U.S. patent number 3,659,424 [Application Number 05/078,771] was granted by the patent office on 1972-05-02 for stowable air scoop.
This patent grant is currently assigned to The United States of America as represented by the Secretary of the Navy. Invention is credited to Albert S. Polk, Jr..
United States Patent |
3,659,424 |
Polk, Jr. |
May 2, 1972 |
STOWABLE AIR SCOOP
Abstract
A foldable ram air scoop for gathering and channeling external
air into a condary thrust chamber, or afterburner, of an
air-augmented thrust propelled missile is provided. The scoop is
deployable prior to launch, being foldable against the missile body
while stowed within a volume restricted storage magazine. The
present air scoop essentially comprises a two-stage folding
mechanism which compactly holds the scoop body against the missile,
controllably deploys the scoop to a desired configuration, and
positively locks the scoop in the proper position.
Inventors: |
Polk, Jr.; Albert S.
(Baltimore, MD) |
Assignee: |
The United States of America as
represented by the Secretary of the Navy (N/A)
|
Family
ID: |
22146115 |
Appl.
No.: |
05/078,771 |
Filed: |
October 7, 1970 |
Current U.S.
Class: |
60/269; 137/15.1;
60/245; 244/53B |
Current CPC
Class: |
F02K
7/10 (20130101); B64D 33/02 (20130101); F02C
7/042 (20130101); Y10T 137/0536 (20150401) |
Current International
Class: |
B64D
33/02 (20060101); B64D 33/00 (20060101); F02C
7/04 (20060101); F02C 7/042 (20060101); F02K
7/00 (20060101); F02K 7/10 (20060101); F02k
009/06 () |
Field of
Search: |
;60/270,269,245,244,35.6L,35.6PP ;137/15.1,15.2 ;244/327
;107/49.3,49.4 ;244/53B,129D |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Hart; Douglas
Assistant Examiner: Olsen; Warren
Claims
I claim:
1. In an aerial vehicle having a combustion chamber, an air scoop
comprising;
an inlet wall,
a movable ramp mounted to cooperate with the inlet wall,
a scoop body,
means slidably connecting the scoop body to the vehicle,
said air scoop being movable from an inoperative position lying
adjacent the vehicle to an operative position extending from the
vehicle,
said scoop body, said ramp and said inlet wall cooperating to
define an air inlet for directing air into the combustion chamber
when the scoop is in operative position, and
means for locking the scoop in extended position.
2. The invention recited in claim 1 and further including a blowout
door at the inner end of the inlet wall.
3. The invention recited in claim 1,
including additionally a leading edge element hingedly connected to
the scoop body.
4. The invention as recited in claim 1,
wherein the means for slidably connecting the scoop body with the
vehicle comprises sheaths formed in the vehicle body at each side
of the inlet wall,
and guides on the scoop body and slidable in the sheaths.
5. The invention as recited in claim 4,
including means for engaging the ramp for moving the ramp into
alignment with the inlet wall as the scoop is moved to operative
position.
6. The invention as recited in claim 5,
wherein said ramp moving means includes a groove on the rear end of
the ramp, said groove defining a rolled portion and a lip, and an
open ended slot in each of the guides near its rear end, said slots
receiving said rolled portion therein.
7. The invention as recited in claim 1,
wherein the scoop body comprises a leading edge element and a body
plate hingedly connected to the leading edge element,
said scoop body lying with a portion of said leading edge element
in engagement with said ramp when the scoop is in inoperative
position, thus providing a smooth aerodynamic surface for said
scoop.
8. The invention as recited in claim 1,
wherein the locking means comprises tracks on the vehicle and
having grooves terminating at corresponding forward ends in locking
ports,
locking elements carried by the scoop and having portions movable
from the grooves into the locking ports,
and springs on the elements and cooperating with a wall of each of
the grooves for moving said elements out of alignment with said
grooves, whereby said scoop will be prevented from moving into
inoperative position.
