by the solenoid, which is actuated by the cabin pressure switch. If cabin pressure drops below normal, the cabin pressure switch energizes...

Deorbit Burn Overview

Following seat ingress activities, the commander CDR and pilot PLT copy updates to the deorbit, entry, and landing DEL preliminary advisory data PAD and the orbital maneuvering system OMS propellant PRPLT PAD. The CDR checks and loads the final deorbit targets previously uplinked by the Mission Control Center MCC . During the remaining half hour before deorbit ignition, the crew configures the horizontal situation display HSD , checks the switch positions for an OMS or reaction control system...

Measuring Chamber and Igniter Pressure

Most tests of solid rocket motors require a means for measuring chamber and igniter pressures. Usually, small-diameter piping or tubing connected to threaded outlets or bosses on the motor chamber is used to transmit pressure to a transducer. The locations in the motor chamber for monitoring pressure are dependent upon several factors described more fully in sec. 2.2.2 i.e., the locations are selected so that 1 the pressure path is short and dynamic response is not jeopardized 2 the pressure...

Entry CRT Parameters

Prior to beginning the discussions of each display, some mission-independent GN& C parameters common to all the entry trajectory displays should be defined. The ENTRY TRAJ 1 display, shown in figure 5-1, is representative of the common format among the entry trajectory displays. The following Gn& C parameter discussion references the ENTRY TRAJ 1 display. 1. The angle of attack currently being obtained from NAV or the ADTA subsystem operating program (SOP) is indicated by the (> )...

Vertical Situation Displays

Two Vertical Situation Displays VSD are used to monitor the guidance function in the TAEM region. The VERT SIT 1 display comes up automatically at TAEM interface or when the crew performs an OPS 305 PRO or an OPS 602 PRO. It also comes up automatically at the end of the Z-translation maneuver in the case of a return to launch site RTLS abort. This discussion does not address the use of these displays as applied to an RTLS and the reader is referred to the Ascent Abort Flight Procedures...

Use of Entry Traj Crt Displays

In this section figure 5-7 (ENTRY TRAJ 1) is used to illustrate how the information presented on the ENTRY TRAJ displays can be used for auto guidance monitoring. Because the five TRAJ displays are basically the same layout and contain the same digital readout information, the monitoring task is similar on the subsequent TRAJ displays. The health of the entry can be considered a function of (1) how well auto guidance is performing in issuing commands to keep drag on drag reference, (2) how well...

Bias Readout

As discussed in a previous section, the H bias term displayed digitally on the ENTRY TRAJ displays is a feedback correction term calculated by guidance. Before the addition of alpha modulation to entry guidance, the only means of controlling drag was by roll command, to keep the orbiter on a guidance-calculated reference D-V profile. One possible source of error that can cause a bias in the actual drag flown with respect to the reference drag is an IMU platform misalignment. In the presence of...

Mobile Transporter

The purpose of the Mobile Transporter (MT) is to provide the following structural attachment between the Mobile Remote Servicer Base System (MBS) Space Station Remote Manipulator System (SSRMS) and the truss rails (MT interfaces directly with MBS) utility interfaces between the United States Orbital Segment (USOS) and the MBS SSRMS (when parked at one of the 10 truss worksites) and the translation force for the entire Mobile Servicing System (MSS) along the International Space Station main...

GRTLS Guidance

As discussed in the previous section, the one fundamental task of guidance during GRTLS is to arrive at the runway with the right amount of energy to complete a safe landing. To manage the energy state while providing satisfactory flight conditions, GRTLS guidance can be divided into the following sections The first three of these phases are designed to provide the transition from an exoatmospheric ballistic trajectory to hypersonic gliding flight. S-turn and TAEM are where most of the energy...

Hiller UH-12 Raven standard observation helicopter

Young Stanley Hiller Jr flew his first helicopter, the coaxial-rotor XH-44, in August 1944. He then made a completely fresh start, with single main rotor with hanging control column, and, by way of UH-5 Commuter prototypes, perfected a patented Rotor-Matic control system with the cyclic stick connected not to the main blades but to short auxiliary blades set at 90° and rotating as part of the main rotor.

Parachute Design Parameters

Ballute Drag

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...

