stealth aircraft

Abstract

A stealth aircraft (1) with an aerodynamically and stealth-optimized airframe (2). The stealth aircraft (1) has a discharge chute (3) located in the airframe (2) to prepare for the release of a payload (4) during flight. The stealth aircraft (1) has an outlet (6) connecting the discharge chute (3) to a rear upper surface (B) of the airframe (2). The stealth aircraft (1) has a control unit (17) configured to actuate the outlet (6) to release the payload (4) from the discharge chute (3) via the outlet (6). The outlet (6) is located on the airframe (2) to release the payload (4) over the upper surface (B) of the airframe (2).

Description

TECHNICAL FIELD

[0001] The invention relates to a stealth aircraft having the features of the preamble of claim 1, as well as a method for operating a stealth aircraft and a computer program therefor.

[0002] The following background is intended only to provide information necessary to understand the context of the inventive ideas and concepts disclosed herein. Therefore, this background section may contain patentable subject matter and should not, per se, be considered prior art. STATE OF THE ART

[0003] DE 10 2004 029 487 A1 discloses an aircraft having a fuselage with a landing gear arranged on the underside of the fuselage and with a fuselage upper side arranged opposite thereto, wherein a weapon carrier device is arranged on the upper side of the fuselage and the weapon carrier device is arranged above the landing gear bays of the main landing gear and above the engine flow channel, viewed in the cross-section of the fuselage at the location of the main landing gear, the aircraft having a flight computer device with a control and mission function and an actuating device for moving control surfaces for controlling the aircraft, wherein the control and mission function has a flight guidance function for guiding the aircraft to a target point or drop-off point and a weapon drop-off function for dropping at least one weapon that can be carried in the weapon carrier device based on a specification,and wherein the aircraft has a function assigned to the control and mission functions, respectively, and a flight attitude sensor system with which the aircraft can be rotated about its longitudinal axis xf so far that a component of the resulting lift force from the underside of the fuselage runs against the direction of gravity.

[0004] DE 10 2011 106 348 A1 discloses an aircraft with a low radar signature, having a first side on which the turbine opening and payload or landing gear bays are arranged. A second side of the aircraft is designed to have a lower radar signature than the first side.

[0005] CN 1 02 328 746 B also refers to stealth aircraft.

[0006] US 2018 / 0 362 163 A1 relates to an aircraft comprising a launch tube extending at least along part of the length of a wing of the aircraft and through which an object can be released from the aircraft. The launch tube comprises an opening at a distal end of the wing. BACKGROUND

[0007] Stealth aircraft are specially designed to minimize detection by external sensors (e.g., electromagnetic or acoustic sensors). These aircraft are designed for military use and are characterized by their stealth technologies, which allow them to minimize electromagnetic, acoustic, and other signatures, making them more difficult for enemy detectors to detect. Stealth aircraft are often capable of surprise attacks and covert reconnaissance missions.

[0008] Of particular importance for stealth properties is the radar cross section (RCS), which is a measure of an object's ability to reflect radar beams. The higher an object's RCS, the easier it is to detect by radar. Stealth aircraft are designed to minimize their RCS, meaning they are only very dimly visible or even invisible to radar systems. This is achieved through special designs, shapes, surface textures, and materials that minimize radar reflection.

[0009] Measures to reduce radar cross-section in stealth aircraft include the use of absorbent materials that absorb radar beams and aircraft surface design, particularly the minimization of openings and gaps to minimize retroreflections. These aircraft often use stealth coatings and aerodynamic shapes to reduce RCS. Radar shielding and special techniques such as internal or fully enclosed weapon mounts can also be used to optimize stealth characteristics.

[0010] Maintaining RCS is particularly important when dropping payloads over enemy territory, as an increased RCS increases the likelihood of detection and attack. Stealth aircraft are designed to maintain their stealth characteristics even during such operations. When opening the cargo bay, the same principles and techniques must be applied to ensure that RCS remains minimized. This can be achieved through clever cargo bay design and the use of absorbent materials to complete the mission successfully and discreetly.

[0011] The invention is based on the object of improving the stealth aircraft in its camouflage function during use, in particular during load shedding. SUMMARY

[0012] This summary is intended to introduce a selection of features and concepts of the invention that are explained further in the description. This summary is not intended to identify important or essential features of the claimed subject matter, nor is it intended to limit the scope of the claimed subject matter.

[0013] According to the invention, the above-mentioned object is achieved by the features of the independent claims.

[0014] Specifically, the task is solved by a stealth aircraft. The stealth aircraft has an aerodynamic and stealth-optimized airframe. The stealth aircraft has a drop chute. The drop chute is arranged in the airframe to prepare for the drop of a load. The load is to be dropped from the stealth aircraft during flight. The stealth aircraft has an outlet. The outlet connects the drop chute to a rear (or rearward-facing) upper side of the airframe. The stealth aircraft has a control unit. The control unit is designed to control the outlet in order to drop the load from the drop chute via the outlet. The outlet is arranged on the airframe such that the load is to be dropped via the upper side of the airframe, preferably backwards in the direction of flight.

[0015] The invention has the advantage that the RCS of the stealth aircraft is kept low for the duration of the mission. Because the release occurs via the topside, a radar located below the stealth aircraft on the ground or in another aircraft (whether monostatic or bistatic) cannot detect the RCS change typically caused by a downward-opening cargo hold. The invention has the additional advantage that the acoustic and optical signatures created by the opening of conventional cargo hold doors on the underside of the aircraft can be avoided. The invention further has the advantage that the change in the aerodynamic properties of the aircraft, which occurs when conventional cargo hold doors on the underside of the aircraft are opened, can be avoided.The invention has the additional advantage that the conventional cargo hold flaps in the underside of the aircraft, which are subject to high aerodynamic forces when opened, can be omitted, thus saving weight.

[0016] Advantageous embodiments of the invention are specified in the subclaims.

