Design method and device of vertical take-off and landing aircraft and storage medium
By calculating the position of components and the trajectory of debris detachment based on lift, design parameters are updated to reduce the impact of debris, thus solving the safety problem caused by debris scattering in traditional vertical takeoff and landing aircraft and improving the safety of the aircraft.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- SHANGHAI VOLANTE AVIATION TECH CO LTD
- Filing Date
- 2026-01-04
- Publication Date
- 2026-04-24
AI Technical Summary
In traditional vertical takeoff and landing aircraft, debris scattered due to damage to lift-generating components can have catastrophic consequences for the fuselage and personnel and equipment, which is difficult to effectively avoid with existing designs.
By acquiring the location of the lift-providing components and the trajectory of debris fall, the affected area and probability are calculated, and the design parameters are updated to reduce the impact of debris until a safety threshold is reached to avoid cascading failure.
It improves the flight safety of vertical takeoff and landing aircraft, reduces catastrophic accidents caused by debris scattering, and enhances the safety of the system.
Smart Images
Figure CN121919989A_ABST
Abstract
Description
Technical Field
[0001] This disclosure relates to the field of aircraft technology, and in particular to a design method, apparatus and storage medium for a vertical take-off and landing aircraft. Background Technology
[0002] Vertical takeoff and landing (VTOL) aircraft, especially electric vertical takeoff and landing (eVTOL) aircraft, have become a key technological vehicle for solving low-altitude three-dimensional transportation problems. To achieve efficient vertical takeoff, landing, and hovering, VTOL aircraft typically include a fuselage and multiple lift-generating components distributed across the fuselage. These lift-generating components provide vertical propulsion during flight. This distributed design of multiple lift-generating components improves the reliability of VTOL aircraft and enables more flexible flight attitude control.
[0003] In the traditional design of vertical takeoff and landing aircraft, lift-providing components are usually densely distributed in designated locations on the fuselage according to a pre-defined layout.
[0004] However, with numerous lift-providing components densely distributed in space, if a component fails due to material fatigue, external impact, or system malfunction during high-speed rotation (e.g., blade breakage), the resulting high-speed debris (or component fragments) will scatter along a specific trajectory with enormous kinetic energy. These fragments are highly likely to strike other objects on the fuselage, such as other nearby, normally functioning lift-providing components and / or personnel and equipment in the cabin, potentially leading to catastrophic consequences for the vertical takeoff and landing (VTOL) aircraft. Therefore, optimizing the layout of lift-providing components and improving design during the design phase to avoid catastrophic consequences from component fragment scattering has become an urgent problem to be solved in improving the safety of VTOL aircraft. Summary of the Invention
[0005] In view of this, this disclosure proposes a design method, device and storage medium for a vertical take-off and landing aircraft, which can continuously update design parameters to reduce the impact of detached debris on the target object until the degree of impact does not reach the preset level, thereby improving the flight safety of the vertical take-off and landing aircraft.
[0006] According to one aspect of this disclosure, a design method for a vertical takeoff and landing (VTOL) aircraft is provided, the VTOL aircraft including a plurality of lift-providing components to provide lift during flight of the VTOL aircraft, the method comprising:
[0007] The component position of the target lift-providing component to be designed among the plurality of lift-providing components is obtained, as well as the debris detachment trajectory of the component fragments generated when the target lift-providing component is damaged;
[0008] Based on the location of the component and the trajectory of the debris, the affected area of the vertical takeoff and landing aircraft during the debris detachment process is determined.
[0009] If the affected area includes a target object other than other lift-providing components, the probability of the target object being affected is obtained; wherein, the other lift-providing components refer to the lift-providing components other than the target lift-providing component among the plurality of lift-providing components;
[0010] If the probability of the target object being affected is greater than or equal to the first probability threshold, then it is determined whether the degree of impact on the target object has reached a preset level.
[0011] If the degree of impact on the target object reaches the preset level, then the updated design parameters of the target lift-providing component are obtained so that the degree of impact on the target object does not reach the preset level.
[0012] In one possible implementation, the method further includes:
[0013] If the degree of impact on the target object does not reach the preset degree, then if the affected area also includes the other lift-providing components, the probability of the other lift-providing components being affected is obtained;
[0014] If the probability of other lift-providing components being affected is greater than or equal to the second probability threshold, the other lift-providing components are taken as the target lift-providing component, triggering the execution of the steps of obtaining the component position of the target lift-providing component to be designed among the plurality of lift-providing components, and the fragment detachment trajectory of the component fragments generated when the target lift-providing component is damaged, and subsequent steps.
[0015] In one possible implementation, the method further includes:
[0016] If the probability of the target object being affected is less than the first probability threshold, or the affected area does not include the other lift-providing components, or the probability of the other lift-providing components being affected is less than the second probability threshold, or the updated design parameters are obtained, then the lift-providing component that has not been designed among the plurality of lift-providing components is taken as the target lift-providing component, triggering the execution of the steps of obtaining the component position of the target lift-providing component to be designed among the plurality of lift-providing components, and the fragment detachment trajectory of the component fragments generated when the target lift-providing component is damaged, and subsequent steps, until all the plurality of lift-providing components are designed.
[0017] In one possible implementation, the probability of the target object being affected and the probability of the other lift-providing components being affected are calculated using the following formula:
[0018] P=P 损坏 × (θ / 360°) × (φ / 90°) × percentage of working time;
[0019] Wherein, P represents the probability that the target object or the other lift-providing component is affected; P 损坏 θ represents the probability of damage to the target lift-providing component; θ represents the angular range of the target object or the other lift-providing component affected by the target lift-providing component on the first plane; φ represents the angular range of the target object or the other lift-providing component affected by the target lift-providing component on the second plane; the first plane refers to a plane parallel to the horizontal plane, and the second plane is perpendicular to the second plane.
