Guided missile with at least one engine for producing forward thrust

Abstract

A guided missile with a sleeve-shaped missile body, at least one engine for producing forward thrust, at least one flight direction control device, and at least one aerodynamic extension. The least one flight direction control device is rotatably mounted to a top area and/or a bottom area of the sleeve-shaped missile body for adjusting a flight direction of the guided missile. The least one aerodynamic extension comprises an aerodynamic cross-sectional shape that is arranged on a left-hand side and/or a right-hand side of the sleeve-shaped missile body.

Claims

1. A guided missile comprising: a sleeve-shaped missile body that extends along a longitudinal axis from a front section to a rear section, along a height axis from a bottom area to a top area, and along a transversal axis from a left-hand side to a right-hand side; at least one engine for producing forward thrust, the at least one engine being accommodated inside the sleeve-shaped missile body and comprising a nozzle that is arranged at the rear section of the sleeve-shaped missile body; at least one flight direction control device that is rotatably mounted to the top area or the bottom area of the sleeve-shaped missile body for adjusting a flight direction of the guided missile; and at least one aerodynamic extension with an aerodynamic cross-sectional shape that is arranged on one of the left-hand side or the right-hand side of the sleeve-shaped missile body, wherein the at least one aerodynamic extension forms together with the sleeve-shaped missile body a lift generating airfoil at an angle oblique to the longitudinal axis for producing additional lift during flight, and wherein a curved extension is arranged on the other one of the left-hand side or the right-hand side of the sleeve-shaped missile body.

2. The guided missile of claim 1, wherein the at least one flight direction control device is of the rudder type and rotatable around the height axis from a position aligned with the longitudinal axis by a rotation angle comprised between −45° and 135°.

3. The guided missile of claim 1, wherein a cross-sectional profile of the curved extension, the sleeve-shaped missile body and the at least one aerodynamic extension together form a wing airfoil.

4. The guided missile of claim 1, wherein the at least one aerodynamic extension comprises a sharp edge.

5. The guided missile of claim 1, comprising at least two flight direction control devices, wherein at least one first flight direction control device of the at least two flight direction control devices is rotatably mounted to the top area of the sleeve-shaped missile body, and wherein at least one second flight direction control device of the at least two flight direction control devices is rotatably mounted to the bottom area of the sleeve-shaped missile body.

6. The guided missile of claim 5, wherein the at least one first flight direction control device and the at least one second flight direction control device comprise rotation axes which are arranged coaxially or at an oblique angle with reference to the height axis.

7. The guided missile of claim 5, wherein the at least one first flight direction control device and the at least one second flight direction control device are arranged in, or close to, the front section of the sleeve-shaped missile body.

8. The guided missile of claim 5, wherein the at least one first flight direction control device and the at least one second flight direction control device are arranged in, or close to, the rear section of the sleeve-shaped missile body.

9. The guided missile of claim 1, wherein the at least one aerodynamic extension comprises at least one aileron which is mounted to a trailing edge of the at least one aerodynamic extension, wherein the trailing edge is an outer edge of the at least aerodynamic extension distal from the sleeve-shaped missile body.

10. The guided missile of claim 9, wherein the at least one aileron comprises a control that is oriented at an oblique angle to the longitudinal axis of the sleeve-shaped missile body.

11. The guided missile of claim 1, further comprising at least one sensor that is mounted to the front section of the sleeve-shaped missile body.

12. The guided missile of claim 1, further comprising at least one additional engine.

13. The guided missile of claim 1, wherein the at least one flight direction control device comprises one of a slat, a flap, a grid fin, a spoiler, an air brake, a morphing airfoil, a small rocket engine, a gas generator, or an explosive for flight direction control.

14. The guided missile of claim 1, wherein the at least one engine comprises one of a rocket engine, an air breathing rocket, a turbine engine, a ram-jet, a scram-jet, an electrically powered fan, or an electrically powered propeller.

