CN115056970A - Method and system for automatically adjusting gravity center of electric airplane, electronic equipment and storage medium - Google Patents
Method and system for automatically adjusting gravity center of electric airplane, electronic equipment and storage medium Download PDFInfo
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D11/00—Passenger or crew accommodation; Flight-deck installations not otherwise provided for
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Abstract
The invention discloses an automatic gravity center adjusting method and system for an electric airplane, electronic equipment and a storage medium, wherein the method comprises the following steps: s1: acquiring measurement data of a weight sensor and a position sensor of each seat; s2: calculating the weight center of gravity of the whole computer; s3: acquiring an optimal position and a moving path of each seat; s4: driving the automatic moving seat position to the optimal scheme position; s5: calculating the weight center of gravity of the whole computer again; s6: acquiring an optimal position, judging whether the center of gravity of the whole aircraft is in the optimal position, if so, continuing to step S7, otherwise, continuing to operate steps S2-S6 until the center of gravity of the whole aircraft is in the optimal position, and continuing to step S7; s7: and locking the seat position. The invention solves the technical problems that the existing airplane has different weights of people on different seats before the airplane is started, the number of passengers is singular, or the whole gravity center of the airplane is shifted due to the movement of people in the airplane navigation process, and the movement state and the flight quality of the airplane are difficult to ensure.
Description
Technical Field
The embodiment of the invention relates to the technical field of aircraft balancing systems, in particular to an automatic gravity center adjusting method and system for an electric aircraft, electronic equipment and a storage medium.
Background
At present, the range of the front limit and the rear limit of the gravity center of a large airplane is large, and the influence of the change of the whole gravity center of the airplane caused by the unbalanced weight of people on a plurality of seats is small. For small aircraft, the weight difference of passengers on different seats or the influence on the center of gravity of the aircraft when the seats are not full is large, which affects the maneuvering quality of the aircraft.
However, with the improvement of the design requirement of the flexibility of the aircraft, under the normal expected operation condition, when the center of gravity of the aircraft moves in the direction unfavorable for the trim state, more design options are still needed to maintain the heading or lateral trim, for example, when the weight of personnel on different seats before the aircraft starts or the seats are not full, or the whole center of gravity of the aircraft deviates due to the movement of personnel during the aircraft navigation, the center of gravity position of the aircraft cannot be optimized through the movement of the seats, and therefore the purpose of stabilizing the attitude and the heading of the aircraft is difficult to achieve, so as to achieve the technical problem of ensuring the movement state of the aircraft and further influencing the flight quality.
It should be noted that although the present invention is directed to a four-seater small manned aircraft, the present invention is applicable to a large aircraft, and can still solve the problem that the flight quality of the aircraft is difficult to guarantee due to the change of the position of the center of gravity of the aircraft caused by the imbalance of members of the aircraft, but the algorithm and the automatic adjustment device are more complicated.
Disclosure of Invention
The embodiment of the invention aims to provide an automatic gravity center adjusting method, a system, electronic equipment and a storage medium for an electric aircraft, which are used for solving the technical problems that the gravity center position of the aircraft cannot be optimized through seat movement and the aim of stabilizing the attitude and the course of the aircraft is difficult to achieve so as to ensure the motion state of the aircraft and further influence the flight quality when the weights of personnel on different seats are different before the aircraft is started or the seats are not full or the personnel move during the aircraft navigation to cause the overall gravity center shift of the aircraft.
In order to achieve the above object, according to a first aspect of the present invention, there is provided an automatic center of gravity adjustment method for an electric aircraft, comprising the steps of:
s1: acquiring measurement data of a weight sensor and a position sensor of each seat;
s2: calculating the weight gravity center of the whole computer according to the equation of the whole computer;
s3: calculating according to a whole-machine gravity center optimal position algorithm to obtain an optimal position and a moving path of each seat;
s4: the seat motor is used for driving the seat to automatically move the seat position to the optimal scheme position;
s5: calculating the weight gravity center of the whole computer according to the whole computer equation again, and synchronizing the step S2;
s6: acquiring an optimal position, judging whether the gravity center of the whole machine is in the optimal position, if so, continuing to step S7, otherwise, returning to step S2, continuing to calculate the weight gravity center of the whole machine according to a whole machine equation, continuing to operate steps S3-S6, and continuing to step S7 until the gravity center of the whole machine is in the optimal position;
s7: and locking the seat position.
