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A vehicle, such as a missile, with a pilot valve system controls the vehicle's thrust valves despite a hostile propellant gas environment. The pilot valve system can have one or more pilot valves. Using refractory elements, the pilot valve ball reciprocates between a supply seat and a vent seat whic

A vehicle, such as a missile, with a pilot valve system controls the vehicle's thrust valves despite a hostile propellant gas environment. The pilot valve system can have one or more pilot valves. Using refractory elements, the pilot valve ball reciprocates between a supply seat and a vent seat which is subject to the filtered inflow of propellant thrust gases. When open, the pilot valve allows the stray thrust gas to communicate to a control chamber which closes a poppet against a valve seat in the nozzle. When an associated solenoid closes the pilot valve by pushing the pilot valve ball against the supply seat, the control chamber is vented to ambient. The poppet may then travel into the cylinder bore and the nozzle is opened to exhaust propellant gases and exert lateral thrust on the vehicle. Certain nozzle thrust geometries provide useful vehicle guidance.

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1. A pilot valve for redirecting thrust to control a thrust valve, comprising:a housing having a supply valve seat and a vent valve seat defining an internal valve chamber; the supply valve seat defining a thrust inlet opening; the vent valve seat defining a pressure vent opening; the valve chamber

1. A pilot valve for redirecting thrust to control a thrust valve, comprising:a housing having a supply valve seat and a vent valve seat defining an internal valve chamber; the supply valve seat defining a thrust inlet opening; the vent valve seat defining a pressure vent opening; the valve chamber in communication with the thrust inlet opening, the pressure vent opening, and configured to communicate with the thrust valve; a valve gate moveable between the supply valve and vent valve seats to selectably seal either the supply valve seat or the vent valve seat; and a valve gate control mechanism operably coupled to the valve gate; whereby when the valve gate is seated in the vent valve seat, thrust pressure is applied to the thrust valve, the thrust being ceased when the valve gate is seated in the supply valve seat, whereupon any residual thrust pressure on the thrust valve is vented through the pressure vent. 2. A pilot valve for redirecting thrust to control a thrust valve as set forth in claim 1, further comprising:the supply valve seat, the vent valve seat, and the valve gate all being made at least in part of a refractory material. 3. A pilot valve for redirecting thrust to control a thrust valve as set forth in claim 2, wherein the refractory material is selected from the group consisting of rhenium, tungsten, niobium, tantalum, molybdenum, and alloys thereof.4. A pilot valve for redirecting thrust to control a thrust valve as set forth in claim 1, further comprising:a vent housing disposed between and spaced apart from the vent valve seat and the valve gate control mechanism to thereby define primary and secondary vents, respectively, the vent housing protecting the valve gate control mechanism from thrust gasses exhausted through the pressure vent. 5. A pilot valve for redirecting thrust to control a thrust valve as set forth in claim 1, wherein the valve gate control mechanism further comprises:a solenoid; and a rod coupling the valve gate to the solenoid; whereby activation of the solenoid urges the valve gate against the supply valve seat. 6. A pilot valve for redirecting thrust to control a thrust valve as set forth in claim 1, further comprising:a thrust filter disposed inline with the supply valve seat; whereby thrust gasses transmitted to the supply valve seat are first filtered by the thrust filter to reduce particulates and condensables. 7. The pilot valve for redirecting thrust to control a thrust valve as set forth in claim 1, further comprising:the housing being constructed of ablative materials. 8. The pilot valve for redirecting thrust to control a thrust valve as set forth in claim 7, further comprising:the ablative material being phenolic. 9. A pilot valve for redirecting thrust to control a thrust valve, comprising:a rhenium-based supply valve seat and a rhenium-based vent valve seat defining a rhenium-based valve chamber; the supply valve seat defining a thrust inlet opening; the vent valve seat defining a pressure vent opening; the valve chamber in communication with the thrust inlet opening, the pressure vent thrust opening, and configured to communicate with the thrust valve; a rhenium-based valve ball moveable between the supply valve and vent valve seats to selectably seal either the supply valve seat or the vent valve seat; a solenoid operably coupled to the valve ball by a rhenium-based rod such that activation of the solenoid urges the valve ball against the supply valve seat; a vent housing disposed between and spaced apart from the vent valve seat and the solenoid to thereby define primary and secondary