Seat adjusting device, system and method of manned aircraft and manned aircraft

Abstract

The invention provides a seat adjusting device, system and method for a manned aircraft and the manned aircraft, and the device comprises a plurality of pitch angle collectors which are respectively used for collecting pitch angles of the manned aircraft; the driving assembly is used for driving a seat in the manned aircraft to rotate; the control assembly is used for determining a target pitch angle based on the pitch angles collected by the plurality of pitch angle collectors at the current moment, and controlling the driving assembly to drive the seat to rotate to the preset pitch angle based on the preset pitch angle and the target pitch angle; according to the device, the pitch angles of the manned aircraft are collected in real time through the multiple pitch angle collectors, the target pitch angle is determined from the multiple pitch angles through the control assembly, and the reliability of the target pitch angle is improved; according to the target pitch angle and the preset pitch angle, the driving assembly is controlled to drive the seat to rotate to the preset pitch angle, so that the pitch angle of the seat is always kept near the preset pitch angle, the pitch angle change of the seat is reduced, and the riding comfort of passengers is improved.

Description

Technical Field

[0001] The present application relates to the field of aircraft, and in particular to a seat adjustment device, system, method and manned aircraft for a manned aircraft. Background Art

[0002] As one of the research hotspots of future transportation, the balance between functionality and comfort of manned aircraft has received more and more attention. Taking compound wing aircraft as an example, it has the characteristics of vertical take-off and landing of rotorcraft, and the characteristics of fast speed and easy cruising of fixed-wing aircraft. However, during the flight, the compound wing aircraft needs to switch its power source between rotor and fixed wing according to the changes in flight attitude. When the power source of the aircraft is switched, the angle of the aircraft changes greatly, causing the passengers to rotate with the aircraft, seriously affecting the riding experience of the passengers in the aircraft. Summary of the invention

[0003] In view of the above problems, the present application provides a seat adjustment device, system, method and manned aircraft for a manned aircraft, which can adjust the angle of the seat in real time according to the angle change of the aircraft, so that the passengers remain relatively stable and reduce the impact of the angle change of the aircraft on the physical and visual perception of the passengers.

[0004] The embodiment of the present application is implemented by adopting the following technical solutions:

[0005] In a first aspect, an embodiment of the present application provides a seat adjustment device, comprising a plurality of pitch angle collectors, each for collecting the pitch angle of a manned aircraft; a drive component, for driving a seat in the manned aircraft to rotate; and a control component, for determining a target pitch angle based on the pitch angles collected by the plurality of pitch angle collectors at a current moment, and controlling the drive component to drive the seat of the manned aircraft to rotate to a preset pitch angle based on a preset pitch angle and the target pitch angle.

[0006] In some embodiments, the control component is further used to determine an adjustment angle and an adjustment direction based on a preset pitch angle and the target pitch angle; and based on the adjustment angle and the adjustment direction, control the drive component to drive the seat of the manned aircraft to rotate to a preset pitch angle.

[0007] In some embodiments, the control component is also used to determine the pitch angle change rate based on the target pitch angle at the current moment, the target pitch angle at the previous moment, and the duration between the current moment and the previous moment, and determine the adjustment angular rate based on the pitch angle change rate, and control the drive component to drive the seat of the manned aircraft to rotate to a preset pitch angle based on the adjustment angle, the adjustment direction and the adjustment angular rate.

[0008] In some embodiments, the control component is further used to determine a rate interval based on the pitch angle change rate, and determine a preset angular rate corresponding to the rate interval as the adjustment angular rate.

[0009] In some embodiments, the control component includes a voter, which has multiple input terminals and an output terminal; each input terminal of the voter is respectively connected to one of the pitch angle collectors, for receiving the pitch angle collected by the pitch angle collector, and the output terminal is used to output a target pitch angle, and the target pitch angle is one of the multiple pitch angles.

[0010] In some embodiments, the control component further includes a plurality of filters, each of which has an input end connected to one of the pitch angle collectors and an output end connected to an input end of the voter; the filter is used to filter the received pitch angle to eliminate noise in the pitch angle.

[0011] In some embodiments, the plurality of pitch angle collectors include a laser gyroscope, an inertial navigation system, and an attitude meter.

