Guided missile

Abstract

The guided missile (1) is a propulsion system (2) with an engine (3) having a combustion chamber (14-17) and at least one discharge nozzle (8-11) connected to the combustion chamber (14-17) by means of a connecting line (18-21) and designed to expel a propellant stream through the discharge nozzle (8-11), where a control device (22-25) is designed to rotate the direction of at least one engine unit (4-7) of the combustion chamber (14-17) and at least one discharge nozzle (8-11) around a rotation axis (26, 33-35) oriented perpendicular to the longitudinal axis (27) of the guided missile (1), to at least one first launch position and at least one second launch position.

Description

[0001] The invention relates to a guided missile with a propulsion system comprising an engine with at least one engine unit, which has a combustion chamber and at least one exhaust nozzle fixed in its orientation to the combustion chamber via a connecting line and is designed to expel a propellant gas flow through the exhaust nozzle.

[0002] Propulsion systems for guided missiles, comprising an engine with a single engine unit, are generally known from the prior art. In these systems, fuel is burned in a combustion chamber, and the combustion gases are expelled under pressure from an outlet nozzle connected to the combustion chamber via a connecting line to generate or modify the missile's motion. Various systems are known for thrust vectoring, for example, in the form of separate lateral thrust engines. However, these have significantly lower power output compared to main engines designed for longitudinal propulsion of the guided missile, thus severely limiting the maximum achievable lateral thrust.

[0003] Further thrust vectoring systems can be implemented in the form of swiveling outlet nozzles, for example, pendulum nozzles. It is known that their swivel range is limited, for example, to a range below 20° for pendulum nozzles. Other known thrust vectoring systems require rotary joints or nozzle needles, or different kinematics that engage with the hot gas jet. Such systems are therefore complex in their design, as they must reliably withstand the high exhaust gas temperatures to protect them from the severe erosion in the hot gas jet.

[0004] A missile with adjustable engines is known from publication US 3 188 024 A. Further missiles are known from publications CH 381 020 A and US 2 981 501 A.

[0005] The invention is based on the objective of providing an improved guided missile in comparison.

[0006] The problem is solved by a guided missile with the features of claim 1, by a propulsion system with the features of claim 8, and by a method with the features of claim 9. Advantageous embodiments are the subject of the dependent claims.

[0007] As described at the outset, the invention relates to a guided missile with a propulsion system comprising an engine. The engine, in turn, comprises at least one engine unit, which has a combustion chamber and at least one exhaust nozzle connected to the combustion chamber via a connecting line. The term "exhaust nozzle" can generally be replaced by the term "exhaust opening." The exhaust nozzle, for example, forms a nozzle angled relative to the longitudinal axis of the engine. For example, the connecting line can, at least in one section, extend radially outward from a region of the combustion chamber and open into the exhaust nozzle, which is angled in a direction parallel to the longitudinal axis of the engine. The exhaust nozzle, or...A propellant gas stream exiting the exhaust nozzle, particularly a hot gas jet, can also be expelled at a specific angle relative to an axis parallel to the engine's longitudinal axis, for example, at an angle relative to an outer surface of the missile's fuselage. As described, the exhaust opening is rigidly connected to the combustion chamber via the connecting line, so that a change in the exhaust opening's orientation relative to the combustion chamber is not possible.

[0008] The invention is based on the finding that the propulsion system of the guided missile has an actuating device configured to rotate the orientation of the combustion chamber and the at least one exhaust nozzle of the at least one engine unit about an axis of rotation, in particular oriented perpendicular to a longitudinal axis of the guided missile, into at least one first exhaust position and at least one second exhaust position. In other words, the at least one engine unit can be associated with an actuating device configured to rotate the engine unit about the axis of rotation and thereby rotate the orientation of the exhaust nozzle relative to the guided missile or a fuselage of the guided missile. In the installed state of the propulsion system, the actuating device is thus configured to rotate the engine unit within the fuselage of the guided missile, namely about the axis of rotation perpendicular to its longitudinal axis.The rotatable engine unit is thus rotatably mounted within the missile's fuselage. The combustion chamber, along with the connecting line and the exhaust nozzle, is always rotated. Advantageously, this eliminates the need for a rotary bushing in the exhaust nozzle area. Such a rotary bushing would be extremely complex to withstand the temperatures, particularly those in the range of several thousand Kelvin, and the corresponding pressures encountered during the operation of the missile and / or the propulsion system.

