Patent Application
20190041178
The invention relates to an improved mid-body, deployable payload and, more particularly, a mid-body payload comprising a seeker having optics which are accommodated within an internal compartment and can be deployed after launch.
A mid-body seeker payload is known in which the seeker optics of the guidance system are retained within the mid-body and designed so as to protect them, as much as possible, from being damaged or obstructed, e.g., dirt, grime, soot, exhaust gases, heat, and flame that typically occur during normal deployment of missiles from a multi projectile magazine, such as those carried under the wings of aircraft or coupled to the exterior of helicopters. Currently, the seeker optics of such guidance systems are located in wings that are deployed after launch and designed to control the flight of the missile (see
Once the missile is fired or launched from the magazine, the wings are automatically deployed by a guidance controller and pivoted outwardly away from the body to facilitate guiding the missile during flight. Once the wings are deployed, the seeker optics supported thereby are moved in a position so as to provide observation the approaching area, e.g., ground, sky, target, etc. The four seeker optics communicate with a guidance controller and work in concert with one another to detect the location of an intended target to be struck. The guidance controller processes the optical images/signals received from the optics and, in turn, transmits guidance signals to the deployed guidance wings which are suitably controlled so as to guide the missile at the intended target.
Although such wing assemblies protect, to some degree, the optics from becoming damaged or partially or completely obstructed by dirt, grime, soot, exhaust gases, heat, and flame, such systems currently utilize four optical sensors, e.g., one accommodated within each wing and this, in turn, adds to the associated cost for the guidance control system. Moreover, as these optical sensors all continuously transmit data to the guidance control system sometimes it may be somewhat difficult for the guidance control system to determine which of the sensors is seeing what image. For example, which sensor or sensors is/are viewing the ground and/or intended target and which sensor or senses is/are viewing the sky.
Furthermore, the data from the optical sensors is processed under the assumption that the four optical sensors are aligned and constantly maintain this alignment throughout the entire flight of the missile. Misalignment is typically accounted for during a laboratory calibration of the sensors and this tends to introduce error into the reconstruction and degrade system performance. The structure of the wing assemblies is driven by the requirement to effectively become an optical bench operating at supersonic speeds. In addition, the optical sensor that is supported in each of the wings of an airframe, such as a missile, tends to introduce drag due to the additional wing thickness that is typically necessary for accommodating and/or protecting the optical system. The drag caused by the wings also compound the difficulties associated with accurately controlling the flight of the airframe.
Wherefore, it is an object of the present invention to overcome the above mentioned shortcomings and drawbacks associated with the prior art and provide a missile guidance system which adequately protects the optical sensors, both prior to and during launch of the missile, and also minimizes the amount of optical sensors required for accurate guidance of the airframe as it travels to the intended target. In particular, instead of each wing carrying an optical sensor, the mid-body supports only a single optical sensor which is separate from and installed downstream of the guidance wings. Prior to and during launch, the optical sensor is completely accommodated within an interior compartment of the mid-body and thus sheltered from the dirt, grime, soot, exhaust gases, heat, and flame which typically occur during launch of the airframe. The mid-body is provided with a door panel that slides, pivots or otherwise moves with respect to the mid-body thereby opening an access window through which the optical sensor can thereafter view the external environment and the intended target. The optical sensor is normally located within the interior compartment of the mid-body but may be tilted with respect to the mid-body such that the optical sensor has a forward facing field of view. In this case because the optical sensor is retained within the interior compartment of the mid body, the forward field of view may be somewhat limited. It is preferred that the optical sensor is movable, relative to the access window once, the door panel is deployed, so as to at least partially extend through the access window. Displacement of the optical sensor so as to partially protrude out through the access window of the mid-body provides the optical sensor with an improved forward field of view. If the door is simply slid out of the way along the mid body, the optical sensor can be pivoted or slid so as to project or extend out from the body.
