WO2004018287A2 - Aircraft payload compartmentalization system - Google Patents

Aircraft payload compartmentalization system Download PDF

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Publication number
WO2004018287A2
WO2004018287A2 PCT/IL2003/000673 IL0300673W WO2004018287A2 WO 2004018287 A2 WO2004018287 A2 WO 2004018287A2 IL 0300673 W IL0300673 W IL 0300673W WO 2004018287 A2 WO2004018287 A2 WO 2004018287A2
Authority
WO
WIPO (PCT)
Prior art keywords
aircraft
fuel tank
compartment
compartmentalized
supplemental
Prior art date
Application number
PCT/IL2003/000673
Other languages
French (fr)
Other versions
WO2004018287A3 (en
Inventor
Zvi Zuckerman
Original Assignee
Rafael - Armament Development Authority Ltd
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 Rafael - Armament Development Authority Ltd filed Critical Rafael - Armament Development Authority Ltd
Priority to AU2003250512A priority Critical patent/AU2003250512A1/en
Publication of WO2004018287A2 publication Critical patent/WO2004018287A2/en
Publication of WO2004018287A3 publication Critical patent/WO2004018287A3/en

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D37/00—Arrangements in connection with fuel supply for power plant
    • B64D37/02—Tanks
    • B64D37/06—Constructional adaptations thereof
    • B64D37/08—Internal partitioning