[0012] In a second aspect, an embodiment of the present application provides a seat adjustment system, including a seat and a seat adjustment device for the above-mentioned manned aircraft.

[0013] In a third aspect, an embodiment of the present application provides a manned aircraft, including an aircraft body and the above-mentioned seat adjustment system.

[0014] In some embodiments, the manned aircraft is a composite-wing manned aircraft, and a rotor and a fixed wing are disposed on the aircraft body.

[0015] In a fourth aspect, an embodiment of the present application provides a seat adjustment method, comprising: obtaining multiple pitch angles of a manned aircraft; determining a target pitch angle based on the multiple pitch angles; and generating an adjustment instruction based on a preset pitch angle and the target pitch angle control, wherein the adjustment instruction is used to control the seat of the manned aircraft to rotate to a preset pitch angle.

[0016] The embodiments of the present application provide a seat adjustment device, system, method and manned aircraft for a manned aircraft, wherein the seat adjustment device includes a plurality of pitch angle collectors, each for collecting the pitch angle of the manned aircraft; a drive assembly, for driving the seat in the manned aircraft to rotate; a control assembly, for determining a target pitch angle based on the pitch angles collected by the plurality of pitch angle collectors at a current moment, and controlling the drive assembly to drive the seat of the manned aircraft to rotate to the preset pitch angle based on a preset pitch angle and the target pitch angle; through the seat adjustment device provided by the present application, during the flight of the manned aircraft, a plurality of pitch angles of the manned aircraft are collected in real time by the plurality of pitch angle collectors, and the target pitch angle is determined from the plurality of pitch angles, thereby improving the reliability of the target pitch angle; and then, according to the determined target pitch angle and the preset pitch angle, the drive assembly is controlled to drive the seat to rotate to the preset pitch angle. Since the pitch angle of the seat is always kept within a certain range of the preset pitch angle, the pitch angle change amplitude of the seat is reduced, thereby avoiding the change in the passenger's body sensation caused by the drastic change in the seat pitch angle, thereby improving the riding comfort of the passenger.

[0017] These and other aspects of the present application will become more clearly understood in the description of the following embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings required for use in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For those skilled in the art, other drawings can be obtained based on these drawings without creative work.

[0019] Figure 1 A schematic block diagram of a seat adjustment device provided in an embodiment of the present application is shown.

[0020] Figure 2 A signal flow diagram of a seat adjustment device provided in an embodiment of the present application is shown.

[0021] Figure 3 A schematic diagram of the seat structure provided in an embodiment of the present application is shown.

[0022] Figure 4 A schematic flow chart of a seat adjustment method proposed in an embodiment of the present application is shown. DETAILED DESCRIPTION

[0023] The embodiments of the present application are described in detail below, and examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present application, and cannot be understood as limiting the present application.

[0024] In order to enable those skilled in the art to better understand the present application, the technical solutions in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without making creative work are within the scope of protection of the present application.

[0025] Manned aircraft refers to aircraft that can carry humans (passengers) in the air and conduct related activities (such as sightseeing, aerial photography, testing, etc.). Manned aircraft need to meet certain safety and comfort requirements, such as stable flight performance, safe and reliable emergency landing system, comfortable seats and environment, etc.

[0026] There are many types of manned aircraft on the market, including fixed-wing aircraft, helicopters, multi-rotor aircraft, etc. They have a wide range of applications, such as air patrol, tourism, news interviews, scientific research, etc. With the development of manned aircraft, manned aircraft have put forward higher requirements on the comfort of passengers on the basis of meeting basic functional requirements. Among them, the change of passengers' physical sensation is an important factor affecting passenger comfort. During the flight of a manned aircraft, as the flight attitude (such as lifting or descending) changes, the pitch angle of the manned flight will change greatly. Taking a composite wing aircraft as an example, the composite wing aircraft starts to accelerate from a hovering state and enters a transition stage. During this stage, as the flight speed increases, the source of the aircraft's horizontal thrust gradually transitions from a combination of the horizontal pull component of the rotor brought by the forward tilt of the aircraft and the thrust of the ducted fan to being borne entirely by the latter. The main source of the aircraft's lift contribution gradually transitions from the lift provided by the rotation of the rotor to the lift provided by the main wing when the aircraft flies at a positive angle of attack (head-up attitude). For the transition stage from cruising to approach to hovering, or even any other flight stage, there may be large pitch changes in the aircraft due to energy optimization management, which causes the passengers to rotate with the manned aircraft, causing physical discomfort to the passengers.

