[go: up one dir, main page]

WO2026005740A1 - Missile utilisant une source d'énergie chargée dans le lanceur - Google Patents

Missile utilisant une source d'énergie chargée dans le lanceur

Info

Publication number
WO2026005740A1
WO2026005740A1 PCT/TR2025/050652 TR2025050652W WO2026005740A1 WO 2026005740 A1 WO2026005740 A1 WO 2026005740A1 TR 2025050652 W TR2025050652 W TR 2025050652W WO 2026005740 A1 WO2026005740 A1 WO 2026005740A1
Authority
WO
WIPO (PCT)
Prior art keywords
missile
energy
voltage
storage unit
energy storage
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
PCT/TR2025/050652
Other languages
English (en)
Inventor
Ali Murat GÜNÇAN
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Roketsan Roket Sanayi ve Ticaret AS
Original Assignee
Roketsan Roket Sanayi ve Ticaret AS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Roketsan Roket Sanayi ve Ticaret AS filed Critical Roketsan Roket Sanayi ve Ticaret AS
Publication of WO2026005740A1 publication Critical patent/WO2026005740A1/fr
Pending legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Definitions

  • the present invention relates to a missile system consisting of missile contains an energy storage battery that is charged before launch instead of a thermal battery and optimised with voltage converter circuits and a launcher containing circuits to charge/discharge the energy storage battery, to reduce costs and increase efficiency.
  • Missiles are weapons that are launched from the air, land or sea to reach their target, usually carrying an explosive load. Missiles usually follow a programmed path towards the target and hit the target. Although missiles are generally used for military purposes, they are also used in space research and scientific studies. Missiles can also be used as a defence system against air defence systems. State-of-the-art missiles have the ability to hit the target very precisely and play an important role in military strategies. Thermal batteries are widely used in missile control and guidance systems. These batteries produce the electrical energy necessary to start the missile engine and ensure that the missile is directed towards its target.
  • Thermal batteries have the ability to operate reliably by means of the special chemicals they contain.
  • thermal batteries are a durable and reliable energy source suitable for long-term use. By using thermal batteries in missiles, targets can be reached with longer ranges and more effectively. These batteries ensure that missiles advance towards targets accurately and reliably and that the target is effectively hit.
  • Said invention generally relates to systems and methods for providing electrical power using supercapacitors.
  • power and data are transferred between at least one modified Hydra 70 type guided rocket positioned within the launch body and activated before launch and the launch vehicle.
  • Power is stored in at least one supercapacitor within the rocket.
  • the invention uses only a supercapacitor as an energy source and does not include any structure or system that provides efficiency in energy management.
  • the invention does not mention the existence of any circuit that increases or decreases voltage in order to use the maximum amount of energy in energy storage products, or increases or decreases voltage depending on the changing conditions during flight. With this situation, the patent has significant efficiency and security gaps since there is no optimisation during charging or discharging of the energy storage unit in the event of aborted firing.
  • the present invention relates to a missile system consisting of missile contains an energy storage battery that is charged before launch instead of a thermal battery and optimised with voltage converter circuits and a launcher containing circuits to charge/discharge the energy storage battery, to reduce costs and increase efficiency, which meets the above-mentioned requirements, eliminates all disadvantages and brings some additional advantages.
  • the aim of the invention is to use different solutions optimised with voltage converter circuits for energy storage in addition to the supercapacitor in the developed rechargeable missile and to increase security with charging and discharging methods.
  • the aim of the invention is to increase the missile efficiency by means of optimisation while reducing the cost.
  • Another aim of the invention is to provide an easily accessible, low-cost and easily producible solution by means of the use of an energy storage battery optimised with voltage converter circuits instead of a thermal battery.
  • Another aim of the invention is to provide high energy efficiency by means of the efficient use of the voltage of the energy storage unit used in the missile and the rapid charging of the energy storage unit via the missile launcher system.
  • Another aim of the invention is to ensure safety by discharging the energy of the energy storage unit in the missile in case the shot is cancelled.
  • Figure-1 is the schematic general view of the connection diagram of the chargeable/dischargeable missile system which is the subject of the invention.
  • Missile 121 Missile Computer
