DESC:RELATED PATENT APPLICATION(S):

This application claims the priority to and benefit of Indian Provisional Patent Application No. 202241054196 filed on September 22, 2022; the disclosures of which are incorporated herein by reference.

FIELD OF THE INVENTION:

The invention generally relates to release mechanism for an umbilical connector which is utilized to disengage the umbilical connector from launcher to missile when missile is launched. Particularly, the invention relates to the release mechanism of umbilical connector for Anti-Tank Guided Missile (ATGM). More particularly, the present invention relates to novel release mechanism for umbilical connector which minimizes the transfer of unavoidable forces from missile to launcher and also disconnects the umbilical connector from the missile and moves the connector to an isolated position as the missile is launched.

BACKGROUND OF THE INVENTION:

The umbilical connector is used to connect a missile to ground support equipment on the launch pad before launch. The umbilical connector includes an umbilical cable which is capable to carry electrical power, ethernet, communications, firing pulse, video analogue data and telemetry data and to transfer it to missile from the launcher and vice-versa. The umbilical connector is disconnected from the missile at the time of launch of missile and separates the missile from the ground support. Umbilical connectors are also used between rocket stages, and between the rocket and its spacecraft payload, these umbilicals are disconnected as stages are disconnected and discarded.

Currently various methods are employed for release of umbilical connector in missile launching systems. In one widely used launching system, the missile launches from a tubular structure which is called launch tube. In all launching systems, it is necessary that electrical power to be supplied to the missile until the launch motor is fired. Some existing prior arts related to releasing of umbilical connector of missile system are as follows:

US patent no. US8052444B1 discloses a latching release system for a connector assembly. The system includes a secondary latching release mechanism coupled to a lanyard release connector and a lanyard. The lanyard release connector has a primary latching release mechanism adapted to hold a complementary connector of a payload. The secondary latching release mechanism includes a mechanical forcing device that applies a force for actuating a primary latching release mechanism of the latching release connector when the mechanical forcing device is actuated by the lanyard such that the payload may be jettisoned from a vehicle.

European patent publication no. EP2392889A2 discloses umbilical connecting device which includes a missile navel that is hinged to a side of a missile and pressed outside the missile by a first pressing member; and a launch pad navel that is hinged to a side of a launch pad, pressed against the missile navel by a second pressing member, and electrically connected with the missile navel that slides when the missile is mounted and disconnected from the missile navel that slides when the missile is launched.

In umbilical connectors of above prior arts and also in most of the existing types of umbilical connector, the connector is located at the end of the missile and as the missile is launched, it automatically pulls away from launcher. This type of umbilical connector works very satisfactorily in most of the launchers. But in case of advanced ATGM’s, apart from electrical power lines, ethernet, communication, firing pulse, video analogue data transfers to missile from launcher and vice versa through umbilical connector. All together these communication lines become a bunch of cables and are required to route to end of missile passing through all missile sub sections. Sometimes it is very difficult to route to end of missile due to space constraint and critical thin shells. There may be intermediate joints are required for umbilical lines in between missile sub sections for integration, due to number of joints, there may be a chance of loss in signal and also delay in signal. Considering all these limitations, it is more efficient and economical to locate the umbilical connector at the side of the missile rather than end of the missile.

Therefore, there is a need to design a more efficient umbilical connector to locate near to the missile. To attain these desired results, the present invention provides a unique arrangement of the umbilical connector release mechanism which transmits a minimum of forces between the launch tube and the missile, which disconnects the umbilical connector from the missile when missile is launched. It reduces the intermediate joints therefore losses and delay in signal are minimized and it is also economically feasible solution.

OBJECT(S) OF THE INVENTION:

The primary object of the present invention is to provide a release mechanism of umbilical connector for Anti-Tank Guided Missile (ATGM).

Another object of the invention is to provide a novel release mechanism of umbilical connector which minimizes the transfer of unavoidable forces from missile to launcher through the release mechanism and also disconnects an umbilical connector from the missile and moves the connector to an isolated position as the missile is launched.

Another object of the invention is to provide a unique arrangement of an umbilical connector mechanism which reduces the intermediate joints required for umbilical lines in between missile sub sections for integration.