15. A guided missile comprising: a sleeve-shaped missile body extending along a longitudinal axis from a front section to a rear section, along a height axis from a bottom area to a top area, and along a transversal axis from a left-hand side to a right-hand side; an engine for producing forward thrust, the engine disposed inside the sleeve-shaped missile body and comprising a nozzle disposed at the rear section of the sleeve-shaped missile body; a flight direction control device rotatably mounted to the top area or the bottom area of the sleeve-shaped missile body to enable adjusting a flight direction of the guided missile; and an aerodynamic extension with an aerodynamic cross-sectional shape disposed on one of the left-hand side or the right-hand side of the sleeve-shaped missile body, wherein the aerodynamic extension with the sleeve-shaped missile body forms a lift generating airfoil at an angle oblique to the longitudinal axis to enable producing additional lift during flight, and wherein a curved extension is disposed on the other one of the left-hand side or the right-hand side of the sleeve-shaped missile body.

16. The guided missile of claim 15, wherein the at least one flight direction control device is of the rudder type and rotatable around the height axis from a position aligned with the longitudinal axis by a rotation angle comprised between −45° and 135°.

17. The guided missile of claim 15, wherein a cross-sectional profile of the curved extension, the sleeve-shaped missile body and the aerodynamic extension together form a wing airfoil, and wherein the aerodynamic extension comprises a sharp edge.

18. The guided missile of claim 16, comprising two flight direction control devices, wherein a first flight direction control device of the two flight direction control devices is rotatably mounted to the top area of the sleeve-shaped missile body, and wherein a second flight direction control device of the two flight direction control devices is rotatably mounted to the bottom area of the sleeve-shaped missile body, and wherein the first flight direction control device and the second flight direction control device comprise rotation axes which are arranged coaxially or at an oblique angle with reference to the height axis.

19. The guided missile of claim 15, wherein the flight direction control device comprises one of a slat, a flap, a grid fin, a spoiler, an air brake, a morphing airfoil, a small rocket engine, a gas generator, or an explosive for flight direction control, and the engine comprises one of a rocket engine, an air breathing rocket, a turbine engine, a ram-jet, a scram-jet, an electrically powered fan, or an electrically powered propeller.

20. A guided missile comprising: a sleeve-shaped missile body extending i) from a front section to a rear section, ii) from a bottom area to a top area, and iii) from a left-hand side to a right-hand side; an engine for producing forward thrust and being accommodated inside the sleeve-shaped missile body, the engine comprising a nozzle at the rear section of the sleeve-shaped missile body; a flight direction control device rotatably mounted to the sleeve-shaped missile body for adjusting a flight direction of the guided missile; and an aerodynamic extension having an aerodynamic cross-sectional shape on one side of the sleeve-shaped missile body, wherein the aerodynamic extension forms together with the sleeve-shaped missile body a lift generating airfoil at an angle oblique to a longitudinal axis of the missile body for producing additional lift during flight, and wherein a curved extension is arranged on the other side of the sleeve-shaped missile body.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) Embodiments are outlined by way of example in the following description with reference to the attached drawings. In these attached drawings, identical or identically functioning components and elements are labeled with identical reference numbers and characters and are, consequently, only described once in the following description.

(2) FIG. 1 shows a perspective view of a guided missile with an aerodynamic extension on its right-hand side,

(3) FIG. 2a shows a top view of the guided missile of FIG. 1 with the aerodynamic extension on the right-hand side,

(4) FIG. 2b shows a top view of the guided missile of FIG. 1 with an aerodynamic extension on its left-hand side,

(5) FIG. 3a shows a schematic cross-sectional view of the guided missile of FIG. 1 with a pair of flight direction control devices, in accordance with some embodiments,

(6) FIG. 3b shows a schematic cross-sectional view of the guided missile of FIG. 1 with a single flight direction control device, in accordance with some embodiments,

