Description:1 Title of the Invention
Device for pilot helmet harness connection and its locking and disengagement deployment system for aircraft.

2 Field of the Invention
The present invention relates to development of a device for connecting pilot helmet mounted systems and its mechanisms to the aircraft. More particularly, the present invention relates to such device that enables quick secure locking and quick unlocking of pilot helmet harness at the aircraft end.

3 Background of the Invention
Presently aircraft pilots wear headset for inter-communication, communication with Air Traffic Controller (ATC), ground stations and other aircrafts. The aircraft have dedicated helmets which typically have inbuilt microphone and headset and are interfaced with radio set for the communication.
The aircraft also have helmet mounted systems incorporated in their pilot helmets or have detachable systems not limited to display and targeting systems, night vision systems, situational awareness system and distributed aperture systems which augment the pilot vision. These systems have power supply and electrical signals wired to the aircraft through the same harness.
The typical pilot helmet has built-in helmet mechanisms, like automatic deployment of visor or face shield or quick release of night vision goggle arrangement etc. The actuation of these mechanism require electrical signal in case of ejection from cockpit in an aircraft. These actuation signals are also connected to the aircraft through harness. These electrical signals are connected to the aircraft radio set and other aircraft systems through a flexible light weight aerospace grade cable or harness. The cable or harness is attached to the aircraft and locked in position to ensure that the harness does not accidently get dislodged due to shock and vibrations. The ease of connection for locking, unlocking and disconnection of the harness to the aircraft is imperative. The contemporary harness do not have quick secure locking and unlocking at the aircraft end.
The contemporary harnesses are relatively thick, heavy and rigid in nature due to thick rubber type molded sheathing. The flexibility of cable is compromised in order to provide resistance to abrasion, fluids and mechanical damage. This lack of flexibility is impediment in easy connection and easy release.
The contemporary harnesses are made of less reliable wires in order to reduce weight or due to weight constraint, and have thick and heavy molded rubber sheathing or jacket for chemical and mechanical abrasion resistance. The contemporary harnesses are thus also prone to failure due to strain at the helmet connection soldering joint. Repair to the harness cannot be carried out due to thick molded rubber sheathing. Thus a failure requires complete rejection of the harness.

3.1 Prior Art
The Patent No. US11394156B2 wherein a harness is disclosed and describes its application for connecting two components one of which may be a helmet and other component may be a control box attached to the vehicle. The patent discloses the cable attaching a first component and a second component using a quick disconnect connector pair. The disclosure is about EMI shielding for cable and its constructional features having quick disconnect connector and disconnecting element however, this patent does not describe the details of its constructional features, mechanism and method for connecting and disconnecting between seat and harness.
The Patent No. US11655041B2 discloses electronic release system for an aircraft ejection seat and does not disclose details about pilot helmet harness and its connection mechanism procedure.
The Pilot Helmet (or only Helmet as termed herein) is a prior art as typically described in Patent No. EP1580587B1. The Helmet may additionally comprise of one or more universal connector(s) mounted on the helmet, connected to cabling, connected to one or more helmet release connector(s) (HRC) also termed herein as Helmet Connector. It does not disclose details about connection mechanism architecture and procedure.
The Patent No. US11394156B2 also relates to the quick disconnect harness system (QDHS) described in P. T. Bapu, M. J. Aulds, Steven P. Fuchs, David M. McCormick, "Quick-disconnect harness system for helmet-mounted displays," Proc. SPIE 1695, Helmet-Mounted Displays III, (30 October 1992), DOI: 10.1117/12.131964. The QDHS is also known as helmet vehicle interface (HVI) consists of universal connector mounted on the helmet, cabling, helmet release connector (HRC) (or helmet connectors or harness connectors on helmet side), quick disconnect connector (QDC) (or hip quick disconnect or harness connectors on ejection seat side) and an in-line release connector (IRC) or panel mounted connector (PMC) corresponding to different architectures.
The quick-release connector assembly disclosed in Expired Patent No. GB2315613A for quick release connector for the electrical interconnection between a pilot's helmet and aircraft cockpit for separation of the connector during ejection of the pilot from the aircraft. The manual connection, locking and disengagement operation of the mechanism described therein requires complicated operation by pilot in multiple steps.
The present disclosure address the limitations described in the above patents. It also proposes a device with complete disclosure of its construction feature and evolves a push and lock mechanism for providing swift, reliable, economic and environmental friendly solution.

