Lunar Reconnaissance Orbiter Project Technical Resource
... 2.3.2.1.1 Mass The mission traded different designs regarding a transfer to lunar orbit. The project examined various direct lunar insertion trajectories and phasing loops. The project also traded monopropellant verses bi-propellant verses hybrid propellant systems. Given a Level 1 requirement of us ...
... 2.3.2.1.1 Mass The mission traded different designs regarding a transfer to lunar orbit. The project examined various direct lunar insertion trajectories and phasing loops. The project also traded monopropellant verses bi-propellant verses hybrid propellant systems. Given a Level 1 requirement of us ...
Validating a Novel Theoretical Expression for Burn time and
... reduced, a decrease in thrust is desirable; this often reduces the drag losses, and usually permits a more effective flight path. Therefore, there is a benefit to vehicle mass, flight performance, and cost in having a higher initial thrust during the boost phase of the flight, followed by a lower th ...
... reduced, a decrease in thrust is desirable; this often reduces the drag losses, and usually permits a more effective flight path. Therefore, there is a benefit to vehicle mass, flight performance, and cost in having a higher initial thrust during the boost phase of the flight, followed by a lower th ...
also available online
... For simplicity, this review will assume circular orbits. Tethers can be in an ellipse; those are just more complicated to discuss. The two connected objects will move at the orbital velocity of their center of mass. If they have unequal masses, the lighter end will be farther from that center of mas ...
... For simplicity, this review will assume circular orbits. Tethers can be in an ellipse; those are just more complicated to discuss. The two connected objects will move at the orbital velocity of their center of mass. If they have unequal masses, the lighter end will be farther from that center of mas ...
III. Single Objective Optimization
... NTEREST in unmanned vehicles (UV) has increased significantly in the last several years for both military and civilian applications. Due to the increase in levels of automation used, there is a shift in UV research away from manually controlling vehicles to managing vehicles at the supervisory contr ...
... NTEREST in unmanned vehicles (UV) has increased significantly in the last several years for both military and civilian applications. Due to the increase in levels of automation used, there is a shift in UV research away from manually controlling vehicles to managing vehicles at the supervisory contr ...
Orbital Maneuvering Vehicle Support To The Space Station
... SS/OMV Proximity Operations will include transport of more powerful upper stages such as an Orbital Transfer Vehicle and payload to a safe distance from the Station, circumnaviga tion of the station with frequent stops for observations and other activities. SS proxi mity operations are typically p ...
... SS/OMV Proximity Operations will include transport of more powerful upper stages such as an Orbital Transfer Vehicle and payload to a safe distance from the Station, circumnaviga tion of the station with frequent stops for observations and other activities. SS proxi mity operations are typically p ...
Electric Propulsion
... Liquid fuels are not confined to any specific region within the tank in low or micro gravity but there are several ways to allow for positive fuel feed during low gravity conditions Capillary devices - use surface tension to keep gas and liquid separated in the tank (requires pressurization). Used ...
... Liquid fuels are not confined to any specific region within the tank in low or micro gravity but there are several ways to allow for positive fuel feed during low gravity conditions Capillary devices - use surface tension to keep gas and liquid separated in the tank (requires pressurization). Used ...
Document
... to the speed to which the propellant can be accelerated • Energy available on board is the only practical limitation ...
... to the speed to which the propellant can be accelerated • Energy available on board is the only practical limitation ...
Comparison of Return to Launch Site Options for a Reusable
... spaceflight as shown above, there were many ideas to implement the simplicity of gliding back to the launch site after releasing an upper stage(s). One example of fully reusable TSTO concept conceived at NASA Langley was the Future Space Transportation System to replace the Space Shuttle6,7,8. This ...
... spaceflight as shown above, there were many ideas to implement the simplicity of gliding back to the launch site after releasing an upper stage(s). One example of fully reusable TSTO concept conceived at NASA Langley was the Future Space Transportation System to replace the Space Shuttle6,7,8. This ...
Introduction to Electric Propulsion
... permanent magnets used for space power generation with Stirling linear alternators and for ion propulsion thrusters. The magnets have been successfully demonstrated in NASA’s Deep Space 1 Ion Engine, launched in 1998. Potential commercial uses of the technology include sensors, instrumentation, gene ...