Definitions

  • the present invention relates generally to aviation and to aircraft payload management. More specifically, the invention deals with the installation of equipment for intelligence collection, communications, flight support and combat activities.
  • accessory equipment is employed for the enhancement of the performance of aircraft capabilities.
  • Military aircraft planners are challenged to the extreme by the users who demand up - to - date weapon systems and intelligence gathering systems to be put to use in order to compete successfully with rival combat systems. Changes in the structure of an aircraft that are made in order to accommodate for new equipment are potentially harmful and may degrade the performance of the aircraft in one or more aspects. In almost any case, the addition or change of equipment on the aircraft involves expensive design procedures, restructuring, and laboratory and field testing.
  • ECM electric counter measures
  • ESM electronic support measures
  • optical payloads for intelligence gathering SAR radars, etc.
  • Fig. 1A is schematic description of a cross section in an external fuel tank in accordance with a preferred embodiment of the present invention containing one supplemental compartment
  • Fig. 1 B is schematic description of a cross section in an external fuel tank in accordance with a preferred embodiment of the present invention
  • Fig. 2A is a schematic description of a communications arrangement
  • Fig. 2B is a schematic description of a communications arrangement
  • Fig. 2C is a schematic description of a communications arrangement
  • Fig. 2D is a schematic description of a communications arrangement on an aircraft including one fuel tanks in accordance with the invention.
  • Fig. 2E is a schematic description of a communications arrangement
  • Fig. 2F is a schematic description of a communications arrangement
  • Fig. 2G is a schematic description of a communications arrangement
  • Fig. 2H is a schematic description of a communications arrangement on an aircraft including two fuel tanks in accordance with the invention
  • Fig. 21 is a schematic description of a communications arrangement on an aircraft including one fuel tank communicating with an external pod of the aircraft.
  • external fuel tanks of aircraft are compartmentalized such that accessory equipment is functionally incorporated therein.
  • the allotment of a compartment for accessory equipment does not appreciably decrease the original functionality of the fuel
  • FTSP supplemental payload
  • externally mounted fuel tank 16 contains a major compartment 18, being filled
  • Compartment 22 is secluded from compartment 20, bearing
  • the external shape In a typical embodiment of the present invention, the external shape
  • the FTSP is a consumer of electrical power and to fulfill the needs for energy a connection to the power supply of the aircraft is required, or as an alternative, an autonomous power supply may be provided.
  • Electric power for the supplemental payload systems or subsystems mounted in accordance with the present invention can be derived from a physical electric connection to the power network of the aircraft. Such a connection can be used for communications purposes, over the same physical connection.
  • a dedicated communications connection can be installed to connect the supplemental system to the communications bus of the aircraft.
  • An end point of the communications network of the aircraft may be physically present in the aircraft or on an external pod thereof.
  • Another alternative is a wireless system, typically a wireless communications system such an RF or an IR frequency system, linking the FTSP with the main communications system of the aircraft.
  • the multi - frequency BluetoothTM system is a likely candidate for such a communications link.
  • a direct link of the FTSP to a ground station is effected though a communications means employing long distance wireless connection.
  • a first FTSP communicates through a wired or a wireless link with another FTSP on the same aircraft, wherein the second FTSP maintains a communications link with the aircraft.
  • FIG. 2A an FTSP 40 installed on an aircraft communicates with the aircraft 42.
  • the aircraft 42 communicates with the ground control 46.
  • Fig. 2B the FTSP 40 installed on an aircraft communicates with the ground control 46.
  • aircraft 48 communicates with two FTSPs which it bears, FTSP 50 and FTSP
  • Aircraft 48 also communicates with ground control 54.
  • FTSP 56 communicates with FTSP 58 which in turn communicates with the aircraft 60 on which both FTSPs are installed.
  • Aircraft 60 also communicates with ground
