CN111090287A - Remote control for controlling an aircraft - Google Patents
Remote control for controlling an aircraft Download PDFInfo
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- CN111090287A CN111090287A CN201811234619.3A CN201811234619A CN111090287A CN 111090287 A CN111090287 A CN 111090287A CN 201811234619 A CN201811234619 A CN 201811234619A CN 111090287 A CN111090287 A CN 111090287A
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- 230000005540 biological transmission Effects 0.000 claims description 2
- 230000001174 ascending effect Effects 0.000 abstract description 2
- 230000007246 mechanism Effects 0.000 description 20
- 230000008859 change Effects 0.000 description 2
- 230000004913 activation Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D1/00—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
- G05D1/10—Simultaneous control of position or course in three dimensions
- G05D1/101—Simultaneous control of position or course in three dimensions specially adapted for aircraft
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- Aviation & Aerospace Engineering (AREA)
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- Automation & Control Theory (AREA)
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Abstract
The invention provides a remote controller for controlling an aircraft, which comprises a control main body, a first control rocker, a second control rocker, a first knob and a second knob, wherein the first control rocker can start the control main body to realize ascending and descending of the aircraft, the second control rocker can start the control main body to realize advancing and retreating of the aircraft, the control main body can be started to realize clockwise or anticlockwise rotation of the aircraft by rotation of the first knob, the control main body can be started to realize left-right translation of the aircraft by rotation of the second knob, and the offset angle of the first knob or the second knob relative to a first starting position is in direct proportion to the running speed of the aircraft. The rotation speed and the left-right translation speed of the aircraft can be finely adjusted through the first knob or the second knob, so that the fine control of the speed of the aircraft is realized, the flying speed of the aircraft is uniform, and the aerial image is smoother and smoother.
Description
Technical Field
The invention belongs to the technical field of aircrafts, and particularly relates to a remote controller for controlling an aircraft.
Background
When the unmanned aerial vehicle flies in the air, the steering of the nose and the left and right sides of the aircraft are adjusted by the rudder amount of the rocker in the traditional remote controller control mode, but the uniform and smooth control flight can be realized only by the experience of manually adjusting and controlling the rudder amount. However, in order to obtain a high-quality aerial image, it is extremely difficult for a user to take a smooth image by manually controlling the rudder amount to fly.
Disclosure of Invention
The invention aims to provide a remote controller for controlling an aircraft, and aims to solve the technical problem that in the prior art, the uniform speed control is difficult to achieve by controlling the flight through manually controlling the rudder amount so as to enable the flight to be smooth.
The invention is realized in that a remote controller for controlling an aircraft, which is used for controlling the flight of the aircraft, comprises:
the control body is used for carrying out wireless transmission with the aircraft and controlling the aircraft to fly, and has a first control state capable of controlling the aircraft to ascend, a second control state capable of controlling the aircraft to descend, a third control state capable of controlling the aircraft to advance, a fourth control state capable of controlling the aircraft to retreat, a fifth control state capable of controlling the aircraft body to rotate anticlockwise, a sixth control state capable of controlling the aircraft body to rotate clockwise, a seventh control state capable of controlling the aircraft to translate leftwards and an eighth control state capable of controlling the aircraft to translate rightwards;
one end of the first control rocker is rotatably connected to the control main body and can start the first control state after the free end of the first control rocker rotates towards a first direction and start the second control state after the free end of the first control rocker rotates towards a second direction;
one end of the second control rocker is rotatably connected to the control main body and can start the third control state after the free end of the second control rocker rotates towards a third direction and start the fourth control state after the free end of the second control rocker rotates towards a fourth direction;
a first knob rotatably connected to the control body and capable of starting the fifth control state after counterclockwise rotation thereof and starting the sixth control state after clockwise rotation thereof; the first knob has a first starting position, an offset angle of the first knob relative to the first starting position when the first knob is rotated counterclockwise is proportional to a counterclockwise rotational velocity of the fuselage of the aircraft, and an offset angle of the first knob relative to the first starting position when the first knob is rotated clockwise is proportional to a clockwise rotational velocity of the fuselage of the aircraft;
a second knob rotatably connected to the control body and capable of starting the seventh control state after counterclockwise rotation thereof and starting the eighth control state after clockwise rotation thereof; the second knob has a second starting position, the angle of offset of the second knob relative to the second starting position when the second knob is rotated counterclockwise is proportional to the speed of the left translation of the aircraft, and the angle of offset of the second knob relative to the second starting position when the second knob is rotated clockwise is proportional to the speed of the right translation of the aircraft.
