A method, device, and storage medium for takeoff and landing control of aircraft cargo hold and support structure.
By flexibly configuring battery modules as cargo holds or supports on unmanned aerial vehicles, the limitations of cargo carrying capacity and range have been solved, enabling efficient logistics operations for aircraft.
Patent Information
- Application Number
- CN202310296673.5
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- Filing Date
- 2023-03-23
- Publication Date
- 2026-01-30
- Estimated Expiration
- 2043-03-23
AI Technical Summary
Existing unmanned aerial vehicles (UAVs) face stringent limitations in cargo carrying capacity during logistics operations due to constraints on takeoff and landing environments and range.
By acquiring cargo data, power consumption data, and landing environment data before aircraft takeoff, the number of battery modules can be calculated and configured. The battery modules can be flexibly converted into cargo holds during takeoff and support structures during landing.
It has improved the aircraft's cargo capacity and range, and enhanced the timeliness of logistics.
Smart Images
Figure CN116280337B_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of unmanned aerial vehicle technology, and in particular to a method, device, and computer-readable storage medium for controlling the takeoff and landing of an aircraft cargo hold and support structure. Background Technology
[0002] In the current technology, with the continuous development of unmanned aerial vehicle (UAV) technology, logistics applications based on UAVs and other unmanned aerial vehicles are becoming increasingly popular. However, due to the limitations of the take-off and landing environment and endurance of UAVs, their cargo capacity is subject to relatively stringent restrictions.
[0003] Therefore, how to effectively improve the endurance and cargo capacity of unmanned aerial vehicles during logistics operations has become an urgent technical problem to be solved. Summary of the Invention
[0004] To address the aforementioned technical deficiencies in the prior art, this invention proposes a landing control method for aircraft cargo hold and support structures, the method comprising:
[0005] Before the aircraft takes off, acquire data on the cargo to be transported, the estimated power consumption for the current flight, and the landing environment at the destination.
[0006] The first configuration quantity, the second configuration quantity, and the third configuration quantity of battery modules are determined based on the cargo data, the power consumption data, and the landing environment, respectively.
[0007] The required fourth configuration quantity of battery modules is calculated based on the first configuration quantity, the second configuration quantity, and the third configuration quantity.
[0008] When the aircraft takes off, a portion of the battery modules in the fourth configuration form a cargo hold for loading goods, and when the aircraft lands, a portion of the battery modules in the fourth configuration form a landing support.
[0009] Optionally, acquiring data on the cargo to be transported, the estimated power consumption data for the current flight, and the landing environment at the destination before aircraft takeoff includes:
[0010] Obtain the cargo weight and cargo dimensions from the cargo data;
[0011] The power consumption data is calculated based on the weight of the cargo, the weight of the aircraft, and the flight range data, and the landing range of the destination is calculated based on the dimensions of the cargo, the dimensions of the aircraft, and the terrain features of the destination.
[0012] Optionally, determining the first, second, and third configuration quantities of battery modules based on the cargo data, the power consumption data, and the landing environment includes:
[0013] Obtain the module power and module size of the battery module;
[0014] Based on the module's power and size, the first configuration number of battery modules for loading cargo is calculated, the second configuration number of battery modules for providing extended battery power is calculated, and the third configuration number of battery modules for assembling the support frame is calculated.
[0015] Optionally, the step of calculating the currently required fourth configuration quantity of battery modules based on the first configuration quantity, the second configuration quantity, and the third configuration quantity includes:
[0016] When the sum of the first configuration quantity and the third configuration quantity is less than the second configuration quantity, a first preset quantity is added to the second configuration quantity as the fourth configuration quantity, wherein the fourth configuration quantity is greater than the first configuration quantity and the third configuration quantity;
[0017] When the sum of the first configuration quantity and the third configuration quantity is greater than or equal to the second configuration quantity, a second preset quantity is reduced from the second configuration quantity to form the fourth configuration quantity, wherein the fourth configuration quantity is greater than the first configuration quantity and the third configuration quantity.
[0018] Optionally, during aircraft takeoff, a portion of the battery modules in the fourth configuration form a cargo hold for loading goods, and during aircraft landing, a portion of the battery modules in the fourth configuration form a landing support, comprising:
[0019] Before the aircraft takes off, a portion of the battery modules in the fourth configuration are assembled into a takeoff support. After the aircraft takes off, a portion of the battery modules in the takeoff support are transferred to the cargo hold.
