GB2181050A

GB2181050A - Aircraft fire control

Info

Publication number: GB2181050A
Application number: GB08524608A
Authority: GB
Inventors: Thomas Cassie Faulds
Original assignee: Individual
Current assignee: Individual
Priority date: 1985-10-05
Filing date: 1985-10-05
Publication date: 1987-04-15
Also published as: GB2181050B; GB8524608D0

Abstract

This invention relates to a fire control system for an aircraft and comprises means for producing a barrier, curtain or blanket at a number of positions along the length of the internal cabin or body of the aircraft. In one example each of the barrier units comprises a fluid pressure duct 21 shaped as a hood around the cabin with a number of spaced nozzles 22 at intervals. These pressure ducts are connected to external quick-connect couplings by which the whole system can be supplied with water or other fire extinguishing fluid from a vehicle on the ground outside the aircraft. Alternatively the aircraft may be provided with a built-in reservoir for fire fighting fluid or there may be a connection to a conventional water supply on board the aircraft. Instead of a liquid "curtain" the system may be arranged to provide a curtain of air or an inert gas. In another alternative the system may be arranged to release mechanical barriers consisting of a large number of separate strands or ribbons. <IMAGE>

Description

SPECIFICATION Aircraft Fire Control This invention relates to systems for controlling fires in aircraft and is particularly though not exclusively applicable to a system designed to confine a fire or fumes to a localised zone in the aircraft cabin with the object of facilitating escape for the passengers and crew.

The invention is based on the appreciation that if a fire occurs in an aircraft near or on the ground there will be very little time available for evacuating passengers and one of the main hazards is the smoke and fumes which not only reduce visibility but are sometimes lethally dangerous, possibly more so than the actual fire itself. The invention is based on the idea of providing means to localise fire, smoke, and fumes within the aircraft for a limited period of time.

Broadly stated the invention consists in an aircraft including a fire control system arranged to provide a barrier, "curtain" or "blanket" at one or more positions along the length of the internal cabin.

In a preferred construction the barrier system comprises a number of liquid spray nozzles or jets.

The nozzles or jets may be connected to fluid pressure supply ducts positioned at intervals along the length of the cabin.

According to another preferred feature of the invention the aircraft includes means for introducing a pressure fluid into the aircraft from an external access point. The access point may include a quick connection coupling for connection to a supply hose of a fire control vehicle. Alternatively or in addition the aircraft may include means for supplying liquid to the system from a liquid container on the aircraft.

The invention may be performed in various ways and one specific embodiment with a number of possible modifications will now be described by way of example with reference to the accompanying drawings in which, Figure 1 is a general perspective view of a passenger aircraft with a fire control system according to the invention indicated diagrammatically, Figure 2 is a fragmentary perspective view partly in section illustrating part of the control system, Figure 3 is a view illustrating one of the external access panels, and Figure 4 is a perspective view illustrating another aircraft with a fire control system according to the invention.

In the aircraft illustrated in Figures 1,2, and 3, the main passenger cabin 10 is as normal in the central part of the body of the aircraft, with the flying deck and crew accommodation 11 at the nose, toilet area 11 nearthetail, and below the passenger cabin a cargo hold 12. The aircraft of course has the usual wings 13, conventionally with under slung engines 14, and a tail assembly 15 which in this particular Tri-Star aircraft includes a third engine.

The fire control system comprises five longitudinally spaced "curtain" units 20 each designed to project a spray of water or other liquid within the cabin to form in effect a curtain preventing or minimising movement of fire or fumes lengthways. As shown in Figure 2 each unit comprises a pressure conduit 21 which extends as a half hoop around the sides and top of the cabin, and is provided with a number of pressure heads or nozzles 22, aimed inwards into the cabin. Further conduits 23, connect one conduit 21 to the next, and the whole fluid pressure system is connected to one or more external access panels 24. These are positioned in the aircraft's outer skin and each includes a closure flap 25, protecting the quickconnect coupling 26, which enables rapid connection to a pressure supply hose on a fire control vehicle on the ground.

Alternatively or in addition the fluid pressure supply system within the aircraft may be connected as required via control valves and/or pumps to a container or reservoir on the aircraft. This may be the conventional water supply normally provided on any aircraft, or it may be a special fire fighting reservoir.

In the alternative aircraft illustrated in Figure 4, the basic essentials of the control system are the same and here again there are a number of control units 20, each comprising a hoop-like pressure conduit 21, with spray heads 22, and means for connection to an external or internal fire fighting supply system.

in place of, or in addition to the localised supply "curtains" described above the control system may use other methods of limiting movement of fire or fumes within the body of the aircraft. For example an effective transverse "curtain" may be achieved by creating a transverse draught or current of air or other gas. Air for such a curtain may be drawn in from outside the aircraft and extracted through exit apertures on the opposite side of the cabin or in the floor or ceiling as the case may be.

Furthermore, the control system may include mechanical devices for restricting movement of fire and fumes, but without impeding movement of passengers towards the escape openings. For example there may be a curtain of strands or ribbons which is released from overhead at any selected station to limit movement of fumes lengthways.