Further, the first control rocker is capable of actuating the fifth control state upon rotation of its free end in a fifth direction and the sixth control state upon rotation of its free end in a sixth direction.
Further, the second control rocker is capable of actuating the seventh control state upon rotation of its free end in a seventh direction and the eighth control state upon rotation of its free end in an eighth direction.
Further, the remote controller for controlling the aircraft further comprises a first change-over switch, and the first change-over switch has a first opening state capable of cutting off a connection path of the first control rocker to start the fifth control state and the sixth control state and a first closing state capable of cutting off a connection path of the first knob to start the fifth control state and the sixth control state.
Further, the remote controller for controlling the aircraft further comprises a second change-over switch, and the second change-over switch has a second opening state capable of cutting off a connection path of the second control rocker to start the seventh control state and the eighth control state and a second closing state capable of cutting off a connection path of the second knob to start the seventh control state and the eighth control state.
Further, the first direction is the same as the fifth direction, the second direction is the same as the sixth direction, the third direction is the same as the seventh direction, and the fourth direction is the same as the eighth direction.
Further, the first direction and the fifth direction are forward, the second direction and the sixth backward, the third direction and the seventh leftward, and the fourth direction and the eighth rightward.
Further, the remote controller for controlling the aircraft further comprises a tripod head horizontal rotating roller for controlling the tripod head horizontal rotating angle of the aircraft and a tripod head pitching roller for controlling the tripod head pitching angle of the aircraft.
Further, the remote controller for controlling the aircraft further comprises a display screen for displaying real-time images acquired by the aircraft.
Further, the remote controller for controlling the aircraft further comprises a flight mode switch for switching the flight mode of the aircraft, a shooting switch for controlling the camera of the aircraft to shoot and record pictures and a throwing switch for controlling the throwing device of the aircraft to throw in actions.
Compared with the prior art, the invention has the technical effects that: according to the invention, the offset angle of the first knob relative to the first starting position when the first knob is rotated anticlockwise is proportional to the anticlockwise rotation speed of the fuselage of the aircraft, the offset angle of the second knob relative to the first starting position when the first knob is rotated clockwise is proportional to the clockwise rotation speed of the fuselage of the aircraft, the offset angle of the second knob relative to the second starting position when the second knob is rotated anticlockwise is proportional to the leftward translation speed of the aircraft, and the offset angle of the second knob relative to the second starting position when the second knob is rotated clockwise is proportional to the rightward translation speed of the aircraft, so that the rotation amount and the rotation speed of the aircraft can be quantized through the first knob and can be finely adjusted according to needs, and the leftward and rightward translation speed of the aircraft can also be quantized through the second knob and can be finely adjusted according to needs, so that the flight amplitude and the change speed of the aircraft can be controlled and fine control can, the flying speed and the steering of the aircraft are more uniform, and the aerial images are smoother and smoother.
On the other hand, the first knob and the second knob can be fixed at screwing positions and cannot be automatically reset, the rocker can be automatically reset when the traditional rocker is controlled, so that the hands of a user cannot leave the rocker, and the rocker is easy to be unstably controlled due to slight hand shaking when the rocker is manually fixed, so that the rocker can be stably controlled by the user with very rich experience to enable the aircraft to run at a constant speed. And because the functions of controlling the aircraft to fly up and down, fly back and forth, and horizontally move left and right and rotate clockwise or anticlockwise are controlled by the four components respectively, a user can simultaneously control at least two components to enable the aircraft to carry out various flight actions simultaneously, and the flight efficiency is improved.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments of the present invention or in the description of the prior art will be briefly described below, and it is obvious that the drawings described below are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.