Further, the calculating the weight center of gravity of the whole computer according to the whole computer equation specifically includes:
the seat is provided with four groups, and the equation of the full-machine equation is as follows:
wherein G is i The weight of a person measured by a seat sensor of the seat, G is the total weight, G i Calculated and added to obtain G 0 The weight of the empty aircraft without the inclusion of personnel.
x i The position of the center of gravity, x, of the person corresponding to the seat g The position of the center of gravity of the whole machine in the x direction; y is i The position of the center of gravity of the person corresponding to the seat in the y direction g The position of the center of gravity of the whole machine in the y direction.
Further, the calculating according to the algorithm of the optimal position of the center of gravity of the whole machine to obtain the optimal position and the movement path of each seat specifically includes:
the full-machine gravity center optimal position algorithm is a multi-constraint equation solving process which comprises a seat x-direction gravity center position equation and a seat y-direction gravity center position equation.
Further, the equation of the seat x-direction gravity center position equation is:
wherein x is i The position of the center of gravity, x, of the person corresponding to the seat g The position of the center of gravity of the whole machine in the x direction.
Further, the equation of the seat y-direction gravity center position equation is:
wherein, y i The position of the center of gravity of the person corresponding to the seat in the y direction g The position of the center of gravity of the whole machine in the y direction.
Further, the origin of the coordinate system is the nose leading edge point, the x-axis is positive in the symmetrical plane of the fuselage, the y-axis is positive in the floor surface of the passenger cabin, and the left direction is positive.
The data of the front and rear limits of the gravity center and the left and right limits of the gravity center before the seat position is adjusted are obtained by calculating the six-degree-of-freedom force equation and the moment equation of the airplane and the efficiency of the control surface.
The data value of the front and rear limits of the gravity center is x f 、x b The data value of the left and right limits of the gravity center is x l 、x r 。
Further, x g Is located at the front and rear limits (x) of the center of gravity f 、x b ) Between data values.
y g Is located at the left and right limits of the center of gravity (x) l 、x r ) Between data values.
According to a second aspect of the invention, the invention also provides an automatic trim system for an electric aircraft, comprising:
the seat data acquisition module is used for acquiring the measurement data of the weight sensor and the position sensor of each seat;
the whole computer gravity center calculation module is used for calculating the weight gravity center of the whole computer according to a whole computer equation;
the seat position planning module is used for calculating according to a full-machine gravity center optimal position algorithm to obtain an optimal position and each seat moving path;
the seat driving control module is used for driving the seat motor to automatically move the seat position to the optimal scheme position;
the whole computer gravity center calculation module is also used for calculating the weight gravity center of the whole computer according to the whole computer equation again;
the whole-machine gravity center comparison module is used for acquiring an optimal position and judging whether the whole-machine gravity center is in the optimal position, if so, the seat position is locked, and if not, the whole-machine gravity center calculation module, the seat position planning module and the seat driving control module are reconfigured again until the whole-machine gravity center is in the optimal position, and the seat position is locked;
and the seat locking control module is used for locking the seat position.
According to a third aspect of the present invention, there is also provided an electronic device comprising a memory, a processor and a computer program stored on the memory and executable on the processor, the processor implementing the steps of the method when executing the computer program.
According to a fourth aspect of the invention, there is also provided a non-transitory computer readable storage medium having stored thereon a computer program which, when executed by a processor, performs the steps of the method.
The embodiment of the invention has the following advantages:
the method and the system can adapt to different numbers of seats according to the size of a cabin, after the initial position of each seat is preset, after a passenger sits before the airplane is started each time, or when the passenger moves in the airplane sailing process, the pressure sensor of the seat can detect the weight of the seated member on the seat in real time and the coordinate information of the seat is detected by the position sensor in real time and is provided for the processor, the processor automatically calculates the position coordinate where each seat in accordance with the gravity center envelope of the whole airplane should be located according to the preset gravity center envelope of the whole airplane, the current actual central position, the detected weight of the passenger and the coordinate distribution information, then converts the coordinate into the moving signals of the transverse moving motor and the longitudinal moving motor, finally drives each seat to move to the position coordinate respectively, and further realizes that the weights of the personnel on different seats before the airplane is started are different, or when the seat is not full or when the whole gravity center of the airplane deviates due to the movement of personnel in the navigation process of the airplane, the gravity center position of the airplane can be optimized by directly moving and balancing through the seat, so that the aim of stabilizing the attitude and the course of the airplane is effectively fulfilled, and the motion state of the airplane is guaranteed so as to improve the flight quality.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below. It should be apparent that the drawings in the following description are merely exemplary, and that other embodiments can be derived from the drawings provided by those of ordinary skill in the art without inventive effort.
