Abstract:
A canard includes a first section and a second section. The first section is configured for the coupling of radial forces to a fuselage of an air vehicle, and the first section is coupled to the second section via a hinge somewhere along the radial extent of the canard. An edge of the first section near the hinge provides a load support for the air vehicle within a launch canister.

Description:
TECHNICAL FIELD 
       [0001]    The present invention relates to support systems for missiles within a launching canister, and in an embodiment, but not by way of limitation, a canard-centric missile support system. 
       BACKGROUND 
       [0002]    In many missile launching systems, a canard is positioned near the nose of the missile to stabilize the missile in flight. Such canards are normally hinged near the root or point of attachment to the missile, which allows the canard to be folded and the missile to be positioned into a launch canister. In such a missile launching system, the canard does not provide support for any load while positioned in the launch canister. When the missile is then launched, a spring or other tension/force imparting mechanism coupled with or integral to the hinge causes the canard to move into its flight position, which is substantially perpendicular to a tangent of the housing of the missile. 
         [0003]    In some missile launching systems, different sections of the missile have different diameters. Most commonly in such systems, an aft section of the missile has a larger diameter than the forward or nose section of the missile. These missiles require a launch canister that is large enough to hold the largest diameter section of the missile. Thus, the forward section of the missile is in cantilever. This creates a situation in which there is not an insubstantial amount of free space between the smaller diameter forward section of the missile and the inside wall of the launch canister. This dead space can result in unwanted movement or flexure of the missile within a launch canister, caused by lateral shock loads (i. e, across a diameter of the launch canister) occurring during normal handling of the missile systems or when a near miss explodes near the launch canister. Such movement of the missile within the launch canister can be minimized by placing a ring or collar around the smaller diameter section of the missile. However, upon launch, such ring or collar is jettisoned, and can cause damage to personnel and/or property at the launch site. 
     
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         [0004]      FIG. 1A  illustrates an example embodiment of a missile canard. 
           [0005]      FIG. 1B  illustrates the missile canard of  FIG. 1A  positioned within a missile launch canister. 
           [0006]      FIG. 2A  illustrates an example embodiment of a missile canard used in a missile canard support system. 
           [0007]      FIG. 2B  illustrates the missile canard of  FIG. 2A  positioned within a missile launch canister. 
       
    
    
     DETAILED DESCRIPTION 
       [0008]    In the following detailed description, reference is made to the accompanying drawings that show, by way of illustration, specific embodiments in which the invention may be practiced. These embodiments are described in sufficient detail to enable those skilled in the art to practice the invention. It is to be understood that the various embodiments of the invention, although different, are not necessarily mutually exclusive. For example, a particular feature, structure, or characteristic described herein in connection with one embodiment may be implemented within other embodiments without departing from the scope of the invention. In addition, it is to be understood that the location or arrangement of individual elements within each disclosed embodiment may be modified without departing from the scope of the invention. The following detailed description is, therefore, not to be taken in a limiting sense, and the scope of the present invention is defined only by the appended claims, appropriately interpreted, along with the full range of equivalents to which the claims are entitled. In the drawings, like numerals refer to the same or similar functionality throughout the several views. 
         [0009]      FIGS. 1A and 1B  illustrate a canard  100  and a canard  100  positioned within a launching canister  150  respectively. The canard  100  includes a first section  125  and a second section  120 . The first section of the canard is connected to a fuselage  110  of a missile. While an embodiment of the present disclosure is described for use in connection with a missile, other embodiments include other air vehicles. The first section  125  and the second section  120  are connected together by a hinge  140 . The hinge  140  permits the first section  125  and the second section  120  to be in alignment in the same plane, and then pivot for folding to form an acute angle as illustrated in  FIG. 1B . In lieu of the hinge  140 , other pivot means or means to force the first section  125  and the second section  120  into alignment in a plane, and then pivot to form an angle, could be used, such as a ball and socket type of joint or connection. As can be seen from  FIG. 1B , the folding of the canard to an acute angle permits the insertion of the missile into the launch canister. The canard as shown in  FIG. 1B  has virtually no lateral shock or other substantial load bearing capacity. 
         [0010]      FIGS. 2A and 2B  illustrate a folding canard system  200  that not only functions as a means to allow the insertion of a missile into a launching canister, but that further functions as a load bearing, support, and stabilization system for the missile while the missile is in the launch canister  150 .  FIG. 2A  illustrates a canard  200  with a first section  125  and a second section  120 . Unlike the canard of  FIGS. 1A and 1B , the canard  200  of  FIGS. 2A and 2B  is hinged outboard of the root  127  of the canard near an approximate midpoint  126  of the canard, dividing the first section  125  and the second section  120  of the canard along a radial extent of the canard, that is, somewhere distant or apart from a root  134  of the canard. 
         [0011]    As illustrated in  FIG. 2B , the canard  200  can be folded such that the first section  125  and the second section  120  form an acute angle, and the canard and missile can then be positioned into the launch canister  150 . As further illustrated in  FIG. 2B , an edge  137  of the first section  125  of the canard contacts the inner wall of the launch canister, and as indicated by arrow A, can withstand an externally generated shock, or intentionally couple this shock into the fuselage  110 . In an embodiment, this shock can be referred to as a lateral shock, since the force experienced by the launch canister  150  and the first section  125  occurs across an axial sector of canister  150  as indicated by arrow A in  FIG. 2B . This lateral shock can be dissipated through the first section  125 , fuselage features  134 , and the fuselage  110 . The exposed forward surfaces of the first section  125  and the second section  120  at points  128  and  129 , or simply somewhere near the hinge line  130 , can be chamfered or otherwise treated to reduce gouging of the internal wall of the launch canister upon egress of a missile. The tip  132  of the second section  120  of the canard also rests against the inside wall of the launch canister, but this does not provide any substantial support against external shocks. 
         [0012]    Fuselage features  134 , if needed, transfer canard axial loads to the fuselage  110  as axial free play is stopped by such a feature. The feature  134  could be a passive land feature machined into the fuselage  110  below the canard first section  125  to distribute the loads into the missile structure. The canard is still free however to pivot in flight due to residual axial free play. An extra benefit of the canard  200  is a reduced panel (bending) load at the hinge  140  in flight. 
         [0013]    In the foregoing detailed description of embodiments of the invention, various features are grouped together in one or more embodiments for the purpose of streamlining the disclosure. This method of disclosure is not to be interpreted as reflecting an intention that the claimed embodiments of the invention require more features than are expressly recited in each claim. Rather, as the following claims reflect, inventive subject matter lies in less than all features of a single disclosed embodiment. Thus the following claims are hereby incorporated into the detailed description of embodiments of the invention, with each claim standing on its own as a separate embodiment. It is understood that the above description is intended to be illustrative, and not restrictive. It is intended to cover all alternatives, modifications and equivalents as may be included within the scope of the invention as defined in the appended claims. Many other embodiments will be apparent to those of skill in the art upon reviewing the above description. The scope of the invention should, therefore, be determined with reference to the appended claims, along with the full scope of equivalents to which such claims are entitled. In the appended claims, the terms “including” and “in which” are used as the plain-English equivalents of the respective terms “comprising” and “wherein,” respectively. Moreover, the terms “first,” “second,” and “third,” etc., are used merely as labels, and are not intended to impose numerical requirements on their objects. 
         [0014]    The abstract is provided to comply with 37 C.F.R. 1.72(b) to allow a reader to quickly ascertain the nature and gist of the technical disclosure. The Abstract is submitted with the understanding that it will not be used to interpret or limit the scope or meaning of the claims.