Fig. 1 is a front view of a remote control for controlling an aircraft provided by an embodiment of the present invention.
Description of reference numerals:
10. a control body; 101. a charging interface; 11. a first control rocker; 12. a second control rocker; 13. a first knob; 14. a second knob; 15. a first changeover switch; 16. a second changeover switch; 20. a display screen; 31. a throwing switch; 32. a shooting switch; 33. a flight mode selector switch; 34. a return switch; 40. a power switch; 51. a hoisting ring; 52. lifting handle
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention.
In the description of the present invention, it is to be understood that the terms "length", "width", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on the orientations or positional relationships illustrated in the drawings, and are used merely for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and thus, are not to be construed as limiting the present invention.
In this embodiment, fig. 1 is a front view of a remote controller provided by the present invention, and is defined according to the XY rectangular coordinate system established in fig. 1: one side in the positive direction of the X axis is defined as front, and one side in the negative direction of the X axis is defined as back; the side in the positive Y-axis direction is defined as the left side, and the side in the negative Y-axis direction is defined as the right side.
Furthermore, the terms "first", "second", "third", "fourth", "fifth", "sixth", "seventh", "eighth" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implying any number of technical features indicated. Thus, features defined as "first", "second", "third", "fourth", "fifth", "sixth", "seventh", "eighth" may explicitly or implicitly include one or more of such features. In the description of the present invention, "a plurality" means two or more unless specifically defined otherwise.
In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can, for example, be fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments.
The invention provides a remote controller for controlling an aircraft, which is used for controlling the flight of the aircraft. The aircraft includes the flight main part, connect in the cloud platform of flight main part, connect in the camera of cloud platform and be used for throwing in the device of puting in of goods and materials.
Referring to fig. 1, the remote controller for controlling an aircraft includes a control body 10 for wirelessly transmitting with the aircraft and controlling the aircraft to fly, a first control rocker 11 having one end rotatably connected to the control body 10, a second control rocker 12 having one end rotatably connected to the control body 10, a first knob 13 rotatably connected to the control body 10, a second knob 14 rotatably connected to the control body 10, a first switch 15 for switching a control path of the first control rocker 11 or the first knob 13, a second switch 16 for switching a control path of the second control rocker 12 or the second knob 14, a mapping antenna for transmitting an image signal, a display screen 20 for displaying a real-time image acquired by the camera, a flight mode switch 33 for switching a flight mode of the aircraft, The device comprises a holder horizontal rotating roller (not shown in the figure) for controlling the holder horizontal rotating angle, a holder pitching roller (not shown in the figure) for controlling the holder pitching angle, a battery (not shown in the figure) for supplying power to the control main body 10, a power switch 40 for connecting or disconnecting the control main body 10 and the battery, a shooting switch 32 for controlling the camera to take pictures or record videos, a throwing switch 31 for controlling the throwing device to throw in actions, a return switch 34 for controlling the aircraft to intelligently return to the air, a hanging ring 51 for hanging and a handle 52 for carrying.