The structures, ratios, sizes, and the like shown in the present specification are only used for matching with the contents disclosed in the specification, so as to be understood and read by those skilled in the art, and are not used to limit the conditions that the present invention can be implemented, so that the present invention has no technical significance, and any structural modifications, changes in the ratio relationship, or adjustments of the sizes, without affecting the effects and the achievable by the present invention, should still fall within the range that the technical contents disclosed in the present invention can cover.
Fig. 1 is a schematic flow chart of an automatic center of gravity adjustment method for an electric aircraft according to an embodiment of the present invention.
Fig. 2 is a schematic diagram illustrating a principle of an automatic trim system of an electric aircraft according to an embodiment of the present invention.
Fig. 3 is a schematic structural diagram of an electronic device according to an embodiment of the present invention.
Wherein the reference numerals are:
a seat data acquisition module 10; a whole-computer gravity center calculation module 20; a seat position planning module 30; a seat drive control module 40; a whole machine gravity center comparison module 50; a seat lock control module 60.
The electronic device 70: a processor 701, a memory 702, a bus 703.
Detailed Description
In order to make the technical solutions of the present invention better understood, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, 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 invention.
Also, the terms "mounted," "disposed," "provided," "connected," and "coupled" are to be construed broadly. For example, it may be a fixed connection, a removable connection, or a unitary construction; can be a mechanical connection, or an electrical connection; may be directly connected, or indirectly connected through intervening media, or may be in internal communication between two devices, elements or components. The specific meanings of the above terms in the present invention can be understood by those of ordinary skill in the art according to specific situations.
It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
At present, in the process of overall design and flight performance analysis of an aircraft, moment imbalance is inevitably caused by changes of speed, gravity center, aerodynamic shape and the like, so a trim system is usually required to compensate, and the trim system of the existing aircraft is usually mainly manually trimmed, Mach number trimmed, speed trimmed and the like.
With the improvement of the flexible design requirement of the aircraft, under the normal expected operation condition, when the gravity center of the aircraft moves towards the direction unfavorable for the trim state, the aircraft still needs to have more design options to maintain the heading trim, for example, the weight of personnel on different seats before the aircraft starts is different, or the whole gravity center of the aircraft deviates due to the movement of personnel in the aircraft navigation process, so that the trim cannot be directly moved through the seats, and the purpose of stabilizing the attitude and the heading of the aircraft is difficult to achieve, thereby ensuring the motion state of the aircraft. .
The invention is characterized in that different numbers of seats are adapted according to the size of a cabin, after the initial position of each seat is preset, after a passenger sits before an airplane is started or when the passenger moves in the airplane sailing process, the pressure sensor of the seat can detect the weight of the seated member on the seat in real time and the coordinate information of the seat in real time by the position sensor and provide the coordinate information to a processor, the processor automatically calculates the position coordinate where each seat in accordance with the gravity center envelope of the whole airplane should be located according to the preset gravity center envelope of the whole airplane, the current actual central position, the detected weight of the passenger and the coordinate distribution information, then converts the coordinate into the movement signals of a transverse movement motor and a longitudinal movement motor, and finally drives each seat to move to the position coordinate where each seat should be located. And then realize before the aircraft starts personnel's weight on the different seats respectively different, or when not full seat, or when the personnel in the aircraft navigation process moved and lead to the whole focus skew of aircraft, can directly remove the trim through the seat and carry out the focus position of optimizing the aircraft, and then effectively reach the purpose of stabilizing the gesture and the course of aircraft to the realization guarantees the motion state of aircraft and then promotes the flight quality.
The embodiment of the invention provides an automatic gravity center adjusting method for an electric airplane, and fig. 1 is a schematic flow chart of the automatic gravity center adjusting method for the electric airplane provided by the embodiment of the invention, and as shown in fig. 1, the method comprises the following steps:
s1: when the airplane is in the starting operation state, initializing system operation data and acquiring measurement data of the weight sensor and the position sensor of each seat.
