Load control device and onboard load

Abstract

The utility model discloses a load control device and an airborne load, and relates to the field of aircraft equipment. The load control device comprises a load fixing part, an electric control assembly and a guide head, the load fixing part is of a cylindrical structure and is provided with a front end and a rear end which are opposite in the axis direction of the load fixing part, the front end of the load fixing part is used for being connected with a load body, and the electric control assembly is arranged in the load fixing part and is connected with the guide head. The guide head is arranged on the outer circumferential face of the load fixing piece in a protruding mode and electrically connected with the electric control assembly. By arranging the seeker on the peripheral surface of the load control device, the seeker can be used for collecting image information of a target and sending the image information to the electric control assembly, and the electric control assembly can judge the relative position of the airborne load and the target according to the information collected by the seeker and adjust the flight direction of the airborne load according to needs, so that the target is tracked, and the tracking efficiency of the airborne load is improved. The accuracy of the drop point is ensured. The airborne load provided by the utility model comprises a load body and the load control device.

Description

Technical Field

[0001] The present application relates to the field of aircraft equipment, and in particular, to a load control device and an airborne load. Background Art

[0002] Airborne payloads are usually mounted on aircraft and dropped to target locations by the aircraft to achieve corresponding functions (such as fire extinguishing, insecticide, etc.). After being dropped, it is difficult to control the relative position of the airborne payload to the target in the prior art, resulting in inaccurate landing points; especially when the target is a moving target, it is even more difficult to ensure that the airborne payload accurately lands at the target location. The deviation of the airborne payload landing point will lead to poor operation results or even operation failure. Utility Model Content

[0003] The purpose of the present application is to provide a load control device and an airborne load, wherein the load control device can identify and track the target during the process of the airborne load being dropped, thereby ensuring the accuracy of the landing point.

[0004] The embodiment of the present application is implemented as follows:

[0005] In a first aspect, the present application provides a load control device, which is applied to an airborne load mounted on an aircraft. The airborne load includes a load body and a load control device. The load control device includes a load fixing part, an electronic control component and a guide head. The load fixing part is a cylindrical structure. The load fixing part has a relative front end and a rear end along its own axial direction. The front end of the load fixing part is used to connect to the load body. The electronic control component is arranged in the load fixing part. The guide head is protruded from the outer peripheral surface of the load fixing part, and the guide head is electrically connected to the electronic control component.

[0006] In an optional embodiment, a mounting groove connecting the inside and the outside of the load fixing component is opened on the side wall of the load fixing component, and a part of the guide head is arranged in the mounting groove.

[0007] In an optional embodiment, the guide head includes a camera and a drive adjustment mechanism, one end of the drive adjustment mechanism is arranged in the mounting groove, the camera is located outside the load fixing member and is transmission-connected to the drive adjustment mechanism, and the drive adjustment mechanism is used to adjust the direction of the camera.

[0008] In an optional embodiment, the load control device further includes a wind blocking portion, which is disposed on an outer peripheral surface of the load fixing member and has a wind blocking surface facing the front end of the load fixing member.

[0009] In an optional embodiment, the wind blocking portion is arranged at the rear end of the load fixing component.

[0010] In an optional embodiment, the air blocking portion is an annular plate body, and the air blocking portion is sleeved on the outer side of the load fixing component.

[0011] In an optional embodiment, the load control device further comprises a plurality of guide wings, which are arranged at circumferential intervals around the load fixing member on the outer surface of the load fixing member, and along the axial direction of the load fixing member, the guide wings are located between the front end of the load fixing member and the wind blocking portion.

[0012] In an optional embodiment, the load control device also includes a plurality of control wings and a plurality of servos. The plurality of control wings are arranged on the outer surface of the load fixing member at circumferential intervals around the load fixing member. Along the axial direction of the load fixing member, the control wings are located between the wind-blocking portion and the guide wing. The plurality of servos are transmission-connected to the plurality of control wings in a one-to-one correspondence. The servos are used to drive the control wings to rotate so as to adjust the falling posture of the onboard load.

[0013] In an optional embodiment, the guide head is located at a front end of the guide wing close to the load fixing member, and the electronic control assembly is located between the guide head and the steering gear along the axial direction of the load fixing member.

