Abstract:
An adjustable mounting apparatus for carrying a camera or other sensor in a small helicopter or other moving platform and isolating the camera from vibration without modification of the aircraft or other platform, and a method for using a sensor such as a camera in a small aircraft or other moving platform operated by a single person. A base portion of the apparatus is carried on a cushioned seat, and a universally adjustable mast is carried on the base in a selected position with respect to the platform and isolated from the base by an elastomeric cushion to eliminate vibration. A camera or other sensor is carried on a servo-controlled attachment fixture fastened to the top of the mast, and a video monitor is located in view of the aircraft operator. Servo-controls for adjusting and operating the camera or other sensor are located in reach of the aircraft operator. A cart is used for storage and to support the mast during installation or removal of the base.

Description:
BACKGROUND OF THE INVENTION 
     The present invention relates to an adjustable sensor supporting and mounting apparatus for carrying a sensor such as a video camera or infra-red sensing device in an aircraft or other moving platform, reducing or eliminating vibration of the platform as experienced by the sensor, and which allows the direction of the camera or other sensor to be controlled by the operator of the helicopter or other moving platform. 
     In certain situations, including firefighting, rescue, wildlife observation and trailing, and law enforcement operations it is desired to have quickly available airborne cameras and video transmitting equipment. This has previously required costly use of fairly large helicopters, for example. News gathering organizations wanting to obtain on-the-spot images of newsworthy events similarly have had to have both an aircraft pilot and a camera operator quickly available, with a helicopter large enough to carry two people plus the required camera equipment or other sensors and transmitting equipment. This requirement has limited the utility of smaller, less-expensive helicopters and non-dedicated, or multipurpose, helicopters and fixed wing aircraft as news-gathering vehicles and for the other sensor uses mentioned above. It has also required the availability of a cameraman in addition to a helicopter pilot, thus requiring the arrival of two people before departure of the aircraft toward the location of an event in progress. 
     Because of the need in the past for an aircraft with the ability to carry the weight of a camera operator or special camera mounting and stabilizing equipment it has been necessary for on-scene airborne photographers to use larger aircraft, with operating costs of several times the cost of operating popular small two-passenger helicopters. 
     Camera operators attempting to obtain video images or photographs of events taking place without externally mounted equipment are usually required to view the events through the side windows or doorway openings of aircraft, particularly helicopters, in order to obtain an unobstructed view, particularly for infrared cameras and sensors. The side door has the advantage of giving an unobstructed view to the side, allowing the aircraft to circle or hover keeping a target in view, but it may also be desired to use video equipment or cameras to photograph objects straight ahead or in other positions as well. Use of a hand-held camera inside a small aircraft for such views is often impractical because of limited cabin size. Also, use of hand-held video cameras may subject camera operators to motion sickness, even though the normal location of a passenger&#39;s seat in a small aircraft often provides an ideal viewpoint. 
     The additional weight of gyro stabilizing equipment for motion picture or video cameras may make use of such stabilizing equipment impractical in very small aircraft. Special mounts for carrying remotely controllable cameras externally of an aircraft&#39;s cabin are extremely expensive and may also be too heavy for use on small helicopters or other light aircraft. Such equipment, when installed, may also impair the availability of an aircraft for other desirable uses, such as for pilot training. Additionally, such devices may require approval of governmental agencies before they can be permanently mounted on any particular model of aircraft. 
     Vibration of a helicopter because of its rotors, or vibration of other aircraft or motor vehicles because of their engines or surfaces being traveled on, can be a problem in obtaining useful camera images. While gyroscopic image stabilization devices are available for some cameras, such devices are expensive and may not be capable of dealing with all of the vibration associated with operation of helicopter or other moving platform on which a camera or other sensor is carried. 
     Attention to some of the foregoing needs and problems has been noted in prior patents including Greenlee U.S. Pat. No. 4,621,786, McKay U.S. Pat. No. 4,685,649, Vasconi U.S. Pat. No. 5,876,005, Bothe, et al., U.S. Pat. No. 5,871,186, Meinel U.S. Pat. No. 5,769,369, Pinson U.S. Pat. No. 4,531,699, Leavitt U.S. Pat. No. 3,638,502, and U.K. Patent Application No. GB 2 161 668A, but those teachings have not provided entirely satisfactory solutions. 