[0009] As described, the axis of rotation can be specifically oriented perpendicular to the longitudinal axis of the guided missile, i.e., perpendicular to the missile's flight direction. The axis of rotation can be considered, for example, as the vertical or lateral axis relative to the missile's symmetry. Thus, the rotatable engine unit—that is, the rotation of the nozzle's orientation together with its combustion chamber, to which it is rigidly attached—offers the possibility of changing the ejection position. This allows the direction from which, or in which, the propellant gas stream is expelled through the nozzle to be altered during missile operation. For this purpose, the drive system includes at least one actuator in the actuating device, such as an electric motor.The actuator is connected to the combustion chamber via a transmission mechanism, for example, a pinion with a rack located on the outer surface of the combustion chamber, or a gear or gear segment on the circumference of the combustion chamber. When the electric motor rotates the pinion, the combustion chamber is rotated, thus changing the orientation of the exhaust nozzle and thereby determining the thrust direction of the engine unit. The guided missile, which incorporates the propulsion system, may have at least one bearing arrangement designed for the rotatable mounting of the combustion chamber.

[0010] In other words, the entire engine unit is rotatably mounted within the missile fuselage, specifically the fuselage of the guided missile, which houses the propulsion unit. To achieve static moment equilibrium, several engine units of the aforementioned type can be accommodated within the missile fuselage, with the individual thrust vectors adding up to a total thrust or propulsion. A configuration with multiple engine units will be discussed in the following description.

[0011] In principle, the term "engine" is used in this description to refer to all engine units, each of which has a combustion chamber and an exhaust nozzle rigidly connected to the combustion chamber. The propulsion system, in turn, comprises the engine and other components necessary for its operation, such as bearings for the engine units and the like. The at least one actuating device associated with the at least one engine unit described can therefore be part of the engine or the propulsion system.

[0012] As described, the actuator is designed and configured to rotate the engine unit, thereby changing the orientation of the exhaust nozzle or setting a desired orientation. For example, the actuator can position the exhaust nozzle in a first ejection position, in which the nozzle has a first orientation, such as a first ejection angle relative to any axis, for example, the longitudinal axis of the propulsion system. Likewise, the actuator can position the exhaust nozzle in at least one second ejection position, in which the nozzle has a second orientation, for example, a second ejection angle relative to any axis, such as the longitudinal axis of the propulsion system. Specifically, the actuator can position the exhaust nozzle in any desired ejection position, such that the angle or...The discharge angle of the outlet nozzle can also be adjusted as desired.

[0013] The actuating device can, for example, be configured to rotate at least one engine unit by 90° in both directions relative to a longitudinal axis of the guided missile. Starting from a basic position of the exhaust nozzle, in which its orientation is aligned along the longitudinal axis of the guided missile, the actuating device can deflect the orientation of the exhaust nozzle by 90° in both directions of rotation, i.e., + / - 90° relative to the longitudinal axis. In a further embodiment, a complete rotation of the engine unit can be performed, allowing it to rotate, for example, continuously through 360°.

[0014] The orientation of the exhaust nozzle can be adjusted to any desired ejection angle or position to expel the propellant gas stream in that orientation, thereby achieving a corresponding change or generation of the missile's motion. If the engine axis of the propulsion unit, i.e., the orientation of the exhaust nozzle, is perpendicular to the missile's longitudinal axis, then a 90° rotation in any direction of rotation can (at least theoretically) produce a thrust vector ranging from 100% axial to 100% lateral. Extending the rotational range to 360° allows for even more precise thrust vector adjustments, for example, with at least one component opposing the current direction of motion.

[0015] In particular, the actuating device may be designed to selectively rotate at least one engine unit into either a longitudinal thrust position or a lateral thrust position. The longitudinal thrust position is present when the engine unit is oriented such that the propellant gas flow is expelled along the longitudinal axis of the propulsion system, thus generating thrust or longitudinal thrust of the guided missile. A lateral thrust position is present when the propellant gas flow is expelled perpendicular to the longitudinal axis of the guided missile, thus generating lateral thrust.

