Abstract: A method for guiding an intercepting missile to a body-to-body contact with an airborne target in the atmosphere. The method includes the steps of guiding the intercepting missile to within an appropriate distance from the airborne target, illuminating the airborne target, using an illuminator carried by the intercepting missile, acquiring an image of the illuminated airborne target and, steering the missile in accordance with an aimpoint on the image.

Abstract: A method and bistatic synthetic aperture radar (SAR) imaging system generate an image of a target area without knowledge of the position or velocity of the illuminator. The system includes an illuminator to illuminate a target area with a null-monopulse radiation pattern interleaved with a sum radiation pattern. The illuminator adjusts the phase terms of the sum radiation pattern to maintain a static electromagnetic field pattern at the target area. A receiver receives the radiation patterns reflected from the target area and generates phase compensation terms by correlating a measured electromagnetic vector field with the known static electromagnetic vector field. The phase compensation terms are used to generate an image of the target area.

Abstract: A combined defense and navigational system on a naval vessel is disclosed. The disclosed system includes a track-while-scan pulse radar which is controlled to provide either navigational information or tracking information on selected targets. Additionally, the disclosed system includes a plurality of guided missiles, each of which may be vertically launched and directed toward intercept of a selected target either by commands from the track-while-scan radar or from an active guidance system in each such missile.

Abstract: A method and system for pointing and stabilizing a device that needs to be pointed and stabilized with a desired direction, are disclosed, wherein current attitude measurement and attitude rate measurement of the device measured by an attitude producer, which includes an inertial measurement unit, and the desired direction information measured by a target coordinates producer are processed by a pointing controller to compute rotation commands to an actuator. An actuator rotates and stabilizes the device at the desired direction according to the rotation commands in the presence of disturbances and parametric uncertainties to account for the undesired vibration due to disturbances. A visual and voice device provide an operator with visualization and voice indication of the pointing and stabilization procedure of the device.

Abstract: A surface imaging radar system for an airborne platform, the system comprises a transmitter for generating a radar signal. The system also comprises an antenna configured to transmit a radar signal generated by the transmitter and receive radar return information from one or more directions directly below the airborne platform to an angular direction of approximately 30 degrees greater than straight down. The system also includes a processor configured to generate surface information based on the received radar return information and an image processor for generating an image based on the surface information.

Abstract: A digital predetection signal processor having a main channel processor, a dual path processor and at least two digital filters for filtering digital guidance signals before the signals are input into the main channel and dual processing path processors. The digital filters are each programmable to digitally filter the digital guidance signals to thereby minimize output signal error. The processor further includes a circuit for performing base 10 logarithmic calculations of a binary signal in a digital system for optimizing accuracy of the calculation, and a priority encoder for determining a most significant bit position of the binary number, with the most significant bit representing a base 2 logarithmic integer component of the input binary signal.

Abstract: A circuit (100) for performing base 10 logarithmic calculations of a binary signal in a digital system that optimizes accuracy of the calculation. The circuit comprises a priority encoder (108) for determining a most significant bit position of the binary number, with the most significant bit representing a base 2 logarithmic integer component of the input binary signal. A decimal selector (120) selects a predetermined number of bits to follow the base 2 logarithmic integer component determined by the priority encoder, with the predetermined number of bits representing a base 2 logarithmic fractional component following the integer component of the input binary signal. An adder (116) combines the integer component with the fractional component to thereby output a base 2 logarithmic value of the input binary signal. A multiplier (132) divides the base 2 logarithmic value of the input binary signal by a base 2 logarithmic value of 10 to thereby output a base 10 logarithmic value of the input binary signal.

Abstract: A process and a device for electromagnetic guidance of a craft, applied in particular to the tracking of targets. Guidance is carried out with respect to the axis of the beam of a monopulse antenna, by coding in space of the beam. The coding is carried out by appropriate modulation of the signals radiated by a sum pattern and difference pattern. A receiver is disposed in the craft to make it possible to determine the position of the craft with respect to the antenna radiation patterns, and hence its position with respect to the axis of the antenna, the determination of this position being performed by demodulating the signals captured by the receiver. The process and device may be applied in particular in respect of the guidance of any number of missiles or intelligent munitions, for example in the tracking of targets.

