WO2017000528A1 - 一种具有多个驱动装置的驱动装置组合体及其应用 - Google Patents
一种具有多个驱动装置的驱动装置组合体及其应用 Download PDFInfo
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- WO2017000528A1 WO2017000528A1 PCT/CN2016/000308 CN2016000308W WO2017000528A1 WO 2017000528 A1 WO2017000528 A1 WO 2017000528A1 CN 2016000308 W CN2016000308 W CN 2016000308W WO 2017000528 A1 WO2017000528 A1 WO 2017000528A1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/40—Arrangements for mounting power plants in aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D41/00—Power installations for auxiliary purposes
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D41/00—Power installations for auxiliary purposes
- B64D2041/002—Mounting arrangements for auxiliary power units (APU's)
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Definitions
- the invention belongs to the field of power systems and can be applied to combined driving devices in the fields of aircraft, ships, excavation or tunneling machines, generator sets, combined light sources, wind power devices, spray spray nets and the like. More particularly, the present invention relates to an aircraft that can infinitely increase the amount of drive and load and an aircraft with a modular combination of multiple flight modes.
- an engine group for example, an aircraft engine group
- a tandem type for example, a linear type, a square shape, a ring type, or the like is often used.
- This method is limited by the cumbersome connection between the engines in the assembly, and unnecessary space and gaps between the engines are generated, resulting in an increase in the volume and weight of the combined device.
- the mechanical structure of the system is complex, and the mechanical structure of the components connected to each other in different positions in the assembly is uneven, resulting in stress concentration in the assembly (system). Infinitely accumulating the engine will eventually lead to the collapse of the connection structure, and thus cannot be infinitely increased.
- the number of engines in the assembly has limited load capacity.
- the fuselage that is, the carrying platform of the aircraft. At present, it is widely used in an aircraft with multiple driving devices.
- the composition of the fuselage is similar, mainly consisting of "central bearing plate or nacelle", arm and landing gear, and the "central bearing plate or nacelle” and the arm are formed by one
- the radial structure of the central point diverging to the periphery. This structure has the advantages of simple structure and light weight when the aircraft is relatively small in size. With the ever-increasing demand for the payload capacity of the aircraft in the future, the problem with this structure is that the more the driving device, the larger the space occupied by the rotating surface of the propeller or the driving device, and the size of the fuselage must be increased, so that it will continue to develop.
- helicopter-type aircraft In addition, the current shortcomings of helicopter-type aircraft are that their structure is almost no lift, high energy consumption, short range, and insufficient residual power in harsh environments, which is difficult to resist strong airflow changes. Under certain climatic conditions, the stability is not good, so the various missions cannot be completed in a long and stable manner.
- the present invention provides a combined drive device that can accommodate more drive devices per unit volume, the combined drive device optimizes the mechanical structure of the assembly, and achieves an even distribution of the weight and load of the aircraft itself.
- Unlimited benign expansion, combined with a streamlined and lightweight installation, the combined device can generate a powerful driving force while It has the characteristics of small size, light weight, high connection strength and strong load capacity.
- the present invention provides a drive assembly having a plurality of drive devices, the distribution of which is as follows:
- each set of parallel lines Is an equidistant line parallel to one side of the triangular unit, including a line in which the side is located, wherein the spacing of each set of parallel lines is a high length on a corresponding side of the triangular unit; the number of the driving devices Greater than or equal to 3, 4, 5, 6, 7, 8, 9, 10, 15, 24 or 30; or
- each of the other driving devices forms a tetrahedral unit having four triangular faces, the apex of which is the center of the four driving devices, the tetrahedral unit as the initial unit body, and the other driving devices are distributed in the The initial unit is external to the body and sequentially incorporated therein in such a manner that each of the other driving devices forms a tetrahedral unit with a triangular face on the unit body; the number of the driving devices is greater than or equal to 4, 5, 6, and 7, 8, 9, 10, 15, 24 or 30.
- the triangular unit is an equilateral triangle or the tetrahedral unit is a regular tetrahedron.
- the drive device is connected by a connection compartment or a connection device selected from, but not limited to, a cavity capsule, a keel frame, a skeleton, a planar body, and a planar hollow. .
- connection bay or connecting device is a fixed connection or an active connection.
- the drive means is an electric drive, an internal combustion engine drive, a hydraulic and hydraulic drive, a pneumatic drive, a manual drive or a composite drive.
- the present invention provides an aircraft that can increase the number of drives and the amount of load indefinitely to solve the problem of the number of engines and the upper limit of the load in the aircraft.
- the present invention also provides a system or aircraft having a plurality of drive devices, the system comprising the drive assembly of the first aspect of the invention.
- the aircraft includes a wing that is mounted on a drive assembly to form an aircraft having a plurality of flight modes.
- This aircraft with multiple flight modes organically integrates the characteristics of helicopter-type aircraft with fixed-wing aircraft, enabling the aircraft to fly accurately over long distances in a high-speed, energy-saving manner and in a low-speed and precise manner, demonstrating its complex missions. It has the advantage of a combination of multiple flight modes.
- the aircraft is removed from the mounting position occupied by the drive and the wing, and the remaining position is the mounting or mounting position of the flight aid or load.
- the wing rotates in the axial direction as a landing support for the aircraft.
- the combined driving device of the invention enables more driving devices to be accommodated in a unit volume, the combined driving device optimizes the mechanical structure of the assembly, adopts a framework of the de-mechanical center, and the weight of the driving device is spread over the connecting structure, so that The weight of the assembly is uniformly carried by the driving device in the assembly, and each additional driving device does not cause pressure on the overall system, but the driving force generated by the driving device carries its own mass and then accumulates the remaining power into the driving device assembly.
- the drive assembly can expand the number of drives infinitely and in a flexible manner, so that the combined device can generate a strong driving force while having small size, light weight and high connection strength. And the load capacity is strong.
- the present invention further provides the driving device assembly of the first aspect of the present invention or the aircraft of the second aspect of the present invention, wherein the driving device assembly is combined in the form of a module group,
- the module group includes a drive unit, a docking unit and an auxiliary unit.
- the aircraft comprises a driving device module, a connecting module, a carrying module and an auxiliary module.
- the driving device module constitutes a driving device unit
- the connecting module and the carrying module can be regarded as a connecting cabin unit, and the driving device module and the carrying module pass
- the connecting module is combined into an aircraft structural unit; the carrying module is also used as the fuselage structure of the aircraft while carrying energy and load; the carrying module is provided with a bearing space and a connection position with other modules or devices; the connecting module is provided with other modules Or the connection location of the device.
- the auxiliary module of the aircraft structural unit can be selectively added, that is, the auxiliary unit, the auxiliary module is not fixed in form and has a wide range of functions, and is used for filling the defects of the above module. In the whole aircraft structure, some auxiliary modules can even replace some of the above modules. effect.
- the auxiliary module acts as a connection pylon, which is responsible for the connection between the above system and the aircraft; when the aircraft needs to be loaded with large-sized and irregular shape loads, The auxiliary module acts as a connection between the load and the aircraft.
- an auxiliary module may be added at the structural unit to increase the connection strength of the overall structure of the aircraft; when the aircraft does not need to carry a heavy load or carry more energy
- the auxiliary module can also be used as a connecting device between the driving device modules, that is, the fuselage structure in the aircraft is composed of a bearing module and an auxiliary module.
- the number of modules constituting the aircraft structural unit is X, X ⁇ 0. According to the actual needs, each structural unit can be different, the number of modules is not equal, and the modules can be arbitrarily combined and combined. Due to the redistribution of energy and load in the structure, each structural unit can provide power and load alone, and can also cascade energy and power, so that the aircraft can be infinitely accumulated and benignly expanded according to the needs, thereby improving the battery life. And load capacity.
- the load bearing module can be equipped with, but is not limited to, an energy source, a load, and an auxiliary device that generate driving force by the drive module.
- the drive module, the connection module, the carrier module and the auxiliary module can be used as bearing or mounting areas for other loads.
- the energy required to generate the driving force on the aircraft drive module may be batteries, fuel, chemical power generation devices, and other energy sources. If the driver module is electrically driven, its battery shape and battery connection line can be set as needed. It can be curved, round, square, etc.; if the drive module is fuel-driven, the load bearing module can carry chemical energy such as fuel.
- the battery (set) or fuel may be disposed on the outer surface of the carrier module as needed, or may be partially or completely disposed within the interior space of the carrier module.
- the battery (group) can also be directly connected to the drive module to form an aircraft fuselage frame, that is, the battery (group) can provide power for the aircraft and directly serve as a connector for the aircraft frame.
- the relationship between the connecting module on the aircraft and the driving device module and the carrying device module may be a one-piece structure, a movable structure, or a split-assembled structure;
- the outer shape of the carrying module is not limited, and may be Round tubular, square tubular, semi-circular tubular, I-shaped, cabin type, irregular shape, etc.; each module on the aircraft can be a fixed connection or an active connection.
- the modular aircraft redistributes energy and load, changes the structural force transmission route, optimizes the stress distribution between the structures, thus solving the complex mechanical structure and load concentration of the traditional aircraft, so that the structure of the aircraft can be as needed.
- Unlimited benign expansion the present invention adopts a modular combined structure to realize commonization and standardization of components in the aircraft.
- the invention can be widely applied in the fields of aerospace, industry, agriculture, environmental protection, fire protection, urban construction, science and technology, and other combinations requiring devices.
- FIG. 1 is a schematic view showing a layout method of a driving device of the present invention
- FIG. 2 and FIG. 3 are schematic diagrams showing the planar geometric representation of the arrangement layout of the driving device of the present invention.
- FIG. 4 is a schematic diagram showing a three-dimensional geometric layout of a layout arrangement of a driving device of the present invention
- FIG. 5 is a schematic view showing a layout of a driving device in an equilateral triangle arrangement according to an embodiment of the present invention
- FIG. 6 is a schematic view showing a layout of a driving device in a diamond shape according to an embodiment of the present invention.
- Figure 7 is a schematic diagram of one embodiment of a drive assembly assembly
- Figure 8 is a schematic view of another embodiment of a drive assembly assembly
- Figure 9 is a schematic view showing a preferred skeleton connection of an embodiment of the present invention.