     What is desired, then, is an improved apparatus and a method for its use for carrying a sensor such as a camera in a helicopter or automobile, or on another moving platform, and for enabling the camera or other sensor to be operated by the helicopter pilot or operator of such other vehicle. Such apparatus should be easily and quickly installed on or removed from a non-dedicated vehicle and easily adjusted to a desired or preferred position and orientation with respect to the helicopter or other platform. The apparatus should substantially isolate the camera or other sensor from vibrations of the helicopter or other platforms, without being unnecessarily complex. 
     Preferably, such a sensor supporting apparatus should be easily constructed and of modest cost and should not require structural modification of the helicopter or other platform in connection with its installation therein. 
     SUMMARY OF THE INVENTION 
     The present invention provides an answer to the aforementioned need for an improved way for an unaccompanied pilot or vehicle operator to safely operate one or more cameras in a mobile platform such as a small helicopter having a limited load carrying capacity, by providing a stable, vibration-limiting, and adjustable sensor-carrying apparatus. 
     Apparatus according to a preferred embodiment of the present invention includes a base having a first spherical mating surface. The base supports a mast including a second spherical mating surface, making the position of the mast thereby adjustable to a desired orientation with respect to the base. The apparatus also includes an elastomeric cushioning body located between the base and the mast, to isolate a camera or other sensor carried on the mast from undesirable vibration of a platform in or on which the apparatus is to be used. 
     According to one preferred embodiment of the apparatus according to the present invention the base defines a concave spherical mating surface and the elastomeric cushioning body is carried on the lower portion of the mast and defines a convex spherical mating surface. 
     The method of the present invention includes placing the base and adjusting the mast with respect to the base to a desired orientation, which may be established as a preset or initial position of the convex mating surface with respect to the concave mating surface, and then holding the mast in that orientation with respect to the base while cushioning the mast to isolate it from vibration imposed on the base by the helicopter or other platform. In one preferred orientation the mast is vertical during straight and level travel, and an attachment fixture attached to the mast allows a camera or other sensor carried thereon to be moved through an angle in a first plane about an axis that may be parallel with the mast, and also allows movement through an angle about an axis parallel with the first plane. 
     In a preferred embodiment the sensor supporting apparatus supports a sensor at a location within the aircraft where the camera lens or other sensor is located in a position comparable to that of the eyes of a person seated in the aircraft. 
     One embodiment of the method includes supporting the base on a cushioned passenger seat and by legs including cushioned feet, and also includes holding the mast in the desired orientation by adjusting flexible elongate tension-bearing members such as nylon straps, extending in separate directions between the mast and a part of the helicopter or other platform. 
     According to another aspect of the method of the present invention an image perceived by the camera or other sensor is disclosed in a location where it is available to a pilot of the helicopter or to the operator of another type of sensor-carrying platform. 
     According to a further aspect of the invention a carrying cart is provided to carry the base and also to support the mast separately with its mating surface on a mating surface of a carrier provided on the cart, so the sensor supporting apparatus can easily be installed in or removed from a helicopter or other mobile sensor-carrying platform. 
     It is a feature of the present invention that it provides an easily installed and functional, adjustable, sensor supporting device that does not require structural modification of an aircraft in which it is installed. 
     The foregoing and other objectives, features, and advantages of the invention will be more readily understood upon consideration of the following detailed description of the invention, taken in conjunction with the accompanying drawings. 
    
    
     BRIEF DESCRIPTION OF THE SEVERAL VIEWS OF THE DRAWINGS 
     FIG. 1 is a partially cutaway perspective view of a small helicopter equipped with a video camera and a still camera supported by the adjustable sensor supporting apparatus of the present invention, carried in a passenger seat the helicopter. 
     FIG. 2 is a perspective view, at an enlarged scale, of the passenger seat of the helicopter shown in FIG. 1, together with he adjustable sensor supporting apparatus and came shown in FIG.  1 . 
     FIG. 3 is a side elevational view of a portion of the helicopter, together with the adjustable sensor supporting apparatus d cameras shown in FIGS. 1 and 2, taken in the dire ion indicated by line  3 — 3  in FIG.  1 . 
     FIG. 4 is a top plan view of the base and a portion of the mast of the adjustable sensor supporting apparatus shown in FIG. 3, taken along line  4 — 4  of FIG.  3 . 
