Ordnance
The SAM system addresses the high cost and single-use limitations of existing missiles by integrating electric ducted fan engines and optimized aerodynamics, resulting in a more cost-effective and reusable defense solution.
Patent Information
- Authority / Receiving Office
- GB · GB
- Patent Type
- Applications
- Current Assignee / Owner
- GREENJETS LTD
- Filing Date
- 2024-07-09
- Publication Date
- 2026-05-20
- Estimated Expiration
- Not applicable · inactive patent
AI Technical Summary
The high cost and single-use nature of existing surface-to-air missiles, such as the MIM-104 Patriot system, pose significant financial burdens, necessitating the development of more cost-effective and reusable missile systems.
Design of a surface-to-air missile (SAM) system incorporating rear-mounted electric ducted fan engines, optimized air intake and exhaust systems, and a modular design to enhance performance and reusability, reducing material and operational costs.
The proposed SAM system achieves enhanced performance and reusability, lowering unit costs and operational expenses while maintaining effective defense capabilities.
Smart Images
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Abstract
Description
[0001] Surface-to-Air missile (SAM) systems are crucial to providing ground based defences to incoming airborne threats. The MIM-104 Patriot system is an example of a mobile such a SAM system, which is also known as an anti-ballistic missile. The Patriot system uses an advanced aerial interceptor missile and high-performance radar system. The MIM-104C PAC-2 missile was the first Patriot missile that was designed for ballistic missile engagements. A PAC-2 is a formidable missile measuring 5.8m and weighing 900kg that is propelled by a solid-fuel rocket motor. The unit cost of a Patriot missile is of the order of $4m, which is significant for a single use, and an associated battery is of the order of $1bn.
[0002] Examples implementations are described below with reference to the accompanying drawings, in which:
[0003] figure 1 shows a view of a surface to air ordnance;
[0004] figure 2 illustrates an interior view of the ordnance of figure 1;
[0005] figure 3 depicts a sectional view of the ordnance of figure 2;
[0006] figure 4 shows a view of busbar power connections for an electric motor; and
[0007] figure 5 shows a view of exhaust vanes of the ordnance of figure 1.
[0008] Figure 1 shows a view 100 of a surface-to-air missile 102. The SAM 102 comprises an elongate body 104 bearing a set 106 of rear mounted electric ducted fan (EDF) engines. The set of rear mounted EDF engines can comprise one or more than one EDF engine. An EDF engine comprises an electric motor that drives a set of fans. The set of fans can comprise one or more than one fan. In the example depicted, the set 106 of rear mounted electric ducted fan engines comprises a pair 108 and 110 of such EDF engines.
[0009] The SAM 102 can also comprise a set of wings. The set of wings can comprise one or more than one wing. In the example depicted in figure 1, the set of wings comprises two wings 112 and 114. The wings 112 and 114 can comprise respective control surface 116 and 118.
[0010] The SAM 102 can also comprise an empennage 120. Examples can be realised in which the empennage 120 comprises a set of stabilisers. Examples can be realised in which the set of stabilisers comprises one or more than one stabilisers. In the SAM 102 depicted in figure 1, the empennage 120 comprises four stabilisers. Only three 122 to 126 of the four stabilisers are visible in figure 1. The empennage 120 of the SAM 102 comprises two horizontal stabilisers; one 126 of which is shown and two vertical stabilisers 122 and 124. Examples can be realised in which one or more than one stabiliser also bears a control surface. Such a control surface can comprise an elevator or a rudder. In the SAM 102 shown in figure 1, the horizontal stabilisers have respective control surfaces such as, for example, the control surface 128 of the horizontal stabiliser 126.
[0011] Each engine 108 and 110 has a respective air intake 130 and 132. Each air intake comprises the volume defined by the central hubs 134 and 136 and the interior of the nacelles or engine housings. In the example shown, the volume is an annular volume within the engine that leads to the fan 138 and 140.