[0017] The stealth aircraft may have an inlet. The inlet may connect the discharge chute to a forward (or forward-facing) upper surface of the airframe. The control unit may be configured to control the inlet and the outlet to discharge the load from the discharge chute via the outlet. The inlet may be arranged and configured on the airframe such that an airflow into the discharge chute caused by the flight operation of the stealth aircraft (from the front in the direction of flight) provides a pressure, preferably pneumatic. The pressure may cause or contribute to the load being pushed through the outlet (rearward in the direction of flight) to discharge the load via the (rearward or rearward-facing) upper surface of the airframe (preferably an outlet opening at the end of the outlet).

[0018] Consequently, a mechanically simple mechanism for dropping loads from the stealth aircraft can be provided.

[0019] The pressure difference between inlet and outlet during load shedding can be greater than 2 times (or 3 times, 4 times or 5 times) the atmospheric pressure prevailing in the stealth aircraft's environment.

[0020] The inlet may have an inlet flap. The inlet flap may be configured to operate in two operating positions, OPEN and CLOSED. The outlet may have an outlet flap. The outlet flap may be configured to operate in two operating positions, OPEN and CLOSED. In the CLOSED operating position, the inlet flap and / or the outlet flap may be flush with a surrounding fuselage surface of the stealth aircraft and, for example, be covered with the same material.

[0021] For this purpose, the inlet can have an inlet flap motor. The outlet can have an outlet flap motor. The control unit can be configured to provide a release signal to both the inlet flap motor and the outlet flap motor to initiate the simultaneous opening and closing of the corresponding inlet flap and outlet flap. Likewise, the control unit can be configured to first control the inlet flap motor and, when the inlet flap is in the OPEN operating position, then control the outlet flap motor to move the outlet flap to the OPEN operating position.

[0022] The inlet may further comprise an inlet duct. The inlet duct may be provided as a ram air duct. The inlet duct may provide a direct air supply connection from the inlet flap to the discharge duct.

[0023] The outlet may further include an outlet duct. The outlet duct may provide a direct air discharge connection from the discharge duct to the outlet flap.

[0024] When both the inlet flap and the outlet flap are in the OPEN operating position, direct air communication between the forward upper surface and the aft upper surface through the airframe can be provided.

[0025] This allows a simple mechanism for dropping loads from the stealth aircraft to be provided using dynamic pressure.

[0026] The inlet flap and the outlet flap can each be aligned with the top surface of the airframe in the closed operating position. The inlet flap can be aligned with the forward upper surface of the stealth aircraft in the closed operating position. The outlet flap can be aligned with the rear upper surface of the stealth aircraft in the closed operating position. The airframe can preferably be an airframe or fuselage.

[0027] By aligning and flushing all openings, all aerodynamic and camouflage properties of the stealth aircraft can be maintained.

[0028] The stealth aircraft may further comprise one or more aircraft engines for propelling the stealth aircraft through the air. The exhaust flap and the one or more aircraft engines may be arranged relative to each other on the airframe in such a way that the (already ejected or jettisoned) load remains unaffected by exhaust gases from the aircraft engine. In particular, the exhaust flap may be arranged between the aircraft engines, for example, centrally between two equally spaced aircraft engines.

[0029] This ensures the stealth characteristics of the stealth aircraft.

[0030] For example, the aircraft engine can form part of the inlet or part of the inlet duct. In this case, part of the inlet duct can correspond to an aircraft engine inlet duct, preferably a serpentine inlet duct. The inlet flap can be arranged in or on the aircraft engine inlet duct. The inlet flap can be a connecting piece between the other part of the inlet or the other part of the inlet duct and the aircraft engine inlet duct. In the OPEN operating position, the other part of the inlet duct or the other part of the inlet duct and the aircraft engine inlet duct can communicate for ventilation purposes. In the CLOSED operating position, the other part of the inlet duct or the other part of the inlet duct and the aircraft engine inlet duct can be watertight, airtight and / or hermetically separated from one another.For example, the intake duct can consist of one and the other part of the intake duct, which can be divided by the intake flap. The same applies to the other aircraft engine in the case of two aircraft engine intake ducts, especially those arranged symmetrically to the cockpit.

[0031] The control unit can be designed to control the inlet and the outlet during flight operation of the stealth aircraft for load shedding such that the outlet flap and the inlet flap are simultaneously in the OPEN operating position in order to jettison the load from the discharge duct on the (rear) upper side of the stealth aircraft by means of an air flow through the inlet duct caused by the flight operation in the direction from the inlet to the outlet.

[0032] This allows for an energy-efficient drop technology with few moving parts and high operational reliability, which at the same time ensures the stealth aircraft's camouflage properties.

[0033] The pressure, which can be provided in whole or in part as aerodynamic dynamic pressure, for example when the inlet flap is open, can be designed or utilized by means of a sabot attached to the load, so that the release of the load requires no further energy or additional electrical and / or mechanical (force-applying) means or techniques. The sabot can be designed so that it separates automatically from the load after the load is released through the action of aerodynamic forces. Thus, the use of a sabot can make a compression device described below superfluous in any case and / or reduce the diameter of the inlet. The inlet or an associated inlet opening can be designed with regard to the sabot and / or a target speed of the stealth aircraft at the time of load release.

[0034] This can reduce costs and the risk of disruption while improving performance.

[0035] The stealth aircraft may further comprise an air pressure sensor. The air pressure sensor may be configured to measure the pressure prevailing in the discharge duct, particularly provided by the air flow into the discharge duct. The measurement may be performed continuously, periodically, (irregularly) at regular intervals, incrementally, or at intervals.

[0036] For example, the air pressure sensor can be powered or switched on when the navigation data indicates that the aircraft is approaching the target area. As long as the navigation data indicates that the stealth aircraft is outside the target area, the air pressure sensor can be de-energized or switched off.

[0037] The stealth aircraft may further comprise, for example, an auxiliary or supporting device, a compressor device. The compressor device may be configured to generate compressed air (also called compressed air). The stealth aircraft may further comprise a compressed air duct. The compressed air duct may be arranged between the compressor device and the discharge duct. The compressed air duct may be configured to direct the compressed air generated by the compressor device into the discharge duct and / or to supply the discharge duct with compressed air.