Abstract: Processing GPS signals received at moving targets and at a fixed location near instrumentation associated with timing and recording an event allows the determination of instantaneous target position to be made without a requirement for additional active tracking. An example is the recording and display of a test event involving a missile intercepting a target. The missile, target, and an instrumentation site all receive GPS signals. The signals are time tagged and the data contained thereon verified by a source and forwarded from each platform to a ground station. The data is correlated with other test data to provide a real time record and display of the missile intercepting the target. Both Time Space Position Information (TSPI) and Miss Distance Indication (MDI) are derived to a very high degree of accuracy using double difference error correction techniques. Both absolute and relative position information can be derived.

Abstract: A combined defense and navigational system on a naval vessel is disclosed. The disclosed system includes a track-while-scan pulse radar which is controlled to provide either navigational information or tracking information on selected targets. Additionally, the disclosed system includes a plurality of guided missiles, each of which may be vertically launched and directed toward intercept of a selected target either by commands from the track-while-scan radar or from an active guidance system in each such missile.

Abstract: A method for velocity match transfer alignment between a carrier vehicle and a carried vehicle. The method includes repeatedly measuring a velocity difference between the carrier vehicle and the carried vehicle, updating a state vector that include a predicted value of the velocity difference, propagating the vector forward in time, and moving the carrier vehicle and the carried vehicle along a trajectory.

Abstract: A combined defense and navigational system on a naval Vessel is disclosed. The disclosed system includes a track-while-scan pulse radar which is controlled to provide either navigational information or tracking information on selected targets. Additionally, the disclosed system includes a plurality of guided missiles, each of which may be vertically launched and directed toward intercept of a selected target either by commands from the track-while-scan radar or from an active guidance system in each such missile.

Abstract: The present invention is directed towards a mobile ballistic missile detection and defense system. The system of the present invention comprises a ship based antiballistic missile (“ABM”), a missile launch detection system, a missile tracking system, and a ship based signal processing system capable of receiving said tracking signal, calculating an intercept trajectory for an antiballistic missile to intercept a missile, and further capable of outputting an intercept trajectory program to an antiballistic missile. The ABM system of the present invention is capable of deployment in the vicinity of rogue nations which may pose a ballistic missile threat to the United States.

Abstract: In a system for estimating the launch point of a missile, Doppler shifted signals reflected from the missile as it travels from its launch point are used in a Kalman filter to estimate the missile position, velocity and acceleration, in earth centered fixed coordinates. The coordinate system is rotated to a rotated earth fixed (REF) coordinate system in which the X-axis passes through the estimated missile launch point and the Z-axis is made parallel to the missile azimuth as represented by the missile velocity determined by the Kalman filter. The error in the downrange component of the missile launch point is then reduced to a minimum in the REF coordinate system using a square root information filter. The coordinate system is then rotated to a second rotated earth fixed coordinate system in which the X-axis passes through the updated launch point position and the Z-axis is positioned at 45 degrees from the missile azimuth.

Abstract: A circuit (100) for performing base 10 logarithmic calculations of a binary signal in a digital system that optimizes accuracy of the calculation. The circuit comprises a priority encoder (108) for determining a most significant bit position of the binary number, with the most significant bit representing a base 2 logarithmic integer component of the input binary signal. A decimal selector (120) selects a predetermined number of bits to follow the base 2 logarithmic integer component determined by the priority encoder, with the predetermined number of bits representing a base 2 logarithmic fractional component following the integer component of the input binary signal. An adder (116) combines the integer component with the fractional component to thereby output a base 2 logarithmic value of the input binary signal. A multiplier (132) divides the base 2 logarithmic value of the input binary signal by a base 2 logarithmic value of 10 to thereby output a base 10 logarithmic value of the input binary signal.

Abstract: A transmitted signal and a received signal are combined and the combination is expected to determine whether or not a target signal is present. Either the transmitted signal or the received signal is combined with an auxiliary signal containing a range of frequencies corresponding to an anticipated Doppler shift, so that an output of the combined transmitted and received signal will be present only if a target signal exhibiting a Doppler shift within the anticipated range is present. The auxiliary signal preferably comprises finite-duration signal portions of different types so as to provide a substantially uniform frequency response throughout the selected range.

Abstract: A device for the unambiguous measurement of the angle of roll of a projectile, comprises at least a radar equipped with means of processing and sending a signal to the casing of the projectile in at least one direction of incident polarization; a set of parallel grooves made on the casing, the depth of which is modulated dissymmetrically with respect to the axis of symmetry of the projectile; the axis of symmetry of the projectile not passing through the point of the antenna of the radar where the antenna beam is generated, the processing means analyzing, in reception, a signal back-scattered by the casing of the projectile, the signal being modulated as a function of the angle of roll of the projectile, the modulation having two maximum local values corresponding to two angular roll positions of the projectile such that the polarization {overscore (E)} is parallel to the grooves, the processing means removing the 180° ambiguity by comparing the levels of the local maximum values.