[0012] The air intakes 130 and 132 are arranged to present a divergent or increasing volume. The divergent volume is arranged to reduce the speed of the air entering the engines 108 and 110 according to the design and operational parameters of the fans 138 to 140.
[0013] The body 104 of the SAM 102 can be shaped in the region 142 and 144 leading to the air intakes 130 and 132 to also reduce the speed of the air flow into the engines 108 and 110. In the SAM 102 shown, the width of the fuselage progressively decreases in the region leading to the intakes 130 and 132.
[0014] The air intakes 130 and 132 have a respective predetermined area, which is known as an air intake area. The respective predetermined area is associated with the area of the disc of a fan 138 and 140. In the example SAM 102 shown, the respective predetermined area is a predetermined number of times the disc area of a fan. Examples can be realised in which the area of the air intake is smaller than the disc area of a fan such that the ratio of the two is less than one. Examples can be realised in which the respective predetermined area is within the range of 0.7 to 4 times the disc area, optionally 0.8 times the disc area of a fan.
[0015] Each engine 108 and 110 of the SAM 102 also comprises a respective exhaust nozzle 146 and 148. Such an exhaust nozzle 146 and 148 presents a convergent volume arranged to increase the velocity of air exiting the engine relative to the air velocity leaving the fan. Each exhaust nozzle 146 to 148 presents a respective exhaust area.
[0016] Examples can be realised in which respective exhaust area is a predetermined number of times the disc area of the fan. Examples can be realised in which the area of the exhaust is smaller than the disc area of a fan such that the ratio of the two is less than one. Examples can be realised in which the respective predetermined area is within the range of 0.6 to 1 times the disc area of a fan. For instance, examples can be realised in which the exhaust area is 0.68 times the disc area.
[0017] Figure 1 also shows a reference system 150. The reference system 150 comprises three mutually orthogonal axes 152 to 156 that define three planes; namely, the XY plane, the XZ plane and the YZ plane.
[0018] Figure 2 illustrates an interior view 200 of the SAM 102 of figure 1. The interior 202 of the fuselage 104 comprising an elongate internal volume 204. The internal volume 204 is arranged to extend between the engines 108 and 110.
[0019] The elongate internal volume 204 is arranged to house an electrical power source 206. In the example depicted, the electrical power source 206 comprises a set of batteries. The set of batteries can comprise plurality of batteries. The SAM 102 shown in figure 2 comprises a plurality of batteries.
[0020] Figure 2 also shows an actuator 208 for controlling the attitude of the control surface 128 of the horizontal stabiliser 126. The actuator 208 causes the control surface 128 to rotate about an axis 210.
[0021] Each engine 108 and 110 has an inverter 212 for controlling the power supplied to the motors. The power from the inverter 212 is supplied to a respective motor using three phase busbar 214, 216, 218. The busbars 214 to 218 supply three phases 200-250A at 50-60V, or 90-125A at 110-120V. As will be described with reference to figure 4, the inverter 212 is exposed to the air flow through a respective engine 108 and 110. The thermal condition of the inverter 212 is influenced by that exposure. The air flow through a respective engine reduces the temperature of the inverter 212.
[0022] Figure 3 depicts a further sectional view 300 of the SAM 102 of figure 1. The SAM 102 comprises a payload 302. Examples can be realised in which the payload is an explosive device arranged to destroy an intercepted object. The SAM 102 also comprises a flight controller 304 for controlling the speed of the motors, and the orientation of the control surfaces such as, for example, the control surfaces 128 and 128’ and the exhaust vanes 502 and 504, and, therefore, the velocity of the SAM 102.
[0023] Figure 4 shows a view 400 of the inverter 212 and associated busbars 214 to 218 for providing power to a respective electric motor (not shown) such as, for example, one of the above electric motors. The inverter 212 and the busbars 214 to 218 are supported on an housing; half 402 of which is shown in figure 4. The housing bears an iso-grid structure. The iso-grid structure provides a balance between structural rigidity and weight.