... permanent magnets used for space power generation with Stirling linear alternators and for ion propulsion thrusters. The magnets have been successfully demonstrated in NASA’s Deep Space 1 Ion Engine, launched in 1998. Potential commercial uses of the technology include sensors, instrumentation, gene ...
PPTX - Florida Institute of Technology
... After Apollo-era we finally witness a renewed interest in a human space exploration program to the Moon and Mars. SPACE Exploration – where are we? Launch system technology still relies on powerful chemical rockets while interplanetary missions use fly-by, electrical engines in addition to chemical ...
... After Apollo-era we finally witness a renewed interest in a human space exploration program to the Moon and Mars. SPACE Exploration – where are we? Launch system technology still relies on powerful chemical rockets while interplanetary missions use fly-by, electrical engines in addition to chemical ...
CDIO S S P D
... Although the end goal is a launched cluster of satellites, it is necessary from an economical standpoint to test new technology close to home and with low risk. Therefore, the CDIO-3 class will effectively fulfill these customer requirements while maintaining the following standards: 2.1. Reducing f ...
... Although the end goal is a launched cluster of satellites, it is necessary from an economical standpoint to test new technology close to home and with low risk. Therefore, the CDIO-3 class will effectively fulfill these customer requirements while maintaining the following standards: 2.1. Reducing f ...
Model Rocket Workshop
... nose fairing separating the two parts of the rocket and allowing the nose fairing to go higher thanks to the loss of mass. As we can see, there are some differences between the simulations. We have two different apogees, the first one it’s about 110 meters, and the second it’s about 157 meters. So, ...
... nose fairing separating the two parts of the rocket and allowing the nose fairing to go higher thanks to the loss of mass. As we can see, there are some differences between the simulations. We have two different apogees, the first one it’s about 110 meters, and the second it’s about 157 meters. So, ...
2015-02-19-Chapter-8 - Help-A-Bull
... • The sum of all of the forces, internal and external is equal to the mass times acceleration. • By Newton’s third law, for each internal force, there is an equal but opposite reaction force, so the internal forces cancel out. ...
... • The sum of all of the forces, internal and external is equal to the mass times acceleration. • By Newton’s third law, for each internal force, there is an equal but opposite reaction force, so the internal forces cancel out. ...
HSC Physics – Core Module 1 – Space
... The Rocket is subject to the following forces: - Its weight force directed downwards - Its thrust directed upwards - The reaction force of the ground on the rocket (equal to the difference between the weight and the thrust while the rocket is still on the ground) directed upward. - Air resistance di ...
... The Rocket is subject to the following forces: - Its weight force directed downwards - Its thrust directed upwards - The reaction force of the ground on the rocket (equal to the difference between the weight and the thrust while the rocket is still on the ground) directed upward. - Air resistance di ...
Micro-Level Coherence
... You’ll also notice that the key term isn’t always repeated in its original form. Sometimes, a synonym is used to identify the term. In the paragraph above, people, public, and taxpayer are all used interchangeably. In the paragraph below, Jules Verne, satellite, and spacecraft are all used interchan ...
... You’ll also notice that the key term isn’t always repeated in its original form. Sometimes, a synonym is used to identify the term. In the paragraph above, people, public, and taxpayer are all used interchangeably. In the paragraph below, Jules Verne, satellite, and spacecraft are all used interchan ...
Presentation - Harlem Children Society
... extremely viscous. • In order to improve the performance of the hybrid rocket, the alcohol gel must contain both a concentrated alcohol and a thickener. The thickener will be methyl cellulose. • The concentrated alcohol will be obtained from a substance called Everclear, which contains 95% alcohol. ...
... extremely viscous. • In order to improve the performance of the hybrid rocket, the alcohol gel must contain both a concentrated alcohol and a thickener. The thickener will be methyl cellulose. • The concentrated alcohol will be obtained from a substance called Everclear, which contains 95% alcohol. ...
The Aerodynamic Forces code grew steadily over the course of the
... Fig. A.1.2.3.5.1, XCP vs angle of attack for a 3 stage vehicle at Mach 3 (Alex Woods) Figure A.1.2.3.5.1 shows that the center of pressure will move aft along the rocket body as angle of attack changes, which is what we expect for a launch vehicle.3 We have some issues with the validity of the resul ...
