Military vehicle

Abstract

The invention relates to a military vehicle (1) with a platform (2) and a rocket launcher (3), wherein the platform (2) is movably connected to the vehicle (1) for aligning the rocket launcher (3), in particular rotatably in the azimuth direction (AR), and wherein the rocket launcher (3) is movably connected to the platform (2) for aligning the rocket launcher (3), in particular pivotably in the elevation direction (ER). Protection of the vehicle (1) and / or the rocket launcher (3) itself against an exhaust jet (5) of a rocket arranged in and / or fired from the rocket launcher (3) is improved by arranging at least one protective shield (4) on the vehicle (1) and / or the platform (2) for intercepting and / or deflecting the exhaust jet (5) exiting the rocket launcher (3), in particular a rocket not released from the rocket launcher (3).

Description

[0001] The invention relates to a military vehicle with the features of the preamble of claim 1.

[0002] Military vehicles are known with a platform, e.g., a turret, and with a rocket launcher, wherein the platform is movable, in particular rotatable in the azimuth direction, and connected to the vehicle, in particular to a vehicle hull of the vehicle, for the purpose of aligning the rocket launcher, and wherein the rocket launcher is movable, in particular pivotable in the elevation direction, and connected to the platform for the purpose of aligning the rocket launcher.

[0003] Vehicle-mounted rocket launchers are mobile launch platforms for reaction-propelled missiles, specifically rockets. Rocket launchers can be aligned using an alignment unit, which is typically part of the platform. This unit can be configured, for example, with rotating turrets, elevation-adjustable mounts, or combinations of these. In combination with rotating platforms, such as turrets, the rocket launcher is able to align the azimuth of a launched missile so that the missile's flight path between the launch point and the target can be covered with minimal energy expenditure and / or in the shortest possible time, thus ensuring a successful impact. Turrets or other platforms to which the rocket launchers are mounted can assume various angles of rotation relative to the vehicle (also called the carrier vehicle).Rotating turrets capable of tilting / elevating the rocket launchers and thus the rockets themselves are known in the prior art. Designs are also known in which both the launch platform and the turret can be rotated and / or tilted / elevated independently of each other.

[0004] Depending on the elevation and rotation angle of the turret and / or rocket launcher, the exhaust plume of a launching rocket can strike the surface of the supporting vehicle. This is particularly problematic when the solid-propellant rocket engine has ignited but the rocket is not released from the launcher. This creates a so-called "hangfire," in which the hot exhaust plume of the rocket engine is focused on a single point for a relatively long time, thus posing a significant inherent destructive potential. It is known that the exhaust plume of a modern solid-propellant rocket can reach temperatures exceeding 3000°K and elevated pressure during a burn time of approximately 10 seconds. The negative effects of the exhaust plume on the launch platform or vehicle are also present during normal operation and can lead to problems. This is especially true when many rockets need to be launched in a short period.A common method to mitigate the effects of the exhaust jet is to limit the rocket launcher's range of motion (ROM). This prevents the exhaust jet from being directed at and destroying vital vehicle structures, or, in the worst-case scenario, from destroying the entire launch platform or vehicle itself.

[0005] A major problem with current rocket launchers is that the requirements for a large platform range and protection against the effects of a hangfire are difficult to reconcile. Furthermore, absolute certainty that a hangfire will not occur cannot be guaranteed.

[0006] To meet these challenges, active and / or passive systems are used that make it possible to handle the hot gases of the exhaust jet in such a way that the overall system is not damaged by a hangfire and that the system is quickly ready for use again after a hangfire in order to persistently maintain operational capability in combat.

[0007] A fundamental problem is that solid-propellant rocket engines cannot simply be switched off and, due to their design, generally have to burn out completely. Interrupting the energy released during this process is a major challenge. Once ignited, solid-propellant engines can be destructively and instantly shut down by a precisely placed cutting charge. EP 0 163 086 B1 discloses such a system, which is mounted externally on the rocket launcher's casing and features an elongated cutting charge that slices open the engine lengthwise. This either extinguishes the engine or causes it to smolder without producing any further thrust. A disadvantage is that this method is destructive to the entire system, rendering the entire mobile system (vehicle, rocket launcher, and platform) unusable after a hangfire.Furthermore, a massive constructive intervention in the rocket launcher system is required.