[0020] Before the aircraft lands, a portion of the battery modules in the cargo hold are transferred to the takeoff support to form the landing support.
[0021] The present invention also proposes a landing control device for an aircraft cargo hold and support structure, the device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, the computer program being executed by the processor to implement:
[0022] Before the aircraft takes off, acquire data on the cargo to be transported, the estimated power consumption for the current flight, and the landing environment at the destination.
[0023] The first configuration quantity, the second configuration quantity, and the third configuration quantity of battery modules are determined based on the cargo data, the power consumption data, and the landing environment, respectively.
[0024] The required fourth configuration quantity of battery modules is calculated based on the first configuration quantity, the second configuration quantity, and the third configuration quantity.
[0025] When the aircraft takes off, a portion of the battery modules in the fourth configuration form a cargo hold for loading goods, and when the aircraft lands, a portion of the battery modules in the fourth configuration form a landing support.
[0026] Optionally, the computer program is implemented when executed by the processor as follows:
[0027] Obtain the cargo weight and cargo dimensions from the cargo data;
[0028] The power consumption data is calculated based on the weight of the cargo, the weight of the aircraft, and the flight range data, and the landing range of the destination is calculated based on the dimensions of the cargo, the dimensions of the aircraft, and the terrain features of the destination.
[0029] Optionally, the computer program is implemented when executed by the processor as follows:
[0030] Obtain the module power and module size of the battery module;
[0031] Based on the module's power and size, the first configuration number of battery modules for loading cargo is calculated, the second configuration number of battery modules for providing extended battery power is calculated, and the third configuration number of battery modules for assembling the support frame is calculated.
[0032] Optionally, the computer program is implemented when executed by the processor as follows:
[0033] When the sum of the first configuration quantity and the third configuration quantity is less than the second configuration quantity, a first preset quantity is added to the second configuration quantity as the fourth configuration quantity, wherein the fourth configuration quantity is greater than the first configuration quantity and the third configuration quantity;
[0034] When the sum of the first configuration quantity and the third configuration quantity is greater than or equal to the second configuration quantity, a second preset quantity is reduced from the second configuration quantity to obtain the fourth configuration quantity, wherein the fourth configuration quantity is greater than the first configuration quantity and the third configuration quantity;
[0035] Before the aircraft takes off, a portion of the battery modules in the fourth configuration are assembled into a takeoff support. After the aircraft takes off, a portion of the battery modules in the takeoff support are transferred to the cargo hold.
[0036] Before the aircraft lands, a portion of the battery modules in the cargo hold are transferred to the takeoff support to form the landing support.
[0037] The present invention also proposes a computer-readable storage medium storing an aircraft cargo hold and support takeoff and landing control program, which, when executed by a processor, implements the steps of the aircraft cargo hold and support takeoff and landing control method as described in any of the preceding claims.
[0038] The present invention provides a landing control method, device, and computer-readable storage medium for aircraft cargo hold and support structures. Before aircraft takeoff, the method acquires data on the cargo to be transported, estimated power consumption data for the current flight distance, and the landing environment of the destination. Based on the cargo data, power consumption data, and landing environment, it determines a first, second, and third configuration quantity of battery modules, respectively. Based on the first, second, and third configuration quantities, it calculates a fourth configuration quantity of battery modules required for landing. During aircraft takeoff, a portion of the fourth configuration quantity of battery modules forms a cargo hold for loading cargo, and during aircraft landing, a portion of the fourth configuration quantity of battery modules forms a landing support structure. This achieves an integrated landing control scheme for cargo hold and support structures based on independent battery modules, allowing the cargo hold and support structures to adaptively switch according to actual flight power requirements, simultaneously improving the aircraft's cargo capacity and range, and enhancing logistics timeliness. Attached Figure Description
[0039] The present invention will be further described below with reference to the accompanying drawings and embodiments. In the accompanying drawings:
[0040] Figure 1 This is the first flowchart of the aircraft cargo hold and support takeoff and landing control method of the present invention;
[0041] Figure 2 This is the second flowchart of the aircraft cargo hold and support takeoff and landing control method of the present invention;
[0042] Figure 3This is the third flowchart of the aircraft cargo hold and support takeoff and landing control method of the present invention;
[0043] Figure 4 This is the fourth flowchart of the aircraft cargo hold and support takeoff and landing control method of the present invention;
[0044] Figure 5 This is the fifth flowchart of the aircraft cargo hold and support takeoff and landing control method of the present invention. Detailed Implementation
[0045] It should be understood that the specific embodiments described herein are for illustrative purposes only and are not intended to limit the scope of the invention.