Another object of the invention is to design a novel release mechanism of umbilical connector which easily releases the missile umbilical connector with minimal frictional forces and without any losses and delay in signal before missile launch.

Another object of the invention is to provide a novel release mechanism of umbilical connector which ejects the missile or space vehicle smoothly from the ground support equipment at the time of launch of missile.

Another object of the invention is to provide a novel, simple and reusable umbilical connector.

Yet another object of the invention is to provide a method for working of a release mechanism of umbilical connector for Anti-tank Guided Missile (ATGM).

SUMMARY OF THE INVENTION:

Accordingly, the present invention provides a release mechanism of umbilical connector for Anti-tank Guided Missile (ATGM). The present invention relates to an umbilical connector release mechanism which is utilized to disengage an umbilical connector from launcher to missile when missile is launched. In particular, the invention aims to release mechanism of umbilical connector which minimizes the transfer of unavoidable forces from missile to launcher through the mechanism and also disconnects an umbilical connector from the missile and moves the connector to an isolated position as the missile is launched. Thus, the umbilical connector is simple and reusable. Also, the invention provides a unique arrangement of an umbilical connector mechanism which reduces the intermediate joints required for umbilical lines in between missile sub sections for integration and therefore, the losses and delay in signal are minimized.

Further, the present invention provides a method for working of a release mechanism of umbilical connector for Anti-tank Guided Missile (ATGM). The invention provides the economically feasible solution in launching system.

In one aspect of the present invention, the invention provides a release mechanism of an umbilical connector (1) for Anti-tank Guided Missile (ATGM), said mechanism comprises:
- two pairs of connectors connected through flex printed circuit board (PCB) (12), wherein a first pair of connectors comprises a missile side micro-D connector (13) and a launch tube side micro-D connector (14) placed in between a missile (7) and a launch tube (2), and a second pair of connectors comprises a launch tube side round connector (15) and a command launch unit side connector placed in between the launch tube (2) and a command launch unit (CLU);
- a lever (16) having a tip potion (17);
- a ramp portion (19) mounted on an on-board computer (OBC) front circular disc (21) for lifting the lever (16) during movement of the missile (7);
- a stopper (20) mounted on the missile (7) for restricting the rotation of the lever (16) during initial travel of missile (7); and
- spring loaded plungers (22) mounted on both sides of the lever (16) for locking;
wherein after launching, when the missile (7) travels approximately 5mm distance from initial position, the missile side micro-D connector (13) and the launch tube side micro-D connector (14) are disengaged from the stopper (20) and the tip portion (17) of the lever (16) contacts the ramp portion (19) of umbilical connector bracket; and
when the missile side micro-D connector (13) and the launch tube side micro-D connector (14) are completely disengaged from the launch tube (2), the first pair of connectors are moved upward and locked by the spring loaded plungers (22) and the missile (7) ejects from the launch tube (2).

The two pairs of connectors connect the missile (7), the launch tube (2) and the command launch unit (CLU).

The launch tube (2) comprises a metal umbilical connector (UC) insert (3) to mount the umbilical connector (1) on it and wherein the umbilical connector (UC) insert (3) comprises hole passages (5) for locating hinge pins (24) and oblong holes passages (6) for locking the lever (16).

The launch tube (2) comprises taping holes (4) for mounting a housing (11) of the umbilical connector (1) and wherein the housing (11) of the umbilical connector (1) houses all the components of the umbilical connector (1).

The flex printed circuit board (PCB) (12) having two ends, one end has micro-D connectors (13, 14) to missile side and other end is for the command launch unit (CLU) with the launch tube side round connector (15).

The missile side micro-D connector (13) being a male micro-D sub connector mounted on the on-board computer (OBC) front disc (21) connects the launcher to the on-board computer (OBC).

The launch tube side micro-D connector (14) being a female micro-D sub connector connects the launcher to the on-board computer (OBC).

The micro-D connectors (13, 14) are selected from screw fitted connectors or snap fitted connectors.

The launch tube side round connector (15) being a female round connector mates with the command launch unit (CLU) side male round connector.

The launch tube side round connector (15) is clamped with the launch tube (2) and the command launch unit (CLU).