[0020] In one possible implementation, after obtaining the component position of the target lift-providing component to be designed among the plurality of lift-providing components, the method further includes:
[0021] The simulated flight process was obtained after the target lift-providing component was damaged;
[0022] If the simulated flight indicates that the vertical takeoff and landing aircraft has an undesirable consequence, updated design parameters of the target lift-providing component are obtained to prevent the vertical takeoff and landing aircraft from having the undesirable consequence.
[0023] In one possible implementation, obtaining the debris detachment trajectory of component fragments generated when the target lift-providing component fails includes:
[0024] Obtain fragment parameters of the component fragments in the target lift-providing component, wherein the fragment parameters include at least one of size information, center of mass information, and angle information;
[0025] Based on the correspondence between fragment parameters and fragment detachment trajectories, the fragment detachment trajectory corresponding to the fragment parameters is determined.
[0026] In one possible implementation, determining the affected area of the vertical takeoff and landing aircraft during the component debris detachment process, based on the component's location and the debris's trajectory, includes:
[0027] In the simulation model of the vertical takeoff and landing aircraft, the initial break-off position of the component fragment is determined based on the component's position;
[0028] The initial detachment location is used as the starting point of the debris detachment trajectory. Based on the area where the debris detachment trajectory intersects with the simulation model, the affected area is determined.
[0029] According to another aspect of this disclosure, a design apparatus for a vertical takeoff and landing aircraft is provided, including a memory, a processor, and a computer program stored in the memory, wherein the processor executes the computer program to implement the steps of the above-described method.
[0030] According to another aspect of this disclosure, a non-volatile computer-readable storage medium is provided, on which a computer program is stored, which, when executed by a processor, implements the steps of the above-described method.
[0031] According to another aspect of this disclosure, a computer program product is provided, including a computer program or a non-volatile computer-readable storage medium carrying the computer program, wherein the computer program, when executed by a processor, implements the steps of the above-described method.
[0032] By acquiring the component location of the target lift-providing component among multiple lift-providing components, and the debris detachment trajectory of the component fragments generated when the target lift-providing component fails; based on the component location and debris detachment trajectory, the affected area of the vertical take-off and landing aircraft during the component fragment detachment process is determined; if the affected area includes target objects other than other lift-providing components, the probability of the target objects being affected is obtained; if the probability of the target objects being affected is greater than or equal to a first probability threshold, it is determined whether the degree of impact on the target objects has reached a preset level; if the degree of impact on the target objects has reached the preset level, the updated design parameters of the target lift-providing component are obtained to ensure that the degree of impact on the target objects does not reach the preset level; this allows for continuous updating of design parameters to reduce the impact of some detached debris on the target objects until the degree of impact does not reach the preset level, thereby improving the flight safety of the vertical take-off and landing aircraft.
[0033] Other features and aspects of this disclosure will become clear from the following detailed description of exemplary embodiments with reference to the accompanying drawings. Attached Figure Description
[0034] The accompanying drawings, which are included in and form part of this specification, illustrate exemplary embodiments, features, and aspects of this disclosure together with the specification and serve to explain the principles of this disclosure.
[0035] Figure 1 A flowchart illustrating a design method for a vertical takeoff and landing aircraft according to an embodiment of the present disclosure is shown.
[0036] Figure 2 A schematic diagram showing the trajectory of debris breakage according to an embodiment of the present disclosure;
[0037] Figure 3 A top view of a simulated model of a vertical takeoff and landing aircraft according to an embodiment of the present disclosure is shown;
[0038] Figure 4 A side view of a simulated model of a vertical takeoff and landing aircraft according to an embodiment of the present disclosure is shown;
[0039] Figure 5 A flowchart illustrating a design method for a vertical takeoff and landing aircraft according to another embodiment of the present disclosure;
[0040] Figure 6 A block diagram showing a design apparatus for a vertical takeoff and landing aircraft according to an embodiment of the present disclosure;
[0041] Figure 7 A block diagram of a design apparatus for a vertical take-off and landing aircraft according to another embodiment of the present disclosure is shown. Detailed Implementation
[0042] Various exemplary embodiments, features, and aspects of this disclosure will now be described in detail with reference to the accompanying drawings. The same reference numerals in the drawings denote elements that have the same or similar functions. Although various aspects of the embodiments are shown in the drawings, they are not necessarily drawn to scale unless specifically indicated otherwise.
[0043] As used herein, the terms “comprising,” “including,” “having,” or variations thereof are open-ended and include one or more of the stated features, integrals, elements, steps, components, or functions, but do not exclude the presence or addition of one or more other features, integrals, elements, steps, components, functions, or groups thereof.
[0044] When an element is referred to as “connected,” “coupled,” “responding,” or a variation thereof relative to another element, it may be directly connected, coupled, or responding to another element, or there may be an intermediate element present.
[0045] Although the terms first, second, third, etc., may be used herein to describe various elements / operations, these elements / operations should not be limited by these terms. These terms are used only to distinguish one element / operation from another. Therefore, without departing from the teachings of this disclosure, a first element / operation in some embodiments may be referred to as a second element / operation in other embodiments.
[0046] The term “exemplary” as used herein means “serving as an example, embodiment, or illustration.” Any embodiment illustrated herein as “exemplary” is not necessarily to be construed as superior to or better than other embodiments.
[0047] Furthermore, to better illustrate this disclosure, numerous specific details are set forth in the following detailed description. Those skilled in the art will understand that this disclosure can be practiced without certain specific details. In some instances, methods, means, components, and circuits well known to those skilled in the art have not been described in detail in order to highlight the main points of this disclosure.
