阅读说明：本技术 一种无人机多余度传感器管理方法、系统及无人机 (Unmanned aerial vehicle redundancy sensor management method and system and unmanned aerial vehicle ) 是由 廖新涛 侯利洋 张帅华 王文龙 刘宇 郭宏选 于 2021-11-15 设计创作，主要内容包括：本申请涉及无人机技术领域,尤其涉及一种无人机多余度传感器管理方法、系统及无人机,其方法为：先按传感器次序依次判断数据类型所对应的多个传感器的标志信息是否正常,若异常则继续判断下一个传感器次序的标志信息,若正常则获取此传感器的当前状态,然后判断此传感器的当前状态是否正常,若异常则继续判断下一个传感器次序的当前状态,若正常则将此数据类型的采集信号源设置为此传感器。本申请提供的无人机多余度传感器管理方法、系统及无人机,能够对多类型传感器进行集中管理,进而有效的获取各种所需的飞行数据。(The application relates to the technical field of unmanned aerial vehicles, in particular to a management method and a system for redundancy sensors of an unmanned aerial vehicle and the unmanned aerial vehicle, wherein the method comprises the following steps: the method comprises the steps of sequentially judging whether mark information of a plurality of sensors corresponding to a data type is normal according to a sensor sequence, if so, continuously judging mark information of a next sensor sequence, if so, acquiring the current state of the sensor, then, judging whether the current state of the sensor is normal, if so, continuously judging the current state of the next sensor sequence, and if so, setting a data type acquisition signal source as the sensor. The unmanned aerial vehicle redundancy sensor management method and system and the unmanned aerial vehicle can be used for carrying out centralized management on various types of sensors and further effectively obtaining various required flight data.)

1. An unmanned aerial vehicle redundancy sensor management method is characterized by comprising the following steps:

s1, acquiring i sensors and sensor sequences corresponding to data types according to the data types to be acquired;

s2, judging whether the mark information of the sensor corresponding to the sensor sequence is normal or not according to the sensor sequence;

s3, if the mark information is normal, acquiring the current state of the jth sensor corresponding to the mark and entering S5;

s4, if the mark information is abnormal, acquiring the mark information of the j +1 th sensor and returning to S2;

s5, judging whether the current state of the sensor is normal or not;

s6, if the current state is normal, setting a collecting signal source corresponding to the data type as a jth sensor corresponding to the current state;

s7, if the current state is abnormal, acquiring the current state of the (j + 1) th sensor and returning to S5;

wherein i is more than or equal to 2, j is more than or equal to 1 and less than i, and the sensor sequence is the arrangement sequence of the i sensors corresponding to the data type from 1 to i.

2. The method as claimed in claim 1, wherein the step S4 of obtaining the flag information of the (j + 1) th sensor and returning to S2 if the flag information is abnormal includes:

s41, if the mark information is abnormal, comparing j +1 with i;

s42, if j +1 is less than i, acquiring the mark information of the j +1 th sensor and returning to S2;

and S43, if j +1= i, setting the acquisition signal source corresponding to the data type as the 1 st sensor and interrupting execution.

3. The method of claim 1, wherein the step S7 of obtaining the current status of the j +1 th sensor and returning to S5 if the current status is abnormal comprises:

s71, if the current state is abnormal, comparing j +1 with i;

s72, if j +1 is less than i, acquiring the current state of the j +1 th sensor and returning to S5;

and S73, if j +1= i, setting the acquisition signal source corresponding to the data type as the 1 st sensor and interrupting execution.

4. The unmanned aerial vehicle redundancy sensor management method of claim 1, wherein when the type of data required to be collected is angular rate, i =3 and the sensor order is primary inertial navigation, standby inertial navigation and rate gyro sequentially.

5. The unmanned aerial vehicle redundancy sensor management method according to claim 1, wherein when the type of data to be collected is a flight attitude, i =3 and the sensor sequence is primary inertial navigation, standby inertial navigation and vertical gyro sequentially.

6. The method of claim 1, wherein when the type of data to be acquired is one of relative ground speed, flight position and track angle, i =3 and the sensor sequence is primary satellite, primary inertial navigation and standby inertial navigation.

