Accession Number:

ADA056343

Title:

Missile Aerodynamic Parameter and Structure Identification from Flight Test Data

Descriptive Note:

Final rept. Feb-Oct 1977

Corporate Author:

ANALYTIC SCIENCES CORP READING MA

Personal Author(s):

• Kain, James E.
• Brown, Charles M., Jr.
• Lee, Jang G.

Report Date:

1977-11-01

Pagination or Media Count:

205.0

Abstract:

An extended Kalman filter algorithm for aerodynamic parameter identification from missile postflight data is developed and verified for realistic test conditions. The algorithm includes a general purpose six-degrees- of-freedom missile airframe model suitable for representing a variety of missile configurations. Verification studies consider low order linear aerodynamic models and higher order models with extensive nonlinear and pitch-yaw coupling effects. The sensitivity of filter performance to initial conditions, measurement data rate and accuracy, input selection, and modeling errors is investigated. A structure identification technique is used to select the most probable aerodynamic model for a given data set from a group of candidate models. In addition, actual flight test data from a complex aerodynamically controlled vehicle is processed with the filter algorithm. The resulting identified model is shown to be an improvement over the preflight model.

Descriptors:

• *GUIDED MISSILES
• *FLIGHT TESTING
• *KALMAN FILTERING
• *DATA REDUCTION
• COMPUTERIZED SIMULATION
• ATTITUDE CONTROL SYSTEMS
• ACCELERATION
• DEGREES OF FREEDOM
• ERROR ANALYSIS
• AERODYNAMIC FORCES
• SIDESLIP
• MOMENTUM

Subject Categories:

• Test Facilities, Equipment and Methods
• Guided Missiles

Distribution Statement:

APPROVED FOR PUBLIC RELEASE