The on-board computer (OBC) provides the electrical power, ethernet, communication, firing pulse, video analogue data to missile from the launcher and vice versa.

The launch tube side micro-D connector (14) along with flex printed circuit board (PCB) (12) is assembled to the lever (16) with mounting screws (23) and wherein the lever (16) has mounting holes (8) for mounting hinge pins (24).

The plunger (22) having a spring (25) is mounted on the lever (16),
wherein initially in pressed condition inside the lever (16) surface, the plunger (22) contacts with inner surface of the umbilical connector (UC) insert (3) of the launch tube (2) before launching of the missile (7),
once the missile (7) starts moving, the bottom tip (17) of the lever (16) slides on the ramp portion (19) intending to rotate the lever (16) and the top surface of plunger (22) slides on inner surface of the umbilical connector (UC) insert (3), and
after approximately 35-degree rotation of the lever (16), the plunger (22) enters in the oblong hole passage (6) due to the spring force thereby arresting the movement of the lever (16).

In another aspect of the present invention, the invention provides a method for working of a release mechanism of an umbilical connector (1) for Anti-tank Guided Missile (ATGM), said method comprises the steps of:
1) after ignition of a launch motor, a missile (7) starts sliding on a launch tube (2);
2) a missile side micro-D connector (13) and a launch tube side micro-D connector (14) are disconnected during initial movement of the missile (7);
3) after approximately 5mm distance movement, a tip portion (17) of a lever (16) contacts with a ramp portion (19) of umbilical connector bracket and the lever (16) with the launch tube side micro-D connector (14) rotate upwards about an umbilical connector hinge (18);
4) after approximately 35-degree rotation of lever (16), the lever (16) is locked by a spring loaded plunger (22); and
5) the missile (7) ejects from the launch tube (2).

The above description merely is an outline of the technical solution of the present disclosure. The summary is descriptive and exemplary only and is not intended to be in any way restricting. In order to know the technical means of the present disclosure more clearly so that implementation may be carried out according to contents of the specification, and in order to make the above and other objectives, characteristics and advantages of the present disclosure clear and easy to understand, specific embodiments of the present invention will be described in detail below.

BRIEF DESCRIPTION OF DRAWINGS:

The drawings described herein are intended to provide a further understanding of the invention and is intended to be a part of the invention. However, the drawings as shown are representative and non-limiting the scope of the invention. In the drawings:

Figure 1 shows the schematic view of the umbilical connector (1) of present invention mounted on the launch tube (2).

Figure 2 shows the mounting assembly on the umbilical connector (1) and the launch tube (2) interface.

Figure 3 shows the cross-sectional view of umbilical connector (1) before launch of the missile.

Figure 4 shows the cross-sectional view of umbilical connector (1) after launch of the missile wherein the missile travels around 5mm distance.

Figure 5 shows the cross-sectional view of umbilical connector (1) after complete launch of the missile.

Figure 6 shows broad view of the umbilical connector (1) and the missile (7) interface.

Figure 7 shows the perspective view of the lever assembly.

Figure 8 shows the schematic view of hinge pins (24) of the umbilical connector lever (16) of present invention.

Figure 9 shows the arrangement of lock spring (25) and lock plunger (22) on the lever (16) of umbilical connector (1) of present invention.

DESCRIPTION OF THE INVENTION:

The present invention discloses a release mechanism of umbilical connector for Anti-Tank Guided Missile.

The umbilical connector release mechanism is utilized to disengage an umbilical connector from launcher to missile when missile is launched. The umbilical connector includes an umbilical cable which is capable to carry electrical power, ethernet, communications, firing pulse, video analogue data and telemetry data and to transfer it to missile from the launcher and vice-versa. The umbilical connector is disconnected from the missile at the time of launch of missile and separates the missile from the ground support. Umbilical connectors are also used between rocket stages, and between the rocket and its spacecraft payload, these umbilicals are disconnected as stages are disconnected and discarded.

Currently various methods are employed for release of umbilical connector in missile launching systems. In one widely used launching system, the missile launches from a tubular structure which is called launch tube. In all launching systems, it is necessary that electrical power to be supplied to the missile until the launch motor is fired. One type of umbilical connector in which the connector is located at the end of the missile and as the missile is launched it automatically pulls away from launcher. This type of umbilical connector works very satisfactorily in most of the launchers.