[0014] In an optional embodiment, the electric control component is electrically connected to the aircraft via a magnetic connector to achieve signal transmission and / or power transmission with the aircraft.

[0015] In an optional embodiment, the magnetic connector includes a magnetic head and a magnetic seat that can be magnetically matched; one of the magnetic head and the magnetic seat is arranged on the surface of the load fixing part, and the other of the magnetic head and the magnetic seat is arranged on the aircraft.

[0016] In an optional embodiment, the load control device further includes a parachute cabin, which is disposed at the rear end of the load fixing component and is used to accommodate and release the parachute.

[0017] In an optional embodiment, the parachute cabin and the load fixing member are coaxially connected in sequence along the axis of the load fixing member.

[0018] In an optional embodiment, the load control device further comprises an antenna assembly, wherein the antenna assembly is disposed on an outer surface of the parachute cabin on a side facing away from the load fixing component.

[0019] In an optional embodiment, the front end of the load fixing member is provided with an opening connected to its inner cavity, a mounting seat is provided in the inner cavity of the load fixing member, the opening at the front end of the load fixing member is used for inserting the load body, and the mounting seat is provided with a thread for threaded connection with the load body.

[0020] In an optional embodiment, the load control device further includes a hanger structure disposed on the load fixing member, and the hanger structure is used to connect to the aircraft.

[0021] In a second aspect, the present application provides an airborne payload for being mounted on an aircraft and dropped to a target location by the aircraft, comprising a payload body and a load control device of any one of the aforementioned embodiments, wherein the payload body is connected to a front end of the load control device.

[0022] The beneficial effects of the embodiments of the present application are:

[0023] The load control device provided by the present application includes a load fixing part, an electric control component and a seeker. The load fixing part is a cylindrical structure. The load fixing part has a front end and a rear end relative to each other along its own axis direction. The front end of the load fixing part is used to connect the load body. The electric control component is arranged in the load fixing part. The seeker is convexly arranged on the outer peripheral surface of the load fixing part. The seeker is electrically connected to the electric control component. By arranging the seeker on the outer peripheral surface of the load control device, the seeker can be used to collect image information of the target and send it to the electric control component. The electric control component can judge the relative position of the airborne load and the target according to the information collected by the seeker, and adjust the flight direction of the airborne load as needed, so as to track the target and ensure the accuracy of the landing point.

[0024] The airborne payload provided in the embodiment of the present application includes a payload body and the above-mentioned payload control device, the payload body is connected to the front end of the payload control device, and the airborne payload can identify and track the target, thereby ensuring the accuracy of the landing point. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required for use in the embodiments will be briefly introduced below. It should be understood that the following drawings only show certain embodiments of the present application and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other related drawings can be obtained based on these drawings without paying creative work.

[0026] Figure 1 This is a schematic diagram of an airborne load in an embodiment of the present application at a first viewing angle;

[0027] Figure 2 This is a schematic diagram of an airborne load at a second viewing angle in an embodiment of the present application;

[0028] Figure 3 It is a cross-sectional view of an airborne load in one embodiment of the present application.

[0029] Icons: 010-airborne load; 100-load control device; 110-load fixing part; 111-mounting seat; 112-seat body; 113-stud; 114-fairing; 120-wind-blocking part; 121-wind-blocking surface; 130-guide wing; 140-control wing; 141-servo gear fixing seat; 150-electric control component; 151-magnetic head; 160-antenna component; 170-hanging structure; 180-seeker; 190-parachute compartment; 200-load body. DETAILED DESCRIPTION

[0030] In order to make the purpose, technical solution and advantages of the embodiments of the present application clearer, the technical solution 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 part of the embodiments of the present application, rather than all the embodiments. The components of the embodiments of the present application described and shown in the drawings here can be arranged and designed in various different configurations.

[0031] Therefore, the following detailed description of the embodiments of the present application provided in the accompanying drawings is not intended to limit the scope of the present application for which protection is sought, but merely represents selected embodiments of the present application. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in the field without creative work are within the scope of protection of the present application.