- Figure 10 is a schematic view showing a preferred planar body mounting of the embodiment of the present invention, wherein Figure 10a is a plan view and Figure 10b is a side view;
- Figure 11 is a schematic view of a preferred planar hollowing installation of the embodiment of the present invention, wherein Figure 11a is a plan view and Figure 11b is a side view;
- 12a and 12b are schematic views showing a preferred driving force output mode of the present invention.
- Figure 13 is a schematic view showing the basic distribution of the driving device of the aircraft of the present invention.
- Figure 14 is a schematic diagram of a feasible layout of an aircraft drive device
- Figure 15 is a schematic diagram of another possible layout of the aircraft drive device.
- Figure 16 is a schematic view of a preferred skeleton structure of the aircraft.
- Figure 17 is a schematic view of a preferred collapsible skeleton structure of an aircraft
- Figure 18 is a schematic view of a preferred planar hollowing out installation of the aircraft, wherein Figure 18a is a plan view and Figure 18b is a side view;
- Figure 19 is a schematic view showing an embodiment of an aircraft constructed in accordance with a load form, wherein Figure 19a is a plan view and Figure 19b is a side view;
- Figure 20 is a schematic view of another embodiment of the aircraft constructed in accordance with the load form, wherein Figure 20a is a plan view and Figure 20b is a side view;
- Figure 21 is a schematic view showing a preferred embodiment of the aircraft of the present invention.
- Figure 22 is a schematic view showing an embodiment of an aircraft of the present invention.
- Figure 23 is a schematic view showing another embodiment of the aircraft of the present invention.
- Figures 24a, 24b, 24c, 24d, 24e and 24f are respectively side views of a preferred mode of operation of the aircraft of the present invention.
- FIG. 25a is a schematic illustration of various modules in the present invention.
- 25b, 25c, 25d, 25e, 25f are schematic views of a modular structural unit of the present invention.
- 26a, 26b, 26c, 26d and 26e are top views of modular different embodiments of the present invention.
- 27a and 27b are top plan views of a particular embodiment of the modularization of the present invention.
- 28a and 28b are top and partial side views of one embodiment of the modularization of the present invention.
- Figure 29 is a schematic illustration of an expanded embodiment of the modularization of the present invention.
- Figure 30 is a schematic view showing an expanded embodiment of the modularization of the present invention.
- Figure 31 is a schematic view showing an expanded embodiment of the modularization of the present invention
- the basic principle of the combined driving device of the present invention is that the driving devices are arranged in a triangle to form a triangular driving device module; preferably, the combined method is that the spatial distance between adjacent driving devices is equal; mapping to a spatial direction based on a triangularly arranged driving device module
- the array is assembled into a combination of driving devices composed of a plurality of driving devices; the number of driving devices in the driving device assembly is N, N ⁇ 3.
- the distance between adjacent driving devices in the driving device assembly is ⁇ 0; in the driving device assembly, the number of driving devices can be increased or decreased as needed; the coincidence of each triangular module combination in the driving device assembly arrangement method can be regarded as Shared location.
- the mapping arrangement combination method of the driving device can be expressed by the following geometric method.
- the triangle ABC is an equilateral triangle
- the axis symmetry equilateral ⁇ BCD of ⁇ ABC is formed by the BC side of the equilateral ⁇ ABC.
- AB, BD, CD, AC are extended in opposite directions on both sides, and the edges equal to the length of the side of the diamond are cut, and the corresponding points are connected to form an infinite number of diamonds, forming a diamond-shaped mesh block, and then connecting the short diagonal lines of all the diamonds to form a myriad
- the geometric structure of an equilateral triangle is an equilateral triangle
- the axis symmetry equilateral ⁇ BCD of ⁇ ABC is formed by the BC side of the equilateral ⁇ ABC.
- AB, BD, CD, AC are extended in opposite directions on both sides, and the edges equal to the length of the side of the diamond are cut, and the corresponding points are connected to form an infinite number of
- another mapping arrangement method of the driving device can also be expressed by the following geometric method.
- the triangle ABC is an equilateral triangle
- the central symmetry ⁇ ADE, ⁇ CFG of ⁇ ABC is made with the three points A, B, and C as the center symmetry points respectively.
- ⁇ BHI respectively
- D, E, F, G, H, I points as the center of the symmetry point to make the equilateral ⁇ ... and so on can get the geometry of an infinite number of equilateral triangles.
- a plurality of driving devices are based on a triangular module, and a combination of N driving devices is constructed through different three-dimensional geometric layouts, N ⁇ 3.
- Construction method: the triangle ABC is an equilateral triangle, and the symmetry point or the symmetry axis can be made by any one of the vertices or the side length of the triangle, and so on, and can be obtained by an infinite number of equilateral triangles.
- Solid geometry
- Each node in the above geometric scheme is the preferred location of the drive.
- the number of driving devices in the driving device assembly and the position of the mounting node can be arbitrarily set without departing from the principle.
- the driving device in each triangular module can also be increased or decreased according to the structural requirements.
- the driving devices are connected by a connecting compartment or a connecting device, and the connecting compartment or the connecting device can be used, but not limited to, a skeleton, a planar body or a planar hollow.
- the connection compartment or connecting device can be made separately or in a planar, skeleton-like structure. If the drive devices are connected in a skeleton manner, they may be fixed connections or active connections. If the driving device is connected by a planar body or a planar body, the driving device can directly mount the surface thereof, or can be mounted in the hollow. In space.
- the driving device may be respectively connected to the driving force conversion device to convert the driving force into an external output force, or may be combined with the driving force generated by the driving device in the driving device system, and then connected to the driving force conversion device.
- the driving force is converted to an external output force.
- the driving device in the present invention is preferably an engine which can be connected to a propeller, a transmission, a tractor, a boring device and the like.
- the engine is fixed by a planar or skeletal structure, and the device constructed by this solution can be installed with different types or models of engines depending on the application.
- the engine can be controlled individually or in combination or in combination.
- the device constructed by this solution can work alone, in partial combination or in all combinations as needed.
- Each of the engines constructed by the solution of the present invention can convert the power generated by the engine and combine the output forces.
- the engine is connected to the propeller, and the power is converted into wind or water and combined into powerful wind or water.
- the forces of a plurality of engines can be combined or partially combined and output by the total shaft.
- the engine can transmit the force to the main shaft by the transmission device through the transmission shaft transmission belt, gas, hydraulic transmission, etc., and the combined output shaft output force or the connection force conversion device outputs the force.
- the preferred solution of the present invention can also be used to mount a generator, a light source, a shower head or other devices that need to be combined, and an area other than the area occupied by the drive device in the system can be installed as another device. Or bearer area.
- a distinguishing feature of the aircraft of the present invention is that the drive means are arranged in a triangle such that more drive means can be accommodated in a unit volume, and the aircraft maintains an optimal spatial layout under the same propulsion.
- the basic principle is that the aircraft driving devices are arranged in a triangle to form a triangular driving device module; the preferred combination method is that the spatial distance between adjacent driving devices is equal; and the spatially oriented mapping is combined and arranged into a plurality of units based on the triangularly arranged driving device modules.
- a combination of drive devices consisting of drive devices; the number of drive devices in the drive assembly is N, N ⁇ 3.
- the preferred method for mapping the drive device mapping arrangement can be expressed by the following geometric method.
- the triangle ABC is an equilateral triangle, and the axis symmetry equilateral ⁇ BCD of ⁇ ABC is formed by the BC side of the equilateral ⁇ ABC as the axis, and the diamond ABCD is formed along the AB and BD respectively.
- CD, AC are extended in opposite directions on both sides, and the sides equal to the length of the diamond are cut, and the corresponding points are connected to form an infinite number of diamonds, and then the short diagonal lines of all the diamonds are connected to form a diamond formed by an infinite number of equilateral triangles.
- the geometric structure, the node of the geometric structure is regarded as the preferred installation position of the driving device, and the node coincidence is regarded as the common position.
- the driving device can be installed in each spatial direction of the node.
- the shape of the driving device assembly and the number of driving devices can be changed according to the flight environment, load weight, shape, and the like.
- the aircraft can be self-cancelled if the jet has a small rotational torque or no anti-torsion or anti-torque force.
- Devices such as jet drives or coaxial anti-propellers, multi-blade drives, may use odd-numbered or even-numbered drive combinations; if a drive with a relatively high rotational torque is used, for example, the way the engine is connected to the propeller, the preferred even number is required.
- the engine is connected to the propeller to counteract the counter-torque.
- an aircraft driven by a plurality of driving devices mostly adopts an engine connection propeller mode. Therefore, a preferred embodiment of the present invention is a diamond mapping, that is, a diamond-shaped module is formed based on an equilateral triangle module, and an engine is installed at a node of the diamond. The engine can be placed up and down.
- the spatial distance of the diagonal within the diamond-shaped module can be adjusted according to the needs of the aircraft, and geometry
- the angle of the apex angle of the diamond in the connector formed by the structure can be adjusted.
- the driving devices of the aircraft are connected by a connecting member, and the connecting member may be, but not limited to, a skeleton or other connecting members.
- the aircraft may preferably be connected by a skeleton, and the skeletons may be fixed or movable.
- the use of a fixed skeleton refers to a form in which an integral skeleton can be manufactured or a skeleton assembly is fixed by a fixed joint; the movable skeletons are connected by a movable connecting member to form a foldable or decomposable skeleton, and the skeleton is restricted by the fixing member in use.
- the skeleton movement constitutes a stable shape, and the skeleton can be folded or disassembled by releasing the fixing member that restricts the movement of the skeleton when the volume is reduced, thereby effectively reducing the volume of the aircraft, especially the large aircraft, and facilitating storage and transportation.
