Rutgers Engineering Honors Council Keynote Speaker Event

Mike Paluszek gave a talk on the Pluto Orbiter mission to the Rutgers Engineering Honors Council Keynote Speaker Event on March 22, 2016. The talk covered the mission and spacecraft and outlined the design process. Mike also discussed engineering careers and how to make the most of one’s own career.

From a member of the audience, “Just wanted to thank you once more for the wonderful talk you gave last Tuesday evening!”

This is a photo of the group.
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A photo of Mike with the officers.

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Lunar Orbit Insertion Maneuver

New functions in the Lunar Cube module in 2016.1 allow you to easily plan lunar insertion and orbit change maneuvers. In the following pictures you can see a lunar orbit insertion from a hyperbolic orbit. In all figures the lunar terrain is exaggerated by a factor of 10.

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The same maneuver looking down on the orbit plane. The green arrows are the force vectors.

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The following figure shows a two maneuver sequence. The first puts the spacecraft into an elliptical orbit. The second circularizes the orbit.

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Lunar Cube Module for 2016.1

We are adding the Lunar Cube Module in 2016.1 to our CubeSat Toolbox for MATLAB! It allows users to analyze and simulateCubeSats in lunar transfer and lunar orbit. It includes a new dynamical model for CubeSats that includes:

  • Earth, Moon and Sun gravity based on the JPL ephemerides
  • Spherical harmonic lunar gravity model
  • Reaction wheels
  • Thrusters
  • Power generation from solar panels
  • Battery energy storage
  • Variable mass due to fuel consumption
  • Solar pressure disturbances
  • Lunar topographic model
  • New graphics functions for lunar orbit operations
  • Lunar targeting function
  • Lunar mission control function for attitude control and orbit control

The module includes a script with a simulation of a 6U Cubesat leaving Earth orbit and reaching the moon. The following figure shows the Earth to Moon trajectory.

LunarTrajectory

This figure shows the transfer orbit near the moon. The lunar topography is exaggerated by a factor of 10 to make it visible. It is based on Clementine measurements.

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Here are results from the new LunarTargeting function. It finds optimal transfers to lunar orbits. The first shows the transfer path to the Moon’s sphere of influence.

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The next shows the lunar hyperbolic orbit. In this case the transfer is into a high inclination lunar orbit.

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Contact us for more information!

Stofiel Aerospace and Princeton Satellite Systems at CES

Stofiel Aerospace LLC had a display at the Consumer Electronics Show. They invited Princeton Satellite Systems to display its products on their table. The booth is shown in the following picture. You can see Stofiel’s rockets.

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Here is a closeup showing our 3U CubeSat with a camera mounted in one of the bays.

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Members of the Stofiel team:

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More members of the Stofiel team:

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Stofiel Aerospace LLC is an aerospace solutions company created by five U.S. military veterans from Cleveland, Ohio. Stofiel Aerospace LLC is currently developing a portable micro/nano-satellite launch system. Their revolutionary system drastically reduces the wait time for small payloads to reach low Earth orbit to days, not years. By utilizing solid rocket motors and Hydrogen-filled balloons, their system finally offers CubeSat manufacturers and clients the opportunity to be considered a “primary payload” for orbital missions. Currently, they are partnered with the Ohio Aerospace Institute in Cleveland, Ohio and working for further funding to continue development of this industry-changing technology. For inquiries, please contact Jason Beeman, CFO at (440) 994-9035.

Reaction Wheel CAD Project

Hello!

I’m a sophomore at MIT who joined PSS as an extern over Independent Activities Period (IAP). Free to choose how to spend the month of January, students can take an extended vacation,  attend short, intensive classes, do research in MIT’s various labs, etc. Many like myself choose to participate in short internships with MIT alumni – the correct lingo for this type of job experience is “externship”.

I was assigned the task of 3D modeling a reaction wheel for a 25 kg satellite. Essentially, the wheel controls the orientation of the satellite in space. Comprised of a small axial flux motor and a flywheel for added inertia, the wheel sits at 40 mm tall and 80 mm wide. It must spin in both directions, and meet tight dimensional constraints. I believed I really had my work cut out for me.