4 Brief Summary of the Invention
The present invention relates to evolving a device and a method of its connection, locking and disengagement deployment system of pilot helmet harness to the aircraft.
The pilot helmet harness device comprises of an aerospace grade plug(s) (prior art) which is/are housed in a backshell fabricated out of aerospace grade lightweight material. The backshell has a push and lock mechanism which ensures the locking of the harness with the aircraft structure. This method ensures quick yet secure locking and quick unlocking/ disengagement/ deployment of harness at the aircraft end. The locking ensures proper connection during entire flight even in case of shock and vibrations.
In the present invention, the device is evolved by using thin walled flexible elastomeric chemical and mechanical abrasion resistant lightweight heat shrink tubing or tape jacket. The flexible elastomeric heat shrink tubing or tape is light weight, resistant to abrasion, fluids, mechanical damage and strain and easy to replace for repair in case of damage. The thin walled jacket improves the flexibility of the harness, improves its reliability and maintainability.
The reliable aerospace grade wires are used in the evolved device. The lightweight and flexible sheathing also enables the harness to have more wires and cables while also being easier to connect, release and easier to maintain and repair.
In the present invention, the failure prone wire joints (due to strain on cables near joints of connector backshell) are reinforced with additional layers of heat shrink tubing or tape under the jacket and backshell to reduce strain on underlying wires and cables.

5 Brief Description of the Drawings
An embodiment of this invention and method of its operation is described, by an example and referring the following drawings, particularly the manner in which it is assembled, utilised and performed.
Figure 1- Illustration of harness connecting the pilot helmet to the aircraft through the ejection seat
Figure 2- Illustration of structure of harness
Figure 3- Illustration of assembled structure of the one or more harness connectors in a single backshell
Figure 4- Illustration of the assembly of one or more harness connectors in a single backshell
Figure 5- Illustration of method of operation of push and lock mechanism of the harness
Figure 6- Illustration of flow diagram describing method of its operation
Figure 7- Illustration of assembled structure of the one or more cable(s) of the harness

6 Detail Description of the Invention
The following specification particularly describes an embodiment of the invention and the manner in which it is assembled, utilised and performed:

Figure 1 illustrates the typical Harness (100) connecting the Pilot Helmet (200) to the Aircraft (300) through the Ejection Seat (400). The connection and locking of pilot helmet harness apparatus to the aircraft is marked in the figure and the right side panels showing its enlarged view and its states of operation for quick locking, namely Align (A), Push (B) and Lock (C). The features of the Harness (100) for the connection are: one or more Harness Connectors (110) on helmet side, one or more Harness Connectors in a single Backshell (120) on ejection seat side and its Push and Lock Mechanism (130). The Pilot Helmet (200) has corresponding mating Helmet Connector(s) (210). The Ejection Seat (400) has a corresponding mating Service Connector (410).

In Figure 1, one or more quick automatic release or simple pull release type Harness Connector(s) (110) of helmet side of the Harness (100) is connected to the corresponding mating Helmet Connector(s) (210) of the Pilot Helmet (200). The other end of the Harness (100) is having one or more Harness Connectors of ejection seat side in a single Backshell (120) which is connected and locked in position to the Service Connector (410) of the Ejection Seat (400) through the Push and Lock Mechanism (130) of the Backshell (120) of the Harness (100). The electrical connections of the Pilot Helmet (200) go through one end of the Harness (100) to the other end of the Harness (100) to corresponding mating Service Connector (410) of the Ejection Seat (400) to the Aircraft (300). The Harness Connector(s) (110) of helmet side and the Harness Connector(s) of ejection seat side in a single Backshell (120) Harness Connectors of ejection seat side in a single Backshell (120) may be reinforced with one or more additional layers of heat shrink tubing or tape under the jacket and backshell.