  • the missile system (100) that consists of a missile (120) that is charged before launch and instead of a thermal battery, has an optimised energy source (130) with a voltage boost circuit (132) and voltage buck circuit (133), and launcher (1 10) containing power unit (1 13) to charge/discharge energy source (130) in order to reduce costs and increase efficiency, is explained only as an example for a better understanding of the subject and in a way that does not create any limiting effect.
  • the missile system (100) shown in Figure-1 which is the subject of the invention, battery, capacitor, supercapacitor and hybrid capacitor are used as energy source (130).
  • the missile system (100) also comprises a voltage boost circuit (132), voltage buck circuit (133) or voltage conversion circuit (134) depending on the changing conditions during the flight in order to use the stored energy at maximum rate.
  • the missile system (100), which is the subject of the invention eliminates the security gap by discharging the energy storage unit (131 ) in the energy source (130) in case of aborted launch.
  • Said missile system (100) basically consists of a missile (120) carrying an explosive head for the destruction or damage of the determined target by remote control and a launcher (1 10) which fires the missile (120).
  • Said launcher (1 10) comprises a control (1 1 1 ) for launching the missile (120), communication (1 12) and power unit (1 13) for charging or discharging the missile (120).
  • Said missile (120) comprises a missile computer (121 ) that is in communication with the control (1 1 1 ) located in the launcher (1 10) and enables the missile (120) to be directed to the target, and an energy source (130) to provide the electrical energy needed by the missile (120) to reach the specified target.
  • Said communication (1 12) is connected to the missile computer (121 ) located in the missile (120) via the umbilical cable (114) and the power unit (1 13) is connected to the energy source (130) located in the missile (120) via the umbilical cable (114).
  • Said energy source (130) comprises an energy storage unit (131 ) and a conversion circuit (134).
  • Said conversion circuit (134) comprises a voltage boost circuit (132) and a voltage buck circuit (133).
  • Said energy storage unit (131 ) is connected to the voltage boost circuit (132) and voltage buck circuit (133) gathered under the conversion circuit (134).
  • the current, voltage, power and similar electrical requirements in the energy storage unit (131 ) and conversion circuit (134) vary according to the needs of the missile system (100).
  • the type of energy storage unit (131 ) selected for the missile (120) charging solution current and voltage values should be calculated.
  • the upper limit values of the voltage and current capacities of the power unit (1 13), and umbilical cable (114) located in the launcher (1 10) and the energy storage unit (131 ) located in the missile (120) should be selected.
  • the characteristics of said energy storage unit (131 ), power unit (1 13) and umbilical cable (1 14) units should be evaluated together and the most suitable solution should be found with more than one optimisation process by applying design changes. For example, in case a supercapacitor is selected as the energy storage unit (131 ), this means charging the capacitor with the maximum constant current it can withstand and stopping the charge at the maximum voltage value it can withstand, and using it for the shortest time for charging.
  • the power unit (1 13) After energy storage unit (131 ) is charged before launching, in case the missile (120) launch operation is abandoned due to a reason such as mission cancellation or malfunction, the power unit (1 13) has equipment consisting of an electronic or mechanical electrical switch (relay, transistor, etc.) to discharge the charge on the energy storage unit (131 ) and a resistor or similar on which the energy will be spent. Appropriate voltage converters are used to recover the electrical energy to be received from the missile (120) to the launcher (110) or the platform to which the missile system (100) is connected. Recovery of the charge in the energy storage unit (131 ) on the missile (120) in case of launch cancellation is necessary for the safety of the missile system (100). It is of great importance that the power unit (1 13) and the umbilical cable (114) are selected in accordance with the current values to be used during both charging and discharging operations.
  • the output voltage of the energy storage unit (131 ) is increased by the voltage boost circuit (132) according to the voltage and current values required by the missile (120), decreased by the voltage buck circuit (133) or, depending on the changing conditions during the flight, both the increase and decrease processes are selectively performed under control by the voltage conversion circuit (134) when necessary.
  • the voltage required by said missile (120) is Vf volts, and the voltage of the energy storage unit (131 ) varies between V1 volts and V2 volts as a function of the energy used and time.
  • the voltage must first be decreased from V1 volts to Vf volts and then increased from V2 volts to Vf volts. In this way, the maximum energy in the energy storage unit (131 ) is converted into a usable form by the missile (120). This means that the flight time, weight and volume of the missile (120) are optimised.

