This document proposes using an entomopter, a flying vehicle that generates lift like an insect using flapping wings, for exploration of Mars. An entomopter could expand exploration beyond rovers by enabling aerial reconnaissance, sampling, and imaging across a greater range than current surface vehicles. The low atmospheric density and gravity of Mars may make it an ideal environment for entomopter flight. The document outlines potential mission profiles using entomopters deployed from landers or rovers to conduct science objectives like surface imaging, atmospheric sampling, and payload delivery. Development of entomopters is ongoing through various university and private programs for terrestrial applications.
The document proposes developing a miniature low-cost launch system called Microlaunchers to help advance space access technology. It would use a three-stage launch vehicle with each stage powered by staged combustion engines. The first stage would be recoverable via gliding to enable frequent low-cost launches. Future goals include developing small payloads to flyby asteroids and land on Near Earth Objects to gain navigational experience and advance capabilities. Developing the system incrementally and through partnerships is suggested.
This document provides an overview of the history and concepts of spaceplanes. It discusses early spaceplane designs from the 1930s and 1940s and traces the development of spaceplanes through programs like NASA's space shuttle. It describes the key characteristics of spaceplanes and the different types of spaceplane operations, including sub-orbital and single-stage to orbit. Major current and historic spaceplane designs and programs are outlined, including concepts from NASA, Airbus, Bristol Spaceplanes, Orbital Sciences, Reaction Engines, Virgin Galactic, and others. The advantages of reusable spaceplanes over expendable rockets are also summarized.
The document proposes a concept for a global constellation of stratospheric scientific platforms using balloons or "StratoSats" to provide low-cost, continuous, and simultaneous global Earth observations. A constellation of tens to hundreds of small, long-duration stratospheric balloons at altitudes of 30-35 km could carry instrument payloads for applications like climate change monitoring, ozone studies, and weather forecasting. Maintaining the positions of the balloons in a uniform global distribution would require trajectory control systems and algorithms to navigate the balloons according to wind patterns and forecasts.
Satellites orbit objects like planets to perform various missions. They have orbits that are either geostationary, asynchronous, or polar. Rockets are used to launch satellites into orbit and have multiple stages powered by liquid or solid propellant engines. The first stage provides maximum thrust at launch while subsequent stages have lower thrust and place the satellite into its proper transfer orbit using liquid or cryogenic engines before the final apogee kick motor releases it onto its mission orbit. Precise propulsion, communication, electrical power, and computer systems are required for successful satellite launch and operation in space.
This document discusses satellite orbits, including:
1) Most satellites orbit Earth in elliptical or circular patterns, either in the same direction as Earth's rotation (prograde) or the opposite direction (retrograde).
2) Satellites are classified based on their orbit - low earth orbit (LEO), medium earth orbit (MEO), or geosynchronous earth orbit (GEO). GEO satellites orbit at 22,300 miles above Earth.
3) Geosynchronous satellites appear stationary from Earth as they orbit at the same rate that Earth rotates, completing one revolution every 24 hours. They provide coverage to about 40% of Earth's surface.
Satellites
Introduction to Satellite Systems
o A satellite is an artificial object which is placed intentionally into an orbit of any natural satellite. Satellites are used for many purposes i.e. weather forecasting, digital transmission, scientific research and development etc.
o In a communication context, a satellite is a specialized wireless transmitter/receiver that is launched by a rocket and placed in orbit around the earth.
o A satellite can be natural, like the moon, or artificial (human made). So we can say that a satellite is an object that moves in a curved path around a planet.
o Satellite can travel around planets or around stars such as our sun. All the planets are satellites around the sun.
o Satellites which are far away from the surface of the earth can cover a wide area on the surface of the earth.
Following are the four important types of Earth Orbit satellites −
• Geosynchronous Earth Orbit Satellites
• Medium Earth Orbit Satellites
• Low Earth Orbit Satellites
• Highest Earth Orbit Satelites
Now, let us discuss about each type of earth orbit satellites one by one.
This document provides an overview of orbiters as part of a seminar on hypersonic technology demonstration vehicles. It defines what an orbit is and discusses different types of orbits including low Earth orbit, medium Earth orbit, and high Earth orbit. It then describes what a spacecraft is, including its anatomy and different types. Finally, it focuses specifically on orbiter spacecraft, explaining their design considerations for entering orbit around distant planets and conducting in-depth studies.
The document proposes developing a miniature low-cost launch system called Microlaunchers to help advance space access technology. It would use a three-stage launch vehicle with each stage powered by staged combustion engines. The first stage would be recoverable via gliding to enable frequent low-cost launches. Future goals include developing small payloads to flyby asteroids and land on Near Earth Objects to gain navigational experience and advance capabilities. Developing the system incrementally and through partnerships is suggested.
This document provides an overview of the history and concepts of spaceplanes. It discusses early spaceplane designs from the 1930s and 1940s and traces the development of spaceplanes through programs like NASA's space shuttle. It describes the key characteristics of spaceplanes and the different types of spaceplane operations, including sub-orbital and single-stage to orbit. Major current and historic spaceplane designs and programs are outlined, including concepts from NASA, Airbus, Bristol Spaceplanes, Orbital Sciences, Reaction Engines, Virgin Galactic, and others. The advantages of reusable spaceplanes over expendable rockets are also summarized.
The document proposes a concept for a global constellation of stratospheric scientific platforms using balloons or "StratoSats" to provide low-cost, continuous, and simultaneous global Earth observations. A constellation of tens to hundreds of small, long-duration stratospheric balloons at altitudes of 30-35 km could carry instrument payloads for applications like climate change monitoring, ozone studies, and weather forecasting. Maintaining the positions of the balloons in a uniform global distribution would require trajectory control systems and algorithms to navigate the balloons according to wind patterns and forecasts.
Satellites orbit objects like planets to perform various missions. They have orbits that are either geostationary, asynchronous, or polar. Rockets are used to launch satellites into orbit and have multiple stages powered by liquid or solid propellant engines. The first stage provides maximum thrust at launch while subsequent stages have lower thrust and place the satellite into its proper transfer orbit using liquid or cryogenic engines before the final apogee kick motor releases it onto its mission orbit. Precise propulsion, communication, electrical power, and computer systems are required for successful satellite launch and operation in space.
This document discusses satellite orbits, including:
1) Most satellites orbit Earth in elliptical or circular patterns, either in the same direction as Earth's rotation (prograde) or the opposite direction (retrograde).
2) Satellites are classified based on their orbit - low earth orbit (LEO), medium earth orbit (MEO), or geosynchronous earth orbit (GEO). GEO satellites orbit at 22,300 miles above Earth.
3) Geosynchronous satellites appear stationary from Earth as they orbit at the same rate that Earth rotates, completing one revolution every 24 hours. They provide coverage to about 40% of Earth's surface.
