Missile Control System Design and Specification for a Long-Range Supersonic Cruise Missile Lockheed Martin Aeronautics Company Advanced Development Programs

Format:

Conference/Event

Author/Creator:

Hostetler, Jeffrey K., author.

Conference Name:

Aerospace Technology Conference & Exposition (2005-10-03 : Grapevine, Texas, United States)

Language:

English

Physical Description:

1 online resource

Place of Publication:

Warrendale, PA SAE International 2005

Summary:

This paper presents an overview of two long-range supersonic cruise missile prototypes and the preliminary design of the Missile Control System (MCS). The MCS provides command and control of all flight-critical subsystems. It is responsible for aerodynamic effector, propulsion flowpath, and embedded digital engine control. The flowpath control system, based on the SR-71flowpath design, includes a movable inlet spike, engine bypass flow control, and ram burner inlet flow valve. The engine controller provides all High Speed Turbojet engine effector commands: variable inlet guide vanes, fuel pumps, and movable exhaust spike. System development leverages model-based specification, design, integration, and verification and validation testing

Notes:

Vendor supplied data

Publisher Number:

2005-01-3379

Access Restriction:

Restricted for use by site license