     FIG. 5 is a partially cutaway, partially exploded view of the portions of the adjustable sensor supporting apparatus shown in FIG. 4, taken in the direction indicated by the line  5 — 5  in FIG.  4 . 
     FIG. 6 is a view of the portion of the mast of the adjustable sensor supporting apparatus shown in FIGS. 4 and 5, in which the cushioning body portion of the mast is shown in section view taken along line  5 — 5  of FIG.  4 . 
     FIG. 7 is a side elevational view of a portion of the helicopter shown in FIG. 1, together with the base portion and the lower portion of the mast of the adjustable sensor supporting apparatus of the present invention, shown spaced apart from each other in order to illustrate the preferred manner of installation and adjustment of the adjustable sensor supporting apparatus of the invention 
     FIG. 8 is a side elevational view, at a further enlarged scale, of the motor driven, servo-controlled camera attachment fixture shown in FIGS. 1-3, carrying a video camera and a still camera, together with an upper portion of the mast. 
     FIG. 9 is a front elevational view of the camera attachment fixture shown in FIG. 8, partially exploded to show the manner of its attachment to the top of the mast. 
     FIG. 10 is a side elevational, partially exploded view of a many controllable camera attachment fixture an upper portion of the mast. 
     FIG. 11 is a perspective view of a portion of a helicopter and a cart used to carry the sensor supporting apparatus shown in FIGS. 1-3 during installation in or removal from an aircraft or other vehicle, and during storage of the apparatus. 
    
    
     DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS 
     Referring now to the drawings which form a part of the disclosure herein, in FIG. 1 a small two passenger helicopter  12  is shown equipped with an adjustable sensor supporting apparatus  14  embodying the present invention mounted on a passenger seat  16 . The supporting apparatus  14  supports a video camera  18  and a still camera  20  both mounted on a motor-driven servo-controlled carrier  22  by which the cameras can be pointed in a desired position relative to the helicopter  12 . A video monitor  24  provided with a signal from the video camera  18  is mounted inside the cabin of the helicopter  12  in a position from which it is visible easily to the pilot during in-flight use of the video camera  18 . 
     Referring now also to FIGS. 2 and 3, as the pilot sits normally in the right hand seat  26  in a currently popular helicopter, the adjustable sensor supporting apparatus  14 , the video camera  18  and still camera  20 , located in the passenger seat  16 , affords a view outward through the left hand side window, or doorway, or portion of a transparent canopy bubble, according to the structure of the particular helicopter, when the cameras are pointed as shown in FIGS. 1 and 2. The cameras  18  and  20  may instead be aimed forward of the aircraft as shown in FIG.  3 . 
     The camera carrier  22  may be controlled by the pilot by the use of a servo-control system. A control panel  28  including joysticks  30 ,  31 ,  32 , and  33  is therefore connected to perform various sensor control functions. For example, the joystick  30  may be used to zoom or change the effective focal length of the lens of the video camera  18  between various wide angle and telephoto settings. Joystick  31  may be used to control the speed of zooming. Joystick  32  may be used to control the speed of changing directional aim, and joystick  33  may be used to control the direction (pan and tilt) of the camera&#39;s aim. Controls may be provided similarly to operate the still camera  20 . 
     Several preset combinations of zoom (focal length) pan (azimuth) and tilt (elevation) are preferably programmed to be available to be selected individually by use of one or more control buttons  29  which may be provided on the control panel  28 . An additional combination of sensor and carrier settings may be accepted and memorized by the servo-control system with the camera carrier in a desired position by using an appropriate control such as a “set” button  34 , and that sensor position and condition can later be resumed by using an appropriate control such as a “recall” button  36 . 
     Alternatively, or additionally, similarly capable control switches for the servo system may be mounted on a cyclic control handle or flight control yoke (not shown) of the aircraft, with necessary wires attached securely but simply and removably by self-locking plastic wiring harness straps. In such a location, force control joysticks or similar thumb-tilt devices are preferably used instead of the joysticks  30 ,  31 ,  32 , and  33 . The functions of the speed control joysticks  31  and  32  may be included in a respective joystick or thumb pressure control switch, if desired, in such a control arrangement. Such control devices are available, for example, from Measurement Systems, Inc., of Fairfield, Conn. as Models 465, 467, 469, and 470 series miniature joysticks and thumb operated joysticks. 
