Patent Publication Number: US-7216642-B2

Title: Pneumatically launched folding wing glider toy

Description:
This application is a divisional of application of Ser. No. 10/776,812 filed Feb. 11, 2004 now U.S. Pat. No. 7,077,359, which claims priority benefit of the disclosure of U.S. provisional patent application 60/446,890 for Pneumatically Launched Folding Wing Glider Toy, filed Feb. 12, 2003. 
    
    
     BACKGROUND OF THE INVENTION 
     The present invention generally relates to toys, and more particularly to pneumatically projected glider aircraft toys. 
     Aerial toys such as airplane gliders have long been used for education and entertainment. Such gliders have conventionally been propelled into flight by way of a sling shot mechanism or by a user throwing the glider into flight. Such gliders have been limited in terms of altitude due to the traditional means used to launch the glider, as well as the drag forces acting against the wings of the glider during its ascent. For example, as to conventional gliders launched by a sling shot mechanism, the maximum altitude of the glider is limited in part by the strength of the rubber band or similar elastic member comprising the launching mechanism. As to gliders launched by a user throwing the glider, the maximum altitude of the glider is limited in part by the strength of the thrower. 
     Additionally, conventional glider launching mechanisms typically lack an orientation-sensitive safety feature. Consequently, such conventional gliders may be launched in virtually any direction. This presents a potential safety hazard in that a conventional glider may be launched directly at a person. Damage to the glider may also result from the glider being launched in an improper direction. 
     In contrast to conventional toy gliders, toy rockets are often propelled into flight by way of a pressurized fluid, such as air or water, or by way of a solid fuel. Such rockets have been able to reach altitudes that are much greater than altitudes attained by conventional gliders. However, rockets typically use a parachute to ease the rocket back to earth. While a parachute is effective in slowing a rocket&#39;s descent, it does not provide the visual stimulation provided by a glider. In addition, the substantially vertical flight path of a rocket is not as visually stimulating as the relatively more arcuate flight path of a glider. 
     Some existing launching mechanisms for pneumatically launched toy rockets include an orientation-sensitive safety feature that relieves pressure when the rocket is not oriented substantially vertically. In other words, where the launching mechanism has been pumped and enough pressure has been created to otherwise launch the rocket, the safety feature will allow the pressure to escape through a vent when the rocket is not oriented substantially vertically at the time the launching trigger is pressed. This produces the undesirable result of having to re-pump the launching mechanism for another launch attempt. In addition, conventional toy rocket safety features are configured to limit the operable launch angle to around 90 degrees; whereas the ideal launch angle for a glider may be less than 90 degrees. 
     Consequently, a significant need exists for a glider that is able to reach altitudes greater than those attained by conventional gliders, yet is able to glide back down to earth like a conventional glider. In addition, a need exists for a launcher that includes an orientation-sensitive safety feature, such that a glider may be launched therefrom only when the launcher is oriented within a particular angular range. 
     SUMMARY OF THE INVENTION 
     The invention overcomes the above-noted and other deficiencies of the prior art by providing a glider capable of reaching relatively great altitudes that is further capable of gliding back down to earth. In particular, a pivoting attachment of wings to a fuselage allows launch of a glider in a low-drag configuration. After a suitable interval upon reaching altitude, the wings extend forward, thus allowing the glider to glide in an entertaining fashion. A launcher may launch a projectile only when the hand-held launcher is oriented within a particular angular range. 
     In one aspect of the invention, a toy glider system is comprised of a glider and a launcher operable to launch the glider. The glider is comprised of pivoting wings and a proximally-open receptacle. The launcher is comprised of a support member configured to be received by the receptacle, a pneumatic pressure source, and a launch feature configured to selectively communicate a pressurized medium from the pressure source to impinge the pressurized medium against the glider. 
     In another aspect of the invention, a toy glider system is comprised of a glider and a launcher operable to launch the glider. The glider is comprised of pivoting wings and a wing sweep mechanism. The wing sweep mechanism has a locking mechanism operable to hold the wings in a locked position. The wing sweep mechanism is operable to urge the wings to an extended position when the locking mechanism is in an unlocked position. The locking mechanism is configured to change from the locked position to the unlocked position when the glider is launched from the launcher. 
     In yet another aspect of the invention, a launcher is operable to launch projectiles with a pressurized medium approximately within a generally upward, non-vertical angular range. The launcher is comprised of a launch guide, a trigger, a linkage, and a safety feature. The launch guide is configured to guide the angle at which projectiles are launched from the launcher. The linkage is configured to cause a projectile to be launched in response to communication of actuation of the trigger. The safety feature is responsive to the angle at which the launch guide is oriented. The safety feature is configured to enable communication of actuation of the trigger to the linkage in response to the launch guide being oriented approximately within a generally upward, non-vertical angular range. 
