초록 ▼

This invention advances the related state-of-the-art by eliminating the physical EO window used by electro-optical imaging infrared seekers for tactical missiles and high-altitude endo-atmospheric interceptors, widely employed in integrated defense systems. This invention increases the probability o

This invention advances the related state-of-the-art by eliminating the physical EO window used by electro-optical imaging infrared seekers for tactical missiles and high-altitude endo-atmospheric interceptors, widely employed in integrated defense systems. This invention increases the probability of intercepting exo-atmospheric ballistic warheads by exo-atmospheric interceptors, and eliminates the existing altitude “gap” of interception, as well as the geographical limitations posed by the mesospheric Noctilucent Clouds. The problem of protecting an imaging EO sensor from aeroheating is solved in this invention by a special purpose device which is enabled immediately after the nose cone ejection event. The role of said device is to augment the sensor fixed sunshade and cavity lengths in the forward direction, and by doing so, the resulting new cavity enables the optimal injection of an optically inert gas into the new extended cavity in front of the sensor, thus effectively blocking the entry of the compressed hot air into the sensor cavity, while simultaneously avoiding any adverse effects of inducing flow instabilities in the flow as well as the disturbance of the injected gas flow on sensor structures. Having a greater length for the hot gas to penetrate, eliminates also the penetration of suspended particles in oncoming air stream.

대표청구항 ▼

1. A protection device for a missile electro-optical (EO) seeker comprising a fixed sunshade that can be mounted surrounding an EO seeker sensor, the fixed sunshade forming a cavity, characterised by comprising: at least one deployable sunshade arranged to be moved in a telescopic manner relative to

