DE102024001454A1 - missile - Google Patents

Abstract

Missile (1), in particular guided missile or cruise missile, comprising an air-breathing engine (2), in particular a turbo-jet engine or a turbo-fan engine, and an inlet (3), in particular a NACA air inlet, having an air inlet (4) arranged in an outer skin (5) of the missile (1), through which air from the environment can be guided or is guided to the engine (2), wherein the missile (1) has at least one adjustment device (6) configured to adjust the sweep of at least one wing (7, 7') of the missile (1) from a transport sweep (8, 8') in a transport state to a flight sweep (10, 10') in a flight state, wherein the adjustment device (6) is configured to set a launch sweep (9, 9') of the at least one wing (7, 7') that is between the transport sweep (8, 8') and the flight sweep (10, 10') is positioned to at least partially cover the air intake (4) in the takeoff sweep (9, 9') in order to reduce the air mass flow of the engine (2).

Description

The invention relates to a missile, in particular a guided missile or cruise missile, comprising an air-breathing engine, in particular a turbo-jet engine, and an inlet having an air inlet arranged in an outer skin of the missile, in particular a NACA air inlet, through which air from the environment can be directed to or is directed to the engine, wherein the missile has at least one adjustment device configured to change the sweep of at least one wing of the missile from a transport sweep in a transport state to a flight sweep in a flight state.

Missiles of the aforementioned type, which have an air-breathing engine supplied by an airflow drawn from the environment to the engine through an air intake in the missile's outer skin, are generally known from the prior art. Such missiles typically also incorporate an adjustment mechanism by which the sweep of the missile's wings can be changed from a transport sweep in transport mode to a flight sweep in flight mode. In other words, the wings exhibit a transport sweep in transport mode, for example, when the missile is carried or transported by a launching platform, particularly a drone or aircraft. In the transport sweep, the wings can be folded, meaning that the transport sweep represents the maximum sweep during the missile's operation. When the missile is deployed, the transport sweep is changed to the flight sweep, for example, by the missile's wings "unfolding" or pivoting. The adjustment device is usually formed by a spring mechanism, so that when the adjustment device is triggered, there is a direct transition from the transport state to the flight state.

With such missiles, it is further known that the engine is designed and certified for specific operating conditions, which, for example, determines the maximum Mach number at which the missile's engine can be started. Above the approved or certified Mach number of the engine, the air mass flow directed through the intake to the engine may be too high, so that a controlled engine start may not be guaranteed. In other words, the missile's engine start capability is limited to the Mach number for which the engine is designed and certified.

This can mean that the launch platform, which transports the missile, can generally move at a higher speed or Mach number, but would have to reduce its speed to the launch Mach number for which the missile's engine is designed to perform in order to deploy the missile. Extending the launch velocity, i.e., enabling reliable launches at higher Mach numbers, usually requires a complex modification of the missile, particularly to the engine. For example, a new engine design and certification may be necessary for the target Mach number at which the missile is to be deployed and the engine started.

The invention is based on the objective of providing an improved missile in which, in particular, the missile can be deployed even under operational conditions, especially above a takeoff Mach number, which is outside the certification of the engine.

As described, the invention relates to a missile, in particular a guided missile or cruise missile, comprising an air-breathing engine, in particular a turbojet engine, and an inlet having an air intake arranged in an outer skin of the missile, in particular a NACA air intake, through which air from the environment can be directed to or is directed to the engine, wherein the missile has at least one adjustment device configured to change the sweep of at least one wing of the missile from a transport sweep in a transport state to a flight sweep in a flight state. An air-breathing engine is understood in particular to be an engine that obtains the oxygen necessary for the combustion of the propellant from the ambient air. In the present case, the ambient air is supplied to the engine via the inlet, which is connected to the air intake arranged in or integrated into the outer skin of the missile. The inlet can in particular be formed by a so-called NACA air intake, which is generally known from the prior art. Specifically, the engine is designed as a turbo-jet engine or turbo-fan engine.