[0038] The control unit can be configured to set a pressure value for the compressor device based on a difference between a target pressure value of the discharge duct and the pressure in the discharge duct measured by the air pressure sensor. The compressor device can be configured to generate compressed air at the set pressure value.

[0039] The control unit can also be designed to adjust a flow area of ​​the inlet channel (e.g. at the inlet flap) as a function of the difference based on the difference between the target pressure value of the discharge shaft and the pressure in the discharge shaft measured by the air pressure sensor.

[0040] The target pressure value of the discharge chute should be a value that ensures detachment of the load from the stealth aircraft.

[0041] The pressure value and / or flow area can be adjusted continuously, periodically, regularly, step by step, intermittently, or in pulses. For example, the compressed air can be adjusted only briefly per load shedding. The same can apply to the flow area.

[0042] This allows for optimized, and if necessary accelerated, drop behavior of the load.

[0043] The stealth aircraft may further include a cargo bay. The cargo bay may have one or more cargo doors located on the underside of the airframe. The one or more cargo doors may extend along a longitudinal axis of the stealth aircraft. The cargo to be jettisoned (on the ground) can be loaded into the stealth aircraft via the one or more open cargo doors (see above for opening the cargo bay, which is also referred to here as the cargo hold). The cargo is to be loaded into the cargo bay or is stored there.

[0044] Thanks to the techniques presented herein, the loading flaps can be equipped with simple hinges and without special reinforcements, as they are only operated when stationary on the ground and are therefore not subject to aerodynamic forces, as is the case with conventional loading flaps when opened during flight. After loading on the ground, the loading flaps of the stealth aircraft described herein can also be sealed, if necessary, to close all gaps and thus optimize the stealth properties of the underside of the fuselage.

[0045] The stealth aircraft may further include a magazine. The magazine may be configured to rotatably or linearly store the jettisoned load between the cargo compartment and the discharge chute. From the discharge chute, the load may be released to the outlet based on a signal from the control unit (e.g., according to navigation data, as described below). The control unit may be configured to keep the one or more cargo bay loading doors closed during flight operations.

[0046] This can support the reliability of the camouflage properties.

[0047] The above-mentioned object is also achieved by a method for operating a stealth aircraft. The stealth aircraft has an airframe with an aerodynamic design and an integrated release chute. The stealth aircraft further has a control unit. The method comprises providing, by a magazine, a load to be jettisoned in the release chute as long as navigation data provided to the control unit does not indicate a target area for dropping the load. The method comprises actuating, by the control unit, an outlet as soon as the navigation data indicate the target area for dropping the load, in order to jettison the load from the release chute above the stealth aircraft by means of pressure in the release chute. Here, jettisoning can also comprise ejection. Here, ejection can mean pressurized ejection / dropping, preferably independent of gravity.

[0048] The method may include providing or initiating, by the control unit, a ram air duct between the discharge chute and a closable inlet flap provided on a top side of the airframe, as soon as the navigation data indicates the target location area for jettisoning the load, in order to jettison the load from the discharge chute, by means of a flow in the ram air duct, above the stealth aircraft.

[0049] Expressions such as “above” or “top” refer to the side of the stealth aircraft facing away from the Earth’s surface.

[0050] The above-mentioned object is also achieved by a computer program. The computer program comprises instructions which, when executed by a computer, cause the computer to carry out or initiate a method for operating a stealth aircraft or steps thereof. The stealth aircraft has an airframe with an aerodynamic design and an integrated delivery chute. The method comprises providing or storing, via a magazine, a load to be jettisoned in the delivery chute as long as navigation data provided to the computer do not indicate a target area for dropping the load. The method comprises actuating or initiating, via the computer, an outlet as soon as the navigation data indicate the target area for dropping the load, in order to jettison the load from the delivery chute by means of pressure (preferably provided by compressed air and / or ram air) in the delivery chute above the stealth aircraft.

[0051] The method may include providing or initiating, by the computer, a ram air duct between the delivery chute and a closable inlet door provided on a top side of the airframe, once the navigation data indicates the target location area for jettisoning the load, to jettison the load from the delivery chute, by means of a flow in the ram air duct, above the stealth aircraft.

[0052] The navigation data can be Global Navigation Satellite Systems (GNSS) coordinates (GPS, Glonass, Galileo, etc.). The GNSS coordinates can refer to position data and include longitude, latitude, and altitude. Longitude can indicate the position east or west of the prime meridian, measured in degrees. One degree (°) can be divided into 60 arc minutes ('), and each arc minute can be divided into 60 arc seconds (''). Latitude can indicate the position north or south of the equator, measured in degrees. Altitude (ellipsoidal altitude or geoidal altitude) can indicate the height of a point above the Earth's ellipsoid, above the Earth's surface, or relative to sea level, measured in meters, feet, or another unit of measurement. Degrees and arc seconds (gon, gon = 1 / 400 of a degree) can also be used for longitude and latitude.

[0053] The computer program may, for example, be a module for launching / operating the stealth aircraft or the control unit as described herein.

[0054] The above-mentioned task is also achieved by a data storage medium. The computer program can be stored on a machine-, processor-, or computer-readable storage medium, such as a permanent or rewritable storage medium. This also includes the possibility of making the computer program available for download on a server or a cloud server, e.g., via a data network such as the Internet or a communications connection such as a wireless connection.

[0055] In other words, the invention relates to the aerodynamic load shedding in stealth aircraft. For example, a closable ram air supply is formed via a closable air inlet. Optionally, a compressed air supply can be provided. By means of the ram air supply, and optionally the compressed air supply, a load can be dropped via the rear upper section of a stealth bomber. The load can be rotatably provided or stored in a rotating magazine (drum). This makes a large shaft opening or cover flap on the underside of the fuselage unnecessary, thus saving weight. For example, this can result in no change in the aerodynamics during the drop. Thus, for example, there can be no change in the signature of the underside of the fuselage during the drop (radar signature, acoustic signature, stealth, camouflage). The drop orEjection of the payload can be generated exclusively by an aerodynamic force, for example. The aerodynamic force can result from the dynamic pressure from the front and / or the suction from the rear. The force can be amplified by a sabot, preferably inverted (even inverted), or a pneumatic impulse. The sabot can thus be mounted inverted on the load, particularly at a rear end of the load.