Entry Data Analysis For Viking Landers I and

NASA-CS-159388 ENTRY DATA ANALYSIS FOB Nd1-7u77o VIKING LANDEHS 1 AMD 2 Final Beport Martin Marietta Corp. Martin Marietta Corporation DENVER DIVISION P. 0. Box 179 Denver, Colorado 80201 NATIONAL TECHNICAL INFORMATION SERVICE This report is submitted as DRL Line Item N3-C003 under Contract NAS1-9000 to satisfy Phases 2 DECSET and 3 LTARP of the Entry and Touchdown Analysis Procedure MDO 1-13 . The principal authors for this report are II. DEORBIT BURN A. Time of Deorbit Burn B. Velocity to be...

Operations Ground Equipment

The GOES ground segment consists of three parts ground station radio frequency RF equipment, telemetry and command system, and the payload processing and spacecraft operations system. The ground station RF equipment is located at the SOCC and CDA facilities. Telemetry and command are provided by the GOES I-M telemetry and command system GIMTACS , also located at the SOCC and CDA. Payload processing and spacecraft operations support is provided by the operations ground equipment OGE . The OGE...

Single Engine Press Purpose

Documents the procedure used to make this call. PROCEDURE USE 2HM NOMS CHANNEL SELECT THE 1E Press-to-MECO BIAS BASED ON SITUATION SIMO BIAS FOR 3-SSME ON SEQ w dump FOR 2-SSME ON POST-ATO SELECTION WHEN MARGIN BIAS CALL SINGLE-ENGINE PRESS 104 GAP CLOSURE (LAST PRE-MECO TAL TO FIRST SINGLE-ENGINE PRESS) CONFIGURE 2HM FOR ONE SSME AT 109 ACLS DOWN USE MAXIMUM CAPABILITY BIAS SET ISHALW FLAG 1 WHEN BIAS REACHED CALL SINGLE-ENGINE PRESS 109 RESET ISHALW FLAG 0 ACLS UP USE 109 THROTTLE BIAS IF...

Tupolev Tu-123

Unlike the Tupolev Tu-121, the Tupolev Tu-123 carried four cameras for oblique and vertical (strip) cameras and ELINT equipment in its jettisonable nose section which was recovered by means of a parachute. The remaining fuselage section contained the engine, some parts of the navigation and control systems (other parts being contained in the nose section), the electric power pack and a brake parachute.

Insulator Materials

Glass-, silica-, and asbestos-reinforced phenolic or epoxy resins are one of two groups of materials commonly used for insulators the other group is the filled elastomers. Much of the preceding discussion of graphite-cloth phenolic and carbon-cloth phenolic fabrication applies to silica , glass , and asbestos phenolic as well. Reinforced plastics. In many designs the use of a separate insulator material between the liner and the structure is desirable for one or more of the following reasons...

Hybrid Rocket Cold Flow Modeling

Due to recent renewed interest in hybrid rocket motors, MSFC has participated in several hot-fire hybrid test programs. A major concern in several of these tests has been low-frequency pressure oscillations within the motor combustion chamber. The Propulsion Laboratory's Motor Systems Division, in conjunction with Auburn University's Dr. Rhonald Jenkins, submitted a Center Director's Discretionary Fund proposal to investigate such oscillations approved September 1995 . Through ongoing research...

An4 Bolt Dimensions

An4 Bolt Dimensions

FUEL TANK PRESSURE SWITCH ASSEMBLY PART NO. 10414338 The fuel tank pressure switch (B260) senses fuel tank pressure and actuates the fuel container pressurization valves (B257) at 17 0.3 psig. The pressure switch (B260) is calibrated by the pressure checkout valve (B259). 1. VENDOR - THE FREBANK COMPANY, PART NO. 4188-1 2. LOCATION - Station 887 in fuel tank No. 1. 3. SERVICE - Air, nitrogen, RP-1 vapor. 2. Differential, 2.0 psig maximum, 0. 3 psi minimum 5. TEMPERATURE - OPERATING - Minus 65 F...

Crew and Equipment Translation Aid CETA

What happens when Lockheed Martin and NASA CTSD team members engineer a solid, roughly 2,500-pound block of aluminum and transform it into a 142-pound frame assembled with more than 1,100 parts You get the Crew and Equipment Translation Aid (CETA), a complex, dynamic mechanical translation device - NASA's equivalent of a flatbed truck. The first of two CETAs will launch this fall on STS-112, station assembly flight 9A.