As already described, it is fundamentally possible to adjust the sweep of at least one wing of the aircraft using the adjustment device. This allows, for example, the wing sweep to be changed from the transport sweep to the flight sweep. The invention is based on the finding that the adjustment device is designed to set a launch sweep of the at least one wing, which is between the The adjustment mechanism is designed to move at least one wing, or in particular a pair of wings, from the transport sweep to a takeoff sweep, thus reducing the air mass flow to the engine and at least partially covering the air intake. In other words, the functionality of the adjustment mechanism is expanded compared to aircraft known from the prior art. The adjustment mechanism is therefore designed to move at least one wing, in particular a pair of wings, from the transport sweep to a takeoff sweep, which can be understood as an intermediate position between the transport sweep and the takeoff sweep. For example, moving the wings to the takeoff sweep reduces the air mass flow compared to the air mass flow present in the takeoff sweep.

The launch sweep is adjusted specifically to start the engine, for example, when the missile has been deployed or is about to be deployed. Compared to conventional adjustment devices, the present adjustment device is designed to transition from the transport sweep to a launch sweep by adjusting at least one wing from the transport sweep to the launch sweep. This allows the air intake to be covered by at least one wing in the transport sweep. The covering can, for example, be radial to a longitudinal axis of the missile. The air intake can be partially opened in the launch sweep. For the movement between the transport sweep and the launch sweep, the wings are pivoted, for example, about a pivot axis parallel to the missile's vertical axis. This achieves a defined position of the wings relative to the missile's longitudinal axis. This allows precise adjustment of the airflow mass entering the intake and thus being supplied to the engine in the launch state. Thus, by adjusting the wing sweep, in particular by adopting the takeoff sweep, the air mass flow in the inlet can be reduced, especially compared to the flight sweep.

Since the certification or design of the engine is usually based on the flight Mach number and free airflow, i.e., the engine's certified Mach number is determined by the air mass flow present at that Mach number entering the inlet from the outside, it is advantageous to extend the engine's operating conditions by obscuring the inlet during the launch sweep at Mach numbers above the certified Mach number to such an extent that the air mass flow entering the inlet is reduced to at least the level of, or below, the air mass flow that would be present at the certified Mach number under free airflow. This allows the missile to be used or launched even at Mach numbers for which the engine is not, in itself, certified or designed. However, by specifically adjusting the launch sweep, the boundary conditions in the inlet are created in such a way that they correspond to the operating conditions for which the engine is designed or certified. Advantageously, it is therefore not necessary to redesign or recertify the engine, and yet the missile can be used with the engine in extended operating conditions.

The described missile can be further developed such that the at least one wing, in particular two wings arranged opposite each other on a fuselage of the missile, covers the air intake with a transport overlap in the transport sweep, while the at least one wing covers the air intake with a launch overlap that is less than the transport overlap. In other words, by moving the at least one wing from the transport sweep to the launch sweep, the air intake can be further opened, since in the launch sweep it has a launch overlap that covers the air intake less than the transport overlap. This means that in the transport sweep, where the at least one wing covers the air intake with a transport overlap, for example, completely obscuring it, the air intake can be "opened" by moving the at least one wing into the launch sweep.

However, during takeoff, the air intake is not fully opened, but rather selectively covered to such an extent that the air mass flow into the intake, and thus into the inlet, is regulated, thereby allowing a defined engine start. After engine start, as already described, the adjustment mechanism allows the at least one wing to be moved from the takeoff sweep to the flight sweep. In the flight sweep, the air intake can, for example, be fully open, meaning that there is no longer any overlap between the at least one wing and the air intake. As described, the portion of the air intake that is open, i.e., not covered by the at least one wing, can be selectively adjusted to regulate the internal air mass flow in the inlet.

In a further embodiment of the missile, the adjustment device can be designed to position at least one wing into the takeoff sweep for a start-up phase of the engine. and, after the engine has started, to adjust at least one wing into its sweep angle. The start-up phase is understood to be the phase or period of time in which the engine is started. For example, the engine start-up phase can be defined as the period between a start command and a complete engine start. The start-up phase typically lasts several seconds, so while the engine is in the start-up phase, or while the missile is performing the engine start-up phase, the adjustment mechanism adjusts at least one wing into the start-up sweep and holds it there for the duration of the start-up phase. Only when the engine has reliably started does the adjustment mechanism adjust at least one wing from the start-up sweep to the flight sweep.