Referring to fig. 1, in the embodiment of the present invention, the control main body 10 includes a housing having an accommodating cavity and a control mechanism located in the accommodating cavity, and the housing is provided with a charging interface 101 for charging the battery and a plurality of mounting holes penetrating through the accommodating cavity. The first control rocker 11 and the second control rocker 12 are rod-shaped, one end of each of the first control rocker 11 and the second control rocker 12 penetrates through one of the mounting holes and extends into the accommodating cavity, the other end of each of the first control rocker 11 and the second control rocker 12 can rotate around one end of the corresponding end extending into the accommodating cavity, the free ends of the first control rocker 11 and the second control rocker 12 are provided with starting points, when the aircraft is not started, the free ends of the first control rocker 11 and the second control rocker 12 are located at the starting points, and at the moment, the first control rocker 11 and the second control rocker 12 are disconnected with the control mechanism. Preferably, the first control rocker 11 and the second control rocker 12 each have at least two degrees of freedom in rotation, and when the free ends of the two leave the starting point and deflect to the side with the degrees of freedom, a connection is established with the control mechanism to control the aircraft to fly. More preferably, the housing is marked with scales for measuring the rotation amplitude of the first control rocker 11 and the second control rocker 12. Further, the remote controller for controlling the aircraft further comprises a rebound structure for automatically returning the free ends of the first remote control rocker or/and the second control rocker 12 to their respective starting points, so that when a user operates the first control rocker 11 and the second control rocker 12, the position of the first control rocker 11 or the second control rocker 12 needs to be manually fixed and the hand cannot be separated from the first control rocker 11 or the second control rocker 12.
In an embodiment of the present invention, the control mechanism has a first control state capable of controlling the ascent of the aircraft, a second control state capable of controlling the descent of the aircraft, a third control state capable of controlling the forward movement of the aircraft, a fourth control state capable of controlling the backward movement of the aircraft, a fifth control state capable of controlling the counterclockwise rotation of the fuselage of the aircraft, a sixth control state capable of controlling the clockwise rotation of the fuselage of the aircraft, a seventh control state capable of controlling the leftward translation of the aircraft, and an eighth control state capable of controlling the rightward translation of the aircraft. The aircraft nose rotates towards the left of the aircraft relative to the tail in a counter-clockwise rotation mode, and the aircraft nose rotates towards the right of the aircraft relative to the tail in a clockwise rotation mode.
The first control rocker 11 can be connected with the control mechanism and starts the first control state after the free end of the first control rocker rotates towards a first direction from the starting point of the first control rocker, the aircraft starts to ascend, when the aircraft reaches a specified height and does not need to ascend continuously, the free end of the first control rocker 11 is restored to the starting point of the first control rocker, and the aircraft stops ascending; the first control rocker 11 can also establish connection with the control mechanism and start the second control state after the free end of the first control rocker rotates from the starting point to the second direction, the aircraft starts to descend, and when the aircraft reaches the designated height and does not need to descend continuously, the free end of the first control rocker 11 is restored to the starting point, and the aircraft stops descending.
The second control rocker 12 can be connected with the control mechanism after the free end of the second control rocker rotates towards a third direction from the starting point of the second control rocker and starts the third control state, the aircraft starts to advance, when the aircraft reaches a specified position and does not need to advance continuously, the free end of the first control rocker 11 is restored to the starting point of the first control rocker, and the aircraft stops advancing; the second control rocker 12 can also establish connection with the control mechanism and start the fourth control state after the free end of the second control rocker rotates from the starting point to the fourth direction, the aircraft starts to retreat, when the aircraft reaches the designated position and does not need to retreat continuously, the free end of the first control rocker 11 is restored to the starting point, and the aircraft stops retreating.
The first knob 13 has a first starting position and is capable of establishing a connection with the control mechanism and activating the fifth control state after it has been rotated counterclockwise from the first starting position, the aircraft starts to rotate counterclockwise, the angle of deviation of its counterclockwise rotation with respect to the first starting position is proportional to the counterclockwise rotational speed of the fuselage of the aircraft, after the fuselage of the aircraft has been rotated to a specified angle, the first knob 13 is restored to the first starting position, the first knob 13 is disconnected from the control mechanism, and the aircraft stops rotating counterclockwise; the first knob 13 is connected to the control mechanism after it is rotated clockwise from the first start position, and a sixth control state is started, the aircraft starts to rotate clockwise, the offset angle of the aircraft relative to the first start position when the aircraft rotates clockwise is proportional to the clockwise rotation speed of the fuselage of the aircraft, after the fuselage of the aircraft rotates to a specified angle, the first knob 13 is restored to the first start position, the first knob 13 is disconnected from the control mechanism, and the aircraft stops rotating clockwise. Preferably, the first knob 13 is offset in rotation by no more than 180 ° counterclockwise or clockwise from the first starting position. In particular, the housing has a rotational speed scale on it for indicating the rotational speed of the aircraft, which is indicated in the circumferential direction of the first knob 13.