EVA Provisions Capabilities and Constraints

1.0 INTRODUCTION AND DEFINITIONS 1.1 Background of STS Extravehicular Activity The Space Transportation System (STS) operational era offers numerous services to payload disciplines in addition to providing payload transportation to and from orbit and supplying an orbital operations platform. One such service is the capability to conduct extravehicular activity (EVA) for both payload and Orbiter operations.

Saturn V Engines Actuators And Nozzle Arrangement

ALL SIGNAL ARROWS INDICATE POSITIVE VEHICLE MOVEMENTS. 2. VEHICLE PITCHES AROUND THE Y AXIS 3. ENGINE ACTUATOR LAYOUTS SHOWN AS VIEWED FROM AFT END OF VEHICLE. 4. DIRECTIONS AND POLARITIES SHOWN ARE TYPICAL FOR ALL STAGES. 5. + ft INDICATES ENGINE DEFLECTION REQUIRED TO CORRECT FOR POSITIVE VEHICLE MOVEMENT. F NOZZLES ON EXT ACTUATOR EXTENDED Ret ACTUATOR RETRACTED ft THRUST VECTOR ANGULAR DEFLECTION PRELAUNCH VERTICAL ALIGNMENT PENDULUMS The PEA includes the following circuitry 1. Amplifiers,...

Spacecraft Contamination From Propulsion Systems Afrpl Tr-84-068

Evolution of Omniaxial Movable Nozzle Thrust Vector Control Systems U . Paper presented at 3d ICRPG AIAA Solid Propulsion Conference Atlantic City, NJ , June 4-6, 1968, CPIA Publ. 167, vol. I, April 1968, pp. 257-293. CONFIDENTIAL 2. Anon. Solid Rocket Motor Thrust Vector Control. NASA Space Vehicle Design Criteria Monograph, NASA SP-8114, December 1974. 3. Anon. Final Test Results, First Stage MINUTEMAN Marquardt Corporation TVC Nozzle MA-103-XDA Using the...

Pu Ap Aerojet General Solid Propellent

Solid Rocket Motor Nozzles Pdf

The state of the art of solid rocket motor nozzle design is such that a successful design for a given set of requirements can, in general, be accomplished without first solving problems experimentally. Experimentation is necessary only when unusually severe requirements exceed the state of the art, when new materials must be proven, or when extremely tight flightweight margins of safety must be achieved. Figure 1 presents the two basic nozzle configurations and illustrates basic nozzle...

Adhesives Sealants And Seals

Thrust Vector Control Nozzle Rocket

Adhesives are materials applied between components to bond the components together structurally. Sealants are liquid-solid mixtures installed between components to prevent gas flow. Seals are shaped materials e.g., O-rings installed between components to prevent gas flow. In most nozzle designs, epoxy adhesive is used for both adhesive and sealant functions. Epoxy adhesives that cure at room temperature are most common however, adhesives that cure at elevated temperatures are used for some...

Specific Impulse

Specific Impulse Efficiency

The propellant specific Impulse value used In motor performance predictions shall be the specific Impulse that can be delivered by the motor. The methods provided in section 3.3.1.1 should be used to account for losses and to predict l,, f the techniques of section 3.3.1.2 should be used to confirm and verify the predicted values. In the final evaluation of the motor design, the demonstrated values for ltpa obtained as recommended in section 3.3.1.2 provide the basis for performance...

Rocket Nozzle Adhesive

Graphite Rocket Nozzle

Figure 30. - Provisions for thermal expansion of throat insert. Pyrolytic graphite. - Pyrolytic graphite is a very-high-density (2.2 gm cm3), erosion-resistant, expensive form of graphite formed by the deposition of gaseous carbon on a substrate. This layer-by-layer deposition results in a highly anisotropic material that differs greatly from polycrystalline graphite. The properties in the direction perpendicular to the layers (commonly referred to as the c direction) differ significantly from...

Liquid Injection Thrust Vector Control

Thrust Vectoring For Model Rockets

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...

