SA519402207B1 - Guided Munition Systems for Detecting off-Axis Targets - Google Patents

Abstract

Systems are disclosed for navigating a missile to a target using a fixed sensor onboard the missile. In an embodiment, a system includes a launch platform traveling a pre-programmed route to deliver the missile within an area. The missile travels a first flight path through the area in effort to detect targets. If no targets are detected along the first flight path, the missile transitions to a second flight path, different from the first flight path, to locate targets off-axis relative to the first flight path. While the missile travels the second flight path, the sensor receives signal identifying a target located at a position off-axis relative to the first flight path. The missile then adjusts the second flight path to direct the missile to the target. In an example embodiment, the first flight path is straight or arced, while the second flight path is u-shaped, corkscrew-shaped, or spiral-shaped. Fig. 1A

Description

Guided Munition Systems for Detecting off-Axis Targets Full Description

Invention background

This disclosure relates to guided munition systems; More specifically, systems

A munition aimed for off-axis target acquisition

Target acquisition systems are designed to detect; to set; and locate

a target within an area for the purposes of dispersing ammunition; Jie missile or dad against the target. Some are designed

target capture systems; Like radar systems also to track the movements of potential targets. Once selected;

Target positions can be used by the missile or a launch pad to guide the missile at a target

intended . Target capture systems can locate the target dl on ¢ inputs as waveforms

radio waves or infrared signals; Reflected 0 received another image from the target. For target acquisition systems installed on

the missile; The missile is launched or otherwise delivered near the target within the receiving area

input. Once received, the input is used to guide the missile toward the target.

US Patent No. 20090228159-1 discloses a semi-active laser system al-in ('I-SALS'") multifaceted imaging sais laser system sides; 1-5815 closes on manual mapping the laser at the target until it starts photographing the target, as it does 5

1-8 After that, aim at the target of the image. Some models use a defocused mapping guide

a little. Other models use existential tension to guide designation

Attentional stimulation of stress in mapping evidence named delusional shadowing disorder. Availability of a template

The designator is a dual-field sight beam with no moving parts.

Gig of invention USP No. 20140042265 “The projectile (1) is fitted with a belt guide device (2); said device has a locking stage during which the latter attempts to detect the ¢(C) target including the direction of sight viewing direction (3) said sighting direction (3) is fixed dually to the projectile (1) and extends along the longitudinal axis 5 (4) of the latter; said projectile (1) includes Wa On a control device (8) for automatic control

with said missile (1) so that Chum in the longitudinal axis (4) cal in flight and during the locking stage of the steering gear (2); circle trackers; whose radius increases in time; Until the target is detected. (C) General description of the invention

0 An example of the present disclosure presents a guided munition system that includes a guided munition (Sa) delivered to an area by means of a launcher that travels along a pre-programmed trajectory into the area; the JED is initially designed along a first flight path through the area and to travel to a trajectory A second flight through the area in response to the non-identification of an on-axis target when flying on the first flight path; the second flight path differs from the first flight path in that it is designed to identify

Off-axis target position relative to the first flight path; a sensor on the surface of the HAN guided warfare; The sensor is located for the guided munition and to detect an input signal indicating the on-axis target as the guided munition moves along the second flight path. in some cases; The guided munition system also includes a signal generator to transmit a signal for target indication; So that the signal from the target is reflected and received by the sensor with the ammunition

0 directed. in other cases; The sensors have a scanning field of between 30 and 40 degrees. in some other cases; The second flight path is a pre-programmed flight path that directs the guided ordnance through a flight path in a highly skewed manner. In other cases dad the guided munition includes a like key that inserts a signal identifier into the guided munition to determine which signals received by the sensor correspond to the target. in other cases; He is

5 The second flight path is a pre-programmed flight path (Cus) that directs the guided munition

through a winding spiral or spiral flight path. in some other cases»; The guided munition system also includes the DULY platform where the launch pad is an unmanned aerial vehicle (unmanned aerial vehicle) the vehicle moves along a pre-programmed trajectory. In Al cases the guided munition is a missile and the sensor is mounted on the missile body for the missile.

Another representative example of the present disclosure provides a method for guiding a missile to a target after the missile has been launched from a launch pad that travels along a pre-programmed trajectory within an area; The method involves directing the missile along a first flight path within the area; response to determine that the target is off-axis relative to the first flight path; Guidance of the missile along a JB flight path different from the first flight path; The second flight path to a fixed sensor position on the missile body for checking sites

0 off-axis” relative to the first flight path; receiving a signal by the fixed sensor while traveling along the second flight path; target presence identification signal; And modify the second flight path to direct the missile to the target dala area based on the received signal. in some cases; The method also includes target identification based on the signal received. In some of these cases; Target identification involves comparing a signal identifier to the received signal using the target information

5 stored on the missile. In the other iad cases, guidance of the missile along the second flight path begins in response to the missile traveling a predetermined distance through the area along the first flight path without detecting the target. In some of these cases; The pre-set distance is at least two kilometers. In cal cases missile guidance is initiated along the second flight path in response to the missile traveling through the area for a predetermined period of time without target detection. in some of these

0 cases; The preset time period is at least five seconds. in some other cases; Guidance of the missile along the second flight path begins after the separation criteria are met; Allows the Launch Laid to exit the area before starting the second flight path. Another representative embodiment of the present disclosure provides a computer-readable medium that includes one or more non-temporary machine-readable media that encodes a set of instructions that when