The second knob 14 has a second starting position and is capable of establishing a connection with the control mechanism after being rotated counterclockwise from the second starting position to activate the seventh control state, the aircraft starts to translate to the left, the angle of deviation of the aircraft from the second starting position when rotated counterclockwise is proportional to the speed of the aircraft translating to the left, when the aircraft does not need to move to the left, the second knob 14 is restored to the second starting state, the second knob 14 is disconnected from the control mechanism, and the aircraft stops moving to the left; the second knob 14 is connected with the control mechanism after the second start position rotates clockwise to start an eighth control state, the aircraft starts to translate rightward, the offset angle of the second knob 14 relative to the second start position when the second knob rotates clockwise is proportional to the speed of the aircraft translating rightward, when the aircraft does not need to move rightward, the second knob 14 is recovered to the second start state, the second knob 14 is disconnected with the control mechanism, and the aircraft stops moving rightward. Preferably, the second knob 14 is offset in rotation by no more than 180 ° counterclockwise or clockwise from the second starting position. In particular, the casing has a translation scale indicating the translation speed of the aircraft, the translation scale being indicated in the circumferential direction of the second knob 14.
According to the invention, the offset angle of the first knob 13 relative to the first starting position when rotating anticlockwise is proportional to the anticlockwise rotation speed of the fuselage of the aircraft, the offset angle of the first knob relative to the first starting position when rotating clockwise is proportional to the clockwise rotation speed of the fuselage of the aircraft, the offset angle of the second knob 14 relative to the second starting position when rotating anticlockwise is proportional to the speed of the aircraft translating leftwards, and the offset angle of the second knob relative to the second starting position when rotating clockwise is proportional to the speed of the aircraft translating rightwards, so that the rotation amount and the rotation speed of the aircraft can be quantified by the first knob 13 and can be finely adjusted as required, and the left-right translation speed of the aircraft can also be quantified by the second knob 14 and can be finely adjusted as required, therefore, the flight amplitude and the change speed of the aircraft are controllable, fine control is realized, the flying speed and the steering of the aircraft are more uniform, and the aerial image is smoother and smoother.
On the other hand, the first knob 13 and the second knob 14 can be fixed at screwing positions and cannot be automatically reset, the rocker can be automatically reset when the traditional rocker is controlled, so that the hands of a user cannot leave the rocker, and the rocker is easily and unstably controlled due to slight hand shaking when the rocker is manually fixed, so that the user is required to have very rich experience to control the rocker stably so as to enable the aircraft to run at a constant speed. And because the functions of controlling the aircraft to fly up and down, fly back and forth, and horizontally move left and right and rotate clockwise or anticlockwise are controlled by the four components respectively, a user can simultaneously control at least two components to enable the aircraft to carry out various flight actions simultaneously, and the flight efficiency is improved.
Further, the first control rocker 11 can also establish connection with the control mechanism and start the fifth control state after the free end of the first control rocker rotates from the starting point to the fifth direction, the aircraft starts to rotate counterclockwise, when the fuselage of the aircraft rotates to a specified angle, the free end of the first control rocker 11 is restored to the starting point, and the aircraft stops rotating counterclockwise; after the free end of the aircraft rotates from the starting point to the sixth direction, the aircraft is connected with the control mechanism and starts the sixth control state, the aircraft starts to rotate clockwise, when the aircraft body rotates to a specified angle, the free end of the first control rocker 11 is restored to the starting point, and the aircraft stops rotating clockwise.
