[특허]Missile, chemical plasm steering system, and method

LOCKHEED MARTIN CORPORATION

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Missile, chemical plasm steering system, and method

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F42B-010/66 F42B-010/00
출원번호	US-0358079 (2016-11-21)
등록번호	US-10113844 (2018-10-30)
발명자 / 주소	Wood, James Richard
출원인 / 주소	LOCKHEED MARTIN CORPORATION
대리인 / 주소	Sanks, Esq., Terry M.
인용정보	피인용 횟수 : 0 인용 특허 : 26

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Embodiments disclosed include a system comprising a missile segment having an external surface conforming to a portion of an external surface of a missile body. The missile segment comprising a plurality of chemical plasma dispensing units (CPDUs) having a chemical plasma reactant (CPR). Each CPDU is addressable so that a group of selected CPDUs in an area is ignited simultaneously to cause a first reaction to push CPR particles into a flow stream surrounding the missile body. The CPR particles to complete a second reaction in the flow stream over a reaction time period to effectuate production of expanding hot gas energy caused by heating air in the flow stream and gaseous reaction products over the missile body to provide an amount of a steering force to change one or more of six degrees of freedom at a location on the body. A missile and method are also provided.

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1. A system comprising: a missile segment having an external surface conforming to an external surface of a portion of a missile body, the missile segment comprising: a plurality of shallow cavities arranged in the external surface of the portion of the missile body and each cavity having an opening; anda plurality of chemical plasma dispensing units (CPDUs) having a chemical plasma reactant (CPR), each respective CPDU being coupled in a respective cavity and being individually addressable so that a group of selected CPDUs in an area is ignited simultaneously to cause a first reaction to push CPR particles into a flow stream surrounding the missile body, the CPR particles to complete a second reaction in the flow stream over a reaction time period to effectuate production of expanding hot gas energy caused by heating air in the flow stream and gaseous reaction products over the missile body to provide an amount of a steering force to change one or more of six degrees of freedom at a location on the missile body which lags the area defined by the group of selected CPDUs. 2. The system according to claim 1, further comprising a computing device configured to determine the group of selected CPDUs to control the one or more of six degrees of freedom defining the location on the missile body to produce the steering force for an angle of attack. 3. The system according to claim 1, wherein the CPDU comprises: a cartridge having a volume of space defined by a plurality of walls forming an enclosure to store the CPR within the enclosure; anda pyrotechnic foil covering a wall of the cartridge to apply an activation response to an area of the CPR, the area of the CPR being in contact with the wall. 4. The system according to claim 1, wherein the CPDU comprises: a cartridge having a volume of space defined by a plurality of walls forming an enclosure to store the CPR within the enclosure; andan initiator comprising multiple points of activation, the initiator being coupled a wall of the cartridge to activate one or more of the multiple points of activation to ignite the CPR. 5. The system according to claim 4, wherein a number of the multiple points of activation selected to ignite the CPR varies a rate at which a quantity of the CPR activates. 6. The system according to claim 1, wherein the CPR comprises a composition of Tantalum and Boron, Titanium and Boron or Titanium and Carbon. 7. The system according to claim 1, further comprising at least one power source to ignite the group of the selected CPDUs, wherein the group of selected CPDUs being arranged in a pattern interspersed among non-selected CPDUs in the area. 8. A missile comprising: a missile body having a nose section, a forward section, an aft section and a tail section;a computing device configured to control steering of the missile body in air; andat least one missile segment comprising an external surface conforming to an external surface of the missile body, the at least one missile segment being integrated in the missile body, the at least one missile segment comprising: a plurality of chemical plasma dispensing units (CPDUs) embedded in the external surface of the at least one missile segment and having a chemical plasma reactant (CPR), each respective CPDU being individually addressable so that a group of selected CPDUs in an area is ignited simultaneously to effectuate production of expanding hot gas energy to cause overpressure in a flow stream with gaseous reaction products over the missile body to provide an amount of a steering force to change one or more of six degrees of freedom at a location on the missile body which lags the area defined by the group of selected CPDUs. 