초록 ▼

A small caliber guided projectile (20) includes a maneuvering unit (22) having a forward opening inlet (36) which provides diffused air to a flow control mechanism (70) prior to exhausting such air through diametrically opposed exhaust nozzles (74, 76). The flow control mechanism (70) includes a pri

A small caliber guided projectile (20) includes a maneuvering unit (22) having a forward opening inlet (36) which provides diffused air to a flow control mechanism (70) prior to exhausting such air through diametrically opposed exhaust nozzles (74, 76). The flow control mechanism (70) includes a primary flow passageway (78) and an upper orifice switching device (100) for controlling bypass flow to one of the exhaust nozzles (76). An orifice switching device (120) controls bypass flow to the other exhaust nozzle (74). In one embodiment, a small, rearward facing step or other means of vortex generation, such as boundary layer energization, is located upstream of the discharge of the flow through switching devices into the nozzles. When the switching devices are closed, flow over the rearwardly facing steps generates a small vortex which enhances flow attachment as a result of the Coanda effect and increases flow through the nozzle. Opening of the orifice switching device results in aspiration through the nozzle, thereby impeding flow. By controlling the respective switching devices, flow through the opposed nozzles may be varied to produce a resultant lateral force on the projectile, permitting control of the trajectory of the projectile.

대표청구항 ▼

1. A guided projectile comprising: a projectile housing with diametrically opposed divergently oriented guidance nozzles mounted therein; a supersonic external compression air inlet and subsonic diffuser for supplying air to the guidance nozzles; and flow control means for selectively diverting

