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Spring 2021

Spike Nozzle Design For Use In Nanosat Orbital Maneuvering Spike Nozzle Design For Use In Nanosat Orbital Maneuvering

Drew Nemeth University of Nevada, Las Vegas, nemetd1@unlv.nevada.edu

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Recommended Citation Recommended Citation Nemeth, Drew, "Spike Nozzle Design For Use In Nanosat Orbital Maneuvering" (2021). Undergraduate Research Symposium Podium Presentations. 10. https://digitalscholarship.unlv.edu/durep_podium/10

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Spike Nozzle Thruster Design for use in Nanosat Orbital Maneuvering

Drew D. Nemeth, RH Thesis Student, Mechanical EngineeringYi-Tung Chen, PhD, Mechanical Engineering, Department ChairWilliam Culbreth, PhD, Mechanical EngineeringDaniel Bubb, PhD, Honors College

Topics Covered

• Fundamental Rocketry Equations• Overview of Nozzles and Designs• Research Motivation• Design Considerations• Proposed Design• Conclusions• Future Work

Fundamental Equations

The law of momentum conservation is the fundamental reason that rocket engines work

[1] m1×v1=m2×v2

Conservation of momentum means a force over time (which is called an impulse) is experienced by a rocket

[1] I=F × t

Since the momentum of a mass increases linearly with its velocity, a higher rocket exhaust velocity, v, leads to a greater impulse

This leads to what is known Tsiolkovsky rocket equation, a fundamental metric for assessing a given rocket’s performance

[1] ∆𝑣=𝑣×ln(𝑚𝑓/𝑚0)

The product of this equation is known as delta v (∆𝑣), and it represents the total velocity change a fully fueled rocket can make

Delta v is important because it defines operational limits of a rocket such as its range, payload, and maneuvering capabilities

Fundamental Equations

So what can make a rocket perform better?

The Tsiolkovsky equation defines at least two methods to improve performance

• Increasing exhaust velocity • Through more efficient engines • More energy dense fuels

• Decreasing dry mass (a lighter rocket)

This research will focus on methods to increase engine efficiency AND reduce unfueled mass in a specific application

Modern state of the art nozzles are DeLaval nozzles, otherwise known as bell nozzles Very efficient when fully optimized [1]Efficiency suffers when operating at non-optimized altitudes [2]

Rocket Nozzles and Designs

Figure 1: visual representation of under and overexpanded flow

Aerospikes, spike nozzles and plug nozzles are different type of nozzle design• They can be optimally efficient at all

altitudes [3]• They can be lighter than bell nozzles [4]

• Their inherent design makes them extremely susceptible to overheating [5]

Spike nozzles are not viable in conditions where sustained engine operation is required [6]

The Aerospike Nozzle

Figure 2: nozzle efficiencies as compared with altitude

Research Motivation

• Continued electronic miniaturization will lead to smaller, cheaper satellites

• These nanosatellites will require maneuvering capacity in orbit

• They will require small, light, inexpensive and easily manufactured thrusters

Additively manufactured spike nozzles may be a good option

for these satellite missions

There will soon come a time where orbital insertion costs fall

well below hardware costs

MISSION TYPES

MOVE-II

Prove a new technology or advance its

Technological Readiness Level (TRL)

TECHNOLOGY DEMO COMMERCIAL RESEARCH EDUCATION

Faraday-1

Aimed at providing payload services

for industries needing low-cost access

to space

TRISAT

Platforms that are aimed at allowing

students to work on a project that makes

it to space. Develops the next generation

of engineers and scientists

IT-SPINS (SpaceBuoy)

Providing a low-cost entry point to

scientific research that must be

performed outside Earth’s atmosphere

REBELSAT-1

In development since mid-2020 (UNLV)

Catalytic monopropellant propulsion using spike nozzle

geometry

10 x 10 x 30 (3U)

First Nevada university satellite

Monopropellant thrusters are common propulsion technologies used in spacecraft.

