Abstract: Simulation and analysis of conceptual flight vehicles in an early design phase is conducted in a framework for evaluating performance and control effectiveness that is captured by multiple design parameters modeling the effects of control and disturbance moments and forces acting upon a conceptual flight vehicle along a specified trajectory. Characteristics of multiple types of flight vehicle effectors are modeled as a system and adjusted in such a framework to converge to a controllable air frame configuration for conceptual flight vehicle under static design considerations prior to performing dynamic analyses and control system simulations.

Abstract: The present invention models dynamic behavior of flight vehicles for simulation, analysis, and design. The present invention allows a user to define the complexity of a flight vehicle model, and such models may be simple rigid body models, models of medium complexity, or very complex models including high order dynamics comprising hundreds of structural flexibility modes and variables related to aero-elasticity, fuel sloshing, various types of effectors, tail-wags-dog dynamics, complex actuator models, load-torque feedback, wind gusts, and other parameters impacting flight vehicles. The present invention accommodates and analyzes multiple vehicle and actuator concepts and configurations as defined in flight vehicle input data, which specifies flight vehicle parameters at a steady-state condition for modeling flight vehicle response to dynamic forces and flight control commands with respect to steady state operation.

Abstract: The present invention models dynamic behavior of flight vehicles for simulation, analysis, and design. The present invention allows a user to define the complexity of a flight vehicle model, and such models may be simple rigid body models, models of medium complexity, or very complex models including high order dynamics comprising hundreds of structural flexibility modes and variables related to aero-elasticity, fuel sloshing, various types of effectors, tail-wags-dog dynamics, complex actuator models, load-torque feedback, wind gusts, and other parameters impacting flight vehicles. The present invention accommodates and analyzes multiple vehicle and actuator concepts and configurations as defined in flight vehicle input data, which specifies flight vehicle parameters at a steady-state condition for modeling flight vehicle response to dynamic forces and flight control commands with respect to steady state operation.

Abstract: The present invention models dynamic behavior of flight vehicles for simulation, analysis, and design. The present invention allows a user to define the complexity of a flight vehicle model, and such models may be simple rigid body models, models of medium complexity, or very complex models including high order dynamics comprising hundreds of structural flexibility modes and variables related to aero-elasticity, fuel sloshing, various types of effectors, tail-wags-dog dynamics, complex actuator models, load-torque feedback, wind gusts, and other parameters impacting flight vehicles. The present invention accommodates and analyzes multiple vehicle and actuator concepts and configurations as defined in flight vehicle input data, which specifies flight vehicle parameters at a steady-state condition for modeling flight vehicle response to dynamic forces and flight control commands with respect to steady state operation.

Abstract: The present invention models dynamic behavior of flight vehicles for simulation, analysis, and design. The present invention allows a user to define the complexity of a flight vehicle model, and such models may be simple rigid body models, models of medium complexity, or very complex models including high order dynamics comprising hundreds of structural flexibility modes and variables related to aero-elasticity, fuel sloshing, various types of effectors, tail-wags-dog dynamics, complex actuator models, load-torque feedback, wind gusts, and other parameters impacting flight vehicles. The present invention accommodates and analyzes multiple vehicle and actuator concepts and configurations as defined in flight vehicle input data, which specifies flight vehicle parameters at a steady-state condition for modeling flight vehicle response to dynamic forces and flight control commands with respect to steady state operation.

Abstract: Piezoelectric actuators bonded on S-shaped brackets extending between a support and a payload, improve vibration isolation therebetween by attenuating resonant vibrations under computer dynamic control relying on predetermined dynamic resonant characteristics and H-Infinity control methods. The system can also be used for pointing the attitude of a payload on a supporting platform. Bonded piezoelectric ceramic actuators bend aluminum portions of the brackets to adjust the attitude and position of the payload respecting the support well suited for improved optical communications, observation and telemetry. The system is enables concurrent vibration isolation and directional control.

Abstract: Piezoelectric actuators bonded on S-shaped brackets extend between a support and a payload. The brackets can be used for vibration isolation by attenuating resonant vibrations under computer dynamic control relying on predetermined dynamic resonant characteristics and H-Infinity control methods. The brackets can also be used for platform directional pointing under computer control.