     The adjustable sensor supporting apparatus  14  includes a base  40  that rests on the passenger seat  16  of the helicopter  12  as shown herein, supported by the cushion  42  on which a passenger would normally sit. A pair of front legs  44  and a pair of rear legs  46  are made of flat metal bars shaped generally as inverted “U”&#39;s and extend beneath the base  40  and thence downward toward the surface of the deck or floor  48  of the cabin of the helicopter  12  on opposite sides of the passenger seat  16 . The pairs of legs  44  and  46  are simply attached in shallow recesses provided in the bottom of the base  40 , as by bolts (not shown), and may be made in various easily interchangeable lengths and widths to fit various aircraft. 
     A foot  50  is attached to each of the legs  44  and  46  by an appropriate fastener such as a bolt and nut combination  52  which can be tightened appropriately in a required position in a respective slot  54 , provided in each leg  44  or  46 , as shown in FIG. 5, to fasten each foot  50  securely to the respective one of the legs  44  and  46 . Each foot  50  includes a cushion in the form of a boot  56  of an energy-absorbing elastomeric material such as a moldable plastic resin, for example a polyurethane material having a durometer hardness in the range of 60-80 on the A scale. One material which has been found satisfactory is a moldable polyurethane plastic resin material available from Evergreen Plastics, Inc., of Beaverton, Oreg., designated as EA2789, and which has a durometer hardness of 70±5 on the A scale. 
     The base  40  may be of any suitably strong and rigid material that is not unnecessarily heavy, including wood or various reinforced materials. A preferred construction, however, is a hollow base of coaxial rotationally molded plastic such as a polyethylene, with a wall thickness of about one quarter inch. 
     The control panel  28  is attached to the base  40  where it is available to the pilot of the aircraft from either side, so that it is immaterial whether the pilot is in the left seat or the right. The front of the base has angled faces  58  to avoid obstructing the pilot&#39;s movement of control yokes and levers. The face  58  on the side of the base  40  that is farther from the pilot may also serve as a place to mount other displays or items related to a particular camera or other sensor. 
     A mast  60  extends upward from the base  40  and is adjustable with respect to the base  40  as will be explained presently, in order to place the mast  60  in a desired orientation with respect to the helicopter  12  or another type of aircraft or other moving platform in connection with which the adjustable sensor supporting apparatus  14  is to be used in accordance with the invention. The mast  60  has a lower end portion  52  which is preferably massive. The lower portion  62  may, for example, be made of a thick-walled (e.g., schedule  40 ) steel pipe with a diameter of about 4 inches. The lower portion  62  also includes a base plate  64 , preferably a flat, circular plate of a substantial thickness, that may also be of steel, with a diameter 65 of about 11 inches and a thickness of about 0.75 inch, for example, and that is preferably welded to the lower end of the cylinder or thick-walled pipe. The upper end portion  66  of the mast may be of 2 inch×2 inch square tubing with ¼ inch wall thickness. 
     A flange  68  is mounted at the top of the upper end portion  66  of the mast  60 , to receive the camera carrier  22  or other sensor attachment fixture desired or required for the particular type of camera or other sensor being carried on the adjustable sensor supporting apparatus  14 . 
     Attached to the lower side of the base plate  64  is a cushioning body  70  of somewhat soft and resilient elastomeric material, and whose general shape is that of a minor segment of a sphere. The cushioning body  70  has a maximum thickness 71 of about 3 inches, in one embodiment of the invention, and has a minimum thickness, as at 75, of at least ½ inch and preferably about an inch. A central axis  72  of the mast  60  extends perpendicular to the center of the base plate  64 , and the cushioning body  70  is centered on and attached to the base plate  64  by bolts  74  located in cylindrical recesses  76  in the cushioning body  70  and engaged by suitable threads in the base plate  64 . 
     In the illustrated embodiment of the invention the cushioning body  70  defines a convex spherical outer or mating surface  78  at the bottom of the mast and aligned with the central axis  72  of the most  60 , although other alignments might be desired for supporting certain devices on the upper end portion  66  of the mast  60 . A margin of the cushioning body extends radially outward beyond the base plate  64  a distance of at least about ¼ inch, as shown at  73 . This provides desired cushioning in radial, or lateral, directions to absorb vibrational movement in directions other than along the central axis  72 . 