S2: and calculating the weight gravity center of the whole computer according to the whole computer equation.
Taking four groups of seats as an example, the equation of the full-machine equation is as follows:
the original point of the coordinate system is the front edge point of the machine head, the x axis is on the symmetrical plane of the machine body and is positive backwards, the y axis is on the floor surface of the passenger cabin and is positive leftwards, and the variation of the height direction of the seat is small and is not considered.
G i The weight of a person measured by a seat sensor of the seat, G is the total weight, G i Calculated and added to obtain G 0 Is the empty weight of the aircraft excluding personnel.
x i The position of the center of gravity, x, of the person corresponding to the seat g The position of the center of gravity of the whole machine in the x direction; y is i The position of the center of gravity of the person corresponding to the seat in the y direction g The position of the center of gravity of the whole machine in the y direction.
S3: and calculating according to the algorithm of the optimal position of the center of gravity of the whole machine to obtain the optimal position and the movement path of each seat.
The full-machine center-of-gravity optimal position algorithm is actually a multi-constraint equation solving process, and comprises a seat x-direction center-of-gravity position equation and a seat y-direction center-of-gravity position equation.
Wherein the equation of the seat x-direction gravity center position equation is as follows:
the equation of the y-direction gravity center position equation of the seat is as follows:
the data of the front and rear limits and the left and right limits of the gravity center before the adjustment of the seat position are obtained by calculating the six-freedom-degree force equation, the moment equation and the efficiency of the control surface of the airplane, and only a set data value x of the front and rear limits of the gravity center is used f 、x b Center of gravity left and right limit x l 、x r Data values are only needed, and no calculation discussion is made.
G i The weight of a person measured by a seat sensor of the seat, G is the total weight, G i Calculated and added to obtain G 0 Is the empty weight of the aircraft excluding personnel.
x i The position of the center of gravity, x, of the person corresponding to the seat g The position of the center of gravity of the whole machine in the x direction; y is i The position of the center of gravity of the person corresponding to the seat in the y direction g The position of the center of gravity of the whole machine in the y direction.
x i The optimum position of (a) is required to satisfy the condition that the front-rear distance of the seat on which a person sits is as large as possible, x g In (x) f 、x b ) To (c) to (d); y is i The optimal position of (a) is required to satisfy that the left-right distance of the seat on which a person sits is as large as possible, y g Falling at the left and right limits of the center of gravity (x) l 、x r ) Between data values, and y g The | is as small as possible to reduce the lateral unbalance and improve the rudder efficiency; the target result can be better achieved using machine-learned algorithms.
S4: the seat motor is used for driving the seat to automatically move the seat position to the optimal scheme position.
S5: the weight center of gravity of the full machine is again calculated according to the full machine equation, step S2.
S6: and acquiring an optimal position, judging whether the gravity center of the whole machine is in the optimal position, if so, continuing to step S7, otherwise, returning to step S2, continuing to calculate the weight gravity center of the whole machine according to the whole machine equation, continuing to operate steps S3-S6, and continuing to step S7 until the gravity center of the whole machine is in the optimal position.
S7: and locking the seat position, and finishing the trimming process.
Fig. 2 is a schematic diagram illustrating a principle of composition of an automatic balancing system for an electric aircraft according to an embodiment of the present invention, and as shown in fig. 2, the system includes:
a seat data acquisition module 10 for acquiring measurement data of the weight sensor and the position sensor of each seat;
the whole computer gravity center calculation module 20 is used for calculating the weight gravity center of the whole computer according to a whole computer equation;
the seat position planning module 30 is used for calculating according to a full-aircraft gravity center optimal position algorithm to obtain an optimal position and each seat moving path;
the seat driving control module 40 is used for automatically moving the seat position to the optimal scheme position through seat motor driving;
the whole computer gravity center calculation module 20 is further used for calculating the weight gravity center of the whole computer according to the whole computer equation again;
and the whole-machine gravity center comparison module 50 is used for acquiring an optimal position and judging whether the whole-machine gravity center is in the optimal position, if so, the seat position is locked, and if not, the whole-machine gravity center calculation module 20, the seat position planning module 30 and the seat driving control module 40 are reconfigured again until the whole-machine gravity center is in the optimal position, and then the seat position is locked.
A seat lock control module 60 for seat position locking.