[0016] As previously described, the actuator can be configured to set any ejection position between the longitudinal thrust position and the transverse thrust position. This offers the advantage that at least one engine unit can be used to generate both longitudinal and transverse thrust. Therefore, additional engine units used exclusively for generating transverse thrust are unnecessary. Consequently, a division of the engine units into main engine units responsible for generating longitudinal thrust and auxiliary units that generate only transverse thrust and have significantly reduced performance compared to the main engine units is not required.Instead, the same engine unit can be used to generate both longitudinal and lateral thrust, with the engine unit being moved to different ejection positions as previously described in order to change the thrust vector accordingly.

[0017] In particular, it can be provided that in the transverse thrust position, all thrust achievable by the engine unit can be generated as transverse thrust. If the engine has multiple engine units, all engine units can be moved into the transverse thrust position, so that all longitudinal thrust achievable by the engine can also be used or provided as transverse thrust as needed. Specifically, propellant gas flows from all combustion chambers can thus be used simultaneously to generate transverse thrust, while the same combustion chambers can be used to generate longitudinal thrust in a different exhaust position of the engine units. This offers the advantage that the generation of transverse thrust is not inferior to the generation of longitudinal thrust in terms of performance; rather, transverse thrust can be generated to the same extent as longitudinal thrust.This offers significantly greater possibilities for generating lateral thrust. Likewise, there is no need to carry and calculate separate combustion chambers and fuel reserves; instead, all thrust can be generated with the same resources. Since the ejection position of the engine units can be changed as needed, it is possible to switch between generating longitudinal and lateral thrust at will, or to generate either lateral or longitudinal thrust depending on the situation.

[0018] As described at the beginning, the engine can have multiple engine units. Specifically, the engine can have at least two rotatable engine units that can rotate independently of each other. Each engine unit can be coupled to its own actuator, which can position the respective engine unit. As previously described, each engine unit provides its own combustion chamber with its own exhaust nozzle, which is connected to the combustion chamber via a connecting line. By setting the individual engine units to independent exhaust positions, the movement of the guided missile can be better controlled. In particular, different thrust vectors or motion vectors can be set.If more than two rotatable engine units are used, for example four rotatable engine units, any motion vectors or thrust vectors can be set, allowing all degrees of freedom of the guided missile's movement to be controlled. Specifically, the guided missile can thus be controlled or steered based on a "bank-to-turn" or "banked-turn" control system.

[0019] The engine can, for example, have four rotatable engine units whose exhaust nozzles are arranged in pairs at opposite circumferential positions of the guided missile. The paired arrangement of the exhaust openings in four or more engine units, which can be controlled independently of each other, makes it possible to control and adjust all movements in space.In principle, various arrangements of the exhaust ports are possible. For example, the first exhaust port of a first engine unit can be located on the first circumferential position of the guided missile; a second exhaust port of a second engine unit can be located on the second circumferential position opposite the first circumferential position of the guided missile; a third exhaust port of a third engine unit can again be located on the first circumferential position of the guided missile; and a fourth exhaust port of a fourth engine unit can be located on the second circumferential position of the guided missile. Thus, the arrangement of the exhaust ports of the at least four engine units can be alternating. The circumferential positions can be diametrically opposed. In principle, the exhaust ports can also be located on any other circumferential position.

[0020] In a further embodiment, the first exhaust port of the first engine unit and the fourth exhaust port of the fourth engine unit can be arranged at the first circumferential position (or the second circumferential position) of the guided missile, and the second exhaust port of the second engine unit and the third exhaust port of the third engine unit can be arranged at the second circumferential position (or the first circumferential position) of the guided missile. The described paired arrangement of the exhaust ports at opposite circumferential positions ensures that the applied moments can be stabilized or balanced, thus generating a defined, and in particular symmetrical, motion of the guided missile.

[0021] All movements in the room can be controlled with four individually controllable nozzles. For installation purposes, it may be necessary to offset the two nozzles of a pair, which means the resulting asymmetries must be taken into account during control. Two rigidly coupled pairs of nozzles avoid these asymmetries. A roll position control system can also be incorporated. Such a roll position control system is described below in connection with a rolling system.