5 Executed by one or more processors leading to the execution of an operation to guide a missile at a target within a target

region; The process includes carrying out missile guidance during a first flight path within the area; response to determine that the target is off-axis relative to the first flight path; carrying out missile guidance along a second flight path different from the first flight path; the second flight path to a fixed sensor position on the missile body to check off-axis positions relative to the first flight path; Receiving a signal by the fixed sensor while traveling along the second flight path » target presence identification signal; And implement the second flight path adjustment to direct the missile to the target within the area based on the signal received. in some cases; The process also includes identifying the target (pl on the received slay). In gal cases the missile guidance along the second flight path is initiated in response to the missile traveling through the area along the first flight path for at least one predetermined time period 0 and a predetermined distance. In some other cases as well; Execution of missile guidance occurs during the second flight path after the separation criteria have been achieved; To enable the launch pad to leave the area. In gual cases, the second flight path is a pre-programmed flight path that guides the missile through a U-shaped, helical, or zigzag flight path. The features described in this document are not all-encompassing; specifically 3 will 5 Many additional features and advantages to one of ordinary skill in the art are evident in the light of the drawings, the description, and the claims.Furthermore, it should be noted that the text used in the specification has been chosen primarily for readability and study purposes and does not restrict the scope of the subject matter created. 1 is a perspective view of the area around a target that includes a launch pad and signal generator located 0 away from the platform (DULY) according to an embodiment of the present disclosure. Figure 12 is a side view of a missile according to a model from the present disclosure.

Figure 2b Ble is a schematic diagram of a missile designed according to a model from the present disclosure. Figure 3 is a flowchart of a typical method for guiding a missile to a target, according to an example from the present disclosure. Figure 14 is an overhead view of the area showing a missile launch from a launch pad; According to a sample from the current statement.

Figure Hob is an overhead view of an area showing a target identification signal at an off-axis position relative to the first trajectory of the missile, according to a sample from the present disclosure. Figure 4c is an overhead view of an area showing a second flight path of the missile within the area; According to a sample from the current disclosure.

0 Figure JD is a side view of an area showing a second flight path of the missile within the area; According to another model from the current disclosure. Figure 4e is an overhead view of the area showing a missile acquiring a target while traveling through a second flight path; According to a sample from the current disclosure. Figure 4f is a side view of an area showing a missile acquiring a target while traveling along a trajectory

5 sec according to the sample from the current list. These and other features of the current models will be better understood by reading the following detailed description; In conjunction with the forms described herein. The accompanying graphics are not intended to scale. For clarification purposes; Not every component can be coded into every graphics. Detailed description:

Then, discover techniques and designs for guided munition systems designed to guide a guided munition 3 such as the Fg ba unmanned aerial vehicle (UAV) missile; or another missile" to a target. Guided ammunition includes; For example, a guided missile »; on

Fixed sensor mounted on the missile and designed to detect a target identification signal. The system includes a launch pad designed to move in a pre-programmed direction to deliver and launch the missile within an area. after launch; The missile travels through a first flight path (eg 'initial flight path') through the area to detect targets off-axis in relation to the missile. An on-axis target is a target in front of or otherwise 'visible' to the missile on the first flight path such that the target identification signal is received or otherwise detected within the field of view (FOV) of the sensor. Any targets on the first flight path The missile travels through a second flight path different from the first flight path to locate off-axis targets relative to the first flight path An off-axis target is a target outside the sensor FOV 0 when the missile is on a path First flight, such as when the target is to the side and/or behind the missile relative to the missile's first flight path or otherwise.According to some embodiments, the second flight path is shaped or designed in a GAT image to expose the missile's sensor to a larger portion of the area believed to be The presence of the target Jie lg in the form of a spiral, zigzag, or letter No. As a result of the movement of the missile along the second flight path, the sensor receives a signal 5 Identification of a target located at a position off-axis relative to the first flight path. The missile, in response to receiving the signal, adjusts The second flight path to guide the missile to the target using the received signal. Overview A WAV like a drone effectively performs reconnaissance and surveillance to identify and engage 0 threats along a route; ie flight path; to accomplish a mission. In one example these vehicles are launched remotely and directed using computers. on the surface to execute a pre-programmed trajectory.In some cases, the UAV will engage an identified threat using guided warfare munitions, such as guided missiles and rocket-propelled grenades.For example, a guided missile can be delivered by the UAV to a target along the flight path.For Clarification; the example in this document will use 5 missiles, but it is understood that any guided munition is equal.

For example, a “radio frequency” laser or radar signal “reflected or otherwise emitted from the target by the missile to accurately direct the missile towards the target. The signal is detected when the signal is within the field of view (FOV) of a sensor mounted on the missile. a target is in front of the missile; So that the signal reflected from the target is received within the FOV of the sensor is an on-axis target. Subsequently; The on-axis position of the target relative to the missile allows the missile to detect and engage the target. reflects off-axis targets such as targets to the side and/or rear of the missile; signals outside the FOV of the sensor” and thus present challenges for guided munition systems. For example (Ja) missiles with fixed or otherwise non-rotating sensors require a launcher to adjust its flight path to the platform's position relative to the target so that the target identification signal can be received within the FOV of the sensor on the missile surface. For self-launching launchers Guidance; Jie drones dll as they execute a pre-programmed trajectory; these subject adjustments cannot be made and therefore off-axis targets cannot be engaged. Sensor missiles are not rotatable” Jie sensor mounted on the ang Cost-effective Biaxial Loads have limited potential applications for the missile. For example; in 5 Ghd adaptable sensors often increase the size and weight of the missile; hence the bi platforms that can order the missile. In addition (SA Rotary sensors are more complex and expensive than fixed sensors because of the number of additional components required to ensure adequate function and accuracy and to achieve this”; techniques and design of guided munition systems designed to guide a guided 0 munition; Jie missile, rocket or missile; at a target are disclosed Guided munitions include; For example, a guided missile; on a fixed surface sensor that is designed to detect a target identification signal. SUEY can be in the form of a Ble (JB) of a reflected type of illumination signal directed at the target, or alternatively, a signal emitted from the target itself. In any of these cases, the signal received at the sensor on the surface of the missile can be used 5 The fixed sensor is a sensor that does not move relative to the Jeo missile) eg; not