Landscapes

  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Abstract

L'invention concerne un système de missile (100) qui est constitué d'un missile (120) qui est chargé avant le lancement et au lieu d'une batterie thermique, a une source d'énergie (130) optimisée avec un circuit d'amplification de tension (132) et un circuit abaisseur de tension (133), et un lanceur (110) contenant une unité d'alimentation (113) pour charger/décharger une source d'énergie (130) afin de réduire les coûts et d'augmenter l'efficacité.
PCT/TR2025/050652 2024-06-24 2025-06-23 Missile utilisant une source d'énergie chargée dans le lanceur Pending WO2026005740A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
TR2024/007974 2024-06-24
TR2024/007974A TR2024007974A1 (tr) 2024-06-24 2024-06-24 Firlaticida şarj edi̇len enerji̇ kaynaği kullanan füze

Publications (1)

Publication Number Publication Date
WO2026005740A1 true WO2026005740A1 (fr) 2026-01-02

Family

ID=98006833

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/TR2025/050652 Pending WO2026005740A1 (fr) 2024-06-24 2025-06-23 Missile utilisant une source d'énergie chargée dans le lanceur

Country Status (2)

Country Link
TR (1) TR2024007974A1 (fr)
WO (1) WO2026005740A1 (fr)

Also Published As

Publication number Publication date
TR2024007974A1 (tr) 2025-10-21

Similar Documents

Publication Publication Date Title
McNab et al. Development of a naval railgun
EP1508019B1 (fr) Appareil de retention d'energie et de retention des donnees dans un projectile guide
Dyvik et al. Recent activities in electrothermal chemical launcher technologies at BAE systems
McNab et al. Naval railguns
US7946209B2 (en) Launcher for a projectile having a supercapacitor power supply
Kaye et al. Induction coilgun for EM mortar
US9784523B2 (en) Hybrid propellant electromagnetic gun system
WO2014088663A1 (fr) Unité de mise à feu haute tension, système d'explosifs et de munitions, et procédé de fonctionnement de celle-ci
US8051776B1 (en) Self-cleaning cartridge actuated and propellant actuated devices
RU2107245C1 (ru) Выстрел и пусковое устройство для выстрела
US5097765A (en) Electric fuze with selectable modes
WO2026005740A1 (fr) Missile utilisant une source d'énergie chargée dans le lanceur
US6202532B1 (en) Data exchange system and method for ammunition rounds
Hundertmark Investigations on the energy chain for a naval railgun
Wisken et al. Capacitive pulsed power supply systems for ETC guns
CN113758384B (zh) 一种用于爆炸物的电子安全系统、方法及存储介质
CN212538951U (zh) 弹夹弹丸检测装置及电磁枪
Sinyaev et al. Plasma-replacement technology of ETC-ignition of powder charges in high-velocity launchers
Goodell Electrothermal chemical (ETC) armament system integration into a combat vehicle
CN114018110B (zh) 一种大口径榴弹引信电子安全系统控制系统
RU2812889C1 (ru) Реактивный снаряд
RU2206060C2 (ru) Снаряд, устройство для проверки расположенной на снаряде электрической системы и способ проверки расположенной на снаряде электрической системы
Wald et al. Electrothermal-chemical research at Soreq nuclear research center, Israel
US12196507B1 (en) Helical electromagnetic counter recoil mechanism
RU2721636C2 (ru) Многоствольный комплекс стрельбы