Timing method, electronic device, storage medium, and program product

Abstract

This application discloses a timing method, electronic device, storage medium, and program product, relating to the field of aircraft technology. The timing method includes: acquiring a mass value monitored by a gravity sensing module; determining the control team to which the aircraft belongs via a circuit board when the duration of a first target detected exceeds a preset hysteresis time, and controlling a timer to start timing; determining the landing time of the control team to which the aircraft belongs based on the timer's duration data, wherein the duration of the first target is the duration of a mass value greater than or equal to a preset threshold; and stopping the timer when the duration of a second target detected exceeds the hysteresis time, wherein the duration of the second target is the duration of a mass value less than a preset threshold. This application improves the timing accuracy of aircraft racing by achieving automatic and accurate detection of the aircraft's landing status and full automation of timing.

Description

Technical Field

[0001] This application relates to the field of aircraft technology, and in particular to timing methods, electronic devices, storage media, and program products. Background Technology

[0002] As an emerging field combining robotics technology and sports competition, unmanned aerial vehicle (UAV) competitions can test the maneuverability and stability of UAVs, as well as the real-time decision-making and control skills of pilots. In competitive games such as "multiple UAVs vying for control of the central platform," accurately determining the time each UAV spends on the central platform is a key factor in determining the outcome of the competition and the scores of the pilots.

[0003] The most common timing and judging method currently used is the "human visual inspection combined with stopwatch" operation mode. That is, two referees are set up at the competition site to work together. One referee visually judges whether the participating aircraft has landed completely on the platform, while the other referee presses the stopwatch to start / stop the timing according to the first referee's command or gesture. After each round, the time recorded by the stopwatch is copied by a person and converted into the corresponding score according to the competition rules.

[0004] However, different judges, and even the same judge, have subjective differences in their judgment criteria for whether the aircraft has fully landed or has been knocked off the platform. Furthermore, human visual observation cannot accurately capture this critical moment, which leads to timing errors.

[0005] The above content is only used to help understand the technical solution of this application and does not represent an admission that the above content is prior art. Summary of the Invention

[0006] The main objective of this application is to provide a timing method, electronic device, storage medium, and program product, which aims to solve the technical problem of how to improve the timing accuracy of aircraft racing.

[0007] To achieve the above objectives, this application proposes a timing method applied to a central platform. The central platform includes a gravity sensing module, a conductive circuit board, and a timer. The conductive circuit board is located on the landing surface of the central platform. The method includes: Obtain the mass value monitored by the gravity sensing module; If the duration of the first target detected is longer than a preset hysteresis time, the control team to which the aircraft belongs is determined by the conductive circuit board, and the timer is controlled to start timing. Based on the duration data of the timer, the landing duration of the control team to which the aircraft belongs is determined, wherein the duration of the first target is the duration of the mass value being greater than or equal to a preset threshold. If the duration of the second target is detected to be longer than the hysteresis time, the timer is controlled to stop counting, wherein the duration of the second target is the duration during which the quality value is less than the preset threshold.

[0008] In one embodiment, the step of determining the control group to which the aircraft belongs via the conductive circuit board includes: The material state of the contact material of the aircraft is determined by the conductive circuit board, wherein the material state includes a conductive state and a non-conductive state; The control team to which the aircraft belongs is determined based on the material condition of the aircraft.

[0009] In one embodiment, the control team includes a conducting team and a non-conducting team, the timer includes a first timer and a second timer, and the step of controlling the timer to start timing includes: If the control team to which the aircraft belongs is a communication team, control the first timer to start timing; If the control team to which the aircraft belongs is a non-guided team, the second timer is started.

[0010] In one embodiment, the central platform includes a countdown module, and prior to the step of acquiring the mass value detected by the gravity sensing module, it further includes: Determine whether the countdown module has reset to zero; If the countdown module's countdown timer has not reached zero, the steps of obtaining the mass value detected by the gravity sensor module and subsequent steps are executed. When the countdown module reaches zero, the step of controlling the timer to stop counting is executed.

[0011] In one embodiment, the central platform includes a display, and the timing method further includes: The display shows the team score of each control team, the landing time of each control team's aircraft, and / or the countdown of the countdown module, wherein the team score is positively correlated with the landing time.

[0012] In one embodiment, the central platform includes multiple sub-platforms, and the timing method further includes: For any sub-platform, if the duration of the first target on the sub-platform is longer than the hysteresis time, the control team of the aircraft landing on the sub-platform is determined by the conduction circuit board of the sub-platform, and the timer of the sub-platform is controlled to start timing. The landing duration of the sub-platform is determined based on the timing data of the timer. In cases where at least two sub-platforms have the same control team, the sum of the landing times of the sub-platforms with the same control team is determined as the landing time of the control team.

[0013] In one embodiment, the gravity sensing module includes a plurality of S-shaped strain gauge sensors connected in a bridge configuration.

[0014] Furthermore, to achieve the above objectives, this application also proposes a timing device applied to a central platform. The central platform includes a gravity sensing module, a conductive circuit board, and a timer. The conductive circuit board is disposed on the landing surface of the central platform. The timing device includes: The acquisition module is used to acquire the mass value detected by the gravity sensing module; The timing module is used to determine the control team to which the aircraft belongs through the conductive circuit board when the duration of the first target detected is greater than a preset hysteresis time, and to control the timer to start timing. Based on the duration data of the timer, the landing duration of the control team to which the aircraft belongs is determined, wherein the duration of the first target is the duration of the mass value being greater than or equal to a preset threshold. The stop timing module is used to control the timer to stop timing when the duration of the second target is detected to be greater than the hysteresis time, wherein the duration of the second target is the duration during which the quality value is less than the preset threshold.