[0056] Although some of the aspects described above relate to the stealth aircraft, the control unit, the method or the computer program, these aspects may also apply to the other aspects thereof in a corresponding manner.

[0057] In one example, the control unit may be implemented using hardware circuits, software means, or a combination thereof. For example, multiple units of the control unit may each be realized in a single physical unit, for example, when multiple functions are implemented in software. The units of the control unit may also be implemented in hardware components. The units of the control unit are each to be understood as functional units that are not necessarily physically separated from one another. For example, the control unit may be realized at least partially as a computer, field-programmable logic array (FPLA), field-programmable gate array (FPGA), microcontroller, CPU (e.g., with multiple cores), graphics processing unit (GPU), application-specific integrated circuit (ASIC), and / or digital signal processor (DSP).

[0058] All technical and scientific terms used herein have the meaning commonly understood by those skilled in the art in the technical field of aerospace engineering; they are to be interpreted based on the definitions found in the dictionary or the technical jargon of that technical field. If technical terms are used incorrectly and thus do not express the technical spirit of the present invention, they shall be replaced by technical terms that convey a correct understanding to those skilled in the art.

[0059] The terms "first" and "second" are merely intended to distinguish components from one another. For example, a first component can be referred to as the second component, and a second component as the first component. It should be noted that these terms, as well as all numerical designations ("one," "two," etc.), are not intended to be exhaustive with regard to the scope of protection, but are also exhaustive with regard to the disclosure content. For example, the expression "two ABC" can mean either "exactly two ABC" or "two or more ABC."

[0060] If it is stated here that a component is "connected" or "communicates" with another component, this may mean, for the purposes of this disclosure, that these components may also be directly connected or communicate with each other. The term "directly" indicates that no further component is present between them.

[0061] The process steps described herein should not be interpreted as requiring them to be performed in a particular order, unless expressly or implicitly stated otherwise, for example, if these process steps cannot be interchanged for technical reasons. The process steps may also be performed directly one after the other (without any further intervening steps) and / or continuously. BRIEF DESCRIPTION OF THE DRAWINGS

[0062] Further objects, features, advantages, and possible applications will become apparent from the following description of non-limiting embodiments with reference to the accompanying drawings, in which: Fig. 1 a schematic representation of a longitudinal section of a stealth aircraft; Fig. 2 is a schematic view of a method for operating the stealth aircraft; and Fig. 3 a schematic view of a control unit of the stealth aircraft.

[0063] The reference symbols used in the drawings and their meanings are summarized in the list of reference symbols at the end of this description. The same or similar components in the drawings are always provided with the same or similar reference symbols. Detailed explanations of known functions and structures are omitted if they detract from the invention. DETAILED DESCRIPTION

[0064] The stealth aircraft, the method for its operation, and the computer program therefor will now be described with reference to the embodiments. Without being limited thereto, specific details are explained to provide a deeper understanding of the invention.

[0065] Furthermore, spatially relative descriptors, such as "bottom," "top," and the like, may be used herein to conveniently describe the relationship of the components depicted in the drawings. The spatially relative descriptors are intended to additionally encompass other orientations of the stealth aircraft in use or operation. The stealth aircraft may be oriented differently (rotated 90 degrees or in a different orientation), and the spatially relative descriptors used herein may be interpreted accordingly.

[0066] Fig. 1 shows a schematic representation of a longitudinal section of a stealth aircraft 1. The stealth aircraft 1 has an airframe 2 with an upper side AB and a lower side C, which are aerodynamically and stealth-optimized. The upper side AB is essentially divided into a front upper side A and a rear upper side B. A first dimension of the rear upper side B can be greater than 1 time (or 1.5 times or 2 times or 3 times) a second dimension of the front upper side A. The first and second dimensions can each be dimensions running in the longitudinal direction (along the longitudinal axis or roll axis) of the stealth aircraft 1 and together result in an aircraft upper side length running along the roll axis. A third dimension of the lower side C can correspond to an aircraft lower side length running along the roll axis and be less than 1 time (or 0.9 times or 0.8 times) the aircraft upper side length running along the roll axis.

[0067] In Fig. 1 also shows the flight direction F, since the stealth aircraft 1 flies forward during operation. An essential component is the discharge duct 3 integrated into the airframe 2. The discharge duct 3 can be pressurized even before operation. In any case, the discharge duct 3 is isolated from the external environment of the stealth aircraft 1 before the load 4 is released (here with a preferably inverted sabot 5) or when the outlet flap 7 of the outlet 6 is closed. In other words, the discharge duct 3 in this case is watertight, airtight and / or hermetically sealed. The outlet 6 is arranged in a rear upper region of the airframe 2. When the outlet flap 7 is open, the load 4 is discharged or ejected from the discharge duct 3 via the outlet channel 8.

[0068] The discharge chute 3 can be pressurized P by means of the inlet 9 and / or the compressor device 15. The inlet 9 has an inlet flap 10, which can be opened or closed simultaneously with the outlet flap. When the inlet flap 10 is open, an air flow caused from the front in the direction of flight F through the inlet channel 11 can provide a pressure P in the discharge chute 3. This pressure P in the discharge chute 3 can also be provided by the compressor device 15 connected to the discharge chute 3 via a compressed air channel 16 (for example, if no inlet 9 is present). Likewise, if the inlet 9 is present, the compressor device 15 can also be used in addition to achieve a predetermined target pressure value for the release if the pressure P generated by the inlet channel indicates that additional pressure is required.Also, if the compressor device 15 is present, the inlet 9 can be used additionally to achieve the target pressure value predetermined for the discharge if the pressure P generated by the compressor device 15 indicates that additional pressure is required.

