The operation of an ideal rocket, thrust equations, characteristic nozzle velocity, effective exhaust velocity.

Characteristics of a solid propellant, particularly composite propellants and the effect of light metal addition.

Specific impulse and calculation from Thrust vs Time graphs.

Estimation of charge mass dependent on grain geometry and burning regime. Vieille’s Law.

Methods of casing construction, calculation of casing dimensions and mass.

Nozzle area ratios, nozzle construction and throat protection.

Contribution of additional elements such as igniters, case bonding, flanges, inhibitors.

An assignment weighted at 100% and length 3000 words consisting of an estimation of a rocket motor dimensions and weight based on a given requirement and Thrust vs Time graph.
Demonstrates achievement of University of Staffs learning outcomes 1, 2, 3 and 4.

Distance Learning through Blackboard VLE. Stages in the process to be explained and demonstrated with student tasks leading to the completion of a full first iteration motor design.

American Institute of Aeronautics and Astronautics (2000). Solid Propellant Chemistry, Combustion and Motor Internal Ballistics. New York: AIAA.

Rudolf X Meyer (1999). Elements of Space Technology. London: McGraw Hill

Gordon C Oates (1997). Aerothermodynamics of Gas Turbine and Rocket Propulsion.

Library facilities
Blackboard VLE

1) Demonstrate a systematic understanding of the principles behind the rocket and solid propellants. (Knowledge and Understanding).
2) Demonstrate an understanding of the uncertainties and limits of the design process by carrying out an iterative design of a small rocket motor. (Learning).
3) Demonstrate a critical awareness of the limitations and evaluation of level of accuracy in the design process and relate this to the required level of accuracy. (Analysis).
4) Communicate conclusions clearly in written form to specialist and non-specialist audiences. Use other forms of communication to check and verify assumptions. (Communication).