[0015] In addition, to achieve the above objectives, this application also proposes an electronic device comprising: a memory, a processor, and a computer program stored in the memory and executable on the processor, the computer program being configured to implement the steps of the timing method described above.

[0016] In addition, to achieve the above objectives, this application also proposes a storage medium, which is a computer-readable storage medium, on which a computer program is stored, and which, when executed by a processor, implements the steps of the timing method described above.

[0017] In addition, to achieve the above objectives, this application also provides a computer program product, which includes a computer program that, when executed by a processor, implements the steps of the timing method described above.

[0018] The one or more technical solutions proposed in this application have at least the following technical effects: First, by acquiring the mass value monitored by the gravity sensing module and accurately judging the landing situation of the aircraft by sensing the load changes on the central platform in real time, the discrepancies or errors in judgment caused by human visual differences are eliminated; Second, when the duration of the first target with a mass value greater than or equal to a preset threshold is longer than a preset hysteresis time, ineffective landing situations such as brief contact with the platform or bouncing contact are effectively filtered out. When the aircraft has fully landed, the control team to which the aircraft belongs is determined by the conductive circuit board, the timing object is identified, and the timer is controlled to start timing, realizing the accurate determination of team affiliation and the synchronous linkage of timing start, avoiding the problems of human communication delay and operation asynchrony. At the same time, the landing duration of the control team to which the aircraft belongs can be determined according to the duration data of the timer, so as to accurately record the time the aircraft stays on the central platform; Third, by detecting the duration of the second target with a mass value less than a preset threshold being longer than the hysteresis time, the critical state of the aircraft leaving the platform can be accurately captured. At this time, the timer is controlled to stop timing, overcoming the limitation that human visual observation cannot accurately capture the moment of the aircraft leaving the platform. This application combines gravity sensing, hysteresis time determination, conductive circuit board team identification, and automatic timing control to achieve automatic and accurate detection of aircraft landing status and full automation of timing, eliminating human visual judgment errors and manual operation delays, thereby improving the timing accuracy and judgment consistency of aircraft competitions. Attached Figure Description

[0019] The accompanying drawings, which are incorporated in and form part of this specification, illustrate embodiments consistent with this application and, together with the description, serve to explain the principles of this application.

[0020] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, for those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0021] Figure 1 This is a flowchart illustrating the timing method of this application in Embodiment 1. Figure 2 A timing workflow diagram of the central platform provided in Embodiment 2 of this application; Figure 3 A schematic diagram of the central platform device provided in Embodiment 2 of this application; Figure 4 This is a schematic diagram of the module structure of the timing device in an embodiment of this application; Figure 5 This is a schematic diagram of the device structure of the hardware operating environment involved in the timing method in the embodiments of this application.

[0022] The purpose, features, and advantages of this application will be further explained in conjunction with the embodiments and with reference to the accompanying drawings. Detailed Implementation

[0023] It should be understood that the specific embodiments described herein are merely illustrative of the technical solutions of this application and are not intended to limit this application.

[0024] It should be noted that in the description of this application and the appended claims, the terms "first," "second," etc., are used only to distinguish descriptions and should not be construed as indicating or implying relative importance.

[0025] To better understand the technical solution of this application, a detailed description will be provided below in conjunction with the accompanying drawings and specific implementation methods.

[0026] Currently, for competitive games like "multiple aircraft vying for control of the central platform," the commonly used timing and judging method is a combination of manual visual inspection and stopwatch operation. This involves two referees working together: one visually assesses whether the participating aircraft has fully landed on the platform, while the other simultaneously starts / stops the stopwatch based on the first referee's commands or gestures. After each round, the stopwatch time is manually recorded and converted into a score according to the competition rules. However, different referees, and even the same referee, may have subjective differences in their judgment of whether an aircraft has fully landed or been knocked off the platform. Furthermore, manual visual inspection cannot accurately capture these critical moments, leading to timing errors.

[0027] This application provides a solution. First, it acquires the mass value monitored by the gravity sensing module. By sensing the load changes on the central platform in real time, it accurately determines the landing status of the aircraft, eliminating discrepancies or errors caused by human visual differences. Then, when the duration of a first target with a mass value greater than or equal to a preset threshold exceeds a preset hysteresis time, it effectively filters out ineffective landing scenarios such as brief touch-ups or bounce-offs. When the aircraft fully lands, the control team to which the aircraft belongs is determined via the conductive circuit board, the timing object is identified, and the timer starts counting, achieving accurate team affiliation determination and synchronized timing start, avoiding delays in human communication and asynchronous operations. Furthermore, by detecting a second target with a mass value less than a preset threshold whose duration exceeds the hysteresis time, it can accurately capture the critical state of the aircraft leaving the platform. At this point, it controls the timer to stop counting, and based on the timer's duration data, determines the landing duration of the control team to which the aircraft belongs, accurately recording the aircraft's dwell time on the central platform, overcoming the limitation of human visual observation in accurately capturing the moment of aircraft departure. This application combines gravity sensing, hysteresis time determination, conductive circuit board team identification, and automatic timing control to achieve automatic and accurate detection of aircraft landing status and full automation of timing, eliminating human visual judgment errors and manual operation delays, thereby improving the timing accuracy and judgment consistency of aircraft competitions.

[0028] It should be noted that the executing entity in this embodiment can be an electronic device with data processing, network communication and program execution functions, such as a tablet computer, personal computer, mobile phone, etc., or a central platform that can realize the above functions.

[0029] The central platform refers to the target area encompassed by the aircraft, a hardware carrier that provides physical space to support the aircraft and monitor their related data. It typically integrates sensors such as gravity sensing modules, conductive circuit boards, and timers. The aircraft refers to an aircraft with autonomous or remote-controlled flight capabilities, such as multi-rotor drones and vertical takeoff and landing fixed-wing aircraft; this embodiment does not impose specific limitations on this.