9. The invention as recited in claim 1,
wherein the locking means comprises tracks on the vehicle and
having said grooves terminating at corresponding forward ends in
locking ports,
side members on the scoop body and having openings,
locking discs in the openings and having locking elements extending
into the grooves,
and springs on the locking elements,
said locking elements being slidably from the grooves into the
locking ports when the scoop is moved fully forward and
outward,
said springs cooperating with corresponding walls of the grooves
for moving the elements out of alignment with said grooves.
10. The invention as recited in claim 5,
wherein the ramp engaging means comprises a spring on the vehicle
and engaging said ramp.
Description
BACKGROUND AND SUMMARY OF THE INVENTION
Air capture and ducting mechanisms for supplying external air to a
ramjet engine have previously been used. Generally, the air
supplied from the environment of the vehicle being propelled by the
ramjet engine burns with fuel in a combustion chamber used
previously as a fuel chamber for booster burn. The air scoop itself
must be large enough to accommodate a desired volume of air, yet
must have sufficient structural integrity to withstand the high
loading imposed on the relatively non-aerodynamic projection
extending from the aerodynamic body surface of the vehicle. Often
it is required that these air-breathing missiles be packaged within
and often launched from a volume restricted chamber. Presently,
thrust augmentation development is primarily directed toward
achievement of greater thrust per unit of either launcher volume,
magazine storage volume, or both. An integral rocket-ramjet vehicle
which necessitates the intake of large quantities of air for
internal combustion provides one solution to the present problem.
Although useful in other applications and missile configurations,
the invention is conveniently applied to the integral rocket-ramjet
vehicle. This vehicle is launched and accelerated by a solid fuel
booster having a fuel chamber which, after burnout and some parts
jettison, becomes a combustion chamber for fuel supplied from a
liquid fuel chamber. Air scoops structured according to the present
invention are disposed on the external surface of the vehicle body
substantially along that portion covering the liquid fuel chamber.
In order to be stowable within a volume restricted storage
magazine, the air scoops must be retractable against and/or within
the vehicle body. On exit from the storage magazine and prior to
launch, the air scoops are deployed in a desired configuration and,
after solid fuel burnout, gather and channel external air through
ducts communicating into the chamber which now functions as a
combustion chamber. Therefore, the principal object of the present
invention is to provide a foldable air scoop which is readily
deployable from a retracted position to an optimum extended
position and which, on assumption of such extended position,
positively locks in place.
Use of the present air scoop mechanism is not limited to the
integral rocket-ramjet briefly described above. For example, an
air-augmented afterburning combustion engine may conveniently
employ the invention to introduce externally-gathered oxidizing air
into a secondary combustion chamber for more complete oxidation of
fuel-rich exhaust gases exiting a primary combustion chamber. In
such instance, the fuel-rich, partially unoxidized gases entering
the secondary combustion, or afterburning, chamber are oxidized by
the air and subsequently ejected from the secondary combustion
chamber with increased specific impulse. In general, the invention
is useful in any known situation requiring external gathering and
channeling of air into a connection chamber for oxidative reaction
therein.
BRIEF DESCRIPTION OF THE DRAWINGS
FIG. 1 is a side elevation of an integral rocket-ramjet missile
employing the foldable air scoop mechanism of the present
invention, said mechanism being shown extended;
FIG. 2 is an exploded perspective, in partial section, of the air
scoop and associated structure within the missile body;
FIG. 2a is an enlarged detail side elevation of the stop mechanism
for the scoop body employed;
FIG. 2b is an enlarged detail perspective, partly in section,
showing one of the locking elements for the scoop body, together
with its associated spring and groove;
FIG. 3 is an enlarged detail section of a portion of the integral
rocket-ramjet missile and showing the air scoop in its stowed
configuration;
FIG. 4 is a view similar to FIG. 3 but showing the scoop in erected
flight configuration;
FIG. 5 is a detail perspective of the locking mechanism for
securing the scoop in extended position;
FIG. 6 is a top plan view of the ramp employed;
FIG. 7 is a side elevation of the ramp shown in FIG. 6; and
FIG. 8 is a transverse section on the line 8--8 of FIG. 7.