[0032] It should be noted that similar reference numerals and letters denote similar items in the following drawings, and therefore, once an item is defined in one drawing, further definition and explanation thereof is not required in subsequent drawings.

[0033] In the description of the present application, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inside", "outside", etc. indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, or the positions or positional relationships in which the utility model product is usually placed when in use. They are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific position, be constructed and operated in a specific position, and therefore cannot be understood as a limitation on the present application. In addition, the terms "first", "second", "third", etc. are only used to distinguish the description, and cannot be understood as indicating or implying relative importance.

[0034] In addition, the terms "horizontal", "vertical" and the like do not mean that the components are required to be absolutely horizontal or suspended, but can be slightly tilted. For example, "horizontal" only means that its direction is more horizontal than "vertical", and does not mean that the structure must be completely horizontal, but can be slightly tilted.

[0035] In the description of this application, it should also be noted that, unless otherwise clearly specified and limited, the terms "set", "install", "connect", and "connect" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two elements. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0036] The airborne load in the existing related technology realizes the corresponding operation by being dropped to the target position by the aircraft. For example, the airborne load contains fire-extinguishing materials, which are dropped to the fire location by the aircraft to extinguish the fire. Usually, the airborne load includes a load control device and a load body. The load body contains materials used to realize the relevant operations (such as fire-extinguishing materials), and the load control device is used to control the landing point of the airborne load so that it can be accurately dropped to the target position. However, it is difficult for the airborne load in the related technology to accurately control the relative position of the airborne load with respect to the target during the falling process, resulting in an inaccurate landing point; especially when the target is a moving target, it is even more difficult to ensure that the airborne load accurately falls at the target position.

[0037] In order to improve the problem in the related art that the landing point of the airborne payload is difficult to accurately control, an embodiment of the present application provides a load control device and an airborne payload. By setting a seeker on the load control device, the relative position information of the target is collected during the process of the airborne payload being dropped and falling, and the flight direction of the airborne payload is adjusted according to the collected information, thereby improving the accuracy of the landing point.

[0038] Figure 1 This is a schematic diagram of an airborne payload 010 at a first viewing angle in an embodiment of the present application; Figure 2 This is a schematic diagram of an airborne payload 010 at a second viewing angle in an embodiment of the present application; Figure 3 This is a cross-sectional view of an onboard payload 010 in one embodiment of the present application. Figures 1 to 3 The airborne load 010 provided in this embodiment includes a load control device 100 and a load body 200. The load body 200 is used to contain materials related to the operation. For example, when the airborne load 010 is used for fire extinguishing, the load body 200 can contain fire extinguishing materials; when the airborne load 010 is used for blasting, the load body 200 can contain explosives; when the airborne load 010 is used for insecticide, the load body 200 can contain insecticides; when the airborne load 010 is used for weeding, the load body 200 can contain herbicides. The load control device 100 is used to control the posture of the entire airborne load 010 and then adjust the landing point of the airborne load 010, so that the airborne load 010 can accurately land at the target position to achieve the operation.

[0039] In the embodiment of the present application, the load control device 100 includes a load fixing part 110, an electric control component 150 and a guide head 180. The load fixing part 110 is a cylindrical structure. The load fixing part 110 has a front end and a rear end relative to each other along its own axis direction. The front end of the load fixing part 110 is used to connect the load body 200. The electric control component 150 is arranged in the load fixing part 110. The guide head 180 is convexly arranged on the outer peripheral surface of the load fixing part 110. The guide head 180 is electrically connected to the electric control component 150. The guide head 180 can be used to collect image information and transmit the image information to the electric control component 150. The electric control component 150 analyzes the position of the airborne load 010 relative to the target at the current moment according to the image information, so as to adjust the flight direction of the airborne load 010 in real time as needed, so as to ensure that the airborne load 010 can accurately land at the target position. The airborne load 010 provided with the guide head 180 can not only adapt to the delivery of fixed landing points, but also track moving targets, thereby improving the application range of the airborne load 010. The image information collected by the seeker 180 includes but is not limited to black and white / color images, infrared images, etc.