  • FTSP 70 communicates with FTSP 72 that also communicates with FTSP 72 that also communicates with FTSP 72 that also communicates with FTSP 72 that also communicates with FTSP 72 that also communicates with FTSP 72 that also communicates with FTSP 72 that also communicates with FTSP 72 that also communicates with FTSP 72 that also communicates with FTSP 72 that also communicates with FTSP 72 that also communicates with FTSP 72.
  • FTSP 78 also communicates with aircraft 80 and with ground
  • FTSP 84 communicates with FTSP 86, which also
  • Aircraft 88 communicates with ground control
  • FTSP 100 communicates with aircraft 102.
  • Fig. 2H FTSP 104 communicates with FTSP 106 as well as with aircraft 108.
  • Aircraft 108
  • FTSP 110 communicates also with FTSP 106.
  • FTSP 110 communicates with an
  • Aircraft 114 communicates with pod
  • An externally mounted jettisonable fuel tank or a conformal fuel tank in accordance with the present invention can carry whole systems or components of systems. Moreover, such tanks can carry several whole systems or parts of different systems. These systems, subsystems or parts of systems are defined in accordance with the present invention as fuel tank supplemental payloads (FTSPs).
  • FTSPs fuel tank supplemental payloads
  • a single supplemental compartment can house several subsystems of the same system, or several subsystems corresponding and linked to systems aboard the aircraft.
  • a radar antenna together with its scanning gear and control is installed, whereas in another supplemental compartment the RF circuitry is housed.
  • column 1 on the left lists mission - dedicated systems (payloads) or subsystems to be deployed in a fuel tank supplemental compartment, whereas column 2 lists supporting systems each complementing the functionality of the system listed in column 1.
  • the connected systems of column 2 may mounted in the same compartment as the mission dedicated system it supports.
  • Such supporting system may use the electrical power resources of the aircraft, or a dedicated power source.
  • such equipment may use the aircraft communications bus, or another wired or wireless communications system.
  • Such supporting systems can be made to communicate also with other FTSP systems on board the same aircraft, located in other compartments, or with support systems or subsystems of such additional FTSPs.
  • Table I An exemplary list of FTSPs systems and complementary systems or subsystems, to be employed in fuel tanks of the invention.
  • Aircraft platforms suitable for versatile fuel tanks of the invention are provided.
  • a fuel tank in accordance with the present invention is a typically a fighter airplane which is usually a cramped platform.
  • the system of the invention may be implemented in any aircraft platform having external or conformal fuel tanks, such as helicopters, unmanned aircraft and civilian manned aircraft.
  • a system in accordance with the present invention can replace a pod installed on an aircraft, the advantages with respect to such a pod are meaningful.
  • a pod has a negative affect on the aerodynamic properties and on the maneuverability of the aircraft, whereas the system of the invention has no such adverse effect.
  • the use of a fuel tank, and especially of an ejectable fuel tank as a housing for a payload or support system thereof reduces the amount of structural changes required to be made in the aircraft, to house the supplemental system.
  • mounting payload in accordance with the present invention can obviate the deviant use of external weapons stations or external fuel tank stations or external air - to - air missile stations, thus preventing a degradation in the overall performance of the aircraft.
  • the option of using a fuel tank for supplemental payload is especially rewarding as regards air to ground surveillance and air to ground and to air surveillance.
  • the reason for that is that bottom fuel tanks have a relatively unobstructed field of view as regards the ground and forward - looking direction.
  • This aspect of the system of the invention can be exploited for implementing electro- optical as well as RF sensors and utilities in an efficient manner.
  • An external fuel tank typically an ejectable one
  • an ejectable fuel tank in accordance with the present invention, is required by several aircraft, the fuel tank can be dismounted from one aircraft when it has finished its mission and subsequently mounted on a different aircraft in preparation for another mission.
  • the system of the present invention affords an extra degree of independence in the structuring design of payload application, with regards to implementing newer systems within the aircraft itself.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Traffic Control Systems (AREA)
  • Filling Or Discharging Of Gas Storage Vessels (AREA)