     A generally cylindrical cavity  80  is defined centrally in the cushioning body  70 , interrupting the mating surface  78  and aligned with the central axis  72  of the mast  60 , in one embodiment of the invention. 
     The mast  60  has a height  79  (including the cushioning body  70 ) of about 16 inches in one preferred embodiment of the invention, to support the cameras  18  and  20  or other sensors where their lenses or other receptors are located near where a passenger&#39;s eyes would be, to provide an optimum field of view. The diameter  65  is preferably at least about half the height  79 , to provide ample stability. 
     As may be seen best in FIG. 5, the base  40  defines a bowl-like concave receptacle  86  for the cushioning body  70 . The receptacle  86  defines a concave, spherical, second mating surface  88  which conforms matingly to the convex spherical mating surface  78  of the cushioning body  70 . A shallow, flat-bottomed cavity  90  intersects with and extends downwardly a small distance beneath the central portion of the concave mating surface  88 . 
     The spherical mating surfaces  78  and  88  have equal radii of curvature, so that the surfaces  78  and  88  fit closely together, yet the base  40  and the mast  60  can be positioned at any desired attitude or orientation of angle or rotation with respect to each other within the range of variation of positions likely to be desired as a result of the inclination of the seat cushion  42  of the passenger seat  16  and the preferred attitude of the helicopter  12  during flight. 
     Once adjusted, the relative positions of the mast  60  and base  40  are maintained, in large part, by the effects of friction between the spherical mating surfaces  78  and  88 . The preferred elastomeric material of the cushioning body  70  is not slippery, and since it is fairly soft it gradually conforms closely to the concave spherical mating surface  88 , making it difficult for the mating surfaces  78  and  88  to slip relative to each other once the mast  60  has been placed in its desired position with respect to the base  40 . A preferred material for the cushioning body  70  also bas a damping effect, absorbing vibratory motion and converting such motion into heat, rather than directing it all to the mast  60 . Preferably such a material has a durometer hardness on the A scale in the range of 60 to 80. One material which has been found to be satisfactory is the previously mentioned moldable polyurethane plastic resin material available from Evergreen Plastics, Inc., of Beaverton, Oreg. designated as EA2798, which has a durometer hardness of 70±5 on the A scale. 
     A number of elongate flexible tension-bearing members, for example, four straps  94 ,  96 ,  98 , and  100 , are each preferably equipped with a respective adjustable buckle  102 , such as a side-release buckle of appropriate strength. An upper end of each strap is attached to the lower end portion  62  of the mast  60  as by a respective slotted plate bolted to the mast  60 . Each of the straps extends downwardly and is connected through one part of the respective buckle  102  to a respective short anchoring strap  104  to which is attached a mating portion of the respective buckle  102 . The anchoring strap  104  is preferably attached to the base of the passenger seat  16  through a suitable anchor plate  106 . It will be understood that the anchor plates  106  could also be attached to other appropriate structures such as to the deck  48  of the helicopter, or to another structure available in another type of aircraft or vehicular platform used to carry the adjustable supporting apparatus  14  and associated cameras or other sensors. 
     Referring also to FIG. 7, the adjustable sensor supporting apparatus  14  is best installed for use, as in the helicopter  12 , by first loosening the bolt and nut combination  52  associated with each of the feet  50 , to the extent required to permit the bolt  52  to move in the slot  54  of each of the legs  44  and  46 . The base  40  is then placed upon the cushion  42  of the passenger seat  16 , with the mast  60  supported by the base  40 , so that the weight of the adjustable mounting apparatus is carried by the passenger seat  16 . Once the seat has had a short time, for example 2 to 3 minutes, to settle and assume a stable, compressed condition, each of the bolt and nut combinations  52  is tightened, with the associated foot  50  resting solidly on the deck  48 . 
     Once the feet  50  have been adjusted and fastened to the respective legs  44  and  46 , the base  40  is supported stably on the passenger seat  16 . The mast  60 , together with any cameras or sensors already attached to the mast  60 , is then raised far enough to separate the mating surfaces  78  and  88  slightly and permit the mast  60  to be rotated and tilted as desired with respect to the base  40 . The cavity  80  in the bottom side of the cushioning body  70 , and the cavity  90  in the bottom of the receptacle  86  in the base  40  contain enough air to prevent the cushioning body  70  from acting as a suction cup in the receptacle  86 , so that when the mast  60  is raised the air contained in the cavities  80  and  90  can flow between the spherical mating surfaces  78  and  88 . The cushioning body  70  can thus be lifted to free the spherical mating surfaces  78  and  88  from each other to allow the orientation of the mast  60  to be adjusted with respect to the base  40 . 