sensor mounted on a gimbal unit). in a representative form; The fixed sensor is a semi-active laser seeker with an FOV of 30 to 40 degrees. The sensor is designed to detect or receive within its FOV (eg, laser, radio frequency, or radar signals) reflected or otherwise emitted from a target within the area. In addition to the SUA, the missile also includes one or More than surface computing systems” such as a flight controller, guidance systems, and target capture systems to operate the missile once launched from the launch pad and guide it toward a target along a flight path. A flight path is an actual or planned path along which the missile travels within an area. The flight guidance and/or control systems are designed to generate commands or instructions to operate one or more missile control surfaces to adjust the flight path of the missile as needed to stay straight to the target 0. The target acquisition system is designed to select a target based on a signal received at the fixed sensor FOV The missile is delivered to the area using a launch pad The launch platform is designed to travel along a pre-programmed direction to deliver and launch the missile within the area In one exemplary embodiment the launch platform is an autonomous UAV Jie an aircraft without a lila where It is pre-programmed 5 to move in a specific direction to accomplish a desired mission objective. The launch pad cannot be played; as a result; altering or otherwise modifying its flight path to engage a target. from a remote location; (Sa) launch the launch pad and this is its operation to and through the area containing the target. Once inside the area the launch pad launches or in the form of GAT delivers the missile to the area. After launch the missile is designed to travel along a first flight path through the area. 0 The first flight path can generally be any path where the probability of detection of the target within the area is available, and in some embodiments it is a straight or arcing path through the area.In any case, the missile travels along the first flight path to detect or in an Others On-Axis Targeting As previously explained, an Axis Target is a target on the missile FOV for a given flight path. Aviation » designed

to operate the missile using input from sensors on the surface; Like accelerometers. These Jie cad communication signals are not used from launch pads or communication stations; to control the missile. The missile travels along the first flight path, searching for a target identification signal within the area. signals are sent; such as those generated by a signal generator located in the area;

to the target (also known as target illustration) and reflected within the area around the target; according to some models. In gal models the signals are generated by the target itself; over the first flight path for a period of time (eg, three to ten seconds; Jie, five seconds).

0 The missile is designed to travel a specified distance (for example, 1 to 4 km; such as 2 km) without detecting the target; before executing a second flight path. The missile is designed to travel through a second flight path different from the first flight path to locate off-axis targets relative to the first flight path. The missile is designed to travel along the second flight path in response to the missile not detecting any targets along the first flight path

5 within the search criteria based on the specific time and distance associated with the first flight path. In an exemplary model, for example, the second flight path is a preprogrammed flight path through the region that positions the sensor in a different direction relative to the missile's first flight path. A pre-programmed flight path (Ble) is a set of instructions and/or commands to control the movement of the missile; And it was lifted or stored on the surface or could be reached in another way to the missile before

0 missile launch. The second flight path allows the missile to detect targets off-axis relative to the missile's first flight path. As explained previously; An off-axis target is a target that is outside the FOV of the sensor relative to the first flight path. Lexie The missile travels through the second flight path; The area changes within the FOV of the sensor; so that the ash sensor scans or otherwise searches different parts of the area to locate targets that are off-axis relative to a trajectory

5 first flight. The second flight path” in some Ble lal is similar to the flight path

— 1 1 — U-shaped, zigzag spiral, or spiral. While moving along the “SY” flight path the missile can descend at a fixed or variable rate depending on mission variables (eg “size of area of interest; initial missile coordinates and size; shape of intended target signature). in response to target signal reception along the second flight path; The missile makes a second flight path adjustment to direct the missile to the target using the signal received. in a representative form; The missile is designed to adjust the second flight path to keep 1 of the received signal within the FOV of the sensor. using the received signal; Missile flight control and guidance systems are designed to generate and/or transmit instructions and commands to operate the missile's control surfaces to guide the missile toward the target. The missile continues to adjust its flight path to keep the signal within the FOV of the sensor until the missile hits or otherwise engages the target. Figure 11 is a perspective rendering of Area 10 around a target 80) The area as dale includes launch pad 30 and signal generator 90 according to a sample from the present disclosure. Area 10 is a collision and airspace around a target (eg; near Bribie From the target) 5 where a munition such as a guided missile or missile can be deployed to engage the target.In some embodiments, the area can include up to 10 terrain variants (eg rivers, streams, hills or mountains) and/or buildings containing On or otherwise protecting the GAT target.In an exemplary model, the Zone 10 is a 20-mile zone ae containing the location of Target 80. Zone 10 can be set or otherwise modified to allow the ammunition to engage Target 80, as described in Figure 0 additional in this document. ang) can also be provided signal 92 from signal generator 90 to target 80 (to clarify the target); By providing a reflex view of this Lad 92 signal from Target 0 within Zone 10 which Missile 35 is searching. Launch Pad 30 transports Missile 35 and delivers Missile 35 to Zone 10 around Target 80. In an analog z model 0; Launch Pad 1 30 is a guided metering vehicle; UAV Jie is autonomous

It includes surface computing systems and sensors designed to execute a pre-programmed path to accomplish a mission objective. A UAV is an aircraft; Like a bila drone designed to steer without a human pilot on board. An autonomous UAV is a UAV that includes a flight computer that controls the avionics to operate the vehicle along a pre-programmed trajectory and does not require remote control using communications signals from the launch pad and/or communications station. A pre-programmed trajectory is a flight trajectory that is prefabricated or otherwise programmed within Platform 30 using firmware or a cain component on some embodiments. Once launched; The Platform 30 typically does not deviate from its preprogrammed path; For example to engage an off-axis target as further described herein. The launch pad can include 30 sensors;

Such as (JB) gyroscopes and accelerometers; designed to provide measurements in any of the following directions dually to platform 30 (eg (Jha) a central axis or midpoint of the station may be used): top-down; side-to-side; forward-backward;

5 to achieve a desirable mission objective; Launch Pad 30 is designed to launch Missile 35 within Area 10. Mission objectives for Launch Pad 30 could include reconnaissance and surveillance to identify and engage threats (eg; Target 80) located along a pre-programmed trajectory within Zone 10. Launch Pad 30 is designed to engage a specific target by firing a guided munition, such as the Guided Missile 35 (here in this document referred to as the 35 Missile) to destroy the target.