Abstract: Given a trajectory and unit pointing vectors determined based on a planar or other approximation of a shock wave, a method and apparatus are provided to calculate times the sensors should have detected, based on a conical geometry of the shock wave. A difference between the calculated times and the actual times measured by the sensors may be minimized. The minimization may be performed by perturbing the unit vectors. When the perturbation of the unit vectors results in an acceptable difference between the calculated times and the measured times, an accurate trajectory of the projectile can be generated from the perturbed unit pointing vectors.

Abstract: A satellite positioning-based guidance system and method that utilize a simulated inertial navigation system are disclosed. The trajectory of the body of a non-thrusted flight vehicle is used instead of a conventional inertial navigation system. The attitude of the flight vehicle is determined using a satellite receiver, and the Extended Kalman filter is used to implement the navigation function.

Abstract: In-Seeker Jamming Device, suitable for an RF missile, utilizes the high-gain antenna and amplifier that are already a part of the missile. During the “blind range” between the termination of the missile's active tracking of the target at a pre-selected distance from the target and its impact on the target, the Jamming Device produces signals that are broadcast via the missile's antenna and are designed to jam and frustrate the active protection system (APS) radars, thereby rendering the APS radars ineffective and the intended targets vulnerable.

Abstract: A robotically controlled steerable gimbal mounted virtual broadband hyperspectral sensor system and methods provide a highly mobile, rapidly responsive and innovative system of locating targets and exploiting hyperspectral and ultraspectral imaging and non-imaging signature information in real-time from an aircraft or ground vehicles from overhead or standoff perspective in order to discriminate and identify unique spectral characteristics of the target. The system preferably has one or more mechanically integrated hyperspectral sensors installed on a gimbal backbone and co-boresighted with a similarly optional mounted color video camera and optional LASER within an aerodynamically stable pod shell constructed for three-dimensional stabilization and pointing of the sensor on a direct overhead or off-nadir basis.

Abstract: A method for guiding an intercepting missile to a body-to-body contact with an airborne target in the atmosphere. The method includes the steps of guiding the intercepting missile to within an appropriate distance from the airborne target, illuminating the airborne target, using an illuminator carried by the intercepting missile, acquiring an image of the illuminated airborne target and, steering the missile in accordance with an aimpoint on the image.

Abstract: An apparatus to determine the three-dimensional location of an airborne platform relative to a target area using two separate antenna assemblies positioned on the airborne platform. The first antenna assembly is adapted to transmit energy downward toward a surface location directly beneath the airborne platform, while the second antenna assembly is adapted to transmit energy forward towards the target area remote from the surface location. A single transmitter is associated with both of the antenna assemblies for transmitting signals toward the surface location and the target area. A receiver coupled to the antenna assemblies receives and detects the signals corresponding to the transmitted energy as reflected by the target area and the surface location. A radar processor is coupled to the receiver and is adapted to determine the range between the airborne platform and the surface location and determine the three-dimensional height of the target area from the detected signals.

Abstract: An interface between an aircraft and a precision-guided missile having automatic target recognition capability receives target image data and target location data from the aircraft, translates the data into formats usable by the missile, and downloads the target data to the missile at any time prior to launch of the missile. The interface includes a mission-planning unit and a terrain and elevation data storage unit enabling the air crew to call up terrain and elevation data on a visual display for planning a missile mission, and to transmit mission parameters to the missile during aircraft flight.

Abstract: A winged bomb is launched from a launch aircraft and glides to a target. During the glide the winged bomb follows a calculated guide path stored in a on board computer, with correction generated by the computer using data from an altimeter and global positioning receiver. Near the termination of the glide a television camera is activated and transmits signals to a remote location from which final correction are manually generated and transmitted by radio to the bomb. The bomb is designed with low radar cross section.

Abstract: The millimeter-wave zoom antenna for guiding a beamrider hypervelocity missile uses varying range information derived from the flight of the missile toward the target as control signals for the beam control computer to perform electronically the zooming and the nutation of the millimeter wave guidance beam that emits from a phased array antenna so as to maintain a constant energy density at the missile receiver regardless of the actual distance of the missile from the launch platform at any given time.