[0030] A gravity sensing module is a sensor device used to sense changes in the mass of an object and convert them into electrical signals. It is usually composed of strain gauge pressure sensors or piezoelectric force sensor arrays. It can convert the vertical pressure on the surface of a platform into an electrical signal, and output a digitally quantized mass value after analog-to-digital conversion.

[0031] A conductive circuit board is a printed circuit board with circuit conduction function. When an aircraft with conductive material lands and comes into contact with the circuit board, a closed electrical circuit is formed. By detecting the on / off state of the circuit or the encoded signal, it is possible to identify which team of aircraft has landed.

[0032] A timer is an electronic device used to accurately measure time intervals. It can start and stop timing according to preset rules and record the measured time value.

[0033] Based on this, the embodiments of this application provide a timing method, referring to... Figure 1 , Figure 1 This is a flowchart illustrating the first embodiment of the timing method of this application.

[0034] In this embodiment, the timing method is applied to the central platform, which includes a gravity sensing module, a conductive circuit board, and a timer. The conductive circuit board is located on the landing surface of the central platform. The timing method includes steps S10 to S30: Step S10: Obtain the mass value detected by the gravity sensing module; For example, the gravity sensing module can be set on the landing surface of the central platform (i.e., the platform surface where the aircraft lands, such as the top surface of the platform); after the central platform is powered on, its gravity sensing module, conductive circuit board and timer are in standby state, wherein the gravity sensing module begins to continuously sense the pressure it bears and converts the pressure into mass value data; then the central platform continuously acquires the mass value output by the gravity sensing module according to a preset sampling frequency through its processor (such as STM32H7, etc.) and uses it for subsequent analysis.

[0035] In one feasible implementation, the gravity sensing module includes multiple S-shaped strain gauge sensors connected in a bridge configuration.

[0036] An S-type strain gauge sensor is a sensor that works based on the principle of strain effect. Its sensitive grid has an S-shaped structure. When the sensor is subjected to an external force, the sensitive grid will deform, causing its resistance value to change. The magnitude of the external force can then be calculated by measuring the change in resistance value.

[0037] Bridge connection refers to a specific circuit connection method, which usually connects multiple sensors (such as the S-type strain gauge sensor in this embodiment) according to a specific bridge circuit structure to improve the sensitivity, accuracy and anti-interference ability of the sensors; common bridge circuits include Wheatstone bridge, etc.

[0038] For example, four S-shaped strain gauge sensors connected by bridges can be evenly distributed or matrixed around the landing surface of the central platform to achieve uniform pressure monitoring of the entire landing surface, ensuring that the mass value can be accurately detected no matter where the aircraft lands on the landing surface, thereby improving the reliability and accuracy of the aircraft landing timing.

[0039] In this embodiment, a gravity sensing module is constructed by bridging multiple S-shaped strain gauge sensors. Multiple sensors share the load, which can more comprehensively reflect the overall stress situation of the platform and improve the accuracy of mass change monitoring during aircraft landing. At the same time, because multiple sensors work together, pressure acquisition and mass value output can still be performed normally even if a single strain gauge sensor fails.

[0040] Step S20: If the duration of the first target detected is longer than the preset hysteresis time, the control team to which the aircraft belongs is determined by the conduction circuit board, and the timer is controlled to start timing. Based on the duration data of the timer, the landing time of the control team to which the aircraft belongs is determined. The duration of the first target refers to the duration of the state where the mass value output by the gravity sensor module is greater than or equal to a preset threshold, determined by continuous monitoring. This preset threshold is the minimum mass of the aircraft that is pre-set.

[0041] Hysteresis time refers to the time threshold parameter used to eliminate critical jitter and confirm a stable state, such as 0.5 seconds, 1 second, etc. This embodiment does not impose specific limitations on it. When the time for the aircraft to enter / exit the platform exceeds the hysteresis time, it is determined that the aircraft is in a valid entry / exit state, avoiding time fragmentation caused by aircraft jitter (such as brief entry / exit due to collision). Its value can be dynamically adjusted according to different stages of the competition. For example, in the initial capture phase of the competition, a shorter hysteresis time can be set to encourage rapid capture; in the later stalemate phase of the competition, a longer hysteresis time can be set to require the aircraft to capture more stably.

[0042] The control team refers to the digital identity of the participating team corresponding to the currently landing flight. It can be identified by setting different electrical coding schemes in the conductive circuit board, such as contact position coding (different teams correspond to different contact areas for conduction), resistance value coding (different teams correspond to different resistance values ​​of conductive materials), frequency coding (different teams correspond to different frequency conduction signals), etc. This embodiment does not impose specific limitations on this.

[0043] Landing time refers to the total time that the aircraft effectively occupies the platform during this landing, which can be determined based on the original count value in the timer after the timing has stopped.

[0044] For example, a specific pattern can be formed by copper plating on the surface of the conductive circuit board. When the bottom of the aircraft is equipped with corresponding electrodes or conductive materials, an electrical path is formed with specific contacts at the moment of landing. By scanning the conduction status of each contact, the team information corresponding to the aircraft can be decoded.

[0045] For example, the central platform compares the acquired quality value with a preset threshold to determine whether the quality value is greater than or equal to the preset threshold, and records the duration of the first target that the quality value meets the condition. When the duration of the first target exceeds a preset hysteresis time, the electrical status of the conductive circuit board (such as contact position or resistance value) is scanned to decode the control team of the currently landing aircraft, and a start timing command is sent to the timer to bind and record its timing data with the control team. At the same time, the duration data of the timer can be determined as the landing duration of the control team to which the aircraft belongs, or the duration data can be added to the historical landing duration of the control team to obtain the cumulative landing duration of the control team, and displayed in real time on the display of the central platform.