Abstract

A compartmentalized fuel tank of an aircraft, in which one compartment carries fuel whereas supplementary compartments carry payloads. The other payloads installed in secluded compartments may be single units or plurality of units, or they may constitute subsystems of a distributed system. Exemplary modules housed in a supplementary compartment of the invention are data collection modules and communication modules.

Description

AIRCRAFT PAYLOAD COMPARTMENTALIZATION SYSTEM
TECHNICAL FIELD OF THE INVENTION
The present invention relates generally to aviation and to aircraft payload management. More specifically, the invention deals with the installation of equipment for intelligence collection, communications, flight support and combat activities.
BACKGROUND OF THE INVENTION
Aircraft use a variety of accessory equipment for diversifying the missions that it can perform. In addition, accessory equipment is employed for the enhancement of the performance of aircraft capabilities. New equipment associated with the ever developing industry of aviation technology, navigation technology, elint technology, communications, electro - optics and else require aircraft builders and planners to accommodate their products to the changing equipment offered for purchase and use. Military aircraft planners are challenged to the extreme by the users who demand up - to - date weapon systems and intelligence gathering systems to be put to use in order to compete successfully with rival combat systems. Changes in the structure of an aircraft that are made in order to accommodate for new equipment are potentially harmful and may degrade the performance of the aircraft in one or more aspects. In almost any case, the addition or change of equipment on the aircraft involves expensive design procedures, restructuring, and laboratory and field testing.
As regards combat aircraft, there is a need for stations for the application of various kinds of payload. Thus, external equipment stations originally intended for weapons and fuel are used for mounting miscellaneous payload such ECM (electric counter measures), self defense systems including ESM (electronic support measures), optical payloads for intelligence gathering, SAR radars, etc.
BRIEF DESCRIPTION OF THE DRAWINGS
Fig. 1A is schematic description of a cross section in an external fuel tank in accordance with a preferred embodiment of the present invention containing one supplemental compartment; Fig. 1 B is schematic description of a cross section in an external fuel tank in accordance with a preferred embodiment of the present invention
containing two supplemental compartments;
Fig. 2A is a schematic description of a communications arrangement
on an aircraft including one fuel tank in accordance with the invention;
Fig. 2B is a schematic description of a communications arrangement
on an aircraft including two fuel tanks in accordance with the invention;
Fig. 2C is a schematic description of a communications arrangement
on an aircraft including two fuel tanks in accordance with the invention;
Fig. 2D is a schematic description of a communications arrangement on an aircraft including one fuel tanks in accordance with the invention;
Fig. 2E is a schematic description of a communications arrangement
on an aircraft including two fuel tanks in accordance with the invention;
Fig. 2F is a schematic description of a communications arrangement
on an aircraft including two fuel tanks in accordance with the invention;
Fig. 2G is a schematic description of a communications arrangement
on an aircraft including one fuel tank in accordance with the invention;
Fig. 2H is a schematic description of a communications arrangement on an aircraft including two fuel tanks in accordance with the invention; Fig. 21 is a schematic description of a communications arrangement on an aircraft including one fuel tank communicating with an external pod of the aircraft.
DETAILED DESCRIPTION OF THE PRESENT INVENTION
In accordance with the present invention, external fuel tanks of aircraft are compartmentalized such that accessory equipment is functionally incorporated therein. Typically, the allotment of a compartment for accessory equipment does not appreciably decrease the original functionality of the fuel
tank. Such accessory equipment will be referred to hereinafter as fuel tank
supplemental payload (FTSP). An embodiment of the invention is schematically
described in Figs. 1A - B to which reference is now made. In Fig. 1A an
externally mounted fuel tank 16 contains a major compartment 18, being filled
mostly with fuel 20. Compartment 22 is secluded from compartment 20, bearing
payloads as will be described below. In another embodiment of the present
invention, described schematically in Fig. 1B, an externally mounted fuel tank
30, includes a major compartment 32, being filled mostly with fuel 34.
Compartment 36 at the front of the fuel tank is secluded from the main
compartment 32. A posterior compartment 38 of the fuel tank 30 is secluded
from the major compartment 32. The added functionality of such fuel tanks is associated with the FTSP, which is maintained in the supplemental compartment. The possible consumption of the fuel during flight does not alter
the functionality of the extra functionality.
In a typical embodiment of the present invention, the external shape
of the fuel tank does not substantially change with respect to the conventional
fuel tank. This way, aerodynamical properties of the compartmentalized fuel
tank are not changed, keeping thus the aircraft's flight characteristics
substantially unchanged. In a typical embodiment of the present invention the FTSP is a consumer of electrical power and to fulfill the needs for energy a connection to the power supply of the aircraft is required, or as an alternative, an autonomous power supply may be provided. Throughout the ongoing description, the nature and usefulness of the equipment as specifically mounted in accordance with the invention will be described, with reference to the fulfillment of the missions assigned to the aircraft.