[0048] It should be noted that the information (including but not limited to user device information, user personal information, etc.), data (including but not limited to data used for analysis, data stored, data displayed, etc.) and signals involved in this application are all authorized by the user or fully authorized by all parties, and the collection, use and processing of related data must comply with the relevant laws, regulations and standards of the relevant regions.
[0049] Figure 1 A flowchart illustrating a design method for a vertical takeoff and landing (VTOL) aircraft according to an embodiment of this disclosure is provided. In this embodiment, the VTOL aircraft (i.e., the VTOL aircraft to be designed) includes multiple lift-providing components to provide lift during flight. Exemplarily, the lift-providing components may be rotors, which can be implemented as propellers. A rotor includes a hub and blades, wherein the hub drives the blades to move, and the blades, in their movement, cut through the air to generate force, thereby enabling the VTOL aircraft to move vertically. Optionally, this method is illustrated using an electronic device as an example. This electronic device includes, but is not limited to, user terminals or servers and other electronic devices with processing capabilities. The user terminal may be a computer, tablet computer, mobile phone, etc. This embodiment does not limit the implementation of the electronic device. Figure 1 As shown, the method includes:
[0050] Step 101: Obtain the component position of the target lift-providing component to be designed among multiple lift-providing components, and the debris detachment trajectory of the component fragments generated when the target lift-providing component is damaged.
[0051] In this embodiment, the electronic device stores component parameters of each component in the vertical takeoff and landing aircraft. These component parameters include at least the component position of each of the multiple lift-providing components. Optionally, the component position can be the location of the rotation center of the lift-providing component, such as the center of the rotor hub. In other embodiments, the component position can also be the tip position of the rotor blade, and / or the root position of the rotor blade, etc. This embodiment does not limit the implementation method of the component position.
[0052] In one example, the location of each lift-providing component is associated with a component identifier, which uniquely indicates the corresponding lift-providing component. This identifier can be a number of the lift-providing component; this embodiment does not limit the implementation of the component identifier. Accordingly, obtaining the location of the target lift-providing component includes: obtaining the component identifier of the target lift-providing component; and determining the component location associated with the component identifier of the target lift-providing component based on the association between the component location and the component identifier.
[0053] Optionally, the electronic device can obtain the component identifier of the target lift-providing component based on a human-computer interaction control; alternatively, the electronic device can use an undesigned lift-providing component as the target lift-providing component and obtain its component identifier. Here, an undesigned lift-providing component refers to a lift-providing component that has not undergone steps 101-105 in this embodiment to estimate the consequences of component fragmentation.
[0054] In other embodiments, the electronic device may directly obtain the component position of the target lift-providing component without determining the component position through component identification. For example, the electronic device may obtain the component position of the target lift-providing component based on human-computer interaction controls; or, the electronic device may use an undesigned lift-providing component as the target lift-providing component and obtain the component position of the target lift-providing component. This embodiment does not limit the method of obtaining the component position.
[0055] Component debris refers to a part of the target lift-providing component, such as a part of a rotor blade. In one example, the trajectory of the debris fragments generated when the target lift-providing component fails includes:
[0056] Obtain the fragment parameters of the component fragments in the target lift-providing component; based on the correspondence between the fragment parameters and the fragment detachment trajectory, determine the fragment detachment trajectory corresponding to the fragment parameters.
[0057] The fragment parameters include at least one of size information, center of mass information, and angle information. Size information indicates the size, shape, and spatial distribution of the component fragment. For example, size information includes at least one of the following: the perimeter, surface area, maximum or minimum size in all directions, thickness, volume, etc. This embodiment does not limit the implementation method of the size information. Center of mass information indicates the mass distribution of the component fragment. For example, center of mass information includes the position of the center of mass of the component fragment. Angle information indicates the initial flight direction of the component fragment at the moment of separation from the lift-providing component. For example, angle information includes, but is not limited to, the angle between the plane containing the component fragment and the plane of rotation containing the target lift-providing component.
[0058] For example, obtaining fragment parameters of component fragments in a target lift-providing component includes: receiving user-defined fragment parameters through a human-machine interface; or, an electronic device determining fragment parameters of component fragments from a preset fragment template, wherein the fragment template includes multiple component fragments and fragment parameters for each component fragment.
[0059] Optionally, the component fragments of the target lift providing component may be one or at least two. This embodiment does not limit the number of component fragments for each target lift providing component.
[0060] Optionally, the electronic device stores a correspondence between fragment parameters and fragment detachment trajectories. This correspondence can be the motion equation of the component fragment, and the fragment detachment trajectory corresponding to the component fragment can be obtained by substituting the fragment parameter into the motion equation; or, the correspondence can be the correspondence between the fragment parameters of each component fragment in the fragment template and the preset fragment detachment trajectory. In this way, after selecting a fragment parameter from the fragment template, the fragment detachment trajectory corresponding to that fragment parameter can be obtained.
[0061] For example, taking a fragment as an example of a rotor blade, refer to... Figure 2 The trajectory of the debris breakoff shown is based on Figure 2 It can be seen that the fragment parameters indicate that the centroid of some fragments is located between the hub (the end connecting the blade and the hub) and the tip of the blade, and the ratio of the distance between the centroid and the hub to the distance between the hub and the tip is 34%. The fragment trajectory corresponding to these parameters is as follows: Figure 2 The spiral trajectory in the image, the path of motion of the spiral trajectory around the center of mass (i.e. Figure 2 The path is formed by the bold black line in the image.
[0062] Step 102: Based on the component location and debris detachment trajectory, determine the affected area of the vertical take-off and landing aircraft during the component debris detachment process.
