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Overview

Project Hermes is the team's entry to the 2018 IREC Unlimited Category. It is entirely SRAD. The design was conceived during summer of 2017. It is a single stage, 6in, minimum diameter rocket with a single separation point.current project, intended to prove our ability to build a rocket capable of flight at multiple times the speed of sound to altitudes close to 100kft. 

 Flight History:

Flight
Vehicle
Motor
Launch Site
Date
Result

Hermes Flight Test 1

Hermes 1Raziel PathfinderL1335Berwick, ME November 11, 2017Pending 

 

 

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Link to Concept Design Review: Concept Design Review.pptx

Responsible Engineers Listed Here.

Mass Budget here.

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June 2017 - Present
Leveraging existing technology for extreme performance
Liftoff Mass: ~175 lbs
Propellant Mass: ~85 lbs
Maximum Velocity: ~Mach 3.5
Maximum Apogee: ~ 80,000ft
Maximum Acceleration:

Table of Contents

OW-152-4G #3Friends of Amateur RocketryJuly 21, 2018Success
Hermes Flight 2Hermes 2P9100 #2Friends of Amateur RocketryJuly 6, 2019Anomaly
Hermes Flight 3Hermes 3P9100 #3Friends of Amateur RocketryJanuary 18, 2019Anomaly

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(March 2019 CAD)

 

Link to integration procedure: Hermes 1 Integration Procedure

Leadership

2017-2018
Leadership
President
VP
Treasurer
Social Chair
Pub. Chair
Charlie GAndrew RIsaac PMaddie JJoanna Z
StructuresPayloadRecoveryPropulsionAvionics
Matthew CMaddie GMaddie JSam AJosef B
2018-2019
President
VP
Treasurer
Chief Engineer
Pub. Chair

Andrew A (Fall)

Julia G (Spring)

Katie K

Julia G (Fall)

Cici M (Spring)

Andrew R

Charlie G (Fall + Spring)

Shannon C (Spring)

StructuresPayloadRecoveryPropulsionAvionics
Dayna EJuan SJakob C/Maggie ZEthan SZack H
2019-2020
President
VP
Treasurer
Chief Engineer
Pub. Chair

Julia G

Katie K

Cici M (Spring)

Jakob C

Diane R

StructuresPayloadRecoveryPropulsionAvionics
Tina/MaxJacob MClaire BVittorio CLuka G

Subsystems

Preliminary Design Review: Preliminary Design Review.pptx

Recovery System

The Hermes recovery system is a piston-actuated, single separation-dual deploy architecture.

Propulsion System

Hermes 1 Propulsion System (8-grain) is an eight-grain custom solid rocket motor that will provide propulsion for the vehicle.

Structures System

The Hermes Structures system.

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June 2017 - Present
Liftoff Mass: 177 lbs
Propellant Mass: 74 lbs
Maximum Velocity: ~Mach 3
Maximum Apogee: ~ 80,000ft
Maximum Acceleration:

Table of Contents

Vehicles

Hermes 1

Hermes I is the first build of a flight-ready Hermes rocket. The structures team delivered an all-composite minimum diameter fin can. Andrew A. constructed a hexagon Avionics Tower, which wrapped around the recovery team's high-altitude-ready piston deployment system. The propulsion subteam prepared and proved a 4 grain 152mm diameter motor for the flight. The rocket was designed to work with an 70KNs motor but was modified to accommodate the 35KNs motor it flew on by putting a motor retention bulkhead into the middle of the air frame. This rocket flew Hermes Flight 1 before being retired to the Rocket Garden in the Unified Lounge.

Responsible Engineers Listed Here.

Mass Budget here.

This rocket was originally envisaged as flying in the 'Unlimited Category' at IREC 2018. Deliverables below:

Project Hermes_Entry Form.xls

200_1st Progress Update.xls

 

Link to vehicle page

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Hermes 2

Hermes II is an iterative improvement on the Hermes I design, intended to eventually serve as a first stage for a spaceshot. The airframe has seen significant upgrades since the Hermes flight, including a simplified avionics bay design, ablative leading edges on the fins, and a shift to a sub-minimum diameter design. More of the rocket structure will be built by the team compared to Hermes I, including the nosecone. The rocket flew on a 74 KNs motor.

The rocket shredded during Hermes Flight 2

 

 

Link to vehicle page

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Hermes 3

Hermes III is an iterative improvement on Hermes II, intending to complete the Hermes II flight profile on a reduced timescale. The mission package design was mostly the same as for Hermes II. Some hardware was removed, including the load cell from the forward closure of the motor. The payload bulkhead was significantly redesigned, and process improvements for structural parts were introduced. Hermes III used an aluminum fin can, and flew on the same design of motor from Hermes II.

The rocket shredded during Hermes Flight 3. Most of the hardware was recovered.

Hermes III overview

Hermes Flight Readiness Review

Link to vehicle page

Vehicles

Raziel Pathfinder

Raziel Pathfinder was an unflown Test Article from 2016-2017's Project Raziel. After undergoing extensive modifications, the pathfinder was uprated to flight hardware. The construction of this vehicle is primarily E-glass. Early manufacturing limitations limit the maximum length of any tube produced using the old methods to 24in, so the fin can is held together with a coupler. Some of the tubes are distinctly out of round due to a low-quality mandrel used for initial production runs. The nosecone is a modified COTS gelcoat covered 4:1 Ogieve nose cone.

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