Abstract: A missile guidance system designed to operate on GPS signals in an anti-jamming environment. The inventive system includes first, second and third airborne vehicles (20). A GPS receiver (24) is mounted on each of the three vehicles (20) to receive signals transmitted from spaceborne satellites (14). Each vehicle (20) acts as a pseudo-satellite or ‘pseudolite’. The received GPS signals are processed by a processor (26) to provide a first intermediate signal indicating the position of the vehicle (20). This signal is retransmitted from each vehicle and received by a GPS receiver mounted on a missile. The received intermediate signal is processed on the missile to provide an output signal indicating the position thereof. The pseudolites would be airborne in the vicinity of a target area.

Abstract: A system is provided for generating multiple frequencies in a specified frequency band, with a specified step size between frequencies, in which the spectral purity of the frequencies is assured. The switching speed between frequencies is very fast, limited only by the speed of the switches used. In one embodiment, only five tones are generated as the base for the rest of the synthesis, in which the relationship of the five tones is f0+/−⅛f0 and +/−{fraction (1/16)}f0. The subject system in one embodiment, utilizes a channel synthesizer and a doppler offset synthesizer which may be utilized in air defense systems for generating the transmit channels to be able to permit a missile seeker to transmit a signal at the appropriate frequency. In one embodiment, spectral purity is achieved by providing a number of stages of up converting, expanding, and dividing down of an input signal.

Abstract: In missile guidance systems, knowledge of the target's flight policy and doctrine, along with an analysis of local topographic features, are used in a minimum commitment guidance policy. By assuming certain objectives of the target, paths may be defined by evaluating the degree of detection avoidance provided by the terrain adjacent to the various paths. To maximize the probability of intercept, a missile may be guided in a direction covering the most likely of these paths for periods while the target is hidden. The paths are then reevaluated each time the target is detected. For highly maneuverable targets that are capable of executing violent changes in direction and speed, the topography-aided guidance system maximizes the probability that the target can escape the missile intercept envelope.

Abstract: A fuzing system for non-spinning or substantially non-spinning weapons is implemented by means of wide angle optics providing at least forward-hemisphere coverage, an array of infrared detectors and a microprocessor for image and data processing, aim-point selection, directional-warhead aiming and skewed-cone fuzing. The skewed-cone fuzing has a generatrix which is the vector sum of missile velocity, warhead velocity and the negative of target velocity.

Abstract: A smart docking surface consisting of closely spaced cantilevered sensor/actuator structures capable of precisely repositioning an object having a ferro-magnetic surface in contact with the smart docking surface. It is designed for use in a micro gravity environment for the final docking sequence of two small (<100 kg) satellites. Its purpose is to reduce the complexity of the docking process where a precise mating is required.

Abstract: In a vehicle safety running system, while a contact probability estimation section estimates that there is a probability that a subject vehicle comes into contact with an object and an automatic braking section performs automatic braking, when the driver voluntarily performs a steering operation to avoid the contact, an automatic braking cancellation gradient is calculated based on the contact probability detected with the contact probability estimation section and the steering operation amount detected with the steering operation amount detection section, whereby automatic braking is cancelled at a speed corresponding to the automatic braking cancellation gradient so calculated. When the contact is easily avoided through the steering operation, the automatic braking cancellation gradient is set large so as to cancel automatic braking quickly, while when the contact is difficult to be avoided, the automatic braking cancellation gradient is set small so as to cancel automatic braking moderately.

Abstract: Disclosed is a method and apparatus for improving airborne vehicle tracking and guidance systems by reducing boresight error induced by polarization of the RF energy impinging on the vehicle radome. The radome wall is formed with a taper which gradually increases from the base near the vehicle antenna to the tip according to a disclosed formula which accounts for frequency, incidence angle, look angle, and the dielectric constant of the radome material. This taper of the radome minimizes the crossplane boresight error component magnitude which is polarization sensitive and produces a polarization insensitive inplane boresight error component. Also disclosed is a method of electronically compensating such radomes for boresight error where the radome boresight error data accumulated during testing is digitized and processed for compensating data in the vehicle electronic system to provide compensated tracking data for the vehicle guidance system.

Abstract: A tandem dual-frequency sensor for a missile that uses a steerable dichroic primary millimeter wave reflector to reflect millimeter wave energy to a secondary reflector while passing laser light in the infra-red region through a dichroic region of the reflector to multiple staring laser detectors mounted behind the primary reflector.

