Apparatus for wing attachment

Abstract: A saddle (30A) for restraining vibration of a wing (14A) [Fig.1] of a missile (10) has a grooved portion (32) adapted to receive the wing (14A). The saddle (30A) has two legs extending away from the grooved portion (32) which are secured (34A, 34D) to the missile (10).

Description: This invention relates to a missile having a wing with a post extending into the body of the missile to locate and lock the wing on the body. Missiles in flight are controlled and stabilized by wings attached to the missile body. The wings, however, can be easily damaged while the missile is being transported or stored before it is fired. To avoid damage and to facilitate mounting the missile on an aeroplane, the wings are often made so that they can be detached while the missile is being transported and then quickly installed after the missile is loaded on an aeroplane. One removable wing design uses a "locking ball". The wing includes a post. A plurality of balls are fabricated in the end of the post. The balls can retract into the post or be locked in a position protruding from the post. The missile is made with a hole (also called a "bore") large enough to receive the post and balls when retracted. To attach the wing, the post is inserted into the bore until the portion of the post with the balls extends through the bore. A locking mechanism then releases the balls and they prevent the post from sliding back out of the bore. Since the balls cannot fit through the bore, the wing is attached to the missile. To prevent the wing from rotating around the post, a pin is attached to the surface of the wing which butts against the missile. The pin fits into a hole in the missile body. This method of attaching wings is adequate for many applications. However, this method of attachment may not be adequate to prevent the wing from fluttering or vibrating in the presence of air turbulence as the missile flies. The problem of wing vibration is exacerbated because the pin and the hole into which the pin fits tend to wear away as the wing vibrates. As the pin fits less snugly into the hole, the vibration becomes worse. A small amount of vibration and wear caused by vibration of the wing is acceptable. Too much wear, however, degrades the performance of the missile. Over time, the wing vibration will increase until the wear becomes unacceptably large, allowing the wing to flutter. In designing a missile, the means for securing the wing must keep the wing vibration and wear at acceptable levels over the useful life of the missile. For missiles which are carried on airplanes before they are fired, wing vibration while the missile is mounted on the airplane must also be considered. Air turbulence is a very complicated phenomenon. While models of airplanes and missiles in flight can be used to estimate air turbulence, the actual amount of turbulence in some situations may deviate sharply from the amount predicted by the models. A missile designer, therefore, may underestimate the amount of turbulence a missile wing is exposed to over its life. Consequently, the method of attaching wings to missiles may not be adequate to keep wing flutter at acceptable levels over the lifetime of the missile. When it is discovered that the design of a missile is inadequate for any reason, it is often very difficult and costly to change the design. Every design change must be carefully evaluated to determine its impact on the performance of the missile. For example, the impact on performance of any added weight or drag of any change must be determined. Changing the method of attaching wings poses unique problems. It is often necessary for aerodynamic reasons to mount a set of wings over the motor of the missile. If changing the method of attaching wings requires recessing parts into the missile or attaching parts to the missile, changes to the motor may be needed. Since the motor comprises a highly pressurized vessel, any changes to the motor must be carefully scrutinized. It must be determined that the changes to the motor design do not create weaknesses in the pressurized vessel. The testing needed to make this determination is very time consuming and undesirable. US-A-3 223 034 on which disclosure the preamble of claim 1 is based, describes a rocket fin assembly in which a shroud is mounted on the missile casing, and a mounting bracket receives the base of the fin. The shroud has a flat bottomed recess to which the mounting bracket is bolted. The bolt holes in the bracket provide clearance for adjustment of the bracket. The base of the fin is held by bolts or rivets in a fin receiving projection of the bracket. A journal member is fixed to and projects out from the shroud to provide a pivot point about which the bracket can be rotated. The shroud is secured over the casing of the aft end of the motor of the missile. The means for restraining motion of the fin includes a tubular member that forms an enclosure about the aft portion of the rocket motor which is upstream from the shroud. An adjusting bracket is received in a rectangular opening in the tubular member where it is fixed by rivets. The adjusting bracket has a raised portion with a recess. Tangentially to the body of the missile two adjusting screws extend into the recess from opposite sides of the raised portion. The tips of the adjusting screws bear on opposite