Appendix B Heading Alignment Cone And Prefinal

Heading Alignment Cone

Before STS-5 the orbiter flew around a heading alignment circle. After STS-4 the reference profile was changed from a circle to an inverted cone Figure B.1-l , where the orbiter would fly a 42 bank angle. This allowed the orbiter to fly more constant bank angles during large turns and also to better manage high-energy situations. Profile options were also included to improve low-energy situations. These options included straight-in approach, radius adjust, and MEP HAC. Of the three, only the...

Equilibrium Glide Phase

The equilibrium glide phase produces an equilibrium glide trajectory consistent with the ranging solution until the trajectory intersects the constant drag ( 33 ft s2) trajectory required to reach the target. The equilibrium glide phase is terminated and the constant drag phase begins when the desired constant drag level is reached. One of the alternate terminations is for the longrange case the equilibrium glide phase transfers directly to the transition phase when the predicted velocity at...

Restartable Solid Rocket Motor

Initiator, Electrical Design and Evaluation of. Military Specification MIL-I-23659, Rev. B, Amend, no. 1, May 17, 1967. 2. Anon. Basic Evaluation Test for Use in Development of Electrically Initiated Explosive Components for Use in Fuzes. Military Standard MIL-STD-322, Oct. 15, 1962. 3. Anon. Environmental Testing Aeronautical and Associated Equipment, General Specification for. Military Specification MIL-E-5272, Rev. C, Amend, no. 1, Jan. 20, 1960. 4. Anon. Fuze and Fuze Components,...

Aiaa Solid Propellant Hercules

A. and Uecker, R. L. The Integrated Design Computer Program and the ACP-1103 Interior Ballistics Computer Program. STM-180. Aerojet-General Corp., Dec. 1964 AD 466965 . 2. Anon. Solid Propellant Rocket Motor Internal Ballistics Computer Programs. Program Manual, RK-TR-67-7, The Boeing Co., Sept. 1967 AD 822349 . 3. Anon. Grain Design and Internal Ballistics Evaluation Program IBM 7094 FORTRAN IV , Program 64101. Bacchus Works, Hercules Powder Co., July 1967 AD...

Final Report Poseidon C3 Joint Venture Joint

A Rapid Method of Evaluating Thrust Stand Dynamic Response. CPIA No. 58A, ICRPG Solid Propellant Rocket Static Test Working Group, Addendum to Bulletin of the 2nd Meeting, Sept. 1964, p. 91. 2. Anon. HIBEX Development, January 1964 September 1965 U . Dev. 6164, Hercules Powder Co., ABL Cumberland, Md. . Unpublished, pp. 11-10, 11 figure II-1A. Confidential 3. Anon. 1965 Production Support Program Final Report U . BSD TR-361, Vol. I, Hercules, Inc., June 1967, pp. 4-60....

Solid Propellant Manual Cpia

Anon, Development and Test of High Energy Solid Propellants, 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,...

Nasa Space Vehicle Design Criteria Monographs Issued To Date

SP-8001 Structures SP-8002 Structures SP-8003 Structures SP-8004 Structures SP-8005 Environment SP-8006 Structures SP-8008 Structures SP-8009 Structures SP-8010 Environment SP-8011 Environment SP-8012 Structures SP-8013 Environment Buffeting During Launch and Exit, May 1964 Flight-Loads Measurements During Launch and Exit, December 1964 Flutter, Buzz, and Divergence, July 1964 Solar Electromagnetic Radiation, June 1965 Local Steady Aerodynamic Loads During Launch and Exit, May 1965 Buckling of...

Abramson H.n. The Dynamic Behaviour Of Liquids In Moving Containers Nasa Sp-106 1966

NASA Space Vehicle Design Criteria Structures , NASA SP-8009, 1968. I. Abramson, H.N., ed. The Dynamic Behavior of Liquids in Moving Containers. NASA SP-106, 1966. 3. Bauer, H.F. Theory of the Fluid Oscillations in a Circular Cylindrical Ring Tank Partially Filled With Liquid. NASA TN D-557, 1960. Lawrence, H.R. Wang, C.J. and Reddy, R.B. Variational Solution of Fuel Sloshing Modes. Jet Propulsion, vol. 128, no. 11, Nov. 1958, pp. 729-736. 5. Moiseyev, N.N. and...

Mars Critters

In order to better understand what types of life scientists will look for when they go to Mars, you will construct a model or draw a picture of an organism that has features that might allow it to live on or near the surface of Mars. Conduct research about the environment on Mars. Consider the geology, gravity, atmosphere, radiation exposure, and weather. Choose a habitat somewhere in the Mars environment for the organism to live. Then construct a model of the plant or animal and include the...

