Description:
FIELD OF THE INVENTION
The present invention generally relates to a system for flexible configuration multi-copter drive and particularly to a system and method for flexible configuration multi-copter drive that allows for customizable and adaptable drone designs with enhanced flight performance and versatility.
BACKGROUND
Multi-copter drones have gained widespread popularity due to their maneuverability, stability, and wide range of applications. Conventional multi-copter drones typically consist of a frame with multiple motor-driven propellers, which generate lift and control the drone's movements. However, existing multi-copter drive systems suffer from limitations in terms of configuration flexibility and adaptability. Traditional multi-copter designs often feature fixed configurations of motor-propeller units, such as quadcopters (four motors), hex copters (six motors), or octocopters (eight motors). While these configurations offer stability and redundancy, they lack the ability to easily adapt to specific mission requirements, payload capacities, or operational constraints. Moreover, existing multi-copter drive systems are often limited in terms of scalability and performance optimization. Adding or removing motor-propeller units to accommodate different payload weights or desired flight characteristics requires significant modifications to the frame and control systems. This limits the versatility and cost-effectiveness of multi-copter drones for various applications. Therefore, there is a need for a flexible configuration multi-copter drive system that allows for customizable and adaptable drone designs, enabling optimal performance, payload capacity, and flight characteristics while maintaining stability and control.
CN203512034U discloses the utility model relates to a multi-rotor wing unmanned aerial vehicle (UAV) for agriculture and forestry plant protection. The multi-rotor wing UAV comprises an aircraft which comprises a main airframe, an aircraft control system, a rotor wing mounting rack, a plurality of rotor wing power support arms, a functional nacelle and an undercarriage, wherein the aircraft control system is arranged in the main airframe; the rotor wing mounting rack is sheathed on the main airframe in a replaceable way; the plurality of rotor wing power support arms are selectively arranged on the rotor wing mounting rack; the functional nacelle is arranged under the main airframe in a replaceable way; the undercarriage is connected with the functional nacelle. The multi-rotor wing UAV is specially designed for aviation plant protection operation, configurations with different power combinations and the functional nacelle can be rapidly replaced, and multiple tasks such as aerial observation and aerial application of the agriculture and forestry plant protection can be completed; the multi-rotor wing UAV has the characteristics of being flexible, low in cost and convenient to use, and having a multitask function.
The existing invention does not allow for customizable and adaptable drone designs, enabling optimal performance. Hence, there is a need for an improved system to provide a flexible configuration multi-copter drive system.
OBJECTIVE OF THE INVENTION
The main objective of the present invention is to provide a reconfigurable multi-copter.
Another objective of the present invention is to provide customizable and adaptable multi-copter designs.
Yet another objective of the present invention is to provide enhanced flight performance and versatility.
Yet another objective of the present invention is to increase economic efficiency.
Further objectives, advantages, and features of the present invention will become apparent from the detailed description provided herein below, in which various embodiments of the disclosed invention are illustrated by way of example.

SUMMARY OF THE INVENTION
The present invention relates to a flexible configuration multi-copter drive system. The present invention includes a drive unit, one or more rotating drives a mounting rail, and a main multi-copter body, the drive unit includes a drive unit socket and an electronic motor control. One or more rotating drives are able to be plugged into the drive unit socket of the drive unit in different types of configurations to form a flexible configuration multi-copter. One or more rotating drives are detachable such that one or more rotating drives are plugged in and plugged out from the drive unit socket of the drive unit based on the type of configuration. Herein, the electronic motor controller is connected to the more or more rotating drives to supply power and control rotor speed and the rotor blade angle. The main multi-copter body is mechanically coupled to the drive unit through the mounting rail. The main multi-copter body includes a control unit, a pluggable connection, and a main power supply. The drive unit is connected to the control unit of the main multi-copter body by means of pluggable connections. The main power supply is located in the main multi-copter body. Herein, the type of configuration of the drive unit is detected by the control unit by the signal coded in the pluggable connection. Herein, the control unit by means of parameters setup stored in the firmware set the drive unit for any possible configurations. Herein one or more rotating drives are able to be plugged into the drive unit socket of the drive unit in different types of configurations that are selected from a quadcopter, a hex copter, and an octocopter.