sides of a downwards projection from the fin, so that appropriate rotation of the two adjusting screws applies a force that rotates the fin about the journal member in the shroud. Thus the fin can be made parallel to the axis of the body of the missile. When the fin has been properly aligned, the bolts holding the mounting bracket to the shroud are tightening to hold the fin in position. According to one aspect of the present invention, a missile of the kind defined hereinbefore at the beginning is characterised by a wing saddle having a first portion with a groove in which a portion of the wing is disposed, and a second portion extending along a surface of the missile parallel with the using and away from the first portion and secured to the surface of the missile at the end of the second portion away from the groove; whereby the first portion restrains the wing against flutter or vibration, the saddle being made from materials used in missile construction, such as steel. According to another aspect of the invention, a missile of the kind defined hereinbefore is characterised in that the body of the missile comprises a shell, and a motor surrounded by the shell, and in that a wing saddle is provided comprising a first portion, disposed above the motor, for restraining motion of the wing, the wing being mounted to the shell, and a second portion, secured to the shell at a point away from the motor, for securing the first portion. Preferred embodiments of the invention have: apparatus for attaching a wing to a missile which reduces vibration induced wear and its associated negative effects; apparatus for attaching a wing to a missile which will not require modifications to the motor of the missile; apparatus to reduce wing wear which can be added to missiles with wings attached using a locking ball. In a preferred embodiment the wing saddle is mounted to the missile body forward of the motor of the missile. A portion of the saddle projects to the rear, over the motor. The portion of the saddle over the motor has a groove formed in it. The wing has a recessed portion which fits into the groove, thereby restraining flutter of the wing. In one embodiment of the invention, the saddle is removable secured to the missile body using screws allowing replacement of the saddle. Brief Description of the Drawings The invention will be better understood by reference to the following more detailed description and accompanying drawings in which: FIG. 1 is an exploded view of a missile incorporating the invention; and FIG. 2 is a more detailed isometric view of the wing saddle in FIG. 1. Description of the Preferred Embodiments FIG. 1 shows a simplified isometric view of a missile 10. Missile 10 has fins (sometimes also called "control surfaces") 12A, 12B, 12C, and a fourth fin (not shown). The fins are for guidance and stabilization of missile 10. The fins are attached in any known manner. Here, the fins are attached in the forward part of the missile 10. However, in some missile designs, the fins are attached to the rear sections of the missile. Missile 10 also has wings 14A...14D. Wings 14A...14D are attached to missile 10 using a "locking ball" arrangement which is known in the art. The details of attachment are shown for wing 14A, but all four wings are attached in the same manner. Wing 14A has a post 16 projecting from it. Post 16 has a plurality of balls 18A and 18B (shown as representative) on one end. Post 16 fits into hole 24. To mount wing 14A, post 16 is inserted into hole 24. A locking mechanism of the type known in the art is then engaged to extend balls 18A and 18B. Since post 16 with balls 18A and 18B extended is bigger than the opening of hole 24, post 16 is restrained in hole 24. Wing 14A is thus secured to the body of missile 10. It will be noted that the locking ball arrangement secures wing 14A to missile 10 at only one point. Wing 14A is, thus, free to rotate around this point. Wing saddle 30A holds wing 14A to prevent rotation. It also greatly reduces wear on hole 24 experienced in prior art missiles. Saddle 30A is made from materials used in missile construction, here D6AC steel. Saddle 30A is mounted to missile 10 via screws 34A...34D. Screws 34A...34D pass through holes 38A...38D, respectively, in saddle 30A and into holes 36A...36D, respectively, in missile 10. Wing 14A has a recess (sometimes called a "spot face") 22 which fits into a clevis 32 which forms a first portion of saddle 30A. Clevis 32 thus restrains wing 14A from rotating It is important to note that the rear portion of missile 10 is motor 40. Clevis 32 is over motor 40. However, holes 36A...36D are forward of motor 40. Mounting saddle 30A requires no structural changes in motor 40, but provides a restraining force above it. The placement of clevis 32 determines the location where restraining force is applied to wing 14A. To prevent rotation around post 16, clevis 32 is preferably spaced apart from post 16. To prevent rotation, clevis 32 must contact wing 14A at a point where the wing is thick enough not to bend at the point where the restoring force is applied. For aerodynamic reasons, wing 14A is thinner at its forward end and thicker at its rear end. Thus, clevis 32 is preferably spaced to the rear of post 16. To reduce pressure on the wing at recess 22, clevis 32 should be as far from post 16 as possible. If wing 14A tapers at the