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SunStation in October

The following image shows SunStation in operation on a bright October day! The load for the day was 12.4 kWh. This includes charging a Nissan Leaf and a Toyota Prius Plugin-in. The total power generated was 40.3 kWh and 21.4 kWh was sold to the grid. As you can see, the installation is much more than carbon neutral with regard to electrical power. It has a gas heating system so is not completely carbon neutral.

OPTICSRE

The orange line is the state of charge for the batteries. The 14.4 kWh of batteries is enough to keep the home running, charge the Prius fully and the Leaf partially, when the grid is down. The system automatically disconnects itself from the grid when there is an outage.

The house itself is fairly energy efficient with mostly LED lights and a few CFLs. The heating system is high efficiency with a 60 W fan that operates most of the time. The house is air-tight and has a whole house air exchange system that operates continuously. The refrigerator is 10 years old and the washer and dryer are less than 10 years old. As you can see, the typical load is 500 W except when the cars are charging. The efficiency could be further improved by installing a state-of-the-art central air system and replacing the refrigerator.

The Nissan Leaf is 100% electric. On a normal day the Prius operates on battery stored energy about 80% of the time. It visits the gas station once every 3 weeks or so.

Besides saving money on power, the system produces 7 Solar Renewable Energy Credits (SRECs) yearly. At current SREC prices, that is about $1500 a year in revenue. The homeowners own the system so all the revenue goes directly to them.

Pluto Spacecraft

Here is a picture of our DFD transfer vehicle. You can see the lander on the front and two Deep Space Optical Communication System (DSOC) assemblies mounted on trusses. There are 2 DFD engines.

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A picture of the Pluto Lander. The solar panels are illuminated by a laser from the orbiter. The lander has a dry mass of 150 kg.

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Both were designed in the Spacecraft Control Toolbox v2015.2.

You can get more information about the Pluto orbital mission on Slideshare.

Pluto Orbiter – the Next Step after New Horizons

The spectacular success of the NASA New Horizons mission has led to many new discoveries about Pluto. The next step would be to send an orbiter. That isn’t easy to do with chemical propulsion but could be done with Direct Fusion Drive.

We’ve done a preliminary mission analysis for a Pluto orbital mission. We are baselining a Delta IV Heavy that can put up to 9,306 kg into interplanetary orbits. These plots show various parameters versus mission duration. The maximum duration is the same as the New Horizons mission, 10 years.

PlutoMission2MW4Yr

Let’s use the 4 year mission as a baseline. It would use a 2 MW DFD engine to reach Pluto in about 4 years and go into orbit. The engine would thrust for 270 days out of the 4 year mission producing 110 km/s delta-V. The trajectory is shown below

PlutoTraj2MW4Yr

Once there, almost 2 MW of power would be available for the science mission, over 10000 times as much power as is available to New Horizons! The New Horizons bit rate is no more than 3000 bits per second. The high power would allow for a bit rate of over 135 Mbps for data transmission back to Earth using the JPL Deep Space Optical Communications System and a 30 kW laser transmitter. The time in transit is much shorter than New Horizons and would produce significant savings on operations costs. Launch times would be more flexible since gravity assists would not be needed.

DFD would use deuterium and helium-3 as fuels. Only 1700 L of helium-3 would be needed for this project. Current U.S. production of helium-3 is 60000 L per year.

Since we would be going all the way to Pluto it would make sense to include a lander. One way to power the lander is using laser power beamed from the orbiter. Here are results for a possible system, beaming over 30 Wh per pass from a 200 km orbital altitude.

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Currently, experiments are taking place in the Princeton Field Reversed Configuration laboratory. Here is the machine in operation at the Princeton Plasma Physics Laboratory:

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The next step is to build a slightly larger machine to demonstrate fusion. Fusion power generation has been demonstrated in the Princeton Plasma Physics Laboratory Tokamak Fusion Test Reactor and the Joint European Torus but never in a machine using helium-3. A flight engine would follow. Its small size would keep the development and production costs down.

DFD would enable many challenging missions include human exploration of Mars, Europa landers and interstellar probes.

Lunar Topography

If you are sending a spacecraft to the moon, you will be interested in lunar topography. A new function in the Spacecraft Control Toolbox lets you superimpose a height map onto any sphere.

MoonTopoThe function RSHMoon.m gives you the Clementine spacecraft topographic data using a spherical harmonic expansion of the rangefinder data.

 

A new function, PlanetWithTerrain.m, lets you superimpose this data onto a sphere.

 

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