Figure 2 illustrates the structure of Harness (100). The features of the Harness (100) are: one or more Harness Connectors (110) of helmet side, one or more Harness Connectors (150) in a single Backshell (120) of Ejection Seat side, one or more Cable(s) (140) of the Harness (100), and in case of plurality of cables one or more Binding(s) (160) of metallic or fiber material.

In Figure 2, the Harness (100) on one end has one or more quick automatic release or simple pull release type Harness Connectors (110) of helmet side which connect to the Pilot Helmet (200). The Harness (100) on the other end has one or more Harness Connectors (150) of the ejection seat side in a single Backshell (120) which connect to the Service Connector (410) of the Ejection Seat (400) and lock to it through the Push and Lock Mechanism (130) of the Backshell (120). The connection between the two end connector(s) of the Harness (100) is made up of one or more Cable(s) (140). In case of plurality of Cables (140) in the Harness (100) the Cables are bound together by one or more Binding(s) (160) of metallic or fibre material.

Figure 3 illustrates the assembled structure of the one or more Harness Connectors (150) (Refer Figure 2) in a single Backshell (120) (Refer Figure 2) of Ejection Seat side with its Push and Lock Mechanism (130). The feature of Backshell (120) shown here is Body (121) of Backshell. The features of Push and Lock Mechanism (130) shown here are: Locking Pin (131), Dowel Pin (132), Ball-End Headless Screw (133) and Shaft Pin (136). The feature of one or more Harness Connectors (150) of Ejection Seat side shown here is two Rectangular Plugs (151).

In Figure 3, the Body (121) of Backshell (120) houses one or more Harness Connectors (150) assembled from Rectangular Plug(s) (151). The Rectangular Plug(s) (151) is a push to insert and pull to remove type connector which connects to the mating Rectangular Sockets(s) of Service Connector (410) (Refer Figure 1) of the Ejection Seat (400) (Refer Figure 1). The Push and Lock Mechanism (130) of the Backshell (120) comprises of the Locking Pin (131) connected to the Shaft Pin (136) using a Dowel Pin (132) and a Ball-End Headless Screw (133) installed on the shorter end of the Locking Pin (131). The longer end of the Locking Pin (131) acts as a lever for locking and unlocking. The Locking Pin (131) is rotated about the spring loaded Shaft Pin (136) for locking in a manner such that the ball-end of Ball-End Headless Screw (133) under force from spring sits in a Circular Notch (412) of the Service Connector (410) of the Ejection Seat (400) and prohibits motion of the Backshell (120) and thus the Harness Connector(s) (150) in the plane of rotation. Rotating the Locking Pin (131) further takes little additional force opposing the spring action about axis of rotation and dislodges the ball-end of Ball-End Headless Screw (133) from the Circular Notch (412) of the Service Connector (410) thus unlocking and permitting motion of the Backshell (120) and thus the Harness Connector(s) (150).

Figure 4 illustrates the assembly of one or more Harness Connectors (150) (Refer Figure 2) in a single Backshell (120) (Refer Figure 2) of Ejection Seat side with its Push and Lock Mechanism (130) of the Harness (100). The features of Backshell (120) shown here are: Body (121), Casing (122) and Rubber Packing(s) (123) of Backshell. The features of Push and Lock Mechanism (130) shown here are: Locking Pin (131), Dowel Pin (132), Ball-End Headless Screw (133), Insulator Tube (134), Spring (135) and Shaft Pin (136). The features of one or more Harness Connectors (150) (Refer Figure 2) of Ejection Seat side shown here are: two Rectangular Plugs (151) and its Connector Screw and Nut pairs (152).