[0027] In order to solve the above problems, the present application proposes a seat adjustment device for a manned aircraft, which can collect the pitch angle of the manned aircraft in real time through a pitch angle collector, use a control component to select a target pitch angle from multiple pitch angles, and control a driving component to drive the rotation of the seat in the manned aircraft according to the target pitch angle and a preset pitch angle, so that the pitch angle of the seat is always maintained within a certain range of the preset pitch angle, thereby reducing the pitch angle change of the passengers, reducing the impact on the body sensation of the operators, and improving the comfort of the passengers.

[0028] The embodiments provided in this application will be described below with reference to the accompanying drawings.

[0029] like Figure 1 As shown, Figure 1 A schematic block diagram of a seat adjustment device provided in an embodiment of the present application is given, and the seat adjustment device includes multiple pitch angle collectors 110, which are respectively used to collect the pitch angles of the manned aircraft; a drive component 120, which is used to drive the seat in the manned aircraft to rotate; a control component 130, which is used to determine the target pitch angle based on the pitch angles collected by the multiple pitch angle collectors 110 at the current moment, and control the drive component 120 to drive the seat of the manned aircraft to rotate to the preset pitch angle based on the preset pitch angle and the target pitch angle.

[0030] The pitch angle is the angle of the aircraft relative to the horizontal plane of the inertial coordinate system.

[0031] The pitch angle collector 110 is a device for measuring the pitch angle of an aircraft, and mainly uses a gyroscope and an accelerometer to measure the attitude change of the aircraft, and then calculates the pitch angle.

[0032] In the embodiment of the present application, the multiple pitch angle collectors 110 include a laser gyroscope, an inertial navigation system, and an horizon. Of course, in other implementations, other devices or components that can collect pitch angles may also be included.

[0033] Among them, the Inertial Navigation System (INS), also known as the inertial reference system, is an autonomous navigation system that does not rely on external information and does not radiate energy to the outside (such as radio navigation); it can establish a navigation coordinate system based on the output of the gyroscope and calculate the speed, position, pitch angle and other information of the vehicle in the navigation coordinate system based on the output of the accelerometer.

[0034] The horizon, also known as the attitude indicator (AI), attitude indicator, attitude azimuth, attitude guidance indicator, etc., is a flight instrument on the aircraft that reports to the pilot the aircraft's attitude relative to the horizon. It indicates the aircraft's pitch (forward and backward tilt) and yaw (tilt to one side) conditions and is the main tool for aircraft flying under instrument meteorological conditions.

[0035] It is worth mentioning that the multiple pitch angle collectors 110 are designed in consideration of the safety of the manned aircraft during flight. During the design process of the manned aircraft, redundancy design is used to improve the reliability and fault tolerance of the operating system. Among them, redundancy design uses hardware and software redundancy to manage key systems by adding a system component with the same function. For example, multiple flight control computer channels are set up so that at least one backup channel can take over the function of the main channel; multiple pitch angle collectors are set up so that at least one pitch angle collector can collect the pitch angle of the aircraft; at the same time, signal interaction and voting between the dual channels are realized through cross-transmission links, so that the final control instruction is the result of the voting of related signals.

[0036] It should be noted that since the pitch angle collector 110 is an essential avionics equipment for the manned aircraft and is pre-installed on the manned aircraft, the cost of the manned aircraft will not be increased due to this solution. In this solution, it is only necessary to extract the pitch angle collected by the existing pitch angle collector at the output end of the flight control computer.

[0037] Among them, the driving component 120 can be a driving motor, or it can be a device such as a hydraulic cylinder that can provide driving force, and there is no specific limitation here; of course, the driving component 120 can also include a transmission mechanism connected to the driving motor or driving cylinder, such as gears, connecting rods, etc., which is connected to the seat through the transmission mechanism.