- the second major feature of the present invention is that the aircraft can determine the size and shape of the aircraft based on the flight environment, the shape and weight of the load. Except for the installation position occupied by the drive unit on the aircraft, the remaining areas can be used as installation or mounting areas for flight aids or loads. Due to the special structure of the aircraft of the present invention, a load mounting area or an area connected to the overall load can be provided in each driving device or each group of driving devices in the aircraft driving system, so that the purpose of the setting is to make the aircraft drive system The resulting driving force is evenly applied to the load portion, and the connection between the drive and the load in the aircraft does not occur because of the concentration of stress in a certain area, resulting in a series of malignant chain reactions affecting the overall flight system.
- the aircraft with multiple flight modes of the present invention is equipped with a wing on the basis of the aircraft drive device and the number of wings is M, M ⁇ 1.
- the wing is connected to the aircraft skeleton through the connecting member, and the connecting member can be a fixed connection or a movable connection, and the wing can be quickly folded and disassembled and installed.
- the wing can be rotated axially.
- the aircraft can rely on the wing to fly or use the wing to decelerate.
- the wing can be used as a buffer to effectively protect the aircraft or adjust the wing rotation. The angle causes it to create resistance in the forward direction to decelerate the aircraft.
- the left and right correspondingly arranged wings generate a rolling force by changing the angular difference to cause the aircraft to roll laterally, similar to the function of the aileron rudder of the fixed-wing aircraft; the front or rear corresponding wing or single wing is generated by adjusting the angle of attack Rise or down
- the pressure causes the aircraft to pitch vertically, similar to the function of a fixed-wing aircraft's elevator.
- the wing can generate additional lift to reduce the burden on the driving device.
- the steering surface effect generated by the operating wing can reduce the load on the driving device when the aircraft changes its posture. It saves energy to a certain extent, prolongs battery life and increases load capacity.
- the wing when the wing rotates along the axial direction to a certain angle with the plane of the fuselage, the wing can also serve as a landing support device for the aircraft, that is, the landing gear, thereby effectively reducing the structural load and take-off weight of the aircraft.
- This embodiment also provides a preferred embodiment of the connection of the drive unit combination system.
- the driving device combination provided by the embodiment provides a combined driving force by driving the device (05) in a triangular arrangement to form a triangular driving device module (01), and preferably the combining method is an adjacent driving device.
- the spatial distance between (05) is equal. As shown in Fig.
- the thick solid line area is an equilateral triangle, and the three vertices, that is, the node (02) can be regarded as the installation position of the driving device (05);
- the driving device triangular module (01) arranged on the triangle is arranged in a spatial direction to form a combination of the driving device (05) composed of a plurality of driving devices (05); the driving device (05) is a driving device in the combination (05)
- the number is X, X ⁇ 3. Among them, (03) is the mapping body of the triangle in the geometric structure, and (11) is the geometric structure reference line.
- the planar preferred method of combining multiple driving devices can be specifically expressed by the following geometric method: as shown in FIG. 2, the triangle ABC is an equilateral triangle, and the axis symmetry equilateral ⁇ BCD of ⁇ ABC is formed by the BC side of the equilateral ⁇ ABC. , respectively, extending along the sides of AB, BD, CD, and AC, and cutting the sides equal to the sides of the diamond, connecting the corresponding points, forming a plurality of diamonds, forming a diamond-shaped mesh block, and then connecting the short diagonal lines of all the diamonds. , forming a geometric structure composed of an infinite number of equilateral triangles (03).
- FIG. 3 Another planar preferred method of combining multiple driving devices can be specifically expressed by the following geometric method: as shown in FIG. 3, the triangle ABC is an equilateral triangle, and the central symmetry of ⁇ ABC is made by symmetrical points of three points A, B, and C respectively. ADE, ⁇ CFG, ⁇ BHI, respectively, D, E, F, G, H, I points as the center of the symmetry point to make an equilateral triangle, and so on can get the geometric structure of an infinite number of equilateral triangles (03).
- the stereoscopic preferred method of combining multiple driving devices can be expressed by the following geometric method.
- the triangle ABC is an equilateral triangle, and the symmetry point or the symmetry axis can be made symmetrically with any one of the vertices or the side length of the triangle.
- the triangle (03), and so on, can obtain a solid geometry composed of an infinite number of mapped equilateral triangles (03).
- Each node (02) in all of the above geometries is considered to be the mounting position of the drive unit (05). Based on demand, The drive unit (05) can be selectively installed at the node (02).
- the most basic triangular layout of the drive assembly of the present invention preferably, employs an equilateral triangle layout, i.e., the spatial distance between adjacent drive units (05) is equal.
- the diamond-shaped layout structure of the driving device assembly of the present invention is a combination of two equilateral triangles, and the coincidence position is a common position of the driving device (05).
- Figure 7 is a schematic view of a drive assembly of the present invention, which is an evolution of Figure 3.
- Figure 8 is a schematic illustration of another drive assembly of the present invention, evolved from Figure 2.
- the invention has the advantage that the driving device (05) can be selectively installed at the node (02) according to actual needs, thereby achieving the desired effect.
- the drive unit (05) is preferably an engine according to the prior art, and the engine can be connected to a propeller, a transmission, a tractor, a boring device or the like.
- the present embodiment also provides a preferred connection mode in which the driving device combination produces a combined driving force system: as shown in FIG. 9, the driving devices (05) are connected in a skeleton manner (04), which may be a fixed connection or an activity. Connection; as shown in Fig. 10a, the driving devices (05) are connected by a planar body, and the driving device (05) can be mounted on the surface of the planar body (06), see Fig. 10b; as shown in Fig. 11a, the driving device ( 05) is connected by a planar hollowing, that is, the driving device (05) is installed in the hollowed out area (07) in the planar body, see Fig. 11b.
- the driving device (05) in the driving device assembly may be combined with the same specifications and the same functions, or may be combined with different specifications and different functions.
- the driving device (05) in the driving device system can be respectively connected to the driving force conversion device (08) to output the driving force outward through the driving force output shaft (12), as shown in FIG. 12a, or the driving device in the driving device system ( 05) After the generated driving force is combined, the connected driving force conversion device (08) outputs the driving force to the outside through the combined force output shaft (10), see Fig. 12b, where (09) is the transmission.
- the preferred embodiment of the present invention can also be used to mount a generator, a light source, a shower head or a device that needs to work in combination, and the system occupies an area occupied by the mounting drive device.
- the area other than the area can also be used as the installation area of the device or system.
- Figure 13 shows the basic distribution of the drive of the aircraft of the present invention, in which the triangle ABC is an equilateral triangle, the three vertices of the triangle are the position of the aircraft drive (05), forming a triangular drive module (01); preferably The spatial distance between adjacent driving devices (05) is equal; the driving device module (01) arranged in a triangle arrangement is arranged in a spatial direction to be combined into a driving device (05) composed of a plurality of driving devices (05).
- Body, the diamond ABCD in this figure is derived from the triangular ABC drive module to form a diamond module, and so on, can form a combination of various forms of drive device (05); drive device (05) in the combination drive device ( The number of 05) is N, N ⁇ 3. Among them, (03) is the mapping body of the triangle in the geometric structure, and (11) is the geometric structure reference line.
- each node (02) in all the geometric structures The drive unit (05) can be installed in the space direction, and the installation effect is best in the up and down direction of the node (02). Further, the size, shape, and number of driving devices (05) of the combination of the driving device (05) can be changed as needed.
- the driving device is exemplified by an engine.
- Several feasible layouts and preferred connection schemes of the driving device evolved from the geometrical structure will be specifically described below.
- the center symmetry triangle (03) is respectively formed, and the engine (16) is installed at the node (02) to become the engine (16) combination shown in Fig. 14.
- the engine (16) is fixed in the main frame through the engine bracket (15), and the upper end of the engine (16) is connected to the propeller (14) to be combined into an aircraft having nine engines (16), and the node (02) is up and down as needed.
- the engine (16) can be optionally installed and can be combined into up to eighteen rotorcraft.
- the engine (16) is selectively installed at the node (02), and the engine (16) assembly shown in Fig. 15 can be obtained.
- the engine (16) can be combined with the propeller (14) to be combined.
- the engine (16) can be installed in each spatial direction at the node (02) as required.
- the engine (16) may be connected by a skeleton, a planar body, or other means. If the engine is connected in a skeleton (04) manner, the skeletons are connected by a skeleton connecting member (13), as shown in Fig. 16, which is a schematic diagram of a preferred skeleton connection of an aircraft having eight engines (16), and the skeleton connecting member (13) can be It is fixed or mobile.
- the fixed skeleton connection can be used to directly manufacture the integrated skeleton (04) or to fix the skeleton assembly by the fixed joint (08); as shown in Fig. 17, the movable joint (04) is connected by the movable joint (08) Connected to form a collapsible or decomposable skeleton (04).
- the skeleton When in use, the skeleton (04) restricts the movement of the skeleton by the fixing member to form a stable shape, and the fixing member for releasing the skeleton movement is required when the volume is reduced during storage and transportation. Realize the folding or disintegration of the skeleton (04).
- the engines are connected in a planar hollowing manner, i.e., the engine (16) is mounted in the hollowed out region (07) in the planar body (06), see Fig. 18b.
- the aircraft of the present invention can determine the size and shape of the aircraft according to the form of the load. Except for the installation position occupied by the drive unit on the aircraft, the remaining areas can be used as installation or mounting areas for flight aids or loads.
- the engine (16) assembly is a diamond-shaped power unit, and each unit can be regarded as a module in the aircraft power system, and each module can generate a certain thrust according to the number of engines (16). Each module can share a part of the load in the aircraft (17).
- the four vertices of the diamond have four engines (16), and each engine (16) generates a certain thrust, that is, the module can generate 4 units of thrust, the diamond module has four engines (16) and the weight of the supporting skeleton (04), battery, etc.
- the 4 units of thrust generated by the module can share the total weight of the module at the same time, while the remaining The thrust can be used to share a portion of the load (17) weight of the aircraft as a whole.
- the power system of the aircraft consists of N power modules.
- the engine (16) in the adjacent power module is regarded as the module shared engine (16), which shares the weight of the load (17) to be shared in the adjacent modules, that is, the takeoff weight of the aircraft is approximated. Evenly distributed to the power system.