In Figure 4, the assembly starts from installation of Casing (122) into the Body (121) and then installing the Rubber Packing(s) (123) completing the Backshell sub-assembly. The Shaft Pin (136) is installed in the Backshell (120) with Spring (135) and Insulator Tube (134). One end of the Shaft Pin (136) is inserted in the Locking Pin (131) and fixed with Dowel Pin (132). The Ball-End Headless Screw (133) is installed on the Locking Pin (131). The Inner core layer (141) (Refer Figure 3) wires and the Outer core layer (141) (Refer Figure 3) wires of the Cable(s) (Refer Figure 2) of the Harness (100) (Refer Figure 2) are connected to the Rectangular Plug(s) (151) of one or more Harness Connectors (150) (Refer Figure 2). The Rectangular Plug(s) (151) are affixed to the Backshell (120) structure by its Connector Screw and Nut pairs (152).

Figure 5 illustrates the method of operation (500) of Push and Lock Mechanism (130) of the Harness (100). The six steps of the method of operation (500) viz. Align (A) (521), Push (B) (522), Lock (C) (523), Unlock (D) (524), Pull (E) (525) and Remove (F) (526) are illustrated here. The features of Push and Lock Mechanism (130) shown here are: Locking Pin (131), Ball-End Headless Screw (133) and Shaft Pin (136). The features of Service Connector (410) of Ejection Seat (400) (refer Figure 1) shown here are: Vertical Slot (411) and Circular Notch (412) in the body of Service Connector (410). The other features shown here are: Body (121) of the Backshell (120) and Rectangular Plug(s) (151) of one or more Harness Connectors (150).

In Figure 5, for the illustration of Push and Lock Mechanism (130) functionality and operation of locking the Harness. The Harness Connectors of ejection seat side in a single Backshell (120) is connected and locked in position to the Service Connector (410) of the Ejection Seat (400) (refer Figure 1) through the Push and Lock Mechanism (130) of the Backshell (120) (refer Figure 1 and Figure 2) of the Harness (100) (refer Figure 1 and Figure 2). The Harness (100) is connected to the Aircraft (300) prior to the functional requirement of communication system or other helmet mounted systems as shown in 1st to 3rd steps as described in aforementioned. The Harness (100) is removed afterwards from the Aircraft (300) as shown in 4th to 6th steps.

As indicated in the Figure 6 the 1st step of method of operation (500) i.e., Align (A) (521), the Backshell (120) is held by its Body (121) by the pilot with Rectangular Plug(s) (151) facing downwards i.e., towards the mating Service Connector (410) of the Ejection Seat (400) (refer Figure 1). The Locking Pin (131) of the Backshell (120) is rotated in a manner that Ball-End Headless Screw (133) is downwards i.e., in the direction of Rectangular Plug(s) (151). The Locking Pin (131) of the Backshell (120) is vertical and aligned with the Vertical Slot (411) in the Service Connector (410) and inserted with light hand. The Ball-End Headless Screw (133) hits the end of the Vertical Slot (411) in the Service Connector (410) in this step.

As indicated in the Figure 6 the 2nd step of method of operation (500) i.e., Push (B) (522), slight pushing force is applied by the pilot holding the Backshell (120) such that the Ball-End Headless Screw (133) slips over the end of the Vertical Slot (411) in the Service Connector (410). The push results in force going through Ball-End Headless Screw (133) to the Locking Pin (131) to the Dowel Pin (132) to the Shaft Pin (136) which is Spring (135) loaded (refer Figure 4). The Spring (135) gets compressed and Shaft Pin (136) moves outward i.e., towards Locking Pin (131). As a result, the Ball-End Headless Screw (133) further slips over the end of the Vertical Slot (411) in the Service Connector (410) till it is fully over the body of Service Connector (410) and the Backshell (120) is pushed into the slot with Rectangular Plug(s) (151) of the Harness (100) mating with the Service Connector (410) of the Ejection Seat (400).

As indicated in the Figure 6 the 3rd step of method of operation (500) i.e., Lock (C) (523), the Locking Pin (131) of the Backshell (120) is rotated (clockwise rotation shown in the figure) in a manner that Ball-End Headless Screw (133) slips into the Circular Notch (412) of the Service Connector (410). This Circular Notch (412) allows Ball-End Headless Screw (133) to slip inward due to the Spring (135) loaded Shaft Pin (136) to move inward under force of uncompressing Spring (135). This locks the Backshell (120) in place and ensuring proper connection during entire flight, even in case of shock and vibrations, with the Service Connector (410).