The missile can be further developed such that the launch sweep is either fixed or variably adjustable. A fixed launch sweep offers the particular advantage that the adjustment mechanism can be designed more simply in terms of both construction and control complexity. In this variant, the launch sweep represents a defined intermediate state between the transport state (transport sweep) and the flight state (flight sweep). For example, if the missile is to be deployed above a launch Mach number for which the engine is designed, the fixed launch sweep can be adopted, largely independent of the prevailing environmental conditions.

According to the second described alternative, the launch sweep can be variably adjustable. This offers the particular advantage that the prevailing environmental conditions or boundary conditions can be taken into account and the launch sweep can be adjusted accordingly. This allows, in particular, the launch sweep to be selected precisely so that it is adapted to the engine's requirements for optimal start-up with respect to the air mass flow entering the air intake and thus the intake.

As described, the adjustment mechanism is fundamentally designed to change the sweep angle of at least one wing, specifically to adjust it from transport sweep to launch sweep and subsequently from launch sweep to flight sweep. For this purpose, the adjustment mechanism can include at least one actuator, which can be of any type, for example, an electric motor, pneumatic actuator, hydraulic actuator, and the like. The adjustment mechanism can have different detent positions for the individual states, for example, a first detent position for transport sweep, a second detent position for launch sweep, and a third detent position for flight sweep.

Furthermore, the missile may be designed so that the launch swept angle is adjustable depending on at least one operating parameter and/or environmental parameter. As previously described, the launch swept angle can be variably adjustable, meaning that the adjustment mechanism can be designed to variably set the launch swept angle. In particular, it may be provided that the launch swept angle can be set to prevailing operating parameters and/or environmental parameters, or that the adjustment mechanism can be designed to set the launch swept angle based on an operating parameter and/or environmental parameter. Operating parameters are understood to be, in particular, the operating variables of the missile or the launch platform. For example, operating parameters can include the engine's air requirement, a maximum permissible air mass flow or air pressure for engine start, an air pressure or air temperature at the intake, an engine temperature, a missile speed, and the like.

Environmental parameters used in free airflow include ambient temperature, angle of attack, ambient air mass flow rate, velocity, Mach number, ambient pressure, and similar parameters. Specifically, air pressure and temperature measurements can be taken at the inlet. The remaining operating parameters and/or environmental parameters can be calculated or determined. Any combination of the individual parameters is possible. Depending on the operating parameter and/or the environmental parameter, a starting thrust angle can be variably set to ensure the optimal air mass flow rate at the inlet. For example, a lookup table can be provided for at least one operating parameter and/or environmental parameter, or the starting thrust angle can be calculated, for example, using a control device, and then adjusted by the adjustment mechanism.

Furthermore, the missile may be designed to automatically adjust the launch swept, for example, during the launch procedure. If an operating parameter and/or an environmental parameter changes, the launch swept can thus be further adjusted variably during the launch phase or the launch procedure. For example, it is possible to adjust the launch swept even during the engine start-up process. The starting arrow can be changed to, for example, continuously allow more air into the inlet. Adjusting the starting arrow during the start-up phase allows for a response to changes in operating parameters and/or environmental parameters.

Furthermore, the missile may be equipped with a detection device designed to detect when the engine is running, and the adjustment device is designed to adjust the at least one wing from the starting sweep to the flight sweep depending on the detected starting sweep. As described, the starting sweep is assumed particularly during the engine start-up phase. To ensure that the engine has started reliably, the detection device can be provided to detect the engine's running sweep. Only when the detection device has registered the engine's running sweep, i.e., when it has been ensured that the engine is operating reliably, will the adjustment device adjust the at least one wing from the starting sweep to the flight sweep, for example, by issuing a corresponding start or release signal to the adjustment device.