(7) FIG. 3c shows a schematic cross-sectional view of the guided missile of FIG. 1 with a pair of flight direction control devices on the top area of the guided missile, in accordance with some embodiments,

(8) FIG. 3d shows a schematic cross-sectional view of the guided missile of FIG. 1 with two pairs of flight direction control devices, in accordance with some embodiments,

(9) FIG. 4a shows a schematic cross-sectional view of the guided missile of FIG. 1 with a curved extension, in accordance with some embodiments,

(10) FIG. 4b shows a schematic cross-sectional view of the guided missile of FIG. 1 with an aerodynamic extension which comprises a sharp edge, in accordance with some embodiments,

(11) FIG. 4c shows a schematic cross-sectional view of the guided missile of FIG. 1 with two aerodynamic extensions which comprise a sharp edge, in accordance with some embodiments, and

(12) FIG. 5 shows a schematic cross-sectional view of the guided missile of FIG. 1 with an additional engine, in accordance with some embodiments.

DETAILED DESCRIPTION

(13) FIG. 1 shows an exemplary guided missile 100 with a sleeve-shaped missile body 105. Illustratively, the sleeve-shaped missile body 105 extends along a longitudinal axis R from a front section 110 to a rear section 111, along a height axis Y from a bottom area (104 in FIG. 3a) to a top area 103, and along a transversal axis P from a left-hand side 101 to a right-hand side 102.

(14) The sleeve-shaped missile body 105 may be made of metallic or composite materials with heat-absorbing materials or protective coatings. The front section 110 of the sleeve-shaped missile body 105 may be embodied as a conical, elliptical, or bulbous fairing.

(15) If desired, the sleeve-shaped missile body 105 may comprise an internal compartment (not shown) for payload. For example, payload may comprise dedicated guidance, navigation, and control equipment, countermeasures equipment, and/or munitions of any type.

(16) The guided missile 100 may comprise at least one sensor 117 that is preferably mounted to the front section 110 of the sleeve-shaped missile body 105. Various type of sensors 117 may be used. By way of example, radar sensors or optical sensors may be used.

(17) Preferably, the guided missile 100 comprises at least one engine (300 in FIG. 3a) for producing forward thrust during operation. The at least one engine (300 in FIG. 3a) may be accommodated inside the sleeve-shaped missile body 105.

(18) The at least one engine (300 in FIG. 3a) may comprise a nozzle 115 that is arranged at the rear section 111 of the sleeve-shaped missile body 105. Upon activation of the at least one engine (300 in FIG. 3a), expanding high-temperature gases may escape at high speeds through the nozzle 115.

(19) Illustratively, the shape of the nozzle 115 is conical. Alternatively, the shape of the nozzle 115 may be cylindrical or any other suitable shape.

(20) Preferably, the guided missile 100 comprises at least one flight direction control device 107 that is rotatably mounted to the top area 103 and/or the bottom area (104 in FIG. 3a) of the sleeve-shaped missile body 105. The at least one flight direction control device 107 may be provided for adjusting a flight direction 113, 114 of the guided missile 100.

(21) Illustratively, the flight direction 113 is oriented in parallel to the longitudinal axis R and, thus, represents a straight flight direction. The flight direction 114, in turn, is oriented obliquely to the longitudinal axis R and, thus, represents an oblique flight direction.

(22) The at least one flight direction control device 107 is preferably of the rudder type. The at least one flight direction control device 107 may be rotatable around the height axis Y by a rotation angle (α1, α2 in FIG. 2a and FIG. 2b) comprised between −45° to 135°, preferably between 0° and 90°.

(23) More specifically, the at least one flight direction control device 107 may be used to control yaw of the guided missile 100. Accordingly, the flight direction 113, 114 of the guided missile 100 may preferably be controlled to be at least in a range comprised between 0° and 90°. In other words, an underlying angle between the straight flight direction 113 and the oblique flight direction 114 should preferably be controllable at least in the range comprised between 0° and 90°.