Abstract: There is provided a rocket trajectory estimating method comprising the steps of: measuring a GLOS angle of a flying rocket a tracking system; passing the GLOS angle data through a batch filter to reduce noises; estimating a rocket trajectory on the basis of the GLOS angle data, the noises of which have been reduced; passing the resulting rocket trajectory data through a Kalman filter to reduce biases; and estimating the rocket trajectory again on the basis of the corrected GLOS angle data and the positional information of the tracking system. Thus, there is provide a rocket trajectory estimating method capable of reducing observation errors (noises and biases) of a tracking system of a passive ranging system, which does not have need of any laser range finders, to enhance the accuracy of rocket trajectory estimation.

Abstract: (U) A system for protecting a strategic bomber approaching the field covered by an airborne surveillance radar is shown to include: A search receiver arrangement to detect interrogating pulses from such radar before detection by such radar is possible and to determine the range of such radar and an air-to-air guided missile adapted first to home on the source of the interrogating pulses and then to be guided to intercept by an active radar seeker.

Abstract: A device for the unambiguous measurement of the angle of roll of a projectile, comprises at least a radar equipped with means of processing and sending a signal to the casing of the projectile in at least one direction of incident polarization; a set of parallel grooves made on the casing, the depth of which is modulated dissymmetrically with respect to the axis of symmetry of the projectile; the axis of symmetry of the projectile not passing through the point of the antenna of the radar where the antenna beam is generated, the processing means analyzing, in reception, a signal back-scattered by the casing of the projectile, the signal being modulated as a function of the angle of roll of the projectile, the modulation having two maximum local values corresponding to two angular roll positions of the projectile such that the polarization {right arrow over (E)} is parallel to the grooves, the processing means removing the 180° ambiguity by comparing the levels of the local maximum values.

Abstract: An air to air homing missile guidance algorithm based on a state-dependent Riccati equation solution of a spherical-based nonlinear intercept representation of the intercept kinematics problem. The achieved algorithm also provides characteristics asymptotically stabilizing the intercept kinematics achieved with the classic proportional navigation or PRONAV intercept algorithm but provides reduced hunting instability and other fuel-consuming and time consuming missile maneuvers. The disclosed algorithm is in the form of four state equations, two equations for an angular acceleration embodiment and two for a linear acceleration embodiment. Each such embodiment includes seven state variables each having a gain coefficient of complex fraction form; each embodiment is additionally refined for differing cross-channel couplings.

Abstract: We describe an efficient algorithm for evaluating the (weighted bipartite graph of) associations between two sets of data with gaussian error, e.g., between a set of measured state vectors and a set of estimated state vectors. First a general method is developed for determining, from the covariance matrix, minimal d-dimensional error ellipsoids for the state vectors which always overlap when a gating criterion is satisfied. Circumscribing boxes, or d-ranges, for the data ellipsoids are then found and whenever they overlap the association probability is computed. For efficiently determining the intersections of the d-ranges a multidimensional search tree method is used to reduce the overall scaling of the evaluation of associations. Very few associations that lie outside the predetermined error threshold or gate are evaluated. Empirical testing for variously distributed data in both three and eight dimensions indicate that the scaling is significantly reduced from N2, where N is the size of the data set.

Abstract: Navigation satellite receiver measurements of the acceleration of a moving vehicle are used to derive valuable attitude information about the vehicle. Three-dimensional accelerometer measurements aboard the vehicle are used to determine the specific force vector in the bow frame. The navigation satellite receiver measurements allow determination of the specific force vector in the earth-fixed frame. The specific force vector measured in both vehicle and earth-fixed frames can be used with additional information to derive vehicle attitude.

Abstract: Items of relative target location information (19) which are obtained on board a platform serving as a sensor carrier (13) for target or position reconnaissance are combined, with association with the navigation satellite system time (34), with items of absolute mission location information (25) which are obtained on board the sensor carrier (13) from the satellite navigation orbit data (22), in order to obtain absolute target position data in which however, due to the system, there is still contained the absolute residual error of the order of magnitude of some ten meters, from the satellite-aided mission location determination.

Abstract: A passive millimeter-wave imaging system (10) that includes a millimeter-wave camera (12) positioned at the end of an aircraft landing strip (14) to provide an image (20) of the aircraft (16) approaching the landing strip (14) along a landing glidepath (18). The camera (12) broadcasts the image (20) of the aircraft (16) approaching the landing strip (14) to the aircraft (16) and to a control tower (24). With this information, the pilot of the aircraft (16) sees his aircraft's position relative to the glidepath (18), and can make landing adjustments accordingly. Likewise, the tower personnel can monitor the aircraft landing glidepath (18) to insure that the aircraft (16) maintain a safe distance relative to the ground.