[0008] US Patent 3,593,525 describes a solid-propellant rocket engine with adjustable thrust between 50% and 100% of its maximum thrust. This engine utilizes a throttled airflow, guided through a Venturi tube, to regulate thrust. The engine operates on the principle of "oxygen negative." By adding more oxygen from the air to the exhaust stream, combustion is optimized, generating even more thrust. US Patent 3,593,525 identifies the increased mass flow of the engine as the primary cause of this increased thrust. However, this system has the disadvantage of only being able to regulate thrust within a range of 50% to 100% and is not suitable for completely shutting down the engine. Consequently, such a system is unsuitable for inducing a shutdown. The oxygen bound within the solid-propellant rocket prevents it from extinguishing.

[0009] US Patent 4,480,522 describes a device that prevents rocket exhaust from coming into contact with and damaging landing gear components. The disclosure in US Patent 4,480,522 includes openings and pressure / flow controls to generate a cold gas stream that opposes the exhaust. This stream forms an interface and thus a barrier between the rocket launcher's guide rails and the exhaust, protecting the guide rails from overheating damage. The disadvantage of the disclosure in US Patent 4,480,522 is that additional actuators and a pressure vessel are required to provide the cooling gas stream. Furthermore, a potential hangfire must be detected in some way to reliably trigger the cooling device.

[0010] US patent 2012 0152090 A1 describes a system for a rocket launcher that uses a sophisticated gas management system to isolate overheating, hangfire, and debris. The system is also modular. The disadvantage of such a system is that it necessitates a design change to the entire rocket launcher system, requiring the addition of more parts, which ultimately limits its mobility.

[0011] The invention is based on the objective of eliminating the described disadvantages of the prior art or at least reducing their effects, in particular by improving the protection of the vehicle and / or the rocket launcher itself against an exhaust jet from a rocket located in and / or fired from the rocket launcher. Furthermore, it is particularly important to prevent harmful effects on the health of operating personnel.

[0012] This problem underlying the invention is now initially solved by a military vehicle with the features of claim 1.

[0013] One aspect of the invention is essentially that at least one protective shield is arranged on the vehicle and / or the platform to intercept and / or deflect an exhaust jet of a rocket exiting the rocket launcher, in particular a rocket not released from the rocket launcher.

[0014] A rocket that has not been released from the launcher is also known as a "hangfire." However, even during normal operation, the rocket's exhaust stream possesses destructive potential. The protective shield thus acts as a device to neutralize the hot exhaust stream of a rocket engine, particularly if the rocket is in an unintentional state of being not released. The entire system (vehicle with platform and rocket launcher) therefore remains functional even after a hangfire, and the crew is not endangered by the exhaust stream. In particular, the crew does not need to abandon the vehicle after a hangfire, as no repairs are necessary. The rocket launcher, as a complex and finely tuned technical system, can remain structurally unaffected by the protective shield, so that requalification of the rocket launcher due to the additional protective shield is unnecessary.

[0015] Advantageously, the protective shield is positioned on the vehicle, surrounding the platform at least within an angle of 90°.

[0016] Thus, a large area of ​​the vehicle where the hot exhaust jet could strike and cause damage is protected by the shield. The shield is preferably formed by a ring-shaped deflector plate structure and mounted on the vehicle's surface.

[0017] Preferably, the rocket launcher, in particular an exhaust outlet of the rocket launcher, is rotatable within a specific azimuth angular range and pivotable within a specific elevation angular range for its alignment in the azimuth direction. The shield is preferably designed such that, when the rocket launcher is aligned within the specific azimuth angular range and elevation angular range, the exhaust outlet faces the shield.

[0018] The protective shield is preferably arranged on the vehicle surrounding the platform in such a way that an exhaust outlet of the rocket launcher is facing the protective shield in every possible position of the rocket launcher.