0 A guided munition is Ble from a Jie (rd) missile, UAV a rocket or missile. Designed to engage a specific target. In an exemplary embodiment, the Missile 35 has a fixed sensor, such as a semi-active laser seeker, a detector photometric or thermal image sensor (eg (Jal) cooled or non-(Be) thermal imaging sensors designed to detect or otherwise receive a signal from a target eg Je; reflected from the target) and; as described herein

5 document further. response to signal reception; The Rocket 35 is designed for signal processing

received to identify target 80 and direct missile 35 to target 80. Missile 35 can be any guided missile; A rocket-propelled grenade or a missile that can be deployed using Launch Pad 30. Ammunition shall be; In some other models it is a launch pad 30 like a UAV instead of a missile. in these models; The 30 launch platform sings its design to engage the Target 80 by operating the UAV inside or otherwise sufficiently close to the Target 80.

Within Area 10 is Target 80. Target 80 can be any physical object or person identified by Missile 35 as a threat that can be identified based on a signal received; As further described in this document. the target is 80; in some cases; A fixed target such as a temporary building or structure. in other cases; The target of 80 is a target

0 animated; Jie tank shown in Figure 1a. regardless of its type; Target 80 is identified using a signal 92 that can be received by a sensor on the missile 35; Then Missile 35 is designed to engage Target 80 within Area 10 using received signal 92. Missile 35 is designed to identify Target 80 using Signal 92 composed of an existing Signal Generator 90 (Jal) in Area 10. For example (Jal) the missile can include 35 has a designed guidance system

5 to direct missile 35 towards target 80 using signal 92. Signal 92 can be any communications or data signal; Jie is a radio signal; Radar and laser are able to transmit target information. Target information is information that can be used to determine a position; distance; Speed; the coordinates of the target within the area and/or with respect to the missile 35. In a representative form; The signal generator 0 is a target designation unit designed to generate and transmit signal 92 to target 80 for clarity

0 Target 80 for target detection purposes. (cdg) alge could be the signal 90 within zone 10 around the target 80. alse could be the signal 90; in some other models; carried on the roof of launch pad 30. In turn, signal 92 is reflected from target 80; It is transmitted to Area 10 around Target 80 where the signal 92 can be received by a sensor mounted on the missile 35. The reflected signal 92 is detected when the signal 92 is within the scanning field

(FOV) of a sensor on missile 35. Once received, the reflected signal 92 is dallas and used to direct missile 35 to target 50. Figure 1b is an overhead view of area 10 around target 80 which includes launch pad 30 and signal generator 90 according to a model from current detection. Lovie enters Launch Pad 30 in Area 10; Target 80 can be located in one of several locations relative to Launch Pad 30.

For example; When the target 80 is directly in front of the launch pad 30 and therefore in front of the missile, the target is considered to be a coaxial target as previously described. Target identification is on the axis; however; Unlikely in most cases because Target 80 is rarely found along the pre-programmed trajectory of Launch Pad 30 so that the Target Identification Signal 80 is within

FOV 0 for the sensor on the 35 missile. Often more; There is no Target 80 in front of Launch Pad 30; The target 80 is therefore outside the FOV of the sensor and is considered an off-axis target. This is illustrated in figure cl where the launch dais 30 Jala zone 10 is positioned with target 80 behind and to the side of platform 30. As can be seen; Signal 92 sent by Age signal 90 Tams is reflected off target 80 and falls after platform 30 and missile 35. Hence; no

15 The fixed sensor is placed on the missile 35 to receive the signal 92. Therefore; so that the 5 missile can engage the target 80 without the need to deflect platform 30 from its preprogrammed path; The 35 missile is designed to pursue target 80. Structure and operation of the system Figure 12 is a side view of the 35 missile according to a model from the detection Mall.

AN 0 such as missiles (Aga gall rockets, rockets and missiles) to engage and destroy potential threats within an area. As can be seen, the 35 missile has a 210 fuselage and 220 control surfaces. The 210 fuselage is designed to house internal components to operate the 35 missile and to provide an aerodynamic shape An antenna to allow the missile to travel along a flight path.

Attached to the body 210 are control surfaces 220. The control surface 220 is a movable surface; like airfoil da fan wing"; Elevator and stabilizer designed to control or otherwise guide the 35 missile toward a target and/or along the missile's trajectory. The 35 missile can have any number of control surfaces 220 placed along the fuselage 210 depending on the application of the 35 missile. In the (ii) model the 35 missile has dida propellers located on the rear hall and wings located near the center of the fuselage 210. It will Several other designs are evident in the light of the present disclosure.Inside fuselage 210 of the 35 missile are the flight control system 230, guidance system 260, 0 and target acquisition system 280.In a representative example Flight Control System 230 is designed to control the movement of the missile 35 along a preprogrammed flight path to guide the missile toward a target. Flight Control System 230 includes a processor 235 (240” memory) and a switch 250. The processor 235 is programmed or otherwise designed to adhere to and distribute instructions and data For example, in some embodiments, the processor 235 is designed to execute a pre-programmed flight path 5 of the missile 35 using signals from one or more sensors in the guidance system.The signals received from external sources (eg a target) are analyzed by the processor 235 to modify The flight path of the missile to engage a target. and until the flight path of the missile is modified; The 235 processor is designed to determine the missile's orientation (eg whether the missile is upside down) relative to a surface (eg the ground) in the area around the target. The missile's direction 0 can be determined in several ways using sensors; Jie magnetometers; rate sensors; accelerometers; To measure the magnetic forces and/or specific gravity acting on the missile. Other methods can be implemented; such as revealing the horizon of the image; Also by processor 235 to determine the direction of a missile. Tay Processor 5 in changing or modifying the flight path of the missile 35 by generating and transmitting instructions and/or commands to the control mechanisms; Jie electromechanical actuators; to operate the 220 control surfaces on the 5 35 missile. Instructions and/or commands generated by the 235 processor can be executed using firmware and/or

or an alin component such as routines and edi-like programs) that analyzes sensor inputs and identifies adjustments to the control surfaces of the missile 220. The processor 235 is designed to transmit flight path data (eg; instructions and/or commands) to memory 240; This data can be saved for future use by the system (eg additional flight path adjustments).