     In another aspect of the invention, a toy glider system is comprised of a glider and a launcher. The glider is comprised of wings and a means to pivot the wings. The launcher is comprised of a means to launch the glider and a means to limit an angular range within which the glider may be launched from the launcher. 
     In yet another aspect of the invention, a wing sweep mechanism in a glider provides for the wings of the glider to be retracted in an overlapping position, as one wing will rotate on a higher plane than the other. The wing sweep mechanism is further configured such that the wings will be parallel to the fuselage of the glider when the wings are in a retracted position; yet the wings will have a 5° angle of attack and a 5° dihedral angle when swept forward in the open position. 
     In another aspect of the invention, the wing sweep mechanism in a glider provides for a dampening effect allowing the wings to rotate forward upon sudden impact with the ground or other objects, preventing damage to the wing sweep mechanism and/or wings. The wings may be readjusted back into the proper operating orientation without damage to the wing sweep mechanism. 
     In yet another aspect of the invention, a pump pressure mechanism prevents over pressurization of a pressure chamber. The pump pressure mechanism has a relief valve feature configured to prevent further increase in pressure that may be created by the pump when the pressure in a pressure chamber reaches a threshold. The threshold is related to the strength of a spring in the relief valve feature. 
     In another aspect of the invention, a pressure mechanism in a launcher requires at least a minimum amount of pressure in order for a projectile to be launched from the launcher. 
     These and other objects and advantages of the present invention shall be made apparent from the accompanying drawings and the description thereof. 
    
    
     
       BRIEF DESCRIPTION OF THE FIGURES 
       The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments of the invention, and, together with the general description of the invention given above, and the detailed description of the embodiments given below, serve to explain the principles of the present invention; it being understood, however, that this invention is not limited to the precise arrangements shown. In the drawings, like reference numerals refer to like elements in the several views. In the drawings: 
         FIG. 1  depicts a perspective view of a glider engaged with a handheld launcher. 
         FIG. 2  depicts a perspective view of a wing sweep mechanism of the glider of  FIG. 1  in an unlocked position. 
         FIG. 3  depicts a perspective view of a wing sweep mechanism of the glider of  FIG. 1  in a locked position. 
         FIG. 4  depicts a cross section of a wing sweep mechanism of the glider of  FIG. 1 . 
         FIG. 5  depicts a partial exploded cross section of the launcher of  FIG. 1 . 
         FIG. 6  depicts a partial exploded cross section of the launcher of  FIG. 1 . 
         FIG. 7  depicts a cross section of the launcher of  FIG. 1 . 
         FIG. 8  depicts a trigger mechanism from the launcher of  FIG. 1  in a safe position. 
         FIG. 9  depicts a trigger mechanism from the launcher of  FIG. 1  in a stand-by position. 
         FIG. 10  depicts a trigger mechanism from the launcher of  FIG. 1  in a firing position. 
     
    
    
     DETAILED DESCRIPTION OF THE INVENTION 
     With reference to the drawings,  FIG. 1  shows a handheld launcher  40  engaged with a glider  10 . With reference to  FIGS. 1 through 4 , there is shown a glider  10  that has two pivoting, retractable wings  20  that deploy, or sweep outward and forward, sometime after launch. The glider  10  has a nose cone  14 , a hollow fuselage  12 , two wings  20  and four tail stabilizers  16 . However, it will be appreciated that any suitable number of wings  20  or tail stabilizers  16  may be used. It will also be appreciated that the glider  10  need not have a cone-shaped nose. In addition, it will be appreciated that all or part of the fuselage  12  may be hollow. Still other configurations may be used. 
     The glider  10  in the present example has a wing sweep mechanism  22  that is configured to hold the wings  20  in a retracted position, partially above the fuselage  12 , as shown in  FIG. 3 . However, it will also be appreciated that a wing sweep mechanism  22  may simply hold the wings  20  near, but not necessarily partially above, the fuselage  12 . Preferably, the wing sweep mechanism  22  holds the wings  20  in a retracted position when the wing sweep mechanism  22  is in a locked position, and urges the wings  20  to an extended position when the wing sweep mechanism  22  is in an unlocked position. 