- each load device or each power module can be provided with a load (17) mounting area or an area connected to the overall load (17) as shown in Fig. 20, so that the purpose of the setting is to make the aircraft
- the driving force generated by the engine (16) in the power system is uniformly applied to the load (17) portion, and the connection between the engine (16) and the load (17) in the aircraft does not occur because stress is concentrated in a certain area.
- the engines (16-1), (16-2), (16-3), (16-4) are arranged in a diamond geometry and connected by a skeleton (04).
- the engine (16) is fixedly mounted on the skeleton (04), and the skeleton (04) is connected by a skeleton connecting member (13).
- the skeleton connecting member (13) may be fixed or movable, and the engine (16) Connecting the propeller (14), the wing (18) is connected to the aircraft skeleton (04) through the wing connecting member (19), and is respectively mounted on the engine (16-2) and the engine (16-4) on both sides, the wing (18) ) can be rotated axially.
- Figure 22 is also a possible implementation of the solution.
- the geometrical method of Fig. 2 or Fig. 3 can be evolved into the aircraft layout structure in the figure, and the engines (16-5), (16-6), (16-7), (16-8) are arranged in a rectangular shape through the skeleton. (04) Cross-connection installation, either fixed connection or movable connection, the engine (16) is connected to the propeller (14), and the wing (18) is symmetrically mounted on both sides of the skeleton (04), the wing (18) Located between the engine (16-5) and (16-7) and between the engines (16-6) and (16-8), the wing connection between the wing (18) and the skeleton (04) (19) Connection, the wing (18) can be rotated axially.
- Figure 23 represents another possible implementation of the solution.
- the geometry method of Figure 2 or Figure 3 can be evolved into the aircraft layout structure in this figure, which is composed of three complete triangular drive unit modules (01), namely the engine (16-9), (16-10) and (16-11) constitute a triangular drive module (01), the engine (16-12), (16-13) and (16-14) form a triangular drive module (01), engine (16-15), (16-16) and (16-17) form a triangular drive module (01).
- the engine (16) is connected by a skeleton (04). It can be a fixed connection or a movable connection.
- the engine (16) ) connecting the propeller (14), the coaxial wing (18) is symmetrically mounted on both sides of the engine (16-9) in the triangular drive module (01), and the other wing (18) is mounted on the triangular drive module (01)
- the area between the engine (16-14) and (16-17), the wing (18) and the skeleton (04) are connected by a wing connecting piece (19), and the wing (18) can be axially Turn.
- the engine (16) can be mounted up and down in the frame (04) due to the characteristics of the aircraft. If there is a special need, the engine (16) or other devices are not excluded from being installed in other directions.
- Figure 24 of the accompanying drawings illustrates several preferred modes of operation for a class of aircraft of the present invention.
- (20) represents the horizontal reference line, and the direction of the arrow is the flight direction of the aircraft.
- Figure 24a shows the auxiliary lift and ascending flight modes.
- the upward tilting angle of the wing (18) will generate lift to assist the engine (16) to provide lift to the aircraft;
- Figure 24b is the auxiliary descending flight mode, and the wing (18) will tilt downward at the same time.
- the angle will generate downward pressure to cause the aircraft to descend, while the coaxial machine in the aircraft
- the wing (18) can be operated separately as if the elevator in the fixed-wing aircraft changes the pitch angle of the aircraft;
- Figure 24c shows the low-speed drag-reducing flight mode, the wing (18) and the engine (16) plane remain approximately parallel or in flight direction, The direction of the airflow maintains the optimal wind resistance angle to reduce the resistance to maintain the best flight state;
- Figure 24d shows the cruise flight mode. In order to achieve the best performance of the aircraft at different speeds, the wing (18) can be adjusted.
- Figure 24e shows the roll flight mode, through the coaxial wing (18) left and right differential deflection The resulting rolling moment allows the aircraft to make a roll maneuver (different to the flight direction or direction of the aircraft);
- Figure 24f shows the landing or landing mode, ie when the aircraft needs to land, the wing (18) and the fuselage plane
- a certain angle can be used as the landing support device of the aircraft, that is, the landing gear.
- the wing (18) is approximately perpendicular to the plane of the fuselage. If it is necessary to increase the size of the landing gear, it is also possible to add support or shock absorbing components to the contact area of the wing (18) and the landing surface.
- 25a is a schematic diagram of each module in the present invention, (21) is a drive module, (22) is a connection module, (23) is a carrier module, and (24) is an auxiliary module.
- the battery is used as the energy source
- the driving device is connected to the propeller as an example.
- one end of the driving device module (21) and the carrying module (23) are connected by a connecting module (22) to form a structural unit
- the connecting module (22) is simultaneously connected with another carrying module (23) to form a structural unit. And so on, can be expanded infinitely.
- Fig. 25b one end of the driving device module (21) and the carrying module (23) are connected by a connecting module (22) to form a structural unit, and the connecting module (22) is simultaneously connected with another carrying module (23) to form a structural unit. And so on, can be expanded infinitely.
- the two ends of the connecting module (22) in the X-axis direction are respectively connected to the carrying module (23), and the two ends of the Y-axis direction are respectively connected to the driving device module (21) to form a structural unit, and the driving device module (21) is further coupled with the propeller (27) Connected to form the engine power group, and so on, can be expanded infinitely.
- the two ends of the carrying module (23) are respectively connected to the driving device module (21) via the connecting module (22) to form a structural unit, the driving device module (21) is connected with the propeller (27), and so on, which can be expanded indefinitely. .
- each driving device module (21) is respectively connected with a propeller (27).
- the function of the auxiliary module (24) in this embodiment is that if the carrying load of the carrying module (23) is large, The connection strength between the carrier module (23) and the drive module (21) in the structural unit is increased.
- one end of the driving device module (21) and the carrying module (23) are connected by a connecting module (22) to form a structural unit, and other loads (26) can be connected through the auxiliary module (24) under the carrying module (23).
- FIG. 26e Figures 26a, 26b, 26c, 26d and 26e are top views of modular different embodiments of the present invention.
- the figure is a modular combination of a structural unit composed of a driving device module (21) and one end of a carrying module (23) connected through a connecting module (22).
- (25) is the propeller rotating surface.
- the driving device module (21) forms a structural unit with the carrying module (23) through the connecting module (22), and the driving device module (21) is formed by the connecting module (22) and the auxiliary module (24).
- the structural unit, all structural units are sequentially fixed in a “ring” to the central connecting module (28) to form a modular aircraft.
- This figure shows that when the required load of the aircraft is small, all the carrying modules (23) do not need to carry batteries or loads.
- the partial load module (23) can be replaced by an auxiliary module (24) to reduce the weight of the aircraft.
- connection module (22) and the carrier module (23) constitute a structural unit, and the plurality of structural units are combined and fixed centering on the connection module (22), and the driving module (21) is respectively mounted on the upper and lower sides of the connection module (22).
- the drive module (21) is fitted with a propeller (27).
- the driving device module (21), the connecting module (22) and the carrying module (23) constitute a structural unit, and the N structural units are "end-to-tail", which are combined into a modular aircraft of a "ring” structure.
- each of the driving device modules (21) is respectively mounted with a propeller (27), and (25) is a propeller rotating surface.
- the driving device module (21), the connecting module (22) and the carrying module (23) constitute a structural unit, and the four structural units are combined into a modular aircraft according to a diamond-shaped frame, and an auxiliary module (24) is installed under the aircraft.
- each of the driving device modules (21) is respectively mounted with a propeller (27), and (25) is a propeller rotating surface.
- Figure 28b is a partial side view with other loads (26) mounted below the auxiliary module (24).
- 29, 30 and 31 are each a schematic view of an expanded embodiment of the modularization of the aircraft of the present invention.
- 29 is an infinite expansion diagram of FIG. 28a
- FIG. 30 is an infinite expansion diagram of FIG. 26e
- FIG. 31 is an infinite expansion diagram of FIG. 26c.
- the invention of course has many other embodiments.
- a fuel-driven engine or an engine driven by other energy sources may also be selected in the drive module, and the like according to the present invention.
- Equivalent variations and modifications of the invention are still within the scope of the invention and should be considered as further embodiments of the invention.
- some of the driving devices do not have to be strictly combined with the equilateral triangle modules, and may also be an isosceles triangle arrangement.
- some driving devices do not have to be strictly in accordance with the combination of the diamond modules, or the parallelogram arrangement and the like.
- the wings in the aircraft structure of the present invention are also selected for installation where technical conditions permit. It can be seen that the related equivalent replacement technical solutions should fall within the protection scope of the present invention.