Spin Stabilization

Spacecraft Attitude Tracking

Spin stabilization has a number of significant advantages for thrusting maneuvers, such as 1 a gyro reference package may not be needed, saving both weight and power, and 2 where the thrust is along the spin axis for a period of several spin cycles typically 10 to 200 there is an averaging of the effect of thrust misalinement. There are two major types of spin-stabilized spacecraft. One is a single rigid or quasi-rigid body spinning with respect to inertial space. The other is a multibody...

Bolt Catcher

Part of the Return to Flight effort included identifying every possible area of the Space Shuttle stack (including the Orbiter, External Tank and Solid Rocket Boosters) where potential debris sources existed. One of those identified for redesign was the bolt catcher fixed to the forward, or top, of the boosters where they attach to the External Tank. These retainers are designed to capture severed bolts when the boosters separate from the tank approximately two minutes after launch.

The Demise of the Spacecraft

After fourteen years, Galileo is out of gas and it's going out with a bang -Gay Hill, End of Mission Webcast announcer180 Galileo's final orbit took it on an elongated loop away from Jupiter, from which it returned on 21 September 2003 to plow into the parent planet's 60,000-kilometer-thick atmosphere.100 This demise was planned in order to avoid any chance that the spacecraft might strike and contaminate the moon Europa, where scientists believe that simple life-forms may exist. If such...

Extension Structure

An extension cooled by turbine exhaust gas is cooled with a fluid normally considered a hot gas thus operating temperature, thermal stress, and thermal distortion are very important aspects of the design problem. Figure 19 shows the Z sections used to attach the outer skin to the inner skin for the F-l nozzle extension. Circumferential maldistribution of the turbine gases caused local coolant starvation and produced warping of the shingles. Holes in the Z members as shown improved the...

Plug Nozzle

A method for directly optimizing truncated aerospike or plug nozzles has not been developed. The bell-nozzle optimization procedure can be applied to plug nozzles, but to obtain a solution it is necessary to assume that the base pressure is zero. The results provide an efficient expansion of the gas on the contoured wall, but low base pressure.

Mare Serenitatis

As an additional tool for the extrapolation of ground-truth data, observations were made of the relationship of the dark material in the Taurus- Littrow landing site and the dark annulus of Mare Serenitatis (fig. 28-11). The following discussion will start with the eastern border of Mare Serenitatis, followed by observations of the color stratigraphic units in the southern part of the mare. Detailed descriptions of the landing site area itself are given under a separate heading of this report.

The Lunar Herringbone Pattern

Morrisona The lunar herringbone pattern was first noted on Lunar Orbiter and Apollo 8 photographs of Copernicus secondary craters as a series of lineations forming V-shaped patterns that, when combined, give the appearance of a herringbone pattern ref. 32-22 . Later, a study of this pattern showed conclusively that its components are V-shaped ridges that typically are associated with secondary craters ref. 32-23 . Figure 32-16 shows the location of four...

Simulation Of Herringbone Pattern Components

The preceding association of the herringbone pattern with lunar secondary craters is characteristic of the pattern. This association suggests that the origin of the herringbone pattern is related to the origin of the secondary craters and that the exact mechanism of formation of the herringbone pattern may be revealed by a study of the formation of secondary craters. The most common hypothesis for formation of secondary craters is production by impact of material ejected from a primary crater....

Propellant Mass Fraction

Propellant mass fraction is a measure of motor design loading efficiency. It is usually defined as the ratio of the mass of initial propellant to the mass of the total motor, where the total motor consists of the initial propellant plus motor inert components (components that do not produce pressure and thrust). Solid-propellant motor mass fractions vary from about 0.3 to 0.96. The lower values generally apply to auxiliary motors, such as separation motors to gas generators and to very small...

Ascent Checklist Sts

Bertsch Chief, Ascent Descent Dynamics Branch This document is under the configuration control of the Crew Procedures Control Board (CPCB). All proposed changes must be submitted on FDF Workflow Crew Procedure Change Request (CR) to D03 FDF Manager. Additional distribution of this book for official use must be requested in writing to D03 FDF Manager. The request must include justification and requester's name, organization, position, and phone number. Contractor requests are made through...