     In the present example, the wing sweep mechanism  22  is comprised of left and right wing pivot support members  24 , a wing pivot mount body collar  26 , a swinging annular member  28  and a rubber band  30 . The wing sweep mechanism  22  is mounted in the forward section of the fuselage  12  of the glider  10 . The pivot support members  24  are attached to the respective wings  20  and are also hingedly attached to the body collar  26 , such that the wings  20  are able to rotate from a position where they are above or near the fuselage  12  to a position where they are fully extended. Each pivot support member  24  has a hook  32  located on the end of the pivot support member  24  that is nearest the fuselage  12 . The hooks  32  of the pivot support members  24  are attached to the same rubber band  30 . It will be appreciated that any suitable elastic alternative to a rubber band  30  may be used, such as, by way of example only, one or more springs. In the present example, the tension in the rubber band  30  urges the hooks  32  together, which rotates the wings  20  to a fully extended position. By way of example only, the rubber band  30  may provide just enough tension to overcome the drag force of flight and draw the wings  20  outward at approximately the apex of flight. Alternatively, a rubber band  30  may be selected that will overcome the drag force of flight and draw the wings  20  outward before or after reaching the apex of flight. 
     The annular member  28  encircles the fuselage  12 , and is hingedly attached to the body collar  26 . The annular member  28  includes a clasp  36  protruding therefrom. The weight distribution of the annular member  28  encourages it to rotate forward relative to the fuselage  12 , such that the clasp  36  is drawn away from the fuselage  12 . In opposition to the force from this weight distribution, a spring  38  is placed between the annular member  28  and the fuselage  12 , which urges the annular member  28  to rotate backward, such that the clasp  36  is drawn toward the fuselage. When the clasp  36  is drawn toward the fuselage  12 , it may engage tabs  34  located at the end of each pivot support member  24  that is nearest the fuselage  12 . Thus, a rearwardly-rotated annular member  28  may serve to hold the wings  20  locked in a retracted position, as shown in  FIG. 3 ; whereas a forwardly-rotated annular member  28  presents an unlocked position, allowing the wings  20  to extend, as shown in  FIG. 2 . When the annular member  28  has been set to the locked position prior to the glider  10  being launched, a sudden change in velocity at launch may cause the annular member  28  to rotate to the unlocked position. 
     The body collar  26  has a top plate  27 , upon which the pivot support members  24  are mounted. As shown in  FIG. 4 , the top plate  27  is tilted at a 5° angle toward the tail of the glider  10 , providing an angle of attack. Alternatively, any other angle of attack may be provided by a different tilt of the top plate  27  or other means. In addition, the pivot support members  24  may be configured such that each wing is mounted at, for example, a 5° positive dihedral angle. Such a dihedral angle may provide wing stabilization and/or other benefits. Any other suitable dihedral angle or configuration may be used. Where a 5° angle of attack is created by tilting the top plate  27 , and the pivot support members  24  are configured to provide a 5° dihedral angle for the wings  20 , the wings  20  will be parallel to the fuselage  12  when the wings  20  are in a retracted position. Thus, in the present example, the wings  20  are relatively flat when in the retracted position, while the wings  20  are at a 5° angle of attack and a 5° dihedral angle when extended. Such a changing configuration may provide desirable aerodynamics for launching and subsequent descent. 
     The wing sweep mechanism  22  in the present example also provides for a dampening effect, allowing the wings  20  to rotate further forward upon sudden impact with the ground or other objects, thereby preventing damage to the wing sweep mechanism  22  and/or wings  20 . As shown in  FIGS. 2 and 3 , a boss  35  protrudes from the top plate  27  of the body collar  26  for each pivot support member  24 . Each boss  35  is configured such that, upon deployment of the wings  20 , the boss will initially stop the sweeping of the wings  20  when the tabs  34  on the pivot support members  24  come into contact with each respective boss  35 . The wings  20  will initially be kept from sweeping further forward by friction between each tab  34  and boss  35  in a positioning shown in  FIG. 2 . However, due to the configuration of each boss  35 , this friction may be overcome upon impact of the glider  10  with the ground or another object, such that each pivot support member  24  may sweep forward past the proper operating orientation, as the tabs  34  are permitted to move over the top of the respective boss  35  when the friction is overcome. This provides a dampening effect of shock absorption, which may reduce the likelihood of the wing sweep mechanism  22  or its components fracturing upon impact. The wings  20  may be readjusted back into the proper operating orientation without damage to the wing sweep mechanism  22 . 
     In the present example, the wings  20  partially overlap when in the retracted position. This is accomplished, in part, by configuring the pivot support member  24  for each wing  20  slightly differently, such that one wing rotates on a higher plane than the other wing. As shown in  FIGS. 2 and 3 , the configuration of the pivot support members  24  is such that the left wing  20  mounted to the left pivot support member  24  will be vertically higher than the right wing  20  mounted to the right pivot support member  24 . It will be appreciated by those of ordinary skill in the art that having one wing  20  slightly vertically higher than another may not significantly affect the flight of the glider  10 . It will also be appreciated that other configurations may be used to permit overlap of the wings  20 . Alternatively, the glider  10  may be configured such that the wings  20  do not overlap at all. 