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Abstract
一种具有多个驱动装置(05)的驱动装置组合体及飞行器,驱动装置(05)以三角形排列,组成三角形驱动装置模块(01);组合方法为相邻驱动装置(05)之间的空间距离相等;以三角形排列的驱动装置模块(01)为基础向空间方向映射排列组合成由多台驱动装置(05)组成的驱动装置组合体,该飞行器还包括机翼(18),机翼(18)与驱动装置组合体连接。该飞行器改进了具有多台驱动装置驱动的飞行器的传统结构布局方式,得以无限增加驱动***进而提升飞行器的飞行性能及载荷能力,其采用模块化组合结构,使得飞行器中零部件实现通用化、标准化。
Description
本发明属于动力***领域,可应用于航空器、航船、挖掘或掘进机械、发电机组、组合光源、风力装置、喷淋喷雾网等领域的组合驱动装置。更具体而言,本发明涉及一种可无限增加驱动装置和载荷量的飞行器以及具有多种飞行模式的模块化组合结构的飞行器。
多个驱动装置以组合方式工作可以产生更强大的驱动力。目前,以发动机组(例如飞行器发动机组)为例:在组合发动机等装置中,大多采用串列式、直线式、方形、环形等排列方式。这种方式受限于组合体中发动机之间连接方式繁琐,发动机之间会产生不必要的空间、空隙,导致组合装置的体积、重量增加。***力学结构复杂,组合体中不同位置发动机之间互相连接固定的部件***力学结构分力不均匀而导致组合体(***)中应力集中,无限累加发动机最终会导致连接结构崩溃,因而不能无限增加组合体中发动机数量,载荷重物能力有限。
机身,即飞行器的承载平台。目前应用广泛的是具有多台驱动装置的飞行器,其机身的组成大同小异,主要由“中心承载板或机舱”、机臂及起落架组成,“中心承载板或机舱”与机臂形成由一个中心点向外周发散的辐射状结构,这种结构在飞行器尺寸相对较小时有着结构简单、重量轻等优势。随着未来对飞行器载荷能力的不断需求,这种结构带来的问题是驱动装置越多,螺旋桨旋转面或驱动装置所占据的空间越大,随之机身的尺寸必然要增加,如此发展下去,航材、结构应力集中问题会愈发严重,需要额外“增重补强”来弥补上述问题,此外,机身结构“死重”的增加也会削减驱动装置有限的驱动力、增加能源消耗。假定忽视这些,无限拓展飞行器尺寸,必然会引发因驱动力被结构重量过度损耗、部分结构应力屈服所带来的连锁反应,最终结构崩溃。
此外,当前直升机类飞行器的普遍缺点是自身结构近乎无升力,能耗较高、航程较短,恶劣环境下剩余功率不足,难以抗拒强气流变化。特定气候条件下,稳定性能欠佳,因而不能长时、稳定地完成各种飞行任务。
发明内容
在第一方面,本发明提供了一种组合驱动装置,使得在单位体积内能够容纳更多的驱动装置,该组合驱动装置优化了组合体力学结构,实现了飞行器自身重量与载荷均匀分配,可以无限良性扩展,加以配合精简轻便的安装方式因而组合装置可以产生强大驱动力的同时又
具备体积小、重量轻、连接强度高、载荷能力强大等特点。
因此,本发明提供了一种具有多个驱动装置的驱动装置组合体,所述多个驱动装置的分布如下:
a.其中三个驱动装置形成三角形单元,所述三个驱动装置位于所述三角形单元的顶点,其他驱动装置分布在所述三角形单元外并且在以下三组平行线的交点上:每组平行线是与所述三角形单元的一条边平行的等距直线,包括所述边所在直线,其中所述每组平行线的间距是所述三角形单元的相应边上的高长度;所述驱动装置的数量大于等于3、4、5、6、7、8、9、10、15、24或30;或者
b.其中四个驱动装置形成具有四个三角形面的四面体单元,所述四面体单元的顶点为所述四个驱动装置的中心,以四面体单元为初始单元体,其他驱动装置分布在所述初始单元体外并且依次以以下方式纳入其中:每个所述其他驱动装置与所述单元体上的一个三角形面形成四面体单元;所述驱动装置的数量大于等于4、5、6、7、8、9、10、15、24或30。
在一个优选的实施方案中,所述三角形单元为等边三角形,或者所述四面体单元为正四面体。
在一个优选的实施方案中,所述驱动装置由连接舱或连接装置连接,所述连接舱或连接装置选自但不限于空腔舱体、龙骨框架、骨架、面状体、面状体镂空。
在一个优选的实施方案中,所述连接舱或连接装置为固定连接或活动连接。
在一个优选的实施方案中,驱动装置为电力驱动装置、内燃机驱动装置、液力与液压驱动装置、气力驱动装置、人力驱动装置或复合驱动装置。
在第二方面,本发明提供了一种可无限增加驱动装置数量和载荷量的飞行器,以解决飞行器中发动机数量以及载荷上限的问题。
因此,本发明还提供了一种具有多个驱动装置的***或飞行器,所述***包括本发明第一方面所述的驱动装置组合体。
在一个具体实施方案中,所述飞行器包括机翼,所述机翼安装在驱动装置组合体上,形成具有多种飞行模式的飞行器。
这种具有多种飞行模式的飞行器将直升机类飞行器与固定翼类飞行器的特点有机整合,使得本飞行器既可以高速节能方式长距离飞行又可以低速精准的方式精确飞行,展现了其在复杂飞行任务中具有多种飞行模式组合的优势。
在一个优选的实施方案中,飞行器上除去驱动装置和机翼占据的安装位置外,其余位置为飞行辅助装置或载荷物的安装或挂载位置。
在一个优选的实施方案中,机翼沿着轴向旋转,作为飞行器的起落支撑装置。
本发明的组合驱动装置,使得在单位体积内能够容纳更多的驱动装置,该组合驱动装置优化了组合体力学结构,采取去力学中心的构架,驱动装置的重量均摊到其连接结构上,使组合体的重量由组合体中驱动装置均匀承载,每增加一台驱动装置对总***不会造成压力,而是驱动装置产生的驱动力承载其自身质量后将剩余功率累加到驱动装置组合体中,增加其总功率及载荷量,因此驱动装置组合体可以无限良性扩展驱动装置数量,加以配合精简轻便的安装方式因而组合装置可以产生强大驱动力的同时又具备体积小、重量轻、连接强度高、载荷能力强大等特点。
在第三方面,本发明还提供了本发明第一方面所述的驱动装置组合体或本发明第二方面所述的飞行器,所述驱动装置组合体以模块组的形式组合而成,所述模块组包括驱动装置单元、连接舱单元和辅助单元。
在一个实施方案中,所述飞行器包括驱动装置模块、连接模块、承载模块和辅助模块,驱动装置模块构成驱动装置单元,连接模块与承载模块可视为连接舱单元,驱动装置模块与承载模块通过连接模块组合成飞行器结构单元;承载模块在承载能源和载荷同时,也作为飞行器的机身结构;承载模块上设有承载空间和与其他模块或装置的连接位置;连接模块上设有与其他模块或装置的连接位置。
飞行器结构单元中可选择性附加辅助模块,即辅助单元,辅助模块形式不固定,作用广泛,用于填补上述模块的不足,在整个飞行器结构中部分辅助模块甚至能够起到代替上述某些模块的作用。例如:飞行器需要搭载影像器材、武器***、无线电***等功能性载荷时,辅助模块即充当连接挂架,负责上述***与飞行器之间的连接件;飞行器需要搭载大尺寸、不规则形状载荷时,辅助模块即充当载荷与飞行器之间的连接件。当承载模块处承载的电池和(或)其它载荷重量较大时,可在结构单元处加装辅助模块以增加飞行器整体结构的连接强度;当飞行器不需要承载较重载荷或搭载更多能源时,也可以用辅助模块充当驱动装置模块之间的连接装置,即飞行器中机身结构由承载模块和辅助模块共同搭配组成。
组成飞行器结构单元的各个模块数量为X,X≥0。根据实际需要,每个结构单元可有差别,模块数量不等,模块之间可任意搭配组合。由于结构中重新分配了能源与载荷,每一个结构单元均可单独提供动力和承担载荷,也可以级联能源和动力,使得本飞行器在结构上可根据需要无限累加和良性拓展,进而提升了续航和载荷能力。承载模块中可以搭载但不限于驱动装置模块产生驱动力的能源、其它载荷及辅助装置。所述驱动装置模块、连接模块、承载模块及辅助模块均可作为其它载荷的承载或挂载区域。
飞行器上驱动装置模块产生驱动力所需的能源可以是电池、燃料、化学发电装置及其它能源。驱动装置模块如果为电驱动,其电池形状以及电池组连接线路可以根据需要进行设置,
可以是弧面形、圆形、方形等等;驱动装置模块如果为燃料驱动,承载模块处可承载燃油等化学能源。可以根据需要,电池(组)或燃料可安置于承载模块外表面,也可部分或完全安置于承载模块内部空间内。电池(组)亦可以直接与驱动装置模块连接组成飞行器机身构架,即电池(组)既为飞行器提供动力能源,又可直接作为飞行器构架的连接件。
飞行器上的连接模块与驱动装置模块和承载装置模块之间的关系可以是一体式结构、活动式结构,也可以是分体组装式结构;承载模块的外部形状并没有限定,根据需要,可以是圆管状、方管状、半圆管状、工字型、舱型、不规则形状等等;飞行器上的各个模块之间可以是固定连接,也可以是活动连接。
综上所述,该模块化飞行器重新分配了能源及载荷,改变了结构传力路线、优化了结构间应力分布,从而解决了传统飞行器力学结构复杂、载荷集中问题,使得本飞行器结构可根据需要无限良性拓展。此外,本发明采用模块化组合结构,使得飞行器中零部件实现通用化、标准化。
本发明可广泛应用于航空航天、工业、农业、环保、消防、城建、科技以及其他需要装置组合工作的领域。
参考随附的附图,本发明更多的目的、功能和优点将通过本发明实施方式的如下描述得以阐明,其中:
以下结合附图对本发明的几个优选实施方式进行简单介绍:
图1是本发明的驱动装置排列布局方法示意图;
图2和图3是本发明的驱动装置排列布局平面几何表述示意图;
图4是本发明的驱动装置排列布局立体几何布局示意图;
图5是本发明的实施例中驱动装置以等边三角形排列组合布局示意图;
图6是本发明的实施例中驱动装置以菱形组合布局示意图;
图7是驱动装置组合体布局的一个实施例示意图;
图8是驱动装置组合体布局的另一个实施例示意图;
图9是本发明实施例的优选骨架连接示意图;