The memory ang;240 can also be in communication with and/or otherwise accessible by the processor 235. In analog form; Data configured and/or controlled by the processor 235 is stored within memory 240 to support various operations of the missile 35. It can access data such as photographs, maps; sensor measurements; signal identifiers; And lookup tables to the processor 235 by

0 Memory 240 to specify a flight path for the missile 35. Memory 240 can be of any suitable type (eg RAM and/or (ROM or other suitable memory) and size; in some cases it may be implemented by volatile memory. non-volatile memory” or a combination thereof Memory 240 can also be any physical device capable of storing data non-temporarily; Jie A computer program product that includes one or more non-machine-readable media

5 Temp encodes a set of instructions that, when executed by one or more processors, help an electronic device operate according to a process. Switch 250b is connected or otherwise in communication with processor 235 and designed to carry out data in the flight control system 230. In analog form; The 250 key is part of key groups; Jie key set is a laser blade key assembly (LSA) type key set

0 Use the LSA key combination manually to design the missile to capture laser signals with the selected laser blade. in some embodiments; The 250 key is a swap or house key designed to enter the signal identifier. The signal ID is a VRBD identifier used by the 235 processor to identify a signal from a target. The processor 235 is designed to compare a signal ID of a received signal with a signal ID based on key setting 250 to determine if the received signal meets a target.

Flight Control System 230 is operationally coupled to or otherwise in communication with Guidance System 0. Guidance System 260 is designed to guide Missile 35 along its flight path. in a representative form; The steering system of the 260 is semi-active steering. The semi-active guidance system receives signals (for example, target identification signals) to guide the missile to the target instead of generating a signal; It is also implemented by active steering systems. The signals generated can be transmitted by other devices; such as a target signal generator (also known as target illumination); In turn, it is reflected or otherwise transmitted from the target within the space around the target. as a result; The 35 missile traveling within the area can detect or otherwise receive the reflected signal and then process it to engage the target.

0 in analog form » The 260 steering system is an internal steering system. An internal guidance system is a computing system that includes a firmware and/or software component and sensors (eg JU 265 accelerometers; gyro sensors 270 and rate sensors 275) designed to determine the direction and velocity of the missile. The accelerometer 265 is designed to measure the acceleration of the missile. Rate sensors 270, Jie gyroscope or yaw rate sensor, are designed to measure the angular rate of change of

5 The movement of the missile relative to the axis of the missile. The internal guidance system can set a position; direction; and missile velocity without the use of external guidance references (eg, communications signals from a remote tracking station). in some other models; The internal guidance system is designed to locate a missile within the zone based on an estimate of the missile's previous position within the zone. The Guidance System 260 can operate in one of several modes to guide the missile through the area

0 and/or to a specific target within the region. in a representative form; The Guidance System 260 guides the Missile 35 using the following modes of operation: (1) spin rate control; (2) roll behavior control and ez ha rate/behavior control; (3) signal capture and pursuit guidance; (4) sang providing continuous FOV and (5) proportional routing to intercept the target. after launch; The missile can initially operate in spin rate control mode to dampen the missile; So that a desirable missile direction can be saved (to prevent

5 the missile from rotation to the direction from top to bottom). once fixed; The missile is designed 35

To operate in the mode of controlling the behavior of the pulley and controlling the rate/behavior of swing and yaw. To guide the missile 35 through the area. while capturing a signal; The Missile 35 is designed to operate in a signal captured and pursuit guidance pattern to adjust the Missile 35's trajectory toward the detected target. and to ensure that the 35 missile engages the target; The 35 missile is designed to operate in a unit providing continuous FOV and proportional guidance for target interception patterns. As it can be seen; The Flight Control System 230 also interfaces with the Target Acquisition System 280. The Target Acquisition System 280 is a system designed to detect; identify and locate a target with sufficient accuracy; So that the 35 missile effectively engages the target. The 280 Target Capture System includes a 5 sensor. In analog form; Sensor 285 is a semi-active laser search module; Such as 0 semi-active distributed aperture laser search unit. The sensor can be 285; in other models; Sle from a photodetector; a thermal image radar detector; and/or video sensor. 5. In contrast to gall-mounted sensors, the sensor is biaxial; is a fixed or otherwise non-rotating sensor” such that sensor 285 does not move with respect to missile 35. Sensor 285 can be located at or near the nose of missile 35 and is designed to detect a signal (eg 5 visible and invisible light; heat energy; or frequency waves radio) from AIM. The signal is detected when the signal enters the FOV of sensor 285. The FOV of sensor 285 can be of any size capable of providing sufficient range to detect a signal from the target; Jie between 30 and 40 degrees. Typical method for locating an off-axis target Figure 3 is a flowchart of a typical 300 method for guiding a missile to a target after the missile has been launched from a launch pad traveling along a pre-programmed trajectory within an area; According to a sample from the current disclosure. Method 300 involves launching 304 missiles from a launch pad; The missile includes a fixed sensor. in a representative form; The launch platform is an autonomous UAV; Jie is an Hla drone that is programmed to move to an area and fire a missile within the area to engage a target. This is illustrated in Figure 4a; Where the launch pad 30 transports the missile 5 35 to the area 10 along a pre-programmed path. The 35 missile is launched from a platform

Launch 30 at a distance above Zone 10. Once launched; Missile 35 travels along first flight path 404 within Zone 10 to locate Target 80 within Zone 10. Target 0 is identified when the reflected signal from Target 80 is received within the FOV of a fixed sensor mounted on Missile 35.