[0038] The control component 130 may include only a processor, such as a micro control unit (MCU), a receiver control unit (RCU, mainly used to receive and process signals from various sensors, including flight attitude, position, speed and other information, and then output control signals to control the movement of the aircraft), etc., or it may include a processor and other control circuits, such as a filtering circuit, a voting circuit, etc.

[0039] The control component 130 controls the driving component 120 to drive the seat to rotate based on the preset pitch angle and the target pitch angle. The control component 130 may generate a control signal based on the preset pitch angle and the target pitch angle, and use the control signal to control the operation of the driving component 120.

[0040] The seat adjustment device provided in the present application collects multiple pitch angles at the current moment through multiple pitch angle collectors 110, and uses the control component 130 to determine the target pitch angle from the multiple pitch angles, thereby improving the reliability of the target pitch angle; at the same time, the control component 130 controls the drive component 120 to drive the seat to rotate according to the determined target pitch angle and the preset pitch angle, so that the seat always remains within a certain range of the preset pitch angle, reducing the pitch angle change of the seat, thereby reducing the impact on the passenger's body sensation and improving the passenger's comfort.

[0041] In some embodiments, the control component 130 is further used to determine an adjustment angle and an adjustment direction based on a preset pitch angle and a target pitch angle; and control the drive component 120 to drive the seat of the manned aircraft to rotate to the preset pitch angle based on the adjustment angle and the adjustment direction.

[0042] Specifically, the adjustment angle is the angle difference between the preset pitch angle and the target pitch angle, and the adjustment direction includes upward rotation and downward rotation. When the preset pitch angle is greater than the target pitch angle, the adjustment direction is upward rotation; when the preset pitch angle is less than the target pitch angle, the adjustment direction is downward rotation.

[0043] It is understandable that the above calculation process can be specifically executed by a processor included in the control component 130.

[0044] Furthermore, the speed of the seat rotation may be fixed or determined based on the pitch angle change rate of the manned aircraft.

[0045] In some embodiments, considering that the pitch angle of the manned aircraft is in real-time dynamic change, when the adjustment speed of the seat does not match the change speed of the pitch angle, the seat adjustment is prone to lag or advance, resulting in a large pitch angle change during the rotation adjustment of the seat, thereby reducing the passenger's riding experience. Therefore, in order to make the rotation of the seat respond to the change of the pitch angle in a timely manner and further improve the comfort of the passengers, in some embodiments, the control component 130 is also used to determine the pitch angle change rate based on the target pitch angle at the current moment, the target pitch angle at the previous moment, and the time between the current moment and the previous moment, and determine the adjustment angular rate based on the pitch angle change rate, and control the drive component 120 to drive the seat of the manned aircraft to rotate to a preset pitch angle based on the adjustment angle, adjustment direction and adjustment angular rate.

[0046] Among them, when the pitch angle collector 110 has a fixed collection cycle, the time length between the current moment and the previous moment is fixed. It is only necessary to obtain the collection cycle of the pitch angle collector 110 once to determine the pitch angle change rate through the target pitch angle at the current moment and the target pitch angle at the previous moment.

[0047] Of course, the collection period of the pitch angle collector 110 may also be variable. For example, when the manned aircraft is in a cruising state, the flight state of the manned aircraft is relatively stable, and the collection period of the pitch angle collector 110 may be longer; when the manned aircraft is in a lifting state, the flight state of the manned aircraft changes rapidly and the collection period of the pitch angle collector 110 is shorter; at this time, the duration between the current moment and the previous moment is variable, and it is necessary to calculate the duration between the current moment and the previous moment each time, and then determine the pitch angle change rate based on the target pitch angle at the current moment and the target pitch angle at the previous moment.

[0048] In some embodiments, the adjustment angular rate is determined based on the pitch angle change rate, and the adjustment angular rate and the pitch angle change rate are in one-to-one correspondence; illustratively, the adjustment angular rate and the pitch angle change rate are in a fixed proportional relationship.