[0046] For example, during the timing process, the score of the control team to which the aircraft belongs can also be determined or updated based on the duration of the timer. For example, the team score increases by 1 point for every 5 seconds the timer duration increases. The score is then linked to the control team and displayed in real time on the central platform's display.

[0047] Understandably, by setting a hysteresis time, mistimed errors caused by short-term fluctuations in quality values ​​are avoided, eliminating the need for manual intervention and improving the accuracy and objectivity of timing. By accurately identifying the control team to which the aircraft belongs through the conductive circuit board, automatic team identification can be achieved when the aircraft lands, avoiding the delay of human visual reaction and improving the timeliness and accuracy of timing.

[0048] In one feasible implementation, step S20, which involves determining the control group to which the aircraft belongs via the conductive circuit board, includes: Step S21: Determine the material state of the contact material of the aircraft through the conductive circuit board, wherein the material state includes a conductive state and a non-conductive state. Contact material refers to the physical medium installed on the bottom of the aircraft for direct contact with the conductive circuit board on the central platform, such as conductive foam and non-conductive foam; while material state is the binary determination result of the conductive circuit board on the electrical properties of the contact material, such as conductive foam and non-conductive foam corresponding to conductive state and non-conductive state, respectively.

[0049] The conducting state refers to the electrical state in which a low-impedance electrical path is formed between the contact material and the contact point of the conductive circuit board; the non-conducting state refers to the electrical state in which a high impedance or an open circuit is present between the contact material and the contact point.

[0050] For example, after the aircraft lands on the central platform, its contact material comes into contact with a conductive circuit board installed on the landing surface of the central platform. The central platform can then use the conductive circuit board to detect the circuit continuity of the contact area between the aircraft and the contact material in real time. For example, by applying a test voltage, if a current is detected flowing through the contact material, it is determined that the contact material of the aircraft and the conductive circuit board form a closed loop, and the material state of the contact material can be determined to be conductive. Conversely, if no current flows through the contact material (i.e., no closed loop is formed), the material state of the contact material is determined to be non-conductive.

[0051] Step S22: Determine the control team to which the aircraft belongs based on the material condition of the aircraft.

[0052] For example, the control team to which an aircraft belongs can be determined based on the material state of the aircraft and the preset mapping relationship between the material state and the team identifier. For instance, when the red team and the blue team are competing for the central platform in a 3v3 battle, aircraft that are in a conductive state when they land can be uniformly identified as aircraft of the red team, and aircraft that are in a non-conductive state when they land can be uniformly identified as aircraft of the blue team.

[0053] In this embodiment, the control team to which the aircraft belongs can be identified by detecting the conduction / non-conduction status of the contact material of the aircraft. This eliminates the need for manual visual identification, has low latency and high reliability, and improves the timeliness and accuracy of team timing.

[0054] In one feasible implementation, the control team includes a conductive team and a non-conductive team, and the timer includes a first timer and a second timer. Step S20, which involves controlling the timer to start counting, includes: Step S23: If the control team to which the aircraft belongs is the communication team, start the first timer. Step S24: If the control team to which the aircraft belongs is a non-guided team, start the second timer.

[0055] The "guided teams" and "non-guided teams" refer to the logical classification labels used by the central platform for participating teams. Based on the aforementioned material status detection results, the central platform can map the aircraft into two different identity identifiers and store them in memory in the form of an enumeration type or a Boolean variable. For example, "1" represents the guided team (red team) and "0" represents the non-guided team (blue team) for subsequent real-time score display.

[0056] The first timer and the second timer refer to two independent and non-interfering hardware timer resources integrated within the central platform. Each has its own independent counter and can be started, stopped, and read independently. In this embodiment, the first timer and the second timer are specifically allocated to the guided and non-guided teams to record the landing time of their respective aircraft on the central platform.

[0057] For example, when the aircraft belongs to a guided flight group and the duration of the first target is longer than the lag time, the first timer starts counting, and the landing time of the aircraft in the guided flight group is determined based on the duration data of the first timer. Then, when the duration of the second target is longer than the lag time, the first timer stops counting. When the aircraft belongs to a non-guided flight group and the duration of the first target is longer than the lag time, the second timer starts counting, and the landing time of the aircraft in the non-guided flight group is determined based on the duration data of the second timer. Then, when the duration of the second target is longer than the lag time, the second timer stops counting. By controlling the start and stop of the independent timers corresponding to each group, the landing time of each group is independently counted. Therefore, after the aircraft leaves the station, it is not necessary to reset the timing data of the first / second timers. Instead, the landing time of each group can be obtained by continuing the counting of the corresponding timers after the aircraft lands again.

[0058] For example, the dual timer can be extended to an N-timer (N≥3) to support more team classification dimensions; for example, four independent timers can be set according to the resistance value of the conductive material (low resistance / medium resistance / high resistance / insulation), or k independent timers can be set according to the number of contact patterns (e.g., k). Each category corresponds to an independent timer, realizing independent timing for multiple teams.

[0059] In this embodiment, by setting an independent timer for each participating team, independent and accurate timing operations can be provided for each team, thereby improving the timing accuracy of the aircraft landing time for each team.

[0060] Step S30: If the duration of the second target is detected to be longer than the hysteresis time, control the timer to stop counting. The second target duration refers to the duration during which the mass value is less than a preset threshold, determined by continuous monitoring of the mass value output by the gravity sensing module. This is the time the aircraft spends away from the platform after landing.