This ensures that the engine can be reliably ignited or started for the specified start interval or duration, and that the increased airflow resulting from the transition to swept flight does not impair the engine start. Furthermore, the detection system allows the precise moment the engine has started to be recorded, enabling the swept flight to be initiated immediately. In other words, a fixed time interval guaranteeing a reliable engine start is unnecessary; instead, the system can record the engine's running state.

The described missile can be further developed such that its transport Mach number is greater than the engine's takeoff Mach number, with the adjustment mechanism being designed to reduce the transport Mach number with respect to the air intake to at least the takeoff Mach number by adjusting the takeoff overlap. As already described, by adjusting at least one wing into the takeoff sweep, the air intake can be covered, namely by adjusting the takeoff overlap, in such a way that the mass flow of air introduced or flowing into the air intake can be reduced, i.e., can correspond to a lower Mach number than the transport Mach number at which the missile is currently being moved. The described embodiment therefore allows the missile to be moved at a transport Mach number that is greater than the takeoff Mach number for which the engine is designed or certified. The takeoff Mach number thus indicates the Mach number up to which the engine can be safely started with the air intake fully open. With regard to the inlet, covering the air intake thus reduces the air mass flow present at the transport Mach number of the missile to an air mass flow in the inlet that corresponds at least to the takeoff Mach number of the engine, i.e., would be present at this number, or is lower.

The described modification of the air mass flow in the inlet allows the missile to be deployed even at Mach numbers exceeding the engine's launch Mach number, for which the engine is designed and certified. This increases the missile's launch velocity without requiring any modifications to the engine itself. This expands the missile's operational range, enabling its use in launch platform conditions for which the engine is not typically designed. Advantageously, this eliminates the need to reduce the launch platform's speed for missile deployment. Specifically, when using the missile as a remote carrier, the launch platform's capabilities can be further utilized, and the missile's deployment does not impose any constraints on the platform's movement. In particular, this enables higher flight speeds and greater ranges—in other words, increased missile performance.

In addition to the missile, the invention relates to an adjustment device for a missile according to one of the preceding claims, which is configured to adjust the sweep of at least one wing of the missile from a transport sweep in a transport state to a flight sweep in a flight state, wherein the adjustment device is configured to set a launch sweep of the at least one wing which lies between the transport sweep and the flight sweep.

The invention further relates to a carrier platform comprising at least one previously described missile. The invention also relates to a method for operating a missile, in particular a guided missile or cruise missile, comprising an air-breathing engine, in particular a turbojet engine, and an inlet having an air intake arranged in an outer skin of the missile, in particular a NACA air inlet through which air from the environment can be directed or is directed to the engine, wherein the missile has at least one adjustment device configured to change the sweep of at least one wing of the missile from a transport sweep in a transport state to a flight sweep in a flight state, wherein a launch sweep of the at least one wing is set which lies between the transport sweep and the flight sweep.

The method can be implemented using the adjustment device described above, particularly as an integral part of the missile. All advantages, details, and features described in relation to the missile are fully transferable to the adjustment device, the launching platform, and the method.

• 1 eine Prinzipdarstellung eines Flugkörpers in einem Längsschnitt;
• 2 eine Prinzipdarstellung einer Unterseite des Flugkörpers von 1 in einem Transportzustand;
• 3 eine Prinzipdarstellung der Unterseite des Flugkörpers von 1, 2 in einem Startzustand; und
• 4 eine Prinzipdarstellung der Unterseite des Flugkörpers von 1-3 in einem Flugzustand.

The invention is explained below with reference to exemplary embodiments and the figures. The figures are schematic representations and show:

• 1 a schematic representation of a missile in a longitudinal section;
• 2 a schematic representation of the underside of the missile 1 in a transport state;
• 3 a schematic representation of the underside of the missile 1 , 2 in a startup state; and
• 4 a schematic representation of the underside of the missile 1-3 in a flight state.

1-4 Figures 1 show a missile 1 in various views and states. The missile 1 is specifically designed as a guided missile or cruise missile. The missile 1 can, for example, be carried or transported by a launching platform (not shown in detail). The missile 1 can, in particular, be configured as a so-called "remote carrier".