[0046] In the following description, the use of suffixes such as "module," "part," or "unit" to denote elements is solely for the purpose of illustrative purposes and has no specific meaning in itself. Therefore, "module," "part," or "unit" may be used interchangeably.
[0047] Figure 1 This is a first flowchart of the aircraft cargo hold and support takeoff and landing control method of the present invention. This embodiment proposes an aircraft cargo hold and support takeoff and landing control method, which includes:
[0048] S1. Before the aircraft takes off, obtain data on the cargo to be transported, the estimated power consumption data for the current flight, and the landing environment of the destination.
[0049] S2. Determine the first configuration quantity, the second configuration quantity, and the third configuration quantity of battery modules based on the cargo data, the power consumption data, and the landing environment, respectively.
[0050] S3. Calculate the required fourth configuration quantity of battery modules based on the first configuration quantity, the second configuration quantity, and the third configuration quantity;
[0051] S4. When the aircraft takes off, a portion of the battery modules in the fourth configuration form a cargo hold for loading goods, and when the aircraft lands, a portion of the battery modules in the fourth configuration form a landing support.
[0052] In this embodiment, the aircraft is a fixed-wing UAV or a multi-rotor UAV. Optionally, the aircraft may have one or more cargo bays built in or externally, and the external landing gear can be structurally modified according to the takeoff and landing environments. Specifically, the cargo bay and landing gear are assembled from multiple independent battery modules, that is, each battery module can be a separate assembly module. For example, multiple assembly modules can be assembled into a rectangle to serve as the cargo bay, or multiple assembly modules can be assembled into two or more tripods to serve as the landing gear. Optionally, in this embodiment, the cargo bay is assembled from six independent surfaces, each surface being an independent battery module, or multiple independent battery modules can be assembled into one surface. Further, in this embodiment, the four sides and one bottom surface of the cargo bay can independently power the aircraft. Optionally, in this embodiment, the four sides and one bottom surface of the cargo bay serve as the four side doors and one bottom door of the cargo bay, respectively. Optionally, in this embodiment, a power supply module is installed on the top surface of the cargo hold. This power supply module is electrically connected to the aircraft's power supply module and also electrically connected to the four side cargo doors and one bottom cargo door, thereby providing power from any one of the four sides and the bottom surface to the aircraft. Similarly, in this embodiment, the landing gear is composed of one or more triangular supports made up of multiple independent surfaces. Each surface is an independent battery module. A power supply module is installed at the top of each triangular support. This power supply module is electrically connected to the aircraft's power supply module and also electrically connected to the battery modules on the other surfaces of the landing gear, thereby providing power from any one surface of the landing gear to the aircraft.
[0053] In this embodiment, before the aircraft takes off, data on the cargo to be transported, estimated power consumption data for the current flight path, and the landing environment of the destination are acquired. The cargo data in this embodiment includes cargo weight and dimensions. Optionally, the estimated power consumption data is calculated based on the current flight path, aircraft weight, cargo weight, and flight weather conditions. Optionally, the destination includes various types such as lockers, windowsills, aprons, and vehicle roofs. Correspondingly, the landing environment in this embodiment includes the terrain features of the landing site and the landable area.
[0054] In this embodiment, the first, second, and third configuration quantities of battery modules are determined based on the cargo data, the power consumption data, and the landing environment, respectively. Optionally, the battery modules in this embodiment are all of uniform specifications, that is, they can be used to assemble cargo compartments as well as landing gear.