DESCRIPTION OF THE PREFERRED EMBODIMENTS
The invention is best described in an operative environment aboard
a particular missile with which the invention has utility. Such a
missile is shown generally at 10 in FIG. 1. The missile 10 is an
airbreathing two-stage vehicle, launched and accelerated by an
integral solid booster section 12, having a fuel chamber 14 which,
on solid fuel burnout, becomes a combustion chamber for sustained
ramjet flight. A liquid fuel chamber 16 disposed immediately
forward of the chamber 14 provides fuel for ramjet flight, while
air scoops 18 constructed according to the present invention
capture external air and direct said air into the chamber 14 for
combustion of the incoming liquid fuel.
The particular advantage of the present air scoops 18 derives from
the necessity of folding said scoops into a low-profile storage
configuration. Often, missiles are stowed prior to launch in
storage magazines offering limited volume. In order to stow the
missile 10 within the most efficient storage volume, external
missile appendages, such as fins and said air scoops, must be made
to be retractable against the body of the missile. Thus, when the
missile 10 is removed from a storage magazine and while it is being
readied for launch, the air scoops 18 are deployed in flight
positions, in a manner to be described hereinafter. If the missile
is not launched and is to be re-stored, the air scoops 18 are
retracted to their stowed positions.
Referring to FIGS. 1 and 2, the several component parts of each
scoop 18 are shown. The missile 10 is seen to be fitted with two of
the scoops 18, one each on diametrically opposite sides of said
missile and on the missile body substantially between the chambers
14 and 16. Each scoop 18 mainly comprises a leading edge element
22, a scoop body 24, and a ramp 26, these components being shown in
an exploded view in FIG. 2 so that the scoop may be more easily
described and understood. The leading edge element 22 is hinged to
the scoop body 24 by a hinge pin 28. This hinged assembly
substantially overlies an air inlet 30 which is defined by a
missile body extension 32, a stationary inlet wall 34, a blowout
door 36, and portions of the body of the missile. The leading edge
element 22 consists of an essentially rectangular plate 38 which
tapers in thickness to an edge 39.
Guides 40 extend angularly downwardly from the rear of the plate 38
at each side thereof and, when the scoop is in the stowed position,
fit into sheaths 42 formed in the body of the missile 10 on either
side of and immediately below the inlet wall 34. The guides 40 each
have a camming surface 44 of rounded contour which communicates
with an open ended slot 46. The guides 40 terminate in pointed end
portions 48 which, at full scoop deployment, extend partially into
the sheaths 42.
Referring also to FIG. 3, the ramp 26 is connected by a hinge pin
50 to a top wall 52 of the fuel chamber 16 and is shaped to
maximize fuel storage volume. The ramp 26 consists of a forward
portion 54 which is relatively gently inclined upwardly and a rear
portion 56 which is inclined relatively sharply downwardly, the
portions 54 and 56 merging at 55. As best seen in FIGS. 2, 4 and 7,
the under side of the rear portion 56 of the ramp 26 is provided
with a stop 57 which has a groove 58 and a lip 59, the stop 57
extending laterally a short distance beyond the side walls of the
ramp 26. A leaf spring 60, fastened to the under side of the ramp
26, bears against the top wall 52 to bias said ramp upwardly when
externally applied forces which tend to hold the ramp down are
lessened. In the stowed position shown in FIG. 3, the front surface
portion 54 of the ramp 26 is seen to lie substantially parallel to
the body of the missile 10.
The scoop body 24, shown best in FIG. 2, performs the major portion
of the air-gathering function of the air scoop 18. The body 24
consists of an inverted U-shape, rectangular body plate 62 having
two side members 63, the body acting as an air-collecting chamber.
The side members 63 gradually increase in height from the hinged
connection of the body 24 with the leading edge element 22, and at
such an angle that the upper edges of the guides 40 of the element
22 will fit flush against the lower edges of said members. The side
members 63 are cut away at 64 and terminate in tapered edge
portions 65. Formed in each of the side members 63 near its outer
end is an opening 66. The scoop body 24 lies substantially parallel
to the missile 10 when the scoop 18 is in the retracted, or stowed,
configuration shown in FIG. 3. In the flight configuration, shown
in FIG. 4, the scoop body 24 is angularly disposed to the missile
10, the sliding edge portions 65 of the side members 63 engaging
the body of the missile.