[0069] To measure the pressure P in the discharge chute 3, an air pressure sensor 14 is used, which communicates with the control unit 17. The control unit 17 assumes the role of the central control unit in the stealth aircraft 1, as described below. The control unit 17 thus assumes control of the essential components, in particular the inlet flap 10, the outlet flap 7, the magazine 13, the compressor device 15, and / or the loading flap(s) 12. Likewise, the control unit can use the air pressure sensor 14 continuously, periodically, (irregularly) regularly, step by step, or at intervals.

[0070] The discharge chute 3 may extend in the direction of the longitudinal axis of the stealth aircraft 1. For example, the discharge chute 3 may be arranged centrally and / or symmetrically to the longitudinal axis of the stealth aircraft 1.

[0071] The load 4 (with optional sabot 5) can be loaded into the stealth aircraft 1 via one or more open loading hatches. For this purpose, a rotating magazine 13, for example, is available to accommodate the load 4 and load the delivery chute 3 with a load 4 to be dropped. The magazine 13 can rotate about the longitudinal axis or perpendicular to it and, for example, be arranged centrally in the stealth aircraft 1. The loading hatch(s) 12 are never opened during operation of the stealth aircraft 1. This prevents a modified signature.

[0072] Fig. 2 shows, in relation to Fig. 1, a schematic view of the method S0 for operating the stealth aircraft 1. The method S0 in Fig. 2 generally describes the operation of the stealth aircraft 1, in which, in S1, the magazine 13 provides the load 4 to be jettisoned in the delivery chute 3 as long as the provided navigation data does not indicate to the control unit 17 a target area for jettisoning the load 4. As soon as the navigation data indicate the target area for jettisoning the load 4, the control unit 17 actuates the outlet 6 in S2 to jettison the load 4 from the delivery chute 3, using the pressure P in the delivery chute 3, above the stealth aircraft 1.

[0073] The blocks of the block diagram in Fig. 2 can, for example, be substantially represented in a machine-, processor- or computer-readable data carrier and thus be executed by a computer or processor 18, as described below with respect to Fig. 3. Examples may further be or refer to a computer program that includes program code for executing at least some of the method steps of Fig. 2 when the computer program is executed on the computer or processor 18. An example may also include a volatile memory 19 or persistent memory 20, as also described below with respect to Fig. 3, which is machine-, processor- or computer-readable and encodes machine-executable, processor-executable or computer-executable programs with instructions that cause the execution of some or all of the method steps.

[0074] Fig. 3 shows a schematic view of the control unit 17 of the stealth aircraft 1. Fig. Figure 3 schematically shows a block diagram illustrating the (central) control unit 17 as a computer device. The control unit 17 may, for example, be an integrated part of the stealth aircraft 1. The control unit 17 implements one or more steps of the method S0 as shown in Fig. 2. In particular, the control unit 17 provides functionality, such as computer software running on the control unit 17 and executing one or more steps of the method S0.

[0075] The data or information referred to below as compact data includes one or more of: navigation data, set pressure value, measured pressure, target pressure value, flow area, or information and signal data related to the inlet, outlet, discharge chute, compressor, magazine, and / or sabot. These elements are referred to as compact data for simplicity, even if not all of the data or information described above may be appropriate in some cases.

[0076] In particular, the control unit 17 may execute instructions associated with the compact data that are included in the computer program described herein and cause the control unit 17 to execute or initiate the one or more steps of the method S0.

[0077] It is contemplated herein that the control unit 17 may take any suitable physical form. As an example, the control unit 17 may be embodied at least partially as an embedded computer, system-on-chip (SOC), and / or single-board computer (SBC). The control unit 17 may be uniform or distributed; span one or more locations in the stealth aircraft 1; or span one or more machines therein. The control unit 17 may execute or initiate one or more steps of the method S0 without significant spatial or temporal limitations. As an example, the control unit 17 may execute or initiate one or more steps of the method S0 in real time, in parallel, or in batch mode. The control unit 17 may execute or initiate step(s) of the method S0 at different times or at different locations.

[0078] The control unit 17 has at least one or more of the following components: the processor 18, the volatile memory 19, the persistent memory 20, a bus 21, an arbiter 22, one or more interfaces 23, a main power supply 24, and an auxiliary power supply 25. The components of the control unit 17 can be implemented at least partially in hardware and / or software. The interconnection of the components of the control unit 17 is shown merely for the sake of simplicity as shown in Fig. 3. In particular, the interconnection and connection may differ in implementation due to signal processing and signaling.

[0079] The processor 18 has means for executing instructions associated with the compact data, e.g., of the computer program described herein. For example, the processor 18 can load the instructions associated with the compact data contained in the computer program described herein, e.g., from the volatile memory 19 and / or the persistent memory 20, and then execute the instructions, which in turn causes the processor 18 to perform the one or more steps of the method S0, such as in Fig. 2. The processor 18 may include an internal register / cache for the compact data, the instructions associated with the compact data, and / or associated addresses. The processor 18 may include an FPGA, ASIC, DSP, microcontroller, CPU, and / or GPU for accessing the internal register / cache. As an example, to execute the instructions associated with the compact data, the processor 18 may retrieve them from the internal register / cache of the processor 18, the volatile memory 19, or the persistent memory 20; decrypt and execute them; and then write a result to the internal register / cache of the processor 18, the volatile memory 19, or the persistent memory 20.

[0080] As an example, processor 18 may include an instruction cache, a data cache, and / or a translation buffer (TLB). The compact data-related instructions in the instruction cache may be copies of instructions in volatile memory 19 and / or persistent storage 20, and the instruction cache may accelerate the fetching of these compact data-related instructions by processor 18. The compact data in the data cache may be copies of data for the compact data-related instructions currently executing on processor 18 in volatile memory 19 and / or persistent storage 20. The results of previous compact data-related instructions executing on processor 18 may be scheduled for access by subsequent compact data-related instructions to be executed on processor 18, or for writing to volatile memory 19 and / or persistent storage 20.The data cache can accelerate the read or write operations of processor 18. The addresses associated with the compact data in the TLB can be address references to addresses in volatile memory 19 and / or persistent storage 20 to accelerate virtual address translation for processor 18.