[0055] In this embodiment, the required fourth configuration quantity of battery modules is calculated based on the first configuration quantity, the second configuration quantity, and the third configuration quantity. Optionally, when the sum of the first configuration quantity and the second configuration quantity is greater than or equal to the third configuration quantity, one approach is that the fourth configuration quantity is the sum of the first configuration quantity and the second configuration quantity, that is, there are battery modules required to assemble a complete cargo hold, and there are also battery modules required to assemble a complete landing gear; another more preferred approach is that the fourth configuration quantity is less than the sum of the first configuration quantity and the second configuration quantity.
[0056] In this embodiment, during aircraft takeoff, a portion of the battery modules in the fourth configuration quantity form a cargo hold for loading goods, and during aircraft landing, a portion of the battery modules in the fourth configuration quantity form a landing support. Optionally, based on the second scheme described above, when the fourth configuration quantity is less than the sum of the first and second configuration quantities, for the aircraft takeoff phase, a portion of the battery modules in the fourth configuration quantity are used to form a cargo hold for loading goods, and for the aircraft landing phase, a portion of the battery modules in the fourth configuration quantity are used to form a landing support.
[0057] The beneficial effects of this embodiment are as follows: Before aircraft takeoff, data on the cargo to be transported, the estimated power consumption data for the current flight distance, and the landing environment of the destination are acquired; based on the cargo data, the power consumption data, and the landing environment, a first configuration quantity, a second configuration quantity, and a third configuration quantity of battery modules are determined respectively; a fourth configuration quantity of battery modules required at the current time is calculated based on the first configuration quantity, the second configuration quantity, and the third configuration quantity; during aircraft takeoff, a portion of the fourth configuration quantity of battery modules forms a cargo hold for loading cargo; during aircraft landing, a portion of the fourth configuration quantity of battery modules forms a landing support. This achieves an integrated takeoff and landing control scheme for cargo hold supports based on independent battery modules, allowing the cargo hold supports to adaptively switch between each other according to the actual power demand for the flight distance, simultaneously improving the aircraft's cargo carrying capacity and endurance, and enhancing logistics timeliness.
[0058] Figure 2 This is a second flowchart of the takeoff and landing control method for aircraft cargo hold and support structures of the present invention. Based on the above embodiment, the step of acquiring data on the cargo to be transported, the estimated power consumption data for the current flight distance, and the landing environment at the destination before aircraft takeoff includes:
[0059] S11. Obtain the cargo weight and cargo dimensions from the cargo data;
[0060] S12. Calculate the power consumption data based on the weight of the cargo, the weight of the aircraft, and the flight range data, and calculate the landing range of the destination based on the dimensions of the cargo, the dimensions of the aircraft, and the terrain features of the destination.
[0061] Optionally, in this embodiment, a portion of the cargo hold is used as part of the landing gear. Based on this, after the aircraft takes off, the landing gear is folded up to become part of the cargo hold, and when the aircraft lands, the landing gear is lowered to provide the support required for landing.
[0062] Optionally, in this embodiment, when the landing gear is used as part of the cargo bay, it is determined whether the size of the cargo bay is less than or equal to the landing range designed for the destination. If the size of the cargo bay is less than or equal to the landing range, the bottom size of the cargo bay is determined to be the current required landing range.
[0063] Figure 3 This is a third flowchart of the takeoff and landing control method for aircraft cargo hold and support structures of the present invention. Based on the above embodiments, the step of determining the first configuration quantity, the second configuration quantity, and the third configuration quantity of battery modules according to the cargo data, the power consumption data, and the landing environment includes:
[0064] S21. Obtain the module power and module size of the battery module;
[0065] S22. Based on the module's power and size, calculate the first configuration number of battery modules for loading cargo, calculate the second configuration number of battery modules for providing extended battery power, and calculate the third configuration number of battery modules for assembling the support frame.
[0066] Optionally, in this embodiment, one approach is to calculate the third configuration number of battery modules used to assemble the takeoff support; another approach is to calculate the third configuration number of battery modules used to assemble the landing support. The required configuration number for the takeoff support is less than or equal to the required configuration number for landing.