     With reference to  FIGS. 1 and 5  through  10 , there is shown a launcher  40  comprised of a manual air pump  42  in a pump housing  44  in fluid communication with a pressure chamber  46 . A check valve  48  prevents air from escaping from the pressure chamber  44  into the pump housing  44 . The pressure chamber  46  is comprised of the inside of a launch tube  50 . A distal end  52  of the launch tube  50  has a hole  54  through which air may exit and provide thrust to the glider  10 . A valve  56  covers the hole  54 , and is held in place by a spring  58 , which aids in preventing pressurized air from escaping through the hole  54  until the valve  56  is proximally retracted. When the valve  56  is so closed, the pressure chamber  46  is sufficiently sealed to allow air to pressurize in the pressure chamber  46  when the pump  42  is reciprocated. The valve  56  is in mechanical communication with the distal end  62  of a rod  60 , which, in the present example, causes retraction of the valve  56  when the rod  60  is moved proximally. Alternatively, an additional lever or linkage may be added such that the valve  56  is proximally retracted when the rod  60  is moved distally. 
     In the present example, the hole  54  acts as a launch feature configured to transmit pressurized air to the glider  10 . However, it will be appreciated that an alternative pressurized medium may be used, such as, by way of example only, water. It will also be appreciated that an alternative launch feature may be used to transmit a pressurized medium to the glider  10 , such as, by way of example only, a hose. 
     The proximal end  64  of the rod  60  is comprised of a piston member  66 . This piston member  66  is slidably disposed within a piston cylinder  70  at the proximal wall  72  of the pressure chamber  46 . At the proximal end of the piston cylinder  70 , there is a hole  74  formed through the proximal wall  72 . The proximal end of the piston member  66  has a protuberance  68  that is configured to fit, in part, through the hole  74 . 
     In the present example, the rod  60  comprises the axis of the piston member  66 , and the piston member  66  is slidably engaged with the rod  60 . The proximal end  62  of the rod  60  has an “e”-clip  69  configured, in part, to keep the piston member  66  from sliding off of the proximal end  62  of the rod  60  when the launcher  40  is fired. It will be appreciated by those of ordinary skill in the art that other configurations may be used. 
     A seal exists between the piston member  66  and wall of the piston cylinder  70 , such that pressure may not escape from the pressure chamber  46  through the proximal hole  74 . Nevertheless, a buildup of pressure within the pressure chamber  46  will urge the piston member  66  to move proximally in the piston cylinder  70 . In order to move the piston member  66  proximally in the piston cylinder  70  in the present example, the air pressure must exert enough force to overcome the opposing force of the piston spring  71 , which urges the piston member  66  distally. It will be appreciated that other configurations may be used. An advantage of the piston spring  71  is that it dictates a minimum amount of pressure that must be built up in the pressure chamber  46  before a launch will be permitted. When the pressure in the pressure chamber  46  is too low to overcome the force of the piston spring  71  exerted on the piston member  66 , a launch may not be achieved; whereas a launch may be achieved when the pressure in the pressure chamber  46  is above this minimum dictated by the piston spring  71 . This feature may prevent low pressure launches of the glider  10  and reduces the potential for damage to the glider  10  when the glider  10  has not obtained a high enough altitude for the wings  20  to open or sweep forward. 
     In the present example, the launcher  40  has a trigger mechanism  80  that controls the proximal retraction of the rod  60 . As shown in  FIGS. 6 through 9 , the trigger mechanism  80  is comprised of a trigger button  82 , a trigger stem  84 , a linkage  86 , a plate  88 , a ball  90 , and a cup  92 . The linkage  86  has an opening  94  formed therethrough and a flange  96 . The linkage  86  is attached to the proximal side of the proximal wall  72  of the pressure chamber  46 ; and the linkage  86  is configured to slide up and down along this side. The opening  94  in the linkage  86  is at least the same size as the hole  74  formed through the proximal wall  72  of the pressure chamber  46 , and the linkage  86  may be slid to a position where the opening  94  in the linkage  86  is aligned with the hole  74  formed through the proximal wall  72  of the pressure chamber  46 . When this hole  74  and opening  94  are so aligned, the protuberance  68  at the proximal end of the piston member  66  may fit, in part, through both holes. In the present example, this alignment will be required for the rod  60  to be sufficiently moved proximally to retract the valve  56  and thereby result in the launch of the glider  10 . This proximal movement of the rod  60  will occur when (a) the force of air pressure on the piston member  66  is greater than the opposing force of the piston spring  71 , (b) the opening  94  in the linkage  86  is sufficiently aligned with the hole  74  in the proximal wall  72  of the pressure chamber  46 , and (c) the air pressure on the piston member  66  causes the piston member  66  to slide proximally along the rod  60 , such that part of the protuberance  68  passes through the hole  74  and the opening  94 , such that the protuberance  68  impinges a proximal force on the “e”-clip  69  at the proximal end  64  of the rod  60 . Other variations will be apparent to those of ordinary skill in the art. 