Nominal Procedure

The cue card (figure 4-14) is written to use either the OMS engine on the 'good' propellant side (i.e., the side with both pods intact) or +X RCS jets. If necessary for some special reason, the other engine could be used, but this would require that procedural modifications be uplinked to the crew. Prior to the burn, a GPC read write procedure is carried out. This procedure, 'OMS SSR-1,' is found in section 11 of the 'Malfunction Procedures.' This procedure causes the proper combination of fuel...

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...

Fluid Thermodynamic Effects

Rocket Engine Turbopump Blades

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...

Space Shuttle Super Light Weight Tank SLWT

The super lightweight external tank (SLWT)made its first Shuttle flight June 2, 1998 on mission STS-91. The SLWT is 7,500 pounds lighter than the standard external tank. The lighter weight tank will allow the shuttle to deliver International Space Station elements (such as the service module) into the proper orbit. The SLWT is the same size as the previous design. But the liquid hydrogen tank and the liquid oxygen tank are made of aluminum lithium, a lighter, stronger material than the metal...

Space Station Remote Manipulator System Ssrms Overview

NO EMERGENCY OFF SWITCH, CAN REMOVE POWER FROM SYSTEM 1.21 FPS 0.36 MPS MAX 4.0 DEG S MAX 2.0 FPS 0.6 MPS MAX 4.7 DEG S MAX Manual Augmented Mode MAM, or simply Manual The primary mode of operation for the SSRMS is Manual mode. The operator at the RWS controls the motion of the SSRMS via the hand controllers. Single Joint Rate Mode SJRM, or Single As the name implies the operator moves one joint at a time. The operator selects the joint to be driven from a rotary switch on the Display and...

The S truss is lowered into its transport canister at the Kennedy Space Center

Power and data cables and the thermal control system that provides heating and cooling wind through the 44-foot by 15-foot, 27,000-pound truss segment to carry energy and information to and from the station's extremities where solar panels collect electrical energy used to power experiments, computers, life support systems and other services. Video cameras, attached to the structure, monitor assembly operations and other activities on the station. Other instruments provide the data that...

International Space Station S and P Truss Summary

The Starboard One, Port One (S1 and P1) trusses will be attached to the SO Truss aboard the International Space Station. The trusses provide structural support for the Active Thermal Control System, Mobile Transporter, CETA cart (Crew and Equipment Translation Aid), camera light operations, and S-band and UHF communications. Once in orbit, the S1 end bulkheads will be used as attachment points for the SO, P3 and S3 truss segments.

Station Modes

Example system configuration changes - Supports all nominal housekeeping, internal maintenance, and nonmicrogravity payload operations. - Entered automatically by the software from microgravity mode, or manually by the crew or ground. Serves as gateway between microgravity, reboost, proximity operations, and external operations modes. - Transition IP segments to standard mode - Power on and activate payload computer - Shutdown EVA operation support equipment - Shutdown Mobile Transporter (MT) -...

This line art highlights the S truss and Mobile Transporter additions that will be made to the International Space

Preparation Pyrotechnic Device

Atlantis' mission will be one of the most complex station assembly flights to date, including four spacewalks and operations with both the shuttle's robotic arm and the station's robotic arm. During the spacewalks, astronauts will truly take on the appearance of high-rise construction workers as they assemble beams, attach work lights, bolt girders and plug in electrical connections. The station's Canadarm2 robotic arm will be used exclusively to hoist the 13-ton truss section, called the...

Avro Ashton

The Avro 688 Tudor was a largely unsuccessful post-war British airliner, built in a number of versions, but only a handful of each of them. The second prototype Tudor I was converted as a jet research aircraft with four Nene 5 engines. Redesignated the Tudor 8, it flew as a jet on September 6 1948, beating the Comet 1 by nearly a year.

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...

Lox Loading And Delivery

As the oxidizer in the bi-propellant propulsion system, lox is contained and delivered through a separate tank and delivery system (figure 4-13). The 345,000 gallon tank is filled through two 6-inch fill and drain lines. Shortly after T-6 hours lox loading begins. Three fill rates are used sequentially a 300 gpm for tank chilldown, a 1500 gpm slow fill rate to stabilize the liquid level and thus prevent structural damage, and a fast fill rate of 10,000 gpm. At approximately 95 full, the rate is...