As indicated in the Figure 6 the 4th step of method of operation (500) i.e., Unlock (D) (524), the Locking Pin (131) of the Backshell (120) is pushed and rotated (anti-clockwise rotation shown in the figure) in a manner that Ball-End Headless Screw (133) slips out of the Circular Notch (412) of the Service Connector (410). This step is similar to the 2nd step and reverse of the 3rd step. The circular push results in force going through Ball-End Headless Screw (133) to the Locking Pin (131) to the Dowel Pin (132) to the Shaft Pin (136) which is Spring (135) loaded (refer Figure 4). The Spring (135) gets compressed and Shaft Pin (136) moves outward i.e., towards Locking Pin (131). As a result, the Ball-End Headless Screw (133) further slips over the edge of the Circular Notch (412) of the Service Connector (410) till it is fully over the body of Service Connector (410). This unlocks the Backshell (120) from the Service Connector (410) and typically the Locking Pin (131) of the Backshell (120) is vertical and aligned with the Vertical Slot (411) in the Service Connector (410).

As indicated in the Figure 6 the 5th step of method of operation (500) i.e., Pull (E) (525), slight pulling force is applied by the pilot holding the Backshell (120) such that the Ball-End Headless Screw (133) slides over the body of the Service Connector (410) into the Vertical Slot (411). The Rectangular Plug(s) (151) of the Harness (100) are de-mated / disconnected from the Service Connector (410) of the Ejection Seat (400).

As indicated in the Figure 6 the 6th step of method of operation (500) i.e., Remove (F) (526), the Harness (100) is removed with light hand such that the Rectangular Plug(s) (151) are fully out of the Service Connector (410) of the Ejection Seat (400).
Figure 6 illustrates flow diagram describing method of operation (500) of using a pilot helmet Harness (100) connection, locking and disengagement/ deployment system in accordance with an aspect of the disclosure.

In Figure 6, for the illustrated flow diagram describing method of operation (500) of using a pilot helmet Harness (100) connection, locking and disengagement/ deployment system i.e. Push and Lock Mechanism (130) functionality and operation (refer Figure 5) in accordance with an aspect of the disclosure.

In block 501, the state is set as the Harness (100) is not connected to Service Connector (410) of Ejection Seat (400). In this state all the electrical / avionics functions of pilot Helmet (200) like headset and helmet mounted system functions are prohibited.

In block 503, the 1st step of method of operation Align (521) is started, viz. the Backshell (120) is aligned with Service Connector (410) of the Ejection Seat (400).

In block 505, the 1st step of method of operation Align (521) is completed, viz. the Locking Pin (131) is rotated to vertical and aligned with the Vertical Slot (411) in the Service Connector (410) and inserted with light hand till Ball-End Headless Screw (133) hits Vertical Slot (411).

In block 507, 2nd step of method of operation Push (522) is carried out. With slight pushing force the Ball-End Headless Screw (133) slips over the end of the Vertical Slot (411) till it is fully over the body of Service Connector (410). In this step the Rectangular Plug(s) (151) of the Harness (100) are electrically mated with the Service Connector (410) of the Ejection Seat (400).

In block 509, 3rd step of method of operation Lock (523) is carried out. The Locking Pin (131) is rotated to lock the Backshell (120) in place with the Service Connector (410).

In block 511, the state is set as the Harness (100) is electrically connected with Service Connector (410) of Ejection Seat (400) and mechanically locked through its Backshell (120). In this state all the electrical / avionics functions of pilot Helmet (200) like headset and helmet mounted systems functions for ground checks and flight operation are permitted.

In block 513, 4th step of method of operation Unlock (524) is carried out. The Locking Pin (131) is rotated in the opposite direction as given in block 509 to unlock the Backshell (120) from the Service Connector (410).

In block 515, 5th step of method of operation Pull (525) is carried out. With slight pulling force the Ball-End Headless Screw (133) slips over the body of Service Connector (410) to the Vertical Slot (411). In this step the Rectangular Plug(s) (151) of the Harness (100) are electrically de-mated from the Service Connector (410) of the Ejection Seat (400).