图10是本发明实施例的优选面状体安装示意图,其中,图10a为俯视图,图10b为侧视图;
图11是本发明实施例的优选面状体镂空安装示意图,其中,图11a为俯视图,图11b为侧视图;
图12a和图12b是本发明的优选驱动力输出方式示意图;
图13是本发明飞行器的驱动装置基本分布示意图;
图14是飞行器驱动装置的一种可行性布局示意图;
图15是飞行器驱动装置的另一种可行性布局示意图;
图16是飞行器的一种优选骨架结构示意图;
图17是飞行器的一种优选可折叠骨架结构示意图;
图18是飞行器的一种优选面状体镂空安装示意图,其中,图18a为俯视图,图18b为侧视图;
图19是飞行器依载荷形态构建的一个实施方式示意图,其中,图19a为俯视图,图19b为侧视图;
图20是飞行器依载荷形态构建的另一个实施方式示意图,其中,图20a为俯视图,图20b为侧视图;
图21是本发明飞行器的一个优选实施布局方式示意图;
图22是本发明飞行器的一个实施布局方式示意图;
图23是本发明飞行器的另一个实施布局方式示意图;
图24a、图24b、图24c、图24d、图24e和图24f分别是本发明飞行器优选工作模式侧视图。
在图1-24中:01三角形驱动装置模块 02-节点 03-映射体 04-骨架 05-驱动装置 06-面状体 07-镂空区域 08-驱动力转换装置 09-传动装置 10-组合力输出轴 11-几何结构参考线 12-驱动力输出轴 13-骨架连接件 14-螺旋桨 15-发动机支架 16-发动机 17-载荷 18-机翼 19-机翼连接件 20-水平参考线
图25a是本发明中各个模块的示意图;
图25b、25c、25d、25e、25f是本发明的模块化结构单元示意图;
图26a、26b、26c、26d和26e是本发明的模块化不同实施例的俯视图;
图27a和27b是本发明模块化特殊实施例的俯视图;
图28a和28b是本发明模块化的一个实施例俯视图和局部侧视图;
图29是本发明模块化的一个拓展实施例的示意图;
图30是本发明模块化的一个拓展实施例示意图;
图31是本发明模块化的一个拓展实施例示意图
在图25-31中:21-驱动装置模块 22-连接模块 23-承载模块 24-辅助模块 25-螺旋桨旋转面 26-其它载荷 27-螺旋桨 28-中心连接模块
通过参考示范性实施例,本发明的目的和功能以及用于实现这些目的和功能的方法将得
以阐明。然而,本发明并不受限于以下所公开的示范性实施例;可以通过不同形式来对其加以实现。说明书的实质仅仅是帮助相关领域技术人员综合理解本发明的具体细节。在下文中,将参考附图描述本发明的实施例。在附图中,相同的附图标记代表相同或类似的部件,或者相同或类似的步骤。
本发明的组合驱动装置的基本原则是驱动装置以三角形排列,组成三角形驱动装置模块;优选组合方法为相邻驱动装置之间的空间距离相等;以三角形排列的驱动装置模块为基础向空间方向映射排列组合成由多台驱动装置组成的驱动装置组合体;驱动装置组合体中驱动装置的数量为N台,N≥3。驱动装置组合体中相邻驱动装置之间距离≥0;驱动装置组合体中,驱动装置的数量可以根据需要有所增减;驱动装置组合体排列方法中各三角形模块组合的重合处可视为共用位置。
本发明中驱动装置映射排列组合方法可由以下几何方法表述,所示三角形ABC为等边三角形,以等边△ABC的BC边为轴作出△ABC的轴对称等边△BCD构成菱形ABCD,分别沿AB、BD、CD、AC向两边反向延长,截得与菱形边长相等的边,连接相应点,构成无数菱形,形成菱形网块,然后将所有菱形的短对角线连接起来,形成无数个等边三角形构成的几何结构。
本发明中驱动装置另一个映射排列组合方法还可由以下几何方法表述,三角形ABC为等边三角形,分别以A、B、C三点为中心对称点做出△ABC的中心对称△ADE、△CFG、△BHI、分别以D、E、F、G、H、I点为中心对称点做出等边△......以此类推可以得到无数个等边三角形构成的几何结构。
空间结构中,多台驱动装置以三角形模块为基础,通过不同的立体几何布局构建由N台驱动装置组成的组合体,N≥3。构建方法:三角形ABC为等边三角形,以三角形中的任意一个顶点或者边长为中心对称点或者对称轴均可做出其立体对称三角形,以此类推,可以得到由无数个等边三角形构成的立体几何结构。
以上几何结构方案中的各节点为驱动装置的优选位置。
根据不同需要,驱动装置组合体中驱动装置的数量及安装节点的位置在不违背原理的基础上可任意设置。在保证组合体运行安全稳定的基础上,每个三角形模块中的驱动装置也可以根据结构需要有所增减。此外,根据不同需求可以选择安装相同规格、相同功能的驱动装置也可以选择安装不同规格、不同功能的驱动装置。
驱动装置之间由连接舱或连接装置连接,连接舱或连接装置可采用但不限于骨架、面状体或面状体镂空等。所述连接舱或连接装置可以单独制成或安装于面状、骨架状结构中。驱动装置之间如果以骨架方式连接,可以是固定连接,也可以是活动连接。驱动装置之间如果以面状体或面状体镂空方式连接,驱动装置可以直接安装其表面,也可以镶嵌安装于其镂空
空间中。
本发明的驱动装置***中驱动装置可以分别连接驱动力转换装置将驱动力转换为对外的输出作用力,也可以将驱动装置***中的驱动装置产生的驱动力组合后,连接驱动力转换装置将驱动力转换为对外的输出作用力。
依据现有技术领域,本发明中的驱动装置优选为发动机,发动机可以连接螺旋桨、变速器、牵引器、掘进装置等装置。
下面以驱动装置视为发动机为例,发动机由面状或骨架结构固定,该方案构建的装置根据用途可安装不同种类或型号的发动机。可对发动机单独控制,也可组合或混合控制。该方案构建的装置根据需要,发动机可以单独工作、部分组合或者全部组合工作。
本发明方案构建的装置中的每台发动机可以将发动机产生的动力转化后组合输出作用力,例如,发动机连接螺旋桨,把动力转化成风力或水力之后组合成强大的风力或水力。
本发明方案构建的装置中可将多台发动机的力全部组合或部分组合后由总轴输出。例如,发动机可由传动装置将力通过传动轴传动皮带、气、液力传动等方式将力传导给总轴,由组合输出轴输出作用力或连接力转换装置输出作用力。
本发明优选方案除用于搭载发动机之外,还可用于搭载发电机、发光源、喷头或其它需要组合工作的装置,且***中去除驱动装置占用的区域以外的区域均可作为其他装置的安装或承载区域。
本发明中飞行器的一个显著特点是驱动装置以三角形排列使得可以在单位体积内容纳更多的驱动装置,飞行器在获得同等推进力的条件下可保持最优的空间布局。
基本原则是飞行器驱动装置以三角形排列,组成三角形驱动装置模块;优选组合方法为相邻驱动装置之间的空间距离相等;以三角形排列的驱动装置模块为基础向空间方向映射排列组合成由多台驱动装置组成的驱动装置组合体;驱动装置组合体中驱动装置的数量为N台,N≥3。
驱动装置映射排列组合的优选方法可用以下几何方法表述,三角形ABC为等边三角形,以等边△ABC的BC边为轴作出△ABC的轴对称等边△BCD构成菱形ABCD,分别沿AB、BD、CD、AC向两边反向延长,截得与菱形边长相等的边,连接相应点,构成无数菱形,然后将所有菱形的短对角线连接起来,形成由无数个等边三角形构成的菱形几何结构,几何结构的节点处视为驱动装置优选安装位置,节点重合处视为共用位置,根据实际需要,节点的各个空间方向均可安装驱动装置。另外,驱动装置组合体的形状及驱动装置数量可以根据飞行环境或载荷重量、形态等需要做出相应变化。
本发明中,飞行器如果是喷气类旋转扭力较小的或无反扭力或反扭力可自身抵消的驱动
装置,例如喷气驱动装置或共轴反桨、多桨驱动装置,可以选用奇数台或偶数台驱动装置组合;如果使用产生旋转扭力比较强的驱动装置,例如,发动机连接螺旋桨的方式,需要优选偶数台发动机连接螺旋桨以抵消反扭力。目前来说,由多台驱动装置驱动的飞行器多采用发动机连接螺旋桨方式,因而,本发明的优选方案为菱形映射,即以等边三角形模块为基础组成菱形模块,在菱形的节点处安装发动机,发动机可以上下布置。
在几何结构中以菱形驱动装置模块(两个三角形模块组成)为基础构建的组合体中,由于飞行器的结构和功能特性,菱形模块内对角线的空间距离根据飞行器需要可以调节,并且,几何结构所构成的连接件中菱形的顶角角度可以调节。
本发明中,飞行器的驱动装置之间由连接件连接,连接件可以采用但不限于骨架或其他连接件。按照飞行器的特性及现有技术条件,飞行器可优选为骨架连接,骨架之间可为固定式或者活动式连接。采用固定式骨架是指可以制造一体式骨架或通过固定连接件固定骨架组件的形态;活动式骨架之间由活动连接件连接,制成可折叠或分解的骨架,在使用时骨架通过固定件限制骨架活动构成稳固的形态,需要减小体积时解除限制骨架活动的固定件即可实现骨架折叠或分解,这样有效地减小了飞行器,尤其是大型飞行器的体积,方便存放和运输。
本发明的第二大特点在于,飞行器可以根据飞行环境、载荷的形态及重量确定飞行器的尺寸、形状。飞行器上除去驱动装置占据的安装位置外,其余区域均可作为飞行辅助装置或载荷物的安装或挂载区域。由于本发明飞行器的特殊构架,飞行器驱动***中每台驱动装置或是每组驱动装置区域内均可设置载荷挂载区域或与整体载荷相连接的区域,这样设置的目的在于使飞行器驱动***中产生的驱动力均匀地施加给载荷部分,飞行器中的驱动装置与载荷之间的连接就不会出现因为应力集中在某个区域而导致影响整体飞行***的一系列恶性连锁反应。
本发明的具有多种飞行模式的飞行器是在飞行器驱动装置基础上加装机翼且机翼数量为M个,M≥1。以骨架方式连接为例,机翼通过连接件与飞行器骨架相连,连接件可以为固定连接或活动连接,可实现机翼快速折叠、分解安装。机翼可以轴向转动。在飞行过程中,飞行器与空气之间存在相对速度时,适当调整攻角机翼会产生升力以辅助驱动装置给飞行器提供升力,尤其是在低速飞行时,机翼通过调整不同角度配合飞行器的不同飞行姿态,从而最大限度地减小不利阻力。在特殊情况下飞行器与空气具有相对速度时,飞行器可以依靠机翼飞行或利用机翼减速,例如,飞行器驱动装置失灵时可以利用机翼滑翔作为缓冲,有效地保护了飞行器,或者调整机翼旋转角度使其在前进的方向上产生阻力从而对飞行器进行减速。
