Comparison of Return to Launch Site Options for a Reusable
... RTLS branch. The optimal staging point for glideback was at a velocity of about 3937 ft/sec at and altitude of about 16.2 nmi, while flyback staged at about 10,498 ft/sec at an altitude of about 34.5 nmi. This study did not fix a payload but fixed a gross weight at liftoff. So mass differences betwe ...
... RTLS branch. The optimal staging point for glideback was at a velocity of about 3937 ft/sec at and altitude of about 16.2 nmi, while flyback staged at about 10,498 ft/sec at an altitude of about 34.5 nmi. This study did not fix a payload but fixed a gross weight at liftoff. So mass differences betwe ...
microEFIS BACKUP ELECTRONIC ATTITUDE REFERENCE SYSTEM
... sensor module (the IMU) and a software package for use with handheld computers, such as the Compaq iPaq 3600/3700,3800 series (typically called Personal Data Assistants – or PDA’s). The ICARUS INSTRUMENTS IMU uses electronic piezoelectric gyroscopes. These are solid state devices, which use a quartz ...
... sensor module (the IMU) and a software package for use with handheld computers, such as the Compaq iPaq 3600/3700,3800 series (typically called Personal Data Assistants – or PDA’s). The ICARUS INSTRUMENTS IMU uses electronic piezoelectric gyroscopes. These are solid state devices, which use a quartz ...
User`s guide
... around the roll, pitch and yaw axis and also sense the aircraft orientation relative to the earth. Three gyroscopes are required to accurately determine aircraft attitude in a strap-down INS. This is required because the aircraft attitude determination requires yaw angular sensing whenever the aircr ...
... around the roll, pitch and yaw axis and also sense the aircraft orientation relative to the earth. Three gyroscopes are required to accurately determine aircraft attitude in a strap-down INS. This is required because the aircraft attitude determination requires yaw angular sensing whenever the aircr ...
NASA`s Space Network Ground Segment Sustainment
... NASA’s Tracking and Data Relay Satellite System (TDRSS) ground terminals will be replaced in the 2015 timeframe. The existing terminals have been subject to many small scale upgrades and modifications since their last major refurbishment in 1994. The ground terminals, in conjunction with seven opera ...
... NASA’s Tracking and Data Relay Satellite System (TDRSS) ground terminals will be replaced in the 2015 timeframe. The existing terminals have been subject to many small scale upgrades and modifications since their last major refurbishment in 1994. The ground terminals, in conjunction with seven opera ...
voyager mission description
... (g) occultation of the Earth by all of Saturn's rings. At Jupiter, it is not possible to provide all of these characteristics with a single flyby. Therefore, the trajectories for each Voyager have been designed to be complementary. For example, an Io flux tube passage is planned for the first-arrivi ...
... (g) occultation of the Earth by all of Saturn's rings. At Jupiter, it is not possible to provide all of these characteristics with a single flyby. Therefore, the trajectories for each Voyager have been designed to be complementary. For example, an Io flux tube passage is planned for the first-arrivi ...
X-33 - blackboard TU Delft
... made out of graphite epoxy composites instead of traditional aluminium is to be the riskiest element (4) ...
... made out of graphite epoxy composites instead of traditional aluminium is to be the riskiest element (4) ...
Station-Keeping Performance of a Large High-Altitude
... Why Are We Interested in It? Is it Feasible? ...
... Why Are We Interested in It? Is it Feasible? ...
toolmaker`s microscope
... (i) Sub-stage lamp provides transmitted light from a bottom source providing collimated green filter Halogen light. (ii) Oblique illuminator with adjustable inclination for surface illumination of sample with relief structure, is also provided. Three separate knobs for different illumination is prov ...
... (i) Sub-stage lamp provides transmitted light from a bottom source providing collimated green filter Halogen light. (ii) Oblique illuminator with adjustable inclination for surface illumination of sample with relief structure, is also provided. Three separate knobs for different illumination is prov ...
06D, 06E Guide Specifications, 3 to 15 tons (06D), 20 to 40 tons (06E)
... on/off switch, and unit designed to start with controlled cylinders unloaded. Factory assembled control box to be tested and mounted on structural base. 2. Safeties in the control box include high- and low-pressure switches, timer to prevent compressor short cycling, overload relays or circuit break ...
... on/off switch, and unit designed to start with controlled cylinders unloaded. Factory assembled control box to be tested and mounted on structural base. 2. Safeties in the control box include high- and low-pressure switches, timer to prevent compressor short cycling, overload relays or circuit break ...
06D, 06E Guide Specifications, 3 to 15 tons (06D), 20 to 40 tons (06E)
... on/off switch, and unit designed to start with controlled cylinders unloaded. Factory assembled control box to be tested and mounted on structural base. 2. Safeties in the control box include high- and low-pressure switches, timer to prevent compressor short cycling, overload relays or circuit break ...
... on/off switch, and unit designed to start with controlled cylinders unloaded. Factory assembled control box to be tested and mounted on structural base. 2. Safeties in the control box include high- and low-pressure switches, timer to prevent compressor short cycling, overload relays or circuit break ...
Reentry Vehicles and Orbital Mechanics Subcommittee
... reducing the very high speed required for space flight. Trajectory and attitude Source: NASA ...
... reducing the very high speed required for space flight. Trajectory and attitude Source: NASA ...
Telemetry and Telecommand (TMTC)
... Computing units have undergone TID ( > 30 Krads) and SEE test. SEU protection is implemented at board level. The RF front-end is based on low power, low cost integrated circuit. It provides transmission capability including ReedSolomon channel coding, modulation and frequency up-conversion and telec ...
... Computing units have undergone TID ( > 30 Krads) and SEE test. SEU protection is implemented at board level. The RF front-end is based on low power, low cost integrated circuit. It provides transmission capability including ReedSolomon channel coding, modulation and frequency up-conversion and telec ...
Saturn V Instrument Unit
The Saturn V Instrument Unit is a ring-shaped structure fitted to the top of the Saturn V rocket's third stage (S-IVB) and the Saturn IB's second stage (also an S-IVB). It was immediately below the SLA (Spacecraft/Lunar Module Adapter) panels that contained the Lunar Module. The Instrument Unit contains the guidance system for the Saturn V rocket. Some of the electronics contained within the Instrument Unit are a digital computer, analog flight control computer, emergency detection system, inertial guidance platform, control accelerometers and control rate gyros. The instrument unit (IU) for Saturn V was designed by NASA at Marshall Space Flight Center (MSFC) and was developed from the Saturn I IU. NASA's contractor to construct the Saturn V Instrument Unit was International Business Machines (IBM).One of the unused Instrument Units is currently on display at the Steven F. Udvar-Hazy Center in Chantilly, Virginia. The plaque for the Unit has the following inscription:The Saturn V rocket, which sent astronauts to the Moon, used inertial guidance, a self-contained system that guided the rocket's trajectory. The rocket booster had a guidance system separate from those on the command and lunar modules. It was contained in an instrument unit like this one, a ring located between the rocket's third stage and the command and lunar modules. The ring contained the basic guidance system components—a stable platform, accelerometers, a digital computer, and control electronics—as well as radar, telemetry, and other units.The instrument unit's stable platform was based on an experimental unit for the German V-2 rocket of World War II. The Bendix Corporation produced the platform, while IBM designed and built the unit's digital computer.