vents, respectively, the vent housing protecting the solenoid from thrust gasses exhausted through the pressure vent; and a thrust filter disposed inline with the supply valve seat such that thrust gasses transmitted to the supply valve seat are first filtered by the thrust filter to reduce particulates and condensables; whereby when the valve ball is seated in the vent valve seat, thrust pressure is applied to the thrust valve, the thrust being ceased when the valve ball is seated in the supply valve seat, whereupon any residual thrust pressure on the thrust valve is vented through the pressure vent. 10. The pilot valve for redirecting thrust to control a thrust valve as set forth in claim 9, further comprising:the vent housing being constructed of ablative material. 11. The pilot valve for redirecting thrust to control a thrust valve as set forth in claim 10, further comprising:the ablative material being phenolic. 12. A thrust valve for controllably directing thrust, comprising:a nozzle having a mouth, a throat, and an annular area around the mouth being generally flat; a block defining a cylinder; a poppet confined between the nozzle mouth and the block, the poppet traveling in the cylinder to open and close the nozzle mouth; the top of the poppet being generally flat and wider than the nozzle mouth, the poppet sealing the nozzle mouth when the poppet top is pressed against the nozzle mouth; and the cylinder configured to communication with a pilot valve that controls pressure between the poppet and the block, pressure applied via the pilot valve urging the poppet against the nozzle mouth; whereby the nozzle may be opened and closed by the pilot valve and thrust is selectably ejected by the thrust valve. 13. A thrust valve for controllably directing thrust as set forth in claim 12, further comprising:a cylinder lining that lines the cylinder; the poppet traveling in the cylinder lining to protect the cylinder. 14. A thrust valve for controllably directing thrust as set forth in claim 13, wherein the cylinder lining further comprises a refractory material selected from the group consisting of rhenium, tungsten, niobium, tantalum, molybdenum, and alloys thereof.15. A thrust valve for controllably directing thrust as set forth in claim 12, wherein the poppet further comprises:a top bevel mediating a wider poppet body diameter with a narrower poppet top diameter; and a bottom bevel circumscribing a bottom of the poppet to define an annular channel about the poppet when the poppet is seated in the cylinder. 16. A thrust valve for controllably directing thrust as set forth in claim 12, wherein the poppet further comprises:the poppet defining a piston ring groove circumscribing the poppet and for receiving a ring to enable better sealing about the poppet as it travels in the cylinder. 17. A thrust valve for controllably directing thrust as set forth in claim 12, wherein the poppet further comprises:rhenium. 18. The thrust valve for controllably directing thrust as set forth in claim 12, further comprising:the nozzle being constructed of ablative material. 19. The thrust valve for controllably directing thrust as set forth in claim 18, further comprising:the ablative material being phenolic. 20. A thrust valve for controllably directing thrust, comprising:a nozzle having a mouth, a throat, and an annular area around the mouth being generally flat; a block defining a cylinder; a rhenium-based cylinder lining that lines and protects the cylinder; a rhenium-based, poppet confined between the nozzle mouth and the block, the poppet traveling in the cylinder lining to open and close the nozzle mouth; the top of the poppet being generally flat and wider than the nozzle mouth, the poppet sealing the nozzle mouth when the poppet top is pressed against the nozzle mouth; a top bevel mediating a wider poppet body diameter with a narrower poppet top diameter; a bottom bevel circumscribing a bottom of the poppet to define an annular channel about the poppet when the poppet is seated in the cylinder; the poppet defining a piston ring groove circumscribing the poppet and for receiving a ring to enable better sealing about the poppet as it travels in the cylinder; the cylinder in communication with a pilot valve that controls pressure between the poppet and the block, pressure applied via the pilot valve urging the poppet against the nozzle mouth; whereby the nozzle is opened and closed by the pilot valve's control of the poppet and thrust is selectably ejected by the thrust valve. 21. The thrust valve for controllably directing thrust as set forth in claim 20, further comprising:the nozzle being constructed of ablative material. 22. The thrust valve for controllably directing thrust as set forth in claim 21, further comprising:the ablative material being phenoic. 23. A thrust valve system, comprising:a thrust valve having a poppet traveling in a cylinder; a pilot valve in communication with the cylinder and a source of thrust; the pilot valve controlling operation of the poppet by controlling thrust pressure between the poppet and the cylinder, the operation of the poppet controlling the operation of the thrust valve; whereby thrust is diverted by the pilot valve to control the thrust valve. 