As can be seen in FIGS. 2b, 4, and 5, the scoop body 24 is slidable
in external tracks 68 which have open longitudinal grooves 69 in
the opposite walls thereof. Each groove 69 terminates at its
forward end in a circular locking port 70 of a diameter greater
than the width of said groove, said port 70 extending through said
track. Spring-loaded locking discs 71 are received within the
circular locking ports 70, as will be explained hereinbelow. The
disc 71 has a circular base 72 and a raised generally rectangular
locking element 73 thereon. The locking element 73 extends
diametrically of the base and is formed with a slot 74 in which is
secured the forward end of a leaf spring 75. As best seen in FIG.
5, the rear end portion of the spring 75 bears against the upper
wall of the groove 69. The base 72 of each locking disc 71 fits
into one of the openings 66 on each side of the scoop body 24. The
locking elements 73 extend from the base 72 and slide in the
grooves 69 in the external tracks 68. The scoop body 24 is thus
mounted for sliding movement along a fixed path. Movement of the
body 24 to a forward, erect position, such as is shown in FIG. 4,
causes the locking elements 73 of the discs 71 to exit the grooves
69 and extend into the circular locking ports 70. The locking discs
71 are caused to rock on release of the locking elements from the
grooves 69, by the action of the springs 75, to such positions that
said locking elements will be mis-aligned with respect to the
grooves. Thus, the discs and locking elements prevent the scoop
body 24 from sliding aft to its retracted configuration.
In FIG. 3, the air scoop 18 is seen in a low-profile, retracted
position. The leading edge element 22, scoop body 24, and ramp 26
are seen to lie substantially parallel to and against the body of
the missile 10. The ramp 26 is held downwardly by the camming
action of the forward portions of the guides 40. The guides 40 of
the edge element 22 are substantially received within the sheaths
42. The scoop body 24 lies substantially flat against the missile,
the locking elements 73 of the locking discs 71 engaging the
grooves 69 of the tracks 68 at the points of greatest distance from
the circular locking ports 70, i.e., near the outer ends of the
grooves.
Erection of each of the air scoop 18 is achieved by an actuator
(not shown), such as a pneumatic jack located on the body of the
missile. The actuator exerts force on the aft end of the scoop body
24 to move the scoop 18 into the deployed configuration shown in
FIG. 4. Deployment of the scoop 18 substantially involves sliding
the scoop body 24 forwardly, the sliding edge portions 65 of the
side members 63 slidably engaging the body surface of the missile
10. Force is thereby exerted on the leading edge element 22. The
scoop body 24 is forced outwardly from the missile body by the
camming action of the guides 40 on a rolled portion 76 located on
the stop 57 on the ramp 26. The locking discs 71 in the openings 66
in the scoop body 24 rotate to allow said body to move forwardly
and outwardly and maintain sliding alignment of the locking
elements 73 of said discs 71 within the grooves 69 in the tracks
68. As the scoop body 24 slides forwardly and outwardly, the
leading edge element 22 also moves forwardly and outwardly as the
guides 40 are drawn from the sheaths 42. However, due to the angle
at which the sheaths 42 are disposed in the body of the missile,
the body plate 62 of the leading edge element 22 maintains
substantially parallel alignment with the missile body by partially
rotating on the hinge pin 28. Continuing forward movement of the
scoop body 24 eventually brings the rear edges of the guides 40
into contact with said scoop body, thus forming continuous side
walls for the air scoop 18.
As the scoop body 24 reaches the point of maximum forward
displacement, the camming surfaces 44 on the guides 40 allow the
ramp 26 to be biased outwardly by the spring 60. As the ramp 26
moves outwardly about the hinge pin 50, the guides 40 engage the
stop 57 with the rolled portion 76 in the slots 46. The
interconnection between the ramp 26 and the guides 40 of the
leading edge element 22 provides, along with the locking discs 71
which lock into the circular locking ports 70 substantially
simultaneously with the occurrence of the interlocking just
described, positive locking of the air scoop 18 in an erect, air
scooping position. In this erect position, the rear portion 56 of
the ramp 26 is seen to align with the inlet wall 34 .
* * * * *