(24) For controlling the rotation of the at least one flight direction control device 107 in operation, the guided missile 100 may comprise a conventional control system (not shown). The at least one flight direction control device 107 may be actuated by hydraulic or electrical power units, under control of the conventional control system.

(25) The at least one flight direction control device 107 may be embodied as a wing-shaped flight direction control device 107. If desired, the at least one flight direction control device 107 may comprise a slat, a flap, a grid fin, a spoiler, an air brake, a morphing airfoil, a small rocket engine, a gas generator, and/or an explosive for flight direction control.

(26) By way of example, the at least one flight direction control device 107 comprises a first flight direction control device 108 and a second flight direction control device 109. Illustratively, the first flight direction control device 108 is arranged in, or close to, the front section 110 of the sleeve-shaped missile body 105 and the second flight direction control device 109 is arranged in, or close to, the rear section 111 of the sleeve-shaped missile body 105. By way of example, the first and second flight direction control devices 108, 109 are rotatably mounted to the top area 103 of the sleeve-shaped missile body 105.

(27) Preferably, the guided missile 100 comprises at least one aerodynamic extension 106 that is arranged on the left-hand side 101 and/or the right-hand side 102 of the sleeve-shaped missile body 105. The at least one aerodynamic extension 106 preferably comprises an aerodynamic cross-sectional shape 112a, 112b, 112c.

(28) Illustratively, the guided missile 100 comprises an aerodynamic extension 106 that is arranged on the right-hand side 102 of the sleeve-shaped missile body 105. The aerodynamic cross-sectional shape 112a, 112b, 112c of the aerodynamic extension 106 forms an aerodynamic wing, by way of example.

(29) Preferably, the at least one aerodynamic extension 106 forms together with the sleeve-shaped missile body 105 a lift-producing airfoil. Such a configuration is advantageous to produce additional lift during flight, as an overall sleeve-shaped missile body area is increased.

(30) The aerodynamic extension 106 preferably extends from the front section 110 of the sleeve-shaped missile body 105 to the rear section 111 of the sleeve shaped missile body 105. Illustratively, the aerodynamic extension 106 is embodied as a truncated triangular prism.

(31) Furthermore, the at least one aerodynamic extension 106 may comprise at least one aileron 116. The at least one aileron 116 may be mounted pivotably to a rear or trailing edge 102a, 102b of the at least one aerodynamic extension 106. The at least one aileron 116 may be a bi-directional aileron 116.

(32) The at least one aileron 116 may be used to control movement of the guided missile 100 around the longitudinal axis R, i.e., rolling of the guided missile 100. The at least one aileron 116 thereby acts as an additional control surface.

(33) The at least one aileron 116 may comprise a control axis 118a, 118b that is oriented at an oblique angle δ1, δ2 to the longitudinal axis R of the sleeve-shaped missile body 105. The control axis 118a, 118b oriented at an oblique angle δ1, δ2 allows efficient control both in straight flight direction and in oblique flight direction. If desired, the at least one aileron 116 may alternatively comprise a control axis 118a, 118b that is oriented in parallel or at a perpendicular angle to the longitudinal axis R of the sleeve-shaped missile body 105.

(34) Illustratively, two ailerons 116 are pivotably mounted to the trailing edges 102a, 102b of the aerodynamic extension 106. The two ailerons 116 may extend from about a midpoint of the aerodynamic extension 106 outward toward a respective tip of the aerodynamic extension 106.

(35) By way of example, a first aileron 116 is pivotably mounted to a front part of the trailing edge 102a of the aerodynamic extension 106 along a control axis 118a. The control axis 118a is oriented at an oblique angle δ1 to the longitudinal axis R of the sleeve-shaped missile body 105. The oblique angle δ1 may be comprised between 0° and 90°.

(36) By way of example, a second aileron 116 is rotatably mounted to the rear part of the trailing edge 102b of the aerodynamic extension 106 along a control axis 118b. The control axis 118b is oriented at an oblique angle δ2 to the longitudinal axis R of the comprise between 0° and 90°.