24. A thrust valve system as set forth in claim 23, wherein the thrust valve further comprises:a nozzle having a mouth, a throat, and an annular area around the mouth being generally flat; a rhenium-based cylinder lining that lines and protects the cylinder; the poppet being a rhenium-based poppet confined between the nozzle mouth and the block, the poppet traveling in the cylinder lining to open and close the nozzle mouth; the top of the poppet being generally flat and wider than the nozzle mouth, the poppet sealing the nozzle mouth when the poppet top is pressed against the nozzle mouth; a top bevel mediating a wider poppet body diameter with a narrower poppet top diameter; a bottom bevel circumscribing a bottom of the poppet to define an annular channel about the poppet when the poppet is seated in the cylinder; the poppet defining a piston ring groove circumscribing the poppet and for receiving a ring to enable better sealing about the poppet as it travels in the cylinder; the cylinder configured to communicate with a pilot valve that controls pressure between the poppet and the block, pressure applied via the pilot valve urging the poppet against the nozzle mouth; whereby the nozzle is opened and closed by the pilot valve's control of the poppet and thrust may be selectably ejected by the thrust valve. 25. A thrust valve system as set forth in claim 23, wherein the pilot valve further comprises:a rhenium-based supply valve seat and a rhenium-based vent valve seat defining a rhenium-based valve chamber; the supply valve seat defining a thrust inlet opening; the vent valve seat defining a pressure vent opening; the valve chamber in fluid communication with the thrust inlet, the thrust valve, and the pressure vent; a rhenium-based valve ball moveable between the supply valve and vent valve seats to selectably seal either the supply valve seat or the vent valve seat; a solenoid operably coupled to the valve ball by a rhenium-based rod such that activation of the solenoid urges the valve ball against the supply valve seat; a vent housing disposed between and spaced apart from the vent valve seat and the solenoid to thereby define primary and secondary vents, respectively, the vent housing protecting the solenoid from thrust gasses exhausted through the pressure vent; and a thrust filter disposed inline with the supply valve seat such that thrust gasses transmitted to the supply valve seat are first filtered by the thrust filter to reduce particulates and condensables; whereby when the valve ball is seated in the vent valve seat, thrust pressure is applied to the thrust valve, the thrust being ceased when the valve ball is seated in the supply valve seat, whereupon any residual thrust pressure on the thrust valve is vented through the pressure vent. 26. The thrust valve system as set forth in claim 23, further comprising:the cylinder defined by a housing constructed of ablative material. 27. The thrust valve system as set forth in claim 26, further comprising:the ablative material being phenolic. 28. A directional control system for a thrust-based vehicle, comprising:a first pair of thrust valves coaxially and oppositely opposed to one another, the coaxial axis between the first pair of thrust valves being generally coplanar with and generally perpendicular to a longitudinal axis of the thrust-based vehicle such that spin is applied to the vehicle when one or both of the first pair of thrust valves fire; a second pair of thrust valves coaxially and oppositely opposed to one another, the coaxial axis between the second pair of thrust valves being generally perpendicular to the coaxial axis of the first pair of thrust valves, the coaxial axis between the second pair of thrust valves being generally perpendicular to but offset a first distance from and not coplanar with the longitudinal axis of the vehicle such that spin is applied to the vehicle when one of the second pair of thrust valves fires; a third pair of thrust valves coaxially and oppositely opposed to one another, the coaxial axis between the third pair of thrust valves being generally perpendicular to the coaxial axis of the first pair of thrust valves and being generally parallel to the coaxial axis of the second pair of thrust valves, the coaxial axis between the third pair of thrust valves being generally perpendicular to but offset the first distance from and not coplanar with the longitudinal axis of the vehicle such that spin is applied to the vehicle when one of the third pair of thrust valves fires; and the first, second, and third pairs of thrust valves being generally coplanar; whereby pitch, yaw and roll of the thrust-based vehicle is controlled by selectable operation of individuals ones of the thrust valves of the first, second, and third pairs of thrust valves. 29. The directional control system for a thrust-based vehicle as set forth in claim 28, further comprising:at least one of said valves constructed of ablative material. 30. The directional control system for a thrust-based vehicle as set forth in claim 29, further comprising:the ablative material being phenolic. 