[0063] In one example, based on the component location and debris detachment trajectory, the affected area of the vertical takeoff and landing aircraft during component debris detachment is determined, including:
[0064] In the simulation model of the vertical takeoff and landing aircraft, the initial detachment position of the component fragment is determined based on the component location; the initial detachment position is used as the starting position of the fragment detachment trajectory, and the affected area is determined based on the area where the fragment detachment trajectory intersects with the simulation model.
[0065] The electronic device stores a simulation model of the vertical takeoff and landing (VTOL) aircraft. This simulation model is a geometric model of the VTOL aircraft, and the model parameters of each component in the VTOL aircraft, as indicated by the simulation model, match the actual parameters of that component. Optionally, the simulation model can be manually drawn and stored in the electronic device, or it can be constructed by the electronic device based on the actual parameters of the components. This embodiment does not limit the method of establishing the simulation model.
[0066] In one example, determining the initial detachment location of a component fragment based on its location includes: obtaining the detachment point of the component fragment when it detaches from the component provided by the target lift force; determining the location of the detachment point based on the relative positional relationship between the detachment point and the component location; and obtaining the initial detachment location.
[0067] For example: a top-view reference of a simulation model of a vertical takeoff and landing aircraft. Figure 3 As shown, assuming the initial detachment location is the center of rotation on the target lift-providing component 31, the area where the debris detachment trajectory determined by this center of rotation intersects with the simulation model is considered as... Figure 3 The arc-shaped area formed by the thickened lines is the affected area.
[0068] Step 103: If the affected area includes target objects other than other lift-providing components, obtain the probability of the target objects being affected.
[0069] Other lift-providing components refer to lift-providing components other than the target lift-providing component among multiple lift-providing components.
[0070] The target object refers to the object that the vertical takeoff and landing (VTOL) aircraft must not be affected by component debris during flight. The target object is different from the lift-providing component. Optionally, the target object can be personnel or equipment within the VTOL aircraft, etc. This embodiment does not limit the implementation method of the target object.
[0071] The sum of the probabilities of the target object being affected is calculated using the following formula:
[0072] P=P 损坏 × (θ / 360°) × (φ / 90°) × percentage of working time;
[0073] Where P represents the probability that the target object will be affected; P 损坏 θ represents the probability of damage to the target lift-providing component; θ represents the angular range of the target object affected by the target lift-providing component on the first plane, i.e., the maximum angular range of the target object facing the target lift-providing component; φ represents the angular range of the target object affected by the target lift-providing component on the second plane, i.e., the angle between the plane containing the target object in the direction horizontal to the first plane and the plane containing the target lift-providing component in the direction horizontal to the first plane; in this embodiment, since the force direction on the lift-providing component is vertically upward to counteract gravity during both vertical takeoff and vertical landing, i.e., the lift-providing component will only fly upward, therefore, in this embodiment, the analysis range of φ is the angular range of 0° to ±90°. The first plane refers to a plane parallel to the horizontal plane, and the second plane is perpendicular to the second plane. The working time percentage refers to the ratio of the working time of the target lift-providing component to the total flight time.
[0074] In this embodiment, the probability of damage to the target lift-providing component is pre-stored in the electronic device. Optionally, since the probability of damage to the target lift-providing component may vary in different working environments, the electronic device can obtain the correspondence between the working environment and the probability of damage. Based on the probability of damage corresponding to each working environment, the maximum value among the affected probabilities for each working environment is determined, and this maximum value is taken as P. 损坏 To determine the probability of the target object being affected and the probability of other lift-providing components being affected.
[0075] Step 104: If the probability of the target object being affected is greater than or equal to the first probability threshold, then determine whether the degree of impact on the target object has reached the preset level.
[0076] The first probability threshold is pre-stored in the electronic device. For example, the first probability threshold could be a probability of 10 per hour of flight. -8 In other embodiments, the value of the first probability threshold may be other values, and this embodiment does not limit the value of the first probability threshold.
[0077] Determining whether the impact on the target object reaches a preset level includes: obtaining the simulated flight process after the target object is affected; determining whether the impact on the target object reaches a preset level if the simulated flight process indicates that the vertical take-off and landing aircraft has experienced undesirable consequences; and determining whether the impact on the target object has not reached a preset level if the simulated flight process indicates that the vertical take-off and landing aircraft has not experienced undesirable consequences.
[0078] Electronic devices use simulation programs to create dynamic models of vertical takeoff and landing (VTOL) aircraft to simulate the actual flight process of VTOL aircraft. In the simulation program, target objects are set to be affected, such as the pilot's hands or equipment damage, so that the corresponding simulated flight process can be obtained.
[0079] Undesirable consequences can refer to catastrophic consequences, that is, consequences that result in multiple deaths, usually accompanied by the loss of the aircraft, involving the complete loss of flight safety, such as extreme situations like aircraft disintegration or crash. In other embodiments, undesirable consequences can also refer to consequences that reduce safety margins and may lead to accidents. This embodiment does not limit the way undesirable consequences are implemented.
[0080] Step 105: If the degree of impact on the target object reaches a preset level, then obtain the updated design parameters of the target lift-providing component so that the degree of impact on the target object does not reach the preset level.
[0081] The design parameters of the target lift-providing component include, but are not limited to: component position, component size, component shape, and distance from adjacent lift-providing components. This embodiment does not limit the implementation method of the design parameters of the target lift-providing component.
[0082] In this embodiment, by continuously updating the design parameters to reduce the impact of some detached fragments on the target object until the degree of impact does not reach the preset level, the flight safety of the vertical take-off and landing aircraft can be improved.