(37) Illustratively, a center of gravity G is embodied at a central position of the guided missile 100. The center of gravity G may be defined as an average location of weight of the guided missile 100. Illustratively, the longitudinal axis R, the transversal axis P and the height axis Y pass through the center of gravity G at 90° angles to each other. Whenever the guided missile 100 changes its flight attitude or position in flight, it rotates about one or more of the three axes. Illustratively, a most extended point of the aerodynamic extension 106 and/or a respective center of the aerodynamic extension 106 along the longitudinal axis R may be aligned with the center of gravity G.

(38) FIG. 2a shows the guided missile 100 of FIG. 1 with the at least one aerodynamic extension 106 which is exemplarily arranged on the right-hand side 102 of the sleeve-shaped missile body 105. The guided missile 100 comprises the at least one flight direction control device 107. The at least one flight direction control device 107 is illustratively of the rudder type.

(39) By way of example, the at least one flight direction control device 107 is rotatably mounted on the top area 103 of the sleeve-shaped missile body 105. The at least one flight control device 107 illustratively comprises the first flight direction control device 108 and the second flight direction control device 109. The first flight direction control device 108 is arranged close to the front section 110 of the sleeve-shaped missile body 105 and the second flight direction control device 109 is arranged close to the rear section 111 of the sleeve-shaped missile body 105.

(40) Rotation of the first and/or second flight direction control devices 108, 109 changes airflow and pressure distribution over and around the guided missile 100. As indicated above, the first and second flight direction control devices 108, 109 may be rotatable around the height axis (Y in FIG. 1) by a rotation angle α1, α2 comprised between −45° and 135°. Thus, the flight direction 113, 114 may be controlled in the range between 0° et 90°.

(41) By way of example, prior to launch or in a first flight configuration, the guided missile 100 travels in the straight flight direction 113 and the first and second flight direction control devices 108 are aligned with the longitudinal axis R of the guided missile 100. During operation, the first and second flight direction control devices 108, 109 may be rotated by rotation angles α1, α2 comprised between −45° and 135° such that the guided missile 100 changes its direction of flight from the straight flight direction 113 into the oblique flight direction 114.

(42) More specifically, the first and second flight direction control devices 108, 109 are preferably embodied such that they may be rotated from a straight position to an oblique position in order to stabilize and control the guided missile 100 in the oblique flight direction 114. Thus, rotation of the first and second flight direction control devices 108, 109 causes transition from a flight configuration with the straight flight direction 113 to a flight configuration with the oblique flight direction 114.

(43) For instance, in order to adjust a desired direction of flight of the guided missile 100, the first and second flight direction control devices 108, 109 are rotated into positions illustrated by means of dashed first and second flight direction control devices 208, 209. The dashed flight direction control devices 208, 209 illustratively define a length axes 114a, 114b which are parallel to the oblique flight direction 114.

(44) After rotation of the first and second flight direction control devices 108, 109, the guided missile 100 is stabilized in order to fly in the oblique flight direction 114, without the need to rotate the front part 110 of the guided missile 100.

(45) FIG. 2b shows the guided missile 100 of FIG. 1 and FIG. 2a with the at least one aerodynamic extension 106. More specifically, FIG. 2b shows the guided missile 100 during flight in the straight flight direction 113 according to FIG. 1 and FIG. 2a, and after rotation of the first and second flight direction control devices 108, 109, indicated with dashed flight direction control devices 208′, 209′ which define length axes 114a′, 114b′, such that the guided missile 100 is adjusted to fly in an illustrative oblique flight direction 114′.