31. A directional control system for a thrust-based vehicle having a longitudinal axis, comprising:a first pair of coplanar thrust valves oppositely opposed to one another, the first pair of coplanar thrust valves having corresponding axes that are generally parallel to the vehicle's longitudinal axis, the plane shared between the first pair of thrust valves being generally coplanar with the longitudinal axis of the thrust-based vehicle such that spin is applied to the vehicle when one or both of the first pair of thrust valves fire; a second pair of coplanar thrust valves oppositely opposed to one another, the second pair of coplanar thrust valves having corresponding axes that are generally parallel to the vehicle's longitudinal axis, the plane shared between the second pair of thrust valves being generally perpendicular to the plane shared between the first pair of thrust valves and generally offset a first distance from and not coplanar with the longitudinal axis of the vehicle such that spin is applied to the vehicle when one of the second pair of thrust valves fires; a third pair of coplanar thrust valves oppositely opposed to one another, the third pair of coplanar thrust valves having corresponding axes that are generally parallel to the vehicle's longitudinal axis, the plane shared between the third pair of thrust valves being generally perpendicular to the plane shared between the first pair of thrust valves, being generally parallel to the plane shared between the second pair of thrust valves, and being generally offset the first distance from and not coplanar with the longitudinal axis of the vehicle such that spin is applied to the vehicle when one of the third pair of thrust valves fires; and the first, second, and third pairs of thrust valves being generally coplanar; whereby pitch, yaw and roll of the thrust-based vehicle is controlled by selectable operation of individual ones of the thrust valves of the first, second, and third pairs of thrust valves. 32. The directional control system for a thrust-based vehicle having a longitudinal axis as set forth in claim 31, further comprising:at least one of said valves constructed of ablative material. 33. The directional control system for a thrust-based vehicle having a longitudinal axis as set forth in claim 32, further comprising:the ablative material being phenolic. 34. A valve system for use in a missile, the valve system comprising:a thrust valve having a piston for diverting hot propellant gas; and a pilot valve in communication with the thrust valve, the pilot valve controlling flow of the hot propellant gas beneath the piston to control operation of the thrust valve. 35. A valve system for use in a missile as set forth in claim 34, wherein the pilot valve further comprises:a housing having a supply valve seat and a vent valve seat defining an internal valve chamber; the supply valve seat defining a thrust inlet opening; the vent valve seat defining a pressure vent opening; the valve chamber in communication with the thrust inlet, the thrust valve, and the pressure vent; a valve gate moveable between the supply valve and vent valve seats to selectably seal either the supply valve seat or the vent valve seat; and a valve gate control mechanism operably coupled to the valve gate; whereby when the valve gate is seated in the vent valve seat thrust pressure is applied to the thrust valve, the thrust being ceased when the valve gate is seated in the supply valve seat, whereupon any residual thrust pressure on the thrust valve is vented through the pressure vent. 36. A valve system for use in a missile as set forth in claim 35, further comprising:the supply valve seat, the vent valve seat, and the valve gate all being made at least in part of a refractory material. 37. A valve system for use in a missile as set forth in claim 35, wherein the refractory material is selected from the group consisting of rhenium, tungsten, niobium, tantalum, molybdenum, and alloys thereof.38. A valve system for use in a missile as set forth in claim 35, further comprising:a vent housing disposed between and spaced apart from the vent valve seat and the valve gate control mechanism to thereby define primary and secondary vents, respectively, the vent housing protecting the valve gate control mechanism from thrust gasses exhausted through the pressure vent. 39. A valve system for use in a missile as set forth in claim 35, wherein the valve gate control mechanism further comprises:a solenoid; and a rod coupling the valve gate to the solenoid; whereby activation of the solenoid urges the valve gate against the supply valve seat. 40. A valve system for use in a missile as set forth in claim 35, further comprising:a thrust filter disposed inline with the supply valve seat; whereby thrust gasses transmitted to the supply valve seat are first filtered by the thrust filter to reduce particulates and condensables. 41. The missile as set forth in claim 34, further comprising:the housing being constructed of ablative material. 42. The missile as set forth in claim 41, further comprising:the ablative material being phenolic.