[0083] Since the affected area may also include other lift-providing components, if debris from the target lift-providing component strikes other lift-providing components, the struck component may be damaged, lose balance, or even disintegrate instantly, generating new debris that further threatens distant lift-providing components and the target object. This phenomenon, where an initial failure of a single lift-providing component triggers the subsequent failure of multiple adjacent components, is called a "cascading failure." Cascading failures drastically amplify the consequences of a single failure, and in severe cases, may cause the aircraft to lose most or even all of its lift, resulting in a catastrophic accident.
[0084] Based on this, in this embodiment, reference Figure 5 Following step 104, the design method for vertical takeoff and landing aircraft further includes:
[0085] Step 51: If the degree of impact on the target object does not reach the preset level, then if other lift-providing components are also included in the affected area, obtain the probability of other lift-providing components being affected.
[0086] The probability of other lift-providing components being affected is calculated in the same way as the probability of the target object being affected, that is, it can be expressed by the following formula:
[0087] P=P 损坏 × (θ / 360°) × (φ / 90°) × percentage of working time;
[0088] Where P represents the probability that other lift-providing components will be affected; P 损坏 θ represents the probability of damage to the target lift-providing component; θ represents the angular range of influence of the target object or other lift-providing components on the first plane by the target lift-providing component; φ represents the angular range of influence of other lift-providing components on the second plane by the target lift-providing component; the first plane refers to a plane parallel to the horizontal plane, and the second plane is perpendicular to the second plane. For detailed descriptions, please refer to the above embodiments, which will not be repeated here.
[0089] for example: Figure 3 The affected area includes other lift-providing components 32, 33, and 35. Therefore, the affected angle range on the first plane based on the other lift-providing component 32 is θ1, and the affected angle range on the second plane is referenced. Figure 4 In the side view of the simulation model shown, φ1 represents the influence of other lift-providing components. By setting θ=θ1 and φ=φ1 in the expression for the probability of influence of these other lift-providing components, the probability of influence of other lift-providing components 32 can be calculated. Similarly, the influence angle range of other lift-providing components 33 on the first plane is θ2, and the influence angle range on the second plane is φ2. Figure 4 (Not shown in the image), by setting θ=θ2 and φ=φ2 in the expression for the affected probability of the other lift-providing components, the affected probability of the other lift-providing components 33 can be calculated. The affected angle range of the other lift-providing components 35 on the first plane is θ3, and the affected angle range on the second plane is φ3 (not shown in the image). Figure 4 (not shown in the figure) By setting θ=θ3 and φ=φ3 in the expression for the probability of other lift-providing components being affected, the probability of other lift-providing components 35 being affected can be calculated.
[0090] Optionally, in step 103, if the affected area does not include the target object, the step of "obtaining the probability of other lift-providing components being affected if the affected area also includes other lift-providing components" can be triggered; if the affected area does not include the target object and other lift-providing components, the lift-providing component that has not been designed among the multiple lift-providing components is taken as the target lift-providing component, and the step of obtaining the component position of the target lift-providing component to be designed among the multiple lift-providing components, as well as the fragment detachment trajectory of the component fragments generated when the target lift-providing component is damaged (i.e., step 101) and subsequent steps are triggered until all multiple lift-providing components are designed.
[0091] Step 52: If the probability of other lift-providing components being affected is greater than or equal to the second probability threshold, other lift-providing components are used as target lift-providing components, triggering the execution of the steps (i.e., step 101) and subsequent steps to obtain the component position of the target lift-providing component to be designed among multiple lift-providing components and the fragment detachment trajectory of component fragments generated when the target lift-providing component is damaged.
[0092] Optionally, the second probability threshold may be the same as or different from the first probability threshold. This embodiment does not limit the value of the second probability threshold.
[0093] for example: Figure 3 If the probability of other lift-providing components 32 being affected is greater than or equal to the second probability threshold, then the other lift-providing components 32 are designated as the target lift-providing components, triggering the execution of step 101. At this time, the target lift-providing component in step 105 may include the initially determined target lift-providing component and the target lift-providing component that was originally another lift-providing component, or it may only include the initially determined target lift-providing component or the target lift-providing component that was originally another lift-providing component. This embodiment does not limit the implementation method of the target lift-providing component for updating design parameters in step 105.
[0094] Step 53: If the probability of the target object being affected is less than the first probability threshold, or the affected area does not include other lift-providing components, or the probability of other lift-providing components being affected is less than the second probability threshold, or updated design parameters are obtained, then the lift-providing component that has not been designed among the multiple lift-providing components is taken as the target lift-providing component. This triggers the execution of the steps to obtain the component position of the target lift-providing component to be designed among the multiple lift-providing components, as well as the fragment detachment trajectory of the component fragments generated when the target lift-providing component is damaged, and subsequent steps, until all multiple lift-providing components are designed and the process ends.
[0095] In this embodiment, when the affected area also includes other lift-providing components, the probability of these other components being affected is obtained. If the probability of these other lift-providing components being affected is greater than or equal to a second probability threshold, these other lift-providing components are used as target lift-providing components, and it is further determined whether the degree of impact on the target object reaches a preset level. It can be determined whether the initially damaged component fragments will lead to cascading failures. In the event of cascading failures, the design parameters of the lift-providing components can be optimized to avoid cascading failures and further improve the safety of the vertical take-off and landing aircraft.
[0096] Optionally, since the lift-providing components of a target that initially fail may themselves cause undesirable consequences for the vertical takeoff and landing aircraft, therefore, reference Figure 5After step 101 (i.e., after obtaining the component position of the target lift-providing component to be designed among multiple lift-providing components), it may further include:
[0097] Step 54: Obtain the simulated flight process after the target lift-providing component is damaged.
[0098] Electronic equipment uses simulation programs to establish dynamic models of vertical takeoff and landing (VTOL) aircraft to simulate the actual flight process of VTOL aircraft. In the simulation program, the target lift-providing component is set to be damaged. Specifically, the component fragments with the fragment parameters obtained above are set to fall off from the target lift-providing component, and the corresponding simulated flight process can be obtained.