1. A protection device for a missile electro-optical (EO) seeker comprising a fixed sunshade that can be mounted surrounding an EO seeker sensor, the fixed sunshade forming a cavity, characterised by comprising: at least one deployable sunshade arranged to be moved in a telescopic manner relative to the fixed sunshade between a first position, in which the at least one deployable sunshade substantially does not protrude the fixed sunshade, and a second position, in which the at least one deployable sunshade is deployed with respect to the fixed sunshade, thus creating a longer cavity with respect to the first position; andat least one container for a pressurizing optically-inert gas;wherein in the second position, the optically-inert gas can be injected into a space forward facing the sensor in the cavity, forming a highly stable flow pattern. 2. The protection device for a missile EO seeker of claim 1, further comprising at least one pneumatic pressure actuator arranged to deploy the at least one deployable sunshade and supplying gas to gas injection manifolds and injectors located in the inner surface of the at least deployable sunshade. 3. The protection device for a missile EO seeker of claim 1, wherein the at least one deployable sunshade and the fixed sunshade are configured as a cylindrical assembly, the deployablcorrected, DD.e sunshade being arranged to slide forward and parallel to the fixed sunshade until at least one stop makes contact, resulting thus in a longer cavity. 4. The protection device for a missile EO seeker of claim 1, further comprising a sunshade cover in the open space of the fixed sunshade when the at least one deployable sunshade is in the first position, the sunshade cover being ejected when the at least one deployable sunshade is being deployed when passing from the first to the second position. 5. The protection device for a missile EO seeker of claim 1, wherein the container for a pressurizing optically-inert gas comprises at least one variable-setting pressure regulator, to pressurize the system for pneumatic action by means of a pair of redundant pyrotechnic valves that are enabled at launch by the sequencing computer, thus retaining an acceptable container pressure without refurbishing. 6. The protection device for a missile EO seeker of claim 5, further comprising at least one redundant pressure regulator, at a high pressure level setting, to be held while the deployable sunshade is being deployed when passing from the first to the second position. 7. The protection device for a missile EO seeker of claim 5, wherein the at least one deployable sunshade is cylindrical and its cylindrical wall ends are reinforced with two stiffening rings, wherein the back end stiffener ring at the back end is located inside the cylindrical wall and it is provided with a snap/latch mechanism to interlock onto an outer ring stiffener of the fixed sunshade, and wherein the free end stiffener ring at the free end of the at least one deployable sunshade acts as a stop for the piston drives of the pneumatic actuators, the free end stiffener ring further having a plurality of orifices that fit into each one of the inner orifice of the pneumatic actuators piston-spigots, these orifices acting as conduits for the pressurized gas to be delivered to an annular low-pressure manifold arranged within the free end stiffener ring. 8. The protection device for a missile EO seeker of claim 1, wherein each pneumatic actuator comprises an outer member, configured as a barrel, and a piston, the back end of the barrel being attached to a back end stiffener ring fixed to the fixed sunshade and to the forward KV platform, wherein the back end stiffener ring houses an annular cavity that acts as a high-pressure manifold with gas being fed directly from at least on pressure regulator, wherein the body of the barrel is configured to slide along the outer surface of the deployable sunshade during its deployment. 9. The protection device for a missile EO seeker of claim 8, wherein the spigot of piston is designed as a hollow rod, the end within the barrel is machined to fit tight-to-slide on the inner surface of barrel and is propelled by gas from high pressure manifold, the other end is attached to stiffener of the deployable sunshade, and its open end discharges into low pressure manifold, once the deployable sunshade reaches its extended position, the piston back-end locks onto the barrel forward end, and the assembly is fully locked into the deployed position. 10. An anti-missile interceptor, comprising: a platform comprising of a forward section of a missile;an electro-optical (EO) seeker sensor mounted on said platform; andan assembly of structures and mechanisms surrounding said EO seeker sensor and forming a cavity, characterised by comprising a fixed sunshade that can be mounted surrounding said EO sensor, the fixed sunshade forming a cavity, and a protection device comprising: at least one deployable sunshade arranged to be moved in a telescopic manner relative to the fixed sunshade between a first position, in which the at least one deployable sunshade substantially does not protrude the fixed sunshade, and a second position, in which the at least one deployable sunshade is deployed with respect to the fixed sunshade, thus creating a longer cavity with respect to the first position; andat least one container for a pressurizing optically-inert gas;wherein in the second position, the optically-inert gas can be injected into a space forward facing the sensor in the cavity, forming a highly stable flow pattern. 11. A tactical missile, comprising: a platform comprising a generic forward section of a missile;an electro-optical (EO) seeker sensor mounted on said platform; andan assembly of structures and mechanisms surrounding said EO seeker sensor and forming a cavity, characterised by comprising a fixed sunshade that can be mounted surrounding said EO sensor, the fixed sunshade forming a cavity, and a protection device comprising: at least one deployable sunshade arranged to be moved in a telescopic manner relative to the fixed sunshade between a first position, in which the at least one deployable sunshade substantially does not protrude the fixed sunshade, and a second position, in which the at least one deployable sunshade is deployed with respect to the fixed sunshade, thus creating a longer cavity with respect to the first position; andat least one container for a pressurizing optically-inert gas;wherein in the second position, the optically-inert gas can be injected into a space forward facing the sensor in the cavity, forming a highly stable flow pattern. 12. A method for increasing the probability of interception of a missile without geographical nor altitude limitations, characterised by using an anti-missile provided with an electro-optical, EOE seeker sensor, a fixed sunshade that can be mounted surrounding said EO sensor, the fixed sunshade forming a cavity, and further comprising a protection device comprising: at least one deployable sunshade arranged to be moved in a telescopic manner relative to the fixed sunshade between a first position, in which the at least one deployable sunshade substantially does not protrude the fixed sunshade, and a second position, in which the at least one deployable sunshade is deployed with respect to the fixed sunshade, thus creating a longer cavity with respect to the first position; andat least one container for a pressurizing optically-inert gas;wherein in the second position, the optically-inert gas can be injected into a space forward facing the sensor in the cavity, forming a highly stable flow pattern. 13. The method of claim 12, wherein: the deployable sunshade is retracted during storage, launch, and ascent trajectory, but it is in an extended position after a nose cone of the tactile missile is ejected; andonce the nose cone and a retainer of the tactile missile are jettisoned, a protective cover is safely ejected as the deployable sunshade is extended. 14. Method for increasing flight speeds of a tactical missile, characterised by using a tactical missile provided with an imaging electro-optical (EO) seeker sensor, a fixed sunshade that can be mounted surrounding said EO sensor, the fixed sunshade forming a cavity, and further comprising a protection device comprising: at least one deployable sunshade arranged to be moved in a telescopic manner relative to the fixed sunshade between a first position, in which the at least one deployable sunshade substantially does not protrude the fixed sunshade, and a second position, in which the at least one deployable sunshade is deployed with respect to the fixed sunshade, thus creating a longer cavity with respect to the first position; andat least one container for a pressurizing optically-inert gas;wherein in the second position, the optically-inert gas can be injected into a space forward facing the sensor in the cavity, forming a highly stable flow pattern. 15. The method of claim 13, wherein: the deployable sunshade is retracted during storage, launch, and ascent trajectory, but it is in an extended position after a nose cone of the tactile missile is ejected; andonce the nose cone and a retainer of the tactile missile are jettisoned, a protective cover is safely ejected as the deployable sunshade is extended. 16. The method of claim 14, further comprising using at least one pneumatic actuator for a triple purpose comprising: ejecting the protective cover;pushing and guiding the deployable sunshade; andacting as plenums for routing the driving gas of the pneumatic action to a manifold of gas injection elements.