9. The missile according to claim 8, further comprising a plurality of shallow cavities arranged in a plurality of cavity sets, each cavity set being arranged circumferentially around the hollow cylindrical body wherein each respective cavity has a respective CPDU embedded therein; and the computing device configured to determine the group of selected CPDUs to control the one or more of six degrees of freedom defining the location on the missile body to produce a maneuver for an angle of attack. 10. The missile according to claim 8, wherein said each CPDU comprises: a cartridge having a volume of space defined by a plurality of walls forming an enclosure to store the CPR within the enclosure; anda pyrotechnic foil covering a wall of the cartridge to apply an activation response to an area of the CPR, the area of the CPR being in contact with the wall. 11. The missile according to claim 8, wherein said each CPDU comprises: a cartridge having a volume of space defined by a plurality of walls forming an enclosure to store the CPR within the enclosure; andan initiator comprising multiple points of activation, the initiator being coupled to a wall of the cartridge to activate one or more of the multiple points of activation to ignite the CPR. 12. The missile according to claim 11, wherein a number of the multiple points of activation selected to ignite the CPR varies a rate at which a quantity of the CPR activates. 13. The missile according to claim 8, wherein the group of selected CPDUs are ignited simultaneously to cause a first reaction to push an amount of CPR particles into the flow stream surrounding the missile body, the CPR particles to complete a second reaction in the flow stream over a reaction time period to effectuate the production of the expanding hot gas energy. 14. The missile according to claim 8, further comprising at least one power source to ignite the group of CPDUs; anda plurality of switches coupled to the plurality of CPDUs and the at least one power source wherein activation of a respective one switch individually addresses a respective one CPDU. 15. A method comprising: determining, by at least one processor, an amount of steering force needed to cause a certain amount of missile body translation along at least one of section of a missile body;determining, by the at least one processor, a group of chemical plasma dispensing units (CPDUs) of a plurality of CPDUs needed to produce the steering force based on an amount of a chemical plasma reactant (CPR) of each CPDU, the group of CPDUs being in an area;igniting, simultaneously, the group of CPDUs, to release CPR particles in a flow stream around the missile body; andeffectuating production of expanding hot gas energy by the released CPR particles to cause overpressure in the flow stream with gaseous reaction products over the missile body to provide the amount of the steering force which changes one or more of six degrees of freedom at a location on the missile body which lags the area defined by the group of selected CPDUs. 16. The method according to claim 15, further comprising determining, by the at least one processor, a translation force by attitude control motors (ACM) devices to control flight of the missile body. 17. The method according to claim 15, wherein said each CPDU comprises: a cartridge having a volume of space defined by a plurality of walls forming an enclosure to store the CPR within the enclosure; anda pyrotechnic foil covering a wall of the cartridge to apply an activation response to an area of the CPR, the area of the CPR being in contact with the wall; andfurther comprising activating the foil to ignite the CPR of said each CPDU in the group of CPDUs. 18. The method according to claim 15, wherein said each CPDU comprises: a cartridge having a volume of space defined by a plurality of walls forming an enclosure to store the CPR within the enclosure; andan initiator coupled a wall of the cartridge to apply multiple points of activation to the CPR, simultaneously; andfurther comprising activating one or more of the multiple points of activation to ignite the CPR. 19. The method according to claim 15, wherein the determining of the group of CPDUs includes determining the area with a set of CPDUs; and selecting a pattern of CPDUs from the set of CPDUs so that the pattern of CPDUs is interspersed among non-selected CPDUs in the area. 20. The method according to claim 15, wherein, the effectuating production of expanding hot gas energy, includes causing a first reaction to push an amount of the CPR particles into the flow stream surrounding the missile body; and completing by the CPR particles a second reaction in the flow stream over a reaction time period to effectuate the production of the expanding hot gas energy.

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