Power links and communications with the FTSP As mentioned above, electric power for the supplemental payload systems or subsystems mounted in accordance with the present invention can be derived from a physical electric connection to the power network of the aircraft. Such a connection can be used for communications purposes, over the same physical connection. As a viable alternative, a dedicated communications connection can be installed to connect the supplemental system to the communications bus of the aircraft. An end point of the communications network of the aircraft may be physically present in the aircraft or on an external pod thereof. Another alternative is a wireless system, typically a wireless communications system such an RF or an IR frequency system, linking the FTSP with the main communications system of the aircraft. The multi - frequency Bluetooth™ system is a likely candidate for such a communications link. As an option, a direct link of the FTSP to a ground station is effected though a communications means employing long distance wireless connection. In another alternative, a first FTSP communicates through a wired or a wireless link with another FTSP on the same aircraft, wherein the second FTSP maintains a communications link with the aircraft. Several exemplary combinations of the communications linking accommodating for FTSP in accordance with the present invention are described schematically in Fig. 2A -
21. In Fig. 2A an FTSP 40 installed on an aircraft communicates with the aircraft 42. The aircraft 42 communicates with the ground control 46. In Fig. 2B the
aircraft 48 communicates with two FTSPs which it bears, FTSP 50 and FTSP
52. Aircraft 48 also communicates with ground control 54. In Fig. 2C FTSP 56 communicates with FTSP 58 which in turn communicates with the aircraft 60 on which both FTSPs are installed. Aircraft 60 also communicates with ground
control 62. In Fig. 2D FTSP 70 communicates with FTSP 72 that also
communicates with the ground control 74. In Fig. 2E FTSP 76 communicates
with FTSP 78. FTSP 78 also communicates with aircraft 80 and with ground
control 82. In Fig. 2F FTSP 84 communicates with FTSP 86, which also
communicates with aircraft 88. Aircraft 88 communicates with ground control
90. In Fig. 2G FTSP 100 communicates with aircraft 102. In Fig. 2H FTSP 104 communicates with FTSP 106 as well as with aircraft 108. Aircraft 108
communicates also with FTSP 106. In Fig. 21 FTSP 110 communicates with an
external pod 112 installed on aircraft 114. Aircraft 114 communicates with pod
112.
Types of payloads utilizable in embodiments of the invention
An externally mounted jettisonable fuel tank or a conformal fuel tank in accordance with the present invention can carry whole systems or components of systems. Moreover, such tanks can carry several whole systems or parts of different systems. These systems, subsystems or parts of systems are defined in accordance with the present invention as fuel tank supplemental payloads (FTSPs). To generalize the deployment strategies taking advantage of supplemental compartments aboard the aircraft in accordance with the present invention, to any one supplemental compartment can be allocated a subsystems, parts, or a whole systems be they functionally connected or not. Conversely, a single supplemental compartment can house several subsystems of the same system, or several subsystems corresponding and linked to systems aboard the aircraft. In a specific example, in one supplemental compartment a radar antenna together with its scanning gear and control is installed, whereas in another supplemental compartment the RF circuitry is housed. In table I, column 1 on the left lists mission - dedicated systems (payloads) or subsystems to be deployed in a fuel tank supplemental compartment, whereas column 2 lists supporting systems each complementing the functionality of the system listed in column 1. The connected systems of column 2 may mounted in the same compartment as the mission dedicated system it supports. Such supporting system may use the electrical power resources of the aircraft, or a dedicated power source. For communications purposes, such equipment may use the aircraft communications bus, or another wired or wireless communications system. Such supporting systems can be made to communicate also with other FTSP systems on board the same aircraft, located in other compartments, or with support systems or subsystems of such additional FTSPs.
Figure imgf000010_0001
Table I. An exemplary list of FTSPs systems and complementary systems or subsystems, to be employed in fuel tanks of the invention.
Aircraft platforms suitable for versatile fuel tanks of the invention
A fuel tank in accordance with the present invention is a typically a fighter airplane which is usually a cramped platform. However, the system of the invention may be implemented in any aircraft platform having external or conformal fuel tanks, such as helicopters, unmanned aircraft and civilian manned aircraft.
Advantages of the system of the invention
Inasmuch as a system in accordance with the present invention can replace a pod installed on an aircraft, the advantages with respect to such a pod are meaningful. A pod has a negative affect on the aerodynamic properties and on the maneuverability of the aircraft, whereas the system of the invention has no such adverse effect. The use of a fuel tank, and especially of an ejectable fuel tank as a housing for a payload or support system thereof, reduces the amount of structural changes required to be made in the aircraft, to house the supplemental system. Moreover, mounting payload in accordance with the present invention, can obviate the deviant use of external weapons stations or external fuel tank stations or external air - to - air missile stations, thus preventing a degradation in the overall performance of the aircraft. The option of using a fuel tank for supplemental payload is especially rewarding as regards air to ground surveillance and air to ground and to air surveillance. The reason for that is that bottom fuel tanks have a relatively unobstructed field of view as regards the ground and forward - looking direction. This aspect of the system of the invention can be exploited for implementing electro- optical as well as RF sensors and utilities in an efficient manner.
An external fuel tank, typically an ejectable one, lends itself easily to interchanging between different aircraft. For example, in the case that an ejectable fuel tank, in accordance with the present invention, is required by several aircraft, the fuel tank can be dismounted from one aircraft when it has finished its mission and subsequently mounted on a different aircraft in preparation for another mission.
As a substitute for a conformal fuel tank system, the system of the present invention affords an extra degree of independence in the structuring design of payload application, with regards to implementing newer systems within the aircraft itself.