Satellites
Introduction to Satellite Systems
o A satellite is an artificial object which is placed intentionally into an orbit of any natural satellite. Satellites are used for many purposes i.e. weather forecasting, digital transmission, scientific research and development etc.
o In a communication context, a satellite is a specialized wireless transmitter/receiver that is launched by a rocket and placed in orbit around the earth.
o A satellite can be natural, like the moon, or artificial (human made). So we can say that a satellite is an object that moves in a curved path around a planet.
o Satellite can travel around planets or around stars such as our sun. All the planets are satellites around the sun.
o Satellites which are far away from the surface of the earth can cover a wide area on the surface of the earth.
Following are the four important types of Earth Orbit satellites −
• Geosynchronous Earth Orbit Satellites
• Medium Earth Orbit Satellites
• Low Earth Orbit Satellites
• Highest Earth Orbit Satelites
Now, let us discuss about each type of earth orbit satellites one by one.
This document provides an overview of orbiters as part of a seminar on hypersonic technology demonstration vehicles. It defines what an orbit is and discusses different types of orbits including low Earth orbit, medium Earth orbit, and high Earth orbit. It then describes what a spacecraft is, including its anatomy and different types. Finally, it focuses specifically on orbiter spacecraft, explaining their design considerations for entering orbit around distant planets and conducting in-depth studies.
Satellites are launched into orbit using launch vehicles, which can be either expendable or reusable. Expendable vehicles are designed for single use and are not recovered after launch, while reusable vehicles like the Space Shuttle can launch payloads into space more than once by recovering components like the main engines and solid rocket boosters. To reach higher orbits over 200km, satellites are first launched into a lower transfer orbit using rockets before using onboard motors to circularize into the final destination orbit. Launch procedures take into account factors like the desired orbit, weather conditions, and precise timing.
Satellite communication uses satellites in orbit around Earth to relay signals between Earth stations. There are different types of satellite orbits including low Earth orbit, medium Earth orbit, and geostationary Earth orbit. Satellites are used for applications like global telecommunications, broadcasting, navigation, remote sensing, and military communications. Key factors that determine satellite orbits include altitude, inclination, and orbital period.
Geostationary satellites orbit approximately 22,300 miles above the Earth's equator. They maintain a constant position relative to locations on Earth's surface. This allows them to be used for telecommunications and weather observation applications. Geostationary satellites have advantages like high coverage area from a small number of satellites, but also disadvantages like inability to observe polar regions and weak signals from long distances.
1) SEDS-UCF designed an autonomous artificial gravity centrifuge experiment to be flown on a microgravity research flight. The experiment aims to qualitatively observe the effects of artificial gravity on fluid boundaries.
2) The experiment meets FAA requirements to be classified as crew equipment by fitting in a non-flammable 12x12x16 inch box and operating automatically once activated. It contains a rotating platform that can generate centrifugal acceleration similar to Earth's gravity.
3) Microgravity is achieved on research flights through parabolic maneuvers that produce about 30 seconds of near-weightlessness. The centrifuge experiment aims to simulate gravity using centrifugal force from rotation within these microgravity periods.
There are several types of satellite orbits that are used for different applications:
1. Equatorial orbits include circular orbits directly above the equator, including geostationary orbits where satellites orbit at the same rate as the Earth's rotation.
2. Polar orbits allow satellites to collect data from the North and South poles to help with weather forecasting and search and rescue missions.
3. Inclined orbits follow paths other than directly over the equator or poles and are used by some countries for domestic communication networks.
This document discusses orbit and constellation design. It provides an 11 step process for orbit design that includes establishing orbit types and requirements, assessing specialized orbits like sun synchronous and evaluating single satellite vs constellation architectures. Constellation design considerations include coverage, number of satellites and orbital planes. Maintaining proper stationkeeping and avoiding collisions are also discussed.
1. Satellite orbits can be equatorial, polar, or inclined depending on their path above the Earth's surface. A geostationary orbit is equatorial with 0 inclination such that the satellite appears stationary from Earth.
2. Spatial, spectral, temporal, and radiometric resolutions describe the detail and information that can be detected by a satellite sensor. Higher resolutions allow for smaller features, narrower wavelength bands, more frequent revisits, and finer differences in energy to be observed.
3. Indian satellites carry sensors with characteristics suited to applications like agriculture, mapping, disaster monitoring, and defense. Their resolutions support tasks like resource monitoring, precision farming, and border security.
This document discusses different types of satellite orbits. It defines an orbit as two bodies orbiting a common center of mass. It describes Kepler's laws of planetary motion. It then defines and compares different orbit classifications including altitude classifications like geostationary and low Earth orbits, inclination classifications, eccentricity classifications, and others. It provides details on important orbit types like geostationary, low Earth, and medium Earth orbits.
NASA Orion Multi Purpose Crew Vechicle - Full ExplanationGokul Lakshmanan
The document summarizes key components and technologies used in NASA's Orion Multi-Purpose Crew Vehicle, including the crew and service modules, thermal protection system, radiation shielding, and launch abort system. Orion will carry crews of up to four astronauts beyond low Earth orbit using advanced technologies like a glass cockpit, auto-docking capabilities, and improved waste management facilities. Its service module will provide power, oxygen, water recycling and other life support functions to sustain crews for up to 8 months.
Geo synchronous and Sun synchronous SatellitesTilok Chetri
There are three main types of satellite orbits:
1) Polar orbits have an inclination of 90 degrees, allowing satellites to observe the entire Earth as it rotates. They complete an orbit every 90 minutes.
2) Sun synchronous orbits allow satellites to pass over the same location at the same local time each day. These orbits are between 700-800 km in altitude.
3) Geosynchronous orbits circle the Earth at the same rate it rotates, allowing satellites to continuously observe nearly half of the Earth. These orbits are used for weather monitoring and communication satellites. Each orbit type has advantages and disadvantages for different applications.
Orbits and space flight, types of orbitsShiva Uppu
This document discusses orbital mechanics including different types of orbits around Earth and other planets. It begins by defining orbital elements like eccentricity, semi-major axis, inclination, and orbital period. It then describes different types of orbits including low Earth orbit, geosynchronous orbit, polar orbit, and Hohmann transfer orbits. Basic orbital equations are provided relating centripetal force, gravitational force, orbital velocity, and orbital radius. Numerical examples are worked through to calculate orbital velocity, orbital radius, and orbital period for satellites orbiting Earth.
There are two types of satellites: natural and artificial. Natural satellites like the Moon orbit planets, while artificial satellites are human-made objects placed into orbit, like Sputnik 1. There are different types of artificial satellites depending on their orbit, such as geostationary satellites that orbit over the equator at a fixed position, and polar satellites that orbit from pole to pole. The escape velocity of a satellite is the minimum speed needed to escape the gravitational pull of the object it orbits, and varies based on location in the solar system. Kepler's laws describe satellite motion, such as elliptical orbits with the orbited body at one focus.
S/C in Heliosynchronous Orbit - Spacecraft Environment AnalysisPau Molas Roca
The document characterizes the space radiation environment for a spacecraft in a heliosynchronous orbit at 800 km altitude. It finds that the main radiation sources are solar particles, trapped radiation in the Van Allen belts, and galactic cosmic rays. The radiation can damage spacecraft devices through single-event effects and dielectric charging. The worst scenarios include higher radiation in the South Atlantic Anomaly and polar regions due to weaker magnetic shielding.