Furthermore, the second control rocker 12 can also establish connection with the control mechanism and start the seventh control state after the free end of the second control rocker rotates from the starting point to the seventh direction, the aircraft starts to translate to the left, when the aircraft moves to the designated position to the left, the free end of the second control rocker 12 is restored to the starting point, and the aircraft stops moving to the left; after the free end of the aircraft rotates towards the eighth direction from the starting point, the aircraft is connected with the control mechanism and starts the eighth control state, the aircraft starts to translate rightwards, when the aircraft moves rightwards to the designated position, the free end of the second control rocker 12 is restored to the starting point, and the aircraft stops moving rightwards.
According to the invention, the first control rocker 11 or the second control rocker 12 can realize the rapid operation of left-right rotation or left-right translation of the aircraft, and the operation experience is better.
Preferably, the first direction is the same as the fifth direction, the second direction is the same as the sixth direction, the third direction is the same as the seventh direction, and the fourth direction is the same as the eighth direction, so as to conform to the use habit and the control hand feeling of the user and reduce the misoperation of the user. More preferably, the first direction and the fifth direction are forward, the second direction and the sixth backward, the third direction and the seventh leftward, and the fourth direction and the eighth rightward. The rotation direction of each rocker is the same as or related to the flight direction of the aircraft, so that the rotation direction of each rocker is easy to remember by a user, and misoperation is reduced.
Further, in the embodiment of the present invention, the first switch 15 has a first on state capable of disconnecting the connection path of the first control rocker 11 for starting the fifth control state and the sixth control state and a first off state capable of disconnecting the connection path of the first knob 13 for starting the fifth control state and the sixth control state, and the second switch 16 has a second on state capable of disconnecting the connection path of the second control rocker 12 for starting the seventh control state and the eighth control state and a second off state capable of disconnecting the connection path of the second knob 14 for starting the seventh control state and the eighth control state.
It can be understood that, when the first switch 15 is in the first open state, a user can control the free end of the first control rocker 11 to rotate from the starting point thereof toward the first direction or the second direction to activate the first control state or the second control state, respectively, and at this time, the activation of the fifth control state and the sixth control state is completed by the first knob 13, and the first control rocker 11 cannot be activated; when the first switch 15 is in the first off state, a user can control the free end of the first control rocker 11 to rotate from the starting point to the first direction, the second direction, the fifth direction or the sixth direction to respectively start the first control state, the second control state, the fifth control state or the sixth control state, and at this time, the start of the fifth control state and the sixth control state is completed by the first control rocker 11, and the first knob 13 cannot be started. When the second switch 16 is in the second on state, the user can control the free end of the second control rocker 12 to rotate from the starting point to the third direction or the fourth direction to start the third control state or the fourth control state, respectively, and at this time, the start of the seventh control state and the eighth control state is completed by the second knob 14, and the second control rocker 12 cannot be started; when the second switch 16 is in the second off state, the user can control the free end of the second control rocker 12 to rotate from the starting point to the third direction, the fourth direction, the seventh direction or the eighth direction to respectively start the third control state, the fourth control state, the seventh control state or the eighth control state, and at this time, the start of the seventh control state and the eighth control state is completed by the second control rocker 12, and the second knob 14 cannot be started.
In this way, the selection of the components for controlling the left-right rotation of the aircraft nose and the left-right translation of the aircraft is realized by the opening or closing of the first switch 15 and the second switch 16, and in practical use, a user can adjust the first switch 15 and the second switch 16 according to the needs and flight requirements of the aircraft to enable the aircraft to reach an optimal flight state.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention.
