STRATEGIC GOAL

The strategic goal of the H2 hybrid rocket project is:

• The development of a general purpose hybrid motor, for use in AspireSpace small sounding rockets.

H2 Hybrid Motor Project Plan

Item	July	August	September	October	November	December
Motor Design	TESTBAR
Motor Construction		TESTBAR
Test Stand Construction			TESTBAR
Phase 1 Static Tests				TESTBAR
Static Motor
Phase 2 Static Tests					TESTBAR
Flight Motor

Hybrid Rocket Project Plan

The following project plan timelines refer to the schedule for the construction of a rocket vehicle for low altitude flight testing of the H2 hybrid motor. Low Altitude in this context is taken to be an altitude of 1000 feet above ground level. Altitudes beneath this, are considered insufficient to allow enough margin of error for recovery system deployment. Altitude much greater than this increase the dispersion of the rocket, and thus need a larger launch site.

The purpose of the low altitude flight testing is to (a) Build up flight experience with the H2 hybrid motor, (b) To identify any design flaws which may only show up during flight, and (c) to build up a consistent, and hopefully successful launch track record, to present to potential launch sites and insurers for future higher altitude flights.

The advantages of the low altitude flight testing are that by restricting the altitude to be attained, (a) a smaller launch site can be used, increasing the number of available options for launch sites, (b) the rocket will be recovered faster, thus allowing faster turn-around time, and the possibility of multiple launches on the same day.

The disadvantage of low altitude flight testing are that by restricting the altitude to be attained, there is a smaller margin of error for recovery system failure.

Note, this rocket is not the same as ASRV-3.

Item	July	August	September	October	November	December
Airframe Component Acquisition				TESTBAR
Airframe Construction					TESTBAR
Recovery System Construction				TESTBAR
Avionics System Design	TESTBAR	TESTBAR	TESTBAR
Avionics Component Acquisition			TESTBAR
Avionics System Construction				TESTBAR
Avionics System Testing					TESTBAR
Abort System Design				TESTBAR
Abort System Construction				TESTBAR
Abort System Testing				TESTBAR
Cargo Bay Design and Construction				TESTBAR
To hold rocket mail and payloads
Systems Integration						TESTBAR
Integration of hybrid motor, avionics, airframe, cargo bay and recovery system
Launch Site Search			TESTBAR
For low altitude (1000 feet) private test flights
Launch Site Acquisition				TESTBAR
Rocket Mail Solicitation		TESTBAR	TESTBAR	TESTBAR
Acquisition of rocket mail orders
Rocket Mail Production					TESTBAR

H2 Hybrid Motor Powered Rocket - Launch Plan

The following project plan timelines refer to a tentative schedule for the flight test programme of a rocket vehicle for low altitude flight testing of the H2 hybrid motor, as well as higher altitude testing. The 3 phases of the flight test programme detailed are as follows:

• Low Altitude - Low Altitude in this context is taken to be an apogee altitude of 1000 feet above ground level. Altitudes beneath this, are considered insufficient to allow enough margin of error for recovery system deployment. Altitude much greater than this increase the dispersion of the rocket, and thus need a larger launch site.
• Medium Altitude - Medium Altitude in this context is taken to be an apogee altitude of 5000 - 10,000 feet above ground level.
• High Altitude - High Altitude in this context is taken to be an apogee altitude of 15,000 - 30,000 feet above ground level.

Item	December-97	January-98	February-98	March-98	April-98	May-98
Low Altitude Flight Tests	TESTBAR	TESTBAR	TESTBAR
Private flights restricted to 1000 feet altitude
Medium Altitude Flight Tests			TESTBAR	TESTBAR	TESTBAR
Private flights to 5000-10,000 feet altitude
2 stage Flight Tests				TESTBAR	TESTBAR	TESTBAR
Private flights with solid and hybrid 2nd stages
High Altitude Flight Tests					TESTBAR	TESTBAR
Public flights to 30,000 feet + altitude

Project Plan Information.

This Project plan for the AspireSpace hybrid motor development uses the world wide web to speed up changes over conventional paper based systems. It allows changes to made online, and for all team members with web access (the majority) to be able to see what the current status is of any aspect of the project.

Please note, this project plan is subject to change.

The inclusion of an actual plan for a flight vehicle and future launches are included on the project plan for completeness. Note; This is not ASRV-3, merely a low altitude test vehicle. ASRV-3 may evolve out of the hybrid development, but is not the low altitude test flights.

It is anticipated that the medium and high altitude launches will use identical hardware to the low altitude launcher, with larger oxidiser loads being carried for longer, higher thrust burns. Thus, launches of these vehicles should only be constrained by launch site acquisition and location rather than technical issues.

Wherever possible, the hybrid test vehicle will make use of existing hardware such as the current avionics and telemetry system, and onboard CCD colour video camera - or a derivative of this system.