The Space Shuttle was NASA's partially reusable orbital spacecraft that operated from 1981 to 2011. It consisted of an orbiter vehicle with two solid rocket boosters and an external fuel tank. The Shuttle launched numerous satellites and components of the International Space Station over 135 missions. However, two orbiters were lost in accidents in 1986 and 2003, resulting in a total of 14 astronaut deaths. Key components of the Shuttle included the three main engines, two solid rocket boosters, and external fuel tank that was jettisoned after launch. Missions involved launch from Florida, orbital operations for up to two weeks, and a gliding landing back on Earth.
This document discusses the concept of global constellations of stratospheric satellites (StratoSats) maintained by trajectory control systems. It proposes maintaining tens to hundreds of small, long-duration balloons at an altitude of 35 km to provide continuous, global earth observations. Key points discussed include StratoSat systems design, promising earth science missions like measuring the Earth's radiation budget, and potential demonstration missions to validate the concept like a hurricane intercept mission or radiometer calibration experiment.
The document summarizes the history and specifications of NASA's Space Shuttle program. It describes key aspects of the shuttle including its 135 missions from 1981 to 2011 which launched satellites and parts for the International Space Station. It details the major components of the shuttle - the orbiter, external tank, solid rocket boosters, and main engines. It provides specifications for components like height, mass, payload capacity. It outlines a typical mission profile from launch to orbital operations to re-entry and landing back on Earth.
Launch Vehicles and Propulsion_Satellite CommunicationBalaji Vignesh
Launch vehicles use multi-stage configurations and rocket propulsion to inject payloads into specific orbital trajectories based on velocity and altitude, with chemical propulsion being the most common but ion engines providing higher exhaust velocities. Satellites are launched on expendable or reusable vehicles depending on their design from sites around the world, with factors like Earth's rotation sometimes providing an assist through sling effect to reduce launch costs. Over 2500 satellites currently orbit Earth for purposes including communication, and careful orbital placement prevents collisions despite increasing congestion.
There are several types of satellite orbits with varying heights from Earth's surface, including LEO, MEO, GEO, and HEO. Directly launching a satellite into its final orbit requires a large amount of energy and fuel, increasing the weight of the launch vehicle. There are two main types of satellite launching: expendable launch vehicles and reusable launch vehicles like the Space Shuttle. ELVs launch satellites into an elliptical transfer orbit before final orbital insertion using apogee kick motors, while RLVs launch to a low parking orbit first before using additional motors to reach the final orbit.
An entomopter, which mimics insect flight, is proposed for exploration of Mars. Key challenges include the low atmospheric density and pressure of Mars. Computational fluid dynamics simulations show entomopters could generate lift coefficients of 4-15 through wing motion and vortex interactions. The design point for a Mars entomopter includes a 0.6m wingspan, 75 degree flap angle, 6 Hz flapping frequency, and 883W power requirement for 1.5kg payload lift at 14m/s cruise speed. Landing would require a brief high-power mode. Fuel selection depends on whether it is produced in-situ or brought from Earth.
The document discusses reusable launch vehicles (RLVs) which aim to reduce the high costs of space launches by recovering and reusing rocket components. Currently, 40% of launch costs come from building non-reusable rockets. RLVs could reduce costs by a factor of 100 by recovering first stage boosters, similar to how SpaceX has landed its Falcon 9 rocket boosters. The document outlines the history of rockets, compares conventional expendable launch vehicles to reusable ones, and describes the key components and launch process of an RLV. It discusses challenges of RLVs like heat stresses during flight and challenges of vertical landing, but notes the technology is feasible and could make space travel more routine and affordable.
Satellites are launched into orbit using launch vehicles, which can be either expendable or reusable. Expendable vehicles are designed for single use and are not recovered after launch, while reusable vehicles like the Space Shuttle can launch payloads into space more than once by recovering components like the main engines and solid rocket boosters. To reach higher orbits over 200km, satellites are first launched into a lower transfer orbit using rockets before using onboard motors to circularize into the final destination orbit. Launch procedures take into account factors like the desired orbit, weather conditions, and precise timing.
Satellite communication uses satellites in orbit around Earth to relay signals between Earth stations. There are different types of satellite orbits including low Earth orbit, medium Earth orbit, and geostationary Earth orbit. Satellites are used for applications like global telecommunications, broadcasting, navigation, remote sensing, and military communications. Key factors that determine satellite orbits include altitude, inclination, and orbital period.
Geostationary satellites orbit approximately 22,300 miles above the Earth's equator. They maintain a constant position relative to locations on Earth's surface. This allows them to be used for telecommunications and weather observation applications. Geostationary satellites have advantages like high coverage area from a small number of satellites, but also disadvantages like inability to observe polar regions and weak signals from long distances.
1) SEDS-UCF designed an autonomous artificial gravity centrifuge experiment to be flown on a microgravity research flight. The experiment aims to qualitatively observe the effects of artificial gravity on fluid boundaries.
2) The experiment meets FAA requirements to be classified as crew equipment by fitting in a non-flammable 12x12x16 inch box and operating automatically once activated. It contains a rotating platform that can generate centrifugal acceleration similar to Earth's gravity.
3) Microgravity is achieved on research flights through parabolic maneuvers that produce about 30 seconds of near-weightlessness. The centrifuge experiment aims to simulate gravity using centrifugal force from rotation within these microgravity periods.
There are several types of satellite orbits that are used for different applications:
1. Equatorial orbits include circular orbits directly above the equator, including geostationary orbits where satellites orbit at the same rate as the Earth's rotation.
2. Polar orbits allow satellites to collect data from the North and South poles to help with weather forecasting and search and rescue missions.
3. Inclined orbits follow paths other than directly over the equator or poles and are used by some countries for domestic communication networks.
This document discusses orbit and constellation design. It provides an 11 step process for orbit design that includes establishing orbit types and requirements, assessing specialized orbits like sun synchronous and evaluating single satellite vs constellation architectures. Constellation design considerations include coverage, number of satellites and orbital planes. Maintaining proper stationkeeping and avoiding collisions are also discussed.
1. Satellite orbits can be equatorial, polar, or inclined depending on their path above the Earth's surface. A geostationary orbit is equatorial with 0 inclination such that the satellite appears stationary from Earth.
2. Spatial, spectral, temporal, and radiometric resolutions describe the detail and information that can be detected by a satellite sensor. Higher resolutions allow for smaller features, narrower wavelength bands, more frequent revisits, and finer differences in energy to be observed.
3. Indian satellites carry sensors with characteristics suited to applications like agriculture, mapping, disaster monitoring, and defense. Their resolutions support tasks like resource monitoring, precision farming, and border security.
This document discusses different types of satellite orbits. It defines an orbit as two bodies orbiting a common center of mass. It describes Kepler's laws of planetary motion. It then defines and compares different orbit classifications including altitude classifications like geostationary and low Earth orbits, inclination classifications, eccentricity classifications, and others. It provides details on important orbit types like geostationary, low Earth, and medium Earth orbits.