[0040] Furthermore, a mounting groove is provided on the side wall of the load fixing part 110 to connect the inside and outside of the load fixing part 110, and a part of the guide head 180 is disposed in the mounting groove. By providing the mounting groove, on the one hand, a space for wiring is provided, so that the guide head 180 can be electrically connected to the electric control component 150 in the load fixing part 110 through a wiring harness; on the other hand, the mounting groove can improve the installation stability of the guide head 180.

[0041] Optionally, the guide head 180 includes a camera and a drive adjustment mechanism, one end of the drive adjustment mechanism is arranged in the mounting groove, the camera is located outside the load fixing member 110 and is transmission-connected to the drive adjustment mechanism, and the drive adjustment mechanism is used to adjust the direction of the camera. In an optional embodiment, the drive adjustment mechanism may include a pan / tilt motor to realize the rotation of the camera on one to three axes. For example, in a specific embodiment, the camera can rotate along a first axis and a second axis under the drive of the drive adjustment mechanism, and the first axis and the second axis are perpendicular to each other and are perpendicular to the axis of the load fixing member 110. Specifically, the first axis can be a pitch axis, and the second axis can be a heading axis, or the first axis can be a heading axis and the second axis can be a pitch axis. By setting a drive adjustment mechanism, the camera can be actively controlled to search for a target, avoiding the problem of being unable to locate the target because the target is outside the field of view of the camera.

[0042] In this embodiment, the load control device 100 further includes a wind blocking portion 120, which is disposed on the outer peripheral surface of the load fixing member 110 and has a wind blocking surface 121 facing the front end of the load fixing member 110. By providing the wind blocking portion 120, the upward resistance of the airborne load 010 during the falling process can be significantly increased, thereby effectively reducing the falling speed, avoiding the situation where the load control device 100 is too late to adjust the flight direction of the airborne load 010, and is conducive to improving the control of the load control device 100 on the landing accuracy.

[0043] Specifically, the air blocking portion 120 is disposed at the rear end of the load fixing member 110. During the falling process of the airborne load 010, the load body 200 should be located at the lower end of the entire airborne load 010, closer to the ground than the load fixing member 110. The air blocking portion 120 is disposed at the rear end of the load fixing member 110, and during the falling process of the airborne load 010, it is subjected to upward resistance, which is conducive to positioning the load body 200 below the load fixing member 110.

[0044] The connection method of the air blocking portion 120 and the load fixing member 110 includes but is not limited to welding, bonding, and connection using fasteners such as screws and rivets. In other optional embodiments, the air blocking portion 120 can also be connected to the rear end surface of the load fixing member 110. In this case, the air blocking portion 120 should extend from the outer peripheral surface of the load fixing member 110 along the radial direction of the load fixing member 110, so as to form a air blocking surface 121 facing the front end of the load fixing member 110. In this embodiment, the air blocking portion 120 is an annular plate body, and the air blocking portion 120 is sleeved on the outside of the load fixing member 110. Optionally, the air blocking portion 120 is perpendicular to the axis of the load fixing member 110.

[0045] In other optional embodiments, the air blocking portion 120 may be discontinuous in the circumferential direction of the load fixing member 110. In other words, the load control device 100 may include a plurality of air blocking portions 120, and the plurality of air blocking portions 120 are arranged at intervals in the circumferential direction of the load fixing member 110; for the sake of flight balance, the plurality of air blocking portions 120 may be evenly spaced.

[0046] It should be understood that the faster the airborne load 010 falls, the greater the resistance it encounters. Therefore, the falling acceleration of the airborne load 010 gradually decreases, and its falling speed tends to converge. When the resistance in the vertical direction is equal to the gravity of the airborne load 010, the movement of the airborne load 010 in the vertical direction becomes uniform motion, and the speed at this time is the convergence speed. It can be understood that the size of the wind blocking surface 121 of the wind blocking part 120 determines the ability of the wind blocking part 120 to provide resistance during the falling process of the airborne load 010. The larger the area of ​​the wind blocking surface 121, the greater the resistance that can be provided. Therefore, designing an appropriate size of the wind blocking surface 121 according to needs can enable the airborne load 010 to have a suitable convergence speed. When the convergence speed is small, it is conducive to accurately controlling the landing point of the loaded load; and a small convergence speed means a longer falling time, which can leave more time for the load control device 100 to adjust the posture and improve the landing point accuracy.