[0022] The missile's engine comprises at least one rotatable engine unit with two opposing exhaust ports. As previously described, the rotatable engine unit can have one exhaust port connected to the combustion chamber via a connecting line, allowing it to rotate with the combustion chamber. The present embodiment provides that such a rotatable engine unit can have two opposing exhaust ports, such that the two exhaust ports, located at opposite circumferential positions, can rotate around the axis of rotation together with the combustion chamber. Several such engine units can be provided, for example, two engine units, each with two opposing exhaust ports.The exhaust openings can, as already described, be arranged at a first circumferential position and a second circumferential position of the guided missile. The described engine units with two exhaust nozzles ensure that the two thrust vectors act at the same point on the longitudinal axis.

[0023] As previously described, depending on the arrangement or configuration of the exhaust nozzles of the individual engine units, an additional roll system may be necessary or at least advantageous. According to one embodiment, the propulsion system can include such a roll system, which has at least one roll nozzle oriented tangentially to the guided missile, for example, to a fuselage of the guided missile, and is designed to set or change a roll position and / or roll movement by expelling gas from the roll nozzle. The roll system can thus expel a gas stream from the roll nozzle that exerts a torque on the guided missile and rotates the guided missile about its longitudinal axis, i.e., that a defined roll position can be set or changed, or a defined roll movement, i.e., a rotation about the longitudinal axis, can be set or changed.The emission from the rolling nozzle can slow down an existing rolling motion, especially to a standstill, or intensify it.

[0024] The rolling system can specifically have two opposing rolling nozzles, enabling rolling movements or changes in rolling position in both directions. Likewise, an initial rolling movement can be generated by an ejection from a first rolling nozzle, which can then be slowed or stopped by an ejection from the second rolling nozzle. Furthermore, the rolling system can have multiple rolling units, each with at least one or two rolling nozzles, which can be specifically oriented opposite each other.

[0025] In addition to the guided missile, the invention relates to a propulsion system for such a guided missile. The guided missile can, in particular, be launched by means of a carrier system that can be detached from the guided missile after an initial operating phase. Thus, the guided missile is not launched from the ground, but rather, when the propulsion system of the guided missile is started or ignited, the missile has already been moved by the carrier system. An alternative or supplementary method for controlling the guided missile can provide that the propulsion system of the guided missile is started or ignited in an operating state in which the guided missile is connected to the carrier system, so that the propulsion system of the guided missile can also be used to correct the trajectory of the carrier system coupled to the guided missile. Specifically, the guided missile or...However, the propulsion system of the guided missile is used in a hypersonic range in which the guided missile has already been decoupled from the delivery system.

[0026] Furthermore, in addition to the drive system and the guided missile, the invention relates to a method for controlling a guided missile, comprising a drive system with an engine having at least one engine unit, which has a combustion chamber and at least one exhaust nozzle fixed in its orientation to the combustion chamber via a connecting line, wherein a propellant gas stream is expelled through the exhaust nozzle, wherein the orientation of the combustion chamber and the at least one exhaust nozzle of the at least one engine unit is rotated about an axis of rotation, in particular oriented perpendicular to a longitudinal axis of the guided missile, into at least one first ejection position and at least one second ejection position, wherein the engine has at least one rotatable engine unit having two oppositely arranged exhaust openings.

[0027] All the advantages, details and features described in relation to the propulsion system and the guided missile are fully transferable to the procedure.

[0028] The invention is explained below with reference to exemplary embodiments and the figures. The figures are schematic representations and show: Fig. 1 a schematic sectional view of a guided missile with a propulsion system comprising four engine units according to a first embodiment in a first operating state; Fig. 2 a guided missile with a propulsion system comprising four engine units according to a second embodiment; Fig. 3 a schematic sectional view of the guided missile of Fig. 1 in a second operating state; Fig. 4 a guided missile with a propulsion system with two engine units according to a third embodiment; Fig. 5a an isolated view of an engine unit according to a fourth embodiment in a first operating state; Fig. 5b an isolated view of the engine unit of Fig. 5a in a second operating state; Fig. 6a an isolated representation of a drive unit according to a fifth embodiment in a first operating state; and Fig. 6an isolated representation of the drive unit of Fig. 6a in a second operating state.

