The Twin Missile Launcher (TML) is used for firing Konkurs Anti-tank Guided Missile (A TGM). Missiles are fired from tracked I wheeled vehicles such as Infantry Combat Vehicles, Light Armoured Tracked Vehicles and Jeep. TML is designed for aiming at a target, launching and guiding the second generation Anti-tank Gui...

An Outdoor Simulator is conceived, designed and developed for training a Pilot in Anti Tank Guided Missile (ATGM) such as Milan in launching and guidance. The system consists of a Launcher with Optical Device, Telescope with Charge Coupled Device (CCD) Camera, Guidance Electronic Unit (GEU) Box, Dummy Missile, Trigg...

The test equipment is used for checking the functioning of launcher for thrust vector controlled, wire guided second-generation antitank guided missile. The test equipment is designed with state of the art technology using microprocessor, capable of identifying the faulty subassembly. The test result is given as GO ...

Described herein an X-band miniature Antenna (100) fitted on Infantry Combat Vehicle (ICV) comprising a helical coil (200) mounted on a rod made of dielectric material to operate in an axial mode emitting a beam of radio waves with circular polarization in a preselected direction wherein one end of the helical coil ...

ELECTROMAGNETIC BEAM MODULATION AND ENCODING SYSTEM FOR GUIDANCE OF GUIDED WEAPON The present disclosure relates to an electromagnetic beam modulation and encoding system for guidance of a guided weapon essentially an anti-tank guided missile and guided bombs. The system comprises a disc-shaped optical chopper (100...

The present disclosure relates to a system for controlling a radio frequency (RF) transmission module (102) of a guided weapon automatically and a method to operate the same. The method (200) comprises receiving (202), by a control unit (108) via a signal conditioner (106) of the system, a first signal (104a) and a ...

The present invention discloses a test system for precursor jet velocity measurement and method thereof. The method disclosed in the present invention is an indirect way to determine precursor jet velocity. The test system (1) mainly includes a precharge (2) and a contact foil (3). The system (1) further includes an...

The present invention discloses a control actuation system for ATGM. The CAS (100) comprises four blades/fins (101) wherein each blade is equipped with individual motor, and a lead screw (102). CAS (100) includes mechanical assembly and electrical system with PID based actuation control unit for executing the comman...

The present invention relates to an Aerodynamic Load Simulator for testing Control and Actuation System. The load simulator (100) is used in the lab for testing the static and dynamic load withstanding capability of motors used in the control actuation system (CAS) (200). The load simulator (100) for testing control...

The present invention discloses a pulse separation device for the chamber of dual pulse rocket motor. The pulse separation device (PSD) (10) separates the dual pulse rocket motor chamber into two partitions i.e. Chamber-I (1) and Chamber-II (2). The PSD (10) consists of multiple components, out of which, one insulat...

A method for controlling a torpedo 200 by utilizing an integrated test system 150 of an electronic device 100. The method includes receiving a response from the torpedo 200 in response to a transmitted generated simulated target signal and a generated simulated speed signal. The method includes determining whether t...

Disclosed is a method of controlling a static firing of a rocket motor using a pyro console system. The method includes generating a first Ignition Safe Arm (ISA) command for arming one or more relays for the static firing of the rocket motor. The method further includes determining whether a first ISA feedback is r...

The present disclosure relates to an actuation test setup (100) for testing a tail unit (210) of an underwater vehicle. The actuation test setup includes a frame (106), a plurality of holders (104), and at least one support bracket (102). The plurality of holders (104) is attached to an inner surface of the frame (1...

Disclosed are systems and a method for operating a seeker (103) of an anti-tank guided missile (ATGM) (101). Firstly, one or more targets are identified within a field of view (FOV) of the seeker (103) from an infrared (IR) based image data associated with the one or more targets within the FOV of the seeker (103). ...

The present disclosure relates to a test apparatus (100) to measure a performance of a propulsion unit. The test apparatus (100) includes a base (106) having a test jig (110), a housing (107) having an opening (109) to receive the propulsion unit, at least one load cell (102), and a servo mechanism (101) installed o...

ABSTRACT OF THE INVENTION CASKET WITH A SPACER FOR AN UNDERWATER VEHICLE A casket (100) for engaging a plurality of fins of an underwater vehicle that includes an outer shell (102) and a plurality of rails (106) adapted to receive the plurality of fins. The casket (100) also includes a holder block (116) extending...

ABSTRACT OF THE INVENTION ANTI-SINKING DEVICE FOR AN UNDERWATER VEHICLE An anti-sinking device (100) is disclosed that includes a chamber (104) having an opening to hold a plurality of metallic balls (106). The anti-sinking device (100) also includes a block (108) removably installed at the opening and adapted to...

Disclosed herein is a test fixture (100) for measuring axial thrust force, lateral thrust components (side forces) and rolling moment generated by a reaction engine (122) with TVC (134). The test fixture (100) comprises a base (102), a housing assembly (104), a thrust load cell (106), and a ring assembly (108). The ...

A two-axis gimbal (102), that has a payload holder (206), an inner body (204), and an outer body (202), is disclosed. The outer body (202) comprises a first drive motor (210) adapted to pivot the inner body (204) about a first axis (AA’). The first feedback unit (212) is adapted to generate a first feedback signal c...

The present invention discloses a unified propulsion system (100) for Anti-Tank Guided Missile. The propulsion system (100) mainly comprises flight motor assembly (A), launch motor assembly (B) and nozzle assembly (C). These flight motor assembly (A) and launch motor assembly (B) are joined together with fasteners a...

The present invention relates to a munitions arming unit for airborne application. The munition arming unit (10) is designed to ensure that the weapon is in “armed” condition only when desired and in “safe” condition at all other times. The munition (M) and the drone are communicatively coupled with an umbilical con...

The present invention relates to a zoom optical system for laser beam rider guidance technique for missile application. The system comprises four lenses (1, 2, 3, 4) made of fused silica material. In laser beam rider guidance (LBRG) system, a spatially modulated laser beam is projected towards target and missile fli...

The present invention discloses release mechanism of umbilical connector for anti-tank guided missile. The release mechanism of umbilical connector (UC) disengages umbilical connector from launcher to missile when missile is launched. The mechanism comprises two pairs of connectors for connecting missile (7), launch...

The present invention discloses a dead weight dump mechanism for light weight torpedo. The invention is designed to recover the torpedo (100) after the mission sequence is completed. The mechanism of the present invention creates positive buoyancy for a negative buoyant torpedo (100) for smooth recovery of the torpe...