NASA Orion Multi Purpose Crew Vechicle - Full ExplanationGokul Lakshmanan
The document summarizes key components and technologies used in NASA's Orion Multi-Purpose Crew Vehicle, including the crew and service modules, thermal protection system, radiation shielding, and launch abort system. Orion will carry crews of up to four astronauts beyond low Earth orbit using advanced technologies like a glass cockpit, auto-docking capabilities, and improved waste management facilities. Its service module will provide power, oxygen, water recycling and other life support functions to sustain crews for up to 8 months.
Geo synchronous and Sun synchronous SatellitesTilok Chetri
There are three main types of satellite orbits:
1) Polar orbits have an inclination of 90 degrees, allowing satellites to observe the entire Earth as it rotates. They complete an orbit every 90 minutes.
2) Sun synchronous orbits allow satellites to pass over the same location at the same local time each day. These orbits are between 700-800 km in altitude.
3) Geosynchronous orbits circle the Earth at the same rate it rotates, allowing satellites to continuously observe nearly half of the Earth. These orbits are used for weather monitoring and communication satellites. Each orbit type has advantages and disadvantages for different applications.
Orbits and space flight, types of orbitsShiva Uppu
This document discusses orbital mechanics including different types of orbits around Earth and other planets. It begins by defining orbital elements like eccentricity, semi-major axis, inclination, and orbital period. It then describes different types of orbits including low Earth orbit, geosynchronous orbit, polar orbit, and Hohmann transfer orbits. Basic orbital equations are provided relating centripetal force, gravitational force, orbital velocity, and orbital radius. Numerical examples are worked through to calculate orbital velocity, orbital radius, and orbital period for satellites orbiting Earth.
There are two types of satellites: natural and artificial. Natural satellites like the Moon orbit planets, while artificial satellites are human-made objects placed into orbit, like Sputnik 1. There are different types of artificial satellites depending on their orbit, such as geostationary satellites that orbit over the equator at a fixed position, and polar satellites that orbit from pole to pole. The escape velocity of a satellite is the minimum speed needed to escape the gravitational pull of the object it orbits, and varies based on location in the solar system. Kepler's laws describe satellite motion, such as elliptical orbits with the orbited body at one focus.
S/C in Heliosynchronous Orbit - Spacecraft Environment AnalysisPau Molas Roca
The document characterizes the space radiation environment for a spacecraft in a heliosynchronous orbit at 800 km altitude. It finds that the main radiation sources are solar particles, trapped radiation in the Van Allen belts, and galactic cosmic rays. The radiation can damage spacecraft devices through single-event effects and dielectric charging. The worst scenarios include higher radiation in the South Atlantic Anomaly and polar regions due to weaker magnetic shielding.
The Space Shuttle was NASA's partially reusable orbital spacecraft that operated from 1981 to 2011. It consisted of an orbiter vehicle with two solid rocket boosters and an external fuel tank. The Shuttle launched numerous satellites and components of the International Space Station over 135 missions. However, two orbiters were lost in accidents in 1986 and 2003, resulting in a total of 14 astronaut deaths. Key components of the Shuttle included the three main engines, two solid rocket boosters, and external fuel tank that was jettisoned after launch. Missions involved launch from Florida, orbital operations for up to two weeks, and a gliding landing back on Earth.
This document discusses the concept of global constellations of stratospheric satellites (StratoSats) maintained by trajectory control systems. It proposes maintaining tens to hundreds of small, long-duration balloons at an altitude of 35 km to provide continuous, global earth observations. Key points discussed include StratoSat systems design, promising earth science missions like measuring the Earth's radiation budget, and potential demonstration missions to validate the concept like a hurricane intercept mission or radiometer calibration experiment.
The document summarizes the history and specifications of NASA's Space Shuttle program. It describes key aspects of the shuttle including its 135 missions from 1981 to 2011 which launched satellites and parts for the International Space Station. It details the major components of the shuttle - the orbiter, external tank, solid rocket boosters, and main engines. It provides specifications for components like height, mass, payload capacity. It outlines a typical mission profile from launch to orbital operations to re-entry and landing back on Earth.
Launch Vehicles and Propulsion_Satellite CommunicationBalaji Vignesh
Launch vehicles use multi-stage configurations and rocket propulsion to inject payloads into specific orbital trajectories based on velocity and altitude, with chemical propulsion being the most common but ion engines providing higher exhaust velocities. Satellites are launched on expendable or reusable vehicles depending on their design from sites around the world, with factors like Earth's rotation sometimes providing an assist through sling effect to reduce launch costs. Over 2500 satellites currently orbit Earth for purposes including communication, and careful orbital placement prevents collisions despite increasing congestion.
There are several types of satellite orbits with varying heights from Earth's surface, including LEO, MEO, GEO, and HEO. Directly launching a satellite into its final orbit requires a large amount of energy and fuel, increasing the weight of the launch vehicle. There are two main types of satellite launching: expendable launch vehicles and reusable launch vehicles like the Space Shuttle. ELVs launch satellites into an elliptical transfer orbit before final orbital insertion using apogee kick motors, while RLVs launch to a low parking orbit first before using additional motors to reach the final orbit.
An entomopter, which mimics insect flight, is proposed for exploration of Mars. Key challenges include the low atmospheric density and pressure of Mars. Computational fluid dynamics simulations show entomopters could generate lift coefficients of 4-15 through wing motion and vortex interactions. The design point for a Mars entomopter includes a 0.6m wingspan, 75 degree flap angle, 6 Hz flapping frequency, and 883W power requirement for 1.5kg payload lift at 14m/s cruise speed. Landing would require a brief high-power mode. Fuel selection depends on whether it is produced in-situ or brought from Earth.
The document discusses reusable launch vehicles (RLVs) which aim to reduce the high costs of space launches by recovering and reusing rocket components. Currently, 40% of launch costs come from building non-reusable rockets. RLVs could reduce costs by a factor of 100 by recovering first stage boosters, similar to how SpaceX has landed its Falcon 9 rocket boosters. The document outlines the history of rockets, compares conventional expendable launch vehicles to reusable ones, and describes the key components and launch process of an RLV. It discusses challenges of RLVs like heat stresses during flight and challenges of vertical landing, but notes the technology is feasible and could make space travel more routine and affordable.
ORIONTWO PROJECT: EXTRA-TERRESTRIAL RESOURCES EXPLOITATION TO ESCAPE THE EART...Alexander Mayboroda
The developed system guarantees radical price reduction on space cargoes delivery.
Cost saving provides additional profit in the sphere of cargo and passenger trnsportation into space.
The project team is looking for partners for the project’s commercialization.
AVANTA Consulting welcomes potential partners to negotiate collaboration on commercialization of OrionTwo Project.
This document provides an overview of aeronautics and aerodynamics. It begins with a brief history of manned flight, starting with the Wright Brothers' first sustained, powered flight in 1903. It then outlines several chapters that will cover topics in fluid mechanics, lift generation, drag forces, high-speed aerodynamics, aircraft propulsion systems, airplane performance, static and dynamic stability, and control. The document provides a table of contents to structure the topics and serves as an introductory guide to the principles of aeronautics.
