Multiple missiles
The multi-missile system addresses the inefficiencies of existing systems by enabling multiple targets to be hit with a single missile, ensuring precise and widespread damage while evading air defenses.
Patent Information
- Authority / Receiving Office
- WO · WO
- Patent Type
- Applications
- Current Assignee / Owner
- SAMSUN ÜNİVERSİTESİ
- Filing Date
- 2025-12-16
- Publication Date
- 2026-07-09
AI Technical Summary
Existing missile systems are inadequate for simultaneously striking multiple targets with a single missile, leading to inefficiencies in time and cost, and are vulnerable to air defense systems.
A multi-missile system comprising a main missile with detachable smaller missiles that separate and target multiple targets after launch, guided by ground stations, using foldable fins and precise separation mechanisms for accurate targeting.
Enables simultaneous destruction of multiple targets with a single missile, reducing time and cost, while avoiding interference from air defense systems and increasing damage over a larger area.
Smart Images
Figure TR2025051702_09072026_PF_FP_ABST
Abstract
Description
[0001] MULTIPLE MISSILES
[0002] TECHNICAL FIELD
[0003] The invention relates to a multi-missile system that enables the destruction of multiple targets with a single missile, resulting in damage over a larger area and long-range damage in military operations, saving both time and cost.
[0004] BACKGROUND
[0005] Missiles are generally self-propelled, guided or unguided weapon systems designed to travel at high speed toward their targets. These systems are designed to carry a warhead or payload over a certain distance and are used for military and civilian purposes.
[0006] Missiles play a central role in modern defense and attack strategies. Their wide range and high precision provide a critical advantage in military operations for neutralizing enemy defenses or attacking long-range strategic targets. Multiple missile systems allow for the simultaneous firing of multiple missiles to achieve effectiveness in wide-area attacks.
[0007] Modern missile technologies focus on high precision, low detectability (stealth technology), hypersonic speeds, and Al-assisted guidance systems.
[0008] Although various proposals and applications for multiple missile systems have been developed in the current state of the art, these developments are insufficient. Some applications for inventions developed for this purpose are given below.
[0009] The invention, described in application number “CN103090745A”, which is in the state of the art, relates to a missile that provides medium-range velocity variation and an anti-interference method. It is stated that the missile overcomes the problem of being vulnerable to interference from the sides, front, and rear during constant flight at medium speed by using a three-stage warhead.
[0010] The invention described in application number “W02005019764A2”, which is in the prior art, relates to a multi-stage missile, a propellant, and a munition delivery vehicle carrying one or more munitions. The propellant accelerates the munition delivery vehicle, which then separates from it. The munition delivery vehicle maneuvers towards the target, and the individual munitions separate and are independently directed towards the target.The prior art includes multiple missiles and munition systems. However, there is no missile capable of simultaneously striking multiple targets in each area with a single missile, thus saving both time and cost, engaging targets in the face of air defense systems, and carrying multiple missiles on a single carrier platform.
[0011] Consequently, due to the above-mentioned shortcomings and the inadequacy of existing solutions in this area, development in the relevant technical field has become necessary.
[0012] AIM OF THE INVENTION
[0013] The primary aim of the invention is to enable multiple targets to be hit with a single missile. This saves both time and cost.
[0014] Another aim of the invention is to carry multiple missiles on a single carrier platform.
[0015] Another aim of the invention is to enable multiple missiles to inflict more destructive and widespread damage over a larger area in an effective battlefield.
[0016] Another aim of the invention is to fire multiple missiles simultaneously within a single missile. This prevents the interference of air defense systems.
[0017] FIGURE LIST FIGURE -1; This is a drawing showing the general view of the multiple missile that is the subject of the invention.
[0018] FIGURE -2; This is a drawing showing the detachable missiles of the multiple missile that is the subject of the invention.
[0019] Reference numbers:
[0020] 1. Explosive Warhead
[0021] 3. Missile Avionics-1
[0022] 4. Foldable Fin
[0023] 5. Engine
[0024] 6. Detachable Fuselage
[0025] 8. Separation Compartment
[0026] 9. Center Ring
[0027] 10. Nose Cone11. Separation Point
[0028] 12. Separation Avionics
[0029] 13. Detachable Missile
[0030] 14. Secondary Nose Cone
[0031] 15. Fins
[0032] DETAILED DESCRIPTION OF THE INVENTION
[0033] The invention relates to a multi-missile system that enables the destruction of multiple targets with a single missile, resulting in damage over a larger area and long-range damage in military operations, saving both time and cost.
[0034] The invention includes the operation of the missile avionics (3), which enables the missile to fly, the operation of the missile's internal sensors such as the explosive warhead (1) that damages the target, the GPS that provides position determination, and the altimeter that allows the missile to see the appropriate altitude, the foldable fin (4) which is foldable to allow the detachable missiles (13) to take up less space inside the missile, the engine (5) that enables the missile to fly, the detachable fuselage (6) that allows the detachable missiles (13) to be carried, the separation compartment (8) that secures both the missile avionics (3) and the engine and prevents the parts from separating from each other, the central ring (9) that secures the missile engine and holds the nose cone (10), the nose cone (10) that provides the dynamics of the missile and makes the missile more stable, the separation cone (11) which is detonated with gunpowder and separates the detachable missiles (13) inside the main missile when detonated, the separation avionics (12) which is the system that enables the detachable missiles (13) inside the main missile to separate in the air, and at least 3 detachable missiles (13) inside the main missile that are fired after separation. The secondary nose cone (14), which enables the main missile to continue moving in the air after separation, consists of fins (15) which increase the missile dynamics, make the missile more stable by enabling it to fly and stay balanced.