[0049] Taking into account that the pitch angle change rate calculated each time is different, in order to make the seat adjustment process smoother, in other embodiments, multiple preset angular rates can be set, each preset angular rate corresponds to a rate range, the rate range is determined according to the pitch angle rate, and the preset angular rate corresponding to the rate range is determined as the adjustment angular rate; when the pitch angle rate fluctuates within the same rate range, the adjustment angular rate does not change, thereby making the seat adjustment process smoother.

[0050] It should be noted that the faster the adjustment angular rate, the faster the seat can be adjusted to the preset pitch angle, but too fast an adjustment angular rate itself will affect the comfort of the passengers. Therefore, making the adjustment angular rate adapt to the pitch angle change rate can maximize passenger comfort.

[0051] It is understandable that during the seat adjustment process, the manned aircraft is still in continuous flight. Considering that the manned aircraft will try to avoid sudden changes in flight attitude during flight, such as descending immediately after lifting, therefore, although the calculated pitch angle change rate is the pitch angle change rate between the previous moment and the current moment, that is, the pitch angle change rate at the current moment, it can still represent the pitch angle change rate between the current moment and the next moment to a certain extent, that is, the pitch angle change rate at the next moment; for example, when the pitch angle change rate at the current moment is large, the pitch angle change rate at the next moment is The angular change rate is also likely to be large. Therefore, a larger adjustment angular rate is required to make the seat's adjustment angular rate adapt to the pitch angle change rate, so that the pitch angle during the seat adjustment process is maintained within the appropriate range of the preset pitch angle, further improving the passenger comfort; when the pitch angle change rate at the current moment is small, the pitch angle change rate at the next moment is also likely to be small. Therefore, a smaller adjustment angular rate is required to make the seat's adjustment angular rate adapt to the pitch angle change rate. At this time, if the seat adjustment rate is too large, the seat will rotate rapidly and affect the passenger comfort.

[0052] The seat adjustment device provided in the embodiment of the present application, since the adjustment angular rate of the seat is determined according to the pitch angle change rate of the manned aircraft, the rotation of the seat matches the pitch angle change of the manned aircraft, thereby avoiding a large pitch angle due to mismatch in the adjustment angular rate during the adjustment process of the seat, thereby affecting the riding comfort of the passengers.

[0053] In some embodiments, the control component 130 includes a voter having multiple input terminals and an output terminal; each input terminal of the voter is respectively connected to a pitch angle collector 110, for receiving the pitch angle collected by the pitch angle collector 110, and the output terminal is used to output a target pitch angle, which is one of the multiple pitch angles.

[0054] The voter may be a voting circuit; further, the voting circuit may include a plurality of comparators.

[0055] Exemplarily, taking three pitch angles A, B, and C as an example, three comparators are set to compare the three pitch angles A, B, and C in pairs, so as to output the target pitch angle; further, the target pitch angle can be the middle value of the three pitch angles, or the maximum value or the minimum value, which can be set according to actual needs; in the present application, the middle value of the pitch angle is selected as the target pitch angle.

[0056] Furthermore, in some embodiments, a voting threshold can be set to determine whether there is a faulty pitch angle collector among multiple pitch angle collectors, thereby facilitating troubleshooting and repair of the manned aircraft; illustratively, if the threshold for comparing A and B exceeds the voting threshold, and the threshold for comparing A and C also exceeds the voting threshold, then the pitch angle collector 110 corresponding to A is considered to be faulty.

[0057] Furthermore, in some embodiments, in order to improve the stability of fault confirmation, a counter can be set to record the number of faults of each pitch angle collector 110. When the number of faults is less than the number threshold, it is considered that the corresponding pitch angle collector 110 is still operating normally; when the number of faults exceeds the number threshold, the pitch angle collector 110 is confirmed to be faulty.

[0058] In some embodiments, considering that the pitch angle collected by the pitch angle collector 110 is transmitted in the form of a signal, in order to reduce the interference of other signals in the transmission line, the control component 130 also includes a plurality of filters, each of which has an input end connected to a pitch angle collector 110 and an output end connected to an input end of a voter; the filter is used to filter the received pitch angle to eliminate noise in the pitch angle.

[0059] Among them, the filter allows specific frequency components in the signal to pass through, while greatly attenuating or suppressing other frequency components.