     A spring  98  at the bottom of the linkage  86  urges the linkage  86  to slide upward by default, such that the linkage opening  94  and the hole  74  in the proximal wall  72  of the pressure chamber  46  are not aligned. The linkage  86  may be slid downward to align the opening  94  and hole  74  by the trigger stem  84  exerting force against the linkage flange  96 . An orientation-sensitive safety feature permits this exertion of force by the trigger stem  84  only when the launch tube  50  is oriented approximately within a particular operable angular range. 
     As shown in  FIGS. 6 through 10 , the orientation-sensitive safety feature of the trigger mechanism  80  is comprised of the plate  88 , the ball  90 , the cup  92 , and protrusions  100  on the trigger stem  84 . The top surface  102  of the plate  88  has protrusions  106  that engage with the protrusions  100  on the trigger stem  84 . The ball  90  rests on the inner base surface  108  of the cup  92 , and is permitted to roll on the surface  108 . Two springs  112  are in the wall of the cup  92 , urging the plate  88  away from the inner base surface  108  of the cup  92 . The springs  112  thus urge engagement of the protrusions  106  on the top surface  102  of the plate  88  with the protrusions  100  on the trigger stem  84 . 
     The inner base surface  108  of the cup  92  is curved, such that the ball  90  will be generally centered on the surface  108  when the launch tube  50  is oriented approximately within a particular operable angular range. By way of example only, the surface  108  may be generally hyperbolic, semi-circular, conical, frusto-conical, or of any suitable curvature. The bottom surface  104  of the plate  88  has a groove  110  centered therein, such that the ball  90  will be positioned underneath the groove  110  when the ball  90  is generally centered on the inner base surface  108  of the cup  92 . As shown in  FIGS. 9 and 10 , this will occur when the launch tube  50  is oriented approximately within the operable angular range. 
     As shown in  FIG. 8 , when the launch tube  50  is not oriented approximately within the particular angular range, the ball  90  is not generally centered on the inner base surface  108  of the cup  92 . Thus, the ball  90  is not positioned under the groove  110 . In this positioning, the ball  90  will prevent the plate  88  from moving downward far enough to allow the protrusions  106  on the top surface  102  of the plate  88  to disengage with the protrusions  100  on the trigger stem  84 . Without this disengagement, the trigger stem  84  will not be permitted to exert force on or otherwise communicate with the linkage flange  96 , and hence, the glider  10  may not be launched. 
     As shown in  FIGS. 9 and 10 , when the launch tube  50  is oriented approximately within the operable angular range, the ball  90  will be generally centered on the inner base surface  108  of the cup  92  and positioned underneath the groove  110 , which allows the plate  88  to move downward far enough such that the protrusions  106  on the top surface  102  of the plate  88  may disengage with the protrusions  100  on the trigger stem  84 . Upon this disengagement, as shown in  FIG. 10 , the trigger stem  84  may exert force against the linkage flange  96 . This force may be exerted by actuation of the trigger button  82 , which is in mechanical communication with the trigger stem  84 . 
     The safety feature of the trigger mechanism  80  may thus provide tactile feedback to a user indicating whether the launch tube  50  is oriented within the operable angular range. By way of example only, the trigger mechanism  80  may be configured such that the glider  10  or other projectile may be launched only when the launch tube  50  is oriented between approximately 60 and 85 degrees relative to the ground. As another example, the operable angular range may be between approximately 55 and 70 degrees, or 65 to 80 degrees. Alternatively, the trigger mechanism  60  may be configured such that the glider  10  or other projectile may be launched only when the launch tube  50  is oriented within any other angular range. 
     The launcher  40  may be configured such that the handle  78  is oriented generally vertically when the launch tube  50  is oriented within the operable angular range. Such a configuration may thereby provide a user visual feedback to gauge approximately whether the launch tube  50  is oriented within the operable angular range. Alternatively, the launcher  40  may be configured such that the handle  78  is oriented any other way when the launch tube  50  is oriented within the operable angular range. 