7. The unmanned aerial vehicle redundancy sensor management method of claim 1, wherein when the type of data required to be acquired is one of altitude and lifting rate, i =4 and the sensor order is primary satellite, primary inertial navigation, backup inertial navigation, and atmospheric air movement in sequence.

8. The unmanned aerial vehicle redundancy sensor management method of claim 1, wherein when the type of data to be collected is a true heading, i =2 and the sensor order is primary inertial navigation, GPS, in that order.

9. An unmanned aerial vehicle redundancy sensor management system based on the unmanned aerial vehicle redundancy sensor management method according to any one of claims 1 to 8, comprising:

the type acquisition module is used for acquiring the type of the data to be acquired;

the order acquisition module is connected with the type judgment module and used for acquiring a plurality of corresponding sensors and sensor orders according to the data types;

the sensor module is used for acquiring flight data corresponding to the data type;

the mark acquisition module is connected with the sensor module and used for acquiring mark information of the sensor;

the mark judging module is connected with the mark acquiring module and used for judging whether the mark information is normal or not;

the state acquisition module is connected with the sensor module and used for acquiring the current state of the sensor;

the state judgment module is connected with the state acquisition module and used for judging whether the current state is normal or not;

the signal source module is connected with the sensor module and is used for setting the acquisition signal source corresponding to the data type as the corresponding sensor;

the sensor module comprises at least one sensor of a main satellite, a main inertial navigation system, a standby inertial navigation system, a rate gyro, a vertical gyro, an air engine and a GPS.

10. A drone, characterized in that it comprises a drone redundancy sensor management system according to claim 9.

Technical Field

The application relates to the technical field of unmanned aerial vehicles, in particular to a management method and system for redundancy sensors of an unmanned aerial vehicle and the unmanned aerial vehicle.

Background

Along with the development of unmanned aerial vehicle technique, unmanned aerial vehicle's kind is more and more. And as a type of unmanned aerial vehicle with fixed wings, the sweepback angle of the outer ends of the wings can be automatically or manually adjusted along with the speed, the fixed wing unmanned aerial vehicle has the advantages of long endurance time, high-altitude flight and the like.

The fixed wing unmanned aerial vehicle is suitable for border cruising, tactical reconnaissance, public security monitoring, anti-terrorism, smuggling, drug control, disaster monitoring, forest fire prevention, communication relay, meteorological monitoring, geographic information reconnaissance and the like, and can simultaneously complete the fields of battlefield reconnaissance and monitoring, positioning calibration, damage assessment, electronic warfare and the like. This has just provided higher requirement to unmanned aerial vehicle's security, reliability.

The unmanned aerial vehicle flight control system carries out combined navigation attitude calculation by acquiring information of the sensor to obtain attitude, height, speed and position information of the aircraft, so that the aircraft is controlled to realize manual stability augmentation or automatic flight. The sensors comprise various sensors, such as a gyroscope, an accelerometer, a magnetometer, a barometer, a satellite positioning system and the like, the sensors are equivalent to an external sensing system of the airplane, the stability and reliability of original data of the sensors are the premise that the airplane can normally fly, how to effectively carry out centralized management on the various sensors is the technical problem which needs to be solved in the conventional flight control of the fixed-wing unmanned aerial vehicle.

Therefore, the unmanned aerial vehicle redundancy sensor management method and system capable of performing centralized management on multiple types of sensors and the unmanned aerial vehicle are provided, and the problem to be solved by technical personnel in the field is solved.

Disclosure of Invention

In order to carry out centralized management on various types of sensors in the flying process of a fixed-wing unmanned aerial vehicle and further effectively acquire various required flying data, the application provides an unmanned aerial vehicle redundancy sensor management method and system and an unmanned aerial vehicle.