But in case of advanced ATGM’s, apart from electrical power lines, ethernet, communication, firing pulse, video analogue data transfers to missile from launcher and vice versa through umbilical connector. All together these communication lines become a bunch of cables and are required to route to end of missile passing through all missile sub sections. Sometimes it is very difficult to route to end of missile due to space constraint and critical thin shells. There may be intermediate joints are required for umbilical lines in between missile sub sections for integration, due to number of joints, there may be a chance of loss in signal and also delay in signal. Considering all these limitations, it is more efficient and economical to locate the umbilical connector at the side of the missile rather than end of the missile.

Accordingly, the present invention provides a unique arrangement of an umbilical connector release mechanism which transmits a minimum force between the launch tube and the missile, which disconnects the umbilical connector from the missile when the missile is launched. It reduces the intermediate joints and therefore, losses and delay in signal are minimized and it is also economically feasible solution.

In one aspect of the invention, the present invention discloses a novel release mechanism of the umbilical connector for the missile or space vehicle wherein the umbilical connector is engaged the missile or space vehicle with the ground support equipment.

Figures 1-9 show the umbilical connector release mechanism and components of the present invention.

Figure 1 shows the umbilical connector (1) wherein the umbilical connector (1) is mounted on the launch tube (2) of the missile. The launch tube (2) serves the purpose of a humidity and temperature-controlled structure that provides a protective housing which combines both a launch support facility and structure.

Figure 2 shows the mounting assembly on the umbilical connector (1) and the launch tube (2) interface. The launch tube (2) comprises an umbilical connector (UC) insert (3) to mount the umbilical connector (1) on it. The UC insert (3) is made up of metal. The UC insert (3) comprises hole passages (5) to locate hinge pins (24) as shown in figure 8 and oblong hole passages for locking UC lever (16) as shown in figure 3. The UC insert (3) also comprises taping holes (4) for mounting the hosing (11) of the umbilical connector (UC) as shown in figure 3.

Figure 3 shows the cross-sectional view of umbilical connector (1). The said umbilical connector (1) comprises a housing (11), a flex printed circuit board (PCB) (12), a missile side micro-D connector (13), a launch tube side micro-D connector (14), a launch tube side round connector (15), a lever (16) having tip portion (17) and a ramp portion (19). It shows the structure of umbilical connector (1) before launch of the missile.

In particular, the present invention provides a release mechanism of an umbilical connector (1) for Anti-tank Guided Missile (ATGM) comprising two pairs of connectors which are used to connect the missile (7), launch tube (2) and a command launch unit (CLU). The first pair of connectors and second pair of connectors are connected through flex printed circuit board (PCB) (12).

A first pair of electrical connectors comprises a missile side micro-D connector (13) and a launch tube side micro-D connector (14). Both the electrical connectors (13, 14) are placed in between the missile (7) and launch tube (2). The missile side micro-D connector (13) is mounted on an on-board computer (OBC) front disc (21) as shown in figure 6. The launch tube side micro-D connector (14) is mounted on lever (16) and other side of launch tube (2). In one embodiment the connectors (13, 14) can be selected from the screw fitted connectors or snap fitted connectors. However, in one preferred embodiment, the pair of electrical connectors (13, 14) are snap fitted.

A second pair of connectors comprises a launch tube side circular or round connector (15) and a command launch unit side connector (not shown). Both the connectors are placed in between launch tube (2) and command launch unit (CLU). The launch tube side circular connector (15) is mounted on umbilical connector housing (11). In one embodiment, the launch tube side circular connector (15) is clamped with launch tube (2) and the command launch unit (CLU).

The housing (11) of the umbilical connector (1) being a structural component houses all the parts of the umbilical connector (1).

The flex printed circuit board (PCB) (12) having two ends, one end has micro-D connectors (13, 14) to missile side and other end has command launch unit (CLU) side connector with round connector (15).

The missile side micro-D connector (13) is a male micro-D sub connector. The launch side micro-D connector (14) is a female micro-D sub connector. Both the missile side micro-D connector (13) and the launch tube side micro-D connector (14) connect the launcher to on-board computer (OBC).