[0099] Step 55: If the simulated flight indicates that the vertical takeoff and landing aircraft has an undesirable consequence, obtain the updated design parameters of the target lift-providing components to ensure that the vertical takeoff and landing aircraft does not have an undesirable consequence, and then proceed to step 53.
[0100] For details regarding the undesirable consequences, please refer to the above text; this embodiment will not repeat them here.
[0101] In this embodiment, when the target lift-providing component is determined to be damaged, the simulated flight process after the damage to the target lift-providing component is obtained. If the simulated flight process indicates that the vertical take-off and landing aircraft will have undesirable consequences, the updated design parameters of the target lift-providing component are obtained so that the vertical take-off and landing aircraft will not have undesirable consequences. This can avoid undesirable consequences directly caused by component fragment damage and ensure the safety of the vertical take-off and landing aircraft.
[0102] Figure 6 This diagram shows a block diagram of a design apparatus for a vertical takeoff and landing (VTOL) aircraft according to an embodiment of the present disclosure. The VTOL aircraft includes a plurality of lift-providing components to provide lift during flight, such as... Figure 6 As shown, the device includes: a data acquisition module 610, a region determination module 620, a probability determination module 630, a degree determination module 640, and a parameter update module 650.
[0103] The data acquisition module 610 is used to acquire the component position of the target lift-providing component to be designed among the plurality of lift-providing components, and the fragment detachment trajectory of the component fragments generated when the target lift-providing component is damaged;
[0104] The area determination module 620 is used to determine the affected area of the vertical take-off and landing aircraft during the component debris detachment process based on the component location and the debris detachment trajectory;
[0105] The probability determination module 630 is used to obtain the probability of the target object being affected when the affected area includes a target object other than other lift-providing components; wherein, the other lift-providing components refer to the lift-providing components other than the target lift-providing component among the plurality of lift-providing components;
[0106] The degree determination module 640 is used to determine whether the degree of influence of the target object has reached a preset degree if the probability of the target object being affected is greater than or equal to a first probability threshold.
[0107] The parameter update module 650 is used to obtain the updated design parameters of the target lift-providing component if the degree of influence on the target object reaches the preset degree, so that the degree of influence on the target object does not reach the preset degree.
[0108] Optionally, the probability determination module 630 is further configured to obtain the probability of other lift-providing components being affected if the degree of impact on the target object does not reach the preset degree, and if the affected area also includes other lift-providing components;
[0109] The data acquisition module 610 is further configured to, when the probability of other lifting components being affected is greater than or equal to a second probability threshold, use the other lifting components as the target lifting component, trigger the execution of the steps of acquiring the component position of the target lifting component to be designed among the plurality of lifting components, and the fragment detachment trajectory of the component fragments generated when the target lifting component is damaged, and subsequent steps.
[0110] Optionally, the data acquisition module 610 is further configured to:
[0111] If the probability of the target object being affected is less than the first probability threshold, or the affected area does not include the other lift-providing components, or the probability of the other lift-providing components being affected is less than the second probability threshold, or the updated design parameters are obtained, then the lift-providing component that has not been designed among the plurality of lift-providing components is taken as the target lift-providing component, triggering the execution of the steps of obtaining the component position of the target lift-providing component to be designed among the plurality of lift-providing components, and the fragment detachment trajectory of the component fragments generated when the target lift-providing component is damaged, and subsequent steps, until all the plurality of lift-providing components are designed.
[0112] Optionally, the probability of the target object being affected and the probability of the other lift-providing components being affected are calculated using the following formula:
[0113] P=P 损坏× (θ / 360°) × (φ / 90°) × percentage of working time;
[0114] Wherein, P represents the probability that the target object or the other lift-providing component is affected; P 损坏 θ represents the probability of damage to the target lift-providing component; θ represents the angular range of the target object or the other lift-providing component affected by the target lift-providing component on the first plane; φ represents the angular range of the target object or the other lift-providing component affected by the target lift-providing component on the second plane; the first plane refers to a plane parallel to the horizontal plane, and the second plane is perpendicular to the second plane.
[0115] Optionally, the device further includes: a flight simulation module;
[0116] The flight simulation module is used to obtain the simulated flight process after the target lift-providing component to be designed is damaged, after obtaining the component position among the plurality of lift-providing components;
[0117] The parameter update module 650 is further configured to obtain updated design parameters of the target lift-providing component when the simulated flight process indicates that the vertical take-off and landing aircraft has an undesirable consequence, so as to prevent the vertical take-off and landing aircraft from having the undesirable consequence.
[0118] Optionally, the data acquisition module 610 is used for:
[0119] Obtain fragment parameters of the component fragments in the target lift-providing component, wherein the fragment parameters include at least one of size information, center of mass information, and angle information;
[0120] Based on the correspondence between fragment parameters and fragment detachment trajectories, the fragment detachment trajectory corresponding to the fragment parameters is determined.
[0121] Optionally, the region determination module 620 is used for:
[0122] In the simulation model of the vertical takeoff and landing aircraft, the initial break-off position of the component fragment is determined based on the component's position;
[0123] The initial detachment location is used as the starting point of the debris detachment trajectory. Based on the area where the debris detachment trajectory intersects with the simulation model, the affected area is determined.
[0124] For details, please refer to the above method implementation examples.
[0125] In some embodiments, the functions or modules of the apparatus provided in this disclosure can be used to perform the methods described in the above method embodiments. The specific implementation can be referred to the description of the above method embodiments, and for the sake of brevity, it will not be repeated here.