In a first aspect, the application provides a method for managing redundancy sensors of an unmanned aerial vehicle, comprising the following steps:

s1, acquiring i sensors and sensor sequences corresponding to data types according to the data types to be acquired;

s2, judging whether the mark information of the sensor corresponding to the sensor sequence is normal or not according to the sensor sequence;

s3, if the mark information is normal, acquiring the current state of the jth sensor corresponding to the mark and entering S5;

s4, if the mark information is abnormal, acquiring the mark information of the j +1 th sensor and returning to S2;

s5, judging whether the current state of the sensor is normal or not;

s6, if the current state is normal, setting a collecting signal source corresponding to the data type as a jth sensor corresponding to the current state;

s7, if the current state is abnormal, acquiring the current state of the (j + 1) th sensor and returning to S5;

wherein i is more than or equal to 2, j is more than or equal to 1 and less than i, and the sensor sequence is the arrangement sequence of the i sensors corresponding to the data type from 1 to i.

According to the technical scheme, whether the mark information of a plurality of sensors corresponding to the data type is normal or not is sequentially judged according to the sequence of the sensors, if the mark information is abnormal, the mark information of the next sensor sequence is continuously judged, if the mark information is normal, the current state of the sensor is obtained, then, whether the current state of the sensor is normal or not is judged, if the mark information is abnormal, the current state of the next sensor sequence is continuously judged, and if the mark information is normal, the acquisition signal source of the data type is set as the sensor. As the i sensors corresponding to the data types and the sensor sequences of the sensors are preset, the flight data which correspond to the data types and can be acquired practically at present can be acquired subsequently directly according to the judgment of the mark information and the current state, the method is simple and convenient, the centralized management can be carried out on the sensors of the multiple types, and then the various required flight data can be acquired effectively.

Preferably, the step S4, if the flag information is abnormal, acquiring the flag information of the j +1 th sensor and returning to S2 includes:

s41, if the mark information is abnormal, comparing j +1 with i;

s42, if j +1 is less than i, acquiring the mark information of the j +1 th sensor and returning to S2;

and S43, if j +1= i, setting the acquisition signal source corresponding to the data type as the 1 st sensor and interrupting execution.

Through the technical scheme, when the mark information of the ith sensor, namely the last 1-order sensor corresponding to the data type, is abnormal, the acquisition signal source is set as the 1 st sensor, namely the default sensor, otherwise, the mark information of the (j + 1) th sensor is acquired and the step S2 is returned, so that when each sensor breaks down or corresponding data cannot be directly acquired, a corresponding processing mode can be provided, and the situation that the acquisition signal source cannot be acquired when the mark information of all the sensors is abnormal is avoided.

Preferably, the step S7, that is, if the current state is abnormal, acquiring the current state of the j +1 th sensor and returning to S5 includes:

s71, if the current state is abnormal, comparing j +1 with i;

s72, if j +1 is less than i, acquiring the current state of the j +1 th sensor and returning to S5;

and S73, if j +1= i, setting the acquisition signal source corresponding to the data type as the 1 st sensor and interrupting execution.

Through the technical scheme, when the current state of the ith sensor, namely the last 1-order sensor corresponding to the data type, is abnormal, the acquisition signal source is set as the 1 st sensor, namely the default sensor, otherwise, the current state of the (j + 1) th sensor is acquired, and the step S5 is returned, so that when each sensor breaks down or corresponding data cannot be directly acquired, a corresponding processing mode can be provided, and the situation that the acquisition signal source cannot be acquired when the current states of all the sensors are abnormal is avoided.

Preferably, when the type of data to be acquired is angular rate, i =3 and the sensor sequence is primary inertial navigation, secondary inertial navigation and rate gyro.

Through the technical scheme, when the data type is the angular rate, the number of the corresponding sensors is 3, the corresponding sensor sequences are the main inertial navigation, the standby inertial navigation and the rate gyro in sequence, namely the default sensor is the main inertial navigation, and the last 1 sensor sequence is the speed gyro, so that the centralized management of the corresponding sensors of the angular rate is realized.

Preferably, when the type of the data to be acquired is flight attitude, i =3 and the sensor sequence is main inertial navigation, standby inertial navigation and vertical gyro sequentially.

Through the technical scheme, when the data type is the flight attitude, the number of the corresponding sensors is 3, the corresponding sensors are sequentially the main inertial navigation, the standby inertial navigation and the vertical gyro in sequence, namely the default sensor is the main inertial navigation, and the last 1 sensor in sequence is the vertical gyro, so that the centralized management of the corresponding sensors of the flight attitude is realized.