Claims (10)
1. A remote control for controlling an aircraft, for controlling the flight of the aircraft, comprising:
the control body is used for carrying out wireless transmission with the aircraft and controlling the aircraft to fly, and has a first control state capable of controlling the aircraft to ascend, a second control state capable of controlling the aircraft to descend, a third control state capable of controlling the aircraft to advance, a fourth control state capable of controlling the aircraft to retreat, a fifth control state capable of controlling the aircraft body to rotate anticlockwise, a sixth control state capable of controlling the aircraft body to rotate clockwise, a seventh control state capable of controlling the aircraft to translate leftwards and an eighth control state capable of controlling the aircraft to translate rightwards;
one end of the first control rocker is rotatably connected to the control main body and can start the first control state after the free end of the first control rocker rotates towards a first direction and start the second control state after the free end of the first control rocker rotates towards a second direction;
one end of the second control rocker is rotatably connected to the control main body and can start the third control state after the free end of the second control rocker rotates towards a third direction and start the fourth control state after the free end of the second control rocker rotates towards a fourth direction;
a first knob rotatably connected to the control body and capable of starting the fifth control state after counterclockwise rotation thereof and starting the sixth control state after clockwise rotation thereof; the first knob has a first starting position, an offset angle of the first knob relative to the first starting position when the first knob is rotated counterclockwise is proportional to a counterclockwise rotational velocity of the fuselage of the aircraft, and an offset angle of the first knob relative to the first starting position when the first knob is rotated clockwise is proportional to a clockwise rotational velocity of the fuselage of the aircraft;
a second knob rotatably connected to the control body and capable of starting the seventh control state after counterclockwise rotation thereof and starting the eighth control state after clockwise rotation thereof; the second knob has a second starting position, the angle of offset of the second knob relative to the second starting position when the second knob is rotated counterclockwise is proportional to the speed of the left translation of the aircraft, and the angle of offset of the second knob relative to the second starting position when the second knob is rotated clockwise is proportional to the speed of the right translation of the aircraft.
2. A remote control for controlling an aircraft according to claim 1, wherein the first control rocker is capable of activating the fifth control state upon rotation of its free end in a fifth direction and the sixth control state upon rotation of its free end in a sixth direction.
3. A remote control for controlling an aircraft according to claim 2, wherein the second control rocker is capable of activating the seventh control state upon rotation of its free end in a seventh direction and the eighth control state upon rotation of its free end in an eighth direction.
4. A remote control for controlling an aircraft according to claim 3, further comprising a first switch having a first on state capable of disconnecting the connection path of the first control rocker actuating the fifth control state and the sixth control state and a first off state capable of disconnecting the connection path of the first knob actuating the fifth control state and the sixth control state.
5. The remote control for controlling an aircraft according to claim 4, further comprising a second toggle switch having a second on state capable of disconnecting the connection path of the second control rocker actuating the seventh control state and the eighth control state and a second off state disconnecting the connection path of the second knob actuating the seventh control state and the eighth control state.
6. The remote control for controlling an aircraft according to any one of claims 1 to 5, wherein the first direction is the same direction as the fifth direction, the second direction is the same direction as the sixth direction, the third direction is the same direction as the seventh direction, and the fourth direction is the same direction as the eighth direction.
7. The remote control for controlling an aircraft according to claim 6, wherein the first direction and the fifth direction are forward, the second direction and the sixth rearward, the third direction and the seventh direction are leftward, and the fourth direction and the eighth direction are rightward.
8. The remote controller for controlling an aircraft according to any one of claims 1 to 5, wherein the remote controller for controlling an aircraft further comprises a pan/tilt roller for controlling a pan/tilt angle of the aircraft and a pan/tilt roller for controlling a pan/tilt angle of the aircraft.
9. The remote control for controlling an aircraft according to any one of claims 1 to 5, wherein the remote control for controlling an aircraft further comprises a display screen for displaying live images captured by the aircraft.
10. The remote control for controlling an aircraft according to any one of claims 1 to 5, wherein the remote control for controlling an aircraft further comprises a flight mode switch for switching a flight mode of the aircraft, a shooting switch for controlling a camera of the aircraft to shoot and record a video, and a release switch for controlling a release device of the aircraft to perform a release action.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811234619.3A CN111090287A (en) | 2018-10-23 | 2018-10-23 | Remote control for controlling an aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
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