[0047] In this embodiment, the load control device 100 further includes a plurality of guide wings 130, which are arranged at intervals around the circumference of the load fixing member 110 on the outer surface of the load fixing member 110, and along the axial direction of the load fixing member 110, the guide wings 130 are located between the front end of the load fixing member 110 and the wind blocking portion 120. The function of the guide wings 130 is to ensure the stable flight of the airborne load 010, and at the same time, it can also increase the maneuverability of the airborne load 010. Since the guide wings 130 are parallel to the axis of the airborne load 010, when the movement direction of the airborne load 010 is inconsistent with its axis, the guide wings 130 are subject to airflow resistance, and the airflow resistance will guide the movement direction of the airborne load 010 to change, so that it approaches the axis direction, and macroscopically, it shows that the airborne load 010 tends to move in the direction of its front end. In this embodiment, the guide wing 130 is closer to the front end of the load fixing part 110 than the wind blocking part 120, so that the airflow first passes through the guide wing 130 to guide the airborne load 010, and then reaches the wind blocking surface 121 to provide reverse resistance for the airborne load 010; if the wind blocking part 120 is set at a position more forward than the guide wing 130, the airflow near the guide wing 130 may be turbulent, and the guide function of the guide wing 130 is difficult to play. In this embodiment, the axis of the airborne load 010 coincides with the axis of the load fixing part 110; and the shape of the load body 200 in this embodiment is also close to a rotating body, and its axis coincides with the axis of the airborne load 010 and the axis of the load fixing part 110.

[0048] In this embodiment, a plurality of guide wings 130 are evenly spaced around the circumference of the load fixing member 110; in this embodiment, the number of guide wings 130 is four, arranged in a cross shape, and in other embodiments, the number of guide wings 130 can be increased or decreased as needed. The guide wings 130 can be connected to the load fixing member 110 by welding, or by fasteners such as screws and rivets.

[0049] In this embodiment, the load control device 100 includes a plurality of control wings 140 and a plurality of steering gears (not shown in the figure), the plurality of control wings 140 are arranged at intervals around the circumference of the load fixing member 110 on the outer surface of the load fixing member 110, along the axial direction of the load fixing member 110, the control wings 140 are located between the wind blocking portion 120 and the guide wings 130, and the plurality of steering gears are connected to the plurality of control wings 140 in a one-to-one corresponding manner, and the steering gears are used to drive the control wings 140 to rotate to adjust the falling posture of the airborne load 010. The steering gears are electrically connected to the electronic control component 150. In this embodiment, the rotation axis of the control wing 140 is perpendicular to the axis of the load fixing member 110. During the falling process, if the current posture of the airborne load 010 does not need to be adjusted, then the control wing 140 only needs to be adjusted to be parallel to the axis of the load fixing member 110 (specifically, it can be in the same plane as the guide wing 130); when the posture adjustment is required, the steering gear drives the control wing 140 to rotate so that it forms an angle with the axis of the airborne load 010. The control wing 140 will be subjected to the impact force of the airflow, which can be decomposed into a component force perpendicular to the axis of the airborne load 010. The component force can make the rear end of the airborne load 010 move radially, so that the axis of the airborne load 010 is deflected, that is, the posture adjustment is achieved. After the posture of the airborne load 010 is deflected, it can further move in the direction of the front end under the action of the guide wing 130. Therefore, by controlling the deflection of the control wing 140 by the steering gear, the posture and movement direction of the airborne load 010 can be adjusted, thereby controlling its landing point.

[0050] In this embodiment, a steering gear fixing seat 141 is disposed on the inner wall surface of the load fixing member 110 , and the steering gear is installed on the steering gear fixing seat 141 .

[0051] In this embodiment, the guide head 180 is closer to the front end of the load fixing member 110 than each guide vane 130, and the electric control assembly 150 is located between the guide head 180 and the steering gear along the axial direction of the load fixing member 110. Specifically, the setting position of the electric control assembly 150 in the load fixing member 110 is adjacent to the guide head 180, so that the guide head 180 can be connected to the electric control assembly 150 through a shorter wire harness.