[0035] The invention relates to a missile system comprising a main missile and three detachable missiles (13) containing three identical smaller missiles. In the invention, the detachable missiles (13) are positioned almost halfway up the main missile, with the nose cone (10) and the secondary nose cone (14). The separation of the upper part of the missile is initiated by the firing of the propellant thanks to the separation avionics (12) during the mission. The upper half of the main missile separates withpropellant at a certain height, and this separation allows the three detachable missiles (13), which are in the upper half of the missile, to be released.
[0036] The invention consists of a main missile that is launched as a whole from the ground platform. After a while, the separation avionics (12) is activated by gyroscope and altimeter sensors in the missile avionics (3), and the propellant is detonated. As a result, the upper half breaks apart into three new missiles, called separable missiles (13), and the remaining main missile continues towards the target with a new nose cone, the secondary nose cone (14). The missile, launched from a standard launch platform, undergoes a separation process in the air after the required altitude is measured and the separation point (11) is determined by gyroscope and altimeter in the missile avionics (3). In other words, the launch process is carried out from a standard launch platform. When the missile separates from the platform, the separation is achieved by detonating the propellant at a certain altitude using an altimeter and separation avionics (12). The altimeter precisely measures the separation altitude of the missile and initiates the separation process when the required altitude is reached.
[0037] With the separation of the upper part, the secondary nose cone (14) inside the main missile is revealed, and the lower half becomes the main rocket and continues to advance towards the target. The upper part of the main missile separates with the help of gunpowder, and during this separation, the detachable missiles (13) are released inside the main missile. Since these detachable missiles (13) are freely attached, they begin to fall from their position. Now of separation, the detachable missiles (13) are ignited in the engines within a maximum of 5 seconds with the help of the launchers located in the missile avionics (3) in each pair of missiles. This process takes place within a maximum of 5 seconds after the separation of the small missiles is completed. When the detachable missiles (13) are fired, they are fired in the correct position with the help of the gyroscope in the missile avionics (3). Foldable fins (4) are used to bring the missiles to the correct position in the air. Each of the detachable missiles (13) is directed towards the designated targets and fulfills its mission. The invention is optimized to ensure that the main missile and the separable missiles (13) reach the target effectively and with the desired accuracy. This targeting system is in the flight systems of the missiles, and the missile avionics (3) are controlled from the ground stations.The reliability and effectiveness of the missile system are enhanced by precise engineering details such as separation altitude and missile firing timing. At this stage, each missile is guided to its target by the ground station. The missile avionics (3) are controlled from the ground stations to guide the missiles to the target. Each of the main missile and the separable missiles (13) performs its task in such a way as to reach the targets as planned. These arrangements are made through the flight computer located in the missile avionics (3). This system increases the accuracy and effectiveness of target acquisition in the missile design.
[0038] When launching the missile, the launch pad uses a propellant separation system to separate at a certain altitude. After the missile is launched and reaches its maximum altitude, the landing moment is measured with an altimeter and separation is ensured at an angle of approximately 60 degrees. Positioning at the determined target is ensured by GPS.
[0039] The invention allows for the simultaneous destruction of multiple targets, preventing surrounding elements from escaping and minimizing the miss rate. It enables the destruction of larger targets in a shorter time. The invention saves costs by using a single missile instead of multiple missiles. It offers an effective solution against air defense systems. The detachable nature of the missile allows air defense systems to lock onto a single missile, while the remaining missiles destroy the target. Cost-effectiveness is achieved by carrying multiple missiles on a single carrier platform. The missiles inflict more destructive and widespread damage over a larger area on the battlefield. Multiple targets are destroyed with a single missile, resulting in cost and time savings.
Claims
CLAIMS1. A multiple missile system, characterized in that it comprises:- An explosive warhead (1) that inflicts damage upon the target,- a missile avionics unit (3) including GPS for position determination, onboard sensors enabling altitude control of the missile, and a flight computer that ensures the operation of these sensors and controls missile flight,- a foldable fin (4) configured to minimize the space occupied by detachable missiles (13) within the main missile, and to position the detachable missiles (13) after separation from the main missile, - a motor (5) enabling the missile’s propulsion,- a detachable fuselage (6) that carries the detachable missiles (13), - a separation compartment (8) securing both the missile avionics (3) and the motor (5), and preventing the components from detaching from each other,- a center ring (9) that secures the missile motor (5) and holds the nose cone (10),- a nose cone (10) that stabilizes the missile and contributes to its aerodynamic performance,- a separation point (11), an area within the main missile where the detachable missiles (13) separate upon ignition of an explosive charge, - a separation avionics (12) unit responsible for enabling the separation of detachable missiles (13) from the main missile while in flight, - at least three detachable missiles (13) housed within the main missile and ignited after separation,- a secondary nose cone (14) ensuring that the remaining half of the main missile continues its flight toward the target after the detachable missiles (13) have separated, and- a multiple of fins (15) that enhance missile dynamics, ensure stable flight, and maintain aerodynamic balance.
2. The multiple missile system according to claim 1, characterized in that it comprises at least three detachable missiles (13), each configured to bedirected toward predetermined targets, thereby enabling engagement of multiple targets simultaneously.
3. The multiple missile system according to claim 1, characterized in that it comprises a missile avionics unit (3) configured to enable both the main missile and each of the detachable missiles (13) to be guided toward their respective targets via a ground control station.
4. The multiple missile system according to claim 1, characterized in that it comprises a separation avionics (12) unit configured to ignite the explosive charge enabling in-air separation of the missile after the required altitude has been measured by the gyroscope and altimeter located within the missile avionics unit (3) and the separation point (11) has been determined.
5. The multiple missile system according to claim 1, characterized in that it comprises at least three detachable missiles (13) positioned in a free configuration within the main missile body.