(46) However, in contrast to FIG. 1 and FIG. 2a the at least one aerodynamic extension 106 is now exemplarily arranged on the left-hand side 101 of the sleeve-shaped missile body 105. Furthermore, the at least one aileron 116 is now pivotably mounted to a trailing edge 201a, 201b of the aerodynamic extension 106 on the left-hand side 101. By way of example, a first aileron 116 is pivotably mounted to a front part of the trailing edge 201a, and a second aileron 116 is pivotably mounted to a rear part of the trailing edge 201b. The two ailerons 116 may preferably pivot in opposite directions to create aerodynamic forces that cause the guided missile 100 to roll.

(47) FIG. 3a shows the guided missile 100 of FIG. 1 with the at least one flight direction control device 107 that is now illustratively embodied by a pair of first and second flight direction control devices 307, 308, both of which are of the rudder type, by way of example. The first flight direction control device 307 is illustratively rotatably mounted on the top area 103 of the sleeve-shaped missile body 105. The second flight direction control device 308 is illustratively rotatably mounted on the bottom area 104 of the sleeve-shaped missile body 105.

(48) By way of example, the first flight direction control device 307 is rotatable around a rotation axis 304. The second flight direction control device 308 is similarly rotatable around the rotation axis 304. In other words, the first flight direction control device 307 and the second flight direction control device 308 share the common rotation axis 304, which is illustratively parallel to the height axis Y. The first flight direction control device 307 and the second flight direction control device 308 are illustratively symmetrical with respect to the transversal axis P of the sleeve-shaped missile body 105.

(49) Furthermore, an internal compartment 301 is illustrated, which is located inside the sleeve-shaped missile body 105. The internal compartment 301 illustratively accommodates at least one engine 300. The at least one engine 300 may comprise a rocket engine, an air breathing rocket, a turbine engine, a ram-jet, a scram-jet, and/or an electrically powered fan or propeller.

(50) As described above at FIG. 1, the sleeve-shaped missile body 105 is provided with the at least one aerodynamic extension 106 on the right-hand side 102. Furthermore, the at least one aileron 116 is pivotably mounted to the at least one aerodynamic extension 106. The at least one aileron 116 may be embodied as triangular prism.

(51) More specifically, the at least one aileron 116 is illustratively pivotable between first and second positions 116a, 116b. By way of example, the at least one aileron 116 is pivotable by an angle γ. The angle γ may be comprised between 0° and 180°.

(52) By way of example, the at least one aerodynamic extension 106 comprises two ailerons 116. Illustratively a first aileron is illustrated in the first position 116a, and a second aileron is illustrated in the second position 116b.

(53) FIG. 3b shows the guided missile 100 of FIG. 1 with the at least one flight direction control device 107 that is now illustratively embodied only by means of the flight direction control device 307 of FIG. 3a. As described at FIG. 3a, the flight direction control device 307 is preferably rotatably mounted on the top area 103 of the sleeve-shaped missile body 105. However, if desired the flight direction control device 307 may alternatively be rotatably mounted on the bottom area 104 of the sleeve-shaped missile body 105.

(54) FIG. 3c shows the guided missile 100 of FIG. 1 with the at least one flight direction control device 107 that is now illustratively embodied by a pair of first and second flight direction control devices, which comprise the flight direction control device 307 of FIG. 3b and an additional flight direction control device 306, which is preferably also of the rudder type. By way of example, the first and the second flight direction control devices 306, 307 are both rotatably mounted on the top area 103 of the sleeve-shaped missile body 105.

(55) Illustratively, the first flight direction control device 307 is now rotatable around a rotation axis 302, and the second flight direction control device 306 is rotatable around a rotation axis 303. The rotation axes 302, 303 are arranged with an angle β relative to each other, by way of example. More specifically, the rotation axis 302 is preferably arranged at an oblique angle β1 with reference to the height axis Y. Similarly, the rotation axis 303 is arranged at an oblique angle β2 with reference to the height axis Y.

(56) By way of example, β1 is equal to β2 with β1=β2=β/2. Thus, the first and second flight direction control devices 307, 306 are arranged symmetrically on the sleeve-shaped missile body 105 with respect to the height axis Y. However, if desired oblique angle β1 and oblique angle β2 may have different values.