In block 517, 6th step of method of operation Remove (526) is carried out. The Harness (100) is removed with light hand out of the Service Connector (410) of the Ejection Seat (400).

Figure 7 illustrates the assembled structure of the one or more Cable(s) (140) of the Harness (100). The cable is divided into five or more layers: Inner core layer (141), Inner insulator layer (142), Outer core layer (143), Outer insulator layer (144) and Jacket (145).

In Figure 7, the Inner Core Layer (141) is made of two or more aerospace grade wires of shielded or un-shielded type twisted or wound clockwise or counter-clockwise. The Inner Insulator Layer (142) is made of thin film of aerospace grade insulator material wound over Inner core layer (141) and in the same direction and providing full coverage with sufficient overlap. The Outer Core Layer (143) is made of two or more aerospace grade wires of shielded or un-shielded type (typically shielded type only) twisted or wound over Inner Insulator Layer (142) counter-clockwise or clockwise in a direction opposite to Inner core layer (141). The Outer Insulator Layer (144) is made of thin film of aerospace grade insulator material wound over Outer core layer (143) and in the same direction and providing full coverage with sufficient overlap. The Jacket (145) is made of aerospace grade thin walled flexible elastomeric heat shrink tubing which is fitted over the Outer Insulator Layer (144) or heat shrink tape wound over it. Near the connector joints of Harness Connector(s) (110) of helmet side and the Harness Connector(s) of ejection seat side in a single Backshell (120) and under the Backshell (120) there may be one or more additional layers of aerospace grade thin walled flexible elastomeric heat shrink tubing or tape under the top layer of Jacket (145) and over the Outer Insulator Layer (144).

All references, including publications, patent applications, and patents, cited herein are hereby incorporated by reference to the same extent as if each reference were individually and specifically indicated to be incorporated by reference and were set forth in its entirety herein.

The use of the term “wire” and similar referents in the context of describing the invention (especially in the context of the following claims) is to be construed to cover both single-strand and multi-strand conductors encased in one or more insulating layer with optional one or more shield jacket over each layer. The term is also construed to cover twisted pair (or twisted polyad cable), twisted shielded pair (or twisted shielded polyad cable), coaxial cable and multi-axial cables each encased in one or more insulating layer with optional one or more shield jacket over each layer. The term is also construed to cover optical fibre media.

The use of the term “harness” in the context of describing the invention is construed to cover the device for pilot helmet harness connection and its locking and disengagement deployment system for aircraft as well as plurality of cables unless otherwise specified herein or otherwise unambiguously contradicted by context. ,
Claims:We Claim,

1. A device (100) for a pilot helmet (200) harness connection and its locking and disengagement deployment system (130) for an aircraft (300) comprising:
a harness connector (150) of ejection seat side in a backshell (120) with a push and lock mechanism (130), said push and lock mechanism (130) characterized in that it comprises:
a lever (131) operating said push and lock mechanism (130);
a fastener (132) affixing said lever (131) to a shaft (136);
a locking appendage (133) connected to said lever (131);
an optional insulator tube (134) covering and physically isolating a spring mechanism (135) and said shaft (136) torso inside said backshell (120);
said spring mechanism (135) providing spring loading to said shaft (136) against a body (121) of said backshell (120); and
said shaft (136) forming axis of operation of said lever (131);
said harness connector (150) of ejection seat side in said backshell (120), said backshell (120) characterized in that it comprises:
said body (121);
an optional casing (122) holding said harness connector (150);
an optional fastener attaching said optional casing (122) to said body (121);
an optional packing (123) cushioning a plug or socket (151); and
an optional filling with aerospace adhesive in said backshell (120) of said harness connector (150) of ejection seat side;
said harness connector (150) of ejection seat side, wherein said harness connector (150) is connected to an electrical cable (140) on one end, said harness connector (150) characterized in that it comprises:
said plug or socket (151) connected to said cable (140); and
a fastener (152) affixing said plug or socket (151) to said backshell (120);
a harness connector (110) of helmet side connected to an inner core layer (141) wire and an outer core layer (143) wire of said cable (140), said harness connector (110) characterized in that it comprises of an optional filling with aerospace adhesive in backshell of said harness connector (110); and
said electrical cable (140) connected to said harness connector (110) of helmet side on one end and said harness connector (150) of ejection seat side in said backshell (120) on the other end, said cable (140) characterized in that it comprises:
said inner core layer (141) made of one or more aerospace grade wire, in case of plurality twisted or wound clockwise or counter-clockwise;
an optional inner insulator layer (142) made of aerospace grade insulator material wound over said inner core layer (141);
said outer core layer (143) made of one or more aerospace grade wire twisted or wound over said inner insulator layer (142) or said inner core layer (141) clockwise or counter-clockwise;
an optional outer insulator layer (144) made of aerospace grade insulator material wound over said outer core layer (143);
a jacket (145) made of aerospace grade flexible material which is fitted over said outer insulator layer (144) or said outer core layer (143), wherein an optional short additional layer of aerospace grade thin flexible material is placed under top layer of said jacket (145) under said backshell (120) of said harness connector (150) of ejection seat side and an optional short additional layer (145) of aerospace grade thin flexible material is placed under top layer of said jacket (145) under the backshell of said harness connector (110) of helmet side; and
an optional binding (160) made metallic or fibre material, binding the said cable (140) in case of plurality of cables.