1.An aircraft including a fire control system arranged to provide a barrier, curtain or blanket at one or more positions along the length of the internal cabin.

2. An aircraft according to claim 1 in which the barrier system comprises a number of liquid spray nozzles or jets.

3. An aircraft according to claim 2 in which the nozzles or jets may be connected to fluid pressure supply ducts positioned at intervals along the length of the cabin.

4. An aircraft according to any of the preceding claims including means for introducing a pressure fluid into the aircraft from an external access point.

5. An aircraft according to claim 4 in which the access point includes a quick connection coupling for connection to a supply hose of a fire control

**WARNING** end of DESC field may overlap start of CLMS **.

Claims

**WARNING** start of CLMS field may overlap end of DESC **. SPECIFICATION Aircraft Fire Control This invention relates to systems for controlling fires in aircraft and is particularly though not exclusively applicable to a system designed to confine a fire or fumes to a localised zone in the aircraft cabin with the object of facilitating escape for the passengers and crew. The invention is based on the appreciation that if a fire occurs in an aircraft near or on the ground there will be very little time available for evacuating passengers and one of the main hazards is the smoke and fumes which not only reduce visibility but are sometimes lethally dangerous, possibly more so than the actual fire itself. The invention is based on the idea of providing means to localise fire, smoke, and fumes within the aircraft for a limited period of time. Broadly stated the invention consists in an aircraft including a fire control system arranged to provide a barrier, "curtain" or "blanket" at one or more positions along the length of the internal cabin. In a preferred construction the barrier system comprises a number of liquid spray nozzles or jets. The nozzles or jets may be connected to fluid pressure supply ducts positioned at intervals along the length of the cabin. According to another preferred feature of the invention the aircraft includes means for introducing a pressure fluid into the aircraft from an external access point. The access point may include a quick connection coupling for connection to a supply hose of a fire control vehicle. Alternatively or in addition the aircraft may include means for supplying liquid to the system from a liquid container on the aircraft. The invention may be performed in various ways and one specific embodiment with a number of possible modifications will now be described by way of example with reference to the accompanying drawings in which, Figure 1 is a general perspective view of a passenger aircraft with a fire control system according to the invention indicated diagrammatically, Figure 2 is a fragmentary perspective view partly in section illustrating part of the control system, Figure 3 is a view illustrating one of the external access panels, and Figure 4 is a perspective view illustrating another aircraft with a fire control system according to the invention. In the aircraft illustrated in Figures 1,2, and 3, the main passenger cabin 10 is as normal in the central part of the body of the aircraft, with the flying deck and crew accommodation 11 at the nose, toilet area 11 nearthetail, and below the passenger cabin a cargo hold 12. The aircraft of course has the usual wings 13, conventionally with under slung engines 14, and a tail assembly 15 which in this particular Tri-Star aircraft includes a third engine. The fire control system comprises five longitudinally spaced "curtain" units 20 each designed to project a spray of water or other liquid within the cabin to form in effect a curtain preventing or minimising movement of fire or fumes lengthways. As shown in Figure 2 each unit comprises a pressure conduit 21 which extends as a half hoop around the sides and top of the cabin, and is provided with a number of pressure heads or nozzles 22, aimed inwards into the cabin. Further conduits 23, connect one conduit 21 to the next, and the whole fluid pressure system is connected to one or more external access panels 24. These are positioned in the aircraft's outer skin and each includes a closure flap 25, protecting the quickconnect coupling 26, which enables rapid connection to a pressure supply hose on a fire control vehicle on the ground. Alternatively or in addition the fluid pressure supply system within the aircraft may be connected as required via control valves and/or pumps to a container or reservoir on the aircraft. This may be the conventional water supply normally provided on any aircraft, or it may be a special fire fighting reservoir. In the alternative aircraft illustrated in Figure 4, the basic essentials of the control system are the same and here again there are a number of control units 20, each comprising a hoop-like pressure conduit 21, with spray heads 22, and means for connection to an external or internal fire fighting supply system. in place of, or in addition to the localised supply "curtains" described above the control system may use other methods of limiting movement of fire or fumes within the body of the aircraft. For example an effective transverse "curtain" may be achieved by creating a transverse draught or current of air or other gas. Air for such a curtain may be drawn in from outside the aircraft and extracted through exit apertures on the opposite side of the cabin or in the floor or ceiling as the case may be. Furthermore, the control system may include mechanical devices for restricting movement of fire and fumes, but without impeding movement of passengers towards the escape openings. For example there may be a curtain of strands or ribbons which is released from overhead at any selected station to limit movement of fumes lengthways. CLAIMS

5. An aircraft according to claim 4 in which the access point includes a quick connection coupling for connection to a supply hose of a fire control vehicle.

6. An aircraft according to claim 4 including means for supplying liquid to the system from a liquid container on the aircraft.

7. A fire control barrier, curtain or blanket system, for use in conjunction with an aircraft to accord with any one of the preceding claims.

8. An aircraft with a fire control system substantially as described with reference to the accompanying drawings.