This document provides an overview of a seminar presentation on supersonic planes. It includes sections on the introduction, history, theories, engine types, and applications of supersonic flight. The presentation was given by Jahani and Abdolzade for a fluid mechanics course taught by Dr. Hoseinalipour in spring 2013.
Aerodynamics of flapping wing MAV
The question which I got from the panel was how to calculate the Reynolds number ?..the ans is by claculating MAC Mean Aerodynamic Chord
This document proposes a concept called the Interplanetary Rapid Transit (IRT) system to enable regular crewed flights between Earth and Mars using reusable spacecraft and infrastructure. Key elements of the concept include cycler spacecraft called "Astrotels" that travel between the planets on repeating orbits, short-range "Taxi" vehicles to transport crews between locations, and producing rocket propellant on the Moon and Mars from local resources to reduce launch costs. The document discusses orbital trajectories, vehicle designs, an example transit schedule, and technologies that could enable affordable regular access to Mars.
For the full video of this presentation, please visit:
http://www.embedded-vision.com/platinum-members/embedded-vision-alliance/embedded-vision-training/videos/pages/may-2016-embedded-vision-summit-nasa-keynote
For more information about embedded vision, please visit:
http://www.embedded-vision.com
Larry Matthies, senior research scientist at the NASA Jet Propulsion Laboratory, presents the "Using Vision to Enable Autonomous Land, Sea and Air Vehicles" keynote at the May 2016 Embedded Vision Summit.
Say you’re an autonomous rover and you’ve just landed on Mars. Vexing questions now confront you: “Where am I and how am I moving?” “What obstacles are around me?” “Are the obstacles moving?” “What other objects are around me that matter to my mission?” As it turns out, Earth isn’t that different from Mars in this regard. If you’re an autonomous car or drone, you face similar challenges. You’ve got to find combinations of sensors that work across different illumination, weather, temperature, and vehicle dynamics; processors that fit the size, weight, and power constraints of the system; and algorithms that can answer the questions given the sensors and processors available. In this talk, Matthies gives an overview of autonomous vehicle computer vision applications, explores successful approaches, and illustrates concepts with application examples from applications on Earth and in planetary exploration.
RLV.pptx and charging system in electrical vehicleSuruAarvi
The document discusses the technology of reusable launch vehicles for satellites. It begins with an introduction to reusable launch vehicles and their main components. It then discusses the history of reusable launch vehicle development. Current programs from SpaceX, ISRO, and other organizations are presented. The working mechanisms from launch to landing of reusable launch vehicles is explained. Key aspects of reusable launch vehicle design like stages to orbit, vertical landing, and retro-propulsion are outlined. Finally, the economics of reuse and technologies required for reusable launch vehicle feasibility are presented.
Analysis Of Owl-Like Airfoil Aerodynamics At Low Reynolds Number FlowKelly Lipiec
The document analyzes the aerodynamic characteristics of an owl-like airfoil at a low Reynolds number of 23,000 using computational fluid dynamics simulations. It finds that the owl-like airfoil achieves higher lift coefficients and lift-to-drag ratios than the Ishii airfoil, which was designed for high performance at low Reynolds numbers. The owl-like airfoil's round leading edge, flat upper surface, and deeply concaved lower surface contribute to lift enhancement through mechanisms like a suction peak and laminar separation bubble near the leading edge. However, the owl-like airfoil does not achieve its minimum drag coefficient at zero lift, unlike the Ishii airfoil. The document aims to provide insights that can
Early pilots navigated visually by looking for landmarks but as flying occurred at night and in poor weather, new navigation technologies were developed. In the 1920s, navigation aids helped pilots determine attitude and position even when the ground was not visible. In 1929, Sperry introduced the artificial horizon and other mechanical aids emerged in the 1930s. Today, aircraft are tracked by radar but GPS now allows pilots to determine their precise position without assistance from air traffic control. This has led to debates around who should control navigation - pilots using GPS or air traffic controllers.
Hovercraft have the ability to travel over land and water surfaces due to pressurized air being pumped into a plenum chamber and escaping out through a skirt. They consist of a hull, skirt, lifting fans, thrust fans and engines. Hovercraft operate by using lifting fans to create an air cushion that lifts the hull above the surface, while thrust fans provide propulsion. They have advantages like traveling over many surfaces and bypassing routes restricted to boats, but also have disadvantages like potential skirt damage and noise. Future applications of hovercraft in Egypt could include military transportation over the new Suez Canal or connecting lakes and tourist sites.
Aerodynamics aeronautics and flight mechanicsAghilesh V
The document discusses the history of aeronautics and provides an overview of key topics in aerodynamics and aircraft performance. It begins with a brief summary of the Wright Brothers' first controlled, powered flight on December 17, 1903. The document then outlines several chapters that will cover topics like fluid mechanics, lift generation, drag, high-speed aerodynamics, thrust production, aircraft performance, stability and control. It provides the table of contents to guide the discussion of aeronautical science concepts.
This document presents a concept for cyclical visits to Mars using astronaut hotels (Astrotels). Key aspects of the concept include using cycler orbits between Earth and Mars to transport small crews in Astrotels, orbital spaceports, and small transfer vehicles (taxis). The concept aims to reduce costs and reliance on Earth resources through in-situ resource utilization and solar electric propulsion. An analysis estimated the total life cycle cost of developing and operating the system at approximately $90 billion over 15 years.
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The British Antarctic Survey presentation described using drones for scientific research in Antarctica, including animal surveys, aerial photography and infrastructure inspections. Challenges include extreme cold, remote locations and high winds. They have flown various fixed-wing and multirotor drones.
The CAA presentation provided an overview of UK regulations for small unmanned aircraft under 20kg. Current rules require visual line of sight and permission for some operations. Harmonized international regulations are being developed to safely integrate drones into airspace as their use increases.
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Helicopters have the unique ability to hover, take off and land vertically, and fly in any direction. Their main distinguishing feature is the ability to hover for extended periods using a rotating wing. This allows helicopters to perform a wide range of missions. Helicopters face challenges in high-speed forward flight due to unequal lift distribution across the rotor blades and vibrations. Various configurations have been developed to counter the reactive torque created by the main rotor, including tail rotors, coaxial rotors, and tiltrotors. Airfoil design for helicopter rotors must account for the changing airspeed and angles of attack experienced throughout each revolution. Advancements in computer modeling have improved airfoil designs and reduced the need for wind tunnel testing
This document provides an overview of elements of aeronautics from the Dr. Ambedkar Institute of Technology. It discusses the history of aviation from da Vinci to the Wright brothers' first flight. It also covers atmospheric properties like pressure, temperature, and humidity. Aircraft classifications are described based on wing configuration, fuselage type, horizontal tail location, and engine number and placement. Basic aircraft components and structures like monocoque and semimonocoque designs are also introduced.
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I. X-ray astronomy will play an increasingly important role in studies of the early universe and large scale structure, but these studies are ultimately limited by sparse photon numbers. There is a need to develop progressively larger collecting area telescopes under increasingly severe mass constraints.