The missile 1 has an air-breathing engine 2, specifically designed as a turbojet engine. The engine 2 is connected to an inlet 3, which has an air intake 4 located in an outer skin 5 of the missile 1's fuselage. In other words, the engine 2 uses oxygen from the ambient air, which is supplied to the engine 2 by an air mass flow that can flow from the environment into the air intake 4 and through the inlet 3 to the engine 2. The inlet 3 can be a standard NACA air intake.

The missile 1 further comprises an adjustment device 6, which is designed to provide a sweep of at least one wing 7 or of the in 1-4 The adjustment device 6 sets the sweep angle of the wings 7, 7' shown as an example. Specifically, the adjustment device 6 sets the sweep angle of the wings 7, 7' equal or opposite. 1 , 2 show, by way of example, a transport condition in which the wings 7, 7' have a transport sweep 8, 8' (cf. 2 In the illustrated embodiment, the wings 7, 7' cover the air inlet 4 in a transport cover. As shown by way of example, the air inlet 4 can be completely covered in the transport state or in the transport cover, so that approximately no ambient air can flow into the air inlet 4 and thus into the inlet 3. For example, the missile 1 can be transported from the launching platform in this transport state.

If the missile 1 is to be deployed, particularly at a Mach number exceeding the launch Mach number for which the engine 2 is designed or certified, the adjustment device 6 can be used, as shown in 3 As shown, the wings 7, 7' are positioned in a launch sweep 9, 9'. The launch sweep 9, 9' can be chosen such that the air mass flow of the ambient air entering air inlet 4 and from there into inlet 3 is reduced to meet the launch conditions of the launch velocity specified by engine 2. In other words, the missile 1 can be moved at a transport Mach number higher than the permissible launch Mach number of engine 2. Although the air mass flow into air inlet 4 would be too high in this case, it can be reduced by the launch overlap of wings 7, 7' in the launch sweep 9, 9' so that it can be used for a reliable engine 2 start.

For example, in 4 A flight sweep 10, 10' is shown, in which the adjustment device 6 moves the wings 7, 7' starting from the in 3 The depicted launch swept direction 9, 9' is in effect. The air intake 4 is clearly fully open in the flight swept direction 10, 10' of the wings 7, 7', so there is no overlap. If the adjustment device 6 were to position the wings 7, 7' in the flight swept direction 10, 10' for takeoff, the transport Mach number of the missile 1 would be limited to the permitted takeoff Mach number of the engine 2, since above the takeoff Mach number of the engine 2 the takeoff envelope would be left and thus a safe start of the engine 2 could not be guaranteed.

Advantageously, in the 9, 9' launch swept direction, it is therefore possible to start or deploy engine 2 at higher speeds, especially higher Mach numbers, and to take advantage of the higher air masses present in this scenario. The flow into air intake 4 or inlet 3 is reduced by the sweep of wings 7, 7' so that engine 2 can operate or start in its takeoff velocity. This is purely by way of example. 1 The figure shows an engine inlet area 14 of engine 2 and a free airflow 15. The free airflow 15 indicates, for example, the air mass flow outside the air inlet 4 that is present at the current Mach number or speed of the missile 1.

By selectively adjusting the wings 7, 7' to the launch sweep 9, 9', the air intake 4 is only partially opened or selectively covered. This means that, unlike a fully opened intake as seen, for example, in the flight sweep 10, 10', only a reduced airflow reaches the engine inlet 14, rather than the free airflow 15. Despite the higher airflow in the free airflow 15, particularly due to the higher Mach number of the missile 1, especially above a certain certification level, this allows for a safe engine start 2. This is because the defined overlap of the air intake 4 by the wings 7, 7' in the launch sweep 9, 9' precisely controls the airflow into the inlet 3 and thus to the engine inlet 14.

As previously described, it is possible, firstly, to predefine the launch sweep 9, 9', for example, to assume a fixed state between the transport sweep 8, 8' and the flight sweep 10, 10'. It is also possible for the launch sweep 9, 9' to be variably adjustable depending on an environmental parameter and/or an operating parameter of the missile 1 or the engine 2. In other words, the adjustment device 6 can variably adjust the launch sweep 9, 9' depending on the environmental or operating parameter in order to optimally adjust the air mass flow to the engine 2 or into the inlet 3 with the resulting launch overlap.