[0126] This disclosure also provides a design apparatus for a vertical takeoff and landing aircraft, including a memory, a processor, and a computer program stored in the memory, wherein the processor executes the computer program to implement the steps of the above method.
[0127] This disclosure also provides a non-volatile computer-readable storage medium storing a computer program thereon, which, when executed by a processor, implements the steps of the above-described method.
[0128] This disclosure also provides a computer program product, including a computer program or a non-volatile computer-readable storage medium carrying the computer program, wherein the computer program, when executed by a processor, implements the steps of the above method.
[0129] Figure 7 This is a block diagram illustrating a design apparatus 1900 for a vertical takeoff and landing (VTOL) aircraft according to an exemplary embodiment. For example, apparatus 1900 may be provided as a server or terminal device. (Refer to...) Figure 7 The apparatus 1900 includes a processing component 1922, which further includes one or more processors, and memory resources represented by memory 1932 for storing instructions, such as application programs, that can be executed by the processing component 1922. The application programs stored in memory 1932 may include one or more modules, each corresponding to a set of instructions. Furthermore, the processing component 1922 is configured to execute instructions to perform the methods described above.
[0130] Device 1900 may also include a power supply component 1926 configured to perform power management of device 1900, a wired or wireless network interface 1950 configured to connect device 1900 to a network, and an input / output interface 1958 (I / O interface). Device 1900 can operate on an operating system, such as Windows Server, stored in memory 1932. TM macOS X TM Unix TM Linux TM FreeBSD TM Or similar.
[0131] In an exemplary embodiment, a non-volatile computer-readable storage medium is also provided, such as a memory 1932 including computer program instructions that can be executed by a processing component 1922 of the device 1900 to perform the above-described method.
[0132] Computer-readable storage media can be tangible devices capable of holding and storing programs / instructions used by instruction execution devices. Computer-readable storage media can be, for example—but not limited to—electrical storage devices, magnetic storage devices, optical storage devices, electromagnetic storage devices, semiconductor storage devices, or any suitable combination of the foregoing. More specific examples (a non-exhaustive list) of computer-readable storage media include: portable computer disks, hard disks, random access memory (RAM), read-only memory (ROM), erasable programmable read-only memory (EPROM or flash memory), static random access memory (SRAM), portable compact disc read-only memory (CD-ROM), digital multifunction disc (DVD), memory sticks, floppy disks, mechanical encoding devices, such as punch cards or recessed protrusions storing instructions thereon, and any suitable combination of the foregoing. The computer-readable storage media used herein are not to be construed as transient signals themselves, such as radio waves or other freely propagating electromagnetic waves, electromagnetic waves propagating through waveguides or other transmission media (e.g., light pulses through fiber optic cables), or electrical signals transmitted through wires.
[0133] The computer program (or computer-readable program instructions) described herein can be downloaded from a computer-readable storage medium to various computing / processing devices, or downloaded via a network, such as the Internet, local area network, wide area network, and / or wireless network, to an external computer or external storage device. The network may include copper transmission cables, fiber optic transmission, wireless transmission, routers, firewalls, switches, gateway computers, and / or edge servers. A network adapter card or network interface in each computing / processing device receives the computer-readable program instructions from the network and forwards them to the computer-readable storage medium in the respective computing / processing device.
[0134] The computer program (or computer program instructions) used to perform the operations of this disclosure may be assembly instructions, instruction set architecture (ISA) instructions, machine instructions, machine-dependent instructions, microcode, firmware instructions, state setting data, or source code or object code written in any combination of one or more programming languages, including object-oriented programming languages such as Smalltalk, C++, etc., and conventional procedural programming languages such as the "C" language or similar programming languages. The computer-readable program instructions may execute entirely on the user's computer, partially on the user's computer, as a standalone software package, partially on the user's computer and partially on a remote computer, or entirely on a remote computer or server. In cases involving a remote computer, the remote computer may be connected to the user's computer via any type of network—including a local area network (LAN) or a wide area network (WAN)—or may be connected to an external computer (e.g., via the Internet using an Internet service provider). In some embodiments, electronic circuitry, such as programmable logic circuitry, field-programmable gate arrays (FPGAs), or programmable logic arrays (PLAs), is personalized by utilizing state information from the computer-readable program instructions to implement various aspects of this disclosure.
[0135] Various aspects of this disclosure are described herein with reference to flowchart illustrations and / or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of this disclosure. It should be understood that each block of the flowchart illustrations and / or block diagrams, and combinations of blocks in the flowchart illustrations and / or block diagrams, can be implemented by computer-readable program instructions.
[0136] These computer-readable program instructions can be provided to a processor of a general-purpose computer, a special-purpose computer, or other programmable data processing apparatus to produce a machine such that, when executed by the processor of the computer or other programmable data processing apparatus, they create means for implementing the functions / actions specified in one or more blocks of the flowchart and / or block diagram. These computer-readable program instructions can also be stored in a computer-readable storage medium that causes a computer, programmable data processing apparatus, and / or other device to operate in a particular manner; thus, the computer-readable medium storing the instructions comprises an article of manufacture that includes instructions for implementing aspects of the functions / actions specified in one or more blocks of the flowchart and / or block diagram.
[0137] Computer-readable program instructions may also be loaded onto a computer, other programmable data processing apparatus, or other device to cause a series of operational steps to be performed on the computer, other programmable data processing apparatus, or other device to produce a computer-implemented process, thereby causing the instructions executed on the computer, other programmable data processing apparatus, or other device to perform the functions / actions specified in one or more boxes of a flowchart and / or block diagram.