Preferably, when the type of data to be acquired is one of relative ground speed, flight position and track angle, i =3 and the sensor sequence is primary satellite, primary inertial navigation and standby inertial navigation.

Through the technical scheme, when the data type is at least one of the relative ground speed, the flight position and the track angle, the number of the corresponding sensors is 3, the corresponding sensors are sequentially the main satellite, the main inertial navigation and the standby inertial navigation, namely, the default sensor is the main satellite, and the last 1 sensor is the standby inertial navigation, so that the centralized management of the corresponding sensors of the relative ground speed, the flight position and the track angle is realized.

Preferably, when the type of data to be acquired is one of altitude and lifting rate, i =4 and the sensor sequence is, in turn, a main satellite, a main inertial navigation system, a standby inertial navigation system and an air compressor.

Through the technical scheme, when the data type is at least one of the altitude and the lifting rate, the number of the corresponding sensors is 4, the corresponding sensor sequence is a main satellite, a main inertial navigation device, a standby inertial navigation device and an atmospheric engine in sequence, namely, the default sensor is the main satellite, and the last 1 sequence sensor is the atmospheric engine, so that the centralized management of the corresponding sensors of the altitude and the lifting rate is realized.

Preferably, when the type of the data to be acquired is a true heading, i =2 and the sensor sequence is primary inertial navigation and GPS in turn.

Through the technical scheme, when the data type is the true heading, the number of the corresponding sensors is 2, the corresponding sensor sequence is the main inertial navigation and the GPS, namely the default sensor is the main inertial navigation, and the last 1 sensor sequence is the GPS, so that the centralized management of the corresponding sensors of the flight attitude is realized.

In a second aspect, the present application further provides an unmanned aerial vehicle redundancy sensor management system, based on any of the above methods for unmanned aerial vehicle redundancy sensor management, including:

the type acquisition module is used for acquiring the type of the data to be acquired;

the order acquisition module is connected with the type judgment module and used for acquiring a plurality of corresponding sensors and sensor orders according to the data types;

the sensor module is used for acquiring flight data corresponding to the data type;

the mark acquisition module is connected with the sensor module and used for acquiring mark information of the sensor;

the mark judging module is connected with the mark acquiring module and used for judging whether the mark information is normal or not;

the state acquisition module is connected with the sensor module and used for acquiring the current state of the sensor;

the state judgment module is connected with the state acquisition module and used for judging whether the current state is normal or not;

the signal source module is connected with the sensor module and is used for setting the acquisition signal source corresponding to the data type as the corresponding sensor;

the sensor module comprises at least one sensor of a main satellite, a main inertial navigation system, a standby inertial navigation system, a rate gyro, a vertical gyro, an air engine and a GPS.

According to the technical scheme, based on the unmanned aerial vehicle redundancy sensor management method, the sequence acquisition module is only needed to read the i sensors corresponding to each preset data type and the sensor sequences of the sensors, the subsequent mark judgment module and the state judgment module can directly judge mark information and the current state, so that the signal source module acquires the flight data corresponding to the data type from the sensor module, the flight data required to be acquired can be acquired practically at present, the method is simple and convenient, the sensors of multiple types can be managed in a centralized mode, and then various required flight data can be acquired effectively.

In a third aspect, the present application further provides a fixed wing drone, including a drone redundancy sensor management system as described above.

Through above-mentioned technical scheme for fixed wing unmanned aerial vehicle possesses aforementioned unmanned aerial vehicle redundancy sensor management system's technological effect.

To sum up, this application only needs to set up i sensors that each data type corresponds and the sensor order of these sensors in advance, follow-up just can be directly according to the judgement of sign information and current state, acquires the flight data that correspond with the data type and can obtain required collection at present conscientiously, and is simple convenient, can carry out centralized management to the polymorphic type sensor, and then the effectual various required flight data that acquire, solves the problem that the redundancy sensor is difficult to carry out effective centralized management.