[0061] For example, during the timing process, the central platform also continuously monitors the changes in the mass value output by the gravity sensing module, compares the acquired mass value with a preset threshold, determines whether the mass value is less than the preset threshold, and records the duration of the second target that the mass value meets the condition; when the duration of the second target exceeds a preset hysteresis time, a stop timing command is sent to the timer, and the score of the timer is cleared. After the next aircraft successfully lands on the central platform, the timing is restarted, and the control team of the aircraft is determined in order to calculate the landing time of each control team.

[0062] This embodiment provides a timing method that uses a gravity sensing module to acquire mass values ​​in real time, converting the physical event of the aircraft landing into a quantifiable digital signal, reducing subjective errors from manual visual judgment. Simultaneously, a hysteresis time mechanism is introduced to stably confirm the duration of the first and second targets, effectively filtering signal jitter caused by aircraft bouncing and platform vibrations, ensuring that the timing start and end points correspond to the actual stable landing and departure times, reducing fragmented timing and improving accuracy. Furthermore, the conductive circuit board detects the conduction / non-conduction status of the materials the aircraft is in contact with to determine its team affiliation, and an independent timer is set for each control team. Based on the identification results, the corresponding team's timer is activated, achieving parallel, independent, and non-interfering precise recording of the occupation time of both sides, ensuring clear and fair timing data. Finally, after confirming the aircraft's effective departure, the landing duration is automatically determined based on the stopped timer duration, replacing the manual recording of stopwatches and score conversion, reducing secondary human errors, and achieving full automation from timing data acquisition to output. As can be seen, this application achieves automatic and accurate detection of aircraft landing status, reliable identification of team identity, and accurate measurement of landing time, solving problems such as visual errors and operational delays in traditional manual timing methods, and improving the timing accuracy of aircraft competitions.

[0063] Based on the first embodiment of this application, in the second embodiment of this application, the content that is the same as or similar to that in the first embodiment described above can be referred to the above description and will not be repeated hereafter. In addition, the central platform includes a countdown module, and before the step of acquiring the mass value monitored by the gravity sensor module, it further includes: Step S01: Determine whether the countdown module has reset to zero; The countdown module refers to an independent timing unit built into the central platform that counts down according to the preset match duration (e.g., 3 minutes). When it reaches zero, it generates a flag signal or interrupts the countdown so that the central platform knows that the match has ended.

[0064] Step S02: If the countdown module's countdown timer has not reached zero, proceed with step S10 and subsequent steps. For example, if the countdown module's countdown timer has not reached zero, the preemption status of the aircraft's central platform can continue to be recorded, thereby continuing to acquire the mass value monitored by the gravity sensor module. If the duration of the first target whose mass value is greater than or equal to a preset threshold exceeds a preset hysteresis time, a timer is started to keep count until the countdown module's countdown timer reaches zero, or the duration of the second target whose mass value is less than a preset threshold exceeds the hysteresis time (i.e., the aircraft leaves the platform).

[0065] Step S03: When the countdown module's countdown reaches zero, execute the step in step S13 to stop the timer from counting down.

[0066] For example, if the countdown module reaches zero, it means the game is over (i.e., the landing and occupation time for all aircraft has ended). The timer needs to be stopped and the score calculated to prevent aircraft from landing outside the allotted time.

[0067] For example, to help understand the implementation flow of the timing method obtained by combining this embodiment with the first embodiment described above, please refer to... Figure 2 , Figure 2 A timing workflow diagram for a central platform is provided. First, it determines whether the countdown to the current match has reached zero (S101), i.e., whether the countdown module's timing has reached zero. If yes, the timer is stopped (S107), and the final score is displayed. If no, it determines whether an aircraft has effectively landed on the central platform (S102). When the mass value output by the gravity sensor module is greater than the first target duration of the preset threshold is greater than the hysteresis time, it can be determined that the aircraft has effectively landed. Then, the contact material of the aircraft can be determined through the conductive circuit board to determine whether it is conductive (S103) to determine the control team to which the aircraft belongs. If the material state of the contact material of the aircraft is conductive, it means that the aircraft belongs to the conductive team, and the first timer corresponding to the conductive team is controlled. The timer starts timing and displays the score (S104). The score can be determined based on the duration data of the first timer (i.e., the landing time of the aircraft) (e.g., the score increases by 1 point for every 5 seconds of timing). If the material state of the contact material of the aircraft is not conductive, it means that the aircraft belongs to the non-conductive team. Then, the first timer corresponding to the non-conductive team starts timing and displays the score (S105). During the timing process, the mass value output by the gravity sensing module is continuously monitored to determine whether the aircraft has left the platform (S106). When the duration of the second target with a mass value less than the preset threshold is greater than the hysteresis time, it can be determined that the aircraft has left the platform. Then, the timer (including the first timer and the second timer) is controlled to stop timing. The team score displayed on the screen is the final score of each controlled team.

[0068] In this embodiment, by setting a countdown module, it is possible to ensure that the data from the gravity sensor module is acquired within the specified competition time period. This ensures that the entire timing system strictly adheres to the basic principle of scoring only when the target is effectively captured within the specified time, avoiding timing errors caused by excessively long or short data acquisition times and improving the timing accuracy during aircraft competitions.

[0069] In one feasible implementation, the timing method further includes: Step A10: Display the team score of each control team, the landing time of each control team's aircraft, and / or the countdown of the countdown module on the display, wherein the team score is positively correlated with the landing time.

[0070] The display refers to the human-computer interaction output terminal of the central platform, which is used to convert digital, text or image information into visible light signals. It can be an LCD (Liquid Crystal Display) screen, an OLED (Organic Light Emitting Diode) screen or a simple indicator light array. This embodiment does not impose specific limitations on it.

