36 results about "Missile defense" patented technology

The multi-target tracking and discrimination system (MOST) fuses with and augments existing BMDS sensor systems. Integrated devices include early warning radars, X-band radars, Lidar, DSP, and MOST which coordinates all the data received from all sources through a command center and deploys the GBI for successful interception of an object detected anywhere in space, for example, warheads. The MOST system integrates the optics for rapid detection and with the optical sensor array delivers high-speed, high accuracy positional information to radar systems and also identifies decoys. MOST incorporates space situational awareness, aero-optics, adaptive optics, and Lidar technologies. The components include telescopes or other optical systems, focal plane arrays including high-speed wavefront sensors or other focal plane detector arrays, wavefront sensor technology developed to mitigate aero-optic effects, distributed network of optical sensors, high-accuracy positional metrics, data fusion, and tracking mounts. Field applications include space monitoring, battlefield artillery, battlefield management, ground defense, air defense, space protection, missile defense, gunfire detection, and the like.

A fire control system for a boost phase threat missile includes sensors for generating target-missile representative signals, and a multi-hypothesis track filter, which estimates the states of various target hypotheses. The estimated states are typed to generate hypotheses and their likelihoods. The states, hypotheses and likelihoods are applied to a multihypothesis track filter, and the resulting propagated states are applied to an engagement planner, together with the hypotheses and likelihoods. The engagement planner initializes the interceptor(s). Interceptor guidance uses the initialization and the propagated states and typing information to command the interceptor.

A technique is provided that uses a dual mode seeker (IR and LADAR) for precise target dynamics measurement, which extends stripping to a much higher altitude than ground based radar. Initial results show that this approach works to altitudes in excess of 100 km. Stripping becomes a reliable way to discriminate lighter weight decoys from reentry vehicles at altitudes and ranges consistent with planned divert capabilities for terminal phase missile defense. It is a finding of this invention that the LADAR will improve the spatial resolution by a factor of five over typical missile defense IR seekers using a common aperture. The LADAR provides a 3D angle, angle, range (AAR) image for each laser pulse which is used to extract the precise target state vectors.

The system and apparatus of the present invention is generally comprised of a non-dedicated, temporarily installed, aircraft observer bubble door, chair, sonotube ejection system, mission electronics LRU rack and workstation assembly which are affixed to the Air Deployment System (ADS) rails, cargo tie down “D” rings, seat belt restraint ring bolt sockets, and litter bar of a host aircraft, thereby precluding the requirement for dedicated airframe modifications. One embodiment of the present invention also utilizes a multi-axis, articulated, foldable chair temporarily installed in conjunction with a segmented or one piece pressurized observer bubble door plug and door retraction system. The door plug assembly is designed to accommodate the simultaneous use of a sonotube stores launch system, a missile defense system, and an observer bubble window. The door plug also accommodates fitment around the envelope of a special mission strut which extends through the interior to the exterior of the host aircraft beneath the door plug's lower periphery. The door plug is also moveably mounted within a temporary retraction rail system which interfaces mechanically to the permanent door retraction rails and the aircraft floor or ADS rail system. When the host aircraft is not equipped with an ADS rail system, the retract rails, chair stanchion, mission electronics racks, and workstation assemblies are mounted to an adaptive floor plate (AFP) which can be modified to interface with various cargo floor “D” rings, or other cargo tie down mechanisms and bolt patterns such that several types of dissimilar aircraft can utilize the subject apparatus either with or without ADS rails installed. Once installed the subject apparatus can be stowed outboard of the fuselage cargo transit envelope to permit use of the ADS rail system in-flight, without affecting normal air drop operations, crew egress, the flight performance envelope, or emergency procedures of the host aircraft.

A fire control system for a boost phase threat missile includes sensors for generating target-missile representative signals, and a multi-hypothesis track filter, which estimates the states of various target hypotheses. The estimated states are typed to generate hypotheses and their likelihoods. The states, hypotheses and likelihoods are applied to a multihypothesis track filter, and the resulting propagated states are applied to an engagement planner, together with the hypotheses and likelihoods. The engagement planner initializes the interceptor(s). Interceptor guidance uses the initialization and the propagated states and typing information to command the interceptor.

Pulsed detonation engines (PDEs) are adapted for use in reaction control systems (RCS), such as thrusters for orbital correction and control (e.g., for earth-orbiting satellites), divert thrust generation and control for space-based interceptor devices, and for missile trajectory correction and motion control. According to one aspect of the invention, PDEs are adapted for motion control of so-called “kill vehicles,” which are small devices, typically launched from satellites, for strategic missile defense.

