CFDRC develops multi-physics software technologies and delivers expert engineering design services for a variety of missile and munition systems. Our missiles and munitions services and applications include:
Missile Flight Simulation & Trajectory Analysis
Missile launching, staging, and maneuvering present unique numerical modeling and simulation challenges due to complex geometry, complex physics, and relative motion between the different bodies. CFDRC has developed coupled CFD, 6-DOF and control modules to solve these challenging problems. Our technology provides solutions for an extensive range of missile transient events, including launching, staging, and maneuvering.
- Performed aerodynamic analysis of missile performance at various speeds and angles of attack and validated results using experimental and flight test data
- Developed databases of aerodynamic coefficients for various missiles including shroud separation and missile intercept fragments, and falling debris
- Performed trajectory simulations using the WPAFB code Earth-to-Orbit (ETO) for an air-launched Pegasus-type launch vehicle first stage booster, analogous to a supersonic missile
Weapon Store Separation
CFDRC has performed several studies of weapons store separation for various customers, and for verification and validation of multiple moving bodies coupled CFD and 6-DOF capabilities.
- Developed coupled 6-DOF and CFD methods utilizing automated overset Chimera grid approach. This software technology was incorporated in the commercial CFD-FASTRAN code and was among the first available such capabilities in commercial software
- Performed JDAM store separation from the F/A-18 aircraft
- Performed studies on small diameter bomb separation from F-16 aircraft
- Supported numerous CFD-FASTRAN software customers in their store separation simulations
Missile Propulsion System Trade-off Analysis
CFDRC has developed and demonstrated software expertise in solid rocket motor (SRM) and liquid bipropellant engine design and propulsion system trade-off analyses. We have applied this knowledge to derive optimum motor designs for specific missions balancing thrust turndown and performance efficiency. CFDRC has performed studies of multiple propellants, addressing items such as controls issues at ignition, operation of the motor at near-extinguishment conditions, propellant energy management , thrust vectoring, and throttle control.
- Developed a 3 DOF missile fly-off code called the Global Engine Mission Analysis (GEMA) tool, which evaluates trajectories and weapon flight characteristics among multiple weapons and propulsion system types for comparison against various mission scenarios
- Developed the Axial Pintle MOtor Design (APMOD) tool that features a flow solver with grain design and ballistics modules to model grain geometries
- Developed a MATLAB-based controls software called PINCON to design propellant controllers for motor ignition, combustion, and recovery
- Developed an Air-Turbo-Rocket engine cycle analysis software to compare performance for mono- and bi-propellant missile systems
Canard Covers & Fin Control
Modern military aircraft are designed to provide air supremacy through effective weapons. Trends in weapons designs are to increase packing efficiency through the use of folding fins, and to enhance gliding time through kinematically designed weapons. Deployable fins are employed for projectile stabilization and canards are employed to provide guidance, control and maneuvering capability. CFDRC has developed multi-physics modeling and simulation tools to analyze missile system aerodynamics and the effects of canards and fins for control and maneuverability, as well as to analyze the risks of re-contact and plume impingement during stage separation and canard cover separation.
- Successfully predicted trajectory of jettisoned canard cover, and assessed risk of impact with aft stabilization fins
- Performed analysis to determine minimal pyrotechnic force required to safely jettison a canard cover
- Conducted jettisoned canopy trajectory simulations, with excellent validation with sled test data
Canister Missile Launch Tube Ejection
CFDRC has experience modeling tube-launched missile systems and applying physics-based simulations to characterize the sequence of events from missile ignition to missile ejection to fin and aero surface deployment upon exit of the canister. This type of simulation allows the analyst or design engineer to evaluate potential contact between the missile and the canister and to evaluate the separation dynamics as the missile exits from the canister while accounting for all the physics and body dynamics.
- Performed an axisymmetric coupled CFD/6-DOF simulation for a missile vertical launch from a canister on a ship deck.
- Performed a 2D tube launch simulation for a missile ejecting out of a canister. The thrust forces were specified using a time dependent pressure and temperature profile at the nozzle exit of the missile
- Performed 3D missile staging events for various missile systems (Titan, Arrow, LRALT, SRALT, and others)
Cruise Missile Intercept Simulation
CFDRC has developed a multi-disciplinary missile interception virtual environment for modeling and simulation of the complex interactions between aerodynamic, dynamics, structures and controls.
- Coupling of high-fidelity multi-physics analysis modules for accurate simulations of missile maneuvers
- Analysis of multiple moving bodies, such as staging and control surface maneuvering via fully coupled 6DOF and prescribed motion models with CFD analysis
- Direct coupling with proprietary guidance and control autopilots for closed-loop control simulation maneuvers
- Finite-element structure dynamic analysis of long and short missile concepts
