Title

Transient And Nonlinear Effects On High Speed, Vibratory, Thermoelastic Instability Phenomena. Part II Aerothermoelastic Applications

Description

This report investigates the equations representing the dynamic, torsion-bending motion of a wing which is one major component of an ultra-high performance manned vehicle. Preliminary work required for this investigation is included as an integral part of the report. This preliminary work includes (1) the derivation of an exact two-dimensional linearized aerodynamic theory for an accelerating unsteady supersonic airfoil, (2) the re-derivation of "piston theory" aerodynamics for arbitrary motion, and (3) a derivation for the torsional stiffness loss of an aircraft wing that includes the effects of a specified time-dependent wall temperature due to the given flight mission and that includes the effects of mid-plane stretching.The computer studies consider "super X-15" type wing performing two specified flight missions and provide answers in the form of pitch and plunge impulse response time histories. The "exact" solutions are compared with two approximate solutions. The results of the comparisons indicate a quasi-steady aero-thermoelastic analysis is adequate for manned vehicles of the foreseeable future. This statement does not apply to the dynamic stability analysis (rigid-body) of these vehicles since their lower rigid-body frequencies permit a moderate to strong coupling between the governing equations and their time-varying coefficients.

Date

1960

Index Abstract

Contrails and DTIC truncated

Photo Quality

Not Needed

Report Number

WADD TR 60-484 Part II

Corporate Author

Aeroelastic And Structures Research Laboratory, Massachusetts Institute of Technology

Laboratory

Flight Dynamics Laboratory

Extent

22

Identifier

AD0266375

AD0266375

Access Rights

OTS

Distribution Classification

1

Contract

AF 33(616)-6185

DoD Project

1370

DoD Task

13478

DTIC Record Exists

Yes

Distribution Change Authority Correspondence

None

Report Availability

Full text available

Date Issued

1960-12

Abstract

This report investigates the equations representing the dynamic, torsion-bending motion of a wing which is one major component of an ultra-high performance manned vehicle. Preliminary work required for this investigation is included as an integral part of the report. This preliminary work includes (1) the derivation of an exact two-dimensional linearized aerodynamic theory for an accelerating unsteady supersonic airfoil, (2) the re-derivation of "piston theory" aerodynamics for arbitrary motion, and (3) a derivation for the torsional stiffness loss of an aircraft wing that includes the effects of a specified time-dependent wall temperature due to the given flight mission and that includes the effects of mid-plane stretching.The computer studies consider "super X-15" type wing performing two specified flight missions and provide answers in the form of pitch and plunge impulse response time histories. The "exact" solutions are compared with two approximate solutions. The results of the comparisons indicate a quasi-steady aero-thermoelastic analysis is adequate for manned vehicles of the foreseeable future. This statement does not apply to the dynamic stability analysis (rigid-body) of these vehicles since their lower rigid-body frequencies permit a moderate to strong coupling between the governing equations and their time-varying coefficients.

Provenance

Lockheed Martin Missiles & Fire Control

Type

report

Format

1 online resource (xv, 117 pages) : ill.

Subject

Airframes

Computers

Deflection

Elastic Properties

Hypersonic Vehicles

Manned

Integral Transforms

Plastic Properties

Artificial Satellites

Spacecraft

Stability

Vibration

Wings

Publisher

Wright-Patterson Air Force Base, OH : Wright Air Development Division, Air Research and Development Command, United States Air Force

Distribution Conflict

No

Creator

Brunelle, Eugene J., Jr.