FlightGlobal.com
Home
Premium
Archive
Video
Images
Forum
Atlas
Blogs
Jobs
Shop
RSS
Email Newsletters
You are in:
Home
Aviation History
1957
1957 - 1137.PDF
16 August 1957 225 CENTRALIZING CENTRALIZING SPINDLE BEVELLED CENTRALIZING RING ,OUTER GIMBAL ^PICK-OFF COILS COMMON EARTH TERMINAL LUGS FOR FINATTACHMENT RUBBER SECTION OF STUB FAIRING SHOWING SPRING LOADED CONTACTS IGNITER ASSEMBLY AIRCRAFT ATTACHMENT PLATE TIE BAR MAGNETIC INSERT DAMPING CUP ATTACHMENT PLATE FOR SEPARATION UNIT FAIRING STUB FAIRING "ATTACHMENT LUGSFOR SEPARATION UNIT FIN ATTACHMENT '• HOLES PLATE QYRO BULKHEAD INNER GIMBAL v FIRING INTERLOCK SWITCH Booster separation is based upon a twin-piston breechblock with a cordite charge. When both are "all burnt" a firing pulse is passed to an igniter and pressure builds up in the cylinder,^ thus shearing a pin and allowing the boosts to separate. The separation unit (below) is attached to the boosts with Pip pins. NOZZLE BLOCK :ontrol instrument sub-assembly. The two I in the pitch and yaw axes, and a roll inertia during the coasting phase. One eters is not shown. production and service test gear) and a sub-divided control depart- ment. One of the two sections covers the missile guidance system and the other the ancillary guidance services. The head of this department is responsible for the missile as a servomechanism, for the design of missile instrumentation and for the design and operation of analogue computers and simulators. Within this organizational arrangement there is also a project engineer system; for each specific project an engineer is appointed to be responsible for technical co-ordination and progress. The Fireflash project engineer was Mr. P. H. Curnow. The problems of guided weapons engineering, which at first sight may appear to have much in common with aircraft design, are in many respects quite different. Although it may be argued that both aircraft and missiles are fundamentally vehicles for conveying a load from one point to another as efficiently as possible, there are important differences in their systems of control and the amount of integration between the various com- ponents that must be used. So stringent are the demands of missile engineering in this respect that failure to appreciate the space or functioning requirements of any part of the concept can only result in a severe loss of efficiency. While in an aircraft room can generally be found for one more essential "black box," the integration of components in a missile is such that there is little likelihood that there will be space to spare for second thoughts on the sizes of its components. But it is naturally in their controlling intelligences that the major differences lie, since the function of "closing the servo loop" performed in an aircraft by the pilot must be replaced by a closed-loop guidance system in the missile; that is, apparatus, either external or within the missile, to detect whether it is accurately on course to_ the target, measure the error between the actual course of the missile and die required course, and inform BOOST ATTACHMENT IGNITER EARTH RETURN CONTACT COMMUNICATING BORE IGNITER SUPPLY CONTACT
Sign up to
Flight Digital Magazine
Flight Print Magazine
Airline Business Magazine
E-newsletters
RSS
Events