The main advantage of the present invention is that the present invention provides a reconfigurable multi-copter.
Another advantage of the present invention is that the present invention provides customizable and adaptable multi-copter designs.
Yet another advantage of the present invention is that the present invention provides enhanced flight performance and versatility.
Yet another advantage of the present invention is that the present invention increases economic efficiency.
Further objectives, advantages, and features of the present invention will become apparent from the detailed description provided herein below, in which various embodiments of the disclosed invention are illustrated by way of example.
BRIEF DESCRIPTION OF THE DRAWINGS
The accompanying drawings are incorporated in and constitute a part of this specification to provide a further understanding of the invention. The drawings illustrate one embodiment of the invention and together with the description, serve to explain the principles of the invention.
Fig.1. illustrates the flexible configuration multi-copter drive system in exploded view.
Fig.2. illustrates the flexible configuration multi-copter drive system isometric view.
Fig.3. illustrates a sectioned view of a flexible configuration multi-copter drive system.
Fig.4. illustrates an implementation of the same controller used with exchangeable rotating drives.
DETAILED DESCRIPTION OF THE INVENTION
Definition
The terms “a” or “an”, as used herein, are defined as one or as more than one. The term “plurality”, as used herein, is defined as two as or more than two. The term “another”, as used herein, is defined as at least a second or more. The terms “including” and/or “having”, as used herein, are defined as comprising (i.e., open language). The term “coupled”, as used herein, is defined as connected, although not necessarily directly, and not necessarily mechanically.
The term “comprising” is not intended to limit inventions to only claiming the present invention with such comprising language. Any invention using the term comprising could be separated into one or more claims using “consisting” or “consisting of” claim language and is so intended. The term “comprising” is used interchangeably used by the terms “having” or “containing”.
Reference throughout this document to “one embodiment”, “certain embodiments”, “an embodiment”, “another embodiment”, and “yet another embodiment” or similar terms means that a particular feature, structure, or characteristic described in connection with the embodiment is included in at least one embodiment of the present invention. Thus, the appearances of such phrases or in various places throughout this specification are not necessarily all referring to the same embodiment. Furthermore, the particular features, structures, or characteristics are combined in any suitable manner in one or more embodiments without limitation.
The term “or” as used herein is to be interpreted as an inclusive or meaning any one or any combination. Therefore, “A, B or C” means any of the following: “A; B; C; A and B; A and C; B and C; A, B and C”. An exception to this definition will occur only when a combination of elements, functions, steps, or acts are in some way inherently mutually exclusive.
As used herein, the term "one or more" generally refers to, but not limited to, singular as well as the plural form of the term.
The drawings featured in the figures are to illustrate certain convenient embodiments of the present invention and are not to be considered as a limitation to that. Term "means" preceding a present participle of operation indicates the desired function for which there are one or more embodiments, i.e., one or more methods, devices, or apparatuses for achieving the desired function and that one skilled in the art could select from these or their equivalent in view of the disclosure herein and use of the term "means" is not intended to be limiting.
disclosure herein and use of the term "means" is not intended to be limiting.
Fig.1. illustrates the flexible configuration multi-copter drive system(100) exploded view. The system(100) is having a flexible drive unit(102), a mounting rail(118), one or more rotating drives(104), a main multi-copter body(116), and an electronic motor control(108). The one or more rotating drives(104) are plugged into the one drive unit socket(106) of the drive unit(102) in different configurations to form a flexible configuration multi-copter. The one or more rotating drives(104) are detachable such that the one or more rotating drives(104) are plugged in and plugged out from the drive unit socket(106) of the drive unit(102). The electronic motor control(108) is connected to the one or more rotating drives(104) to supply power and control rotor speed and rotor blade angle. The main multi-copter body(116) having a pluggable connection(112), main power supply(114) and a control unit(110). The main multi-copter body(116) is mechanically coupled to the drive unit(102) through the mounting rail(118) The drive unit(102) is connected to the control unit(110) of the main multi-copter body(116) by means of the pluggable connections(112). A main power supply(114) located in the main multi-copter body(116).