     The mast  60  is lowered into the receptacle  86  in the base  40  when it has been adjusted to the desired orientation, bringing portions of the mating surfaces  78  and  88  into contact with each other again. The cushioning body  70  rapidly accommodates itself to the shape of the concave spherical mating surface  88 , resisting relative movement between the mast  60  and the base  40 . The side straps  94  and  96 , the front strap  98 , and the rear strap  100  are then attached to the respective short anchoring straps  104  by the buckles  102 . It will be seen that an opening  101  extends between the base  40  and the control panel  28  to accommodate the forward strap  98 . Each of the straps is then adjusted with respect to its respective buckle  102 , so as to place each of the straps  94 ,  96 ,  98 , and  100  under a small amount of tension to assist in holding the mast  60  in the required position with respect to the base  40 . 
     Preferably, the straps  94 ,  96 ,  98 ,  100 , and  104  are made of a strong and somewhat elastic textile material, such as Nylon webbing of adequate strength, as often is used for luggage carrying straps, weapons slings, belts, and the like. For example, Nylon webbing material readily available from various sources, having a width of one inch and a tensile strength of 300 pounds is satisfactory for the adjustable supporting apparatus  14  shown. 
     Tension in the straps  94 ,  96 ,  98 , and  100  urges the adjustable supporting apparatus  14  and any sensors carried upon the top of the mast  60  downward toward the deck  48  so that the legs  44  and  46  and the associated feet  50  then carry a portion of the weight and of the tension forces in the straps. This keeps the adjustable mounting apparatus  14  and any sensors such as cameras carried on the mast  60  securely fixed and substantially immovable in the adjusted position with respect to the helicopter  12 , so that gravity and the forces and accelerations of flight maneuvers will not significantly move the apparatus  14  and sensors carried on it. 
     Because a helicopter vibrates noticeably during operation it is desired to isolate the sensors such as the cameras carried on the mast  60  from the vibration. Isolation is preferably accomplished in accordance with the present invention partly by the effects of the elastomeric boots  56 , which isolate the feet  50  and the legs  44  and  46  from the vibration of the deck  48 . The legs  44  and  46 , with their inverted “U” shape, have some resiliency and thus they also provide some freedom for the base  40  to avoid moving with the vibration of the helicopter. The cushion  42  of the passenger seat  16  generally isolates the base  40  from vibration of the helicopter  12 , as the seats are designed to provide the most comfortable location and to isolate the passenger and pilot from vibration to the extent possible. 
     Additionally, the cushioning body  70 , by virtue of its elastomeric nature, provides further isolation of the mast  60  from any vibration that is transmitted to the base  40 . Finally, the elasticity of the straps  94 ,  96 ,  98 , and  100  helps prevent transmission of vibration to the mast  60  while the straps hold the mast in its adjusted position with respect to the base  40 . 
     The inertia of the relatively massive mast  60 , including the base plate  64 , opposes any forces of vibration attempted to be exerted through the base  40 , so that those forces are to a great extent dissipated and diffused in deforming the cushioning body  70  elastically instead of moving the mast  60 . A substantial amount of vibrational energy is thus absorbed in and converted to a small amount of internal heating of the cushioning body  70 , rather than moving the cameras or other sensors supported by the mast  60 . 
     When a camera used with the apparatus includes it own image stabilization devices, the apparatus of the invention provides improved image quality by damping vibration in the frequency ranges not affected by the image stabilization devices. Thus, for example, cameras that are internally stabilized, such as a Sony® VX1000, are able to perform better as a result of the reduction of vibration that results from use of the apparatus according to the present invention for support in an aircraft such as the helicopter  12 . 