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III. Looking beyond Constellation, a radically different approach is needed based on super lightweight reflectors and perhaps in situ assembly of the telescope. This could enable an ultra high throughput X-
This document discusses the concept of an X-ray interferometer called MAXIM that could achieve micro-arcsecond resolution. It would consist of an optics spacecraft holding multiple flat mirrors in formation with a detector spacecraft to form interference patterns. The goal is to image phenomena like black hole accretion disks and supernovae with much higher resolution than current telescopes. A pathfinder mission is proposed with 100 microarcsecond resolution using two spacecraft separated by 1.4 meters as a technology demonstration.
USAF intercepted a report of a Cuban pilot's encounter with a UFO. In the 1970s, reliable military personnel sighted unidentified aerial objects near nuclear weapons facilities. Though the Air Force said these were isolated incidents, an Air Force document revealed they implemented increased security measures. Newly declassified documents from the CIA, FBI and other agencies indicate unidentified flying objects exist and some pose a threat to national security by demonstrating technologies beyond present human capability. However, the government has misled the public about the true nature and implications of the UFO phenomenon.
This document summarizes the agenda for the NIAC Phase I Fellows Meeting held on October 23-24, 2002. It provides an overview of the presentations and speakers, including status reports on various advanced aerospace concepts from NIAC fellows, as well as keynote speeches from experts in the fields of aerial robotics and the search for extraterrestrial intelligence.
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high-value future air and space system concepts and their enabling technologies. A value model called
Foundations 2025 was developed to quantify and compare different system concepts. Various futuristic
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the most valuable system concepts and technologies that could enhance future air and space capabilities.
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This document proposes concepts and technologies for counterspace operations in 2025, including space detection, anti-satellite weapons, space interdiction nets, miniaturized satellites, satellite cloaking, kinetic and directed energy weapons. It outlines offensive and defensive counterspace architectures and recommends further analysis of miniaturization, stealth, detection and targeting concepts as well as kinetic and directed energy weapons. The goal is to maintain US space superiority as space becomes increasingly vital to national security and more countries and commercial entities access space.
1. Planetary Exploration Using Biomimetics
An Entomopter for Flight On Mars
Phase II Project NAS5-98051
NIAC Fellows Conference
June 6, 2001
NASA Ames Research Center
Anthony Colozza
Northland Scientific / Ohio Aerospace Institute
Cleveland, Ohio
2. Planetary Exploration Using Biomimetics
Page 2
Team Members
• Mr. Anthony Colozza / Northland Scientific Inc.
• Dr. Robert Michelson / Georgia Tech Research Institute
• Dr. Thomas Scott / University of Missouri
• Mr. Teryn Dalbello / ICOMP
• Mr. Frank Porath / OAI
Consultants
• Mrs. Lisa Kohout / NASA Glenn Research Center
• Mr. Mark Seibert / NASA Glenn Research Center
3. A Flight vehicle can be used to revolutionize Mars exploration.
• Mars has been a primary objective of planetary exploration for
the past 20 years.
• To date, all exploration vehicles have been landers, orbiters,
fly-bys and, most recently, a rover (Sojourner).
• The ability to fly on Mars has the potential to expand the range
covered with greater resolution and can provide a means for
atmospheric sampling.
• Present day aerospace technology (aerodynamics, materials,
propulsion, power, communications) have advanced to the point
to enable this type of vehicle.
Page 3
Mars Exploration
5. Page 5
Candidate Mars Micromission Aircraft
Battery Powered Electric Aircraft
Rocket Powered Aircraft
6. Page 6
Flight on Mars – General Issues
• Deployment is required on entry, since there is no ability
to take off with a conventional aircraft from the ground.
• No place to land aircraft after flight is complete.
• Aircraft must fly at 0.5 to 0.8 Mach. This limits imaging
and data gathering capability.
• For the micromission, aircraft endurance is limited to 20
minutes due to the available communication window
during flight.
7. Page 7
Flight on Mars – Environmental Issues
• Extremely low atmospheric density - 1/70th that at Earth
surface
• Lower speed of sound than on Earth - 22% less
• Conventional aircraft must fly in a low Reynolds number,
high Mach number flight regime (difficult aerodynamics)
• Gravity 1/3 that of the Earth
• Atmosphere is 95% Carbon Dioxide
• Surface temperature extremes -143°C to 27° C
8. Page 8
Flight on Mars – Aerodynamics Issues
• No conventional aircraft has previously flown in
aerodynamic flight regime in which flyer will operate:
– Wing: Re < 50,000, M > 0.5
– Propeller: Re = ~15,000, M = ~0.8
• Aerodynamic performance of airfoils in this regime not well
understood.
• Main issue is laminar separation of boundary layer.
• Ability to transition flow to turbulent and re-attach boundary
layer is main challenge.
• Need to investigate physics of this boundary layer.
• New airfoil and boundary layer trip mechanisms will need to
be designed.
9. Project Goal
The Goal of this Project is to Use the
Present State of Knowledge on
Entomopter Development and Apply
this to Developing an Entomopter for
the Mars Environment.
Page 9
10. Page 10
An Entomopter is an Innovative Approach to
Small Aircraft Flight on Mars
What is an Entomopter?
• An Entomopter is a flying vehicle that generates lift
in a fashion similar to that of an insect.
• It is based on a present DARPA program to develop
micro-aircraft (on Earth) with flight characteristics
like those of insects (flapping wings).
• Mars flight would be in the same flight Reynolds
number regime experienced by large insects on
Earth.
• Extremely high potential lift generation capability
(CL
~ 5.0)
11. • The aerodynamic force generated via conventional
mechanisms is insufficient to explain the nature of
insect flight.
• The probable mechanism for lift generation is an
interaction of the wings with a starting vortex.
• This interaction is dependent on the low Reynolds
number of insect flight.
Page 11
Theory of Insect Flight
12. Page 12
The Main Difference Between Flapping Flight and Airfoil
Flight is the Continual Formation and Shedding of the Wing
Air Moves Over Wing Surface with no Separation.
Flow Over Wing
Trailing Vortex
Conventional Airfoil Produces a Steady State Standing Vortex.
Vortex Does Not
Effect Lift Generation
by the Wing.
3 Dimensional
Wake Structure
Vortex is Shed After
Bound Vortex is Formed each Stroke
After Each Stroke.
Bound Vortex is the Source of Lift
Vortex Tube
Vortex in Flapping Flight.
13. Page 13
Vortex Wake is not Completely Understood.
It is Believed that the Vortex is Caused by Flow Separation
Over the Leading Edge of the Wing
Stroke cycle starts with downward motion.
Start of the vortex tube occurs over the entire
edge of the wing.
During the stroke, the tubes merge and form a
vortex.
Vortex tube unites at the end of the down stroke
and is then shed.
Vortex
Due to rotation of the wing, there is no vortex ring formed on the upstroke.
14. Page 14
Vortex Interaction
• Flapping wings are not capable of generating the
maximum circulation possible.
• This is due to the rate of flapping and the time
delay required for the growth of this circulation.
• It is believed insects overcome this by interacting
with their own vortex wake.
15. Page 15
Wing Lift Distribution
Throughout the Stroke Cycle
Lift
Stroke
Position
Vertical
Horizontal
- +
Lift is 0 at the beginning of the stroke.