Fig.2. illustrates the flexible configuration multi-copter drive system(100) isometric view. The system(100) is having a flexible drive unit(102), one or more rotating drives(104), a main multi-copter body(116). The one or more rotating drives(104) are plugged into the one drive unit socket(106) of the drive unit(102) in different configurations to form a flexible configuration multi-copter. The one or more rotating drives(104) are detachable such that the one or more rotating drives(104) are plugged in and plugged out from the drive unit socket(106) of the drive unit(102). The main multi-copter body(116) is having a main power supply(114) and a control unit(110). The main multi-copter body(116) is mechanically coupled to the drive unit(102). A main power supply(114) is located in the main multi-copter body(116).
Fig.3. illustrates a sectioned view of a pluggable connection(112) and a mounting rail(118). The drive unit(102)(not shown in Fig.3) is connected to the control unit(110) (not shown in Fig.3) of the main multi-copter body(116) (not shown in Fig.3) by means of the pluggable connections(112). The mounting rail(118) is mechanically connected by means of seals, clamps or similar force-locked and detachable connections.
Fig.4. illustrates the implementation of the same controller used with exchangeable rotating drives.
The present invention relates to a flexible configuration multi-copter drive system. The present invention includes a drive unit, one or more rotating drives a mounting rail, and a main multi-copter body, the drive unit includes a drive unit socket and an electronic motor control. One or more rotating drives are able to be plugged into the drive unit socket of the drive unit in different types of configurations to form a flexible configuration multi-copter. One or more rotating drives are detachable such that one or more rotating drives are plugged in and plugged out from the drive unit socket of the drive unit based on the type of configuration. In an embodiment, the one or more rotating drives are able to be plugged into the drive unit socket of the drive unit in different types of configurations that are selected from a quadcopter, a hex copter, and an octocopter. Herein, the electronic motor control is connected to the more or more rotating drives to supply power and control rotor speed and rotor blade angle. The main multi-copter body is mechanically coupled to the drive unit through the mounting rail. In the preferred embodiment, the mounting rail is mechanically attached to the main multi-copter body that is coupled to the drive unit by means of detachable connections of the mounting rail that are selected from of seals, clamps, and similar force-locked. The main multi-copter body includes a control unit, a pluggable connection, and a main power supply. The drive unit is connected to the control unit of the main multi-copter body by means of the pluggable connections. The main power supply is located in the main multi-copter body. Herein, the type of configuration of the drive unit is detected by the control unit by the signal coded in the pluggable connection. Herein, the control unit by means of parameters setup stored in the firmware set the drive unit for any possible configurations. In an embodiment, the electronic motor control and the control unit are equipped with a single-board computer. In an embodiment, the main multi-copter body has multiple sensors and payload selected from optical sensor, thermal sensor, LIDAR sensor, Ground Penetrating Radar (GPR) Sensor, Camera, Tactical EO/IR sensors, Ultra-high-resolution aerial cameras.