[0071] The team score is a numerical variable that is calculated and dynamically updated in real time based on the landing time and a preset scoring rule (positive correlation). It can be a linear function of the landing time (e.g., 1 point per second) or a non-linear function (e.g., 1 point per second for the first 30 seconds, and 2 points per second thereafter). This implementation does not impose specific restrictions on the scoring rule.

[0072] For example, please refer to Figure 3 , Figure 3 A schematic diagram of a central platform device is provided, comprising a landing surface 201, a team score display area 202, a team identification display area 203, a landing time display area 204, and a countdown display area 205. The landing surface 201 is equipped with a gravity sensing module and a conductive circuit board for monitoring weight changes on the central platform and determining the control team to which the aircraft belongs. The team score display area 202 displays the team score for each team, which is positively correlated with landing time (e.g., for every 5 seconds increase in landing time, the team score increases by 1 point). The team identification display area 203 displays the identification information of each control team, such as using red squares to represent connected teams (red team) and blue squares to represent non-connected teams (blue team). The landing time display area 204 displays the total landing time of each control team's aircraft since the start of the competition, allowing participants and spectators to intuitively understand the current timing status. The countdown display area 205 displays the countdown timer.

[0073] In this embodiment, the team scores of each control team, the landing time of the aircraft, and the countdown information are displayed in real time on the monitor, so that all relevant personnel (such as referees, operators, and spectators) can understand the progress of the competition or mission in a timely and accurate manner, so that operators can adjust their tactics in time and improve the viewing experience of the audience.

[0074] In one feasible implementation, the central platform includes multiple sub-platforms, and the timing method further includes: Step E10: For any sub-platform, if the duration of the first target on the sub-platform is longer than the hysteresis time, the control team of the aircraft landing on the sub-platform is determined through the conduction circuit board of the sub-platform, and the timer of the sub-platform is started to start timing. The landing duration of the sub-platform is determined based on the timing data of the timer. A sub-platform refers to multiple independent timing units logically or physically divided within a central platform. Each sub-platform is a complete, functionally self-consistent micro-timing system, possessing its own independent gravity sensing module, circuit board, timer, and corresponding decision logic. Physically, they can be different areas on the same large platform or multiple separate small platforms.

[0075] The landing time of a sub-platform refers to the cumulative time recorded by a dedicated timer on a specific sub-platform, during which the sub-platform is effectively occupied by a certain team of aircraft. It only reflects the occupation status of a single sub-platform.

[0076] Step E20: In the case where there are at least two sub-platforms with the same control team, the sum of the landing times of the sub-platforms with the same control team is determined as the landing time of the control team.

[0077] For example, each sub-platform continuously monitors changes in the mass value output by its respective gravity sensor module. For any sub-platform, when it detects that the duration of a first target with a mass value greater than or equal to a preset threshold exceeds a preset hysteresis time, the sub-platform immediately identifies the control team of the landing aircraft on it and controls its timer to start counting to determine the landing duration of the control team on that sub-platform. Then, the central platform's processor performs statistical analysis on the control team and landing duration information of each sub-platform to determine if at least two sub-platforms have the same control team. If so, the landing durations of the sub-platforms with the same control team are added together to obtain the landing duration of the identical control team.

[0078] In this embodiment, by accurately recording the landing time of each sub-platform when multiple sub-platforms are set up, and summing the landing times of all sub-platforms with the same control team based on this, the total landing time of the team is obtained. This ensures that even in complex scenarios of intense multi-aircraft combat and simultaneous landing at multiple points, the occupation time of every second can be accurately captured and recorded, avoiding omissions or conflicts that may occur from single-point measurements, and improving the accuracy and reliability of timing.

[0079] It should be noted that the above examples are only for understanding this application and do not constitute a limitation on the timing method of this application. Any simple modifications based on this technical concept are within the protection scope of this application.

[0080] This application also provides a timing device, please refer to... Figure 4 The timing device is applied to the central platform, which includes a gravity sensing module, a conductive circuit board, and a timer. The conductive circuit board is located on the landing surface of the central platform. The timing device includes: The acquisition module 10 is used to acquire the mass value detected by the gravity sensing module; The timing module 20 is used to determine the control team to which the aircraft belongs through the conductive circuit board when the duration of the first target detected is greater than a preset hysteresis time, and to control the timer to start timing, wherein the duration of the first target is the duration of the mass value being greater than or equal to a preset threshold. The stop timing module 30 is used to control the timer to stop timing when the duration of the second target is detected to be greater than the hysteresis time, and to determine the landing duration of the control team to which the aircraft belongs based on the duration data of the timer, wherein the duration of the second target is the duration of the mass value being less than the preset threshold.

[0081] Optionally, the timing module 20 is also used for: The material state of the contact material of the aircraft is determined by the conductive circuit board, wherein the material state includes a conductive state and a non-conductive state; The control team to which the aircraft belongs is determined based on the material condition of the aircraft.

[0082] Optionally, the control team includes a conducting team and a non-conducting team, the timer includes a first timer and a second timer, and the timing module 20 is further used for: If the control team to which the aircraft belongs is a communication team, control the first timer to start timing; If the control team to which the aircraft belongs is a non-guided team, the second timer is started.

[0083] Optionally, the central platform includes a countdown module and an acquisition module 10, and is further used for: Determine whether the countdown module has reset to zero; If the countdown module's countdown timer has not reached zero, the steps of obtaining the mass value detected by the gravity sensor module and subsequent steps are executed. When the countdown module reaches zero, the step of controlling the timer to stop counting is executed.

[0084] Optionally, the central platform includes a display, and the timing device further includes a display module (not shown in the figure) for: The display shows the team score of each control team, the landing time of each control team's aircraft, and / or the countdown of the countdown module, wherein the team score is positively correlated with the landing time.