[0029] Fig. 1 Figure 1 schematically shows a guided missile 1 with a propulsion system 2 comprising an engine 3 with several engine units 4-7. In the embodiment shown in Figure 2, the propulsion system 2 is a propulsion system 3 with several engine units 4-7. Fig. 1-3 As described, engine 3 has exactly four engine units 4-7. In principle, the number of engine units 4-7 can be changed as desired. Fig. 2 Figure 1 also schematically shows a guided missile 1 with a propulsion system 2, which has an engine 3 with several engine units 4, namely engine units 4-7, which, compared to the first embodiment, are made of Fig. 1 are configured or arranged differently.

[0030] In principle, the descriptions of the two exemplary embodiments can be freely exchanged or transferred between each other.

[0031] As described, the guided missile 1 has a propulsion system 2 with an engine 3. The guided missile 1, which is in Fig. 1 and in detail in Fig. 3 , 4The figure, depicted in various operating states, shows a first engine unit 4, a second engine unit 5, a third engine unit 6, and a fourth engine unit 7. The first engine unit 4 has a first exhaust opening 8, the second engine unit 5 has a second exhaust opening 9, the third engine unit 6 has a third exhaust opening 10, and the fourth engine unit 7 has a fourth exhaust opening 11. The first exhaust opening 8 of the first engine unit 4 is located on a first circumferential position 12 of the guided missile 1. Similarly, the fourth exhaust opening 11 of the fourth engine unit 7 is also located on the first circumferential position 12 of the guided missile 1.In contrast, the second outlet opening 9 of the second engine unit 5 and the third outlet opening 10 of the third engine unit 6 are arranged on a second circumferential position 13 of the guided missile 1, which is opposite the first circumferential position 12 of the guided missile 1.

[0032] At the in Fig. 2 In the guided missile 1 shown according to the second embodiment, the arrangement of the exit openings 8-11 is different. Here, the first exit opening 8 and the second exit opening 9 are arranged as previously described, namely the first exit opening 8 at the first circumferential position 12 and the second exit opening 9 at the second circumferential position 13. However, the third exit opening 10 is located at the first circumferential position 12 and the fourth exit opening 11 is located at the second circumferential position 13. As already mentioned, the following description is freely transferable and interchangeable.

[0033] Each of the engine units 4-7 has a combustion chamber 14-17, which is connected to the respective outlet opening 8-11 via a connecting line 18-21. Each outlet opening 8-11 is rigidly connected to its associated combustion chamber 14-17 via its associated connecting line 18-21, i.e., it is not movable relative to the combustion chamber 14-17. The individual engine units 4-7 are located in the Fig. 1-4 In each of the illustrated embodiments, an actuating device 22-25 is assigned, each comprising an actuator (not shown in detail) and a gearbox coupled to the combustion chamber 14-17 to rotate the combustion chamber 14-17 about a rotational axis 26, 33-35, particularly relative to a fuselage of the guided missile 1. The rotational axes 26, 33-35 are, for example, perpendicular to a longitudinal axis 27 of the propulsion system 2 or of the guided missile 1. The longitudinal axis 27 can, for example, run centrally through the spherical combustion chambers 14-17. The longitudinal axis 27 can, in particular, be the longitudinal center axis of the missile 1. Rotational axes 26, 33-35 that deviate from a perpendicular position to the longitudinal axis 27 are also possible, for example, rotational axes 26, 33-35 that are inclined to the longitudinal axis 27.

[0034] The adjusting devices 22-25 thus make it possible to align each of the engine units 4-7 individually and independently about their respective axes of rotation 26, 33-35, so that the ejection positions of the outlet openings 8-11, i.e., the directions in which a propellant gas stream can exit the outlet openings 8-11, can be set. This makes it possible to set a desired thrust vector. Each of the engine units 4-7 can be used to generate both longitudinal and lateral thrust. Depending on the rotational movement or the angle by which the individual outlet openings 8-11 are rotated, particularly independently of one another, a thrust vector can be set from various components. An example of this is shown in Fig. 1 and 2The figure shows that all engine units 4-7 with their exhaust openings 8-11 are in a basic position in which the exhaust openings 8-11 are aligned along the longitudinal axis 27. As described, this position can be individually adjusted for each engine unit 4-7 by means of the adjusting devices 22-25, so that they can be rotated about the axes of rotation 26, 33-35 according to arrow 28.

