HCC Reels for Combines and Swathers
... HCC Reels effectively divide, lift, and feed standing or down crops, including soybeans, canola, wheat, lentils, irrigated crops, rice, and milo. The design of HCC Reels uses fewer parts, leading to a 35-40% improvement in visibility, giving the operator a clearer view of the cutter bar and crop fee ...
... HCC Reels effectively divide, lift, and feed standing or down crops, including soybeans, canola, wheat, lentils, irrigated crops, rice, and milo. The design of HCC Reels uses fewer parts, leading to a 35-40% improvement in visibility, giving the operator a clearer view of the cutter bar and crop fee ...
Lunar Reconnaissance Orbiter Project Technical Resource
... Given a Level 1 requirement of using an intermediate class launch vehicle, the best solution was for a mono-propellant system on a direct lunar insertion trajectory. Further analysis has yielded a maximum throw mass for the launch vehicle of 1480 kilograms (kgs). This throw mass set the initial mass ...
... Given a Level 1 requirement of using an intermediate class launch vehicle, the best solution was for a mono-propellant system on a direct lunar insertion trajectory. Further analysis has yielded a maximum throw mass for the launch vehicle of 1480 kilograms (kgs). This throw mass set the initial mass ...
Attitude and Orbit Control for small satellites
... propulsion instruments must be as simple as possible; while to keep precision up, they must be as advanced as possible. But components are not the most expensive part in a satellite. The design, test, veri cation and launch procedures are far more expensive, since the rst three take many man-hours ...
... propulsion instruments must be as simple as possible; while to keep precision up, they must be as advanced as possible. But components are not the most expensive part in a satellite. The design, test, veri cation and launch procedures are far more expensive, since the rst three take many man-hours ...
Experimental Study of the Machian Mass Fluctuation Effect
... produced by In-FEEP (Indium Field Emission Electric Propulsion) thrusters, designed and manufactured at ARC Seibersdorf research. The force produced by single thrusters of this sort falls in the micronewton range, reaching millinewtons for clustered systems. The balance consists of a symmetric arm ( ...
... produced by In-FEEP (Indium Field Emission Electric Propulsion) thrusters, designed and manufactured at ARC Seibersdorf research. The force produced by single thrusters of this sort falls in the micronewton range, reaching millinewtons for clustered systems. The balance consists of a symmetric arm ( ...
Orbital Maneuvering Vehicle Support To The Space Station
... portation System. Various types of missions, operating modes, and performance capabili ties for the OMV are described as are typical mission scenarios, with the OMV based at the Shuttle and at the Space Station (SS). Particular emphasis is placed on OMV mis sions in support of the SS. Retrieval of ...
... portation System. Various types of missions, operating modes, and performance capabili ties for the OMV are described as are typical mission scenarios, with the OMV based at the Shuttle and at the Space Station (SS). Particular emphasis is placed on OMV mis sions in support of the SS. Retrieval of ...
Comparison of Return to Launch Site Options for a Reusable
... similar to a conventional airplane. The major deterrent to developing a RLV has been the large upfront development cost without the launch frequency necessary to justify that cost. The only partially reusable vehicle developed is the Space Shuttle which has shown to have large operation expenses and ...
... similar to a conventional airplane. The major deterrent to developing a RLV has been the large upfront development cost without the launch frequency necessary to justify that cost. The only partially reusable vehicle developed is the Space Shuttle which has shown to have large operation expenses and ...
Solid propellant thruster for space application
... Propulsion module Mass :1.28g 1 shot every 1.21 day ...
... Propulsion module Mass :1.28g 1 shot every 1.21 day ...
Station-Keeping Performance of a Large High-Altitude
... Example SpaceBased Solution to Wide-Area Surveillance ...
... Example SpaceBased Solution to Wide-Area Surveillance ...
ASTR 380 The Challenge of Interstellar Travel
... When we take into account that the fuel itself needs to be accelerated, we find that the final speed is really vfinal=vejecta ln[M(fuel)/M(craft)] Need huge fuel mass to get to high speeds if vejecta is low! Minimum fuel to payload ratio to achieve 0.1 speed of light Speed of ejecta (km/sec) ...
... When we take into account that the fuel itself needs to be accelerated, we find that the final speed is really vfinal=vejecta ln[M(fuel)/M(craft)] Need huge fuel mass to get to high speeds if vejecta is low! Minimum fuel to payload ratio to achieve 0.1 speed of light Speed of ejecta (km/sec) ...
also available online
... orbital velocity of their center of mass. If they have unequal masses, the lighter end will be farther from that center of mass than the heavy end. The distance from the center of mass determines the energy that can be given to either object by a toss. If the wire is cut, or released, the two masses ...
... orbital velocity of their center of mass. If they have unequal masses, the lighter end will be farther from that center of mass than the heavy end. The distance from the center of mass determines the energy that can be given to either object by a toss. If the wire is cut, or released, the two masses ...
Model Rocket Workshop
... could have altered the rocket trajectory. Although we must say that we were not able to find the thrust tolerance in the datasheet, previous experiences of other people around the world using these engines seem to indicate that this hypothesis is plausible. Finally, although the launch day was not m ...