[0052] In this embodiment, the electric control component 150 is electrically connected to the aircraft through a magnetic connector to achieve signal transmission and / or power transmission with the aircraft. Optionally, the electric control component 150 includes a battery, and the aircraft can charge the electric control component 150 through the magnetic connector, so that the electric control component 150 has enough power to control the movement of the airborne payload 010 after it is deployed (such as providing power for the steering gear). The aircraft can also transmit signals to the airborne payload 010 through the magnetic connector to control the airborne payload 010 to perform related actions.

[0053] In this embodiment, the magnetic connector includes a magnetic head 151 and a magnetic seat that can be magnetically matched, the magnetic head 151 is arranged on the surface of the load fixing part 110, and the magnetic seat is arranged on the aircraft. However, the present application is not limited to this, and in other embodiments, the magnetic head 151 may be arranged on the aircraft, and the magnetic seat may be arranged on the surface of the load fixing part 110.

[0054] Before the airborne payload 010 is dropped, the magnetic head 151 can be magnetically connected to the magnetic seat of the aircraft. After the airborne payload 010 is dropped, the gravity of the airborne payload 010 will overcome the magnetic attraction between the magnetic head 151 and the magnetic seat, thereby disconnecting the magnetic head 151 from the magnetic seat. By setting up a magnetic connector, the efficiency of connecting and disconnecting the airborne payload 010 and the aircraft can be significantly improved. The magnetic connector also has the advantages of convenience, anti-misinsertion, dustproof and waterproof, high efficiency and energy saving.

[0055] The magnetic head 151 can be arranged on the outer surface of the middle section of the load fixing part 110, and the magnetic head 151 is connected to the electronic control component 150 through a wiring harness. Furthermore, the load control device 100 also includes a hanging structure 170 arranged on the load fixing part 110, and the hanging structure 170 is used to connect the aircraft, and the aircraft flies with the airborne payload 010 through the hanging structure 170. The magnetic suction connector can be arranged on the same side of the load fixing part 110 as the hanging structure 170, so that before the airborne payload 010 is dropped, the magnetic head 151 is located on the side of the airborne payload 010 close to the aircraft, which facilitates the electrical connection between the magnetic head 151 and the magnetic seat on the aircraft.

[0056] In this embodiment, the load control device 100 further includes a parachute compartment 190, which is disposed at the rear end of the load fixing member 110, and the parachute is contained in the parachute compartment 190 and released. Before product testing, the parachute can be installed in the parachute compartment 190, and the parachute can be released in time after the airborne load 010 is dropped and before it lands, so as to buffer the impact force of the airborne load 010 when it lands, reduce the risk of damage to the airborne load 010, and make the airborne load 010 (or the load control device 100) reusable. Optionally, the parachute compartment 190 is connected to the load fixing member 110 by nylon rivets, and the load control device 100 includes an ignition module, which can ignite the guncotton stored in the parachute compartment in advance, and the impact force generated by the guncotton explosion causes the parachute compartment 190 to expand, break the nylon rivets and separate from the load fixing member 110, thereby releasing the parachute. In other embodiments, an electrically-controlled sliding door may also be provided on the parachute compartment 190 to control the opening or closing of the parachute compartment 190; a launching device may be provided in the parachute compartment 190, and when the electrically-controlled sliding door is opened, the launching device can release the parachute from the parachute compartment 190.

[0057] As shown in the figure, the parachute compartment 190 and the load fixing part 110 are coaxially connected in sequence along the axis of the load fixing part 110. This arrangement enables the load control device 100 to have a better aerodynamic shape, which is beneficial to the stability of the flight. In the present embodiment, the parachute compartment 190 is a disc-shaped box body, and the diameter is slightly larger than the rear end diameter of the load fixing part 110. Optionally, the wind blocking part 120 is connected to the parachute compartment 190 by screws. In other optional embodiments, an annular plate-shaped connecting plate can also be welded on the outer peripheral side of the load fixing part 110, and the wind blocking part 120 is connected to the connecting plate by screws; or, the wind blocking part 120 is directly welded to the outer peripheral surface of the load fixing part 110.