     While a ball  90  is used in the illustrative embodiment of an orientation-sensitive safety mechanism, it will be understood by those of ordinary skill in the art that any other means may be used to prevent launching when the launch tube  50  is not oriented within the operable angular range. Such an alternative orientation-sensitive safety mechanism may employ the use of, by way of example only, a lever or pendulum or other orientation-sensitive blocking means. It will also be appreciated that the safety feature of the present invention may be used with other trigger mechanisms. 
     The exterior of the launch tube  50  is generally the same shape as the interior of the glider&#39;s hollow fuselage  12  and is of a size that allows the launch tube  50  to slide into the glider&#39;s fuselage  12 . The fit between the fuselage  12  and the launch tube  50  will preferably be tight enough to allow most of the air escaping the launch tube  50  through the hole  54  to propel the glider  10 . While the present example discloses a cylindrical launch tube  50 , it will be appreciated by those of ordinary skill in the art that any suitable shape may be used, such as, by way of example only, a triangular or square tube. Where an alternative shape is used for the launch tube  50 , the inside of the glider&#39;s fuselage will preferably be of the same alternative shape, such that the fit between the fuselage and launch tube will be tight enough to allow most of the air escaping the launch tube through the hole  54  to propel the glider. 
     The pump  42  in the present example has a relief valve feature  120  in its proximal end. This relief valve feature  120  is comprised of a proximal hole  122  at the proximal end of the pump  42 , a diaphragm  124 , a spring  126 , and a relief hole  128 . The spring  126  urges the diaphragm  124  against the proximal hole  122 . The force of the spring  126  is strong enough to allow the pump  42  to function normally, such that reciprocation of the pump  42  may pressurize air in the pressure chamber  46 . However, when the air pressure is strong enough to overcome the force of the spring  126 , air may escape through the proximal hole  122 , past the diaphragm  124 , and out the relief hole  128  to the outside of the launcher  40 . Thus, the relief valve feature  120  may provide a threshold for the pressure in the pressure chamber  46  such that, when the pressure is below the threshold, the pump  42  will function normally; whereas when the pressure is above the threshold, reciprocation of the pump  42  will not cause the pressure to increase. The threshold may be dictated in part by the strength of the spring  126 . Accordingly, a relief valve feature  120  may provide a means to prevent over pressurization of the pressure chamber  46 . 
     In addition, a glider guide ramp  76  is located around the exterior base of the launch tube  50 . In part, this guide ramp  76  prevents the glider  10  from rotating about the axis of the launch tube  50  when the glider  10  is fully engaged with the launch tube  50 . It will be appreciated that a launcher  40  need not include this guide ramp  76 , particularly when the launch tube  50  is non-cylindrical. 
     In the present example, the launch tube  50  acts, in part, as a support member configured to be received by the hollow fuselage  12  of the glider  10 ; while the fuselage  12  acts as a proximally-open receptacle configured to receive such a support member. It will be appreciated, however, that an alternative support member configuration and/or receptacle configuration may be used. 
     While the launcher  40  in the present example is disclosed in the context of a glider  10 , it will also be appreciated by those of ordinary skill in the art that, with or without obvious alterations, the launcher  40  may be used to launch a variety of projectiles. Thus, it is not intended that the scope of the invention be limited to the launching of gliders  10 . It will also be understood that a launcher  40  having an orientation-sensitive safety feature such as that in the trigger mechanism  60  of the present example may be used to launch any type of projectile. In addition, it will be appreciated that a launcher having a trigger mechanism  60  such as the one disclosed herein need not launch projectiles pneumatically. Indeed, an orientation-sensitive safety feature having aspects that are the same as or functionally equivalent to those comprising the trigger mechanism  60  of the present example may be employed in a launcher that uses, by way of example only, combustion, electromagnet pulse, springs, or any other means to launch projectiles. 
     In use, the fuselage  12  of the glider  10  is slid onto the launch tube  50 . The wings  20  are then rotated such that they are above or near the fuselage  12 , while the annular member  28  is positioned such that the clasp  34  engages the tabs  34  of the pivot support members  24 , thereby holding the wings  20  in the position above or near the fuselage  12 . While a user holds the launcher  40  by the handle  78  with one hand, the pump  42  is reciprocated with the other hand, providing the desired air pressure to the pressure chamber  46 . Alternatively, the pump  42  may be reciprocated to provide desired air pressure to the pressure chamber  46  prior to the glider  10  being slid onto the launch tube  50 . As pressure builds in the pressure chamber  46 , the piston member  66  at the proximal end  64  of the rod  60  is urged proximally by the air pressure. However, the rod  60  does not move proximally because the opening  94  in the linkage  86  is not aligned with the hole  74  formed through the proximal wall  72  of the pressure chamber  46 . Thus, passage of the protuberance  68  at the proximal end of the piston member  66  is prevented by the linkage  86 . 