The on-board computer (OBC) provides the electrical power, ethernet, communication, firing pulse, video analogue data to missile from the launcher and vice versa.

The lever (16) having hinge (18) is a structural component. Figure 7 shows the perspective view of the lever assembly. The launch tube side micro-D connector (14) along with flex PCB (12) is assembled to the lever (16) with mounting screws (23). Spring loaded plungers (22) are mounted on both sides of lever (16) for locking. The lever (16) has mounting holes (8) for mounting hinge pins (24) as shown in figure 7 and figure 8. A bottom tip (17) of the lever (16) slides over the ramp portion (19) during missile movement. It intends to rotate the lever (16) and locks at elevated position. The ramp portion (19) is mounted on on-board computer (OBC) front circular disc (21) for lifting the lever during missile (7) movement as shown in figure 6.

Further, as shown in figure 9, the lock spring (25) and a lock plunger (22) are mounted on the lever (16). Initially, the plunger (22) is in pressed condition inside the lever surface and the plunger (22) contacts with inner surface of the umbilical connector (UC) insert (3) of the launch tube (2) before launching of the missile (7). Once the missile (7) starts moving, the bottom tip (17) of lever (16) slides on ramp portion (19) and it intends to rotate the lever (16) and the plunger top surface slides on inner surface of UC insert (3). After approximately 35-degree rotation of lever, the plunger (22) enters in oblong hole passage (6) due to spring force thereby arresting the movement of the lever (16).

The launch tube side connector (15) is a female round connector. The female round connector (15) mates with command launch unit (CLU) side male round connector (not shown).

The stopper (20) being a small structural component is mounted on the missile (7) as shown in figure 6. The stopper (20) is used for restricting the rotation of lever (16) during initial 5mm travel of missile.

The integration of umbilical connector (1) of the present invention is given below:
i. Load the missile (7) in launch tube (2).
ii. Connect the launch tube side micro-D connector (14) with the missile side micro-D connector (13) by inserting lever assembly on launch tube (2) by pressing spring loaded plungers (22).
iii. Align the hinge pin mounting hole (8) of lever (16) and hole passage (5) on UC insert (3) on launch tube (2) by moving the missile (7) slightly using missile stopper screw provided at backside of launch tube (2).
iv. Assemble the hinge pins (24).
v. Assemble the round connector (15) on umbilical housing (11) using connector lock nut.
vi. Mount the umbilical connector housing (11) on launch tube (2) by using screws.
vii. Connect the command launch unit (CLU) to launch tube side round connector (15).

Figure 3 shows the structure of umbilical connector (1) before launch of the missile (7), wherein the missile side micro-D connector (13) and the launch tube side micro-D connector (14) are connected or attached with the launch tube (2). The one end of the lever (16) is attached with the launch tube side micro-D connector (14).

Figure 4 shows the cross-sectional view of umbilical connector (1) after launch of the missile when the missile travels around 5mm distance from the initial position. At this time, the missile side micro-D connector (13) and the launch tube side micro-D connector (14) are disengaged or separated from the stopper (20). The tip (17) of the lever (16) contacts the ramp portion (19) of the UC bracket.

Figure 5 shows the cross-sectional view of the umbilical connector (1) after complete launch of the missile. After launching of the missile, the missile side micro-D connector (13) and the launch tube side micro-D connector (14) are completely disengaged from the launch tube (2). The first pair of connectors (13, 14) are moved upward and locked by spring loaded plungers (22) wherein the spring-loaded plungers (22) are mounted on lever (16) to arrest the lever position when missile launch.