[0081] The volatile memory 19 may be a dynamic RAM (DRAM) or a static RAM (SRAM). The volatile memory 19 may, in particular, be embodied as the data storage medium described herein, on which the computer program described herein may be at least temporarily stored. Furthermore, the volatile memory 19 may be a single-channel or multi-channel RAM. The volatile memory 19 may include a main memory for storing instructions related to the compact data for the processor 18, which then executes these instructions; or include the compact data for the processor 18, which the processor 18 uses to operate on them. For example, the control unit 17 may load these instructions into the volatile memory 19 from the persistent memory 20 or another source (such as another computer, the network, or the cloud).Processor 18 can then load these instructions from volatile memory 19 into the internal register / cache of processor 18. To execute these instructions, processor 18 can retrieve and decrypt these instructions from the corresponding internal register / cache. During or after executing these instructions, processor 18 can write a result (which may be intermediate or final results) to the internal register / cache. Processor 18 can then write the result to volatile memory 19.

[0082] For example, processor 18 executes only instructions related to the compact data in processor 18's internal register / cache or volatile memory 19 (as opposed to persistent memory 20), and operates only on the compact data in processor 18's internal register / cache or volatile memory 19 (as opposed to persistent memory 20).

[0083] The persistent memory 20 has a mass storage device, e.g., a non-volatile mass storage device (NVM), for the compact data or the instructions associated with the compact data. The persistent memory 20 can, in particular, be embodied as the data storage device described herein, on which the computer program described herein can be stored. As an example, the persistent memory 20 can be a flash memory, in particular an SSD or eMMC. The persistent memory 20 can store the compact data in an erasable or non-erasable manner. The persistent memory 20 can be located in the control unit 17, i.e., internally, or externally.

[0084] The processor 18 can be connected to the persistent memory 20 directly or indirectly, e.g., via the arbiter 22. The connection can be implemented via a clock bus, command bus, and data bus. This is shown only schematically with reference to bus 21 in Fig.3. The persistent memory 20 receives instructions associated with the compact data and the compact data in conjunction with a clock signal provided by the processor 18 on the clock bus. The clock signal clocks the reception of the instructions associated with the compact data and the compact data. The processor 18 sends an instruction associated with the compact data to the persistent memory 20 via the instruction bus. Furthermore, the processor 18 sends the compact data to the persistent memory 20 via the data bus according to the instruction or receives the compact data from the persistent memory 20 via the data bus.

[0085] In one example, persistent memory 20 may have a clock pin through which the clock signal is received at persistent memory 20. The clock signal may be a write enable signal and / or a read enable signal. Persistent memory 20 may further have first and second input / output (I / O) pins. The compact data is received at persistent memory 20 via the first I / O pin in synchronization with the clock signal. Persistent memory 20 may further have a command / address buffer, control logic, and an I / O buffer. The command / address buffer operates at a first operating speed and, synchronously with the clock signal, buffers the command and corresponding address received via the second I / O pin and associated with the compact data. One I / O buffer operates at the first operating speed and buffers the compact data as read data from the NVM or writes the compact data as write data to the NVM. The first and second I / O pins may coincide.Here, the clock signal can be formed by a first and second clock signal, in which the first clock signal only switches during a period in which the command and address (both related to the compact data) are received from persistent memory 20, and the second clock signal only switches during a period in which the compact data is received by persistent memory 20. The first operating speed corresponds to a data input speed or data output speed between persistent memory 20 and processor 18. The control logic controls an operation with respect to the NVM based on the buffered command and the buffered address (both related to the compact data). Here, the control logic operates at a second operating speed that is lower than the first operating speed and corresponds to an internal operating speed of persistent memory 20.

[0086] The bus 21 can be understood herein as a subsystem of the control unit 17 that transmits the compact data and / or electrical power between the components of the control unit 17. The (one) bus 21 can connect the components of the control unit 17 to one another via the same set of lines. The bus 21 can be designed for dedicated communication of the compact data between two or more of the components of the control unit 17. The bus 21 can be a system bus via which the processor 18 is connected to the other components of the control unit 17. In this case, the bus 21 can be synchronous - the compact data is transferred bidirectionally with a clock edge of a clocking of the bus 21 - and / or asynchronous - no clocking, but a handshake takes place to transfer the compact data.In such a semi-synchronous system bus, the bus 21 is clocked, but control lines allow wait cycles to also use slow components, such as the persistent memory 20, via the bus 21.

[0087] Arbiter 22 can be provided for at least partial control over bus 21. Arbiter 22 can be considered a coprocessor subordinate to processor 18. Arbiter 22 regulates access to bus 21 related to the compact data based on a two-way handshake or three-way handshake. For this purpose, three signals are used: Bus Request (BREQ) for forwarding the compact data, Bus Grant (BGRT) for confirming and approving forwarding, and Bus Grant Acknowledge (BGA) for optional forwarding feedback. Arbiter 22 simultaneously receives multiple BREQs from different components of control unit 17 via bus 21. Arbiter 22 sorts the BREQs by priority and forwards them sequentially—in a pipeline—to processor 18. Once the processor 18 has received the BREQ, the processor 18 sends the BGRT to the arbiter 22 or directly to the component of the control unit 17 that sends the BREQ.A subordinate BREQ of the BREQs in the pipeline—e.g., from another component of the control unit 17—is forwarded to the processor 18 in response to a BGRT sent by the processor 18 relating to the BREQ with priority in the pipeline and related to at least a portion of the compact data. The BGRT relating to the subordinate BREQ is sent by the processor 18 to the arbiter 22 after at least a portion of the compact data has been processed. The arbiter 22 can, for example, in turn, in response to the BGRT relating to the subordinate BREQ, send a BREQ of the BREQs further down the pipeline—e.g., relating to another portion of the compact data—to the processor 18. Likewise, in response to each BGRT from the processor 18, the arbiter 22 can send a respective BGA relating to it to the processor 18. With the procedure described here, a BGA can be omitted entirely.This saves overhead in the communication between the components of the control unit 17. This means that a two-way handshake is provided instead of a three-way handshake.

