Aeronautics and astronautics – Aircraft power plants
Reexamination Certificate
2000-09-08
2002-06-18
Poon, Peter M. (Department: 3643)
Aeronautics and astronautics
Aircraft power plants
Reexamination Certificate
active
06405977
ABSTRACT:
This invention relates to the field of vehicle propulsion systems and more specifically, but not exclusively, to engine intake ducts.
Traditional design techniques and trends within the aircraft industry have led designers to produce aircraft with profiles which use double curvature panels to describe their external lines. The use of such complicated external shapes in the design of both military and civil aircraft has resulted in the need for elaborate and therefore expensive tooling used in both the manufacture of detailed parts, such as the engine intake ducts, and final assembly.
Within the military aircraft industry, traditional design drivers have been for operational performance improvements, however, more recently a switch in emphasis has been towards providing an effective balance between performance improvement and life cycle cost reductions. This new direction in aircraft design has enabled engineers to study the possibilities of eliminating the familiar double curvature airframes and additionally has provided for research into possible new methods of manufacture and assembly for engine intake ducts.
Patent application no. WO 97/22516 describes a method of assembling an aircraft from a plurality of modular structural components. This document discloses an aircraft having a common wing component and common propulsion support frame component, such that several variants of the aircraft, each variant having the different structural qualities necessary to perform different roles, could be assembled from a basic number of common components. Other modular structural components, such as flaps, may be specific to a particular variant of aircraft, and may be fixed to the common basic structure during assembly of that variant. This commonality of airframe parts allows a substantial reduction in the cost of designing and manufacturing aircraft variants requiring different structural qualities in order to fulfil their different roles.
However, it is highly desirable that just one aircraft variant is able to perform a variety of different missions. U.S. Pat. No. 3,640,492 teaches one aircraft structure which is adapted to house a variety of mission specific modules. These modules are interchangeable between the same type of aircraft and can be rapidly replaced in the event of damage or changed if the aircraft needs to be reconfigured for a different mission. Each module contains a different avionics mission system which is electrically connected to the main control system of the aircraft when the module is mechanically installed.
Providing modular mission systems for rapid role changing for different missions is useful, however, one of the prime cost driving elements associated with the final assembly of modern combat aircraft is that relating to the installation of aircraft systems. Whilst mission systems consist primarily of avionics systems, such as laser rangers for weapon delivery, which are designed to carry out specific missions, known aircraft systems are integral to the aircraft and are usually necessary for the general functioning of the aircraft, whatever the mission. The integration and final assembly of aircraft systems such as environmental control systems (ECS), engine systems and fuel systems is arguably the most time consuming and expensive area of final assembly, as well as proving time consuming and expensive in subsequent repair and maintenance, therefore much research has been conducted into the possible reduction in complexity of such systems.
Furthermore, although modular avionics systems allow one aircraft to fulfil a variety of roles, several variants still must be manufactured, for use in, for example, long range missions or those missions requiring a faster, more manoeuvrable aircraft, where it is the integral aircraft systems that need to be varied.
Patent application No. WO 97/22516 describes the building of several aircraft variants using a basic set of common structural components, to reduce the number of different structural components needed to build the family of aircraft. Variant-specific components need to be fixed to the common basic aircraft structure, and these components are also designed to meet the structural requirements of that particular variant.
Patent application No. WO 97/22516 particularly discloses three types of powerplant support systems designed to meet the different propulsion system requirements of three aircraft variants. The powerplant support systems have several components in common, and are designed to form part of the structure of the variant in which they are installed, not being readily detachable.
The present invention seeks to reduce the need for several variants of aircraft for adaptation to different roles and further seeks to reduce the cost and time factors associated with the assembly, repair and maintenance of aircraft propulsion systems.
According to the present invention in one aspect thereof there is provided a modular air intake duct system for a vehicle comprising:
at least one intake duct; and
attachment means for attaching said at least one intake duct to at least one structural member of a vehicle;
wherein said at least one intake duct is adapted to be demountably attached to a load bearing structural member of said vehicle, said at least one intake duct itself being adapted to bear substantially no load; and
wherein said at least one intake duct is modular, said at least one intake duct comprising at least one module.
Preferably said at least one intake duct is demountably located within a structural framework of the vehicle and does not form substantially any part of the external surface of the vehicle. Advantageously the external surface of the vehicle comprises at least one detachable panel adjacent said at least one intake duct for allowing the rapid installation and removal of said at least one intake duct. Preferably said at least one intake duct comprises three modules, these being a rearward duct module, a central duct module and a forward duct module.
The structural framework of the vehicle advantageously comprises at least one shear web, said at least one shear web being load bearing and extending substantially along the length of the vehicle. Said at least one intake duct is preferably adapted to be attached to said at least one shear web, using said attachment means. Preferably there are at least two shear webs.
The attachment means may comprise spigots and brackets. Advantageously said at least one intake duct has spigots fixed thereto.
Advantageously the attachment means further comprises frame members. The frame members preferably comprise at least two portions, each portion being adjacent a shear web and extending in a direction perpendicular to the length of the shear web. Each portion is advantageously detachably fixed to a shear web, and may be fixed using brackets.
The frame members preferably allow an intake duct to be correctly positioned between and adjacent their two portions. The frame members are advantageously adapted to hold the intake duct in a desired position, by means of the spigots fixed to the intake duct and brackets fixed to the frame members and the shear webs. To allow a different size of duct to be installed between the shear webs, the frame members may be detached from the shear webs and may be replaced by frame members of a different size, to accommodate the new duct.
The modules of said at least one intake duct may be advantageously separately removable or installable, leaving the remaining duct modules in position. The brackets are advantageously adapted to allow the spigots of each of the modules to be rapidly released.
It will be seen that using the invention, a modular intake duct of a vehicle may be changed rapidly to accommodate repairs or a role change, by removing said at least one detachable panel and releasing the spigots of all or some of the modules of the duct then replacing these modules with different ones.
At least one powerplant of the vehicle may be changed for a particular mission, and at least one intake duct or module thereof may, in acco
Ash Geoffrey J
House Peter R
Whaites Colin
Bae Systems plc
Jakel Kevin
Nixon & Vanderhye P.C.
Poon Peter M.
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