Thus, the above-mentioned description can be summarized as, a release mechanism of an umbilical connector (1) for Anti-tank Guided Missile (ATGM), said mechanism comprises:
- two pairs of connectors connected through flex printed circuit board (PCB) (12), wherein a first pair of connectors comprises a missile side micro-D connector (13) and a launch tube side micro-D connector (14) placed in between a missile (7) and a launch tube (2), and a second pair of connectors comprises a launch tube side round connector (15) and a command launch unit side connector placed in between the launch tube (2) and a command launch unit (CLU);
- a lever (16) having a tip potion (17);
- a ramp portion (19) mounted on an on-board computer (OBC) front circular disc (21) for lifting the lever (16) during movement of the missile (7);
- a stopper (20) mounted on missile (7) for restricting the rotation of the lever (16) during initial travel of missile (7); and
- spring loaded plungers (22) mounted on both sides of the lever (16) for locking;
wherein after launching, when the missile (7) travels approximately 5mm distance from initial position, the missile side micro-D connector (13) and the launch tube side micro-D connector (14) are disengaged from the stopper (20) and the tip portion (17) of the lever (16) contacts the ramp portion (19) of umbilical connector bracket; and
when the missile side micro-D connector (13) and the launch tube side micro-D connector (14) are completely disengaged from the launch tube (2), the first pair of connectors (13, 14) are moved upward and locked by the spring-loaded plungers (22) and the missile (7) ejects from the launch tube (2).

In another aspect of the present invention, the present invention provides the steps of releasing novel umbilical connector (1) after the launching the missile (7). The release mechanism of an umbilical connector (1) works in following steps as given below:
(a) After ignition of launch motor, missile starts sliding on launch tube.
(b) When the missile starts sliding and travels approximately 5 mm distance from the initial stage, the missile side micro-D connector (13) and the launch tube side micro-D connector (14) are disconnected or disengaged.
(c) After 5 mm distance movement of missile (7), the lever bottom tip (17) contacts with ramp portion (19) of UC bracket, so lever (16) with launch tube side micro-D connector (14) rotate upwards about the UC hinge (18).
(d) After then approximately 35° rotation of lever (16), the lever (16) is locked by spring loaded plungers (22) and
(e) At this time, the missile (7) ejects from launch tube (2).

Thus, the above-mentioned description can be summarized as, a method for working of a release mechanism of an umbilical connector (1) for Anti-tank Guided Missile (ATGM), said method comprises the steps of:
1) after ignition of a launch motor, a missile (7) starts sliding on a launch tube (2);
2) a missile side micro-D connector (13) and a launch tube side micro-D connector (14) are disconnected during initial movement of the missile (7);
3) after approximately 5mm distance movement, a tip portion (17) of a lever (16) contacts with a ramp portion (19) of umbilical connector bracket and the lever (16) with the launch tube side micro-D connector (14) rotate upwards about an umbilical connector hinge (18);
4) after approximately 35-degree rotation of lever (16), the lever (16) is locked by spring-loaded plungers (22); and
5) the missile (7) ejects from the launch tube (2).

Thus, the present invention designs a release mechanism of umbilical connector for Anti-Tank Guided Missile (ATGM) which minimizes the transfer of unavoidable forces from missile to launcher through the mechanism and also disconnects an umbilical connector from the missile and moves the connector to an isolated position as the missile is launched.

ADVANTAGES OF THE INVENTION:

The novel release mechanism for umbilical connector of the invention have following advantageous features over the currently known release mechanism:
- The novel mechanism of umbilical connector helps to eject the missile from ground support smoothly.
- It minimizes missile ejection force.
- Induce positive electrical connection therefore it avoids the signal losses.
- The construction of umbilical connector is simple and can be reusable.
- It reduces the intermediate electrical joints and therefore, losses and delay in signal are minimized.
- It is also economically feasible solution.
,CLAIMS:

1. A release mechanism of an umbilical connector (1) for Anti-tank Guided Missile (ATGM), said mechanism comprises:
- two pairs of connectors connected through flex printed circuit board (PCB) (12), wherein a first pair of connectors comprises a missile side micro-D connector (13) and a launch tube side micro-D connector (14) placed in between a missile (7) and a launch tube (2), and a second pair of connectors comprises a launch tube side round connector (15) and a command launch unit side connector placed in between the launch tube (2) and a command launch unit (CLU);
- a lever (16) having a tip potion (17);
- a ramp portion (19) mounted on an on-board computer (OBC) front circular disc (21) for lifting the lever (16) during movement of the missile (7);
- a stopper (20) mounted on the missile (7) for restricting the rotation of the lever (16) during initial travel of missile (7); and
- spring loaded plungers (22) mounted on both sides of the lever (16) for locking;
wherein after launching, when the missile (7) travels approximately 5mm distance from initial position, the missile side micro-D connector (13) and the launch tube side micro-D connector (14) are disengaged from the stopper (20) and the tip portion (17) of the lever (16) contacts the ramp portion (19) of umbilical connector bracket; and
when the missile side micro-D connector (13) and the launch tube side micro-D connector (14) are completely disengaged from the launch tube (2), the first pair of connectors are moved upward and locked by the spring loaded plungers (22) and the missile (7) ejects from the launch tube (2).