[0088] Bus 21 can also include a data bus, address bus, and control bus. The compact data is transmitted bidirectionally between the components of control unit 17 via the data bus. The address bus is operated solely by processor 18 and unidirectionally transmits memory addresses associated with the compact data. The control bus is controlled solely by arbiter 22, e.g., in the sense of a watchdog, and transfers control of it to the processor in the pipelined manner described above to control the transmission of the compact data.

[0089] The interface(s) 23 enable the control unit 17 to communicate with one or more GNSS receivers (not shown). Direct wired communication connections with the one or more GNSS receivers can be established via the interface(s) 23. For example, this can be an ad hoc network or local area network (LAN) consisting of the control unit 17 and the one or more GNSS receivers.

[0090] The interface(s) 23 enable the control unit 17 to communicate with a network, e.g., Bluetooth, WLAN, a mobile radio system, and / or at least part of the Internet, when the stealth aircraft 1 has ground contact. If ground contact is lost, the control unit 17 can prevent communication and / or powering of wireless interface(s), except for the GNSS receivers.

[0091] The interface(s) 23 can enable user interaction with the control unit 17 in an environment of the control unit 17 (for example, on-board computers in the environment or within the aircraft cockpit). The interface(s) 23 can comprise device and / or software drivers that enable the processor 18 to control the interface(s) 23 to communicate an action instruction based on the compact data to the aircraft cockpit, in particular to the pilot, or to a general control system for controlling the stealth aircraft 1.

[0092] The interface(s) 23 can ensure a power supply to the components of the stealth aircraft 1 by means of the main power supply 24 and the auxiliary power supply 25.

[0093] The interface(s) 23 may enable sensor measurements in a close proximity to the control unit 17. The interface(s) 23 may be connected to the external air pressure sensor 14, which couples to the processor 18 of the control unit 17. The interface(s) 23 may include device and / or software drivers that enable the processor 18 to control the interface(s) 23 to obtain measured values ​​from the air pressure sensor 14, on which the compact data is based or which are represented by the compact data.

[0094] The control unit 17 as an (NR) UE can be used in Narrow Band (NB) Internet of Things (IoT) applications where only occasional and small amounts of data are sent in the uplink (UL), such as the compact data. This can occur immediately before the takeoff of the stealth aircraft 1. For example, the control unit 17 can be part of a 4-stage Random Access Channel (RACH) transmission procedure, which includes the transmission of four messages (Msg1, Msg2, Msg3, and Msg4) before transmitting the compact data to the serving base station. Here, the control unit 17 can perform random access by sending a RACH preamble—e.g., Msg1—on a RACH resource. The serving base station can respond with a Random Access Response (RAR)—e.g., Msg2. The control unit 17 can then send a Radio Resource Control (RRC) connection request - e.g. Msg3 - in the Physical Uplink Shared Channel (PUSCH) (e.g. NR-PUSCH).The serving base station can then respond with an RRC Connection Setup—e.g., Msg4—which completes the initial access process of control unit 17. This RACH mode is an inefficient way of transmitting the compact data, since a transfer of the compact data between control unit 17 and the serving base station only takes place after the four messages.

[0095] The control unit 17 can also transmit the compact data via the communication interface 23 upon a predefined event. This predefined event can be the successful completion of a communication connection with a network. In this case, the control unit 17 can retrieve the compact data stored in the volatile memory 19 and forward it in packets via the communication interface 23 over the mobile radio system.

[0096] The main power supply 24 supplies at least one or more of the components of the control unit 17 and the stealth aircraft 1 with electrical power, e.g., via the bus 21 and the interface(s) 23. In particular, the main power supply 24 charges the auxiliary power supply 25 with electrical power, e.g., from outside the control unit 17, e.g., in the case where the main power supply 24 is connected to the power source outside the control unit 17. Here, the main power supply 24 may represent a preferred component used to power the components of the control unit 17 and may, for example, comprise an accumulator or a battery. The main power supply 24 may comprise further components such as voltage regulators, DC voltage stabilizers, series regulators, buck converters, and / or boost converters to meet the corresponding requirements of the components of the control unit 17.The main power supply 24 can have either a dedicated fixed power supply connection to the external power source or a detachable power supply connection for charging the accumulator or battery of the main power supply 24. For this purpose, the main power supply 24 can have an inverter to provide a predetermined DC power supply from a connected AC power source as the external power source. The predetermined DC power supply can also already be provided by a connected DC power source as the external power source. The DC power supply can be regulated via the above-mentioned voltage regulators and supplied to the components controlled by the control unit 17 and the other components of the stealth aircraft 1 as set DC power supplies.

[0097] The auxiliary power supply 25 is connected to the volatile memory 19 and / or the permanent memory 20 via the bus 21. The auxiliary power supply 25 is charged by the electrical power of the main power supply 24. The auxiliary power supply 25 can be arranged inside or outside the control unit 17, or inside or outside the volatile memory 19 and / or the permanent memory 20. For example, the auxiliary power supply 25 can be housed on a main board of the control unit 17 to supply the volatile memory 19 and / or the permanent memory 20 with auxiliary power. The auxiliary power supply 25 can, in particular, be embodied in the form of a supercapacitor, an accumulator, and / or a battery. The power capacity / energy capacity of the main power supply 24 can be many times greater, for example, at least 10 times or 50 times greater, than the power capacity / energy capacity of the auxiliary power supply 25.

[0098] The processor 18 monitors changes in the electrical power supplied by the main power supply 24. In the event of a sudden power failure, e.g., if the power source external to the control unit 17 is disconnected from the main power supply 24 or the main power supply 24 degrades or fails for another reason, and the processor 18 determines that the electrical power supplied by the main power supply 24 to one or more of the components of the control unit 17 has fallen below a threshold, e.g., 0.8 or 0.75 of an operating power of the main power supply 24, the processor 18 causes the auxiliary power supply 25 to assume a remaining supply power for a shutdown of the control unit 17. The shutdown includes supplying at least the processor 18, the volatile memory 19, and / or the persistent memory 20 with electrical power for the duration of the shutdown.During the shutdown process, the compact data currently located in the volatile memory 19 and / or the compact data currently being processed in the processor 18 are directly erased, for example, by quickly and completely discharging the supercapacitor.