Kamov Ka-26 small utility flying machine

First flown in 1965, the Kamov Ka-26 is widely used as an agricultural, ambulance. fire-fighting, survey and search-and-rescue helicopter. Its adaptability is largely a result of its unusual configuration. The piston engines are mounted on short wings and this allows a variety payloads, including chemical spraying equipment, to be mounted  aft if the enclosed cabin. It is a very compact design because the contra-rotating rotors mean that a tail rotor is not required.

Kamov Ka-226T hard-to-reach mountainous areas helicopter

The Kamov Ka-226T is light multipurpose helicopter with the maximum take-off weight of 4,000 tons. The Ka-226T is intended for performing special tasks including cargo transportation (up to 1,630 kg), and passenger/service personnel transportation to hard-to-reach mountainous areas, under conditions of hot climate and over the offshore water. The helicopter is powered with two ARRIUS 2G1 turbo-shaft engines.

Ka-126 helicopter designed by Sergei Mikheyev

The Kamov Ka-126 is Russian light utility helicopter with co-axial rotors, and it was designed by general Kamov helicopter designer Sergei Mikheyev. The co-axial twin-rotor helicopter Ka-126 have a 2.5t gross weight and a it useful load. An improved removable cabin section enable the Soviet helicopter to seat 6 passenger. It is supposed to use the detachable mission-specific payload module with the commonised set of electro-optical, infrared and radio-frequency wavebands, relay hear or cargo...

Kamov Ka-226 Sergei unique maneuverability helicopter

The Kamov Ka-226 is light multipurpose helicopter with the maximum take-off weight of 3,400 tons and it is intended for passenger transportation (up to 7 persons), cargo transportation (up to 1,300 kg), economic zones patrolling, monitoring missions and other special tasks. The helicopter is powered with two Rolls-Royce turbo-shaft engines.

Ka-50-2 Erdogan helicopter for Turkish Air Force

The Kamov Ka-50-2 Erdogan is a single-seat small attack helicopter with coaxial rotor, developed in cooperation with Kamov and IAI for Turkish Air Force.  It was developed from Ka-50 Black Shark/Werewolf. Primary duty is to detect and destroy land-targets. It should be in service with Turkish Air Force, but contract is canceled.

Technical Reports

Advanced Studies Program, Advanced Systems Office, MSEC, Huntsville, Alabama, October 1966. ATUM Study Program, Final Report, Ball Brothers Research Corporation, April 1, 1966. D5-13183, Final Report Studies of Improved Saturn V Vehicles and Intermediate Payload Vehicles (P-115) Summary, Boeing Company, October 7, 1966. FR-MTS-01, Final Report, Pegasus Program, 1965, Fairchild Hiller Space Systems Division, October 1965. IBM 66-966-0016, Saturn IU Program Plan, IBM Space Systems Center,...

Smallscale Analogs Of The Cayley Formation And Descartes Mountains In Impactassociated Deposits

Cayley Formations

Heada Introduction The exploration of the Cayley Formation and material of the Descartes Mountains and an understanding of the origin and evolution of these units were primary objectives of the Apollo 16 lunar mission. The purpose of this subsection is to examine several areas associated with impact crater deposits that show small-scale features similar in morphology to the regional characteristics of the Cayley and Descartes units shown in the Apollo 16 photography.

Cayley Formation Interpreted As Basin Ejecta

The discovery that samples returned from the Cayley Formation at the Apollo 16 landing site consist mainly of nonvolcanic breccias sees. 6 and 7 of this report suggests that the hypothesis in which light plains-forming materials may be ejecta from multi-ring basins should be reevaluated refs. 29-15 to 29-17 . Improved information on the morphology and distribution of the Cayley Formation, provided by Apollo 16 orbital photography, leads to a concept in which the Cayley Formation was deposited...

Student Procedure Activity B

Materials ruler protractor pencil colored pencils Path and Speed of a Meteor Using the map provided, you will be led through the procedures of triangulating the path and explosion of a meteor and determining a likely area to look for meteorites. Review the use of a protractor if necessary. Section 1. The attached map shows the location of two people when they saw the meteor. The observer in Drygulch Flats was looking 80 East of North when she saw the meteor explode.