[0067] Optionally, in this embodiment, during takeoff, a portion of the cargo hold is used as a takeoff support. After takeoff, the takeoff support is retracted and the cargo hold is replenished. For example, when the cargo hold has a rectangular structure, at least two sides of the rectangle are controlled to slide downwards. On the one hand, this serves as a takeoff support; on the other hand, it opens the side doors to facilitate the loading of goods to be transported. Shortly after takeoff, at least two sides of the rectangle are controlled to slide upwards and retract. This avoids additional wind resistance caused by the support and facilitates obstacle avoidance during flight. Furthermore, it closes the cargo hold to prevent goods from being lost.
[0068] Figure 4 This is the fourth flowchart of the aircraft cargo hold and support takeoff and landing control method of the present invention. Based on the above embodiment, the step of calculating the currently required fourth configuration quantity of battery modules according to the first configuration quantity, the second configuration quantity, and the third configuration quantity includes:
[0069] S31. When the sum of the first configuration quantity and the third configuration quantity is less than the second configuration quantity, a first preset quantity is added to the second configuration quantity as the fourth configuration quantity, wherein the fourth configuration quantity is greater than the first configuration quantity and the third configuration quantity;
[0070] S32. When the sum of the first configuration quantity and the third configuration quantity is greater than or equal to the second configuration quantity, a second preset quantity is reduced from the second configuration quantity to form the fourth configuration quantity, wherein the fourth configuration quantity is greater than the first configuration quantity and the third configuration quantity.
[0071] Optionally, in this embodiment, the difference between the second configuration quantity and the first configuration quantity and the third configuration quantity is used as the first preset quantity, thereby reducing the number of battery modules required while meeting the battery life requirements.
[0072] Optionally, in this embodiment, the second preset quantity is determined based on the difference between the required number of landing gear and takeoff gear, thereby making full use of the conversion of the landing gear to further reduce the number of battery modules required while meeting the battery life requirements.
[0073] Figure 5 This is the fifth flowchart of the takeoff and landing control method for aircraft cargo hold and support structure of the present invention. Based on the above embodiments, when the aircraft takes off, a portion of the battery modules in the fourth configuration number are used to form a cargo hold for loading cargo, and when the aircraft lands, a portion of the battery modules in the fourth configuration number are used to form a support structure for landing, including:
[0074] S41. Before the aircraft takes off, a portion of the battery modules in the fourth configuration are assembled into a takeoff support. After the aircraft takes off, a portion of the battery modules in the takeoff support are transferred to the cargo hold.
[0075] S42. Before the aircraft lands, a portion of the battery modules in the cargo hold are transferred to the takeoff support to form the landing support.
[0076] Optionally, in this embodiment, when the cargo hold is a cylindrical structure, the side of the cylinder is controlled to slide downwards. On the one hand, it serves as a takeoff support, and on the other hand, it opens the side door to facilitate the delivery of goods to be transported. In a short period of time after takeoff, the side of the cylinder is controlled to slide upwards and retract. On the one hand, this avoids the support from causing additional wind resistance and facilitates obstacle avoidance during flight. On the other hand, it closes the cargo hold to prevent goods from being lost.
[0077] Optionally, in this embodiment, when the cargo hold is a cylindrical structure, the bottom surface of the cylinder is controlled to slide downwards via multiple guide rails until it reaches a limit position. On the one hand, this bottom surface serves as a takeoff support; on the other hand, the open ground facilitates the placement of goods to be transported. Shortly after takeoff, the bottom surface of the cylinder is controlled to slide upwards and retract, simultaneously supporting the goods as they enter the cargo hold. Based on this, on the one hand, additional wind resistance caused by the support structure can be avoided, and obstacle avoidance during flight can be facilitated; on the other hand, the closed cargo hold prevents goods from being lost.
[0078] Based on the above embodiments, the present invention also proposes a landing control device for an aircraft cargo hold and support structure. This device includes a memory, a processor, and a computer program stored in the memory and executable on the processor. When the computer program is executed by the processor, it implements the following:
[0079] Before the aircraft takes off, acquire data on the cargo to be transported, the estimated power consumption for the current flight, and the landing environment at the destination.
[0080] The first configuration quantity, the second configuration quantity, and the third configuration quantity of battery modules are determined based on the cargo data, the power consumption data, and the landing environment, respectively.
[0081] The required fourth configuration quantity of battery modules is calculated based on the first configuration quantity, the second configuration quantity, and the third configuration quantity.