Though less efficient, they are inherently much simpler than bipropellant engines,

and are well suited for use on small spacecraft with limited missions. These thrusters

may be further improved through the integration of spike nozzles, plug nozzles and

aerospikes. While these nozzles have yet to be tested in space applications,

RebelSat-1 intends to take this first step.

Design Considerations

• Requires a simple system with relatively high Delta V for testing purposes

• The thruster will catalytically decompose a monopropellant

• Must account for safety and availability of monopropellant

• Hydrogen Peroxide was chosen as having a specific impulse while remaining relatively safe

• The complex geometry must be compact and easy to manufacture and prototype

• 3D printed polycarbonate was chosen as the prototype material for the entire system, as it is resistant to hydrogen peroxide and high temperatures [7]

• Eventually print out of steel or titanium

Design Considerations

• Prototypes must operate at low temperatures and pressures for ease of testing

• Hydrogen peroxide can be used at different concentrations, some low enough to safely be used indoors

• Must provide mass, volume or efficiency savings over equivalent bell nozzle

• 3D printing is well suited for providing the precise geometries necessary for reaping the benefits of aerospikes

Proposed Prototype Design

A completely 3D printed thruster system, including 300 cc propellant tank, feed lines and 10N nozzle

• Designed to fit in currently 3D printed chassis

Includes two high pressure solenoid valves for filling and thruster operation

• Operated using RebelSat-1's flight computer

Monitored by an array of pressure transducers at tank, feed line and chamber

Catalytic chamber for decomposing hydrogen peroxide• Decomposed over fine silver mesh

Conclusions

• Aerospike nozzles were found to be a viable alternative to bell nozzles for catalytic small satellite thrusters

• These nozzles are capable of offering reduced nozzle mass and volume in addition to slightly increased efficiency

• A prototype test article was designed, with the eventual goal of testing an aerospike nozzle in space

Future Work

• Test stand design

• Rao contour nozzle redesign

• Prototype manufacture and testing

• Hybrid Thruster (?)

END.

Thank you!

Citations

[1] Sutton, George Paul, and Oscar Biblarz. “Rocket Propulsion Elements : Sutton, George Paul : Free Download, Borrow, and Streaming.” Internet Archive, Hoboken, N.J. : Wiley, 1 Jan. 1970, archive.org/details/Rocket_Propulsion_Elements_8th_Edition_by_Oscar_ Biblarz_George_P._Sutton.

[2] Scott, Jeff. “Ask Us - Nozzle Overexpansion & Underexpansion.” Aerospaceweb.org | Ask Us - Nozzle Overexpansion & Underexpansion, 2005, www.aerospaceweb.org/question/propulsion/q0220.shtml.

[3] Corda, Stephen, et al. “Flight Testing the Linear Aerospike SR-71 Experiment (LASRE).” Researchgate.net, NASA, Sept. 1998, www.researchgate.net/publication/2421935_Flight_testing_the_linear_aerospike_SR-71_experiment_LASRE.

[4] T. Biu, J. R. C. Murray, S. C. A. Bartel and M. Dennet, "Flight Research of an Aerospike Nozzle Using High Power Solid Rockets," 41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2005.

[5] Whitmore, Stephen A., and Isaac W. Armstrong. “Development and Testing of Conventional and Additively Manufactured Aerospike Nozzles for Small Satellite Propulsion.” AIAA Propulsion and Energy 2019 Forum, 2019, doi:10.2514/6.2019-4229.

[6] Blau, Patrick. “GOES-R, S, T, U Spacecraft – GOES-R, S, T, U: Spaceflight101.” GOESR S T U Spaceflight101, Spaceflight101, 2016, spaceflight101.com/goes-r/goes-r-spacecraft/.

[7] https://www.industrialspec.com/images/files/hydrogen-peroxide-material-compatibility-chart-from-ism.pdf