摘要:
An optical assembly for high-G application includes an optical element formed from a brittle material. A rigid frame with a channel surrounds the outer diameter region of the optical element. A compliant material fills the space between the rigid frame and the outer diameter region of the optical element to prevent physical contact between the rigid frame and optical element during a high-G event.
摘要:
The present invention relates to a missile or aircraft with a hierarchical, modular, closed-loop flow control system and more particularly to aircraft or missile with a flow control system for enhanced aerodynamic control, maneuverability and stabilization. The present invention further relates to a method of operating the flow control system.Various embodiments of the flow control system of the present invention involve different elements including flow sensors, active flow control device or activatable flow effectors and logic devices with closed loop control architecture. The sensors of these various embodiments are used to estimate or determine flow conditions on the various surfaces of a missile or aircraft. The active flow control device or activatable flow effectors of these various embodiments create on-demand flow disturbances, preferably micro-disturbances, at different points along the various aerodynamic surfaces of the missile or aircraft to achieve a desired stabilization or maneuverability effect. The logic devices are embedded with a hierarchical control structure allowing for rapid, real-time control at the flow surface.
摘要:
Embodiments include active protection systems and methods for an aerial platform. An onboard system includes one or more radar modules, detects aerial vehicles within a threat range of the aerial platform, and determines if any of the plurality of aerial vehicles are an aerial threat. The onboard system also determines an intercept vector to the aerial threat, communicates the intercept vector to an eject vehicle, and causes the eject vehicle to be ejected from the aerial platform to intercept the aerial threat. The eject vehicle includes a rocket motor to accelerate the eject vehicle along an intercept vector, alignment thrusters to rotate a longitudinal axis of the eject vehicle to substantially align with the intercept vector, and divert thrusters to divert the eject vehicle in a direction substantially perpendicular to the intercept vector. The eject vehicle activates at least one of the alignment thrusters responsive to the intercept vector.
摘要:
The present invention relates to a forebody flow control system and more particularly to aircraft or missile flow control system for enhanced maneuverability and stabilization at high angles of attack. The present invention further relates to a method of operating the flow control system. In one embodiment, the present invention includes a missile or aircraft comprising an afterbody and a forebody; at least one deployable flow effector on the missile or aircraft forebody; at least one sensors each having a signal, the at least one sensor being positioned to detect flow separation on the missile or aircraft forebody; and a closed loop control system; wherein the closed loop control system is used for activating and deactivating the at least one deployable flow effector based on at least in part the signal of the at least one sensor.
摘要:
An on-board guidance system for a flying body, such as a cruise missile, includes a radar device for a self-sufficient scanning of the topography during flight. Scanning antennas provide signals for evaluation and further application in a search and guide logic circuit. An on-board computer calculates an exact horizon angle which is used as an altitude guide or control value.
摘要:
A method for steering solid propellant ballistic vehicles during powered flight which eliminates the requirement for cutoff control by allowing simultaneous fuel depletion and velocity-to-be-gained, V.sub.G, nulling. The vehicle booster is steered along a velocity trajectory of length equal to the remaining velocity capability, V.sub.CAP, which results in a fuel-inefficient trajectory. The trajectory is divided basically into three phases--an exit phase, a fuel-depletion guidance (FDG) phase and a short phase of constant attitude thrusting just prior to final stage burnout. For the exit phase the launch azimuth and the pitch-over magnitude can be varied from their usual fuel-efficient values. During fuel-depletion guidance the additional degree of freedom is the angle, .theta., between V.sub.G and the desired thrust direction, U.sub.S, where: ##EQU1## a.sub.T being the sensed acceleration vector.
摘要:
A position sensor for measuring differential pressure comprising a ring longitudinally restrained on a cylindrical body in proximity to a pair of exit ports diametrically opposed on said cylindrical body; and in communication with a central bore portion in said body and a pressure differential measuring means in communication with said exit ports.