1. A guided projectile comprising: a projectile housing with diametrically opposed divergently oriented guidance nozzles mounted therein; a supersonic external compression air inlet and subsonic diffuser for supplying air to the guidance nozzles; and flow control means for selectively diverting air flow through said nozzles permitting input of lateral forces to the projectile, said flow control means comprising a bifurcated discharge arrangement with vortex generator means for generating a small vortex within each nozzle and downstream of said generator means to cause flow entrainment and attachment to the wall of the nozzle, thereby increasing flow through a selected one of said nozzles, said flow control means further comprising a valve for selectively directing air into the non-selected nozzle downstream of said vortex generator means to permit aspiration and prevention of flow attachment to the boundary wall of the non-selected nozzle to impede flow through the nozzle. 2. The guided projectile according to claim 1 wherein said inlet is a forward opening inlet. 3. The guided projectile according to claim 1 further comprising control means for controlling said valve to vary flow through said nozzle and control the lateral force on the projectile. 4. The guided projectile according to claim 1 further comprising means for selectively switching said valve from an open to a closed position in response to guidance control means for controlling the trajectory of the projectile. 5. The guided projectile according to claim 1 wherein said vortex generator means comprises a rearward facing step for generating a small vortex in the nozzle to cause flow entrainment and attachment to the wall of the nozzle. 6. The guidance nozzle according to claim 5 wherein said flow control means further comprises a controllable valve for selectively directing air into the guidance nozzle downstream of said rearward facing step to prevent flow attachment to the boundary wall of the nozzle to impede flow through the nozzle. 7. The guided projectile according to claim 6 further comprising means for selectively switching said valve from an open to a closed position in response to guidance control means for controlling the trajectory of the projectile. 8. The guided projectile according to claim 1 wherein said nozzles have adjacent inlets and exhaust on opposite sides of said projectile, both nozzles receiving flow from the forward opening inlet such that impedance of flow through one nozzle increases flow through the other. 9. The guided projectile according to claim 1 further comprising an explosive mechanism concentrically mounted within said housing with said inlet formed around said explosive mechanism. 10. The guided projectile according to claim 1 wherein said projectile comprises two guidance nozzles mounted on opposite sides of said housing and directed outwardly at a fixed selected angle from the longitudinal axis of the projectile housing. 11. A method of guiding a projectile comprising: directing air from a supersonic inlet to a pair of guidance nozzles oriented at a predetermined angle to the longitudinal axis of the projectile; and selectively controlling flow through said nozzles to control the trajectory of the projectile by generating a flow attaching vortex in a selected one of said guidance nozzles to cause flow attachment to the wall of the nozzle and simultaneously preventing vortex formation in the other nozzle, thereby increasing flow through the selected nozzle. 12. The method according to claim 11 wherein said prevention of vortex formation comprises: aspirating flow through the non-selected nozzle to prevent the development of a flow attaching vortex therein to impede flow therethrough. 13. The method according to claim 12 wherein said aspirating step comprises: selectively diverting a portion of the inlet air through a valve means and reintroducing said air downstream in one of said nozzles. 14. The method according to claim 11 wherein said step of controlling flow through the nozzle includes generating a flow attaching vortex in the nozzle using a rearward facing step near the mouth of the nozzle to generate a small vortex downstream thereof to cause flow attachment to the wall of the nozzle, thereby increasing flow through the nozzle. 15. The method according to claim 14 wherein said step of controlling flow through the nozzle further comprises controlling the flow of fluid adjacent said rearward facing step to control the development of a flow attachment vortex in the nozzle. 16. The method according to claim 11 further comprising: selectively bleeding a portion of air from the inlet through valve means for preventing the generation of a vortex in one of the guidance nozzles to control flow through said nozzle, thereby imparting a lateral guiding force on the projectile. 17. The method according to claim 16 further comprising: controlling the bleeding of air through the valve means to said guidance nozzles to control the direction of said projectile. 18. The method according to claim 16 wherein said step of selectively bleeding of air through the valve means comprises controlling a valve structure in a bypass orifice. 19. A method of guiding a projectile comprising: channeling inlet air past a vortex generator to selectively generate a vortex prior to exhausting the air through a first and second guidance nozzle, said vortex generation causing the enhancement of flow through the guidance nozzle; and selectively diverting air through a bistatic controllable valve means to a point downstream of the vortex generator and into the flow through the non-selected guidance nozzle, said injection preventing the generation of a vortex in the non-selected guidance nozzle to impede flow therethrough and direct flow through the selected nozzle, thereby imparting a lateral force on the projectile. 20. The method according to claim 19 wherein the vortex generation is accomplished by passing air from the inlet over a rearwardly facing step mounted adjacent to the guidance nozzle inlet. 21. The method according to claim 19 further comprising: selectively switching said valve means from an open to a closed position in response to guidance control means to control the trajectory of the projectile. 22. A guided projectile comprising: a projectile housing with diametrially opposed divergently oriented guidance nozzles mounted therein; a supersonic external compression air inlet for supplying air into said projectile housing; means for diverting said air through one of or dividing substantially equally between said divergently oriented guidance nozzles; means for generating and controlling the formation of a vortex in one or preventing vortex generation in both of said nozzles downstream of said diverting means for causing either flow attachment to the wall of a selected nozzle thereby entraining all inlet flow through said selected nozzle to control the lateral force on the projectile or permitting division of the flow between the nozzles to negate lateral forces and thereby guide the projectile, said generating and controlling means further comprising a bistatic fluidically controlled valve for selectively directing an amount of air into a non-selected one of the guidance nozzles downstream of said vortex generator means to aspirate and thereby prevent flow attachment to the boundary wall of said non-selected nozzle to impede flow through the nozzle. 23. The guided projectile according to claim 22 further comprising control means for controlling said valve to control flow through said nozzle and control the lateral force on the projectile. 24. The guided projectile according to claim 22 further comprising means for selectively switching said valve to either one or the other of said nozzles to impede flow through the non-selected nozzle or closing said valve to both said nozzles to permit equal flow through both of said nozzles in response to guidance control means for controlling the trajectory of the projectile. 25. The guided projectile according to claim 22 wherein said vortex generator means comprises a rearward facing step for generating a small vortex in the nozzle to cause flow attachment to the wall of the nozzle. 26. The guidance nozzle according to claim 25 wherein said flow control means further comprises a bistatic fluidically controlled valve for selectively directing air into a non-selected one of the guidance nozzles downstream of said rearward facing step to aspirate and thereby prevent flow attachment to the boundary wall of said selected nozzle to impede flow through the nozzle. 27. The guided projectile according to claim 26 further comprising means for selectively switching said valve to either one or the other of said nozzles to impede flow through the non-selected nozzle or to permit equal flow through both of said nozzles in response to guidance control means for controlling the trajectory of the projectile.