U.S. patent number 3,911,787 [Application Number 05/446,701] was granted by the patent office on 1975-10-14 for safe aircraft ammunition container.
This patent grant is currently assigned to Textron, Inc.. Invention is credited to Charles M. Seibel.
United States Patent |
3,911,787 |
Seibel |
October 14, 1975 |
Safe aircraft ammunition container
Abstract
Aircraft ammunition is loaded nose-down in an ejectable
container that is attached to the bottom of the aircraft external
to primary aircraft structure, to minimize peril in the event of
explosion of the ammunition.
Inventors: |
Seibel; Charles M. (Hurst,
TX) |
Assignee: |
Textron, Inc. (Providence,
RI)
|
Family
ID: |
23773545 |
Appl.
No.: |
05/446,701 |
Filed: |
February 28, 1974 |
Current U.S.
Class: |
89/34; 89/37.16;
244/137.1 |
Current CPC
Class: |
B64D
7/00 (20130101); B64D 1/04 (20130101); F42B
39/20 (20130101); F41A 9/29 (20130101) |
Current International
Class: |
F42B
39/00 (20060101); F41A 9/00 (20060101); B64D
1/00 (20060101); B64D 1/04 (20060101); F42B
39/20 (20060101); B64D 7/00 (20060101); F41A
9/29 (20060101); B64D 001/04 () |
Field of
Search: |
;89/1.5F,34,37.5R,37.5C |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Bentley; Stephen C.
Attorney, Agent or Firm: Richards, Harris & Medlock
Claims
What is claimed is:
1. An airborne ammunition container for an aircraft,
comprising:
a. a housing container to accommodate ammunition pieces;
b. said housing container connected to said aircraft external to
the primary aircraft structure;
c. a blowout cover on the bottom of said ammunition container
whereby an explosion in the container can be vented down through
the cover;
d. means for storing ammunition pieces within said housing
container such that the trajectory of said ammunition pieces when
detonated within said container is away from said aircraft; and
e. means to eject said housing container from said aircraft.
2. The combination as set forth in claim 1, wherein said ejecting
means comprise a plurality of pyrotechnic thrusters.
3. The combination as set forth in claim 2, wherein said thrusters
are four in number.
4. The combination of claim 1 additionally comprising a solid
barrier positioned over said ammunition container whereby the
aircraft and crew are provided with blast protection thereby.
5. In an airborne weapon system in which a feed mechanism
transports ammunition to a weapon, the combination which
comprises:
a. an aircraft fuselage with an ammunition container nested in an
underside open cavity and connected to said aircraft external of
primary aircraft structure;
b. means for storing ammunition in said container with the
projectiles pointing downward away from said fuselage and means
comprising a blowout cover on the bottom of the ammunition
container;
c. a plurality of breakaway fasteners to connect said container to
said feed mechanism; and
d. a plurality of pyrotechnic thrusters to disconnect said
container from said aircraft.
6. The combination as set forth in claim 5, wherein said thrusters
are four in number.
7. The combination as set forth in claim 5 additionally comprising
a solid barrier positioned over said ammunition container whereby
the aircraft and crew are provided with blast protection thereby.
Description
FIELD OF THE INVENTION
This invention relates to storage of ammunition on board an
aircraft, and more particularly, to an ammunition container located
on an aircraft external to primary aircraft structure with
orientation of the ammunition within an ejectable container so as
to ensure aircraft safety.
PRIOR ART
Ammunition containers on board an aircraft are typically housed
within the aircraft fuselage or wing, or within gun pods firmly
attached to the aircraft. The feeding mechanism draws either belted
ammunition from a standard linked ammunition cannister or delinked
ammunition from a drum magazine.
Ammunition linked in belts has characteristically been used with
weapons having low rates of fire. The ammunition is fed to the gun
by a feed mechanism which draws belted ammunition from the
container, extracts the ammunition from the belt links, feeds the
ammunition to the gun, and ejects the links and spent cases. The
linear movements of the gun components in recoil and counter-recoil
are transformed mechanically to provide the drive means for the
feed mechanism. Electric, hydraulic, or pneumatic devices may
provide alternate external power to drive the feed mechanism.
With weapons having high rates of fire, such as those utilizing the
Vulcan principle, linkless feed systems are employed because of the
problems associated with link and spent ammunition disposal. The
linkless feed system contains either a single or twin ammunition
conveyor belt within flexible chuting. With a single belt the spent
cases are ejected overboard, but in many installations a return
conveyor for spent cartridge cases is povided. A central rotor in
the form of a helical archimidean screw moves the round from the
drum into the conveyor in a multi-stage operation. The system may
be driven by a ram air turbine, or from gun gas bled from the
barrels. If linked ammunition is used it is fed through the gun via
a delinking feeder typically driven by an electric or hydraulic
motor.
