School of Engineering (SoE)
Permanent URI for this community
Browse
Browsing School of Engineering (SoE) by Type "Presentation"
Now showing 1 - 7 of 7
Results Per Page
Sort Options
Item Open Access Airport safety, capacity and investment(2005-07-12T22:30:55Z) Brooker, PeterThe title ‘Airport Safety, Capacity and Investment’ could potentially cover an enormous range of topics and approaches. Techniques used include probabilistic risk analysis, queueing theory, operational research, and cost benefit analysis (CBA). The aim here is both to give an impression of the whole subject and to focus on a few key topics. Surveillance technology plays an important part in delivering safety and capacity, but has to be seen in the larger system picture, particularly when investment is contemplated.Item Open Access Debris mitigation in geostationary earth orbit(Cranfield University; School of Engineering, 2004-12-18T11:04:06Z) Todd, Laura; Bowling, TomThe Inter-Agency Debris Committee recommendation for the reorbiting of geostationary satellites at the end of life involves an altitude increase of no more than 300km for most operational satellites. Although this reduces the collision probability in the geostationary ring itself, it does not remove the possibility of fragmentation debris produced in the reorbital region from passing into the geostationary ring. Unless the satellites are reorbited to a higher altitude than the current recommendations, the debris problem will continue to escalate to an unmanageable level. Due to mass and fuel budgets there are a limited number of available propulsive options, which can achieve the necessary reorbit. The research focus selected has been solar sails and this paper describes ongoing research for the reorbit of geostationary satellites using this method.Item Open Access Development of a relative motion model for satellite formation flying around L2(Cranfield University; School of Engineering, 2004-12-18T10:57:38Z) Roberts, Jennifer A.A technique for satellite formation flying modelling in LEO is applied at L2. Analytical solutions to the equations of motion of a hub satellite relative to L2 are used to define a halo reference orbit. An expression for the gravity gradient is obtained at the hub and the linearised equations of motion of the mirror satellites relative to the hub are derived. The relative motion model is implemented in Matlab/Simulink and evaluated for different initial conditions. The analytical solutions to the equations of relative motion are derived. These and other equations of motion are compared to the Satellite Tool Kit numerical orbit propagator.Item Open Access Dynamic analysis of flexible space shuttle remote manipulator system with large payloads(Cranfield University; School of Engineering, 2005-06-27T15:48:00Z) Wiedemann, Simon M.; Kirk, Colin L.This paper presents a new approach for determination of vibration response of the triply articulated Space Shuttle Remote Manipulator System (SRMS) with large rigid overhanging payloads. In contrast to other researchers dynamic modelling is based on the exact eigenvalue analysis of the two main flexible links with a rigid end effector and payload, including the effect of interaction of the Shuttle. A wide range of SRMS configurations and payloads with joints free and locked is examined for bang-bang slews and with all joints locked for payload positioning using Shuttle thruster firing.Item Open Access Formation flying linear modelling(Cranfield University; School of Engineering, 2005-06-27T16:19:27Z) Izzo, Dario RoccoAn extension of the Hill-Clohessey-Wiltshire equations is presented. The equations refer to the relative motion of two satellites as seen by a Chief undergoing a circular Keplerian motion. Both the Earth oblateness and the air drag are included. The new set of equations is then used to study a simple 100m Leader-Follower formation in a near polar orbit at 600Km of altitude. As the system shows to be linear with time periodic coefficients, Floquet theory is used to determine the stability of the formation and the relative trajectory. Poincar exponents are also determined and discussed.Item Open Access Performance comparison of reusable launch vehicles(Cranfield University; School of Engineering, 2005-06-27T16:11:27Z) Ayre, Mark; Bowling, TomA parameterised generic launch vehicle design is subjected to performance evaluation using the ORBITER model which is capable of optimising both the design and trajectory of the vehicle. The launcher initial mass, flight path angle, velocity and altitude are varied around design points of existing vehicle concepts to investigate the subsequent effect on performance for payload delivery into a 90km by 200km orbit. The performance results suggest that SSTO systems are unfeasible, delivering marginal positive payload performance only when externally accelerated to high speed using a sled mechanism. The optimal vehicle type from a purely performance perspective is deemed to be the TSTO vertically launched configuration.Item Open Access Total System Management: strategic engineering design(2005-07-12T22:33:12Z) Brooker, PeterThe subtitle is ‘Strategic Engineering Design’. The origins of these words are very interesting. ‘Strategic’ is from the Classical Greek for leading an army. Engineering is from the Latin ingenium word for skill. Design has many meanings: an attractive one is to ‘plan and execute artistically’. The discussion here is about the things that need to be done to achieve these very positive words, with engineering used in the widest sense. The main need is for ‘system understanding’ of potential systems.