[0060] Furthermore, the filter can be a filter circuit composed of capacitors, inductors and resistors, that is, hardware filtering; it can also be a filter software that is used to identify useful signals and interference signals and filter out interference signals, that is, software filtering. The specific filtering is not specifically limited here.

[0061] The seat adjustment device for a manned aircraft provided in the present application collects multiple pitch angles of the manned aircraft through multiple pitch angle collectors 110, filters the collected pitch angles using a filter, and then selects a target pitch angle at an intermediate value from the multiple pitch angles through a voter, and finally controls the drive component 120 to drive the seat to rotate to the preset pitch angle based on the target pitch angle and the preset pitch angle, so that the pitch angle of the seat is always maintained near the preset pitch angle, reducing the change of the pitch angle of the seat, thereby reducing the impact of the pitch angle change on the passenger's body sensation, and improving the passenger's comfort.

[0062] To facilitate understanding of this solution, please refer to Figure 2 , Figure 2 A signal flow diagram of a seat adjustment device for a manned aircraft provided in an embodiment of the present application is given, and the specific process is as follows:

[0063] Sensors such as laser gyroscopes and inertial navigation systems generate pitch angle signals (that is, the pitch angle collector 110 in this application collects the pitch angle);

[0064] The pitch angle signal is transmitted to the flight control computer, which processes the pitch angle signal to obtain a processed signal, which is transmitted to the drive motor (that is, the process in which the control component 130 in the present application determines the target pitch angle from multiple pitch angles, and controls the operation of the drive component 120 based on the preset pitch angle and the target pitch angle), and the drive motor adjusts the seat angle according to the received processed signal (that is, the process in which the drive component 120 in the present application drives the seat of the manned aircraft to rotate to the preset pitch angle).

[0065] It should be noted that the process of processing signals by the flight control computer may also include filtering the pitch angle signal and then voting to obtain a target pitch angle signal, and processing the target pitch angle signal into a level signal that can be received by the drive motor.

[0066] In other embodiments, the present application also provides a seat adjustment system for a manned aircraft, including a seat and the seat adjustment device provided in the above embodiments.

[0067] Among them, the structure of the seat is as follows Figure 3 As shown, the seat includes a seat headrest P1, a seat backrest P2, a seat armrest (not shown in the figure), a safety belt device (not shown in the figure), a motor bracket P3, a shaft bracket P4, a seat cushion P5 and a shaft P6.

[0068] The safety belt devices are always on the seat back P2 and the seat cushion P5 respectively. The passenger's back is fixed by the safety belt device on the seat back P2, and the passenger's hips and thighs are fixed by the safety belt device on the seat cushion P5, so that the passenger always rotates synchronously with the seat.

[0069] The seat is connected to the manned aircraft through a motor bracket P3, and a drive motor (not shown in the figure) is arranged on the motor bracket P3. The output shaft of the drive motor is connected to the rotating shaft P6, and the rotating shaft P6 is fixedly connected to the rotating shaft bracket P4. The rotating shaft bracket P4 is installed at the bottom of the seat cushion P5. When the drive motor rotates, the drive motor drives the rotating shaft P6 to rotate, and the rotating shaft P6 transmits the rotational torque through the rotating shaft bracket P4 to rotate the entire seat at an appropriate angular velocity.

[0070] In some embodiments, the present application also provides a manned aircraft, including an aircraft body and the above-mentioned seat adjustment system.

[0071] Among them, the aircraft body can be a single-rotor aircraft, a multi-rotor aircraft, a fixed-wing aircraft or a compound-wing aircraft, etc.

[0072] In some embodiments, the manned aircraft is a composite-wing manned aircraft, and a rotor and a fixed wing are disposed on the aircraft body; wherein, the rotor and the fixed wing may be provided with one or more.

[0073] It should be noted that, since the manned aircraft has all the technical features of the seat adjustment device provided in the aforementioned embodiment, the manned aircraft at least has all the beneficial effects described in the aforementioned embodiment, which will not be repeated here.