Method 300 also includes the 308 determining that the target is off-axis relative to the first flight path. in a representative form; The missile is designed to detect the absence of targets at an on-axis position relative to the missile's first flight path in response to no target acquisition signals being received within the FOV of the missile-mounted sensor. This has been shown in Figure 4b; Where the missile 5 moves along the first flight path 404 to capture or otherwise identify targets in

FOV 0 408 for the sensor on Missile 35 (eg, pivot targets in front of Missile 35). As cans (Sa) the target 80 is outside the FOV 408 of the sensor. As a result (IY) the signal 92 transmitted by the signal generator 90 and reflected from the target 80 is placed outside the FOV 8 of the sensor. Signal 92 is therefore not received by the sensor on the Missile 35. In response to this, the Missile 35 is designed to determine the absence of targets in an on-axis position

5 for first flight path 404 of Missile 35. In response; Missile 35 determines that target 0 is off-axis relative to the first flight path 404 of Missile 35. In some cases; The area around the target can include signals that are not related to the target; such as communication signals; It can be received by the sensor on the missile. to distinguish between target identification signals and non-target signals; The missile is designed to analyze each signal received by the missile

0 sensor using the signal identifier. A signal identifier is a unique identifier (eg a signal frequency) that is used by a processor to identify a signal from a target. The signal identifier is programmed or otherwise entered into the missile using one or more switches on the missile; As described earlier in this document. As the missile travels along the first flight path; The missile is designed to analyze any signals received to determine if the signal meets an on-axis target. if not

If any of the received signals indicate a target on the eal, the missile is designed to search for targets located off-axis relative to the first flight path of the missile. Method 300 also involves guiding the 312 missile through a second flight path that differs from the first flight path within the area. The second flight path locates the fixed sensor mounted on the missile at a different location within the area. as a result; Objects within lead to the FOV of the sensor

to change response to the missile's transition along the second flight path. Subsequently; The missile can identify and engage off-axis targets relative to a first flight path (eg, initial flight path). This is illustrated in a representative sample in Figures 4c and 4d; Where the second flight path 412 Ble is on a flight path in the form of the letter Na or a zigzag spiral or a spiral. in

0 some of these models; The second flight path is vertically descending while the fixed sensor of the missile 35 is simultaneously and effectively exposed to the 360 scan angle of zone 10. Hence; Assuming the fixed sensor is in the forward nose area of the missile 35; Missile 35 can effectively 'see' most or all of Area 10 with Missile 35 making one or more substantially full turns of a secondary flight path in a spiral; or

ls 5 jagged. Note that Launch Pad 30 leaves Zone 10 (this is indicated by the pad marked with hidden lines) and thus; Missile 35 can move freely across the space around Area 10 to execute Flight Path 412-Second. The start of Flight Path 412-Second is indicated by Missile 35 shown in the hidden lines. With Missile 35 moving along the second flight path 412; The sensor mounted on the 35 missile can detect signals from

0 targets located in different parts of Area 10. To implement the second flight path 412; The flight control system is designed to activate or otherwise operate one or more control surfaces (eg, wings; ailerons; and rudders) of a missile to modify the flight path of the missile. The second flight trajectory aly can be optimized on multiple factors with the missile. The size of the rocket can be taken; For example; into account when determining the second flight path. A big missile can move.”

5 for example; through a large part of the area (eg in a large circular pattern) to a position

The sensor is mounted on the missile at a different location within the region. Smaller missiles with lower flight paths can move; however; Through the missile through gia smaller by area. Other factors; Jie shape, speed and maneuverability of the missile and sensor type (FOV) can also be used to determine a second flight path for the missile. The second flight path can also guide the missile through the area with a fixed or variable declining rate of

A specific coordinate over the area. The missile is designed; in some embodiments; To descend at a constant rate (eg, 500 feet per second) along the second flight path. in other models; however; The rate of descent may not be uniform during the second flight path. A second flight path can lead to eg; to move the missile at a low rate of descent through the area; so that faces

0 The missile gradually changes the coordinate. The missile's lower rate of descent allows additional time to search the area for target discovery. With the missile coupling from the surface of Jo (Sabil Jad) Earth) to the area; however"; The missile can descend more quickly to avoid being seen by missile detection systems and/or anti-aircraft technology. The missile is designed; in some embodiments; To achieve separation criteria before the missile begins its trajectory

5 second flight. A separation criteria can be any action or process that allows the launch pad to leave the area before the missile moves through a second flight path. The onli time (eg JE) can be used as a separation criterion, such that the missile initiates a second flight path after a period of time, Jie 30 seconds, has elapsed after the missile has launched. Other separation criteria can include distance (eg » 1 kilometer (ie) that the missile travels after launch or a coordinate (eg

0 example; 1500 meters) the missile is above the surface of the area. The various GAY designs will become apparent in light of the present disclosure. The missile is designed to perform a second flight path in response to no signal being received from a target at an on-axis position relative to the missile's first flight path. In detail HST the missile is designed; in some embodiments; To perform a second flight path in response to a target identification signal not being received during

5 fixed time period; Like five seconds. in these models; The rocket is designed for a timer start (on

Sebel Jal (using the processor within the flight control system) to measure the time it took for the missile to alay within the area. in some cases; The timer can start with the missile being launched from the launch pad. In other cases, the timer may include; on a time delay function; Where the timekeeper begins to measure time at a period of time after launch; Jie 30 seconds; To enable the launch pad to leave space. The missile is designed; In (Hal) models to implement the second flight path based on the distance traveled by the missile; Jie 2 km. In more detail; the missile is designed to specify the Mach axe to determine the de ju missile. The Mach number is the body velocity ratio ( eg" rocket) to the speed of sound in the surroundings (Je) for example (Jal air). The Mach number can be estimated in several ways; It includes the use of internal navigation systems and a global positioning system to measure speed

0 missile relative to the speed of sound for a missile moving from a first position to a second position within the region. add to that; The Mach number can also be deduced using measurements; such as axial acceleration and absolute pressure; To determine the speed of a missile. in any case; The Mach axe can be used to determine the distance traveled by the missile over a period of time. The specified distance can be used to perform the second flight path if no targets are identified during the missile's first flight path.

