Aerial photography camera mount assembly for a helicopter

An assembly for mounting, supporting, and releasably holding an angularly adjustable aerial photography camera that is to be used to take aerial reconnaissance photographs, while the assembly is detachably connected to the internal surface of a helicopter that is in stable flight and has an opening in each side. The assembly includes: a rectangular frame which carries the camera; another rectangular frame which carries ballast (i.e., a counterweight); and, a main frame to which the rectangular frames are releasably connected, and in which the frames are slidably movable in opposite directions simultaneously. In flight, the rectangular frames are simultaneously extended on each side of the center of gravity, and of the longitudinal centerline, of the helicopter, and through the opposite openings in the helicopter, with the camera extending out of one of the openings, and with the counterweight extending out of the other opening. This symmetrical loading, and the resultant continued stability of the helicopter in flight, permit the taking of the aerial photographs with the camera.

CROSS REFERENCE TO RELATED APPLICATION 
The inventive camera mount assembly taught herein is related in general 
subject matter to U.S. Pat. No. 4,114,839, filed on Aug. 19, 1977, and 
entitled "Aerial Photograph Camera Mount," in that one of the assemblies 
described therein to hold an aerial photograph camera in an oblique 
position can be utilized, or can be adapted to be utilized, in this camera 
mount assembly. 
BACKGROUND OF THE INVENTION 
This invention relates generally to aerial photography and more 
particularly, to a novel assembly which permits the taking of aerial 
(reconnaissance) photographs from a helicopter in flight. 
In aerial photographs of the type needed in reconnaissance, aerial 
photography cameras are mounted in the aircraft on mounts that are fixedly 
positioned in predetermined locations in the aircraft to provide maximum 
coverage of the ground below. In this regard, it is fair and accurate to 
say that aerial photography aircraft are built primarily to accomplish 
aerial photography, or are extensively modified to accomplish that 
purpose, with the "trade-off" resulting in a significant lessening of the 
capability to perform the functions for which the aircraft was built 
originally. 
In the military establishment an urgent need has arisen to use a helicopter 
(i.e., the UH-1N) to take high quality aerial reconnaissance photographs, 
without adversely affecting the other mission capabilities of the 
helicopter, and without "missionizing" the helicopter by extensive 
modifications, and most importantly, without adversely affecting the 
sensitive stability of the helicopter in flight. 
We have invented a unique aerial photography camera mount assembly that 
fulfills this need; and, thereby, we have significantly advanced the 
state-of-the-art. 
SUMMARY OF THE INVENTION 
This invention pertains to a novel aerial photography camera mount 
assembly, adapted for use in taking aerial reconnaissance photographs with 
an aerial photograph camera extending from a helicopter having a starboard 
side with an opening therein, a port side with an opening therein, a 
horizontal planar internal surface located between these openings, a 
plurality of tiedown rings affixed to this horizontal internal surface, 
and a center of gravity located within this horizontal internal surface 
and having a longitudinal axis and a transverse axis that intersect, are 
perpendicular to each other, and are coplanar with the horizontal internal 
surface, and with this transverse axis situated between and aligned with 
the starboard and port side openings. 
Accordingly, the principal object of this invention is to teach the 
structure of such a unique aerial photography camera mount assembly for a 
helicopter. 
This principal object, as well as other related objects, of this invention 
will become readily apparent after a consideration of the description of 
the invention, together with reference to the Figures of the drawings.

DESCRIPTION OF THE PREFERRED EMBODIMENT 
As a preliminary matter, and with reference to Figures 1-3, inclusive, 
therein are shown various and diverse views of the helicopter 11 with 
which our inventive aerial photography camera mount assembly 20 is to be 
used. More specifically, the helicopter 11 has a starboard (i.e., right) 
side 12 with and opening 12A therein, a port (i.e., left) side 13 with an 
opening 13A therein, a planar horizontal internal surface, generally 
designated 14 and indicated by phantom lines, therein located between the 
openings 12A and 13A, a first plurality of cargo tiedown rings, such as 
15A, 15B, 15C, 15D, 15E, 15F, 15G, and 15H, that are affixed to this 
horizontal portion 14, and a center of gravity, designated "CG," that is 
location in portion 14 and that has a longitudinal (i.e., horizontal) 
axis, designated "A-B" and a transverse axis, designated "C-D." These 
axes, "A-B" and "C-D" intersect at "CG"). The axes also are perpendicular 
to each other; and, are coplanar with each other and with horizontal 
internal surface 14. Additionally, transverse axis "C-D" is situated 
between, and is aligned with, the starboard and port side openings 12A and 
13A. 
It is here to be noted that our assembly is, of course, also to be used 
with an aerial photography camera (not shown here, but to be shown later) 
that is loaded with film, and that both the camera and the film have 
weight. Accordingly, the term "camera" as used herein is intended to means 
such a camera, as is described above, that is loaded with the appropriate 
film. 