Drawings

Fig. 1 is a schematic flow chart of one implementation of a method for managing redundancy sensors of an unmanned aerial vehicle according to an embodiment of the present application;

fig. 2 is a schematic flow chart of one implementation of a method for managing redundancy sensors of an unmanned aerial vehicle according to an embodiment of the present application;

fig. 3 is a block diagram of a structure of one implementation of the unmanned aerial vehicle redundancy sensor management system according to the embodiment of the present application.

Detailed Description

In order to make those skilled in the art better understand the technical solutions in the present application, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are only a part of the embodiments of the present application, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.

The embodiment of the application provides a method for managing redundancy sensors of an unmanned aerial vehicle, which comprises the following steps as shown in figure 1:

s1, acquiring i sensors corresponding to data types and sensor sequences according to the data types needing to be acquired;

s2, judging whether the mark information of the sensor corresponding to the sensor sequence is normal or not according to the sensor sequence;

s3, if the mark information is normal, acquiring the current state of the jth sensor corresponding to the mark and entering S5;

s4, if the mark information is abnormal, acquiring the mark information of the j +1 th sensor and returning to S2;

s5, judging whether the current state of the sensor is normal or not;

s6, if the current state is normal, setting a collecting signal source corresponding to the data type as a jth sensor corresponding to the current state;

s7, if the current state is abnormal, acquiring the current state of the (j + 1) th sensor and returning to S5;

wherein i is more than or equal to 2, j is more than or equal to 1 and less than i, and the sensor sequence is the arrangement sequence of i sensors corresponding to the data types from 1 to i.

The type of data to be collected in step S1 refers to various flight data that needs to be collected by the fixed-wing drone during flight, including but not limited to at least one of angular rate, flight attitude, relative ground speed, altitude, flight position, lift rate, track angle, and true heading. And generally can set up the redundancy sensor on the unmanned aerial vehicle, each flight data all can correspond a plurality of sensors promptly for each data possess multiple collection or acquire the source, form the redundancy mechanism.

The sensor sequence is a sub-sequence table or sequence information formed by a plurality of corresponding sensors according to a certain sequence and a certain data type, and corresponding calling can be directly carried out according to the data type when needed.

In step S2, it is determined whether the flag information of the corresponding sensor is normal according to the sensor order, that is, it is determined whether the flag information of the sensor in the 1 st order is normal according to the pre-formed order, and the subsequent processing of steps S3 and S4 is determined according to the determination result.

If it is determined in step S3 that the flag information of the jth sensor in the jth sequence, i.e., the sensor sequence, is normal, indicating that the sensor is the current signal source, the method proceeds to step S5 after the current state of the sensor is continuously obtained. It should be noted that the current state of the sensor is different from the meaning corresponding to the flag information, and the flag information indicates whether the sensor is a current signal source, and the current state represents whether the working state of the sensor is normal, for example, whether communication or data transmission is possible, or whether data required to be acquired can be normally acquired, and whether the acquired data meets a preset format or preset requirements.

In step S4, the flag information of the jth sensor in the jth sequence, i.e., the sensor sequence, is also determined, and different from step S3, the flag information of the sensor is abnormal, which indicates that the sensor is not the current signal source, at this time, the flag information of the jth sensor in the next sequence, i.e., the sensor sequence, is obtained instead, and the process returns to step S2, and the flag information of the jth sensor +1 is determined to be normal or not.

In returning to step S2, j +1 is set as the updated value of j. That is, if it is determined in step S4 that the flag information of the 2 nd sensor is abnormal, the flag information of the 3 rd sensor is acquired and sent back to step S2 to be determined, if normal, the current state of the 3 rd sensor is acquired in step S3 this time, and if abnormal, the flag information of the 4 th sensor continues to be acquired in step S4.

In step S5, whether the current state acquired in step S3 is normal or not is determined according to the determination result, and the subsequent processing in steps S6 and S7 is determined.

If the current state is normal in step S6, the signal source corresponding to the data type in step S1 is set as the jth sensor corresponding to the current state and the execution is interrupted, that is, the jth sensor corresponding to the current state obtained in step S3 is obtained, and the flight data required to be collected by the data type is obtained from the jth sensor.