5 Method 300 also includes receiving 316 target signals by the fixed sensor when the missile is on the second trajectory. in a representative form; The missile is designed to determine the presence of a target within an area based on receiving a signal reflected from or otherwise offset against the target. This is illustrated in Figures 4e and 4f; With it, Missile 35 moves along Transition Trajectory 414 (eg First Flight Trajectory 404 and Second Flight Trajectory 412 in Figures 4c and 4d) within the zone.

0 10 to set targets; Jie target 80. While moving along a second flight path 412 (eg a spiral, zigzag, or o(U) trajectory the missile 5 is repositioned within zone 10 so that it enters the signal 92) reflected from the target 80) in the FOV 408 of the missile-mounted sensor 35. The sensor, Jie semi-active laser search unit, is designed to determine the presence of the target 80 in response to the detection of a reflected signal 92 (eg; receiving

5 photons from a laser signal) within FOV 408. The sensor handles in some models; Also the reference

2 to verify or otherwise determine whether signal 92 corresponds to a target; As previously described. Once verified; The guidance system on the surface of Missile 35 is designed to initiate instructions and/or commands to the flight control system to modify the second flight path of the Missile 35. Method 300 also includes the modification of the 320 second flight path of the missile to direct the missile to the target within the area based on the signal received. Once the goal is set; The missile is being designed

To adjust his flight path Je (JE flight path II) to engage the target. This is illustrated in Figures 4e and 4f; Whereby the missile 35 while moving along trajectory 4 (eg First Flight Trajectory 404 and Second Flight Trajectory 412 in Figure 4c found) receives signal 92 to identify target 80; A spin sets the path to the target 416. In the form

Lia 0 Trajectory 416 is a flight path that allows Missile 35 to memorize the received signal FOV (ala 92) of the fixed sensor mounted on Missile 35 while the missile is moving towards Target 0. Several other models will become clear in light of this disclosure. Other considerations will become clear. The various other designs in light of this disclosure, for example, as described

5 previously in this document; The missile is designed to perform a second flight path in response to no signal being received from an on-axis target relative to the missile's first flight path. The missile is designed; in some embodiments; To execute the second flight path in a specified direction relative to the first flight path in response to detecting a signal from the launch pad. In detail FST The platform is designed to generate and transmit a signal; like a laser pointer; Jala the airspace around the missile (eg JB to the left or right of the missile);

0 as the missile travels along the first flight path. Particles within the airspace around the missile reflect at least part of the signal towards the FOV of the missile-mounted sensor. This part of the signal is called the return scatter. in response; The missile is designed to detect the reflected signal (return scatter) and perform a second flight path in the direction of the detected signal.

— 4 2 — in some embodiments; The area around the target in which the guided munition travels can be modified; like a guided missile; during the execution of the first and second flight trajectories or otherwise modified to allow the missile to identify and engage the target. The missile can be designed; For example; During first and second flight execution to increase or decrease the area size (eg » from 20 square miles to a terribly mile) to detect the signal reflected from the area dads target. response to region modification; Complete

Design the missile to re-implement or otherwise save again the first and second flight trajectories within the modified area. in some cases; however; Adjustments in the area size ls can be restricted to factors (Jie the initial coordinates and the fuel capacity of the missile. In some other cases, the missile is designed to adjust the area around the target in response to target acquisition. In this case the missile is designed

0 adjusts the area using the detected signal; So that the selected target is inside the center of the area. The foregoing description of models for the current disclosure is presented for illustrative and descriptive purposes. It is not intended to be detailed or restricted to disclose Mal in the exact way that was disclosed. And many modifications and differences are available in the pain of that list. The scope of detection Jal is to be restricted not by detailed description; but rather by the protections attached to it.

Claims (1)