(57) FIG. 3d shows the guided missile 100 of FIG. 1 with the at least one flight direction control device 107 that is now illustratively embodied by two pairs of first and second flight direction control devices 311, 312; 309, 310, all of which are of the rudder type, by way of example. More specifically, the two pairs comprise a first flight direction control device 311, a second flight direction control device 312, a third flight direction control device 309 and a fourth flight direction control device 310.

(58) Illustratively, the first flight direction control device 311 and the second flight direction control device 312 are rotatably mounted on the top area 103 of the sleeve-shaped missile body 105. The third flight direction control device 309 and the fourth flight direction control device 310 are rotatably mounted on the bottom area 104 of the sleeve-shaped missile body 105.

(59) By way of example, the first flight direction control device 311 and the fourth flight direction control device 310 are arranged on a common rotation axis 302. The second flight direction control device 312 and the third flight direction control device 309 are arranged on a common rotation axis 303. By way of example, in order to obtain an equal repartition of the weight, the rotation axes 302 and 303 are crossing at the center of the at least one engine 300.

(60) Illustratively, the first flight direction control device 311 and the second flight direction control device 312 are arranged relative to each other at the oblique angle β of FIG. 3c. Similarly, the third flight direction control device 309 and the fourth flight direction control device 310 are also arranged at the oblique angle β.

(61) Furthermore, the rotation axis 302 is preferably arranged at the oblique angle β1 of FIG. 3c with respect to the height axis Y and the rotation axis 303 is arranged at the oblique angle β2 with respect to the height axis Y. By way of example, β1 is equal to β2 with β1=β2=β/2. However, if desired oblique angle β1 and oblique angle β2 may have different values.

(62) FIG. 4a shows the guided missile 100 of FIG. 1 with the at least one aerodynamic extension 106 arranged on the right-hand side 102 of the sleeve-shaped missile body 105. By way of example, the guided missile 100 comprises the at least one flight direction control device 107 according to FIG. 3a, which comprises the first flight direction control device 307 that is rotatably mounted on the top area 103 the sleeve-shaped missile body 105, and the second flight direction control device 308 that is rotatably mounted on the bottom area 104 of the sleeve-shaped missile body 105. However, any other number, orientation and/or positioning of respective individual flight direction control devices may alternatively be considered.

(63) In contrast to FIG. 1 and FIG. 3a, the sleeve-shaped missile body 105 is now further provided with a curved extension 400 arranged on the left-hand side 101. Provision of the curved extension 400 in addition to the at least one aerodynamic extension 106 may be more efficient for a flight in subsonic speed.

(64) Illustratively, the cross-sectional profile of the curved extension 400, the sleeve-shaped missile body 105 and the at least one aerodynamic extension 106 together forms a wing airfoil 412. Implementation of the wing airfoil 412 may be advantageous in terms of lifting forces. Moreover, the wing airfoil 412 may reduce drag during flight of the guided missile.

(65) FIG. 4b shows the guided missile 100 of FIG. 1 with the at least one aerodynamic extension 106 arranged on the right-hand side 102 of the sleeve-shaped missile body 105. By way of example, the guided missile 100 comprises the at least one flight direction control device 107 according to FIG. 3a, which comprises the first flight direction control device 307 that is rotatably mounted on the top area 103 the sleeve-shaped missile body 105, and the second flight direction control device 308 that is rotatably mounted on the bottom area 104 of the sleeve-shaped missile body 105. However, any other number, orientation and/or positioning of respective individual flight direction control devices may alternatively be considered.

(66) However, in contrast to FIG. 1 and FIG. 3a the at least one aerodynamic extension 106 now also extends on the left-hand side 101 of the sleeve-shaped missile body 105. In other words, the at least one aerodynamic extension 106 is arranged on the left-hand side 101 of the sleeve-shaped missile body 105 and on the right-hand side 102 of the sleeve-shaped missile body 105. By way of example, the at least one aerodynamic extension 106 on the left-hand side 101 and on the right-hand side 102 of the sleeve-shaped missile body 105 respectively comprises a sharp edge 401. The sharp edge 401 may be advantageous for supersonic speed flight of the guided missile 100.