In an embodiment, the present invention relates to a flexible configuration multi-copter drive system. The present invention includes a drive unit, one or more rotating drives a mounting rail, and a main multi-copter body, the drive unit includes one or more drive unit sockets and an electronic motor control. One or more rotating drives are able to be plugged into the one or more drive unit sockets of the drive unit in different types of configurations to form a flexible configuration multi-copter. One or more rotating drives are detachable such that one or more rotating drives are plugged in and plugged out from the one or more drive unit sockets of the drive unit based on the type of configuration. In an embodiment, the one or more rotating drives are able to be plugged into the one or more drive unit sockets of the drive unit in different types of configurations including, but not limited to a quadcopter, a hex copter, and an octocopter. Herein, the electronic motor control is connected to the more or more rotating drives to supply power and control rotor speed and the rotor blade angle. The main multi-copter body is mechanically coupled to the drive unit through the mounting rail. In the preferred embodiment, the mounting rail is mechanically attached to the main multi-copter body that is coupled to the drive unit by means of detachable connections of the mounting rail that are selected from of seals, clamps, and similar force-locked. The main multi-copter body includes a control unit, a pluggable connection, and a main power supply. The drive unit is connected to the control unit(110) of the main multi-copter body by means of the pluggable connections. The main power supply is located in the main multi-copter body. Herein, the type of configuration of the drive unit is detected by the control unit by the signal coded in the pluggable connection. Herein, the control unit by means of parameters setup stored in the firmware set the drive unit for any possible configurations. In an embodiment, the electronic motor control and the control unit are equipped with a single-board computer. In an embodiment, the main multi-copter body has multiple sensors and payload selected from optical sensor, thermal sensor, LIDAR sensor, Ground Penetrating Radar (GPR) Sensor, Camera, Tactical EO/IR sensors, Ultra-high-resolution aerial cameras.
In an embodiment, the present invention relates to a method to operate the flexible configuration multi-copter drive system, the method includes
one or more rotating drives are plugged into a drive unit socket of the drive unit in different types of configurations to form a flexible configuration multi-copter;
one or more rotating drives are detachable such that one or more rotating drives are plugged in and plugged out from the drive unit socket of the drive unit based on the type of configuration;
an electronic motor control is connected to the one or more rotating drives to supply power and control rotor speed and rotor blade angle;
a main multi-copter body, the main multi-copter body is mechanically attached to the drive unit through a mounting rail;
the drive unit is connected to the control unit of the main multi-copter body by means of the pluggable connections,
a main power supply;
the main power supply located in the main multi-copter body;
the configurations of the drive unit are detected by the control unit by the signal coded in the pluggable connection; and
the control unit by means of parameters setup stored in the firmware of the control unit, configures the drive unit for any possible configurations.
Herein, one or more rotating drives are able to be plugged into the drive unit socket of the drive unit in different types of configurations that are selected from a quadcopter, a hex copter, and an octocopter.
In an embodiment, the present invention relates to a method to operate the flexible configuration multi-copter drive system, the method includes
one or more rotating drives are plugged into one or more drive unit sockets of the drive unit in different types of configurations to form a flexible configuration multi-copter;
one or more rotating drives are detachable such that one or more rotating drives are plugged in and plugged out from the one or more drive unit sockets of the drive unit based on the type of configuration;
an electronic motor control is connected to the one or more rotating drives to supply power and control rotor speed and rotor blade angle;
a main multi-copter body, the main multi-copter body is mechanically attached to the drive unit through a mounting rail;
the drive unit is connected to the control unit of the main multi-copter body by means of the pluggable connections,
a main power supply;
the main power supply located in the main multi-copter body;
the configurations of the drive unit are detected by the control unit by the signal coded in the pluggable connection; and
the control unit by means of parameters setup stored in the firmware of the control unit, configures the drive unit for any possible configurations.
Herein, one or more rotating drives are able to be plugged into the one or more drive unit sockets of the drive unit in different types of configurations that are selected from a quadcopter, a hex copter, and an octocopter.