For example, the air mass flow can be adjusted to optimally meet the starting requirements of engine 2. Various environmental parameters can be taken into account, such as air pressure, air temperature, speed or Mach number, and the like. Likewise, various operating parameters of the missile 1, such as speed or Mach number, air pressure at inlet 3 or at engine 2, flow velocity at inlet 3 or engine 2, air temperature at inlet 3, and the like, can be determined, recorded, or calculated. Furthermore, the adjustment device 6 can track the starting swept 9, 9', for example, adjusting the starting swept 9, 9' in the direction of the flight swept 10, 10' during the engine 2 start-up phase to provide engine 2 with a larger airflow, as required for optimal engine start, and, in particular, to reduce the air mass flow initially during the start-up phase to ensure reliable ignition of engine 2.

In 1 A detection device 11 is schematically depicted, which is designed to detect a started state of the engine 2. In principle, the transition from the starting sweep 9, 9' to the flight sweep 10, 10' can be initiated by the adjustment device 6 after a defined time interval, which is sufficient for a safe start of the engine 2 across all operating states. Based on the detection by the detection device 11, it is not necessary to wait for the defined time interval; rather, the detection device 11 can detect in the current operating situation that the engine 2 has been safely started. In this case, the detection device 11 can send a start signal to the adjustment device 6, so that the latter directly adjusts the wings 7, 7' from the starting sweep 9, 9' to the flight sweep 10, 10', for example, with respect to a longitudinal axis 12 or a vertical transverse axis 13 of the missile 1.

Advantageously, a reduction in airflow mass is thus possible by adjusting the sweep angle of wings 7, 7'. The operational range of the missile 1 can be extended beyond the limits of engine 2 by means of the adjustment device 6, in particular by setting wings 7, 7' to the launch sweep angle 9, 9'. In particular, it becomes possible to release the missile 1 at higher speeds or higher Mach numbers, so that a launch platform, for example, does not have to reduce its speed for the release of the missile 1. This is achieved in particular by the fact that engine 2 or the inlet 3 is not exposed to the external airflow, and that the air intake 4 is not directly exposed to the external airflow at the higher speeds. Instead, air intake 4 is deliberately covered in the launch sweep 9, 9', specifically in the launch overlap, such that the effective air mass flow into air intake 4 is reduced, in particular to at least the air mass flow that would flow into intake 3 with a fully open air intake 4 at the certified launch Mach number of engine 2. Thus, without any modification to engine 2, namely by deliberately reducing the air mass flow into intake 3, it can be ensured that engine 2 can be reliably ignited. and a stable flame can form in the combustion chamber of engine 2.

In other words, the certified launch area or launch velocity of engine 2 does not need to be left, as the specified conditions for the air mass flow into inlet 3, even at the higher transport Mach numbers at which missile 1 is to be deployed, are maintained. This means that the launch platform can reach significantly higher speeds, particularly depending on engine 2, up to high subsonic or low transonic flight Mach numbers, without requiring a reduction in the launch platform's speed for missile 1 deployment or any modifications by the engine manufacturer. Furthermore, as described, the air mass flow into inlet 3 can be adjusted to ensure optimal engine ignition.

The adjusting device 6 is coupled to the wings 7, 7', in particular mechanically, for adjusting the sweep angle of the wings 7, 7'. The adjusting device 6 can adjust the sweep angle of the wings 7, 7', for example, by electromechanical, electromagnetic, hydraulic, pneumatic, or any other means.

The advantages, details, and features shown in relation to the individual figures can be combined, interchanged, and transferred to one another as desired. The method described herein can be carried out using the adjustment device 6 or with the missile 1. The missile 1 can, for example, be part of a carrier platform, which is not shown in detail. The description is therefore also fully transferable to the method, the adjustment device 6, and the carrier platform.