[0019] However, ensuring that the exhaust outlet of the rocket launcher faces the shield in every possible position of the rocket launcher can also be achieved by arranging the shield, facing the exhaust outlet of the rocket launcher, on the platform.

[0020] The shield then rotates in the azimuth direction along with the platform, allowing it to be designed to be correspondingly smaller than a shield attached to the vehicle, particularly its hull. The shield attached to the platform can thus be understood as an extension of the rocket launcher, although, as mentioned, the rocket launcher itself is not restricted in its function by the shield.

[0021] According to an advantageous embodiment of the vehicle, a ramp-shaped, curved and / or concave deflection surface for the exhaust jet is formed by means of the protective shield.

[0022] The exhaust jet is thus neutralized at the surface of the vehicle and / or platform by deflecting it. A ramp-shaped deflection surface is particularly easy to manufacture. In particular, a curved and / or concave deflection surface allows the exhaust gases to be diverted very efficiently.

[0023] According to a further, preferred embodiment of the vehicle, the protective shield is tubular in shape, so that the exhaust jet can be guided through the tubular protective shield.

[0024] Thus, a lateral effect of the exhaust jet is suppressed. A tubular shield with a corresponding tubular deflector surface can be attached to either the platform or the vehicle itself, particularly its body. In the former case, the tubular deflector surface can advantageously rotate with the platform.

[0025] In order to successfully deflect the exhaust jet away from the vehicle using the protective shield, one axis of the tubular protective shield has an angle between 10° and 80° to the surface of the vehicle.

[0026] It can be advantageous if the protective shield has an outer shell, wherein at least one interior space is formed by means of the outer shell, wherein a phase-change material is arranged at least partially, in particular completely, in the interior space.

[0027] The protective shield is designed to absorb at least some of the energy from the exhaust jet, thus cooling it. Integrating the phase-change material into the shield prevents excessive heating of the entire shield. This utilizes the phase transition effect, which allows energy to be absorbed by the phase-change material at a constant temperature. The outer shell is phase-stable, meaning it maintains a solid state within the relevant temperature range.

[0028] Preferably, the phase change material is designed to undergo a phase change from solid to liquid and / or from liquid to gaseous by means of the exhaust gas jet impacting the protective shield. In the case of a phase change material with a planned phase change from liquid to gaseous, a type of heat tube and / or a type of heat surface element is formed by means of the protective shield itself.

[0029] Preferably, the phase change material has a phase change temperature from solid to liquid or from liquid to gaseous of 95°C to 650°C. This phase change temperature is then exceeded by the energy input of the exhaust jet, particularly in the case of a hang fire.

[0030] According to a preferred embodiment, the phase change material comprises metal, tin, plastic, water, methanol, ethanol, acetone and / or zeolite granules.

[0031] For example, the protective shield can be formed using a tin-steel sandwich structure, with the steel forming the outer shell and the tin acting as the phase change material. In such a shield, approximately 60 kJ / kg of heat input can be absorbed through the transition of the tin from solid to liquid. Tin has a melting point of approximately 231°C.

[0032] The energy density of a solid rocket propellant is approximately 5 MJ / kg. If the outer casing is filled with water, the phase transition effect is particularly pronounced due to the transition from liquid to vapor and the specific properties of water. The enthalpy of vaporization is approximately 2.2 MJ per kg of water. This means that about 2.3 kg of water are required to cool 1 kg of solid rocket propellant. Accordingly, a material that is liquid at room temperature with a high enthalpy of vaporization, such as water or methanol, is preferably used as the phase change material. Alternatively or additionally, substances that are solid at room temperature, such as metals with a melting point below 600 °C, e.g., the aforementioned zinc, or plastics with a melting point above 100 °C, can also be used as phase change materials.

[0033] The phase change material is preferably surrounded or encased in a "sandwich-like" manner by the solid material forming the outer shell. The outer shell material is preferably temperature-stable up to over 1000°C and as thermally conductive as possible. Preferably, the wall thickness of the outer shell material is so small that the heat from the exhaust gas jet heats the inner phase change material as quickly and evenly as possible, thus maximizing heat dissipation from the surface of the protective shield.