It is also possible for the optical sensor to be secured to the inside surface of the door panel. In this case the door panel will be pivoted with respect to the mid-body so as to extend from the mid-body thereby exposing the optical sensor to the forward field of view. With this design, the door can have a hinge that is arranged parallel to the longitudinal axis such that one lateral side of the door pivots out away from the mid body thereby providing the optical sensor with a forward field of view. It is also possible for the door to have a hinge that is aligned laterally with respect to the longitudinal axis. In this case, the hinge would be located on the trailing end of the door such that the front of the door panel pivots outwardly away from the mid-body thereby exposing the optical sensor to the forward field of view.
With such a system, the door panel can be made inexpensively by simply curving a metal plate so as to have the same or substantially the same radius of curvature as the exterior wall of the mid-body of the missile. The door panel could simply be stamped in an inexpensive manner. In this manner, the door panel forms part of the exterior skin, shell, or casing of the mid-body until the door panel is deployed or opened. Thus the door panel does not take up any interior space of the mid-body. As a result, additional area within the mid-body is thus available for sensor suite/options. Similarly, since only one optical sensor is being used, the need for optical bench wings is eliminated, and with it the overall cost associated with manufacturing wings that accommodate seeker optics. In addition, the overall weight of the optical system is reduced. The savings of interior space and weight can benefit in different configurations of optical sensors.
Since only one optical sensor is used instead of the four optical sensors employed as with prior art systems, the associated costs of the seeker optics is reduced by up to 75%. It should he noted that with one optical sensor, only one quadrant of the forward area is viewable instead of a 360 degree field of view as with the prior art. Since only one sensor is used, it is much easier to determine the upward or downward position of the sensor, i.e., the orientation of the airframe with respect to the ground, horizon or target during flight.
This invention can be used with many different kinds of seeker systems, like a laser seeker, laser guided optics (types of optical and seeker systems). The seeker optics will be protected within the mid-body, meaning the sensitive optical sensors can be temporarily sealed within the mid-body by the panel door and, therefore, will be protected and not be obstructed, damaged or contaminated by debris, exhaust, heat, etc., as one or more neighboring weapons are launched from the launch system. By removing the seeker system from the wings, it becomes possible to simply adapt the seeker and/sensor depending of the needs of the mission. That is to say, the targets and clutter of the target area can define the optimum type of seeker and as the variability of the payload is increased by the reduction of interior space required for the optical bench wings, optimum performance can be achieved by the modular design of the seeker. In this manner, the mid-body can be GPS guided using an imager and a terrestrial mapping/navigation system.
It is an object to arrange a seeker system within the mid-body in such a manner that minimal drag is introduced into the airframe upon deployment of the seeker system.
Another object is to fully enclose the seeker optics within the mid-body of the missile, both during storage and launch, and the seeker optics can be simply deployed during flight without any significant introduction of drag or impairment to the flight characteristics of the airframe.
A further object of the invention is to utilize a movable panel door which can be secured along the mid-body of an airframe during storage and when the airframe is in a launch tube of a launching system. The closed position of the door panel covers and seals the guidance system, including the seeker optics, within an interior compartment of the mid-body of the airframe and thereby protects the seeker optics, including its optical sensors, from being obstructed or damaged by debris, soot, exhaust gases, and heat as one or more neighboring missiles are launched from the launch system. The door panel can be actuated so as to slide, pivot or move with respect to the mid-body of the projectile thereby opening an access window through which seeker optics can thereafter commence observation. The door panel, once moved to its deployed position, is designed to have minimal or negligible affect on the aerodynamic characteristics of the airframe during flight.
Removal of the seeker optics from the guidance wings of the mid-body further simplifies the design and manufacture of the wings as well as reduces the associated costs of the known guidance wings. Since the wings do not comprise, house or support any seeker optics, the wings can be generally easily formed by a conventional stamping process. The wings can be rolled over the body frame, thereby eliminating most of the wing slot seal in the mid-body since they are external to mid-body. Due to this, additional area is available, within the mid-body, to accommodate sensor suite/options thus enabling multiple sensor configurations to be installed as well as long wave and/or short wave infrared imagers.