Abstract: A system (10) for determining the range between a missile (14) and a target (18) adapted for use with a semi-active missile system. The system (10) includes a first circuit (12) for generating a periodic signal (24) that is periodically frequency modulated. A second circuit (16) determines a closing rate at which the missile 14 is approaching the target 18 via the periodic signal 24. A third circuit (16) determines a value containing information corresponding to the range and the closing rate via the periodic signal. A fourth circuit (16) determines the range from the closing rate and the value. In a specific embodiment, the first circuit (12) includes an illumination system (12). The illumination system (12) includes a periodically modulated carrier signal generator (32) that generates the periodic signal (24). The periodically modulated carrier signal generator (32) includes a frequency source, a frequency modulator, and an illumination system computer.

Abstract: A search radar including the improvement of apparatus for enhancing the estimation of the target angle within a search scan of the radar is disclosed. More specifically, the improvement apparatus utilizes the generated scan angles and target amplitude measurements correspondingly associated therewith to generate intermediate signals which are representative of the natural logarithm of the target amplitude measurements plus the square of the corresponding scan angle multiplied by a predetermined constant. For each search scan, the apparatus computes separately signals representative of the moments of: the scan angles, the squares of the scan angles, the products of the scan angles and corresponding intermediate signals, and the intermediate signals. In turn, the apparatus operates on the computed moment representative signals in some prespecified mathematical relationship to effect an optimum estimation for the target angle in each search scan of the radar.

Abstract: The present invention relates to a method and a system for determining a weapon firing strategy for an evading target. The method of the present invention comprises the steps of sensing the motion of the target, analyzing the motion of the target, providing a weapon employment decision aid, determining the evasion region for the target using the weapon employment decision aid and the analyzed motion, visually displaying the evasion region, feeding operator knowledge about the evading target, and generating a representation of the probability of the location of the evading target. The weapon employment decision aid utilizes beta density functions to determine the evasion region. The weapon employment decision aid displays target course and speed in the form of bar graphs and allows the operator to input information about target evasion course and speed and uncertainty levels.

Abstract: A method for assigning a target within a cluster of targets to a specific one of a plurality N of weapons launched from M airplanes is provided. The method includes providing the specific weapon with an index (m,n) based on the weapon bay n and the airplane m from which it is to be launched, receiving the central location and determining the shape of the cluster; dividing the cluster shape into N sub-clusters wherein each sub-cluster n has M sectors m, determining the center of gravity of each sector; associating the specific weapon with the sector having index (m,n); and assigning a target from among the targets in the associated sector to the specific weapon.

Abstract: A frequency adjusting arrangement is disclosed whereby the frequency of a local oscillator, incorporating an Yttrium-Iron-Garnet filter as the frequency determining element, is controlled to follow a coded waveform having a bandwidth wider than the bandwidth of the circuit in which such filter is used.

Abstract: A system is provided for generating multiple frequencies in a specified frequency band, with a specified step size between frequencies, in which the spectral purity of the frequencies is assured. The switching speed between frequencies is very fast, limited only by the speed of the switches used. In one embodiment, only five tones are generated as the base for the rest of the synthesis, in which the relationship of the five tones is f0+/−⅛f0 and +/−{fraction (1/16)}f0. The subject system may be utilized in air defense systems for generating the transmit channels to be able to permit a missile seeker to transmit a signal at the appropriate frequency. In one embodiment, spectral purity is achieved by providing a number of stages of up converting, expanding, and dividing down of an input signal.

Abstract: A mobile space lift range system using a ground control station and an unmanned airborne vehicle that relayed data to and from a space lift vehicle to control it. The unmanned airborne vehicle may selectively include one or more sensor systems, a radar system, a command and telemetry system, and a user test system. The unmanned airborne vehicle is a high attitude, long endurance vehicle that provides a flexible, mobile range to support launch-anywhere space lift scenarios.

Abstract: Two new adaptive homing guidance laws are developed which are variants of Augmented Proportional Navigation (PRONAV). The first guidance law commands flight path angle rate and is referred to as adaptive matched augmented PRONAV (AMAAP). The second guidance law commands linear acceleration and is referred to as adaptive matched augmented linear PRONAV (AMALP). The major attributes of these guidance laws are (1) they are the solutions of a linear quadratic control problem, (2) they do not require an estimate of time-to-go (tgo), (3) they are matched to a nonlinear model of the target's motion, (4) they adapt in real time to provide optimal guidance over each small segment of the intercept trajectory, and (5) they optimally account for missile deceleration.