Reference sign

1

missile

2

engine

3

Enema

4

air intake

5

outer skin

6

Adjustment device

7, 7'

wing

8.8'

Transport route

9.9

Starting arrow

10, 10'

Flight path swept

11

Recording device

12

Longitudinal axis

13

transverse axis

14

Engine inlet surface

15

free airflow

Claims (10)

Missile (1), in particular guided missile or cruise missile, comprising an air-breathing engine (2), in particular a turbo-jet engine or a turbo-fan engine, and an inlet (3), in particular a NACA air inlet, having an air inlet (4) arranged in an outer skin (5) of the missile (1), through which air from the environment can be guided to or is guided to the engine (2), wherein the missile (1) has at least one adjustment device (6) configured to adjust the sweep of at least one wing (7, 7') of the missile (1) from a transport sweep (8, 8') in a transport state to a flight sweep (10, 10') in a flight state, characterized in that the adjustment device (6) is configured to set a launch sweep (9, 9') of the at least one wing (7, 7') which is between the transport sweep (8, 8') and the The flight sweep (10, 10') is positioned to at least partially cover the air intake (4) in the takeoff sweep (9, 9') in order to reduce the air mass flow of the engine (2). missile (1) after Claim 1 , characterized in that the at least one wing (7, 7'), in particular two wings (7, 7') arranged opposite each other on a fuselage of the missile (1), in the transport sweep (8, 8') cover the air inlet (4) to a transport overlap, wherein the at least one wing (7, 7') in the launch sweep (9, 9') covers the air inlet (4) to a launch overlap that is smaller than the transport overlap. missile (1) after Claim 1 or 2 , characterized in that the adjustment device (6) is designed to position the at least one wing (7, 7') in the starting sweep (9, 9') for a starting phase of the engine (2) and to position the at least one wing (7, 7') in the flight sweep (10, 10') after the engine (2) has started. Missile (1) according to one of the preceding claims, characterized in that the launch swept direction (9, 9') is fixed or that the launch swept direction (9, 9') is variably adjustable. Missile (1) according to one of the preceding claims, characterized in that the launch sweep (9, 9') depends on at least an operating parameter and/or environmental parameter is adjustable. Missile (1) according to one of the preceding claims, characterized by a detection device (11) which is designed to detect a started state of the engine (2), wherein the adjustment device (6) is designed to position the at least one wing (7, 7') depending on the detected started state from the start sweep (9, 9') into the flight sweep (10, 10'). Missile (1) according to one of the preceding claims, characterized in that a transport Mach number of the missile (1) is greater than a takeoff Mach number of the engine (2), wherein the adjustment device (6) is designed to reduce the transport Mach number with respect to the inlet (3) at least to the takeoff Mach number of the engine by means of the takeoff overlap. Adjustment device (6) for a missile (1) according to one of the preceding claims, which is configured to adjust the sweep of at least one wing (7, 7') of the missile (1) from a transport sweep (8, 8') in a transport state to a flight sweep (10, 10') in a flight state, characterized in that the adjustment device (6) is configured to set a launch sweep (9, 9') of the at least one wing (7, 7') which lies between the transport sweep (8, 8') and the flight sweep (10, 10'). Carrier platform comprising at least one missile (1) according to one of the Claims 1 until 7 . A method for operating a missile (1), in particular a guided missile or cruise missile, comprising an air-breathing engine (2), in particular a turbo-jet engine or a turbo-fan engine, and an inlet (3) having an air inlet (4) arranged in an outer skin (5) of the missile (1), in particular a NACA air inlet, through which air from the environment can be guided to or is guided to the engine (2), wherein the missile (1) has at least one adjustment device (6) configured to adjust the sweep of at least one wing (7, 7') of the missile (1) from a transport sweep (8, 8') in a transport state to a flight sweep (10, 10') in a flight state, characterized in that a launch sweep (9, 9') of the at least one wing (7, 7') is set, which is between the transport sweep (8, 8') and the flight sweep (10, 10') is positioned to at least partially cover the air intake (4) in the takeoff sweep (9, 9') in order to reduce the air mass flow of the engine (2).