With reference to FIGS. 4 and 5 therein are shown side elevation views of a 
preferred embodiment 20 of our invention in, respectively, the retracted 
position and fully extended position. 
In its most basic and generic form, our invention 20, comprises: a first 
means, generally designated 30, for mounting, supporting, and releasably 
holding an aerial photography camera (such as is designated 90) in an 
angularly adjustable position, with of course this first means 30 having 
weight, and the camera 90 (i.e., as previously defined herein, the camera 
and the appropriate film (not shown) with which it is loaded) also having 
weight; a second means, generally designated 40 and operatively associated 
with the first means 30, for counterbalancing the combined weight of the 
fist means 30 and of the film-loaded camera 90 that is mounted, supported, 
and releasably held by the first means 30; a third means, generally 
designated 50 and operatively associated with the first means 20 and the 
second means 30, for removably holding the first and second means in 
parallel, equal spaced-apart relationship, and for detachably 
interconnecting the first and second means, and also for slidably moving 
simultaneously the first and second means in diametrically opposed (i.e., 
opposite) directions, with this third means 50 positioned on the 
horizontal internal surface 14, FIGS. 2 and 3, of the helicopter 11, and 
also centrally located oer the center of gravity "CG," FIG. 3, and the 
intersection "E," FIG. 3, of the transverse axis "C-D" and the 
longitudinal axis "A-B," and additionally releasably attached to some of 
the first plurality of cargo tiedown rings, such as 15A-15H, inclusive, 
FIG. 3; and, a fourth means, generally designated 80 and that is 
releasably connected to the third means 40 and also is in selective 
cooperative engagement with the first means 30 and the second means 40, 
for preventing inadvertent jettisoning of the first means 30, of the 
film-loaded camera 90 releasably held by the first means 30, and of the 
third means 40, from the helicopter 11. 
Now, with reference to FIGS. 6A and 6B, shown therein are various views of 
the first means 30 for mounting, supporting, and releasably holding the 
film-loaded camera 80 in an angularly adjustable position. This means 30 
includes a first subassembly 31 which comprises: a first frame member 32, 
essentially rectangular in shape, having a first end 32A and a second end 
32B and, of course, weight; a box section, generally designated 33, 
hingedly attached to the first frame member 32, near the first end 32A of 
it 32; and, a fifth means 34, adjacent to the box section 33 and attached 
to the first frame member 32 at the first end 32A, for selectively varying 
the angularity of the film-loaded camera 70 in relation to the first frame 
member 32. 
With reference to FIGS. 7A, 7B and 7C, therein is shown the second means 40 
for counterbalancing the weight of the first means 30 and the weight of 
the film-loaded camera 80 that is releasably held by the first means 30. 
This means 40 includes a second subassembly 41 which comprises: a second 
frame member 42, essentially rectangular in shape, having weight, a first 
end 42A, and a second end 42B, with this second frame member positioned in 
parallel, equal-spaced-apart relationship to the first frame member 32 of 
the first subassembly 31, as shown in FIGS. 4 and 5; and, a counterweight 
43 attached to the second frame member 42 at the second end 42B. The 
combined weight of this second means 40 equals the combined weight of the 
first means 30 and of the camera 90 releasably mounted on it 30. 
Now, with reference to FIGS. 8A, 8B and 8C, therein are shown various views 
of the third means 50 for removably holding the first means 30 and the 
second means 40 in parallel, equal spaced-apart relationship, and for 
detachably interconnecting the first means 30 and the second means 40, and 
also for slidably moving simultaneously the first means 30 and the second 
means 40 in diametrically opposed (i.e., opposite) directions. This means 
50 includes a third subassembly 51 which comprises: a third member 52, 
essentially box-like in shape and hollow, having a front vertical surface 
52A, a lower horizontal surface 52B connected to the front vertical 
surface 52A, a rear vertical surface 52C parallel to the front vertical 
surface 52A and connected to the lower horizontal surface 52B, an upper 
horizontal surface 52D parallel to the lower horizontal surface 52B and 
connected to the rear vertical surface 52C and to the front vertical 
surface 52A, an open first end 52E, and an open second end 52F; a first 
transverse horizontal support member 53 attached to and extending beyond 
the front vertical surface 52A of the third frame member 52, with this 
support member 53 having a first end 53A and a second end 53B; a first and 
a second transverse horizontal guide members, 54 and 55, that are 
positioned, respectively, above and below the first transverse horizontal 
support member 53, and are attached to the front vertical surface 52A of 
the third frame member 52, with these horizontal guide members 54 and 55 
parallel to, and equally spaced-apart from, the first transverse 
horizontal support member 53; a second transverse horizontal support 
member 56 attached to and extending beyond the rear vertical surface 52C 
of the third frame member 52, with this support member having a first end 
56A and a second end 56B; a third and a fourth transverse horizontal guide 