[0099] At this point, it should be noted that all parts described above, viewed individually and in any combination, particularly the details shown in the drawings, are claimed as essential to the invention. Modifications to these are familiar to those skilled in the art. LIST OF REFERENCE SYMBOLS 1 stealth aircraft 2 airframe 3 Discharge chute 4 Last 5 sabots 6 Outlet 7 Outlet flap 8 exhaust channel 9 Entrance 10 Inlet flap 11 Inlet channel 12 tailgate(s) 13 Magazine 14 Air pressure sensor 15 Compressor device 16 compressed air duct 17 Control unit 18 processor 19 Volatile memory 20 permanent storage 21 buses 22 Arbiters 23 interface(s) 24 Main power supply 25 Auxiliary power supply A Front top B Rear top C Bottom F Flight direction P pressure

Claims

[1] Stealth aircraft (1) with an aerodynamic and stealth-optimised airframe (2), the stealth aircraft (1) comprising: a delivery chute (3) arranged in the airframe (2) to prepare for the release of a load (4) to be released from the stealth aircraft (1) during flight operation of the stealth aircraft (1); an outlet (6) connecting the discharge duct (3) to a rear upper surface (B) of the airframe (2); a control unit (17) designed to control the outlet (6) in order to discharge the load (4) from the discharge shaft (3) via the outlet (6); and characterized by , that the outlet (6) is arranged on the airframe (2) to drop the load (4) over a side of the stealth aircraft (1) facing away from the earth's surface. [2] Stealth aircraft (1) according to claim 1, characterized by , that the stealth aircraft (1) further comprises an inlet (9) connecting the discharge duct (3) to a forward upper surface (A) of the airframe (2); and the inlet (9) on the airframe (2) is arranged and designed such that an air flow into the discharge duct (3) caused by the flight operation of the stealth aircraft (1), in the direction of flight (F) from the front, provides a pressure (P) which causes the load (4) to be pushed rearward in the direction of flight (F) through the outlet (6) in order to drop the load (4) over the top (B) of the airframe (2). [3] Stealth aircraft (1) according to claim 2, characterized by , that the inlet (9) has an inlet flap (10) which is designed to be operated in two operating positions, OPEN and CLOSED; the outlet (6) has an outlet flap (7) which is designed to be operated in the two operating positions, OPEN and CLOSED; the inlet (9) further comprises an inlet duct (11) providing a direct air supply connection from the inlet flap (10) to the discharge duct (3); and the outlet (6) further comprises an outlet duct (8) which provides a direct air discharge connection from the discharge duct (3) to the outlet flap (7). [4] Stealth aircraft (1) according to claim 3, characterized by that the inlet flap (10) and the outlet flap (7) are each aligned in the CLOSED operating position with the upper side (A, B) of the airframe (2), which is preferably an airframe or fuselage. [5] Stealth aircraft (1) according to claim 3 or 4, characterized by , that the stealth aircraft (1) further comprises one or more aircraft engines for propelling the stealth aircraft (1) in the air; and the exhaust flap (7) and the one or more aircraft engines on the airframe (2) are arranged relative to one another so that the load (4) remains unaffected by exhaust gases from the aircraft engine. [6] Stealth aircraft (1) according to one of claims 3 to 5, characterized by that the control unit (17) is designed to control the inlet (9) and the outlet (6) during flight operation of the stealth aircraft (1) for load shedding such that the outlet flap (7) and the inlet flap (10) are simultaneously in the OPEN operating position in order to drop the load (4) from the discharge chute (3) on the upper side (B) of the stealth aircraft (1) by means of an air flow through the inlet duct (11) caused by the flight operation in the direction from the inlet (9) to the outlet (6). [7] Stealth aircraft (1) according to one of claims 2 to 6, characterized by , that a) the pressure (P) is designed taking into account a sabot (5) attached to the load (4), and / or (b) the stealth aircraft (1) further comprises: an air pressure sensor (14) designed to measure the pressure (P) provided by the air flow into the discharge duct (3); a compressor device (15) designed to generate compressed air; and a compressed air duct (16) arranged between the compressor device (15) and the discharge duct (3), for discharging the generated compressed air into the discharge duct (3) and for supplying the discharge duct (3) with the compressed air; and the control unit (17) is further designed to set a pressure value of the compressor device (15) based on a difference between a target pressure value of the discharge shaft (3) and the measured pressure (P) of the discharge shaft (3), and the compressor device (15) is designed to generate the compressed air with the set pressure value. [8] Stealth aircraft (1) according to one of the preceding claims, characterized by , that the stealth aircraft (1) further comprises a cargo compartment with one or more loading flaps (12) arranged on an underside (C) of the airframe (2), which extend along a longitudinal axis of the stealth aircraft (1) and via which the load (4) to be dropped is to be loaded into the stealth aircraft (1); the stealth aircraft (1) further comprises a magazine (13) designed to rotatably or linearly store the load (4) to be dropped between the cargo compartment in which the load (4) is to be loaded and the discharge chute (3) from which the load (4) is to be released to the outlet (6); and the control unit (17) is designed to keep the one or more loading flaps (12) of the cargo hold closed during flight operations. [9] Method (S0) for operating a stealth aircraft (1) having an airframe (2) with an aerodynamic design and an integrated discharge chute (3), and a control unit (17), the method (S0) comprising: Providing (S1), by a magazine (13), a load (4) to be dropped in the delivery shaft (3), as long as navigation data provided to the control unit (17) do not indicate a target area for dropping the load (4); and Actuating (S2), by the control unit (17), an outlet (6), as soon as the navigation data indicate the target location area for dropping the load (4), in order to drop the load (4) from the discharge chute (3), by means of a pressure (P) in the discharge chute (3), over a side of the stealth aircraft (1) facing away from the earth's surface. [10] A computer program comprising instructions which, when the computer program is executed by a computer, cause the computer to execute or initiate the method (S0) according to claim 9 or steps (S1, S2) thereof.

Images