     Referring next to FIGS. 8 and 9, it will be seen that the camera carrier  22  includes a pair of mounting plates, an upper mounting plate  108  on which the video camera  18  is mounted as shown in FIG. 2, and a lower mounting plate  110 , on which a still camera  20  is mounted, also as shown in FIG.  2 . The carrier  22  is attached to the flange  68  by screws  112  extending though holes  114  in the flange  68  and engaged in threaded bores  116  in the motorized camera carrier  22 . Respective motors (not shown) within the servo-controlled motorized camera carrier  22  are controlled by signals carried through a control cable  118 , to move a crank plate  122  to which the mounting plates  108  and  110  are connected, about the central axis  72  of the mast  60 , or about an axis  120  extending at right angles to the central axis  72 . 
     Preferably, the mast  60  will be located with respect to the base  40  so that the central axis  72  of the mast  60  is vertical when the helicopter  12  carrying the adjustable sensor supporting apparatus  14  is in straight and level flight, or when another mobile platform is in its normal orientation. When the axis  72  is vertical the axis  120  will be in a horizontal plane, so that rotation of the upper portion  124  of the camera carrier  22  with respect to its base  117  effects a panning movement, or change in azimuth direction, of a camera mounted on the camera carrier  22 , and rotation about the axis  120  will elevate or depress the line of sight of the camera or other sensors carried on the device, in a vertical plane. This allows for nearly vertically downward aim of a camera or other sensor directed laterally of the helicopter  12  or other vehicle. One suitable servo-controlled, motorized camera carrier of this type is available from the Panja Company, formerly AMX, of Dallas, Tex. as its “AMX Positract-30” model, although various other similar devices would work. 
     As shown in FIG. 10, it is also feasible to carry a camera or other sensor on a manually operated camera carrier  126 , whose base  128  similarly is attached to the flange  68  at the top end  62  of the mast  60  to permit movement of a camera carried on the manually operated camera mount  126  about the central axis  72  of the mast  60  or a normally horizontal axis  120  perpendicular to the axis  72 . 
     Useful stabilization of the aim or smoothing of the movement of a sensor may be provided by use of a small gyro stabilizer in association with the camera carrier  22  or  126 . One satisfactory gyro-stabilized tracking device is available from Ken-Lab, Inc., of Essex, Conn. under the designation Kenyon Gyro Stabilizer, model Commander KS-6. 
     So that the entire apparatus may remain independent of the helicopter  12  or other moving sensor carrying platform in which it is to be used, a power supply may be provided in a portable case  132  that is located in an available space, such as beneath the passenger seat  16 . The case  132  may also include a computer connected with the control panel  28  and which is part of a servo-control system for operating the camera carrier  22  and the cameras or other sensors. The power supply may include enough electric batteries to power the sensor and the servo-control system for an acceptable time, or may also be connected electrically to an electrical supply system of the helicopter  12  or other platform. 
     As shown in FIG. 11, a cart  140  of suitably strong construction, as of welded steel tubing, has a pair of wheels  142  and feet  144  to support the cart  140  in an upright position. A shelf  146  is provided to support the base  40  with the legs  44  and  46  straddling the shelf  146 . A bottom shelf or box  148  supports the power supply and computer case  132 . A mast-carrying support  150  is similar in shape to the base  40  but without the control panel  28  or any legs, and includes a concave receptacle similar to receptacle  86 , to receive the cushioning body  70 . The mast carrier portion or support  150  may be of construction similar to the base  40 , but including a pair of tubular holes  152 . A pair of parallel generally horizontal arms  154  of metal that are part of the frame of the cart  140  extend through the tubular holes  152 , attaching the carrier  150  integrally to the cart  140 . Buckle parts may be provided on the cart  140  to mate with buckle parts  102  of the straps  94 ,  96 ,  98 , and  100  to secure the mast  60  to the cart  140 . 
     The cart  140 , on the ground, preferably receives and supports the mast  60  at a convenient height, similar to its height when installed in the helicopter  12  or other aircraft with respect to which a particular cart  140  is intended to be used. As a result the mast  60  is easily moved to or from the carrier  150  without being raised or lowered much, while the sensor supporting apparatus is being installed in or removed from the helicopter  12  or other aircraft. The sensor supporting apparatus can be stored on the cart  140 , and easily moved on the cart  140 , to or from an aircraft with which it is used. 
     The terms and expressions which have been employed in the foregoing specification are used therein as terms of description and not of limitation, and there is no intention, in the use of such terms and expressions, of excluding equivalents of the features shown and described or portions thereof, it being recognized that the scope of the invention is defined and limited only by the claims which follow.