Claims

1. A compartmentalized fuel tank of an aircraft, wherein a compartment thereof contains fuel stored for supplying energy to said aircraft, and in at least one supplemental compartment at least a supplemental subsystem of said aircraft is installed.
2. A compartmentalized fuel tank of an aircraft as in claim 1 and wherein said compartment thereof containing fuel is major compartment of said fuel tank.
3. A compartmentalized fuel tank of an aircraft as in claim 1 and wherein a communications system is installed in a compartment thereof.
4. A compartmentalized fuel tank of an aircraft as in claim 1 and wherein a data link is installed in a compartment thereof.
5. A compartmentalized fuel tank of an aircraft as in claim 1 and
wherein a towed payload is installed in a compartment thereof.
6. A compartmentalized fuel tank of an aircraft as in claim 1 and wherein a decoy system is installed in a compartment thereof.
7. A compartmentalized fuel tank of an aircraft as in claim 6 and wherein said decoy is a chaff system.
8. A compartmentalized fuel tank of an aircraft as in claim 6 and 5 wherein said decoy is a flare system.
9. A compartmentalized fuel tank of an aircraft as in claim 6 and wherein said decoy is an expendable RF decoy system.
10 10. A compartmentalized fuel tank of an aircraft as in claim 6 and wherein said decoy is an expendable active system.
11. A compartmentalized fuel tank of an aircraft as in claim 1 and wherein a radar - warning receiver is installed in a compartment
15 thereof.
12. A compartmentalized fuel tank of an aircraft as in claim 1 and wherein a navigation system is installed in a compartment thereof.
20 13. A compartmentalized fuel tank of an aircraft as in claim 12 and wherein said navigation system is an inertial navigation system, installed in a compartment thereof.
14. A compartmentalized fuel tank of an aircraft as in claim 12 and wherein said navigation system is a GPS based system, installed in a compartment thereof.
5 15. A compartmentalized fuel tank of an aircraft as in claim 1 and wherein an optical sensor is installed in a compartment thereof.
16. A compartmentalized fuel tank of an aircraft as in claim 15 and wherein said optical sensor is a UV sensor.
10
17. A compartmentalized fuel tank of an aircraft as in claim 15 and wherein said optical sensor is a IR sensor.
18. A compartmentalized fuel tank of an aircraft as in claim 15 and 15 wherein said optical sensor is a visible light sensor.
19. A compartmentalized fuel tank of an aircraft as in claim 1 and wherein a laser source is installed in a compartment thereof.
20 20. A compartmentalized fuel tank of an aircraft as in claim 19 and wherein said laser source is for target designation.
21. A compartmentalized fuel tank of an aircraft as in claim 19 and wherein said laser source is for data collecting.
25
22. A compartmentalized fuel tank of an aircraft as in claim 1 and wherein a radar system is installed in a compartment thereof.
5 23. A compartmentalized fuel tank of an aircraft as in claim 22 and wherein said radar is a SAR system.
24. A compartmentalized fuel tank of an aircraft as in claim 1 and wherein a ESM system is installed in a compartment thereof.
10
25. A compartmentalized fuel tank of an aircraft as in claim 1 and wherein said fuel tank is external.
26. A compartmentalized fuel tank of an aircraft as in claim 25 and 15 wherein said fuel tank is jettisonable.
27. A compartmentalized fuel tank of an aircraft as in claim 1 and wherein a whole system is installed in a compartment thereof.
20 28. A compartmentalized fuel tank of an aircraft as in claim 1 and wherein an antenna and RF circuitry of an elint system are installed in compartment thereof.
29. A compartmentalized external fuel tank of an aircraft as in claim
28 and wherein said elint system is a di - axial system for direction finding of an emitting target.
30. A compartmentalized external fuel tank of an aircraft as in claim 28 and wherein said elint system is geo - location referenced.
31. A method for incorporating supplemental payload in an aircraft, comprising the steps of:
• compartmentalizing at least one fuel tank of said aircraft;
• using a first compartment of said at least one fuel tank for storing fuel for a flight of said aircraft; and
• using at least a second compartment of said aircraft for functionally incorporating at least a subsystem of said supplemental payload.
32. A method for incorporating supplemental payload in an aircraft as in claim 31 , and wherein said compartmentalized fuel tank is external.
33. A method for incorporating supplemental payload in an aircraft as in claim 31 , wherein a subsystem of said supplemental payload equipment is installed in one compartment, and wherein another subsystem of said supplemental payload equipment is installed in another compartment of said at least one fuel tank.
34. A method for incorporating supplemental payload in an aircraft as in claim 31 , and wherein a communications system is installed within at least said second compartment.
35. A method for incorporating supplemental payload equipment in an aircraft as in claim 34, and wherein said communications system communicates with a communication system of said aircraft.
36. A method for incorporating supplemental payload equipment in an aircraft as in claim 34, and wherein said communication system communicates with a communication system of another supplemental payload equipment installed in another supplemental compartment of said aircraft.
37.
PCT/IL2003/000673 2002-08-21 2003-08-13 Aircraft payload compartmentalization system WO2004018287A2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AU2003250512A AU2003250512A1 (en) 2002-08-21 2003-08-13 Aircraft payload compartmentalization system

