Correlation of HIFiRE-5a Flight Data with Computed Pressure and Heat Transfer

Joseph S. Jewell; James H. Miller; Roger L. Kimmel

doi:10.2514/1.a33725

Temperature Prediction Methodology for a Missile Flying at Low and High Altitudes

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.592-594.1794 ◽

2014 ◽

Vol 592-594 ◽

pp. 1794-1800

Author(s):

G. Vijayakumar ◽

Ashwani Kumar Kachroo

Keyword(s):

Heat Transfer ◽

Heat Flux ◽

Wall Temperature ◽

Thermal Environment ◽

Three Dimensional ◽

High Rate ◽

Heat Transfer Analysis ◽

Vehicle Speed ◽

Time Duration ◽

Flight Data

Missiles fly at supersonic and hypersonic speeds. Airframe forms the aerodynamic shape of the missile and houses several components essential for mission with suitable structural supports. The missile airframe is subjected to high rate of heating caused by kinetic heating due to very high vehicle speed. Heat transfer analysis of the missile airframe structure is required to be performed for wall temperature predictions to select the material of missile construction with suitable wall thickness and also to check design adequacy for ensuring the safe operation in the severe thermal environment experienced during flight. This paper describes the methodology of evaluation of heat flux distribution over missile wall, prediction of missile wall temperature distribution considering airframe as heat sink and validation of the methodology against flight data. Heat flux has been estimated using classical engineering methods for both stagnation as well as off-stagnation regions including the effect of angle of attack, rarified flow, thermal radiation and solar heating. Transient three dimensional heat transfer analysis with convective and radiative boundary conditions has been carried out for predicting the missile wall temperature profiles. Parametric study has been carried out, considering various parameters such as material of construction, thickness and time duration. The prediction methodology has been validated and a close match is observed between the predictions and flight data.

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Correlation of HIFiRE-5b Flight Data With Computed Pressure and Heat Transfer for Attitude Determination

47th AIAA Fluid Dynamics Conference ◽

10.2514/6.2017-3133 ◽

2017 ◽

Cited By ~ 7

Author(s):

Joseph S. Jewell ◽

Roger L. Kimmel ◽

Jonathan Poggie ◽

Kevin Porter ◽

Thomas J. Juliano

Keyword(s):

Heat Transfer ◽

Attitude Determination ◽

Flight Data

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Thermal Management Solutions for enhanced Digital Flight Data Acquisition Unit in Avionics Applications

International Symposium on Microelectronics ◽

10.4071/isom-2015-wp64 ◽

2015 ◽

Vol 2015 (1) ◽

pp. 000517-000525

Author(s):

Vicentiu Grosu ◽

Chris Lindgren ◽

Tamas Vejsz

Keyword(s):

Heat Transfer ◽

Data Acquisition ◽

Thermal Management ◽

Airline Industry ◽

Airflow Rate ◽

Confined Space ◽

Flight Data ◽

Conjugated Heat Transfer ◽

Data Acquisition Unit ◽

New Generation

According to the Federal Aviation Administration, the commercial airline industry should expect to see the number of passengers traveling per year to grow from its current level of 750 million to nearly 1 billion by 2030. To meet this demand, airlines are placing orders for thousands of new aircraft over the next decade and beyond. With this increase in airline traffic, newer aircraft systems will generate an ever increasing amount of data per flight, data that allows airlines to further enhance their flight operations, flight safety, and reliability. For commercial avionics, the migration of the data acquisition and reporting functions from the traditional interface environments to newer, faster, and more network-centric architectures is creating a new generation of “smart” aircraft. Teledyne Controls' enhanced Digital Flight Data Acquisition Unit is an integral part of a new generation of aircraft and combines the functions of Mandatory Data Acquisition and Recording with a sophisticated Aircraft Conditioning Monitoring System that the aircraft operator uses to monitor the performance and reliability of each aircraft in its fleet. Some of the critical goals in the development of the Digital Flight Data Acquisition Unit are reducing the size and weight over previous generations, while maximizing performance and reducing cost. All of these opposing requirements make the design and fabrication very challenging. One such challenge includes dissipating high power in a confined space, and this makes thermal management a critical component of the overall LRU (line-replaceable unit) design. In addition, to increase the reliability over the lifespan of the unit, passive cooling systems are often required in place of internal fans. This presents another set of challenges, such as optimizing the airflow provided by the aircraft in the electronics bay compartment. This paper will present some of the critical elements in thermal management such as heat sinks, components placement, thermal interface materials, thermal vias, thermal links, packaging approaches and cooling strategy. The design and optimization of the system are based on analytical solutions, conjugated heat transfer and experimental results. The LRU should safely operate under various environmental conditions: ground operation, flight operation, high operating temperature and loss of cooling air where each environmental condition has different parameters for coolant airflow rate, effect of the surroundings, and ambient and coolant air temperature. Draw-Through and Blow-Through cooling analysis were performed using CFD (Computational Fluid Dynamics). The thermal analysis problems solved are conjugated heat transfer for laminar flow with radiation in steady-state or transient regimes. Multiple approaches were identified to remove heat from the critical components through optimization of the components and subsystems. These same approaches can also be used to increase the system's performance and reliability.

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