摘要:
A submarine detecting and tracking system which utilizes sonouoys to track both a target submarine and a guided torpedo. The sonobuoy signals are received and processed on a surface vessel or aircraft and the torpedo is guided by remote control to intercept the target submarine.
摘要:
An underwater missile homing system, comprising: two pairs of test thermocouple (TC) junctions, means for mounting one pair of TC junctions on the missile so that they extend laterally therefrom in opposite directions, and means for mounting the other pair of TC junstions on the missile so that they extend vertically therefrom in opposite directions. Guidance means are provided on the missile for guiding the missile in a horizontal direction and in a vertical direction. Means are also provided responsive to signals obtained from the TC junctions for controlling the guidance means, whereby said missile will home in on a sea-going vehicle, in azimuth and elevation, which emits heat in its wake.
摘要:
1. In a homing torpedo having A. A RIGID ELONGATED BODY HAVING AN OUTER SHELL AND HAVING FRONT AND REAR ENDS, B. A DIRECTIONAL TRANSDUCER HAVING AN AXIS OF DIRECTIONALITY, SAID TRANSDUCER BEING DISPOSED WITHIN SAID SHELL AND ROTATABLY CARRIED BY THE RIGID BODY ADJACENT ITS FRONT END, C. MEANS FORMING AN ACOUSTIC WINDOW IN THE FRONTAL SURFACE OF THE OUTER SHELL OF THE TORPEDO OPERATIVELY ASSOCIATED WITH THE TRANSDUCER TO TRANSMIT AND RECEIVE ACOUSTIC SIGNALS, D. MEANS OPERATIVELY ASSOCIATED WITH SAID TRANSDUCER FOR SENDING AN ACOUSTIC SIGNAL TO A TARGET, E. MEANS OPERATIVELY ASSOCIATED WITH SAID TRANSDUCER FOR RECEIVING AN ECHO-SIGNAL RETURNED FORM THE TARGET AND FOR PRODUCING AN ERROR SIGNAL CORRESPONDING TO THE DEVIATION BETWEEN TARGET AND THE AXIS OF DIRECTIONALITY, F. STEERING MEANS CONTROLLED BY SAID ERROR SIGNAL TO CHANGE THE TORPEDO HEADING IN A DIRECTION TENDING TO RESTORE ALIGNMENT OF THE TARGET AND THE AXIS OF DIRECTIONALITY OF THE TRANSDUCER, THE IMPROVEMENTS, IN COMBINATION, COMPRISING; G. MEANS SUPPORTING SAID TRANSDUCER FOR ROTATION SOLELY ABOUT A VERTICAL AXIS OF ROTATION, H. MEANS RIGIDLY COUPLED TO THE TORPEDO BODY FOR SENSING THE ANGULAR VELOCITY AT WHICH THE TORPEDO HEADING CHANGES AND FOR PRODUCING A TRANSDUCER TURNING SIGNAL HAVING AN AMPLITUDE AND SIGNAL POLARITY CORRESPONDING TO THE MAGNITUDE AND ANGULAR DIRECTION OF SAID ANGULAR VELOCITY, AND OPERABLE INDEPENDENT OF MOVEMENT OF SAID TRANSDUCER, I. A REVERSIBLE MOTOR DRIVINGLY CONNECTED TO SAID TRANSDUCER TO TURN SAME ABOUT SAID AXIS OF ROTATION, J. AND CONTROL MEANS CONNECTED TO OPERATE SAID REVERSIBLE MOTOR, SAID CONTROL MEANS BEING RESPONSIVE TO SAID TRANSDUCER TURNING SIGNAL TO TURN THE TRANSDUCER IN AN ANGULAR DIRECTION OPPOSITE TO THE ANGULAR DIRECTION IN WHICH THE TORPEDO HEADING CHANGES AND AT AN ANGULAR VELOCITY PROPORTIONAL TO AND SLOWER THAN THE ANGULAR VELOCITY OF HEADING CHANGE.