左右对应设置的机翼通过改变角度差的方式产生滚转力使飞行器发生横向滚转,类似于固定翼飞机的副翼舵的功能;前后对应设置的机翼或单个机翼通过调整攻角产生上升或者下
压力使飞行器发生纵向俯仰,类似于固定翼飞机的升降舵的功能。该飞行器在以一定速度飞行时,机翼可以产生额外的升力从而减小驱动装置的负担,同时,操纵机翼产生的舵面效应使飞行器改变姿态时也可减小驱动装置的负担,这在一定程度上节约了能源,延长了续航时间,也提高了载荷能力。
另外,当机翼沿着轴向旋转与机身平面达到一定角度时,机翼还可以作为飞行器的起落支撑装置,即起落架,从而有效地减少了飞行器的结构负担和起飞重量。
本具体实施方式还提供了驱动装置组合***的连接方式的优选方案。
下面将结合本发明实施例中的附图,对本发明实施例中的技术方案进行描述,显然,所描述的实施例仅仅是本发明一部分实施例,而不是全部的实施例。基于本发明的实施例,本领域普通技术人员在没有做出创造性劳动前提下所获得的所有其他实施例,都属于本发明的保护范围。
请参考图1-图4,本具体实施方式提供的驱动装置组合产生组合驱动力的方法是驱动装置(05)以三角形排列,组成三角形驱动装置模块(01),优选组合方法为相邻驱动装置(05)之间的空间距离相等,如图1中粗实线区域为等边三角形,其三个顶点,即节点(02)处可视为驱动装置(05)的安装位置;以图1中三角形上排列的驱动装置三角形模块(01)为基础向空间方向映射排列组合成由多台驱动装置(05)组成的驱动装置(05)组合体;驱动装置(05)组合体中驱动装置(05)的数量为X台,X≥3。其中,(03)为几何结构中三角形的映射体,(11)为几何结构参考线。
多台驱动装置组合的平面优选方法具体可用以下几何方法表述:如图2,三角形ABC为等边三角形,以等边△ABC的BC边为轴作出△ABC的轴对称等边△BCD构成菱形ABCD,分别沿AB、BD、CD、AC向两边反向延长,截得与菱形边长相等的边,连接相应点,构成无数菱形,形成菱形网块,然后将所有菱形的短对角线连接起来,形成无数个等边三角形(03)构成的几何结构。
多台驱动装置组合的另一个平面优选方法具体可用以下几何方法表述:如图3,三角形ABC为等边三角形,分别以A、B、C三点为中心对称点做出△ABC的中心对称△ADE、△CFG、△BHI,分别以D、E、F、G、H、I点为中心对称点做出等边三角形,以此类推可以得到无数个等边三角形(03)构成的几何结构。
多台驱动装置组合的立体优选方法可用以下几何方法表述,如图4,三角形ABC为等边三角形,以三角形中的任意一个顶点或者边长为中心对称点或者对称轴均可做出其立体对称三角形(03),以此类推,可以得到由无数个映射等边三角形(03)构成的立体几何结构。
以上所有几何结构中的各节点(02)视为驱动装置(05)的安装位置。根据实际需要,
可在节点(02)处选择性安装驱动装置(05)。
如图5所示本发明驱动装置组合体的最基本的三角形布局结构,优选地,采用等边三角形布局,即相邻驱动装置(05)之间的空间距离相等。
如图6所示为本发明驱动装置组合体的菱形布局结构,即两个等边三角形组合而成,重合处为驱动装置(05)共用位置。
图7是本发明的一个驱动装置组合体示意图,本图是由图3演变而来。图8是本发明的另一个驱动装置组合体的示意图,由图2演变而来。本发明的优势在于,根据实际需要,可以选择性在节点(02)处安装驱动装置(05),从而达到理想效果。
本发明中,驱动装置(05)按照现有技术优选为发动机,发动机可以连接螺旋桨、变速器、牵引器、掘进装置或其它装置。本具体实施方式还提供了驱动装置组合产生组合驱动力***的优选连接方式:如图9所示,驱动装置(05)之间以骨架方式(04)连接,可以是固定连接,也可以是活动连接;如图10a所示,驱动装置(05)之间以面状体连接,驱动装置(05)可以安装在面状体(06)表面,见图10b;如图11a所示,驱动装置(05)之间以面状体镂空方式连接,即驱动装置(05)安装在面状体内镂空区域(07),见图11b。
驱动装置组合体中的驱动装置(05)可以是相同规格、相同功能进行组合,也可以是不同规格、不同功能进行组合。此外,驱动装置***中驱动装置(05)可以分别连接驱动力转换装置(08)通过驱动力输出轴(12)向外输出驱动作用力,见图12a,也可以将驱动装置***中驱动装置(05)产生的驱动力组合后,连接驱动力转换装置(08)通过组合力输出轴(10)向外输出驱动作用力,见图12b,其中(09)为传动装置。
值得提出的是,本发明优选实施方案除用于搭载发动机之外,还可用于搭载发电机、发光源、喷头或其需要组合工作的装置,且***中去除用于安装驱动装置所占据的区域以外的区域还可以作为装置或***的安装区域。
图13示出了本发明飞行器的驱动装置的基本分布,图中三角形ABC为等边三角形,三角形的三个顶点处为飞行器驱动装置(05)位置,组成三角形驱动装置模块(01);优选地,相邻驱动装置(05)之间的空间距离相等;以三角形排列的驱动装置模块(01)为基础向空间方向映射排列组合成由多台驱动装置(05)组成的驱动装置(05)组合体,本图中菱形ABCD即由三角形ABC驱动装置模块衍生而来形成菱形模块,依此类推,可以形成各种形态的驱动装置(05)组合体;驱动装置(05)组合体中驱动装置(05)的数量为N台,N≥3。其中,(03)为几何结构中三角形的映射体,(11)为几何结构参考线。
本发明飞行器中驱动装置映射排列组合的优选实施方式的几何方法表述同前。
需要提出的是,为了发挥飞行器的最佳动力效果,所有几何结构中的节点(02)的各个
空间方向均可安装驱动装置(05),其中以节点(02)上下方向安装效果最佳。此外,驱动装置(05)组合体的尺寸、形状及驱动装置(05)数量可以根据需要做出变化。
驱动装置以发动机为例,下面将具体介绍由几何结构演变而来的驱动装置的几种可行性布局及优选连接方案。
依据图3的几何方法,以等边三角形ABC的三个顶点为基础,分别做其中心对称三角形(03),节点(02)处安装发动机(16)即成为图14所示发动机(16)组合体,发动机(16)通过发动机支架(15)固定于主体构架中,发动机(16)上端连接螺旋桨(14)即组合成为具有九台发动机(16)的飞行器,根据需要,节点(02)上下方向均可选择性安装发动机(16),最多可组合为十八旋翼飞行器。
依据图2的几何方法,在节点(02)处选择性安装发动机(16),可以得到如图15所示发动机(16)组合体,发动机(16)上连接螺旋桨(14)即可组合成为多轴多旋翼飞行器,同样,根据需要节点(02)处各个空间方向均可安装发动机(16)。
以上布局中,发动机(16)之间可由骨架、面状体镂空或其它方式连接。如果发动机以骨架(04)方式连接,骨架之间由骨架连接件(13)连接,如图16所示为具有八台发动机(16)的飞行器的优选骨架连接示意图,骨架连接件(13)可以是固定式或活动式。采用固定式骨架连接可以直接制造出一体式骨架(04)或通过固定连接件(08)固定骨架组件的形态;如图17所示,活动式骨架(04)之间由活动连接件(08)连接,制成可折叠或分解的骨架(04),在使用时骨架(04)通过固定件限制骨架活动构成稳固的形态,在存放和运输中需要减小体积时解除限制骨架活动的固定件,实现骨架(04)折叠或分解。如图18a所示发动机之间以面状体镂空方式连接,即发动机(16)安装在面状体(06)内镂空区域(07),见图18b。
本发明中的飞行器可以根据载荷的形态确定飞行器的尺寸、形状。飞行器上除去驱动装置占据的安装位置外,其余区域均可作为飞行辅助装置或载荷物的安装或挂载区域。如图19和图20所示,该发动机(16)组合体以菱形为动力单元,每个单元可视为飞行器动力***中的一个模块,每个模块根据发动机(16)数量可以产生一定的推力,每个模块可以分担飞行器中的一部分载荷(17),比如以菱形模块为例,菱形4个顶点有四台发动机(16),每台发动机(16)产生的推力一定,即该模块可以产生4个单位的推力,菱形模块中有四台发动机(16)以及配套的骨架(04)、电池等产生的重量,该模块产生的4个单位的推力可以同时分担模块的总体重量,同时剩余的推力可以用于分担飞行器总体的一部分载荷(17)重量。飞行器的动力***由N个动力模块组成,相邻动力模块中发动机(16)视为模块共用发动机(16),共同分担相邻模块中需分担的载荷(17)重量,即飞行器的起飞重量近似均匀的分担到动力***中。
飞行器动力单元中,如图19每台动力装置或每个动力模块内均可设置载荷(17)挂载区域或如图20与整体载荷(17)相连接的区域,这样设置的目的在于使飞行器动力***中的发动机(16)产生的驱动力均匀地施加给载荷(17)部分,飞行器中的发动机(16)与载荷(17)之间的连接就不会出现因为应力集中在某个区域而导致影响整体飞行***的一系列恶性连锁反应。
如图21,本具体实施方式提供的优选方案中,发动机(16-1)、(16-2)、(16-3)、(16-4)以菱形几何结构排列,通过骨架(04)连接,发动机(16)固定安装于骨架(04)处,骨架(04)之间通过骨架连接件(13)连接,骨架连接件(13)可以是固定式,也可以是活动式,发动机(16)连接螺旋桨(14),机翼(18)通过机翼连接件(19)与飞行器骨架(04)相连分别安装于发动机(16-2)和发动机(16-4)的两侧,机翼(18)可以轴向转动。