The present invention also relates to a mid-body for an airframe, both the mid-body and the airframe having a leading end and a trailing end, and the mid-body comprising a cylindrical housing that defines a longitudinal axis and has an interior compartment. A guidance controller is housed within the mid-body for controlling flight of an airframe. A plurality of wings have a first end that is pivotably coupled to the housing adjacent a leading end of each of the plurality of wings. Each of the plurality of wings is movable from a retracted position into a deployed position in which a second end of each of the plurality of wings extends away from the housing to provide guidance during flight. The housing of the mid-body has an access window which facilitates communication between the interior compartment of the housing and an external environment. A door panel having a closed position, in which the door panel covers the access window, and an open position, in which the door panel is moved relative to the access window to facilitate communication between the interior compartment of the housing and the external environment. An optical sensor is accommodated within the interior compartment of the housing and has a forward field of view. The optical sensor, once the door panel is moved into its deployed position, facilitates viewing the external environment and supplying data to the guidance controller for controlling operation of the plurality of wings during flight.
The accompanying drawings, which are incorporated in and constitute a part of the specification, illustrate various embodiments of the invention and together with the general description of the invention given above and the detailed description of the drawings given below, serve to explain the principles of the invention. The invention will now be described, by way of example, with reference to the accompanying drawings in which:
It should be understood that the drawings are not necessarily to scale and that the disclosed embodiments are sometimes illustrated diagrammatical and in partial views. In certain instances, details which are not necessary for an understanding of this disclosure or which render other details difficult to perceive may have been omitted. It should be understood, of course, that this disclosure is not limited to the particular embodiments illustrated herein.
The invention will be understood by reference to the following detailed description, which should be read in conjunction with the appended drawings. It is to be appreciated that the following detailed description of various embodiments is by way of example only and is not meant to limit, in any way, the scope of the present invention.
Turning now to
As shown in
According to the invention, the guidance wings 26 do not include, support, or house any seeker optics. As a result of this, the wings 26 can be formed simply and oriented closely adjacent to exterior surface 42 of the mid-body housing 30 of the airframe 2. Accordingly, much of the wing slot seal and the interior compartment 32, previously required within the mid-body 24 for retraction of the wings 26, can be eliminated.
Each of the wings 26 have one or more movable/pivotable flaps 34 that are controlled by the guidance controller 64, based on signals received by the optical system (see
A door panel 28 is supported by the mid-body 24 of the airframe 2, between the wings 26 and the rocket motor interface 16. In
The mid-body 24, as shown in
When the door panel 28 is in its closed position, the door panel 28 closes the access opening or window 54 formed in the mid-body 24 which provides access to the interior compartment 32. The outer edges 46, 48, 50, 52 of the door panel 28 and inner edges of the access window 54 can be chamfered or have shoulders that mate with each other to help support and permit relative movement of the door panel 28 with respect to the mid-body 24. It is possible that the outer edges 46, 48, 50, 52 of the door panel 28 and/or the inner edges of the window 54 may be provided with a sealing gasket or some other conventional seal such that when the door panel 28 is in its closed position, the interior compartment 32 of the mid-body 24 is completely sealed with respect to the external environment. Such seal helps prevent any soot, dirt, debris, exhaust particles, heat, etc., from entering into the interior compartment 32 of the mid-body 24 via the access window 54 and possibly damaging an optical sensor 56. The door panel 28 is connect to the housing 30 of the mid-body 24 in such a manner that the guidance controller 64 actuates a door panel actuator 65 which moves, pivots or slides the door panel 28 with respect to the mid-body 24 and thereby opens the access window 54 so that the optical sensor 56, accommodated within the interior compartment 32, can view the external environment.