[0034] To enable the creation of complex structures, it is also conceivable that the phase change material is present in bound and / or lumpy form. Zeolite granules mixed with water are one example. If the phase change material is lumpy, i.e., in granular form, it can be "filled" into the outer shell during the manufacturing of the protective shield.

[0035] Preferably, at least one heat pipe, preferably with an integrated wick structure, is connected to the at least one interior space. A heat sink is formed by means of the heat pipe and / or the heat pipe is connected to a heat sink, in particular a condenser.

[0036] The heat pipe is also known as a "heat tube" by experts. These additional heat tubes can further reduce the heat impact of the exhaust jet on the protective shield, or conversely, allow more heat to be absorbed by the shield and the heat tubes connected to it. Heat tubes and heat surface elements, or heat pipes and vapor chambers, are components that transfer heat via an evaporation and condensation cycle. When heat is supplied to one end of the heat tubes or heat surface elements by the rocket's hot exhaust jet, a working fluid, particularly the phase change material, evaporates and flows—driven by the temperature and / or pressure gradient—along an adiabatic zone to the condenser. This condenser can be connected anywhere on the vehicle or directly to the vehicle's cooling system.There, the vapor condenses and releases its latent heat to the external heat sink, e.g., a radiator grille. To maintain the cycle, the condensate must be returned to the evaporation area.

[0037] This typically involves the use of an integrated wick structure (e.g., a grooved, mesh, or sintered structure) that transports the condensate back to the evaporation zone via capillary action. If the condenser is located above the evaporation zone, gravity can also be used for the return transport. This is then referred to as a two-phase thermosiphon. Other forces, such as centrifugal forces, can also be used to return the working fluid. The evaporation zone is also specifically designed by means of a protective shield. The working fluid used depends on the temperature range in which the heat pipe or heat surface element is to be used.

[0038] Advantageously, the tubular shield has an intake area and an acceleration area. From a fluid dynamics perspective, the intake area is located between the rocket launcher's exhaust outlet and the acceleration area. The intake area has a larger flow cross-section than the acceleration area. The shield has at least one intake opening in the intake area for supplying air, particularly fresh air.

[0039] Thus, the tubular protective shield is designed as a type of Venturi tube. The fluid flow of the exhaust jet from the rocket engine creates a negative pressure, which is used to enrich the hot exhaust jet with air, particularly fresh air. A positive effect of this enrichment is the cooling effect of the entire mass flow around the exhaust jet. The mass flow is preferably designed to minimize mixing between the hot exhaust gas and the cooling "jacket flow layer." This cooling jacket flow reduces the heating of the surrounding tubular outlet pipe, thus minimizing its impact on the system.Another positive effect of such a tubular protective shield, designed as a kind of Venturi tube, is that the Venturi effect allows more oxygen to enter the combustion system, thus enabling cleaner combustion and positively impacting emissions. Furthermore, the Venturi effect can be used to create a negative pressure at another preferred location.

[0040] The suction opening is preferably connected to an ABC hatch system of the vehicle, so that potentially contaminated air from an area around an ABC hatch of the ABC hatch system can be accelerated towards the suction opening by the exhaust jet.

[0041] In particular, a negative pressure can be generated at the inlet of an ABC filter system within the ABC hatch system. The extraction effect achieved through this negative pressure can, in a particularly favorable scenario, prevent contaminants from entering the ABC hatch system.

[0042] The additional airflow generated by the Venturi effect can preferably be used for multiple purposes. Firstly, it can be used to push the exhaust cloud further away from the ABC hatch. Secondly, the Venturi effect can also be used to cool the heat pipe and to clean an intake device around the ABC hatch system. A type of hose system can be used for this purpose. Passive pressure valves are preferably used to control and / or regulate these airflows, so that emergency situations can be detected and defused accordingly, even without electronic and electrical aids such as sensors and actuators.