图22也是本方案的一种可行性实施方式。由图2或图3的几何方法可演变为本图中的飞行器布局结构,发动机(16-5)、(16-6)、(16-7)、(16-8)以矩形排列,通过骨架(04)交叉连接安装,可以是固定式连接,也可以是活动式连接,发动机(16)连接螺旋桨(14),机翼(18)对称安装于骨架(04)两侧,机翼(18)分别位于发动机(16-5)与(16-7)之间和发动机(16-6)与(16-8)之间区域,机翼(18)与骨架(04)之间由机翼连接件(19)连接,机翼(18)可以轴向转动。
如图23,代表了本方案的另一种可行性实施方式。由图2或图3的几何方法可演变为本图中的飞行器布局结构,由三个完整的三角形驱动装置模块(01)组合而成,即发动机(16-9)、(16-10)与(16-11)组成一个三角形驱动装置模块(01),发动机(16-12)、(16-13)与(16-14)组成一个三角形驱动装置模块(01),发动机(16-15)、(16-16)与(16-17)组成一个三角形驱动装置模块(01),发动机(16)之间由骨架(04)连接,可以是固定式连接,也可以是活动式连接,发动机(16)连接螺旋桨(14),同轴机翼(18)对称安装于三角形驱动装置模块(01)中发动机(16-9)的两侧,另一个机翼(18)安装于三角形驱动装置模块(01)中发动机(16-14)与(16-17)之间的区域,机翼(18)与骨架(04)之间由机翼连接件(19)连接,机翼(18)均可轴向转动。
以上所有实施例中,由于飞行器的特性,骨架(04)处均可上下方向安装发动机(16),若有特别需求,也不排除在其它方向上安装发动机(16)或其它装置。
附图中的图24展示了本发明中的一类飞行器的几种优选工作模式。如图,(20)代表了水平参考线,箭头方向为飞行器飞行方向。图24a为辅助升力及上升飞行模式,机翼(18)同时向上倾斜角度会产生升力以辅助发动机(16)给飞行器提供升力;图24b为辅助下降飞行模式,机翼(18)同时向下倾斜角度会产生下压力促使飞行器下降,同时飞行器中同轴机
翼(18)可单独动作实现如同固定翼飞行器中升降舵的作用使飞行器改变俯仰角度;图24c为低速降阻飞行模式,机翼(18)与发动机(16)平面保持近似平行或与飞行方向、气流方向保持最理想的风阻的角度以减小阻力维持最佳飞行状态;图24d为巡航飞行模式,为达到在不同航速下飞行器均具有最佳的性能表现,机翼(18)可通过调整攻角已达到最佳的气动布局,从而使飞行器在各种姿态、航速下均能呈现最佳的升阻比;图24e为滚转飞行模式,通过同轴机翼(18)左右差动偏转所产生的滚转力矩可使飞行器做横滚机动(相对飞行器飞行方向或迎流方向分别差动);图24f为降落或着陆模式,即飞行器需要着陆时,机翼(18)与机身平面达到一定角度可作为飞行器的起落支撑装置,即起落架,本图中机翼(18)近似垂直于机身平面。如果需要增加起落架尺寸时也可在机翼(18)与着陆面接触部位增加支撑或减震组件。
如图25a所示为本发明中各个模块的示意图,(21)为驱动装置模块,(22)为连接模块,(23)为承载模块,(24)为辅助模块。
下面对本发明的结构单元做进一步详细说明,按照现有飞行器的配置,本实施方式中均以电池为能源,驱动装置连接螺旋桨为例。图25b中,驱动装置模块(21)与承载模块(23)的一端通过连接模块(22)连接组成一个结构单元,连接模块(22)同时又与另一个承载模块(23)连接组成一个结构单元,以此类推,可以无限拓展。图25c中,连接模块(22)的X轴方向两端各自连接承载模块(23),Y轴方向两端各自连接驱动装置模块(21)组成一个结构单元,驱动装置模块(21)又与螺旋桨(27)相连组成发动机动力组,以此类推,可以无限拓展。图25d中,承载模块(23)两端分别经连接模块(22)安装驱动装置模块(21)组成一个结构单元,驱动装置模块(21)连有螺旋桨(27),以此类推,可以无限拓展。图25f,承载模块(23)两端分别经连接模块(22)安装驱动装置模块(21),同时,在两个连接模块(22)处、承载模块(23)下方设有辅助模块(24)共同组成一个结构单元,每个驱动装置模块(21)分别连有螺旋桨(27),本实施例中的辅助模块(24)的作用是若承载模块(23)中承载载荷重量较大时,可增加结构单元中承载模块(23)与驱动装置模块(21)之间的连接强度。图25e,驱动装置模块(21)与承载模块(23)的一端通过连接模块(22)连接组成一个结构单元,承载模块(23)下方通过辅助模块(24)可连有其它载荷(26)。
关于飞行器的模块化具体实施方式,参见图26至图31。
图26a、26b、26c、26d和26e是本发明的模块化不同实施例的俯视图。图中分别为由驱动装置模块(21)与承载模块(23)的一端通过连接模块(22)连接组成的结构单元进行模块化组合而成。图中(25)为螺旋桨旋转面。其中,图26e中,驱动装置模块(21)通过连接模块(22)与承载模块(23)组成一个结构单元,驱动装置模块(21)通过连接模块(22)与辅助模块(24)组成一个
结构单元,所有结构单元依次呈“环形”固定于中心连接模块(28)组成模块化飞行器,本图展示的是当飞行器所需载荷量较小时,无需所有承载模块(23)都承载电池或载荷时,可将部分承载模块(23)由辅助模块(24)替换,以减轻飞行器重量。
如图27a,连接模块(22)和承载模块(23)组成结构单元,多个结构单元以连接模块(22)为中心进行组合固定,连接模块(22)上下分别安装驱动装置模块(21),驱动装置模块(21)安装有螺旋桨(27)。
如图27b,驱动装置模块(21)、连接模块(22)和承载模块(23)组成结构单元,N个结构单元“首尾连接”,组合成“环形”结构的模块化飞行器。其中,每个驱动装置模块(21)上分别安装有螺旋桨(27),(25)为螺旋桨旋转面。
如图28a,驱动装置模块(21)、连接模块(22)和承载模块(23)组成结构单元,四个结构单元按照菱形构架组合成为模块化飞行器,飞行器下方安有辅助模块(24),用于挂载载荷。其中,每个驱动装置模块(21)上分别安装有螺旋桨(27),(25)为螺旋桨旋转面。图28b为局部侧视图,辅助模块(24)下方搭载有其它载荷(26)。
图29、图30和图31均是本发明飞行器模块化的拓展实施例的示意图。其中,图29为图28a的无限拓展示意图,图30为图26e的无限拓展示意图,图31是图26c的无限拓展示意图。
必须说明的是,除了上述实施方式以外,本发明当然还有很多其他的实施方式,例如,驱动装置模块中也可以选择以燃料驱动的发动机或者以其它能源驱动的发动机,诸如此类依据本发明所做的等效变化及修改,仍属于本发明的范围,故都应视为本发明的进一步实施例。例如:由于飞行器的结构与功能特性,有些驱动装置之间不必严格按照等边三角形模块组合,也可以是等腰三角形排列布局组合。同理,有些驱动装置也不必严格按照菱形模块组合,也可以是平行四边形排列布局组合等。此外,本发明飞行器结构中的机翼也是在技术条件允许的情况下选择安装位置。可见,相关的等同替换技术方案均应落在本发明要求的保护范围内。
所述附图仅为示意性的并且未按比例画出。虽然已经结合优选实施例对本发明进行了描述,但应当理解本发明的保护范围并不局限于这里所描述的实施例。
结合这里披露的本发明的说明和实践,本发明的其他实施例对于本领域技术人员都是易于想到和理解的。说明和实施例仅被认为是示例性的,本发明的真正范围和主旨均由权利要求所限定。
Claims (10)
- 一种具有多个驱动装置的驱动装置组合体,其特征在于:多个驱动装置的分布如下:a.其中三个驱动装置形成三角形单元,所述三个驱动装置位于所述三角形单元的顶点,其他驱动装置分布在所述三角形单元外并且在以下三组平行线的交点上:每组平行线是与所述三角形单元的一条边平行的等距直线,包括所述边所在直线,其中所述每组平行线的间距是所述三角形单元的相应边上的高长度;所述驱动装置的数量大于等于3、4、5、6、7、8、9、10、15、24或30;或者b.其中四个驱动装置形成具有四个三角形面的四面体单元,所述四面体单元的顶点为所述四个驱动装置的中心,以四面体单元为初始单元体,其他驱动装置分布在所述初始单元体外并且依次以以下方式纳入其中:每个所述其他驱动装置与所述单元体上的一个三角形面形成四面体单元;所述驱动装置的数量大于等于4、5、6、7、8、9、10、15、24或30。
- 根据权利要求1所述的驱动装置组合体,其特征在于:所述三角形单元为等边三角形,或者所述四面体单元为正四面体。
- 根据权利要求1或2所述的驱动装置组合体,该方法特征在于:所述驱动装置由连接舱或连接装置连接,所述连接舱或连接装置选自但不限于空腔舱体、龙骨框架、骨架、面状体、面状体镂空。
- 根据权利要求3所述的驱动装置组合体,该方法特征在于:所述连接舱或连接装置为固定连接或活动连接。
- 根据权利要求1至4任一项所述的驱动装置组合体,其特征在于:驱动装置为电力驱动装置、内燃机驱动装置、液力与液压驱动装置、气力驱动装置、人力驱动装置或复合驱动装置。
- 具有多个驱动装置的飞行器,其特征在于:所述***包括根据权利要求1-5任一项所述的驱动装置组合体。
- 根据权利要求6的飞行器,其特征在于:所述飞行器包括机翼,所述机翼与所述驱动装置组合体连接。
- 根据权利要求7所述的飞行器,其特征在于:所述机翼沿着轴向旋转,作为飞行器的起落支撑装置。
- 根据权利要求6-8任一项所述的飞行器,所述飞行器还包括飞行辅助装置或载荷物。
- 根据权利要求1-5任一项所述的驱动装置组合体或根据权利要求6-9任一项所述的飞行器,其特征在于,所述驱动装置组合体以模块组的形式组合而成,所述模块组包括驱动装置单元、连接舱单元和辅助单元。
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