2. The mechanism as claimed in claim 1, wherein the two pairs of connectors connect the missile (7), the launch tube (2) and the command launch unit (CLU).

3. The mechanism as claimed in claim 1, wherein the launch tube (2) comprises a metal umbilical connector (UC) insert (3) to mount the umbilical connector (1) on it; and
wherein the umbilical connector (UC) insert (3) comprises hole passages (5) for locating hinge pins (24) and oblong holes passages (6) for locking the lever (16).

4. The mechanism as claimed in claim 1, wherein the launch tube (2) comprises taping holes (4) for mounting a housing (11) of the umbilical connector (1); and
wherein the housing (11) houses all the components of the umbilical connector (1).

5. The mechanism as claimed in claim 1, wherein the flex printed circuit board (PCB) (12) having two ends, one end has micro-D connectors (13, 14) to missile side and other end is for the command launch unit (CLU) with the launch tube side round connector (15).

6. The mechanism as claimed in claim 1, wherein the missile side micro-D connector (13) being a male micro-D sub connector mounted on the on-board computer (OBC) front disc (21) connects the launcher to the on-board computer (OBC).

7. The mechanism as claimed in claim 1, wherein the launch tube side micro-D connector (14) being a female micro-D sub connector connects the launcher to the on-board computer (OBC).

8. The mechanism as claimed in claim 5, wherein the micro-D connectors (13, 14) are selected from screw fitted connectors or snap fitted connectors.

9. The mechanism as claimed in claim 1, wherein the launch tube side round connector (15) being a female round connector mates with the command launch unit (CLU) side male round connector.

10. The mechanism as claimed in claim 9, wherein the launch tube side round connector (15) is clamped with the launch tube (2) and the command launch unit (CLU).

11. The mechanism as claimed in claim 1, wherein the on-board computer (OBC) provides the electrical power, ethernet, communication, firing pulse, video analogue data to missile from the launcher and vice versa.

12. The mechanism as claimed in claim 1, wherein the launch tube side micro-D connector (14) along with flex printed circuit board (PCB) (12) is assembled to the lever (16) with mounting screws (23); and
wherein the lever (16) has mounting holes (8) for mounting hinge pins (24).

13. The mechanism as claimed in claim 1, wherein the plunger (22) having a spring (25) is mounted on the lever (16),
wherein initially in pressed condition inside the lever (16) surface, the plunger (22) contacts with inner surface of the umbilical connector (UC) insert (3) of the launch tube (2) before launching of the missile (7),
once the missile (7) starts moving, the bottom tip (17) of the lever (16) slides on the ramp portion (19) intending to rotate the lever (16) and the top surface of plunger (22) slides on inner surface of the umbilical connector (UC) insert (3), and
after approximately 35-degree rotation of the lever (16), the plunger (22) enters in the oblong hole passage (6) due to the spring force thereby arresting the movement of the lever (16).

14. A method for working of a release mechanism of an umbilical connector (1) for Anti-tank Guided Missile (ATGM), said method comprises the steps of:
1) after ignition of a launch motor, a missile (7) starts sliding on a launch tube (2);
2) a missile side micro-D connector (13) and a launch tube side micro-D connector (14) are disconnected during initial movement of the missile (7);
3) after approximately 5mm distance movement, a tip portion (17) of a lever (16) contacts with a ramp portion (19) of umbilical connector bracket and the lever (16) with the launch tube side micro-D connector (14) rotate upwards about an umbilical connector hinge (18);
4) after approximately 35-degree rotation of lever (16), the lever (16) is locked by spring loaded plungers (22); and
5) the missile (7) ejects from the launch tube (2).