[0058] Furthermore, the load control device 100 further includes an antenna assembly 160, which is disposed on the outer surface of the parachute cabin 190 on the side away from the load fixing member 110. The antenna assembly 160 is electrically connected to the electric control assembly 150. The antenna assembly 160 includes a GPS antenna for identifying the current position of the airborne load 010. The electric control assembly 150 compares the current position with the target position, and can determine the attitude control strategy of the airborne load 010 to make the airborne load 010 fly to the target position.

[0059] Since the antenna assembly 160 needs to transmit wireless signals, it is suitable to be arranged outside the load fixing part 110 to ensure signal quality. The antenna assembly 160 is arranged on the side of the parachute cabin 190 away from the load fixing part 110, which can avoid the antenna assembly 160 from affecting the aerodynamic shape of the airborne load 010 as much as possible, which is beneficial to the flight movement of the airborne load 010; and can reduce the air resistance of the antenna assembly 160 itself, ensuring its normal operation.

[0060] In the embodiment of the present application, the load body 200 is connected to the front end of the load control device 100. In the present embodiment, the front end of the load fixing part 110 is provided with an opening communicating with the inner cavity thereof, and a mounting seat 111 is provided in the inner cavity of the load fixing part 110. The opening at the front end of the load fixing part 110 is used for inserting the load body 200, and the mounting seat 111 is provided with a thread for screwing with the load body 200. Specifically, the mounting seat 111 includes a seat body 112 and a stud 113. The seat body 112 has a circular outer edge, and the outer edge of the seat body 112 is connected to the inner wall of the load fixing part 110; the stud 113 is provided in the middle of the seat body 112, and the axis of the stud 113 coincides with the axis of the load fixing part 110. One end of the load body 200 extending into the load fixing part 110 has a screw hole, and the screw hole cooperates with the stud 113. Since the load body 200 is embedded in the front end of the load fixing part 110 for connection, the opening edge of the load fixing part 110 has a limiting effect on the load body 200, and the mounting seat 111 also has an axial and radial positioning effect on the load body 200. Therefore, the load body 200 has better stability and is easy to maintain coaxiality with the load fixing part 110.

[0061] Furthermore, an annular fairing 114 is provided at the front end opening edge of the load fixing member 110, and the fairing 114 is coaxially arranged with the load fixing member 110 for reducing the gap between the outer surface of the load body 200 and the front end opening edge of the load fixing member 110, so that the airborne load 010 has a better aerodynamic shape.

[0062] The load body 200 is a main component for containing working materials (such as fire extinguishing agent, explosives, etc.), and since the load fixing member 110 of this embodiment has an inner cavity, the load fixing member 110 can also be used to contain a part of the working materials.

[0063] The aircraft used for the airborne payload 010 provided in the embodiment of the present application may be a drone, or other types of aircraft that require a pilot to operate the aircraft.

[0064] In summary, the load control device 100 provided by the present application includes a load fixing part 110, an electric control component 150 and a seeker 180. The load fixing part 110 is a cylindrical structure. The load fixing part 110 has a front end and a rear end relative to each other along its own axis direction. The front end of the load fixing part 110 is used to connect the load body 200. The electric control component 150 is arranged in the load fixing part 110. The seeker 180 is convexly arranged on the outer peripheral surface of the load fixing part 110. The seeker 180 is electrically connected to the electric control component 150. By arranging the seeker 180 on the outer peripheral surface of the load control device 100, the seeker 180 can be used to collect image information of the target and send it to the electric control component 150. The electric control component 150 can judge the relative position of the airborne load 010 and the target according to the information collected by the seeker 180, and adjust the flight direction of the airborne load 010 as needed, so as to achieve tracking of the target and ensure the accuracy of the landing point.

[0065] The airborne payload 010 provided in the embodiment of the present application is used to be mounted on an aircraft and dropped to a target location by the aircraft. The airborne payload 010 includes a payload body 200 and the above-mentioned payload control device 100. The payload body 200 is connected to the front end of the payload control device 100. The airborne payload 010 can identify and track the target, thereby ensuring the accuracy of the landing point.