2. The device (100) as claimed in Claim 1, wherein:
said body (121) and said casing (122) with its fastener are characterised by light weight aerospace grade material like aluminium alloy;
said insulator tube (134) is characterised by aerospace grade rigid insulating material like thermosetting plastic;
said lever (131), said fastener (132), said locking appendage (133), said shaft (136), said spring mechanism (135) and said fastener (152) is characterised by high tensile strength aerospace grade material like steel alloy;
said packing (123) is characterised by aerospace grade elastic material like synthetic rubber;
said filling with aerospace adhesive is characterised by insulating, heat resistant and vibration resistant bonding material like low molecular silicon rubber;
said jacket (145) is characterised by aerospace grade flexible, thermal resistant, abrasion resistant and chemical resistant material like cross-linked elastomers; and
said inner insulator layer (142) and said outer insulator layer (144) are characterised by thin aerospace grade insulator material with superior dielectric, chemical and thermal properties like polytetrafluoroethylene.

3. A method of operation (500) of said device (100) claimed in Claim 1, said method of operation (500) comprising:
a not-connected state (501) where said device (100) is not connected to said service connector (410) of said ejection seat (400) of said aircraft (300);
an align (521) operation, comprising:
aligning (503) said backshell (120) of said harness connector (150) of ejection seat side with said service connector (410); and
aligning (505) said lever (131) of said push and lock mechanism (130) with a slot (411) of said service connector (410);
a push (522) operation, comprising pushing (507) said backshell (120) into said service connector (410);
a lock (523) operation, comprising operating (509) said lever (131) to lock said locking appendage (133) into a notch (412) of said service connector (410);
a connected-locked state (511) where said device (100) is connected to said service connector (410) of said ejection seat (400) of said aircraft (300);
an unlock (524) operation, comprising operating (513) said lever (131) to unlock said locking appendage (133) from said notch (412) of said service connector (410);
a pull (525) operation, comprising pulling out (515) said backshell (120) from said service connector (410); and
a remove (526) operation, comprising removing (517) said backshell (120) from said service connector (410).

4. The device (100) claimed in Claim 1 by means of method (500) claimed in claim 4, said not-connected state (501) is changed to said connected-locked state (511) by said align (521) operation, said push (522) operation and said lock (523) operation swiftly and said device (100) reverts to said initial not-connected state (501) by said unlock (524) operation, said pull (525) operation and said remove (526) operation swiftly;
wherein said short additional layer (145) under said backshell (120) of said harness connector (150) of ejection seat side and under the backshell of said harness connector (110) of helmet side reducing strain on wire joints of said cable (140) to said connectors and improving reliability of said device (100); and
wherein said device (100) is repairable resulting in reduced waste and environmental friendly solution in comparison to contemporary harnesses.