Fig. 3 is a schematic structural diagram of an entity of an electronic device 70 according to an embodiment of the present invention, and as shown in fig. 3, the electronic device 70 includes: a processor 701(processor), a memory 702(memory), and a bus 703.
The processor 701 and the memory 702 complete communication with each other through the bus 703.
Embodiments of the present invention further provide a non-transitory computer-readable storage medium, where the non-transitory computer-readable storage medium stores computer instructions, and the computer instructions enable a computer to execute the methods provided by the foregoing method embodiments, for example, the method includes: s1: acquiring measurement data of a weight sensor and a position sensor of each seat; s2: calculating the weight gravity center of the whole computer according to the equation of the whole computer; s3: calculating according to a whole-machine gravity center optimal position algorithm to obtain an optimal position and each seat moving path; s4: the seat motor is used for driving the seat to automatically move the seat position to the optimal scheme position; s5: calculating the weight gravity center of the whole computer according to the whole computer equation again, and synchronizing the step S2; s6: acquiring an optimal position, judging whether the gravity center of the whole machine is in the optimal position, if so, continuing to step S7, otherwise, returning to step S2, continuing to calculate the weight gravity center of the whole machine according to a whole machine equation, continuing to operate steps S3-S6, and continuing to step S7 until the gravity center of the whole machine is in the optimal position; s7: and locking the seat position.
Those of ordinary skill in the art will understand that: all or part of the steps for implementing the method embodiments may be implemented by hardware related to program instructions, and the program may be stored in a computer readable storage medium, and when executed, the program performs the steps including the method embodiments; and the aforementioned storage medium includes: various media that can store program codes, such as ROM, RAM, magnetic or optical disks.
Through the above description of the embodiments, those skilled in the art will clearly understand that each embodiment may be implemented by software plus a necessary general hardware platform, and may also be implemented by hardware. With this understanding in mind, the above-described technical solutions may be embodied in the form of a software product, which can be stored in a computer-readable storage medium, such as ROM/RAM, magnetic disk, optical disk, etc., and includes instructions for causing a computer device (which may be a personal computer, a server, or a network device, etc.) to execute the methods of the various embodiments or some parts of the embodiments.
Finally, it should be noted that: the above examples are only intended to illustrate the technical solution of the present invention, but not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.
Claims (10)
1. An automatic gravity center adjusting method for an electric airplane is characterized by comprising the following steps:
s1: acquiring measurement data of a weight sensor and a position sensor of each seat;
s2: calculating the weight gravity center of the whole computer according to the equation of the whole computer;
s3: calculating according to a whole-machine gravity center optimal position algorithm to obtain an optimal position and a moving path of each seat;
s4: the seat motor is used for driving the seat to automatically move the seat position to the optimal scheme position;
s5: calculating the weight gravity center of the whole computer according to the whole computer equation again, and synchronizing the step S2;
s6: acquiring an optimal position, judging whether the gravity center of the whole machine is in the optimal position, if so, continuing to step S7, otherwise, returning to step S2, continuing to calculate the weight gravity center of the whole machine according to a whole machine equation, continuing to operate steps S3-S6, and continuing to step S7 until the gravity center of the whole machine is in the optimal position;
s7: the seat position is locked.
2. The method for automatically adjusting the center of gravity of an electric aircraft according to claim 1,
the calculating of the weight center of gravity of the whole computer according to the whole computer equation specifically comprises:
the seat is provided with four groups, and the equation of the full-machine equation is as follows:
wherein G is i The weight of a person measured by a seat sensor of the seat, G is the total weight, G i Calculated and added to obtain G 0 Empty weight, excluding personnel;
x i the position of the center of gravity, x, of the person corresponding to the seat g The position of the center of gravity of the whole machine in the x direction; y is i The position of the center of gravity of the person corresponding to the seat in the y direction g The position of the center of gravity of the whole machine in the y direction.
3. The method for automatically adjusting the center of gravity of an electric aircraft according to claim 2,
the calculation is performed according to the algorithm of the optimal position of the center of gravity of the whole machine, so as to obtain the optimal position and the moving path of each seat, and the method specifically comprises the following steps:
the full-machine gravity center optimal position algorithm is a multi-constraint equation solving process which comprises a seat x-direction gravity center position equation and a seat y-direction gravity center position equation.