[0024] The busbars 214 to 218 are fed to respective electrical connectors 404 to 408 for coupling to respective phases of a motor. The electrical connectors 404 to 408 are housed within a half 410 of a nose cone. The nose cone is an example of the above-described nose cones 134 and 136. The busbars 214 to 218 are housed within an aerodynamic strut 412.
[0025] Referring to figure 5, there is shown a view 500 of the pair of exhaust nozzles 546 and 548. The exhaust nozzles 546 and 548 have respective sets of exhaust vanes. The sets of exhaust vanes can comprise one or more than one exhaust vane. In the SAM 502 depicted in figure 5, a first exhaust nozzle 546 of the pair has an associated set of exhaust vanes comprising a single exhaust vane 502 and a second exhaust nozzle 548 of the pair comprises a set of exhaust vanes comprising a single exhaust vane 504. Each exhaust vane projects at least partially into the exhaust airflow (not shown). Examples can be realised in which each exhaust vane projects fully into the exhaust vane. In such examples, the exhaust vanes 502 and 504 would span the full diameter of the exhaust nozzle area 506 and 508. Although the exhaust vanes have been shown as being disposed in a transverse plane, that is, an XY plane, examples are not limited to such an arrangement. Examples can be realised in which the exhaust vanes are disposed within some other predetermined plane such as, for example, an XZ plane. Although sets of exhaust vanes have been described that comprise a single transversely disposed exhaust vanes, examples are not limited to such an arrangement. Examples can be realised in which a set of exhaust vanes comprise a number of exhaust vanes disposed at respective angles relative to one another. For instance, examples can be realised in which a set of exhaust vanes comprises a pair of exhaust vanes in which one exhaust plane is positioned within a transverse plane and the other exhaust vane is positioned within a sagittal plane. In such an arrangement, the pair of exhaust vanes would be perpendicular to one another.
Claims
1. Ordnance for intercepting an airborne body; the ordnance comprising an elongate body bearing at least a pair of rear mounted electric ducted fan engines; each engine comprising an electric motor and an associated fan.
2. The ordnance of claim 1, in which each electric ducted fan engine has an associated intake with a respective intake area and an exhaust nozzle with a respective exhaust area.
3. The ordnance of claim 2, in which the intake presents a divergent volume arranged to reduce the velocity of air engaging the fan relative to a freestream air velocity / relative to an ordnance airspeed velocity.
4. The ordnance of either of claims 2 and 3, in which the respective intake area is a predetermined number of times the disc area of the fan, optionally, the predetermined area is between 0.7 and 4 times the disc area, preferably, the predetermined number of times is 0.8.
5. The ordnance of any of claims 2 to 4, in which the exhaust nozzle presents a convergent volume arranged to increase the velocity of air exiting the fan or engine relative to the air velocity leaving the fan.
6. The ordnance of any of claims 2 to 5, in which the respective exhaust area is a predetermined number of times the disc area of the fan, optionally, the predetermined area is between 0.6 and 1 times the disc area, preferably, the predetermined number of times the disc area is 0.68.
7. The ordnance of any of claims 2 to 6, in which the intake comprises a respective fuselage section having a surface profile that varies from one dimension to a smaller dimension.
8. The ordnance of any preceding claim, in which the fuselage has an elongate internal volume arranged to house an electrical power source; the electrical power source comprises a set of batteries.
9. The ordnance of claim 8, in which the elongate internal volume extends between at least fore portions of the rear mounted electric ducted fan engines.
10. The ordnance of any preceding claim, bearing a set of wings bearing control surface and a set of rear or tail control surfaces.
11. The ordnance of any preceding claim comprising at least one inverter; the at least one inverter being arranged to supply electrical power to each electric motor.
12. The ordnance of claim 11, in which the at least one inverter power supply comprises a set of busbars for carrying current to a respective electric motor.