Increases and achieves its extreme value in
the second half of the downstroke.
Begins to lessen at the end of the
downstroke.
Becomes negative throughout the
upstroke.
16. Page 16
Lift Generation
• Unlike conventional airfoils, there is no dramatic reduction
in lift after the wing achieves super critical angles of attack.
• This suggests that flow separation (prior to vortex
formation) does not occur.
• It is believed that this is due to low Reynolds number flight
and the high wing flap rate (10-1 to 10-2 seconds).
• Additional lift producing mechanisms include:
– Rotational motion of the wing (Magnus force)
– Wake interaction
• Control is achieved by lift variations through these
mechanisms.
• CL = 5.3 has been demonstrated on terrestrial Entomopter
wind tunnel tests.
17. • Reynolds Number ≥106 polar curves indicate an evident crisis
of flow, caused by early separation around a still wing.
• Reynolds Number ≥ 104 this flow crisis is greatly reduced and
the flow displays a smooth shape.
• 10 < Reynolds Number > 103 flow separation is absent.
• As Reynolds Number decreases, other lift producing
mechanisms may come into play (differential drag & velocity
and boundary layer effects).
Page 17
Reynolds Number Effect
18. • The Mars environment may be ideal for Entomopter
flight:
– Low atmospheric density means a larger vehicle (≈ 1 m wingspan)
which reduces the need for miniaturization, increases lifting capacity
– Low gravitational force (1/3 that of Earth) increases the potential
flapping frequency and reduces the required wing loading
• An Entomopter would have the ability to take off,
fly, land and possibly hover.
• An Entomopter would be capable of slow flight and
precision flight control.
Page 18
An Entomopter on Mars
19. Page 19
Entomopter Flight System for Mars
Rover Mobile Base Refueling Station Entomopter
20. Page 20
Mission Profiles
• Independent exploration using an Entomopter
– Pro: Entomopter is not restricted to the area around a central vehicle
– Con: Short mission duration since fuel supply is limited to carrying
capacity
• Exploration in conjunction with a fixed lander
– Pro: Can provide the ability to refuel (possibly using “In-Situ” fuel
production) with multiple flight capability and bring back samples for
analysis on the lander
– Con: Limited to the area around the lander
• Exploration in conjunction with a rover vehicle
– Pro: Extended terrain coverage as the rover moves across the surface,
enhancing navagation of the rover, potential to refuel with multiple
flight capability, capability to bring back samples to the rover for
analysis
– Con: Increased logistical complexity
21. Page 21
Rover/Entomopter Operation
• Multiple Entomopters would be flown on each mission.
• Each Entomopter would carry one or more science
instruments which could be different for each vehicle.
22. Page 22
Mission Profile Diagram
Flight Profile
Base Vehicle
15 Minute Period on Surface,
Relay Data, Receive Navigation Commands
Take Surface Data, Collect Samples
3 Hour Period on the
Surface for Detailed
Sample Collection Analysis
0 2 4 6
Time (hrs)
Flight Profile
Base Vehicle
Four Entomopter Vehicles Operating
from a Base Ground Vehicle
12 Minuite Round Trip Flight Time
Flight Profile 1 Minuite
Flight or Hover Intervals
15 Minuite Period on Surface,
Relay Data, Recieve Navigation Commands
Take Surface Data, Collect Samples
Four Entomopter Vehicles Operating
From a Base Ground Vehicle
12 Minute Round Trip Flight Time
Flight Profile 1 Minute
Flight or Hover Intervals
3 Hour Period on the
Surface for Detailed
Sample Collection
Analysis
0 2 4 6
Time (Hours)
23. Page 23
Science Objectives
• Surface Mineralogy and Sampling
– Collect and return samples to the base vehicle
– Perform composition analysis with an alpha proton X-ray spectrometer
• High resolution Surface Imaging
– Image terrain, atmosphere and horizon. Also provide close up views of surface
material
• Atmospheric Condition and Sampling
– Collect atmosphere samples at various altitudes, record temperature, pressure,
wind speed/direction and dust content
• Payload Delivery
– Deliver payloads (micro science stations) to the surface
• Magnetic Field Mapping
• Infrared and Radar Mapping
– IR imaging of the surface
– Radar transmitter to provide a radar map while in flight
25. Page 25
Entomopter Development
• Entomopters for terrestrial applications have been under
development for a number of years.
• Mainly supported by DARPA and performed by universities
and some private companies, i.e. Georgia Tech Research
Institute (GTRI), Stanford University, etc.
• GTRI design is the baseline for the Mars Entomopter
development.
• Mars Entomopter will be a larger version of the terrestrial
design to maintain the correct flight Reynolds number.
• The wing loading for both the Mars and Earth versions will be
the same, but due to the increased size and lower gravity on
Mars, the Mars version will carry significantly more mass.
26. Page 26
GTRI Entomopter Design
• Flapping wing vehicle with tandem “see-saw” wings
phased at 180° about a central torsional fuselage
• Integrated lift, control, and propulsion systems
• Simplicity weight reduction from non-moving lift
control surfaces
• Instantaneous response characteristics from pneumatics
• High CL at Low α = No need to fly near Clmax
• Positive lift at negative α on upstroke due to pneumatic
flow control
• Leading-edge pneumatic lift augmentation induces flow
structure over the wing to remain attached longer,
increasing CL
27. Page 27
Entomopter Wing Motion
• Wings oscillate at a constant rate. (On the Earth-based
Entomopter, it is between 25Hz and 30 Hz.)
• Because of the constant rate motion the structure can be
designed to act as a spring tuned to this frequency to store
energy from the wing motion.
28. Page 28
Aerodynamic Approach
• The aerodynamics of the terrestrial Entomopter is
applicable to Mars flight if the vehicle is properly scaled
(i.e. Wing span increases from 15 cm to 92 cm).
• Wing airfoil is thin with moderate camber and a sharp
leading edge to enhance vortex formation.
• The vortex separation point is controllable through the
venting of exhaust gasses onto the wing surface, enabling
lift control on each wing while maintaining a constant beat
frequency.
• The design of the flexible ribs within the wing in
conjunction with circulation control allows for lift to be
produced on both the up and downstrokes.
29. Page 29
Lift Generation
• It is estimated that the combination of boundary layer blowing in
combination with the wing flapping will produce lift coefficients
between 7.95 and 10.6.
• Based on this, a 1 m wingspan Entomopter on Mars should be
capable of lifting between 5 and 7 kg total mass.
30. GTRI Entomopter Flight Control
CL can be modulated independently on each wing to change lift on each beat by
recycling waste gas and blowing it out the edges of the wing.
Page 30
Flight Direction
Roll by Asymmetric Lift,
Port to Starboard
Pitch by Asymmetric Lift,
Fore to Aft
Yaw by Asymmetric Thrust by Reduced
Jet Deflection, Port to Starboard
ΔCM
ΔCN
ΔCRoll
Very Rapid Response Times;
Unsteady blowing augments forces
31. Page 31
Propulsion System
• The wing motion is supplied by a “Reciprocating Chemical
Muscle (RCM)” that presently uses Hydrogen Peroxide as its
energy source.