[0043] The vehicle preferably has a neutralization medium supply by means of which a neutralization medium such as sodium hydroxide, sodium hydroxide vapor or the like can be supplied to the exhaust jet, in particular by means of at least one capillary and / or by means of at least one evaporation valve preferably arranged on the protective shield.

[0044] It is known that the exhaust gas from solid-propellant rocket motors carries a considerable amount of chemicals that can react with moisture to form hydrochloric acid. This hydrochloric acid can have devastating effects on vehicle corrosion and, in particular, on the health of the crew. A particularly preferred solution for neutralizing such hydrochloric acid is the use of sodium hydroxide, which forms sodium chloride when combined with hydrochloric acid. Especially if the neutralizing medium can be fed into the exhaust stream via the evaporation valve located on the heat shield, the phase-change material can also be used as such a neutralizing medium. The phase-change material can therefore also contain sodium hydroxide. It is then possible to modify and / or utilize the vapors of the phase-change material that occur during the cooling of the exhaust stream in such a way that they "wash out" the hydrochloric acid from the exhaust system formed by the heat shield.

[0045] There are now numerous possibilities for advantageously designing and further developing the military vehicle according to the invention. Reference may first be made to the claims subordinate to claim 1. In the following, a preferred embodiment of the military vehicle according to the invention will be explained and described in more detail with reference to the drawing and the accompanying description. The drawing shows: Fig. 1 is a schematic representation of a first embodiment of the military vehicle in a side view, Fig. 2 is a highly schematic representation of a second embodiment of the military vehicle in a top view, Fig. 3 is a schematic representation of a third embodiment of the military vehicle in a side view, Fig. 4 is a highly schematic representation of a fourth embodiment of the military vehicle in a top view, Fig. 5 is a schematic representation of a fifth embodiment of the military vehicle in a side view, and Fig. 6 is a schematic representation of a sixth embodiment of the military vehicle in a side view.

[0046] Fig. 1 to Fig. 6Figures 1 and 2 each show an embodiment of a military vehicle 1 comprising a platform 2 and a rocket launcher 3. The platform 2 is movable for aligning the rocket launcher 3, in particular rotatable in the azimuth direction AR, and is connected to the vehicle 1, specifically to a vehicle body 1.W of the vehicle 1. The rocket launcher 3 is movable for aligning itself, in particular pivotable in the elevation direction ER, and is connected to the platform 2. The vehicle 1 is propelled by means of wheels and / or tracks. The platform 2 can also be configured as a turret. Fig. 1 to Fig. 6 Each figure shows an embodiment of the vehicle 1 in which the platform 2 is rotatable in the azimuth direction AR, as indicated by the curved double arrows in Fig. 2 and Fig. 4 symbolizes. Fig. 1 to Fig. 6Figure 1 further shows an embodiment of vehicle 1 in which the rocket launcher 3 can be pivoted in the elevation direction ER, as indicated by the curved double arrows in Figure 1. Fig. 1 , Fig. 3 , Fig. 5 and Fig. 6 This is symbolized. However, other types of movement are also conceivable. Vehicle 1 has corresponding actuators and / or motors to realize these movements.

[0047] At least one protective shield 4 is arranged on the vehicle 1 and / or the platform 2 to intercept and / or deflect an exhaust jet 5 exiting the rocket launcher 3, particularly from a rocket not released from the rocket launcher 3. The exhaust jet 5 is deflected away from the vehicle 1 by the protective shield 4, thus protecting the vehicle 1 from damage caused by the exhaust jet 5. Furthermore, the protective shield 4 is able to partially absorb the energy of the exhaust jet 5 and thus cool it.

[0048] According to Fig. 1 and Fig. 2 The protective shield 4 is connected to the vehicle 1, in particular the vehicle tub 1.W.

[0049] The protective shield 4 is according to Fig. 1 and Fig. 2 on the vehicle 1, surrounding the platform 2 at least within an angle φ of 90°. According to Fig. 2Two V-shaped protective shields 4, viewed from above, are connected to the vehicle 1, in particular the vehicle hull 1.W, on two opposite sides of the platform 2. Fig. 2 Each of the two protective shields 4 extends over the entire width of the vehicle 1, in particular the vehicle hull 1.W.