[0074] In some embodiments, the present application also provides a seat adjustment method for a manned aircraft, which is applied to the seat adjustment device provided in the present application, such as Figure 4 , Figure 4 A flow chart of a seat adjustment method provided in an embodiment of the present application is given, and the seat adjustment method includes:

[0075] S410: Acquire multiple pitch angles of the manned aircraft.

[0076] The multiple pitch angles may be multiple pitch angles collected by different collection devices at the same collection position; or multiple pitch angles collected by collection devices at different collection positions, and no specific limitation is made here.

[0077] It is worth mentioning that the multiple pitch angles obtained can be stored, so as to facilitate the subsequent analysis of the flight status of the manned aircraft or the calculation of the pitch angle change rate based on the stored pitch angles.

[0078] In some embodiments, before obtaining multiple pitch angles of the manned aircraft, a seat mode of the manned aircraft can also be obtained. The seat mode is an adjustment mode or a fixed mode. The adjustment mode means that the seat needs to be adjusted in angle, and the fixed mode means that the seat does not need to be adjusted in angle.

[0079] When the seat mode is the adjustment mode, multiple pitch angles of the manned aircraft are obtained; when the seat mode is the fixed mode, multiple pitch angles of the manned aircraft are not obtained.

[0080] It can be understood that when the seat mode is the adjustment mode, the seat is adjusted along with the pitch angle of the manned aircraft, so that the pitch angle of the seat remains stable, thereby improving the comfort of the passengers; when the seat mode is the fixed mode, the seat changes along with the changes of the manned aircraft, so that the passengers have a real flying experience.

[0081] S420: Determine a target pitch angle based on the multiple pitch angles.

[0082] In some implementations, the target pitch angle is one of a plurality of pitch angles, and may be an intermediate value, a maximum value, or a minimum value of the plurality of pitch angles.

[0083] In other implementations, the target pitch angle may be a pitch angle obtained by processing multiple pitch angles, such as the target pitch angle being an average of the multiple pitch angles.

[0084] Furthermore, the target pitch angle is determined based on multiple pitch angles, and selection can be performed using hardware devices such as voters and comparators; it can also be performed using a software program in a processor, and no specific limitation is made here.

[0085] S430: generating an adjustment instruction based on the preset pitch angle and the target pitch angle, where the adjustment instruction is used to control the seat of the manned aircraft to rotate to the preset pitch angle.

[0086] The preset pitch angle can be fixed to 0 degrees, or it can be a custom angle entered by the passenger before each flight.

[0087] Furthermore, when the preset pitch angle is determined by a custom angle entered by a passenger, it is necessary to set an angle range to avoid incorrect settings. When the custom angle entered by the passenger is within the angle range, the custom angle is set to the preset pitch angle; when the custom angle entered by the passenger is outside the angle range, the preset pitch angle is set to 0 degrees.

[0088] It should be noted that the adjustment instruction should at least include the rotation angle and the rotation direction; of course, the adjustment instruction may also include the adjustment speed.

[0089] Considering that the seat is installed in a manned aircraft, its rotation range is limited, and the pitch angle of the manned aircraft has a large variation range. When the pitch angle of the manned aircraft is large, the seat may not be able to rotate to the preset pitch angle. Therefore, in some embodiments, the control of generating an adjustment instruction based on the preset pitch angle and the target pitch angle may include:

[0090] The pitch angle range is determined according to the rotation range of the seat and the preset pitch angle. If the target pitch angle is within the pitch angle range, an adjustment instruction is generated based on the target pitch angle signal and the preset pitch angle; if the target pitch angle is outside the pitch angle range, an adjustment instruction is generated based on the target pitch angle signal and the rotation range of the seat.

[0091] Among them, the rotation range of the seat will not change after the seat is installed on the manned aircraft, and can be obtained by reading the hardware parameters of the seat.

[0092] It can be understood that when the target pitch angle is within the pitch angle range, the seat can be rotated to the preset pitch angle. Therefore, an adjustment instruction is generated based on the target pitch angle signal and the preset pitch angle, so that the adjustment instruction controls the seat to rotate to the preset pitch angle, thereby improving the comfort of the passenger; when the target pitch angle is outside the pitch angle range, the seat cannot reach the preset pitch angle position even if it is rotated to the maximum angle. Therefore, an adjustment instruction is generated based on the target pitch angle signal and the rotation range of the seat, so that the adjustment instruction controls the seat to rotate to the maximum angle, so that the difference between the pitch angle of the seat and the preset pitch angle is minimized, thereby satisfying the comfort of the passengers to a certain extent.