[0082] When the aircraft takes off, a portion of the battery modules in the fourth configuration form a cargo hold for loading goods, and when the aircraft lands, a portion of the battery modules in the fourth configuration form a landing support.
[0083] Optionally, the computer program is implemented when executed by the processor as follows:
[0084] Obtain the cargo weight and cargo dimensions from the cargo data;
[0085] The power consumption data is calculated based on the weight of the cargo, the weight of the aircraft, and the flight range data, and the landing range of the destination is calculated based on the dimensions of the cargo, the dimensions of the aircraft, and the terrain features of the destination.
[0086] Optionally, the computer program is implemented when executed by the processor as follows:
[0087] Obtain the module power and module size of the battery module;
[0088] Based on the module's power and size, the first configuration number of battery modules for loading cargo is calculated, the second configuration number of battery modules for providing extended battery power is calculated, and the third configuration number of battery modules for assembling the support frame is calculated.
[0089] Optionally, the computer program is implemented when executed by the processor as follows:
[0090] When the sum of the first configuration quantity and the third configuration quantity is less than the second configuration quantity, a first preset quantity is added to the second configuration quantity as the fourth configuration quantity, wherein the fourth configuration quantity is greater than the first configuration quantity and the third configuration quantity;
[0091] When the sum of the first configuration quantity and the third configuration quantity is greater than or equal to the second configuration quantity, a second preset quantity is reduced from the second configuration quantity to obtain the fourth configuration quantity, wherein the fourth configuration quantity is greater than the first configuration quantity and the third configuration quantity;
[0092] Before the aircraft takes off, a portion of the battery modules in the fourth configuration are assembled into a takeoff support. After the aircraft takes off, a portion of the battery modules in the takeoff support are transferred to the cargo hold.
[0093] Before the aircraft lands, a portion of the battery modules in the cargo hold are transferred to the takeoff support to form the landing support.
[0094] It should be noted that the above-described device embodiments and method embodiments belong to the same concept. The specific implementation process can be found in the method embodiments, and the technical features in the method embodiments are also applicable to the device embodiments, which will not be repeated here.
[0095] Based on the above embodiments, the present invention also proposes a computer-readable storage medium storing an aircraft cargo hold and support takeoff and landing control program, which, when executed by a processor, implements the steps of the aircraft cargo hold and support takeoff and landing control method as described in any of the above claims.
[0096] It should be noted that the above-described medium embodiments and method embodiments belong to the same concept. The specific implementation process can be found in the method embodiments, and the technical features in the method embodiments are also applicable to the medium embodiments, which will not be repeated here.
[0097] It should be noted that, in this document, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Unless otherwise specified, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes that element.
[0098] The sequence numbers of the above embodiments of the present invention are for descriptive purposes only and do not represent the superiority or inferiority of the embodiments.
[0099] Through the above description of the embodiments, those skilled in the art can clearly understand that the methods of the above embodiments can be implemented by means of software plus necessary general-purpose hardware platforms. Of course, they can also be implemented by hardware, but in many cases the former is a better implementation method. Based on this understanding, the technical solution of the present invention, in essence, or the part that contributes to the prior art, can be embodied in the form of a software product. This computer software product is stored in a storage medium (such as ROM / RAM, magnetic disk, optical disk), and includes several instructions to cause a terminal (which may be a mobile phone, computer, server, air conditioner, or network device, etc.) to execute the methods described in the various embodiments of the present invention.
[0100] The embodiments of the present invention have been described above with reference to the accompanying drawings. However, the present invention is not limited to the specific embodiments described above. The specific embodiments described above are merely illustrative and not restrictive. Those skilled in the art can make many other forms under the guidance of the present invention without departing from the spirit and scope of the claims. All of these forms are within the protection scope of the present invention.
Claims
1. A method of landing control of an aircraft cargo hold and a support, characterized in that, The method comprises: Before the aircraft takes off, obtaining current cargo data to be transported, current flight estimated power consumption data, and destination landing environment; According to the cargo data, the power consumption data, and the landing environment, respectively determine the first configuration number, the second configuration number, and the third configuration number of the battery module; According to the first configuration number, the second configuration number, and the third configuration number, calculate the fourth configuration number of the battery module required at present; When the aircraft takes off, a part of the battery modules in the fourth configuration number are used to form a cargo compartment for loading cargo, and when the aircraft lands, a part of the battery modules in the fourth configuration number are used to form a support for landing; Wherein, Obtain the module power and the module size of the battery module; According to the module power and the module size, calculate the first configuration number of the battery module for loading cargo, calculate the second configuration number of the battery module for providing endurance power, and calculate the third configuration number of the battery module for building a support.