(67) Furthermore, the guided missile 100 illustratively comprises the at least one engine 300 of FIG. 3a. By way of example, the at least one engine 300 is arranged centrally in the cross section of the sleeve-shaped missile body 105, which is advantageous in term of weight repartition.

(68) FIG. 4c shows the guided missile 100 of FIG. 1 with the at least one aerodynamic extension 106 that extends on the left-hand side 101 and on the right-hand side 102 of the sleeve-shaped missile body 105 according to FIG. 4b. Furthermore, the guided missile 100 illustratively comprises the at least one flight direction control device 107 of FIG. 1 that is illustratively embodied according to FIG. 3d, i.e., with the two pairs of first and second flight direction control devices 311, 312; 309, 310. However, a higher number of flight direction control devices may also be considered, which may be advantageous to change quickly and efficiently an underlying direction of flight of the guided missile 100 at supersonic speed.

(69) FIG. 5 shows the guided missile 100 according to FIG. 4a with the sleeve-shaped missile body 105 and the at least one engine 300. However, in contrast to FIG. 4a, the guided missile 100 now preferably comprises an additional engine 500, which may also be provided for producing forward thrust.

(70) Similar to the at least one engine 300, the additional engine 500 is preferably accommodated inside the sleeve-shaped missile body 105. Illustratively, the additional engine 500 is accommodated on the right-hand side 102 of the sleeve-shaped missile body 105 and, more specifically, on the right side of the at least one engine 300. By way of example, the at least one engine 300 and the additional engine 500 are arranged in parallel to each other.

(71) If desired, the additional engine 500 may be accommodated as illustrated inside the at least one aerodynamic extension 106. More specifically, the sleeve-shaped missile body 105 preferably comprises an additional internal compartment 501, in which the additional engine 500 is located.

(72) Preferably, the additional engine 500 is smaller than the at least one engine 300. However, if desired the additional engine 500 could have a similar size to the at least one engine 300.

(73) Preferably, the additional engine 500 comprises a rocket engine, an air breathing rocket, a turbine engine, a ram-jet, a scram-jet, and/or an electrically powered fan or propeller.

(74) It should be noted that the above-described embodiments are merely described to illustrate possible realizations of the present disclosure, but not in order to restrict the present disclosure thereto. Instead, multiple modifications and variations of the described embodiments are possible and should, therefore, also be considered as being part of the disclosure.

(75) By way of example, any combination of flight direction control devices could be possible according to the disclosure. Furthermore, any number of additional engines could be used. If desired, the engines could be stacked in series inside the guided missile.

REFERENCE LIST

(76) 100 guided missile 101 left-hand side 102 right-hand side 102a, 201a trailing edge front part 102b, 201b trailing edge rear part 103 top area 104 bottom area 105 sleeve-shaped missile body 106 aerodynamic extension 107 multiplicity of flight direction control devices 108, 109, 306, 307, 308, 309, 310, 311, 312 individual flight direction control devices 110 front section 111 rear section 112a, 112b, 112c cross-sectional shape 113, 114, 114′ flight direction 114a, 114b, 114a′, 114b′ axis of the flight direction control device 115 nozzle of the rocket engine 116 ailerons 116a, 116b position of aileron 117 sensor 118a, 118b control axis 208, 208′ first flight direction control device after rotation 209, 209′ second flight direction control device after rotation 300 engine 301 internal compartment 302, 303, 304 rotations axes 400 curved extension 401 sharp edge 412 wing airfoil 500 additional engine 501 additional internal compartment R longitudinal axis Y height axis P transversal axis G center of gravity α1, α2 rotation angles β1, β2, δ1, δ2 oblique angles γ aileron pivot angle