[0035] For example, in Fig. 3 As an example, the fourth engine unit 7 is shown rotated 90° relative to the one in Fig. 1 The depicted operating state is shown as having been rotated about the axis of rotation 35. In this operating state, purely by way of example, the first engine unit 4, the second engine unit 5, and the third engine unit 6 generate longitudinal thrust, while the fourth engine unit 7 generates lateral thrust. The depicted position or operating state is to be understood as merely exemplary. It is also possible for each of the other engine units 4-7 to be rotated to any other ejection position, for example, all engine units 4-7 to be rotated to the ejection position in which the fourth engine unit 7 is shown, in order to generate maximum lateral thrust. It is also possible for each of the engine units 4-7 to be rotated completely about its axis of rotation 26, 33-35, i.e., in particular by 360°.Basically, it is sufficient if, starting from the longitudinal thrust position, a rotation of + / - 90° takes place, so that it is possible to transition from the longitudinal thrust position to a transverse thrust position in both directions.

[0036] Fig. 4 Figure 1 shows a guided missile 1 with a propulsion system 2, which includes an engine 3 with, for example, two engine units 4 and 5. The preceding description regarding the mobility of the engine units 4-7 applies entirely to the engine units 4 and 5 in Figure 1. Fig. 4 transferable. The engine units 4, 5 are thus also assigned actuators 22, 23, which can rotate the engine units 4, 5 about axes of rotation 26, 33, which, for example, run perpendicular to the longitudinal axis 27, as shown by arrows 28. In contrast to the previous description, the engine units 4, 5 each have two outlet openings 8, 8' and 9, 9' respectively, which are arranged on the opposite circumferential positions 12, 13 of the guided missile 1. Each combustion chamber 14, 15 is thus assigned two outlet openings 8, 8', 9, 9' and connected via corresponding connecting lines 18, 18', 19, 19'. If the engine unit 4, 5 is rotated about the axis of rotation 26, 33-35 (see arrows 28) both outlet openings 8, 8' and 9, 9' are rotated together with the combustion chamber 14, 15.

[0037] The drive system 2, which is in Fig. 4 As shown, a rolling system 29 has, for example, two pressure chambers 30, 30' and two rolling nozzles 31, 32, which are tangentially aligned so that propellant gas can flow tangentially to generate a rolling motion of the guided missile 1, i.e., a rotation about the longitudinal axis 27. The rolling system 29 can thus be used to set or change a rolling position, i.e., an orientation of the guided missile 1 about its longitudinal axis 27, or to set or change a rolling motion so that a rotation about the longitudinal axis 27 can be set or changed. Each rolling nozzle 31, 32 can also be designed as a double nozzle that can be controlled by a valve so that propellant gas can be expelled in each of the two directions accordingly. In this embodiment, the rolling system 29 is preferably designed as a cold gas system. In contrast, the engine units 4-7 are designed as hot gas systems.It is also possible to implement the rolling system 29 as a hot gas system.

[0038] Fig. 5a, 5b shows an isolated representation of an engine unit 4-7 in two operating states, starting from Fig. 5a by rotating engine unit 4-7 into the Fig. 5b The second operating state shown can be transitioned to. The engine unit 4-7 shown can, for example, be any of the engine units 4-7 from Fig. 1-3 represent. An analogous representation can be found in Fig. 6a, 6b for an engine unit 4, 5 with two outlet openings 8, 8' and 9, 9' respectively. Each of the two engine units 4, 5 can be one of the engine units from Fig. 4 to represent. In principle, as described, all engine units 4-7 shown can be combined arbitrarily, or a propulsion system 2 of a guided missile 1 can have any such combinations of engine units 4-7.

[0039] The guided missile 1 with the propulsion system 2 described herein enables, in particular, that all fuel in the combustion chambers 14-17 can be used selectively or as needed for generating both longitudinal and lateral thrust. By changing the ejection position of the exhaust openings 8-11, it is possible to react flexibly to the requirements of the motion and thus achieve a change in the motion vector at short notice.