If the current state is abnormal in step S7, the current state of the (j + 1) th sensor in the next sequence, that is, the sensor sequence, is obtained instead, and the process returns to step S5 to determine the current state of the (j + 1) th sensor.

In returning to step S5, j +1 is set as the updated value of j. That is, if it is determined in step S7 that the current state of the 2 nd sensor is abnormal, the current state of the 3 rd sensor is acquired and returned to step S5 to make the determination, and if it is normal, the current state of the 3 rd sensor is acquired in step S6 this time, and if it is abnormal, the current state of the 4 th sensor continues to be acquired in step S7.

According to the technical scheme, whether the mark information of a plurality of sensors corresponding to the data type is normal or not is sequentially judged according to the sequence of the sensors, if the mark information is abnormal, the mark information of the next sensor sequence is continuously judged, if the mark information is normal, the current state of the sensor is obtained, then, whether the current state of the sensor is normal or not is judged, if the mark information is abnormal, the current state of the next sensor sequence is continuously judged, and if the mark information is normal, the acquisition signal source of the data type is set as the sensor.

Different flight data can be obtained through a plurality of sensors or sensor redundancy, and the redundancy management of the sensors is in a master-slave switching mode in consideration of the performance difference of different sensors. If the current redundancy is abnormal, namely the current sensor is abnormal, switching to the first standby redundancy, namely the 2 nd sensor in the sensor sequence, if the first standby redundancy is abnormal, continuing switching to the second standby redundancy, namely the 3 rd sensor in the sensor sequence, and the like; if all the redundancies are abnormal, the default redundancy is used.

As the i sensors corresponding to the data types and the sensor sequences of the sensors are preset, the flight data which correspond to the data types and can be acquired practically at present can be acquired subsequently directly according to the judgment of the mark information and the current state, the method is simple and convenient, the centralized management can be carried out on the sensors of the multiple types, and then the various required flight data can be acquired effectively.

In one implementation of the embodiment of the present application, as shown in fig. 2, the step S4, namely, if the flag information is abnormal, the step S2 of obtaining the flag information of the j +1 th sensor includes:

s41, if the mark information is abnormal, comparing j +1 with i;

s42, if j +1 is less than i, acquiring the mark information of the j +1 th sensor and returning to S2;

and S43, if j +1= i, setting the acquisition signal source corresponding to the data type as the 1 st sensor and interrupting execution.

In practical applications, due to various factors or reasons, it may occasionally happen that the flag information of all the sensors is abnormal, and the i-th sensor described in step S43 is also the last 1 sensor in the sensor sequence, and if the flag information of this sensor is abnormal, it indicates that the flag information of all the sensors in the sensor sequence is abnormal, so the acquisition signal source corresponding to the data type is directly set as the 1 st sensor, that is, the corresponding conventional default sensor.

Of course, according to actual needs, when the marker information of the ith sensor is abnormal, the marker information of the (i-1) th sensor is determined again, and when the marker information of the (i-2) th sensor is abnormal again, the marker information of the (i-2) th sensor is determined again, and so on.

Or, when the marker information of the ith sensor is abnormal, after the preset time, the marker information of the ith sensor is judged again, if the marker information of the ith sensor is abnormal, the marker information of the (i-1) th sensor is judged again, if the marker information of the (i-2) th sensor is abnormal again, and the like.

Through the technical scheme, when the mark information of the ith sensor, namely the sensor in the last 1 order corresponding to the data type, is abnormal, the acquisition signal source is set to be the 1 st sensor, namely the default sensor, so that when all the sensors are not the current signal source, a corresponding processing mode can be provided, and the situation that the acquisition signal source cannot be acquired when the mark information of all the sensors is abnormal is avoided.

In one implementation of the embodiment of the present application, as shown in fig. 2, the step S7, namely, if the current state is abnormal, the acquiring the current state of the j +1 th sensor and returning to S5 includes:

s71, if the current state is abnormal, comparing j +1 with i;

s72, if j +1 is less than i, acquiring the current state of the j +1 th sensor and returning to S5;

and S73, if j +1= i, setting the acquisition signal source corresponding to the data type as the 1 st sensor and interrupting the execution.