Each of these weapon systems enclose the ammunition container
within an aircraft member. Further, the ammunition is stored in the
container and conveyed to the gun with the projectile pointed at
either the crew or essential components of the flight system.
During periods of emergency which arise from such contingencies as
a direct hit or an impending crash, the crew must rely primarily on
blast barriers to survive any ensuing explosion of the ammunition
container.
SUMMARY OF THE INVENTION
The present invention is directed to aircraft ammunition storage to
provide for rapid ejection of the ammunition in times of emergency,
and to minimize peril to the aircraft and crew while the container
remains in aircraft storage.
More particularly, the ammunition is stored nose-down in the
container, directed away from the aircraft and crew. The ammunition
container is nested in a cavity in the underside of the aircraft
behind the gun turret, with the bottom of the container forming the
lower contour of the aircraft.
Pyrotechnic units secure the ammunition storage unit to the
aircraft and are adapted to sever and force the container down and
away from the helicopter.
In a still further aspect, the forward portion of the system is
connected to the storage portion by means of break-away fasteners
so that upon ejection the forward portion remains in place.
DESCRIPTION OF THE DRAWINGS
For a more complete understanding of the present invention and for
further objects and advantages thereof, references may now be had
to the following description taken in conjunction with the
accompanying drawings in which:
FIG. 1 is a perspective view of a helicopter with part of the
fuselage broken away to illustrate an ammunition container coupled
to a feed mechanism supplying ammunition to a weapon.
FIG. 2 is a sectional view looking down from the top of a
helicopter onto an integrated weapon system including an ammunition
container.
FIG. 3 is a perspective view of an ammunition container with a
portion of the outer housing broken away showing nose-down
orientation of ammunition.
FIG. 4 is a sectional view of a helicopter feeding mechanism.
DESCRIPTION OF A PREFERRED EMBODIMENT
Referring to FIGS. 1 and 2, a flat storage and linkless feed system
supplies ammunition to weapon 11. The storage system incorporates a
unique ammunition storage container 2 which is a rectangular box.
An ammunition feed chute 4 and a return chute 6 house conveyor
elements which transport ammunition to a weapon feeder. Chute 4 is
connected to one corner of container 2 and to a flexible-shaft
drive booster 7 forward of the container. Another sealed fixed
chute 8 is connected from booster 7 and extends forward to a
receptacle to which a flexible chute 9 is attached. Chute 9 routes
the ammunition into the weapon feeder in a turret 10. The empty
conveyor leaves the feeder in a flexible chute which attaches to
the other corner of container 2 in the same manner as the feed
chute. Chute 6 routes the conveyor back to a corner of the
container 2. Chutes 6 and 9 are sealed and serve to vent the gun
gases above the turret.
A drive shaft 5a is shown connected between the container 2 and
booster 7. Drive shaft 5b is connected from booster 7 to the
receptacle of chute 8.
Two beams 14a and 14b contain structure for supporting gear boxes
and index mechanisms for required stoker and exit sprockets.
A solid barrier 3 provides blast protection for the aircraft and
crew.
To eject container 2, ejection forces are produced by four
pyrotechnic thrusters 1 which secure container 2 to helicopter 12.
When ejection is initiated, the thrusters 1 sever container 2 and
force it down and away from aircraft 12. The forward portion of the
feed mechanism is connected to container 2 by means of break-away
fasteners 13. When the container is ejected, the forward portion of
the feed mechanism remains in place.
In FIG. 3 container 2 is ejected from aircraft 12 with stored
ammunition 15 in a nose-down orientation. Thus, the ammunition is
always pointed away from the helicopter and crew when stored on
board an aircraft.
In FIG. 4, container 2 is located in a cavity behind the gun turret
in the underside of aircraft 12. The bottom of the container forms
the lower contour of aircraft 12 in the area of the cavity. The
container has blow-out cover 16 over its entire surface below the
bulk of the ammunition. Should an explosion occur in the storage
area, the blow-out cover offers the path of least resistance and
vents the majority of the concussion or debris down and away from
the aircraft 12 and its crew, control system, and other flight
essential components.
In accordance with the present invention, there is provided a
rectangular aircraft ammunition container within which ammunition
is stored nose-down away from aircraft and crew. Pyrotechnic
thrusters secure the container in a cavity in the under side of the
aircraft, while break-away fasteners couple the container to the on
board feed mechanism. The base of the container is a blow-out cover
forming the lower contour of the aircraft in the area of the
cavity.
In the event of impending danger, the container may be ejected by
firing support thrusters. If the container explodes while secured
to the aircraft, the blow-out cover vents the majority of the
concussion and debris away from the aircraft.
Having described the invention in connection with certain specific
embodiments thereof, it is to be understood that further
modifications may now suggest themselves to those skilled in the
art and it is intended to cover such modifications as fall within
the scope of the appended claims.
* * * * *