2. The method of landing control of an aircraft cargo hold and stowage according to claim 1, characterized in that, The method comprises: Obtain the weight and size of the cargo in the cargo data; According to the weight of the cargo, the weight of the aircraft, and the flight data, calculate the power consumption data, and according to the size of the cargo, the size of the aircraft, and the topographic features of the destination, calculate the landing range of the destination.
3. The method of landing control of an aircraft cargo hold and stowage according to claim 2, wherein, The method comprises: When the sum of the first configuration number and the third configuration number is less than the second configuration number, increase the first preset number on the basis of the second configuration number as the fourth configuration number, wherein the fourth configuration number is greater than the first configuration number and the third configuration number; When the sum of the first configuration number and the third configuration number is greater than or equal to the second configuration number, reduce the second preset number on the basis of the second configuration number as the fourth configuration number, wherein the fourth configuration number is greater than the first configuration number and the third configuration number.
4. The method of landing control of an aircraft cargo hold and stowage according to claim 3, wherein, The method comprises: Before the aircraft takes off, a part of the battery modules in the fourth configuration number are used to form a take-off support, and after the aircraft takes off, a part of the battery modules of the take-off support are transferred to the cargo compartment; Before the aircraft lands, a part of the battery modules of the cargo compartment are transferred to the take-off support to form a landing support.
5. An aircraft cargo hold and stowage landing control apparatus, characterized by, The device comprises a memory, a processor, and a computer program stored on the memory and executable on the processor, and the computer program is executed by the processor to realize: Before the aircraft takes off, obtaining current cargo data, current flight estimated power consumption data, and destination landing environment; According to the cargo data, the power consumption data, and the landing environment, respectively determining a first configuration number, a second configuration number, and a third configuration number of battery modules; According to the first configuration number, the second configuration number, and the third configuration number, calculating a fourth configuration number of battery modules required at present; When the aircraft takes off, a part of the battery modules in the fourth configuration number are used to form a cargo compartment for loading cargo, and when the aircraft lands, a part of the battery modules in the fourth configuration number are used to form a landing support; Obtaining the module power and the module size of the battery modules; According to the module power and the module size, calculating the first configuration number of battery modules for loading cargo, the second configuration number of battery modules for providing endurance power, and the third configuration number of battery modules for forming a support.
6. The aircraft cargo hold and stowage landing control apparatus of claim 5, wherein, When the computer program is executed by the processor, the following steps are realized: Obtaining the weight and size of the cargo in the cargo data; According to the weight of the cargo, the weight of the aircraft, and the flight data, calculating the power consumption data, and according to the size of the cargo, the size of the aircraft, and the topographic features of the destination, calculating the landing range of the destination.
7. An aircraft cargo hold and stowage landing control apparatus according to claim 6, characterised in that, When the computer program is executed by the processor, the following steps are realized: When the sum of the first configuration number and the third configuration number is less than the second configuration number, increasing a first preset number on the basis of the second configuration number as the fourth configuration number, wherein the fourth configuration number is greater than the first configuration number and the third configuration number; When the sum of the first configuration number and the third configuration number is greater than or equal to the second configuration number, reducing a second preset number on the basis of the second configuration number as the fourth configuration number, wherein the fourth configuration number is greater than the first configuration number and the third configuration number; Before the aircraft takes off, a part of the battery modules in the fourth configuration number are used to form a take-off support, and after the aircraft takes off, a part of the battery modules of the take-off support are transferred to the cargo compartment; Before the aircraft lands, a part of the battery modules of the cargo compartment are transferred to the take-off support to form a landing support.
8. A computer-readable storage medium, characterized in that, The computer readable storage medium stores an aircraft cargo compartment and support landing control program, and when the aircraft cargo compartment and support landing control program is executed by the processor, the steps of the aircraft cargo compartment and support landing control method in any one of claims 1 to 4 are realized.
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