[0093] The seat adjustment method provided by the present application determines a target pitch angle based on multiple pitch angles acquired in real time, and generates an adjustment instruction based on the target pitch angle and a preset pitch angle, so that the adjustment instruction controls the rotation of the seat; through the seat adjustment method provided by the present application, during the flight of the manned aircraft, the pitch angle of the seat is always maintained at the preset pitch angle, the change of the pitch angle of the seat is reduced, thereby avoiding the influence of the pitch angle change on the passenger's body sensation, and improving the passenger's comfort.

[0094] The above are only preferred embodiments of the present application, and are not intended to limit the present application in any form. Although the present application has been disclosed as above with preferred embodiments, it is not intended to limit the present application. Any technical personnel in the field can make some changes or modify the technical contents disclosed above into equivalent embodiments without departing from the scope of the technical solution of the present application. However, any brief modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present application without departing from the content of the technical solution of the present application are still within the scope of the technical solution of the present application.

Claims

1. A seat adjustment device for a manned aircraft, characterized in that: include: A plurality of pitch angle collectors, each used to collect the pitch angle of the manned aircraft; A drive assembly, used for driving the seats in the manned aircraft to rotate; The control component is used to determine a target pitch angle based on the pitch angles collected by the multiple pitch angle collectors at the current moment, and control the drive component to drive the seat of the manned aircraft to rotate to the preset pitch angle based on the preset pitch angle and the target pitch angle.

2. The device according to claim 1, characterized in that The control component is also used to determine the adjustment angle and the adjustment direction based on the preset pitch angle and the target pitch angle; Based on the adjustment angle and the adjustment direction, the driving assembly is controlled to drive the seat of the manned aircraft to rotate to a preset pitch angle.

3. The device according to claim 2, characterized in that The control component is also used to determine the pitch angle change rate based on the target pitch angle at a current moment, the target pitch angle at a previous moment, and the duration between the current moment and the previous moment, and determine the adjustment angular rate based on the pitch angle change rate, and control the drive component to drive the seat of the manned aircraft to rotate to a preset pitch angle based on the adjustment angle, the adjustment direction, and the adjustment angular rate.

4. The device according to claim 3, characterized in that The control component is further configured to determine a rate interval based on the pitch angle change rate, and determine a preset angular rate corresponding to the rate interval as an adjustment angular rate.

5. The device according to claim 1, characterized in that The control assembly includes a voting device having a plurality of input terminals and an output terminal; Each input end of the voter is connected to one of the pitch angle collectors for receiving the pitch angle collected by the pitch angle collector, and the output end is used to output a target pitch angle, which is one of the multiple pitch angles.

6. The device according to claim 5, characterized in that The control component further comprises a plurality of filters, each of which has an input end connected to one of the pitch angle collectors and an output end connected to an input end of the voter; The filter is used to filter the received pitch angle to eliminate noise in the pitch angle.

7. The device according to claim 1, characterized in that The plurality of pitch angle collectors include a laser gyroscope, an inertial navigation system and an attitude meter.

8. A seat adjustment system for a manned aircraft, characterized in that: The invention comprises a seat and a seat adjustment device for a manned aircraft as claimed in any one of claims 1 to 7.

9. A manned aircraft, characterized in that: It comprises an aircraft body and the seat adjustment system as claimed in claim 8.

10. The manned aircraft according to claim 9, characterized in that: The manned aircraft is a composite-wing manned aircraft, and a rotor and a fixed wing are arranged on the aircraft body.

11. A method for adjusting a seat of a manned aircraft, characterized in that: include: Obtain multiple pitch angles of a manned aircraft; determining a target pitch angle based on the plurality of pitch angles; An adjustment instruction is generated based on a preset pitch angle and the target pitch angle, and the adjustment instruction is used to control the seat of the manned aircraft to rotate to the preset pitch angle.

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