[0050] The rocket launcher 3, in particular an exhaust outlet 6 of the rocket launcher 3, is rotatable in the azimuth direction AR within a specific azimuth angle range α and pivotable in the elevation direction ER within a specific elevation angle range β. The shield 4 is designed such that, when the rocket launcher 3 is aligned within the specific azimuth angle range α and within the specific elevation angle range β, the exhaust outlet 6 faces the shield 4.

[0051] According to Fig. 2Two azimuth angle ranges α are realized, corresponding to the two protective shields 4. Such two azimuth angle ranges α can be realized in different mechanical ways, for example, by allowing the rocket launcher 3 to be pivoted in the elevation direction ER beyond a position vertically oriented upwards from the vehicle and within an elevation angle range β of up to 180°. Other realizations of the azimuth angle ranges α are conceivable. It is also conceivable that mechanical movement of the rocket launcher 3 is possible even within larger angular ranges, but that ignition of the rocket to be fired by means of the rocket launcher 3 is prevented, for example, by the control system of the rocket launcher 3, if no protective shield 4 is facing the exhaust outlet 6.

[0052] The protective shield 4 is according to Figs. 3 to 6 , facing the exhaust outlet 6 of the rocket launcher 3, arranged on platform 2. According to Figs. 3 to 6The protective shield 4 is connected to the platform 2, and advantageously, the protective shield 4 moves with the platform 2 when the platform 2 moves, and can therefore be made correspondingly smaller than if the protective shield 4 were connected to the vehicle 1, in particular the vehicle body 1.W. The platform 2 is according to Figs. 3 to 6 with the protective shield 4 arranged on the platform 2, in particular rotatable by 360° in the azimuth direction AR, wherein in every angular position in the azimuth direction AR the protective shield 4 faces the exhaust gas outlet opening 6.

[0053] By means of the protective shield 4, a according to Fig. 1 ramp-shaped, one according to Fig. 3 , Fig. 5 and Fig. 6 A curved and / or concave deflecting surface 7 is formed for the exhaust jet 5. The deflecting surface 7 is oriented such that the exhaust jet 5 is directed away from the vehicle 1.

[0054] The protective shield 4 is according to Fig. 3 , Fig. 5 and Fig. 6The shield is tubular in shape so that the exhaust jet 5 can pass through it. Such a tubular shield 4 is, in particular, bent perpendicular to its axis A. However, the shield can also be bent along such an axis.

[0055] The axis A of the tubular protective shield 4 has an angle γ between 10° and 80° to the surface 8 of the vehicle 1. The flow cross-section of the tubular protective shield 4 advantageously widens towards an outlet opening of the tubular protective shield 4 facing away from the exhaust outlet opening 6, in particular forming a diffuser shape.

[0056] According to Fig. 5The protective shield 4 has an outer sheath 9, wherein at least one interior space 10 is formed by means of the outer sheath 9, and wherein a phase-change material 11 is arranged at least partially, and in particular completely, in the interior space 10. It is conceivable to provide and form one or two or more fluidically separated interior spaces 10. In particular, if two or more fluidly separated interior spaces are provided and formed, it is conceivable that two or more different phase-change materials are also used.

[0057] The phase change material 11 is designed to undergo a phase change from solid to liquid and / or from liquid to gaseous by means of the exhaust gas jet 5 impacting the protective shield 4.

[0058] The phase change material 11 has a phase change temperature from solid to liquid or from liquid to gaseous of 95°C to 650°C.

[0059] The phase change material 11 contains metal, tin, plastic, water, methanol, ethanol, acetone, sodium hydroxide and / or zeolite granules.

[0060] According to Fig. 5 at least one heat pipe 12, preferably designed with an integrated wick structure, is connected to the at least one interior space 10, wherein a heat sink 13 is formed by means of the heat pipe 12 and / or wherein the heat pipe 12 is connected to a heat sink 13, in particular to a condenser.