• The RCM has gone through 3 stages of development to reduce
mass and size and is presently capable of 70 Hz operation - 4th
development stage is presently under way.
• The RCM utilizes gas expansion based on the fuel
decomposition. The fuel can either be a mono-propellant or a
bi-propellant.
• A process control system meters
the fuel into the reaction chamber.
32. • For gas bearings to reduce friction without wetted parts
• To produce an ultrasonic sonar signal (frequency modulated
continuous wave FMCW) for obstacle avoidance and altimetry
• For flow augmentation over the wings enabling lift control over
the wings on a beat-to-beat basis
• For directional thrust
• To entrain atmospheric gasses through an ejector as a means of
cooling the exhaust gases and increasing mass flow
Page 32
Additional Uses for the Exhaust Gases
33. Page 33
Operational Design Considerations
• Fuel to power the Entomopter
– Must be compatible with the extremes of the Mars
environment.
– Is desirable to be able to manufacture the propellant (at
least partially) for indigenous materials.
• Autonomous control and self-stabilized behavior
– Ability to navigate, takeoff, land, refuel, adjust attitude
and situational/environment awareness.
34. Page 34
Propellant Selection
• To be utilized, the propellant must be in liquid form
during storage and operation, ideally with minimal
thermal control.
• The ability to refuel the Entomopter is a vital component
of the proposed mission scenario and greatly enhances the
science data collection ability.
• Extra fuel for the Entomopter would need to be either
brought from the Earth or manufactured on Mars using
“In-Situ” resources or some combination of these.
• The components to make up most propellants (Nitrogen,
Carbon, Oxygen and Hydrogen) with the exception of
Hydrogen, can be found within the atmosphere or soil
of Mars.
36. Page 36
Propellant Production
• The basic components of these propellants (Nitrogen,
Carbon Oxygen) can be obtained from the atmosphere.
• The CO2 can supply the Carbon Oxygen, and Nitrogen
can be obtained directly from the atmosphere.
• The CO2 N can be separated from the atmosphere using
a sorption compressor.
• Once separated, the CO2 can be broken apart using a
Zirconia solid-oxide generator
37. Direct Oxidation with CO2
• An additional non-conventional propellant concept was
considered: the direct combustion of CO2 with a metal.
• Main issues are: High CO2 pressure required, producing
correct distribution and density of metal particles CO2 and
metal oxides that are formed are difficult to remove.
Page 37
Metal Reaction Ignition
Temperature
Magnesium Mg + CO2 = MgO +CO 340°C
Lithium 2Li + CO2 = Li2O + CO 851°C
Aluminum 2AL + 3CO2 = AL2O3 +
CO
2000°C
39. Page 39
Communications Scheme
• The communications scheme is based on ultra-wideband
(UWB) technology.
– UWB emits rapid sequencing of extremely short ( 1ns)
wideband ( 1 GHz) low power bursts of radio frequency
energy.
• UWB system will reduce power, mass and volume over
conventional communications systems.
– Analysis has predicted that data can be transferred over a
10 mile range at a T1 rate on 56 mW of average power.
• UWB system is software controlled and reconfigurable in
real time to perform different functions as needed.
40. Page 40
Direct Oxidation with CO2
Entomopter
vehicles
Obstacles
(Rocks, boulders)
Communications,
Positioning
Imaging (Synthetic vision),
Collision Avoidance and
Situational Awareness
Base
UWB can be simultaneously used for a number of tasks:
• High rate digital communications between one or more of the Entomopters
and the lander or rover.
• Precise position control between the Entomopters and surface or obstacles.
• In-flight collision avoidance radar imaging.
• Timing synchronization between Entomopters.
41. Page 41
Power Production Requirements
• Communications
– 0.5 Watt peak
– 3 W-hr total energy
• Science Instruments
Instrument Power (Watts)
– 2 Watts peak
– 10.7 W-hr total
• Internal Computer Systems
– 1 Watt continuous
– 6 W-hr total
Transmission Power (Watts)
0.5
Check In Session Data Transfer Session
0.0 Time (Hours) 6.0
2
0 Time (Hours) 6
Internal Systems Power (Watts)
1.0
0.0
Time (Hours) 6.0
42. Page 42
Photovoltaic/Battery Power System
• This system was the most attractive based on
performance and weight.
• Consists of CuInSe2 thin film array on the wings
with a Lithium Polymer battery for storage.
• Array Performance
– 10% efficient
– 0.20 m2 area
– Array Mass 0.014 kg
• Battery Performance
PV Array
Battery Charge Controller
– 6.5 W-hr capacity
– Battery Mass 0.048 kg
• Estimated system mass 0.068 kg
To Load
Battery
43. Page 43
• Equator
– 55.71 W-hr
• 85° N Latitude
– 107.67 W-hr
7
6
5
4
3
2
1
0
-1
0 5 10 15 20 25 30
Time (Hours)
Latitude 0°
Latitude 85°, Vernal
Equinox
Array Performance
44. Page 44
Alternate Power System Concepts
• Thermoelectric powered by exhaust gases
• Linear Alternator on the RCM
– For these concepts to produce power, the vehicle must be
running. During down time (on the surface) a battery
backup would be needed to supply power. The weight of
this battery was greater than the PV system.
• Thermoelectric powered by radioisotope heater unit
(RHU)
– Can produce power during the complete mission.
However, the mass of the required RHU alone is greater
then the PV/ battery system mass.
45. Page 45
Phase II Goals:
Aerodynamic Analysis
• Aerodynamic analysis will be the main focus of the
Phase II work:
– Analysis of unsteady low Reynolds number flow over the wing.
– Analysis of boundary layer blowing scheme.
– Production of a 3-D flow field visualization over the wings.
– Investigation of shed vortices interaction with wings and
fuselage.
– Wind tunnel flow visualization tests.
• The analysis work will be used to validate the Entomopter
concept:
– Validate aerodynamic performance projections.
– Validate scaling of the Entomopter to size required on
Mars.
46. Page 46
Additional Phase II Goals
• Vehicle Design
– Scale-up from the terrestrial version will be investigated,
also component placement, instrumentation, payload, and
operations
• Structural Analysis
– Analysis of the structural loading and design of the fuselage
for maximum momentum storage of the wing energy.
• Communications System Analysis
– Proposed ultra-wide-band (UWB) communications system
will be further evaluated.
• Propulsion System and Propellant
– Additional work is planned for scaling the propulsion
system to operate within the Mars environment. This
includes weight reduction, performance, and types
of fuels.
47. Page 47
Additional Phase II Goals
• Flight Control System
– Evaluation and lay out of an autonomous flight control system
based on the UWB capabilities and or exhaust ultrasonic
emissions
• Power System
– Component lay out of power system based on Phase I results
• Mission Analysis
– Operational issues, science capabilities, lander / rover
interaction, exploration capabilities will be examined
• Development Plan / Cost Estimate
– Establishment of a development plan for identified
technologies. A preliminary cost estimate for the
development and operation of an Entomopter system