13. The ordnance of claim 12, in which the busbars are housed within, or shaped as, an aerodynamic structure, optionally, the busbars are exposed to the airflow through the engines to cool the busbar.
14. The ordnance of any of claims 12 to 13, in which the at least one inverter has at least one surface exposed to the interior of the engine to cool the inverter in the presence of air flow.
15. The ordnance of any of claims 12 to 14, in which the at least one inverter delivers a predetermined power to an electric motor at a predetermined voltage and at a predetermined current.
16. The ordnance of claim 15, in which the predetermined power is between 8kW and 11 kW.
17. The ordnance of either of claims 15 and 16, in which the predetermined voltage is between 50V and 120V, 50V to 60V or 110V to 120V.
18. The ordnance of any of claims 15 to 17, in which the current is between 200A and 250A, or 90A to 125AAmendments to the Claims have been filled as follows:CLAIMS1. Ordnance for intercepting an airborne body; the ordnance comprising an elongate body bearing at least a pair of rear mounted electric ducted fan engines; each engine comprising an electric motor and an associated fan.
2. The ordnance of claim 1, in which each electric ducted fan engine has an associated intake with a respective intake area and an exhaust nozzle with a respective exhaust area.
3. The ordnance of claim 2, in which the intake presents a divergent volume arranged to reduce the velocity of air engaging the fan relative to a freestream air velocity / relative to an ordnance airspeed velocity.
4. The ordnance of either of claims 2 and 3, in which the respective intake area is a predetermined number of times the disc area of the fan.
5. The ordnance of any of claims 2 to 4, in which the exhaust nozzle presents a convergent volume arranged to increase the velocity of air exiting the fan or engine relative to the air velocity leaving the fan.
6. The ordnance of any of claims 2 to 5, in which the respective exhaust area is a predetermined number of times the disc area of the fan.
7. The ordnance of any of claims 2 to 6, in which the elongate body has a pair of regions leading to respective air intakes for the pair of rear mounted electric ducted fan engines; the pair of regions having respective surface profiles that vary from one dimension to a smaller dimension to reduce the speed of air flow into respective engines of the pair of rear mounted electric ducted fan engines.
8. The ordnance of any preceding claim, in which the elongate body has an elongate internal volume arranged to house an electrical power source; the electrical power source comprising a set of batteries.
9. The ordnance of claim 8, in which the elongate internal volume extends between at least fore portions of the rear mounted electric ducted fan engines.
10. The ordnance of any preceding claim, bearing a set of wings bearing control surface and a set of rear or tail control surfaces.
11. The ordnance of any preceding claim comprising at least one inverter; the at least one inverter being arranged to supply electrical power to each electric motor.
12. The ordnance of claim 11, in which the at least one inverter power supply comprises a set of busbars for carrying current to a respective electric motor.
13. The ordnance of claim 12, in which the busbars are housed within, or shaped as, an aerodynamic structure, optionally, the busbars are exposed to the airflow through the engines to cool the busbar.
14. The ordnance of any of claims 12 to 13, in which the at least one inverter has at least one surface exposed to the interior of the engine to cool the inverter in the presence of air flow.
15. The ordnance of any of claims 12 to 14, in which the at least one inverter delivers a predetermined power to an electric motor at a predetermined voltage and at a predetermined current.
16. The ordnance of claim 15, in which the predetermined power is between 8kW and 11kW.
17. The ordnance of either of claims 15 and 16, in which the predetermined voltage is between 50V and 120V, 50V to 60V or 110V to 120V.
18. The ordnance of any of claims 15 to 17, in which the current is between 200A and 250A, or 90A to 125A.
19. The ordnance of claim 4, in which the respective intake area is between 0.7 and 4 times the disc area of the fan.
20. The ordnance of claim 19, in which the respective intake area is 0.8 times the disc area.
21. The ordnance of claims 6, in which the respective exhaust area is between 0.6 and 1 times the disc area.
22. The ordnance of claims 21, in which the respective exhaust area is between 0.68 times the disc area.