... could have altered the rocket trajectory. Although we must say that we were not able to find the thrust tolerance in the datasheet, previous experiences of other people around the world using these engines seem to indicate that this hypothesis is plausible. Finally, although the launch day was not m ...
Document
... Advanced (Electric) Propulsion The Concept: • Definition - Electric propulsion: A way to accelerate a propellant through electro(magnetic) fields • There is no intrinsic limitation (other than the relativistic one) to the speed to which the propellant can be accelerated • Energy available on board ...
... Advanced (Electric) Propulsion The Concept: • Definition - Electric propulsion: A way to accelerate a propellant through electro(magnetic) fields • There is no intrinsic limitation (other than the relativistic one) to the speed to which the propellant can be accelerated • Energy available on board ...
Satellite Communication
... – Processes (and stores) data from payload (telescope instruments, Earth resource sensors, etc.) – Routes data to users – Prepares commands for uplink to payload ...
... – Processes (and stores) data from payload (telescope instruments, Earth resource sensors, etc.) – Routes data to users – Prepares commands for uplink to payload ...
f2f 140731
... Test of the bottom filter prototype Function: final vertical filter Dimension: f730 x 272h Weight: 99kg Blades: Marasing steel x3 Load: 48.6kg Aimed frequency: 0.4Hz One vertical position sensor: LVDT One vertical actuator: voice coil Attitude control: two motors for pitch, one motor for yaw ...
... Test of the bottom filter prototype Function: final vertical filter Dimension: f730 x 272h Weight: 99kg Blades: Marasing steel x3 Load: 48.6kg Aimed frequency: 0.4Hz One vertical position sensor: LVDT One vertical actuator: voice coil Attitude control: two motors for pitch, one motor for yaw ...
CDIO S S P D
... on sensitive optics, induce inadvertent charging, and actually ablate material off the spacecraft thereby causing permanent damage. Third, for missions such as NASA’s Terrestrial Planet Finder (TPF), the propellant plume can put a thermally bright haze across the line-of-sight of the telescope. For ...
... on sensitive optics, induce inadvertent charging, and actually ablate material off the spacecraft thereby causing permanent damage. Third, for missions such as NASA’s Terrestrial Planet Finder (TPF), the propellant plume can put a thermally bright haze across the line-of-sight of the telescope. For ...
Electric Propulsion
... ΔVideal performance = Isp g ln[mi/(mi - mp)] is the basic relationship between ΔV (performance) and Isp for a single stage propulsion system. This is not the same as the ΔV required to attain proper orbit, or for orbit changes. This equation allows us to calculate the initial-to-final mass ratio for ...
... ΔVideal performance = Isp g ln[mi/(mi - mp)] is the basic relationship between ΔV (performance) and Isp for a single stage propulsion system. This is not the same as the ΔV required to attain proper orbit, or for orbit changes. This equation allows us to calculate the initial-to-final mass ratio for ...
Single-stage-to-orbit
A single-stage-to-orbit (or SSTO) vehicle reaches orbit from the surface of a body without jettisoning hardware, expending only propellants and fluids. The term usually, but not exclusively, refers to reusable vehicles. No Earth-launched SSTO launch vehicles have ever been constructed. To date, orbital launches have been performed either by multi-stage fully or partially expendable rockets, or by the Space Shuttle, which was multi-stage and partially reusable.Launch costs for low Earth orbit (LEO) range from $4500 to $8500 per pound of payload ($10,000–$19,000 / kg). Reusable SSTO vehicles offer the promise of reduced launch expenses by eliminating recurring costs associated with hardware replacement inherent in expendable launch systems. However, the nonrecurring costs associated with design, development, research and engineering (DDR&E) of reusable SSTO systems are much higher than expendable systems due to the substantial technical challenges of SSTO.It is considered to be marginally possible to launch a single stage to orbit spacecraft from Earth. The principal complicating factors for SSTO from Earth are: high orbital velocity of over 7,400 metres per second (27,000 km/h; 17,000 mph); the need to overcome Earth's gravity, especially in the early stages of flight; and flight within Earth's atmosphere, which limits speed in the early stages of flight and influences engine performance. The marginality of SSTO can be seen in the launch of the space shuttle. The orbiter and main tank combination successfully orbits after booster separation from an altitude of 45 kilometres (28 mi) and a speed of 4,828 kilometres per hour (1,341 m/s; 3,000 mph). This is approximately 12% of the gravitational potential energy and just 3% of the kinetic energy needed for orbital velocity (4% of total energy required).Notable single stage to orbit research spacecraft include Skylon, the DC-X, the Lockheed Martin X-33, and the Roton SSTO. However, despite showing some promise, none of them has come close to achieving orbit yet due to problems with finding the most efficient propulsion system.Single-stage-to-orbit has been achieved from the Moon by both the Apollo program's Lunar Module and several robotic spacecraft of the Soviet Luna program; the lower lunar gravity and absence of any significant atmosphere makes this much easier than from Earth.