[0040] As mentioned at the outset, all advantages, details and features described in relation to the individual figures and the individual embodiments are freely interchangeable, transferable and combinable with one another.

Claims

1. Guided missile (1) comprising a propulsion system (2) which has an engine (3) with at least one engine unit (4-7), said at least one engine unit having a combustion chamber (14-17) and at least one exhaust nozzle (8-11), which in terms of its orientation is connected fixedly to the combustion chamber (14-17) via a connecting line (18-21), and being configured to expel a propellant-gas stream through the exhaust nozzle (8-11), wherein the propulsion system (2) has a positioning device (22-25) which is configured to change the orientation of the combustion chamber (14-17) and the at least one exhaust nozzle (8-11) of the at least one engine unit (4-7) by rotation about an axis of rotation (26, 33-35), oriented in particular perpendicularly to a longitudinal axis (27) of the guided missile (1), into at least one first expulsion position and at least one second expulsion position, characterized in that the engine (3) has at least one rotatable engine unit (4-7) having two oppositely arranged exhaust nozzles (8, 8', 9, 9').

2. Guided missile (1) according to Claim 1, characterized in that the positioning device (22-25) is configured to rotate the at least one engine unit (4-7) in both directions of rotation through at least 90° in relation to a longitudinal axis (27) of the guided missile (1).

3. Guided missile (1) according to Claim 1 or 2, characterized in that the positioning device (22-25) is configured to rotate the at least one engine unit (4-7) selectively into a longitudinal thrust position or a transverse thrust position.

4. Guided missile (1) according to Claim 3, characterized in that, in the transverse thrust position, the entire thrust generatable by means of the engine unit (4-7) is generatable as transverse thrust.

5. Guided missile (1) according to one of the preceding claims, characterized in that the engine (3) has at least two rotatable engine units (4-7) which are rotatable independently of one another.

6. Guided missile (1) according to one of the preceding claims, characterized in that the engine (3) has four rotatable engine units (4-7) whose exhaust nozzles (8-11) are arranged in pairs at opposite circumferential positions (12, 13) of the propulsion system (2).

7. Guided missile (1) according to one of the preceding claims, characterized by a rolling system (29), said rolling system having at least one rolling nozzle (31, 32), which is oriented tangentially to the guided missile (1), and being configured to set or vary a rolling position and / or rolling movement by way of expulsion from the rolling nozzle (31, 32).

8. Propulsion system (2) for a guided missile (1) according to one of the preceding claims, comprising an engine (3) with at least one engine unit (4-7), said at least one engine unit having a combustion chamber (14-17) and at least one exhaust nozzle (8-11), which in terms of its orientation is connected fixedly to the combustion chamber (14-17) via a connecting line (18-21), and being configured to expel a propellant-gas stream through the exhaust nozzle (8-11), wherein the propulsion system (2) has a positioning device (22-25) which is configured to change the orientation of the combustion chamber (14-17) and the at least one exhaust nozzle (8-11) of the at least one engine unit (4-7) by rotation about an axis of rotation (26, 33-35), oriented in particular perpendicularly to a longitudinal axis (27) of the guided missile (1), into at least one first expulsion position and at least one second expulsion position, characterized in that the engine (3) has at least one rotatable engine unit (4-7) having two oppositely arranged exhaust nozzles (8, 8', 9, 9').

9. Method for controlling a guided missile (1) comprising a propulsion system (2) which has an engine (3) with at least one engine unit (4-7), said at least one engine unit having a combustion chamber (14-17) and at least one exhaust nozzle (8-11), which in terms of its orientation is connected fixedly to the combustion chamber (14-17) via a connecting line (18-21), wherein a propellant-gas stream is expelled through the exhaust nozzle (8-11), wherein the orientation of the combustion chamber (14-17) and the at least one exhaust nozzle (8-11) of the at least one engine unit (4-7) is changed by rotation about an axis of rotation (26, 33-35), oriented in particular perpendicularly to a longitudinal axis (27) of the guided missile (1), into at least one first expulsion position and at least one second expulsion position, characterized in that the engine (3) has at least one rotatable engine unit (4-7) having two oppositely arranged exhaust nozzles (8, 8', 9, 9').