Department of
Mechanical and Industrial Engineering

University of Minnesota Duluth

Hybrid
Experimental
Rocket
Motor
Evaluation
System

Project H E R M E S

Hybrid
Experimental
Rocket
Motor
Evaluation
System

Hermes
Wing-footed messenger
of the gods

UROP 2012 Tests

Date
Injector Description
View Video
(Flash)
Download Video
(WMV)
Data
(log)
Data (Xcel)
    NOS_2 NOS_2 UROP_100 UROP_100
    NOS_3 NOS_3 UROP_101 UROP_101
    NOS_4 NOS_4 UROP_102 UROP_102

Recent Tests

Date
Motor
Designation
Fuel Grain
length/OD/ID (in.)
Injector
i.d.(in.)/angle
Ex. Nozzle
i.d.(in.)/geom.
Peak Thrust
(lbs)
Burn Time
(sec.)
Data
Plots
Video
of Test
5/20/05 ERM-02C 7.125/1.5/0.7 0.072/120 0.31/bell 31.8 8.3 Thrust ERM_02C.avi
5/20/05 ERM-02B 7.125/1.5/0.7 0.055/60 0.31/bell 22.5 4.6 Thrust ERM_02B.avi
5/9/05 ERM-02A 7.125/1.5/0.5 0.055/60 0.31/bell 26.2 9.5 Thrust ERM_02A.avi
5/6/05 Big_Boy2 18.65/1.866/0.77 0.111/0 0.23/bell 38.8 11.0 Thrust
Temperature
Pressure
Big_Boy2.wmv
5/4/05 Big_Boy1 18.65/1.866/0.77 0.125/0 0.23/bell 40.6 8.0 Thrust
Temperature
Pressure
Big_Boy1.avi
5/20/05 ERM-01I 11.125/1.5/0.5 0.109/60 0.31/bell 38.4 5.7 Thrust ERM_01I.avi
5/20/05 ERM-01H 11.125/1.5/0.7 0.109/60 0.31/bell 42.6 10.0 Thrust ERM_01H.avi
5/13/05 ERM-01G 11.125/1.5/0.7 0.082/60 0.31/bell 41.3 9.0 Thrust none
5/9/05 ERM-01F 11.125/1.5/0.5 0.072/60 0.31/bell 36.9 8.8 Thrust ERM_01F.avi
4/29/05 ERM-01E 11.125/1.5/0.5 0.055/60 0.25/conv-div 17.6 11.5 Thrust ERM_01E.mov
4/28/05 ERM-01D 11.125/1.5/0.5 0.043/60 0.25/conv-div 13.4 5.5 Thrust ERM_01D.avi
4/27/05 ERM-01C 11.125/1.5/0.5 0.043/60 0.36/conv-div 8.3 6.0 Thrust ERM_01C.avi
4/22/05 ERM-01B 11.125/1.5/0.5 0.043/60 0.50/straight 14.8 4.0 Thrust ERM_01B.avi
4/20/05 ERM-01A 11.125/1.5/0.5 0.043/60 0.50/straight 10.1 3.5 none ERM_01A.avi
3/15/05 Igniter (H) 1.0/1.5/0.5 N/A N/A N/A 6.0 none IGN_Horz.avi
3/15/05 Igniter (V) 1.0/1.5/0 N/A N/A N/A 12.0 none IGN_Vert.avi

Project Goals:

  1. Develop, design, build, and test a functional and safe hybrid rocket motor by December 2007 with the following characteristics:
    • Thrust:
    • Burn time:
    • Maximum combustion chamber pressure:
    • Maximum combustion chamber temperature:
    • Launch weight:
    • Motor initial cost:
    • Cost per launch:
  2. Develop, design, build, and test a hybrid-powered recoverable, reusable, sounding rocket by June 2008 with the following characteristics:
    • Launch weight:
    • Payload weight::
    • Maximum acceleration:
    • Maximum velocity:
    • Maximum altitude:
    • Vehicle initial cost:
    • Cost per launch:

Research and Development Areas:

Personnel:

Faculty Support:

Test System Design and Integration

  • Spring 2005
    • Rosanna Belanger, Laboratory Supervisor
    • John Cirilli
    • Josh Line
    • Luke Schwartz
  • Fall 2004
Rocket motor design
  • Spring 2005
    • Tony Pike, Laboratory Supervisor
    • Jim Artmann
    • Ryan Erickson
    • Nate Hartman
Undergraduate research projects
  • Spring 2005
    • Jeff Rogers

Hybrid Rocket Links:

Hybrid Rocket Science:

Commercial Hybrid Rocket Motors:


Hermes
Wing-footed messenger
of the gods
Copyright 2005, University of Minnesota, Duluth.
The University of Minnesota is an equal opportunity educator and employer.
This website maintained by The Department of Mechanical and Industrial Engineering
Send comments or questions by e-mail to Dr. Ryan Rosandich.
Last modified: 2/10/2005