A method for accurately determining whether a response tool will be effective for responding to a given enemy threat object. Embodiments described herein provide a method and system for responding to a threat object, for example, negating missile threats. Embodiments may include validating effectiveness of a response to the threat object. Other embodiments may include verifying the continued effectiveness of a response to the threat object. Further embodiments may include providing feedback to re-perform the method for responding to the threat object. The system may include a mathematical method, and associated algorithms, to assess, in an automated fashion, the performance of non-kinetic techniques with respect to negating the threat object.

The invention belongs to the field of force utilization of air defense and anti-missile weapons and equipment, and in particular relates to a method for analyzing the force scale demand of ground air defense weapons. The present invention takes the air defense confrontation between the enemy and the enemy as the background, and comprehensively considers factors such as the enemy's attack direction, the tactical and technical indicators of the enemy's weapons, the combat use mode, the characteristics of different defensive locations or areas, different firepower connection conditions, and different firepower density requirements. , analyze and calculate the force scale and structure requirements of ground air defense weapons in three basic combat deployment styles of ring, sector and linear for different defense areas, and construct the analysis and calculation model of ground air defense force scale structure, which is aimed at single type and multiple types respectively Mixed ground air defense weapons calculate the force scale requirements, and obtain a reasonable number of troops and equipment structure required for ground air defense weapons to defend a specific target, effectively improving the coordination efficiency of the ground air defense firepower network and the effectiveness of comprehensive defense operations.

The invention belongs to the technical field of missile defense, and particularly relates to a remote interception launch data acquisition method and system based on a single-sided launch table, and the method comprises the steps: constructing a remote interception missile pseudo-six-degree-of-freedom trajectory calculation model, and determining an interception region boundary of an interception missile according to the interception capability and conditions of the interception missile; obtaining the maximum negative attack angle of each trajectory according to the number of the intercepted trajectories and the boundary of the intercepted region of the intercepted projectiles; based on the average launching point and launching azimuth angle values and the maximum negative angle of attack of each trajectory, generating a general single-sided launching table of a fixed launching azimuth angle by using a trajectory calculation model; and according to the single-sided firing table and the target prediction trajectory, initial values of the firing data are obtained, correcting the initial values of the firing data through one-time Newton iteration, and accurate values of the firing data are obtained. The problems of remote interception missile data calculation with an uncertain launching point and the like are solved, the calculation amount is reduced, the stability and efficiency of calculation equipment are improved, the real-time requirement of remote interception missile launching data calculation can be met, and the invention has high engineering application value and prospect.

A KV-based missile defense system and method of strategic engagement provides performance improvement for both singleton and raid scenarios by launching multiple interceptors that place a follower KV in a trailing position with respect to a lead KV. Knowledge of the target cloud gained by the lead KV is transmitted to the follower KV and incorporated to inform the target selection of the follower KV. The follower KV trails the lead KV with sufficient spacing in time and distance to select a target and maneuver to engage the target pre-acquisition. This also allows the follower KV to receive and incorporate knowledge of target impact by the lead KV. This knowledge may be transmitted back to another follower KV and so forth in a “string” of KVs to inform target selection and down to the ground to inform strategic engagement. Updated non-KV observational data can be uplinked and transmitted forward along the string to the lead KV.

The invention provides a manufacturing method of a ground-interception missile defense system and application of the missile defense system. The manufacturing method of the ground-interception missile defense system is characterized in that the base and the inner layer of the ground-interception missile defense system are cast by use of an alloy steel, a plurality of layers are formed for mounting an outer layer, a second layer is made of a composite bullet resistant material composed of a soft bullet resistant material and a shock-absorptive material in addition to the alloy steel, a third layer is knitted by use of carbon fibers and a c/c composite material, an outer layer is coiled by use of a high-strength alloy steel, welded by use of steel hoops at intervals and hooped section by section, the joint of each layer is hooped by use of one steel hoop and fastened by use of a screw button, each layer is spaced with a fire-resistant antiknock glue, a groove is formed in the inner layer of a device head, sleeves a connection and is tightened by use of a screw, an outer opening is in a flaring shape, and an additional interception protective layer is mounted in the device; the ground-interception missile defense system is mounted on a heavy traction vehicle; a vehicle-mounted radar is combined with optical detection to realize tracking of a defense penetration missile and to transmit inducing signals; a vehicle-mounted navigation system is used for realizing tracking the defense penetration missile along with a phased array radar, and correcting and commanding the traction vehicle to move by use of alignment and calibration so that the missile is capable of falling into the device.

A method for aiding a helicopter pilot to avoid a heat seeking missile includes the step of detecting a threat from a missile. The method also includes the step of reducing heat emanating from the helicopter's engine and rapidly reducing altitude. Then, when the threat has passed flight is resumed. A system for accomplishing the above is also described which simultaneously reduces engine temperature, deflects the exhaust gases, injects water into the exhaust gases, reduces altitude and launches a countermeasure.