[0085] Optionally, the central platform includes multiple sub-platforms, and the timing module 20 is further used for: For any sub-platform, if the duration of the first target on the sub-platform is longer than the hysteresis time, the control team of the aircraft landing on the sub-platform is determined by the conduction circuit board of the sub-platform, and the timer of the sub-platform is controlled to start timing. The landing duration of the sub-platform is determined based on the timing data of the timer. In cases where at least two sub-platforms have the same control team, the sum of the landing times of the sub-platforms with the same control team is determined as the landing time of the control team.

[0086] Optionally, the gravity sensing module includes multiple S-shaped strain gauge sensors connected in a bridge configuration.

[0087] The timing device provided in this application, employing the timing method described in the above embodiments, can solve the technical problem of how to improve the timing accuracy in aircraft racing. Compared with the prior art, the beneficial effects of the timing device provided in this application are the same as those of the timing method provided in the above embodiments, and other technical features of the timing device are the same as those disclosed in the methods of the above embodiments, and will not be repeated here.

[0088] This application provides an electronic device, which includes: at least one processor; and a memory communicatively connected to the at least one processor; wherein the memory stores instructions executable by the at least one processor, which are executed by the at least one processor to enable the at least one processor to perform the timing method in the first embodiment described above.

[0089] The following is for reference. Figure 5The diagram illustrates a structural schematic of an electronic device suitable for implementing embodiments of this application. The electronic devices in these embodiments may include, but are not limited to, mobile terminals such as mobile phones, laptops, digital broadcast receivers, PDAs (Personal Digital Assistants), PADs (Portable Application Descriptions), PMPs (Portable Media Players), in-vehicle terminals (e.g., in-vehicle navigation terminals), and fixed terminals such as digital TVs and desktop computers. Figure 5 The electronic device shown is merely an example and should not impose any limitation on the functionality and scope of use of the embodiments of this application.

[0090] like Figure 5 As shown, the electronic device may include a processing unit 1001 (e.g., a central processing unit, a graphics processing unit, etc.), which can perform various appropriate actions and processes according to a program stored in a read-only memory 1002 or a program loaded from a storage device 1003 into a random access memory 1004. The random access memory 1004 also stores various programs and data required for the operation of the electronic device. The processing unit 1001, the read-only memory 1002, and the random access memory 1004 are interconnected via a bus 1005. An input / output interface 1006 is also connected to the bus. Typically, the following systems can be connected to the input / output interface 1006: input devices 1007 including, for example, touchscreens, touchpads, keyboards, mice, image sensors, microphones, accelerometers, gyroscopes, etc.; output devices 1008 including, for example, liquid crystal displays (LCDs), speakers, vibrators, etc.; storage devices 1003 including, for example, magnetic tapes, hard disks, etc.; and communication devices 1009. The communication device 1009 allows the electronic device to communicate wirelessly or wiredly with other devices to exchange data. Although the diagrams show electronic devices with various systems, it should be understood that it is not required to implement or have all of the systems shown. More or fewer systems may be implemented alternatively.

[0091] Specifically, according to the embodiments disclosed in this application, the processes described above with reference to the flowcharts can be implemented as computer software programs. For example, embodiments disclosed in this application include a computer program product comprising a computer program carried on a computer-readable medium, the computer program containing program code for performing the methods shown in the flowcharts. In such embodiments, the computer program can be downloaded and installed from a network via a communication device, or installed from storage device 1003, or installed from read-only memory 1002. When the computer program is executed by processing device 1001, it performs the functions defined in the methods of the embodiments disclosed in this application.

[0092] The electronic device provided in this application, employing the timing method described in the above embodiments, can solve the technical problem of how to improve the timing accuracy in aircraft racing. Compared with the prior art, the beneficial effects of the electronic device provided in this application are the same as those of the timing method provided in the above embodiments, and other technical features of this electronic device are the same as those disclosed in the previous embodiment method, and will not be repeated here.

[0093] It should be understood that the various parts disclosed in this application can be implemented using hardware, software, firmware, or a combination thereof. In the description of the above embodiments, specific features, structures, materials, or characteristics can be combined in any suitable manner in one or more embodiments or examples.

[0094] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

[0095] This application provides a computer-readable storage medium having computer-readable program instructions (i.e., a computer program) stored thereon, which are used to execute the timing method in the above embodiments.

[0096] The computer-readable storage medium provided in this application embodiment may be, for example, a USB flash drive, but is not limited to, electrical, magnetic, optical, electromagnetic, infrared, or semiconductor systems or devices, or any combination thereof. More specific examples of computer-readable storage media may include, but are not limited to: electrical connections having one or more wires, portable computer disks, hard disks, random access memory (RAM), read-only memory (ROM), erasable programmable read-only memory (EPROM or flash memory), optical fibers, portable compact disk read-only memory (CD-ROM), optical storage devices, magnetic storage devices, or any suitable combination thereof. In this embodiment, the computer-readable storage medium may be any tangible medium containing or storing a program that can be used by or in conjunction with an instruction execution system or device. The program code contained on the computer-readable storage medium may be transmitted using any suitable medium, including but not limited to: wires, optical cables, RF (Radio Frequency), etc., or any suitable combination thereof.

[0097] The aforementioned computer-readable storage medium may be included in an electronic device or may exist independently without being assembled into an electronic device.