[0061] According to Fig. 5The heat sink 13, which is thermally connected to the protective shield 4, is formed by several heat pipes 12. The heat pipes 12 project from the protective shield 4 and are connected to it. The interiors of the heat pipes 12 are fluidically connected to the interior 10 of the protective shield 4, thus forming a common interior space. The heat sink 13 is formed primarily by the large outer surface area exposed to the ambient air created by the heat pipes 12, enabling significant heat transfer from the outer circumference of the heat pipes 12 to the ambient air. Alternatively, it would be conceivable to connect at least one heat pipe to the protective shield whose interior is fluidically sealed and therefore not fluidically connected to the interior of the protective shield. In this case, heat transfer would only occur between the heat pipe and the protective shield, primarily by conduction.

[0062] According to Fig. 6The tubular shield 4 has an intake area 14 and an acceleration area 15. From a fluid dynamics perspective, the intake area 14 is located between the exhaust outlet 6 of the rocket launcher 3 and the acceleration area 15. The intake area 14 has a larger flow cross-section than the acceleration area 15. The shield 4 has at least one suction opening 16 in the intake area 14 and / or in the acceleration area 15 for supplying air, in particular fresh air.

[0063] According to Fig. 6 The suction opening 16 is connected to an ABC hatch system 17 of the vehicle 1, in particular by means of a hose 16.S, so that potentially contaminated air from an area around an ABC hatch 18 of the ABC hatch system 17 can be accelerated towards the suction opening 16 by the exhaust jet 5.

[0064] Also Fig. 6Figure 1 shows a heat sink 13 thermally connected to the protective shield 4, which is formed here by means of several heat pipes 12. The heat pipes 12 are projecting from the protective shield 4 and connected to it. According to the design, the heat pipes 12 have Fig. 6 each creates a fluidically dense interior space.

[0065] Vehicle 1 exhibits according to Fig. 1 A neutralization medium supply 19 is provided, by means of which a neutralization medium such as sodium hydroxide solution, sodium hydroxide vapor, or the like can be supplied to the exhaust gas jet 5, in particular by means of at least one capillary and / or by means of at least one evaporation valve, preferably arranged on the protective shield 4. The neutralization medium supply 19 is designed according to Fig. 1The neutralizing medium supply is located on a side of the protective shield 4 facing the vehicle 1. However, it can also be located on a side of the protective shield facing away from the vehicle and / or in a central area of ​​the protective shield. The neutralizing medium can also be supplied to the deflection area 7 of the protective shield 4.

[0066] The protective shield 4 safely protects the vehicle 1 and the operating personnel from the exhaust jet 4 of a rocket arranged in the rocket launcher 3. Reference symbol list

[0067] 1 Military vehicle 1. Vehicle hull 2 ​​Platform 3 Rocket launcher 4 Shield 5 Exhaust jet 6 Exhaust outlet 7 Deflection surface 8 Vehicle surface 1 9 Outer shell 10 Interior 11 Phase change material 12 Heat pipe 13 Heat sink 14 Intake area 15 Acceleration area 16 Intake opening 16 Hose 17 ABC hatch system 18 ABC hatch 19 Neutralizing medium supply A-axis of the tubular shield 4 AR-azimuth direction ERE-elevation direction α-azimuth angle range β-elevation angle range φ-angle range of the shield 4 γ-angle

Claims

1. Military vehicle (1) with a platform (2) and with a rocket launcher (3), wherein the platform (2) is movably connected to the vehicle (1) for aligning the rocket launcher (3), in particular rotatable in the azimuth direction (AR), wherein the rocket launcher (3) is movably connected to the platform (2) for aligning the rocket launcher (3), in particular pivotable in the elevation direction (ER), characterized by the fact that at least one protective shield (4) for intercepting and / or deflecting an exhaust jet (5) of a rocket exiting the rocket launcher (3), in particular a rocket not released from the rocket launcher (3), is arranged on the vehicle (1) and / or the platform (2).

2. Vehicle (1) according to claim 1, characterized by the fact that the protective shield (4) is arranged on the vehicle (1), surrounding the platform (2) at least within an angle range (φ) of 90°.