     The launcher  40  is then held in a position such that the launch tube  50  is oriented within the operable angular range, allowing the ball  90  to be generally centered on the inner base surface  108  of the cup  92  and positioned underneath the groove  110 . The protrusions  106  on the top surface  102  of the plate  88  may then disengage with the protrusions  100  on the trigger stem  84 , allowing the trigger stem  84  to exert force on the linkage flange  98 . When the trigger button  82  is actuated, the trigger stem  84  exerts force on the linkage flange  96 , causing the linkage  86  to slide downward. When the linkage  86  has thus slid downward, the opening  94  in the linkage  86  becomes aligned with the hole  74  in the proximal wall  72  of the pressure chamber  46 , permitting the protuberance  68  at the proximal end of the piston member  66  to fit, in part, through both openings. With this fit so permitted, the pressure built up in the pressure chamber  46  causes the piston member  66  to slide along the rod  60  proximally, such that the protuberance  58  impinges a force against the “e”-clip  69  at the proximal end  64  of the rod  60 . This transfer of force causes the rod  60  to move proximally, which retracts the valve  56  at the distal end  52  of the launch tube  50 , permitting the pressurized air to pass through the hole  54  at the distal end  52  of the launch tube  50 . The pressurized air is thus impinged against the glider  10 , thereby causing the glider  10  to be propelled into flight. When the force of the spring  58  acting against the valve  56  at the distal end  52  of the launch tube  50 , and the force of the piston spring  71 , overcome the pressure force urging the piston member  66  to move proximally, the rod  60  will move distally, such that the valve  56  at the distal end  52  of the launch tube  50  again covers the hole  54  at the distal end  52  of the launch tube  50 . The piston spring  71  will continue to urge the piston member  66  distally, such that the part of the protuberance  68  is no longer in the opening  94  of the linkage  86 . With the protuberance  68  absent from the opening  94 , the linkage spring  98  urges the linkage  86  upward again, such that the opening  94  in the linkage is no longer aligned with the hole  74  in the proximal wall  72  of the pressure chamber  46 . 
     Upon the sudden change in glider  10  velocity caused by the launch, the annular member  28  will rotate forward such that the clasp  36  is no longer engaged with the tabs  34  on the pivot support members  24 . However, drag forces acting upon the glider  10  may initially hold the wings  20  in a retracted position above or near the fuselage  12 . At approximately the apex of flight, the resilient tension in the rubber band  30  that is connected to the hooks  32  on the pivot support members  24  will overcome the drag and will draw the hooks  32  on the pivot support members  24  together, thereby causing the wings  20  to sweep to a fully extended position. The glider  10  will eventually glide to a safe landing. 
     The above components are preferably made of one or more polymeric materials. However, the components may be made of any lightweight resilient or other material. By way of example only, the nose cone  14  may be made of a soft foam material to prevent damage. Additionally, pieces of aluminum or other malleable, non-resilient material may be added on or near wing or tail stabilizer edges as a means for adjusting the wings or tail stabilizers. 
     It is also understood that any suitable means other than air propulsion, such as, by way of example only, liquid, solid fuel, a slingshot, combustion, or electromagnetic pulse may be used to propel the glider  10 . 
     It will be apparent to those of ordinary skill in the art that while a preferred embodiment of the invention has been disclosed in detail, numerous other modifications and improvements may be made thereon. Some alternate embodiments of the invention are described below. 
     For example, in an alternate embodiment of the wing sweep mechanism, a glider consistent with aspects of the invention may use a timing mechanism to deploy the wings during flight. A timing device and a locking device for holding the wings back may comprise an alternate wing sweep mechanism that may be mounted in the forward section of the glider. The locking device may initially hold the wings proximate to the fuselage to provide a low drag configuration for the launching of the glider. An off-the-shelf timer having a winding knob may be used as the timing device to release the wings and/or cause extension of the wings subsequent to launch. The wings may be urged forward by any suitable means, such as, by way of example only, one or more resilient members or gears. The glider may be launched by any suitable launcher, such as, by way of example only, a sling shot or a pneumatic launcher. 