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
IL15138302A IL151383A0 (en) 2002-08-21 2002-08-21 Aircraft payload compartmentalization system
IL151383 2002-08-21

Publications (2)

Publication Number Publication Date
WO2004018287A2 true WO2004018287A2 (en) 2004-03-04
WO2004018287A3 WO2004018287A3 (en) 2004-06-17

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Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2955787A (en) * 1956-12-27 1960-10-11 Lockheed Aircraft Corp Auxiliary fuel tank
US3447768A (en) * 1967-02-08 1969-06-03 Whittaker Corp Lifting body external fuel stores
US4679483A (en) * 1986-02-07 1987-07-14 U.S. Philips Corporation Dispenser and dispensing cassette
US5191370A (en) * 1990-09-18 1993-03-02 Agip S.P.A. Multi-section helicopter-borne rotatable beam, specially adapted to support range-finder cameras and television focusing cameras for stereophotogrammetric surveys
US5663518A (en) * 1994-06-06 1997-09-02 Advanced Technology Materials, Inc. Method and device for the in-flight cutting and dispensing of chaff dipoles from an aerial vehicle

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2955787A (en) * 1956-12-27 1960-10-11 Lockheed Aircraft Corp Auxiliary fuel tank
US3447768A (en) * 1967-02-08 1969-06-03 Whittaker Corp Lifting body external fuel stores
US4679483A (en) * 1986-02-07 1987-07-14 U.S. Philips Corporation Dispenser and dispensing cassette
US5191370A (en) * 1990-09-18 1993-03-02 Agip S.P.A. Multi-section helicopter-borne rotatable beam, specially adapted to support range-finder cameras and television focusing cameras for stereophotogrammetric surveys
US5663518A (en) * 1994-06-06 1997-09-02 Advanced Technology Materials, Inc. Method and device for the in-flight cutting and dispensing of chaff dipoles from an aerial vehicle

Also Published As

Publication number Publication date
IL151383A0 (en) 2004-03-28
WO2004018287A3 (en) 2004-06-17
AU2003250512A1 (en) 2004-03-11
AU2003250512A8 (en) 2004-03-11

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