rear end, the wing thickness at recess 22 must be thick enough to withstand the pressure. Here, the thickness is around 2.54mm (1/10 of an inch). Turning to FIG. 2, more details of saddle 30A are shown. FIG. 2 shows that saddle 30A is aerodynamically shaped so as not to excessively increase drag when it is mounted on missile 10. The exact shape will differ depending on such factors as the shape of missile 10, the shape of wing 14A, and the placement of wing 14A on missile. The aerodynamic shape of saddle 30A is preferably developed using known design and simulation techniques. The general shape of saddle 30A lends to the aerodynamic design. For example, the forward edge 42 is tapered to reduce drag. Also, holes 38A...38D are countersunk holes so that screws 34A...34D (FIG. 1) will not project above the surface of saddle 30A. Additionally, wall 44B of clevis 32 is shaped to fit into recess 22 (FIG. 1). Likewise, wall 44A is shaped to fit into an identical recess (not shown) on the opposite side of wing 14A. This arrangement allows side 46 of saddle 30A to taper gradually away from wing 14A. In constructing saddle 30A, the width of clevis 32 is selected to be slightly wider than thickness of the portion of wing 14A (FIG. 1) inserted in clevis 32. Moreover, walls 44A and 44B taper outward slightly. This design allows wing 14A (FIG. 1) a slight amount of play, here a maximum of 0.27mm (0.005") to facilitate quick installation and removal of wing 14A. It should also be noted that any edges of saddle 30A in contact with wing 14A are rounded. For example, corners 50A and 50B are rounded. Without this rounding, it has been found that wing 14A tends to develop cracks at the point of contact between saddle 30A and wing 14A. Having described one embodiment of the invention, it will be apparent to one of skill in the art that various modifications could be made. For example, the shape of saddle 30A could be changed to provide less drag. The location of clevis 32 relative to post 16 could change. Also, other methods of attaching saddle 30A to missile 10 could be used. The disclosed embodiment showed screws used for attachment. This method allows for the saddle to be replaced if vibration causes the groove to wear out. However, welding or other techniques could be used to attach the saddle to the missile.

Claims: A missile having a wing with a post (16) extending into the body of the missile to locate and lock the wing (14A) on the body, characterised by a wing saddle (30A) having a first portion (32) with a groove in which a portion of the wing (14A') is disposed, and a second portion extending along a surface of the missile parallel with the wing (14A) and away from the first portion (32) and secured to the surface of the missile at the end of the second portion away from the groove whereby the first portion (32) restrains the wing (14A) against flutter or vibration, the saddle (30A) being made from materials used in missile construction, such as steel. A missile according to claim 1, characterised in that a third portion extends along a surface of the body of the missile parallel with the wing (14A) and is secured to the surface of the body of the missile at the end of the third portion away from the groove. A missile according to claim 2, characterised in that the missile has a motor and the first portion (32) of the saddle (30A) is disposed above the motor; and the second and third portions of the saddle (30A) are secured to the surface of the body of the missile away from the motor. A missile according to claim 3, characterised in that the second and third portions of the saddle (30A) are secured to the surface of the body of the missile using screws (34A,34B,34C,34D). A missile according to claim 4, characterised in that the portion of the wing (14A) in the groove is spaced apart from the walls (44A,44B) of the groove by a tolerance of 0.076 to 0.127mm (0.003 to 0.005 inches). A missile according to claim 2, characterised in that the wing (14A) has recesses (22) formed in the portion thereof disposed in the groove. A missile having a wing with a post (16) extending into the body of the missile to locate and lock the wing (14A) on the body, characterised in that the body of the missile comprises a shell, and a motor surrounded by the shell, and in that a wing saddle (30A) is provided comprising a first portion (32), disposed above the motor, for restraining motion of the wing (14A), the wing (14A) being mounted to the shell, and a second portion, secured to the shell at a point away from the motor, for securing the first portion (32). A missile according to claim 7, characterised in that the first portion (32) has a groove formed therein. A missile according to claim 8, characterised in that the second portion of the saddle (30A) and a third portion thereof are connected to and extend away from the first portion (32), the third portion also being secured to the shell at a point away from the motor. A missile according to any preceding claim, characterised in that the saddle (30A) is aerodynamically shaped to reduce its drag.

Inventors: COLANANNI LAURA M, LAILER ROBERT H JR, LUSSIER DAVID B, PORTER FRANK K JR, COLANANNI, LAURA M., LAILER, ROBERT H., JR., LUSSIER, DAVID B., PORTER, FRANK K., JR.
Applicants: RAYTHEON CO, RAYTHEON COMPANY
Application year: 1991
Main classification: F42B10
IPC codes: F42B15, B64C9, F42B10