In practical application, due to various factors or reasons, the current states of all the sensors are abnormal occasionally, and the ith sensor described in step 73 is also the last 1 sensor in the sensor sequence, and if the current state of the sensor is abnormal, it indicates that the current states of all the sensors in the sensor sequence are abnormal, so the acquisition signal source corresponding to the data type is directly set as the 1 st sensor, that is, the acquisition signal source corresponds to the conventional default sensor.

Of course, according to actual needs, when the current state of the ith sensor is abnormal, the current state of the (i-1) th sensor is determined again, and when the current state of the (i-2) th sensor is abnormal again, the current state of the (i-2) th sensor is determined again, and so on.

Or, when the current state of the ith sensor is abnormal, after a preset time, the current state of the ith sensor is judged again, if the current state of the ith sensor is abnormal, the current state of the (i-1) th sensor is judged again, and if the current state of the (i-2) th sensor is abnormal again, the current state of the (i-2) th sensor is judged again, and so on.

Through the technical scheme, when the current state of the ith sensor, namely the sensor in the last 1 order corresponding to the data type, is abnormal, the acquisition signal source is set as the 1 st sensor, namely the default sensor, so that when each sensor breaks down or corresponding data cannot be directly acquired, a corresponding processing mode can be provided, and the situation that the acquisition signal source cannot be acquired when the current state of all the sensors is abnormal is avoided.

In practice, the sensors can acquire flight data including, but not limited to, at least one of angular velocity, flight attitude, relative ground speed, altitude, flight position, lift rate, track angle and true heading, and some sensors can acquire various flight data. Therefore, according to different data types required to be acquired by flight, different sensor types and corresponding sensor sequences can be provided, including various situations, as follows:

in one implementation of the embodiment of the present application, when the data type is angular rate, i =3 and the sensor sequence is primary inertial navigation, secondary inertial navigation, and rate gyro.

Namely, the angular velocity corresponds to 3 sensors, and the order of the sensors is main inertial navigation, standby inertial navigation and rate gyro in sequence, so that when the sign information or the current state is judged, the 1 st sensor is main inertial navigation, the 2 nd sensor is standby inertial navigation, the 3 rd sensor is rate gyro, wherein the main inertial navigation is taken as a default sensor corresponding to the angular velocity.

Through the technical scheme, the centralized management of the corresponding sensors of the angular rate is realized.

In one implementation manner of the embodiment of the present application, when the type of data to be acquired is a flight attitude, i =3, and the sensor sequence is a main inertial navigation system, a standby inertial navigation system, and a vertical gyro.

That is, the flying attitude corresponds to 3 sensors, and the order of the sensors is main inertial navigation, standby inertial navigation and vertical gyro in sequence, so that when the sign information or the current state is judged, the 1 st sensor is main inertial navigation, the 2 nd sensor is standby inertial navigation, the 3 rd sensor is vertical gyro, wherein the main inertial navigation is taken as the default sensor corresponding to the flying attitude.

Through the technical scheme, the centralized management of the corresponding sensors of the flight attitude is realized.

In one implementation of the embodiment of the present application, when the type of data to be acquired is one of a relative ground speed, a flight position, and a track angle, i =3 and the sensor sequence is, in turn, a primary satellite, a primary inertial navigation, and a secondary inertial navigation.

Namely, the relative ground speed, the flight position and the track angle all correspond to 3 sensors, and the sensor sequence is the main satellite, the main inertial navigation and the standby inertial navigation in sequence, so that when the mark information or the current state is judged, the 1 st sensor is the main satellite, the 2 nd sensor is the main inertial navigation and the 3 rd sensor is the standby inertial navigation, wherein the main satellite is used as a default sensor corresponding to the ground speed, the flight position and the track angle.

Through the technical scheme, the centralized management of the sensors corresponding to the relative ground speed, the flight position and the track angle is realized.

In one implementation of the embodiment of the present application, when the type of data to be acquired is one of an altitude and a lifting rate, i =4, and the sensor sequence is, in turn, a primary satellite, a primary inertial navigation system, a secondary inertial navigation system, and an air compressor.