Protection Elements 1- Guided munition system; It includes: a guided munition that can be delivered to an area by means of a launcher that travels along a pre-programmed path to the area; The guided munition is designed to travel initially along a Jf flight path through the area and to travel to a second flight path through the area in response to the non-identification of an on-axis target when flying on the first flight path; The second flight path differs from the first flight path in that it is designed to locate a target off-axis relative to the first flight path; a sensor on the surface of the guided munition; The sensor is located for the guided munition and to detect an input signal indicating the on-axis target as the guided munition moves along the 0 -span second flight path. 2. The system of claim 1 also includes a signal generator to transmit a signal for target indication; So that the signal is reflected from the target and received by the sensor of the guided munition, sensor of the guided munition. 3. The system pursuant to claim 1; Whereas, the 560507 sensor has a scanning field between 30 and 40 degrees. 4. The system pursuant to claim 1; Where the second flight path is 0 a pre-programmed flight path Cus directs the guided ordnance through the flight path in a letter-no-large form. 5- System according to protection [o] where the guided ammunition includes a switch, the switch inserts a signal identifier into the guided ammunition to identify signals received by the sensor 5 corresponding to the target. 6. The system pursuant to claim 1; Where the second flight path is a pre-programmed flight path that directs the guided ammunition through a spiral flight path or a corkscrew flight. 7. The system pursuant to claim 1; load includes the launch pad; Where is the platform The launch is an unmanned aerial vehicle (UAV) that moves along a pre-programmed trajectory. 8- The system according to claim 1 where the guided munition is a missile and sensor 560501 is installed on the missile body in relation to the missile. 9- A method of navigating a missile at a target after the missile has been launched from a launch pad that travels along a pre-programmed trajectory within an area; The method includes: guiding the missile along the flight path of the first Jala region; response to determine that the target is off-axis relative to the first flight path; 5 Navigating a missile along a second flight path different from the first flight path (the second flight path) to a fixed sensor position on the missile body to check off-axis positions; For the first flight path; receiving a signal by the fixed sensor while traveling along the second flight path; target presence identification signal; And Modifying the second flight path to direct the missile to the target within the Bly area on the received signal. 0 - the method according to claim 9; It also includes target identification based on the signal received. — 7 2 — 1- The method according to claim 10) where target identification involves comparing a signal identifier of the received signal using the target information stored on the missile. 2- The method according to claim 9 where navigating a missile begins along the flight path The second flight path in response to the missile moving a predetermined distance through the area along the first flight path without detecting the target 3- The method according to claim 12, where the predetermined distance is at least two kilometers 0 14- The method according to claim 9 Cus initiates guidance of the missile along the flight path (SE path) in response to the movement of the missile through the area for a predetermined period of time without detecting the target. 6. The method in accordance with claim 9; fan Cus directs the missile along the second flight path after the separation criteria ¢ are met to allow platform 1 to exit the area before ed the second flight path. 0 17- A computer program product comprising one or more non-temporary machine-readable media that encodes a set of instructions Al that when executed by one or AST processors leads to the execution of an operation to direct a missile to a target within an area; The process includes: carrying out guidance of the missile through a first flight path within the area; Response to determine that the target is off-axis relative to the first flight path 5 Executing missile guidance along a second flight path different from the flight path the first flight path the second flight path to a fixed sensor position on the missile body to check off-axis positions relative to the first flight path; receiving a signal by the fixed sensor while traveling along the second flight path; target presence identification signal; And the implementation of the second flight path modification to direct the missile to the target within the ly area on the received signal. 8. A computer software product pursuant to claim 17; It also includes target identification based on the signal received. 9- The product of the computer program according to Claim 17 wherein the execution of missile guidance along the second flight path begins in response to the missile traveling through the area along the first flight path for at least one predetermined period of time and a predetermined distance. 5 20- Software product pursuant to claim 17) where execution of missile guidance occurs during the second flight path after the separation criteria are met; Sal the launcher from leaving the area. 1- Software product ly of claim 17) The second flight path 0 is a pre-programmed flight path that guides the missile through a U-shaped, spiral, or corkscrew flight. Figure 1a remove the sign 1 8 Aa 54 i a( 8 ; 4 l l a a a at TN LE] | i Sarooq at NGF a ® > va / 0 XX | / // sign I ro send sign ] de 1 Figure AB Z 2 Tah ‎A | 1 | fp 3 Ni. 3 A E |[ oo 7 | D 3 A 37 —_ 3 1 —_ . iv form i. 1 4 : 1 1° — 3 2- ab 5 he 1.) and 3 | n |5 and 2 $ oy a H - um | | I 3 le'ya 3 3 x i i Se J mam 3 gd 2 8: 1 1 > \ 1 - \ 4 m \ 5 ] < a a You launch a rocket from tla launch. The aE missile includes the Mitch Salle Tai 1 extension that the target is far from the orbit in proportion Po x vod x ok 3 for the path of pale 0 first for the missile Khay Kou dg a for Sari During a flight path in 8 g > rie | receiving a target signal via [AE AS 1 b a 3 Whitton BE Ro on 3rd q ray heed! Samad BRE A eda cd TREE Na Ra Tg es PR ta gtd) to whagh + tg — 3 4- i $ § Lr Wt 3 in 1, AL 7 c 3-7 3 3: X - > 2 ws : — 3 5- Fig. B 3 i ANY a 3 z | B Cp 7 tT i 0 i m 5 1 | A. 2 - 3 miles I © | v 3 2 A 1 “AN MA 3 1 = SE A 2 2 — 3 6 — zd Jed z and Tal] i 3 ä 1 , y 0 a 2 ; M Dams — Lee me + sn my - = ~ i ; 0, . J 3 Foe Hy 9 #2 a a 0 =: g \ 5 Wo 1 8 m ) ih 3 i 3 f 4 5 HB ; ) z Z Figure 4 of 1 Ma 21.2; re for ES 1 er 9 4 < : 8 i.e. alm mac - 3 º (! 5 z hi | - 2 1 .a a m 3S ~~ oa i | ,3 1 a a | 1 | 1 5 y y A y 8 3 “ > 3 4 | | | y 7 1 3 1 | i 83 Be | a l y 1 | y "0 A \ \ badly V \ z b kn 4 — 3 8 — fig. e 1: Fos 1 b live 3 3 + ug dr / laa 1 - ; Min > Monastery: A 3 - : . AN i J 3. oo ] = be i = i $3 3 | Py f 3 z 47 -9 3 _— form 3% A NY]O 1 1 0 ad 7 1 = oo m ' 0) 1 7 3 yd | Pd o 3 a 1 sr 3 0 m A EN 1 0 140 no > a a son soni a m [gC) 2 lm hurr 37 [A 1 0 " a b | | H 3 ° َ ْ | i z \ a | 3 3 a z | /\ j J 3 - The Saudi Authority for Intellectual Property Sweden Authority for Intellectual Property pW RE .¥ + \ A 0 § Um 5 + < Ne ge “Benaj > Aye Ki Jada Li Days TEE Bbha Nase eg + Ed - 2 - 3 .++ .* provided that the annual financial fee is paid for the patent and that it is not null and void due to its violation of any of the provisions of the patent system, layout designs of integrated circuits, plant varieties and industrial designs or its implementing regulations. »> Issued by + BB 0.B Saudi Authority for Intellectual Property > > > “+ PO Box 1011 .| for ria 1*1 uo ; Kingdom | Arabic | For Saudi Arabia, [email protected]