A longitudinal edge of the door panel 28 can be secured to the housing via a hinge 58 which enables the door to pivot outwardly away from the mid-body 24. The hinge 58 can be located, for example, along either one of the longitudinal side edges of the door panel 28, as shown in
Similarly, if the hinge 58 located along the trailing edge 48 of the door panel 28, when the door panel 28 is pivoted to its opened and deployed position via the door panel actuator, controlled by the guidance controller, the access window 54 is opened, however, the interior surface 60 of the door becomes directly exposed to the air flowing around the airframe 2 during flight. It is to be appreciated that hinges 58 can be secured to the exterior surfaces of the door panel 28 and mid-body 24 in a conventional manner, such as by screws, rivots or welds such that when deployed the door panel 28 remains fixed to the housing 30 of the mid-body 24. Likewise, hinges (not shown) can be connected to the interior surfaces of the of the door panel 28 and mid-body 24. Although hinges 58 can have a low profile and facilitate pivoting of the door panel 28 into the opened and deployed positions, when supported by a hinge 58 and deployed, the door panel 28 projects from the housing 30 of the mid-body 24 and may introduce a small amount of drag on the airframe 2 during flight.
According to another embodiment, the exterior surface 42 of the mid-body 24 has a pair of guide tracks 62 that extend along the opposite side edges of the access window 54 (see
It is to be appreciated that instead of the door panel 28 being movably coupled to the mid-body 24 by a hinge 52, a pair of tracks 62, or some other slidable attachment mechanism, the door panel 28, once deployed, may become completely dislodged and separated from the mid-body 24, as generally shown in the embodiment of
Instead of a mid body with four optical sensors, one on each wing, the inventive mid-body 24 only comprises a single optical sensor 56 that is placed downstream of the guidance wings 26. As diagrammatically shown in
Alternatively, it is also possible for the optical sensor 56 to be secured to the inside of the door panel 28, such as shown in
The forward field of view of the optical sensor 56 will now be described with reference to
The forward field of view of the optical sensor 56 is understood to comprise a combination of both (1) a horizontal field of view HFOV, as shown in
Since only one optical sensor 56 is utilized by the guidance controller 64, the associated cost of the optical system is greatly reduced, e.g., by up to 75% in comparison to currently known optical systems. It should be noted that with one optical sensor 56, only one quadrant of the forward field of view, e.g., 90 degrees or less, will be viewed instead of a 360 degree field of view as with the prior art systems. Since only one optical sensor 56 is utilized, it is generally much easier for the guidance controller 64 to determine an upward or a downward facing orientation of the optical sensor 56, i.e., the orientation of the airframe 2 with respect to the ground. Furthermore, processing of the signals received by the guidance controller 64 from the single optical sensor 56 is greatly simplified in comparison to processing of signals being received from four optical sensors. This results in control signals being transmitted by the guidance controller 64 to the wings 26 at an improved rate, thereby enhancing control of the wings 26 and the flaps 34 as well as improving the overall flight characteristics of the airframe 2 during flight.
While various embodiments of the present invention have been described in detail, it is apparent that various modifications and alterations of those embodiments will occur and be readily apparent to those skilled in the art. However, it is to be expressly understood that such modifications and alterations are within the scope and spirit of the present invention, as set forth in the appended claims. Further, the invention described herein is capable of other embodiments and of being practiced or of being carried out in various other related ways. In addition, it is to be understood that the phraseology and terminology used herein is for the purpose of description and should not be regarded as limiting. The use of “including,” “comprising,” or “having,” and variations thereof herein, is meant to encompass the items listed thereafter and equivalents thereof as well as additional items while only the terms “consisting of” and “consisting only of” are to be construed in a limitative sense.
The foregoing description of the embodiments of the present disclosure has been presented for the purposes of illustration and description. It is not intended to be exhaustive or to limit the present disclosure to the precise form disclosed. Many modifications and variations are possible in light of this disclosure. It is intended that the scope of the present disclosure be limited not by this detailed description, but rather by the claims appended hereto.
