Computational Optimization of the F-35 External Fuel Tank for Store Separation

Charlton, Eric F.; Davis, M. Bruce

doi:10.2514/6.2008-376

Cited by 13 publications

(5 citation statements)

References 7 publications

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“…The flow simulations presented were performed with Lockheed Martin's Splitflow CFD code a . 10,11 Splitflow is a finite-volume flow solver with up to second-order spatial accuracy, and uses an implicit time marching scheme. Fluxes are upwind differenced for inviscid terms, and Roe's flux difference splitting scheme is employed.…”

Section: Flight Conditions Performance Metrics and Simulation mentioning

confidence: 99%

Numerical Simulations of Busemann Hypersonic Inlets At Finite Flight Angles

Ramasubramanian

Starkey

2008

26th AIAA Applied Aerodynamics Conference

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Complete axisymmetric Busemann inlet bodies with a design Mach number of 6.0 are numerically simulated by the solution of the Euler equations at off-nominal pitch/yaw angles ranging up to 9 •. The inviscid flow solutions are presented graphically, and performance parameters at the throat including pressure recovery, static temperature ratio, static pressure ratio and adiabatic compression efficiency, are found for each flight condition. Simple statistical measures are used to obtain some indications of distortion level at the throat. Compared to the ideal conceptual Busemann inlet, an inlet with a finite leading edge attached to the Busemann compression surface is approximately 10% lower in adiabatic efficiency. Further, when the inlet is turned by 3 • , the compression efficiency decreases again by nearly 10%. At a 6 • flight angle, the adiabatic compression efficiency drops to a mere 42%. When the inlet is finally turned to 9 • , it ceases to meaninngfully function as an inlet and simple computations for the efficiency give unphysical results. Graphical and tabular presentations of the flow solutions for each case are provided and discussed.

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Section: Flight Conditions Performance Metrics and Simulation mentioning

confidence: 99%

Numerical Simulations of Busemann Hypersonic Inlets At Finite Flight Angles

Ramasubramanian

Starkey

2008

26th AIAA Applied Aerodynamics Conference

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“…Previous works have also been devoted to studying the dynamical separation between the carrier aircraft and the space rocket [15], store separation [16], [17], and separation dynamics of air-to-air missiles [18]. The above cases separate the rocket or missile downward.…”

Section: Introductionmentioning

confidence: 99%

Numerical and Experimental Study on Vertical Takeoff and Separation of the Compound Aircraft

et al. 2022

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The traditional technical solution to achieve vertical take-off of the fixed-wing aircraft is adding power components, which will inevitably increase the weight of the aircraft. This paper proposes a compound flight scheme to achieve vertical take-off for the fixed-wing aircraft, using the carrier aircraft with vertical take-off capability to carry the target aircraft. Compared with the vertical take-off performance of a single aircraft, the present scheme enables the target aircraft to have a larger carrying capacity and longer flight distance. In order to verify the feasibility of the current scheme, this paper first investigates the steady aerodynamic performance of the compound aircraft and the dynamical separation process by computational fluid dynamics simulation. The steady lift coefficient of the compound aircraft during the acceleration stage and the unsteady aerodynamic force during the separation stage are obtained and analyzed. Next, an unmanned aerial vehicle (with vertical take-off and horizontal acceleration capabilities) is designed specifically, and the flight experiments of the vertical take-off and separation processes are conducted. Successful separations are achieved many times in the flight tests, which validate the feasibility of the present scheme.INDEX TERMS Compound aircraft, CFD, vertical take-off, dynamical separation of two aircraft.

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“…A great deal of three-dimensional coupled solver based on the unsteady Euler equation and six-degree-freedom rigid body equations have been developed [11][12][13][14] . The coupled solvers have been used to solve the problems of air-to-air missile launching [15] , cluster bomb separation [16] , store separation [17] , store trajectory optimization [18] , store aerodynamic performance optimization [19] and store stability analysis [20] . In order to balance the simulation accuracy and performance, a quasi-steady approach has been implemented to model the dynamic responses of the store separation [21][22] .…”

Section: Introductionmentioning

confidence: 99%

The influence of the elastic vibration of the carrier to the aerodynamics of the external store in air-launch-to-orbit process

Yang

2016

Acta Astronautica

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The separation between the carrier and store is one of the most important and difficult phases in Air-launch-to-orbit technology. Based on the previous researches, the interference aerodynamic forces of the store caused by the carrier are obvious in the earlier time during the separation. And the interference aerodynamics will be more complex when considering the elastic deformation of the carrier. Focusing on the conditions that in the earlier time during the separation, the steady and unsteady interference aerodynamic forces of the store are calculated at different angle of attacks and relative distances between the carrier and store. During the calculation, the elastic vibrations of the carrier are considered. According to the cause of formations of the interference aerodynamics, the interference aerodynamic forces of the store are divided into several components. The relative magnitude, change rule, sphere of influence and mechanism of interference aerodynamic forces components of the store are analyzed quantitatively. When the relative distance between the carrier and store is small, the interference aerodynamic forces caused by the elastic vibration of the carrier is about half of the total aerodynamic forces of the store. And as the relative distance increases, the value of interference aerodynamic forces decrease. When the relative distance is larger than twice the mean aerodynamic chord of the carrier, the values of interference aerodynamic forces of the store can be ignored. Besides, under the influence of the steady interference aerodynamic forces, the lift characteristics of the store are worse and the static stability margin is poorer.

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Computational Optimization of the F-35 External Fuel Tank for Store Separation

Cited by 13 publications

References 7 publications

Numerical Simulations of Busemann Hypersonic Inlets At Finite Flight Angles

Numerical Simulations of Busemann Hypersonic Inlets At Finite Flight Angles

Numerical and Experimental Study on Vertical Takeoff and Separation of the Compound Aircraft

The influence of the elastic vibration of the carrier to the aerodynamics of the external store in air-launch-to-orbit process

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