3. Vehicle (1) according to claim 1 or 2, characterized by the fact thatthe rocket launcher (3), in particular an exhaust outlet opening (6) of the rocket launcher (3), which is rotatable in the azimuth direction (AR) in a certain azimuth angle range (α) and pivotable in the elevation direction (ER) in a certain elevation angle range (β), wherein the protective shield (4) is designed such that the exhaust outlet opening (6) is directed towards the protective shield (4) when the rocket launcher (3) is aligned in the certain azimuth angle range (α) and in the certain elevation angle range (β).

4. Vehicle (1) according to any of the preceding claims, characterized by the fact that the protective shield (4) is arranged on the platform (2) facing the exhaust outlet opening (6) of the rocket launcher (3).

5. Vehicle (1) according to any of the preceding claims, characterized by the fact that by means of the protective shield (4) a ramp-shaped, curved and / or concave deflection surface (7) for the exhaust jet (5) is formed.

6. Vehicle (1) according to any of the preceding claims, characterized by the fact that the protective shield (4) is tubular in shape, so that the exhaust jet (5) can be guided through the tubular protective shield (4).

7. Vehicle (1) according to the preceding claim, characterized by the fact that an axis (A) of the tubular protective shield (4) has an angle (γ) between 10° and 80° to the surface (8) of the vehicle (1).

8. Vehicle (1) according to any of the preceding claims, characterized by the fact that the protective shield (4) has an outer sheath (9) wherein at least one interior space (10) is formed by means of the outer sheath (9) wherein at least partially, in particular completely, a phase change material (11) is arranged in the interior space (10).

9. Vehicle (1) according to the preceding claim, characterized by the fact thatthe phase change material (11) is designed to undergo a phase change from solid to liquid and / or from liquid to gaseous by means of the exhaust jet (5) striking the protective shield (4).

10. Vehicle (1) according to claim 8 or 9, characterized by the fact that the phase change material (11) has a phase change temperature from solid to liquid or from liquid to gaseous of 95°C to 650°C.

11. Vehicle (1) according to claim 8, 9 or 10, characterized by the fact that the phase change material (11) comprises metal, tin, plastic, water, methanol, ethanol, acetone and / or zeolite granules.

12. Vehicle (1) according to claims 8 to 11, characterized by the fact that at least one heat pipe (12) preferably designed with an integrated wick structure is connected to the at least one interior space (10), wherein a heat sink (13) is formed by means of the heat pipe (12) and / or wherein the heat pipe (12) is connected to a heat sink (13), in particular to a condenser.

13. Vehicle (1) according to any one of claims 6 to 12, characterized by the fact that The tubular shield (4) has an intake area (14) and an acceleration area (15), wherein the intake area (14) is arranged in terms of flow technology between the exhaust outlet opening (6) of the rocket launcher (3) and the acceleration area (15), wherein the intake area (14) has a larger flow cross-section than the acceleration area (15), wherein the shield (4) has at least one suction opening (16) in the intake area (14) and / or in the acceleration area (15) for supplying air, in particular fresh air.

14. Vehicle (1) according to the preceding claim, characterized by the fact that the suction opening (16) is connected to an ABC hatch system (17) of the vehicle (1), so that potentially contaminated air from an area around an ABC hatch (18) of the ABC hatch system (17) can be accelerated towards the suction opening (16) by the exhaust jet (5).

15. Vehicle (1) according to any of the preceding claims, characterized by the fact that the vehicle (1) has a neutralization medium supply (19) by means of which a neutralization medium such as sodium hydroxide, sodium hydroxide vapor or the like can be supplied to the exhaust jet (5), in particular by means of at least one capillary and / or by means of at least one evaporation valve preferably arranged on the protective shield (4).

16. Vehicle (1) according to claim 15, characterized by the fact that the phase change material (11) includes the neutralization medium.

17. Method for intercepting and / or redirecting an exhaust jet (5) exiting a rocket launcher (3) with a military vehicle (1) according to any one of claims 1 to 16

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