4. The method for automatically adjusting the center of gravity of an electric aircraft according to claim 3,
the equation of the x-direction gravity center position equation of the seat is as follows:
wherein x is i The position of the center of gravity of the person corresponding to the seat in the x direction，x g The position of the center of gravity of the whole machine in the x direction.
5. The method for automatically adjusting the center of gravity of an electric aircraft according to claim 4,
the equation of the y-direction gravity center position equation of the seat is as follows:
wherein, y i The position of the center of gravity of the person corresponding to the seat in the y direction g The position of the center of gravity of the whole machine in the y direction.
6. The method for automatically adjusting the center of gravity of an electric aircraft according to claim 5,
the origin of the coordinate system is a nose leading edge point, the x axis is on a fuselage symmetry plane and is positive backwards, the y axis is on a cabin floor surface and is positive leftwards;
the data of the front and rear limits of the gravity center and the left and right limits of the gravity center before the seat position is adjusted are obtained by calculating the six-degree-of-freedom force equation and the moment equation of the airplane and the efficiency of the control surface;
the data value of the front and rear limits of the gravity center is x f 、x b The data value of the left and right limits of the gravity center is x l 、x r 。
7. The method for automatically adjusting the center of gravity of an electric aircraft according to claim 6,
x g is located at the front and rear limits (x) of the center of gravity f 、x b ) Between data values;
y g is located at the left and right limits of the center of gravity (x) l 、x r ) Between data values.
8. An automatic trim system for an electric aircraft, comprising:
the seat data acquisition module is used for acquiring the measurement data of the weight sensor and the position sensor of each seat;
the whole computer gravity center calculation module is used for calculating the weight gravity center of the whole computer according to a whole computer equation;
the seat position planning module is used for calculating according to a full-machine gravity center optimal position algorithm to obtain an optimal position and each seat moving path;
the seat driving control module is used for driving the seat motor to automatically move the seat position to the optimal scheme position;
the whole computer gravity center calculation module is also used for calculating the weight gravity center of the whole computer according to the whole computer equation;
the whole-machine gravity center comparison module is used for acquiring an optimal position and judging whether the whole-machine gravity center is in the optimal position, if so, the seat position is locked, and if not, the whole-machine gravity center calculation module, the seat position planning module and the seat driving control module are reconfigured again until the whole-machine gravity center is in the optimal position, and the seat position is locked;
and the seat locking control module is used for locking the seat position.
9. An electronic device comprising a memory, a processor and a computer program stored on the memory and executable on the processor, characterized in that the steps of the method according to any of claims 1 to 7 are implemented when the computer program is executed by the processor.
10. A non-transitory computer-readable storage medium, on which a computer program is stored, which, when being executed by a processor, carries out the steps of the method according to any one of claims 1 to 7.
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106525211A (en) * | 2015-09-14 | 2017-03-22 | 波音公司 | Vehicle Occupant Sensor System and Method |
| CN107672814A (en) * | 2017-10-13 | 2018-02-09 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of ultimate control of aircraft and manipulation device and method |
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| CN111846245A (en) * | 2020-07-30 | 2020-10-30 | 牧羽航空科技（江苏）有限公司 | Aircraft focus automatically regulated seat structure |
| CN114555471A (en) * | 2019-10-16 | 2022-05-27 | 飞机客舱改装有限公司 | System, aircraft and method for payload monitoring |
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2022
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| CN106525211A (en) * | 2015-09-14 | 2017-03-22 | 波音公司 | Vehicle Occupant Sensor System and Method |
| CN108608913A (en) * | 2017-01-23 | 2018-10-02 | 长城汽车股份有限公司 | Seat dynamic adjusting method, system and the vehicle of vehicle |
| CN107672814A (en) * | 2017-10-13 | 2018-02-09 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of ultimate control of aircraft and manipulation device and method |
| CN108621728A (en) * | 2018-06-15 | 2018-10-09 | 中宇航通（北京）科技有限公司 | A kind of hovercar center of gravity automatic regulating system and method and hovercar |
| CN114555471A (en) * | 2019-10-16 | 2022-05-27 | 飞机客舱改装有限公司 | System, aircraft and method for payload monitoring |
| CN111846245A (en) * | 2020-07-30 | 2020-10-30 | 牧羽航空科技（江苏）有限公司 | Aircraft focus automatically regulated seat structure |
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