[0098] The aforementioned computer-readable storage medium carries one or more programs. When the aforementioned one or more programs are executed by an electronic device, the electronic device causes the electronic device to: acquire the mass value monitored by the gravity sensing module; determine the control team to which the aircraft belongs via a conductive circuit board when the duration of the first target detected is greater than a preset hysteresis time, and control a timer to start timing; determine the landing time of the control team to which the aircraft belongs based on the duration data of the timer, wherein the duration of the first target is the duration of the mass value being greater than or equal to a preset threshold; and stop timing when the duration of the second target detected is greater than the hysteresis time, wherein the duration of the second target is the duration of the mass value being less than a preset threshold.

[0099] Computer program code for performing the operations of this application can be written in one or more programming languages ​​or a combination thereof, including object-oriented programming languages ​​such as Java, Smalltalk, and C++, and conventional procedural programming languages ​​such as the "C" language or similar programming languages. The program code can be executed 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 remote computers, the remote computer can 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 can be connected to an external computer (e.g., via the Internet using an Internet service provider).

[0100] 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 this application. In this regard, each block in a flowchart or block diagram may represent a module, segment, or portion of code containing one or more executable instructions for implementing a specified logical function. It should also be noted that in some alternative implementations, the functions indicated in the blocks may occur in a different order than those indicated in the drawings. For example, two consecutively indicated 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, can be implemented using a dedicated hardware-based system that performs the specified function or operation, or using a combination of dedicated hardware and computer instructions.

[0101] The modules described in the embodiments of this application can be implemented in software or hardware. The names of the modules do not necessarily limit the functionality of the unit itself.

[0102] The readable storage medium provided in this application is a computer-readable storage medium that stores computer-readable program instructions (i.e., a computer program) for executing the above-described timing method, thereby solving the technical problem of how to improve the timing accuracy of aircraft racing. Compared with the prior art, the beneficial effects of the computer-readable storage medium provided in this application are the same as those of the timing method provided in the above embodiments, and will not be repeated here.

[0103] This application also provides a computer program product, including a computer program that, when executed by a processor, implements the steps of the timing method described above.

[0104] The computer program product provided in this application can solve the technical problem of how to improve the timing accuracy of aircraft racing. Compared with the prior art, the beneficial effects of the computer program product provided in this application are the same as those of the timing method provided in the above embodiments, and will not be repeated here.

[0105] The above description is only a part of the embodiments of this application and does not limit the patent scope of this application. All equivalent structural transformations made under the technical concept of this application and using the contents of the specification and drawings of this application, or direct / indirect applications in other related technical fields, are included in the patent protection scope of this application.

Claims

1. A timing method, characterized in that, The timing method is applied to a central platform, which includes a gravity sensing module, a conductive circuit board, and a timer. The conductive circuit board is located on the landing surface of the central platform. The timing method includes: Obtain the mass value monitored by the gravity sensing module; If the duration of the first target detected is longer than a preset hysteresis time, the control team to which the aircraft belongs is determined by the conductive circuit board, and the timer is controlled to start timing. Based on the duration data of the timer, the landing duration of the control team to which the aircraft belongs is determined, wherein the duration of the first target is the duration of the mass value being greater than or equal to a preset threshold. If the duration of the second target is detected to be longer than the hysteresis time, the timer is controlled to stop counting, wherein the duration of the second target is the duration during which the quality value is less than the preset threshold.

2. The timing method as described in claim 1, characterized in that, The step of determining the control team to which the aircraft belongs via the conductive circuit board includes: The material state of the contact material of the aircraft is determined by the conductive circuit board, wherein the material state includes a conductive state and a non-conductive state; The control team to which the aircraft belongs is determined based on the material condition of the aircraft.

3. The timing method as described in claim 2, characterized in that, The control team includes a conductive team and a non-conductive team, the timer includes a first timer and a second timer, and the step of controlling the timer to start timing includes: If the control team to which the aircraft belongs is a communication team, control the first timer to start timing; If the control team to which the aircraft belongs is a non-guided team, the second timer is started.

4. The timing method as described in claim 1, characterized in that, The central platform includes a countdown module, and prior to the step of acquiring the mass value detected by the gravity sensor module, it further includes: Determine whether the countdown module has reset to zero; If the countdown module's countdown timer has not reached zero, the steps of obtaining the mass value detected by the gravity sensor module and subsequent steps are executed. When the countdown module reaches zero, the step of controlling the timer to stop counting is executed.

5. The timing method as described in claim 4, characterized in that, The central platform includes a display, and the timing method further includes: The display shows the team score of each control team, the landing time of each control team's aircraft, and / or the countdown of the countdown module, wherein the team score is positively correlated with the landing time.

6. The timing method as described in claim 1, characterized in that, The central platform includes multiple sub-platforms, and the timing method further includes: For any sub-platform, if the duration of the first target on the sub-platform is longer than the hysteresis time, the control team of the aircraft landing on the sub-platform is determined by the conduction circuit board of the sub-platform, and the timer of the sub-platform is controlled to start timing. The landing duration of the sub-platform is determined based on the timing data of the timer. In cases where at least two sub-platforms have the same control team, the sum of the landing times of the sub-platforms with the same control team is determined as the landing time of the control team.

7. The timing method as described in claim 1, characterized in that, The gravity sensing module includes multiple S-shaped strain gauge sensors connected in a bridge configuration.

8. An electronic device, characterized in that, The electronic device includes: a memory, a processor, and a computer program stored in the memory and executable on the processor, the computer program being configured to implement the steps of the timing method as described in any one of claims 1 to 7.

9. A storage medium, characterized in that, The storage medium is a computer-readable storage medium, and a computer program is stored on the storage medium. When the computer program is executed by a processor, it implements the steps of the timing method as described in any one of claims 1 to 7.

10. A computer program product, characterized in that, The computer program product includes a computer program that, when executed by a processor, implements the steps of the timing method as described in any one of claims 1 to 7.

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