     In another embodiment of the wing sweep mechanism, a substitute for the annular member is a catch comprised of a clasp and engagement tabs. The catch is hingedly attached to the body collar. The weight distribution of the catch encourages it to rotate freely forward, relative to the fuselage, such that the clasp is drawn away from the fuselage. When the glider is slid onto the launch tube, the tabs engage an engagement ramp on the launch tube, which rotates the catch such that the clasp is drawn towards the fuselage. When the clasp is drawn toward the fuselage, the pivot support members may be rotated to a position where the wings are above the fuselage, wherein the clasp will engage the pivot support members and thereby hold the wings above or near the fuselage in a locked position. When the glider is launched, the tabs disengage the engagement ramp, which allows the catch to rotate, such that the clasp disengages with the pivot support members. With the locking mechanism in this unlocked position, the wing sweep mechanism will urge the wings to the extended position. 
     In yet another embodiment of the wing sweep mechanism, the rotation of the annular member to release the pivot support members may be controlled by rubber bands. A rubber band, of appropriate strength, may be selected to hold the clasp in a position nearest the fuselage such that the clasp is able to engage and hold the pivot support members. Upon launch, the rubber band will initially be able to oppose the force of gravity acting on the catch. However, the rubber band will eventually weaken and stretch allowing the annular member to rotate such that the clasp is drawn away from the fuselage, releasing the pivot support members. In this or other alternative configurations, an interface feature on the launcher, such as an engagement ramp, may not be necessary to change a locking mechanism from a locked to unlocked position. Alternatively, other interface features may be used. 
     A glider may alternatively incorporate an actuating mechanism that is triggered by the sudden acceleration experienced during launching, such that the actuating mechanism unlocks the wings and/or causes the extension of the wings at launch. As another example, a wing sweep mechanism may include an extension spring or a compression spring coupled between the fuselage and a wing, or between wings, to resiliently urge the wings to an extended position. 
     In an alternate embodiment of the trigger mechanism  60 , the trigger mechanism may act as a fluid gate by controlling the transfer of air for example, between a pressure chamber and the launch tube, rendering a valve  52  at a distal end of the launch tube unnecessary. In this alternate embodiment, a spring-loaded valve prevents air from escaping the pressure chamber into the launch tube. The trigger mechanism may include a ball in a chamber above the valve and a trigger button above the chamber. The chamber may be configured such that the ball is seated directly between the trigger button and the valve only when the launcher is oriented within a particular angular range. When the launcher is so oriented, depression of the trigger button will force the ball against the valve, opening the same and allowing pressurized air in the pressure chamber to escape into the launch tube and thereby launch the glider. When the launcher is not oriented properly, and thus the ball is not seated directly between the trigger button and the valve, depression of the trigger button will not cause the opening of the valve and the glider will not be launched. As an alternative to a ball in a chamber, a pendulum, lever, or any other orientation-sensitive mechanism or configuration may be used. 
     In yet another alternate embodiment of the trigger mechanism, a vent hole is used to release pressurized air away from the glider when the trigger button is pressed while the launcher is not oriented within a particular angular range. This may be accomplished by providing a ball in a chamber having a vent hole, such that the ball covers the vent hole when the launcher is oriented within a particular angular range. When the trigger button is pressed while the launcher is not oriented within the particular angular range, the ball will not be covering the vent hole, and thus the pressurized air will escape through the vent hole rather than launch the glider. When the launcher is oriented within the particular angular range, the ball will cover the vent hole, allowing the pressurized air to launch the glider. As an alternative to a ball, any other device that may be used to close off fluid connection to a vent hole by way of gravitational force, such as a lever or a pendulum, may be utilized. 
     It will also be appreciated that the launcher  40  may further comprise a pressure chamber. In such an embodiment, the launch tube  44  may not need to be sealed, and may merely act as a member to support the glider  10  and/or act as a launch guide. It will be further appreciated that, where a pressure chamber or the like is used, the launch tube  44  may serve as a communicator of the pressurized fluid. In addition, while the present example discloses a manual air pump  42  as a pneumatic pressure source, any alternative pneumatic pressure source may be used, such as, by way of example only, an automatic air compressor or other suitable source. 
     In summary, numerous benefits have been described which result from employing the concepts of the invention. While the present invention has been illustrated by the description of several embodiments and while the illustrative embodiments have been described in considerable detail, it is not the intention of the applicant to restrict or in any way limit the scope of the appended claims to such detail. The foregoing description of one or more embodiments of the invention has been presented for purposes of illustration and description. It is not intended to be exhaustive or to limit the invention to the precise form disclosed. Obvious modifications or variations are possible in light of the above teachings without departing from the invention. It should be understood that every structure described above has a function and such structure can be referred to as a means for performing that function. The one or more embodiments were chosen and described in order to best illustrate the principles of the invention and its practical application to thereby enable one of ordinary skill in the art to best utilize the invention in various embodiments and with various modifications as are suited to the particular use contemplated. Accordingly, it is intended that the invention be limited only by the spirit and scope of the appended claims.