Further objectives, advantages, and features of the present invention will become apparent from the detailed description provided herein below, in which various embodiments of the disclosed present invention are illustrated by way of example and appropriate reference to accompanying drawings. Those skilled in the art to which the present invention pertains may make modifications resulting in other embodiment employing principles of the present invention without departing from its spirit or characteristics, particularly upon considering the foregoing teachings. Accordingly, the described embodiment are to be considered in all respects only as illustrative, and not restrictive, and the scope of the present invention is, therefore, indicated by the appended claims rather than by the foregoing description or drawings. Consequently, while the present invention has been described with reference to a particular embodiment, modifications of structure, sequence, materials, and the like apparent to those skilled in the art still fall within the scope of the invention as claimed by the applicant
, Claims:A flexible configuration multi-copter drive system(100), the system(100) comprises:
a drive unit(102), the drive unit(102) having;
an at least one drive unit socket(106) and
an electronic motor control(108);
an at least one or more rotating drives(104), the at least one or more rotating drives(104) are able to be plugged into the at least one drive unit socket(106) of the drive unit(102) in different types of configuration to form a flexible configuration multi-copter, wherein, the at least one or more rotating drives(104) are detachable such that the at least one or more rotating drives(104) are plugged in and plugged out from the at least one drive unit socket(106) of the drive unit(102) based on the type of configuration;
wherein, the electronic motor control(108) is connected to the at least one rotating drive(104) to supply power and control rotor speed and rotor blade angle;
a mounting rail(118);
a main multi-copter body(116), the main multi-copter body(116) is mechanically coupled to the drive unit(102) through the mounting rail(118), the main multi-copter body(116) having
a control unit(110),
a pluggable connection(112), the drive unit(102) is connected to the control unit(110) of the main multi-copter body(116) by means of the pluggable connections(112), and
a main power supply(114), the main power supply(114) located in the main multi-copter body(116);
wherein, the type of configuration of the drive unit(102) is detected by the control unit(110) by the signal coded in the pluggable connection(112);
wherein, the control unit(110) by means of parameters setup stored in the firmware set the drive unit(102) for any possible configurations.
1. The flexible configuration multi-copter drive system(100) as claimed in claim 1, wherein the mounting rail(118) is mechanically attached to the main multi-copter body(116) that is coupled to the drive unit(102) by means of detachable connections of the mounting rail(118) that are selected from of seals, clamps, and similar force-locked.
2. The flexible configuration multi-copter drive system(100) as claimed in claim 1, wherein the at least one or more rotating drives(104) are able to be plugged into the at least one drive unit socket(106) of the drive unit(102) in different types of configuration that are selected from a quadcopter, a hex copter, and an octocopter.
3. The flexible configuration multi-copter drive system(100) as claimed in claim 1, wherein the electronic motor control(108) and the control unit(110) are equipped with a single-board computer.
4. The flexible configuration multi-copter drive system(100) as claimed in claim 1, wherein the main multi-copter body(116) has multiple sensors and payload selected from an optical sensor, a thermal sensor, a LIDAR sensor, a Ground Penetrating Radar (GPR) Sensor, a Camera, an Tactical EO/IR sensors, an Ultra-high-resolution aerial cameras,
5. The flexible configuration multi-copter drive system(100) as claimed in claim 1, wherein the method to operate the flexible configuration multi-copter drive system(100), the method comprising:
an at least one or more rotating drives(104) are plugged into an at least one drive unit socket(106) of the drive unit(102) in different types of configuration to form a flexible configuration multi-copter;
the at least one or more rotating drives(104) are detachable such that the at least one or more rotating drives(104) are plugged in and plugged out from the at least one drive unit socket(106) of the drive unit(102) based on the type of configuration;
an electronic motor control(108) is connected to the at least one rotating drive(104) to supply power and control rotor speed and rotor blade angle,
a main multi-copter body(116), the main multi-copter body(116) is mechanically attached to the drive unit(102) through a mounting rail(118),
the drive unit(102) is connected to the control unit(110) of the main multi-copter body(116) by means of the pluggable connections(112),
a main power supply(114);
the main power supply(114) located in the main multi-copter body(116),
the configurations of the drive unit(102) is detected by the control unit(110) by the signal coded in the pluggable connection(112); and
the control unit(110) by means of parameters setup stored in the firmware of the control unit(110), configures the drive unit(102) for any possible configurations.
6. The method as claimed in claim 2, wherein the at least one or more rotating drives(104) are able to be plugged into the at least one drive unit socket(106) of the drive unit(102) in different types of configuration that are selected from a quadcopter, hex copter, and an octocopter