... Fig. A.1.2.3.5.1, XCP vs angle of attack for a 3 stage vehicle at Mach 3 (Alex Woods) Figure A.1.2.3.5.1 shows that the center of pressure will move aft along the rocket body as angle of attack changes, which is what we expect for a launch vehicle.3 We have some issues with the validity of the resul ...
chapter 8
... the right proportions at the right times poses a significant engineering challenge. Another example of a liquid bipropellant system is the Space Shuttle main engine: it uses liquid hydrogen (LH2) as the fuel and liquid oxygen (LOX) as the oxidizer. The exhaust gas is water vapor. There are over a hu ...
... the right proportions at the right times poses a significant engineering challenge. Another example of a liquid bipropellant system is the Space Shuttle main engine: it uses liquid hydrogen (LH2) as the fuel and liquid oxygen (LOX) as the oxidizer. The exhaust gas is water vapor. There are over a hu ...
Lecture2
... The first couple of minutes after a space shuttle launch can be described as follows: The initial mass is 2x10E6 kg, the final mass (after 2 minutes) is about 1x10E6 kg, the average exhaust speed is about 3000 m/s. If all this were taking place in outer space, with negligible gravity, what would be ...
... The first couple of minutes after a space shuttle launch can be described as follows: The initial mass is 2x10E6 kg, the final mass (after 2 minutes) is about 1x10E6 kg, the average exhaust speed is about 3000 m/s. If all this were taking place in outer space, with negligible gravity, what would be ...
STEM Lesson #LD02 The Model Rocket
... • Shock Cord Attachment – a metal eye for the secure attachment of the shock cord. ...
... • Shock Cord Attachment – a metal eye for the secure attachment of the shock cord. ...
AP Rocket Propulsion
... 1. A rocket moving in free space has a speed of 3x103m/s relative to Earth. Its engines are turned on, and fuel is ejected at a speed of 5x103m/s relative to the rocket a) What is the speed of the rocket relative to Earth once its mass is reduced to one half its mass before ignition? ...
... 1. A rocket moving in free space has a speed of 3x103m/s relative to Earth. Its engines are turned on, and fuel is ejected at a speed of 5x103m/s relative to the rocket a) What is the speed of the rocket relative to Earth once its mass is reduced to one half its mass before ignition? ...
Propulsion systems
... Launch Need lift-off acceleration, a, to be greater than gravitational acceleration, g. (“a>g”) for ...
... Launch Need lift-off acceleration, a, to be greater than gravitational acceleration, g. (“a>g”) for ...
Design and Development of a CubeSat De
... Demonstrate commercial viability Prove it is a robust and viable system Achieve these objectives with a minimum cost ◦ Orbital demonstrator ◦ Suborbital flight ◦ High altitude balloon flight ...
... Demonstrate commercial viability Prove it is a robust and viable system Achieve these objectives with a minimum cost ◦ Orbital demonstrator ◦ Suborbital flight ◦ High altitude balloon flight ...
H2Go: The Untapped Power Source ASME Student Design
... Insert Picture of Device As the bucket falls, the Kevlar line unwinds on the vehicle generating a rotating motion The bucket falls and contacts the release mechanism rolling the vehicle forward The vehicle touches the ground and rolls down the course ...
... Insert Picture of Device As the bucket falls, the Kevlar line unwinds on the vehicle generating a rotating motion The bucket falls and contacts the release mechanism rolling the vehicle forward The vehicle touches the ground and rolls down the course ...
Reusable launch system
A reusable launch system (or reusable launch vehicle, RLV) is a launch system which is capable of launching a launch vehicle into space more than once. This contrasts with expendable launch systems, where each launch vehicle is launched once and then discarded.No true orbital reusable launch system is currently in use. The closest example was the partially reusable Space Shuttle. The orbiter, which included the Space Shuttle main engines, and the two solid rocket boosters, were reused after several months of refitting work for each launch. The external tank and launch vehicle load frame were discarded after each flight.Orbital RLVs are thought to provide the possibility of low cost and highly reliable access to space. However, reusability implies weight penalties such as non-ablative reentry shielding and possibly a stronger structure to survive multiple uses, and given the lack of experience with these vehicles, the actual costs and reliability are yet to be seen.