members 57 and 58 positioned, respectively, above and below the second 
transverse horizontal support member 56, and attached to the rear vertical 
surface 52C of the third frame member 52, with the third and fourth 
transverse horizontal guide members 57 and 58 parallel to, and equally 
spaced-apart from, the second transverse horizontal support member 56; an 
upper sprocket 61 rotatably attached to the upper horizontal surface 54D 
of the third frame member 52; a lower sprocket 62 rotatably attached to 
the front vertical surface 52A of the third frame member 52; an endless 
chain 63 in engagement with the upper and lower sprockets 61 and 62; a 
crank handle 64 rotatably connected to the upper sprocket 61; a driven 
shaft 65 having a first and a second end 65A and 65B, with the first end 
65A rotatably connected to the lower sprocket 62, and with the second end 
65B rotatably connected to the rear vertical surface 52C of the third 
frame member 52; a first idler shaft 66 having a first end 66A, a second 
end 66B, and a first idler pulley 66C on the shaft 66 and located between 
the first and second ends 66A and 66B, with the first end 66A rotatably 
connected to the first end 53A of the first transverse horizontal support 
member 53, and with the second end 66B rotatably connected to the first 
end 56A of the second transverse horizontal support member 56; and, a 
second idler shaft 67 having a first end 67A, a second end 67B, and a 
second idler pulley 67C on the shaft 67 and located between the first and 
second ends 67A and 67B, with the first end 67A rotatably connected to the 
second end 53B of the first transverse horizontal support member 53, and 
with the second end 67B rotatably connected to the second end 56B of the 
second transverse horizontal support member. 
As shown in FIGS. 4 and 10B, the third subassembly 51 of third means 50 
further comprises: a first cable means 68 interconnecting the driven shaft 
65, the first idler pulley 66C on first idler shaft 66, and the second end 
32B of the first frame member 32 of the first subassembly 31; and, a 
second cable means 69 interconnecting the driven shaft 65, the second 
idler pulley 67C and the first end 42A of the second frame member 42 of 
the second subassembly 41. 
With reference to FIGS. 9A and 9B in conjunction with reference to FIGS. 
8A, 8B and 8C, the third subassembly 51 of the third means 50 also further 
comprises: a first plurality of roller bars, such as 71, 72 and 73, 
attached in a vertical position to the front vertical surface 52A of the 
third frame member 52, and internal of that surface 52A with each one of 
the roller bars of this plurality, such as the representative one in FIGS. 
9A and 9B, being identical and comprising two spaced-apart, horizontally 
disposed rollers, such as 71A and 71B, rotatably attached to a bar, such 
as 71C, with at least one of the bars, preferably the center disposed bar 
(such as 72C) being in an inverted condition, with this plurality of 
roller bars also including rollers 72A and 72B and bar 72C, and rollers 
73A and 73B and bar 73C; a second plurality of roller bars, such as 74, 75 
and 76, attached in a vertical position to the rear vertical surface 52C 
of the third frame member 52, and internal of that surface 52C, with each 
one of the second plurality of roller bars 74, 75 and 76 identical to each 
one of the first plurality of roller bars 71, 72 and 73, and with at least 
one of the second plurality of bars, preferably the center disposed bar 
(preferably 75C) being in an inverted condition, with this plurality of 
roller bars also including rollers 74A and 74B and bar 74C, rollers 75A 
and 75B and bar 75C, and rollers 76A and 76B and bar 76C; a first roller 
support means 77 (see also FIG. 5) attached to and disposed above the 
first end 53A of the first transverse horizontal support member 53, and 
also dipsosed under first frame member 32; and, a second roller support 
means 78 (see also FIG. 5) attached to and disposed below second end 53B 
of the first transverse horizontal support member 53, and also disposed 
under second frame member 42. 
Now, with reference to FIGS. 10A and 10B, therein are shown various views 
of the fourth means 80 for preventing inadvertent jettisoning of the first 
means 30, and of the film-loaded camera 90 that is releasably held by the 
first means 30, and also of the second means 40 from the helicopter 11. 
This means 80 (also shown in FIGS. 4, 5, 8A and 8B) includes a fourth 
subassembly 81 which comprises: a locking rod 82 having a first end 82A, a 
second end 82B, an opening 82C in and through the first end 82A, with the 
rod 82 positioned vertically and passing through the upper horizontal 
surface 52D of the third frame member 52, and passing through the first 
frame member 32, near the second end 32B of that member 32, and also 
passing through the second frame member 42, near the first end 42A of that 
member 42; and, a sixth means 83 for releasably locking the locking rod 82 
in place, with this means 83 including: an abutment bar 83A, attached to 
the upper horizontal surface 52D of the third frame member 52, that has an 
opening 83B (in and through the bar 83A) which is in registration with the 
opening 82C in and through the first end 82A of the locking rod 82; and, a 
locking pin 83C that is removably inserted into, and passes through, the 
opening 82C in the locking rod 82 and the opening 83C in the abutment bar 
83A. 