[0066] The above are only preferred embodiments of the present application and are not intended to limit the present application. For those skilled in the art, the present application may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. A load control device, applied to an airborne load mounted on an aircraft, the airborne load comprising a load body and the load control device, characterized in that: The load control device includes a load fixing part, an electronic control component and a guide head. The load fixing part is a cylindrical structure. The load fixing part has a front end and a rear end relative to each other along its own axial direction. The front end of the load fixing part is used to connect with the load body. The electronic control component is arranged in the load fixing part. The guide head is protruded from the outer peripheral surface of the load fixing part, and the guide head is electrically connected to the electronic control component.

2. The load control device according to claim 1, characterized in that: A mounting groove communicating the inside and outside of the load fixing member is provided on the side wall of the load fixing member, and a part of the guide head is arranged in the mounting groove.

3. The load control device according to claim 2, characterized in that: The guide head includes a camera and a drive adjustment mechanism, one end of the drive adjustment mechanism is arranged in the installation groove, the camera is located outside the load fixing member and is transmission-connected to the drive adjustment mechanism, and the drive adjustment mechanism is used to adjust the direction of the camera.

4. The load control device according to claim 1, characterized in that: The load control device further includes a wind blocking portion, which is disposed on an outer peripheral surface of the load fixing member and has a wind blocking surface facing a front end of the load fixing member.

5. The load control device according to claim 4, characterized in that: The wind blocking portion is arranged at a rear end of the load fixing member.

6. The load control device according to claim 4, characterized in that: The wind blocking part is an annular plate body, and the wind blocking part is sleeved on the outer side of the load fixing part.

7. The load control device according to claim 4, characterized in that: The load control device further comprises a plurality of guide wings which are arranged at intervals around the circumference of the load fixing member on the outer surface of the load fixing member. Along the axial direction of the load fixing member, the guide wings are located between the front end of the load fixing member and the wind blocking portion.

8. The load control device according to claim 7, characterized in that: The load control device also includes a plurality of control wings and a plurality of servos. The plurality of control wings are arranged on the outer surface of the load fixing component at circumferential intervals around the load fixing component. Along the axial direction of the load fixing component, the control wings are located between the wind blocking portion and the guide wings. The plurality of servos are transmission-connected to the plurality of control wings in a one-to-one correspondence. The servos are used to drive the control wings to rotate so as to adjust the falling posture of the airborne load.

9. The load control device according to claim 8, characterized in that: The guide head is located at a front end of the guide vane close to the load fixing member relative to the guide wing. Along the axial direction of the load fixing member, the electric control component is located between the guide head and the steering gear.

10. The load control device according to any one of claims 1 to 9, characterized in that: The electric control component is electrically connected to the aircraft via a magnetic connector to achieve signal transmission and / or power transmission with the aircraft.

11. The load control device according to claim 10, characterized in that: The magnetic connector includes a magnetic head and a magnetic seat that can be magnetically matched; one of the magnetic head and the magnetic seat is arranged on the surface of the load fixing part, and the other of the magnetic head and the magnetic seat is arranged on the aircraft.

12. The load control device according to any one of claims 1 to 9, characterized in that: The load control device also includes a parachute compartment, which is arranged at the rear end of the load fixing component and is used to accommodate and release a parachute.

13. The load control device according to claim 12, characterized in that: The parachute cabin and the load fixing component are coaxially connected in sequence along the axis of the load fixing component.

14. The load control device according to claim 13, characterized in that: The load control device further comprises an antenna assembly, wherein the antenna assembly is arranged on an outer surface of the parachute cabin on a side facing away from the load fixing component.

15. The load control device according to any one of claims 1 to 9, characterized in that: The front end of the load fixing member is provided with an opening connected to its inner cavity, and a mounting seat is provided in the inner cavity of the load fixing member. The opening at the front end of the load fixing member is used for inserting the load body, and the mounting seat is provided with a thread for threaded connection with the load body.

16. The load control device according to any one of claims 1 to 9, characterized in that: The load control device further comprises a hanging structure arranged on the load fixing member, and the hanging structure is used for connecting with the aircraft.

17. An airborne payload, used to be mounted on an aircraft and dropped to a target location by the aircraft, characterized in that: It comprises a load body and a load control device according to any one of claims 1 to 16, wherein the load body is connected to the front end of the load control device.

Images