[0138] The flowcharts and block diagrams in the accompanying drawings illustrate the architecture, functionality, and operation of possible implementations of systems, methods, and computer program products according to various embodiments of the present disclosure. In this regard, each block in a flowchart or block diagram may represent a module, segment, or portion of an instruction containing one or more executable instructions for implementing a specified logical function. In some alternative implementations, the functions marked in the blocks may occur in a different order than those shown in the drawings. For example, two consecutive blocks may actually be executed substantially in parallel, and they may sometimes be executed in reverse order, depending on the functions involved. It should also be noted that each block in the block diagrams and / or flowcharts, and combinations of blocks in the block diagrams and / or flowcharts, may be implemented using a dedicated hardware-based system that performs the specified function or action, or using a combination of dedicated hardware and computer instructions.
[0139] The various embodiments of this disclosure have been described above. These descriptions are exemplary and not exhaustive, nor are they limited to the disclosed embodiments. Many modifications and variations will be apparent to those skilled in the art without departing from the scope and spirit of the described embodiments. The terminology used herein is chosen to best explain the principles, practical application, or technical improvements to the embodiments in the market, or to enable others skilled in the art to understand the embodiments disclosed herein.
Claims
1. A design method for a vertical takeoff and landing aircraft, characterized in that, The vertical takeoff and landing (VTOL) aircraft includes multiple lift-providing components to provide lift during flight of the VTOL aircraft, the method comprising: The component position of the target lift-providing component to be designed among the plurality of lift-providing components is obtained, as well as the debris detachment trajectory of the component fragments generated when the target lift-providing component is damaged; Based on the location of the component and the trajectory of the debris, the affected area of the vertical takeoff and landing aircraft during the debris detachment process is determined. If the affected area includes a target object other than other lift-providing components, the probability of the target object being affected is obtained; wherein, the other lift-providing components refer to the lift-providing components other than the target lift-providing component among the plurality of lift-providing components; If the probability of the target object being affected is greater than or equal to the first probability threshold, then it is determined whether the degree of impact on the target object has reached a preset level. If the degree of impact on the target object reaches the preset level, then the updated design parameters of the target lift-providing component are obtained so that the degree of impact on the target object does not reach the preset level.
2. The method according to claim 1, characterized in that, The method further includes: If the degree of impact on the target object does not reach the preset degree, then if the affected area also includes the other lift-providing components, the probability of the other lift-providing components being affected is obtained; If the probability of other lift-providing components being affected is greater than or equal to the second probability threshold, the other lift-providing components are taken as the target lift-providing component, triggering the execution of the steps of obtaining the component position of the target lift-providing component to be designed among the plurality of lift-providing components, and the fragment detachment trajectory of the component fragments generated when the target lift-providing component is damaged, and subsequent steps.
3. The method according to claim 2, characterized in that, The method further includes: If the probability of the target object being affected is less than the first probability threshold, or the affected area does not include the other lift-providing components, or the probability of the other lift-providing components being affected is less than the second probability threshold, or the updated design parameters are obtained, then the lift-providing component that has not been designed among the plurality of lift-providing components is taken as the target lift-providing component, triggering the execution of the steps of obtaining the component position of the target lift-providing component to be designed among the plurality of lift-providing components, and the fragment detachment trajectory of the component fragments generated when the target lift-providing component is damaged, and subsequent steps, until all the plurality of lift-providing components are designed.
4. The method according to claim 1 or 2, characterized in that, The probability of the target object being affected and the probability of the other lift-providing components being affected are calculated using the following formula: P=P 损坏 × (θ / 360°) × (φ / 90°) × percentage of working time; Wherein, P represents the probability that the target object or the other lift-providing component is affected; P 损坏 θ represents the probability of damage to the target lift-providing component; θ represents the angular range of the target object or the other lift-providing component affected by the target lift-providing component on the first plane; φ represents the angular range of the target object or the other lift-providing component affected by the target lift-providing component on the second plane; the first plane refers to a plane parallel to the horizontal plane, and the second plane is perpendicular to the second plane.
5. The method according to claim 1, characterized in that, After obtaining the component position of the target lift-providing component to be designed among the plurality of lift-providing components, the method further includes: The simulated flight process was obtained after the target lift-providing component was damaged; If the simulated flight indicates that the vertical takeoff and landing aircraft is experiencing an undesirable consequence, updated design parameters of the target lift-providing component are obtained to prevent the vertical takeoff and landing aircraft from experiencing the undesirable consequence.
6. The method according to claim 1, characterized in that, Acquiring the debris detachment trajectory of component fragments generated when the target lift-providing component fails includes: Obtain fragment parameters of the component fragments in the target lift-providing component, wherein the fragment parameters include at least one of size information, center of mass information, and angle information; Based on the correspondence between fragment parameters and fragment detachment trajectories, the fragment detachment trajectory corresponding to the fragment parameters is determined.
7. The method according to claim 1, characterized in that, The determination of the affected area of the vertical takeoff and landing aircraft during the debris detachment process, based on the component's location and the debris's trajectory, includes: In the simulation model of the vertical takeoff and landing aircraft, the initial break-off position of the component fragment is determined based on the component's position; The initial detachment location is used as the starting point of the debris detachment trajectory. Based on the area where the debris detachment trajectory intersects with the simulation model, the affected area is determined.
8. A design apparatus for a vertical takeoff and landing aircraft, comprising a memory, a processor, and a computer program stored in the memory, characterized in that, The processor executes the computer program to implement the steps of the method according to any one of claims 1 to 7.
9. A non-volatile computer-readable storage medium having a computer program stored thereon, characterized in that, When the computer program is executed by a processor, it implements the steps of the method according to any one of claims 1 to 7.
10. A computer program product comprising a computer program, or a non-volatile computer-readable storage medium carrying a computer program, characterized in that, When the computer program is executed by a processor, it implements the steps of the method according to any one of claims 1 to 7.