Returning to FIG. 3, therein is shown a seventh means, generally designated 
84, for releasably attaching the third means 50 to some of the first 
plurality of cargo rings (such as 15A-15H, inclusive) that are affixed to 
the horizontal internal surface 14 of the helicopter 11. This means 84 
includes: a second plurality of cargo tiedown rings, such as 85A and 85B, 
FIGS. 3, 4, 5 and 8A, affixed to the front vertical surface 52A of the 
third frame member 52 of the third means 50; a third plurality of cargo 
tiedown rings, such as 86A and 86B, that are affixed to the rear vertical 
surface 52C of the third frame member 52 of the third means 50; a first 
cargo tiedown strap 87, of predetermined length and passing through the 
second plurality of cargo tiedown rings 85A and 85B, having a first end 
87A and a second end 87B, with the first end 87A releasably connected to 
one of the first plurality of cargo tiedown rings, such as 15D, and with 
the second end 87B releasably connected to another one of the first 
plurality of cargo tiedown rings, such as 15A; and, a second cargo tiedown 
strap 88, of predetermined length and passing through the third plurality 
of cargo tiedown rings 86A and 86B, having a first end 88A and a second 
end 88B, with the first end 88A releasably connected to one of the first 
end 88A releasably connected to one of the first plurality of cargo 
tiedown rings, such as 15E, and with the second end 88B releasably 
connected to another one of the first plurality of cargo tiedown rings, 
such as 15H. 
As a matter of preference, and not of limitation, the first subassembly 31 
of the first means 30, the second subassembly 41 of the second means 40, 
the third subassembly 51 of the third means 50, the fourth subassembly 81 
of the fourth means 80, and the third and fourth plurality of cargo 
tiedown rings (such as, respectively, 85A and 85B, and 86A and 86B) of the 
seventh 84 means are all made of metal. 
Additionally, also as matters of preference, and not of limitation: the 
first plurality of roller bars (such as 71, 72 and 73, FIGS. 8A and 8B) 
and three in number; the second plurality of roller bars (such as 74, 75 
and 76, FIG. 8B) are also three in number; the second plurality of cargo 
tiedown rings (such as 85A and 85B, FIGS. 3, 4, 5 and 8A) are two in 
number; and, the third plurality of cargo tiedown rings (such as 86A and 
86B) are also two in number. 
MANNER OF OPERATION OF THE PREFERRED EMBODIMENT 
The manner of operation of the preferred embodiment 20 of our invention can 
be very easily ascertained by any person of ordinary skill in the art from 
the foregoing detailed description, coupled with reference to the Figures 
of the drawings. 
For others, it is sufficient to say that, when it is desired to take an 
aerial photograph (either vertical or oblique) by using our invention 20 
in the described helicopter 11 when it is in flight, the camera 90 is 
properly set angularly; the starboard and port side doors, if any, of the 
helicopter 11 are opened, exposing the starboard opening 12A and the port 
opening 13; the crank 64, FIGS. 4, 5, 8A and 8B is appropriately turned, 
resulting in the simultaneous deployment of the first means 30 (with 
camera 90), and of the second means 40 (with the counterweight or ballast 
43), to opposite sides of the center of gravity "CG," FIG. 3, and of the 
longitudinal axis "A-B" of the helicopter 11, thereby maintaining 
symmetrical loading and stability of the helicopter 11 in flight. To 
prevent the inadvertent jettisoning of the first and second means 30 and 
40 from the helicopter 11, the fourth means 80 is used, i.e., the locking 
rod 82 is passed through the third frame member 52, and through the 
extended first frame member 32 and the extended second frame member 42, 
where these members 32 and 42 overlap, and the locking pin 83C is inserted 
into and through the rod 82 and the abutment bar 83A. The photograph(s) is 
(are) taken, as necessary or as desired. When the taking of the 
photograph(s) is completed, the above-described procedure is reversed. 
CONCLUSION 
It is abundantly clear from all of the foregoing, and from the Figures of 
the drawings, that the stated principal object, as well as other related 
objects, of our invention have been achieved. 
It is to be noted that, although there have been described the fundamental 
and unique features of our invention as applied to a preferred embodiment, 
various other embodiments, variations, adaptations, substitutions, 
additions, omissions, and the like may occur to, and can be made by, those 
of ordinary skill in the art, without departing from the spirit of our 
invention. For example, four cargo tiedown straps, rather than two, may be 
used to releasably attach the third frame member 52 of third means 50 to 
the internal surface 14 of the helicopter 11, as shown in phantom in FIG. 
3.