That is, altitude and lifting rate all correspond 4 sensors, and the sensor order is main satellite, main inertial navigation, is equipped with inertial navigation, atmospheric engine in proper order to when judging sign information or current state, 1 st sensor is main satellite, and 2 nd sensor is main inertial navigation, and 3 rd sensor is for being equipped with inertial navigation, and 4 th sensor is atmospheric engine, and wherein main satellite is as the acquiescence sensor that altitude and lifting rate correspond.

Through the technical scheme, the centralized management of the corresponding sensors of the altitude and the lifting speed is realized.

In one implementation manner of the embodiment of the present application, when the type of data to be collected is a true heading, i =2 and the sensor sequence is the primary inertial navigation and the GPS in turn.

That is, the true course corresponds to 2 sensors, and the order of the sensors is the main inertial navigation and the GPS in sequence, so that when the flag information or the current state is judged, the 1 st sensor is the main inertial navigation, the 2 nd sensor is the GPS, wherein the main inertial navigation is taken as the default sensor corresponding to the true course.

Through the technical scheme, the centralized management of the corresponding sensors of the altitude and the lifting speed is realized.

Simultaneously, this application still provides an unmanned aerial vehicle redundancy sensor management system, based on as above-mentioned any one unmanned aerial vehicle redundancy sensor management method, as shown in fig. 3, include:

the type acquisition module 1 is used for acquiring the type of data to be acquired;

the order acquisition module 2 is connected with the type judgment module 1 and is used for acquiring a plurality of corresponding sensors and sensor orders according to the data types;

the sensor module 3 is used for acquiring flight data corresponding to the data type;

the mark acquisition module 4 is connected with the sensor module 3 and used for acquiring mark information of the sensor;

the mark judging module 5 is connected with the mark acquiring module 4 and used for judging whether the mark information is normal or not;

the state acquisition module 6 is connected with the sensor module 3 and used for acquiring the current state of the sensor;

the state judgment module 7 is connected with the state acquisition module 6 and used for judging whether the current state is normal or not;

the signal source module 8 is connected with the sensor module 3 and is used for setting the acquisition signal source corresponding to the data type as a corresponding sensor;

the sensor module 3 comprises at least one sensor of a main satellite, a main inertial navigation system, a standby inertial navigation system, a rate gyro, a vertical gyro, an air engine and a GPS.

In actual use, the operation steps and the data transmission relation among the modules can refer to the unmanned aerial vehicle redundancy sensor management method, the same technical effects are achieved, and the description is omitted.

According to the technical scheme, based on the unmanned aerial vehicle redundancy sensor management method, the sequence acquisition module is only needed to read the i sensors corresponding to each preset data type and the sensor sequences of the sensors, the subsequent mark judgment module and the state judgment module can directly judge mark information and the current state, so that the signal source module acquires the flight data corresponding to the data type from the sensor module, the flight data required to be acquired can be acquired practically at present, the method is simple and convenient, the sensors of multiple types can be managed in a centralized mode, and then various required flight data can be acquired effectively.

In addition, this application still provides a fixed wing unmanned aerial vehicle, include as above unmanned aerial vehicle redundancy sensor management system.

In practical use, the fixed-wing drone can refer to the drone redundancy sensor management method and system for acquiring flight data, and has the same technical effects, and the description is not repeated here.

Through above-mentioned technical scheme for fixed wing unmanned aerial vehicle possesses aforementioned unmanned aerial vehicle redundancy sensor management system's technological effect.

It is further noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other identical elements in a process, method, article, or apparatus that comprises the element.

It should be understood that, although the steps in the flowcharts of the figures are shown in order as indicated by the arrows, the steps are not necessarily performed in order as indicated by the arrows. The steps are not performed in the exact order shown and may be performed in other orders unless explicitly stated herein. Moreover, at least a portion of the steps in the flow chart of the figure may include multiple sub-steps or multiple stages, which are not necessarily performed at the same time, but may be performed at different times, which are not necessarily performed in sequence, but may be performed alternately or alternately with other steps or at least a portion of the sub-steps or stages of other steps.

The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present application. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the application. Thus, the present application is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.