AU2014100764A4 - Vehicular System allowing the Modular Construction of Unmanned Aerial Vehicles - Google Patents

Abstract

An Unmanned Aerial Vehicle (UAV) platform which groups components into pre-built modules for a 'plug-and-play' construction, thus allowing a versatile, four or more rotor powered UAV system. The UAV would consist of the following modules in any combination: four or more Engine Booms [2], one or more structural Airframe Modules [1], one or more Flight System Modules [4], one or more Payload Structures [3], and one or more Payload Modules [21]. Herein, the Engine Booms mount onto the Airframe, the Payload Structure mounts onto the Airframe and the Payload Modules and Flight System Modules may be mounted on to the structural Airframe or the Payload Structure. This invention allows for the interchangeability of modules to allow the UAV to adapt its mission capability quickly, in a cost effective manner, while modularisation also aids reliability and the ability to operate in harsh environments. Figure 1 | | |A| | | | | | | | | | | 1I | | | | | II "N ? -4|| | || |I | 2 1 X X'

Description

1 VEHICULAR SYSTEM ALLOWING THE MODULAR CONSTRUCTION OF UNMANNED AERIAL VEHICLES BACKGROUND OF THE INVENTION [0001] Unmanned Aerial Vehicles (UAVs) are aerospace systems which can either be operated remotely by pilot, by pre-programmed commands or through computing systems with artificial intelligence capabilities. UAVs are increasingly sought after to perform tasks such as; surveillance, data measurement and recording, topographical mapping and use in military domains. The UAV is preferable in many circumstances over a Manned Aerial Vehicle because of the UAV's reduced cost of construction, less stringent maintenance requirements and long operability durations. In particular Multi-Rotor Aerial Vehicles are increasingly being explored as viable airborne platforms due to their stability. An example of a Multi-Rotor Vehicle is the Quadcopter, or Quadrocopter, which manoeuvres by varying the Revolutions per Minute of its four engines. SUMMARY OF THE INVENTION [0002] Cost, ease of use and reliability are the most common factors that are required to be dealt with when a sufficiently advanced technology is introduced to mainstream markets. While military-industrial contracts cater for the inherent high costs of advanced technology - for non-military markets; low cost, reliability and ease of use are the major concerns of consumers. Ideally, a UAV that is operable and/or maintainable without a specialist engineer is required. The non-military market demands the aforementioned UAV characteristics as well as tailored operational capabilities to the consumers desires, be that; surveillance, data measurement and recording, topographical mapping or other non-military uses. Whilst the technical problem is predominantly a non-military problem, the solution will probably also have operational niches in military forces. [0003] This invention solves the three problems listed above: cost, ease of use and reliability; through the design of a modular UAV platform. The use of an airframe with a multitude of mounting joints, allows the 'plug-and-play' of a potentially large variety of modules. These modules may include, but are not limited to; engine-arms, batteries, flight computers, flight sensors and a range of payload modules, of different sizes, and specifications to suit the required operation. The invention is not 2 the sensors and components themselves, as they have already been invented. Rather the invention is an entire UAV platform which allows a modularly constructed UAV system from a variety of easily interchangeable modules. [0004] The invention will vastly reduce current UAV maintenance costs, as well as increase operational reliability. The 'plug-and-play' concept of the modules and the airframe allow for easy replacement of worn or unsafe parts. Mechanical expertise is not required for maintenance due to the conscious efforts at simplifying the construction of the invention for the user. Operational reliability is a by-product of the modularisation of the airframe. Over the duration of an operation, down-time due to maintenance should be almost entirely eradicated. Reduced maintenance costs and increased reliability result in lower costs of maintenance, faster completion of operational goals and an absence of expensive mechanical expertise on-site. [0005] The illustrations provided from here on in are for communication purposes only, and are not intended to precisely outline the scope of the claims of this invention. An example of the potential embodiments of this invention are illustrated in Figure 1, Figure 2, Figure 3, Figure 4, Figure 5, Figure 6 and Figure 7. [0006] Figure 1 shows schematic view of the top of one embodiment of the invention, where all of the modules are disconnected from the Airframe. The dotted lines show the path where the parts mount onto the Airframe. The Fixed Gimbal is shown in the inset, and mounts onto the Airframe along the dotted lines. [0007] Figure 2 is a schematic view depicting one embodiment of the invention along the longitudinal plane. The dotted lines show where the Landing Gear Modules attach to the Landing Gear mounts on the Airframe. [0008] Figure 3 is a schematic view depicting one embodiment of the invention along the longitudinal plane, in which the Payload Structure is a Gyroscopic Gimbal. The Gyroscopic Gimbal is shown in a partially rotated orientation, with the inner gyro parallel to the viewer's lateral plan of vision. [0009] Figure 4 is a schematic view showing the top of an embodiment of the invention where a different selection of Airframe Modules comprise the Airframe. Figure 4 shows the comparison between the unconstructed modules and the constructed modules. The constructed version including the Landing Gear Modules.

3 [0010] Figure 5 is a Longitudinal depiction of the various embodiments of the Landing Gear Modules [0011] Figure 6 is a depiction of the top view of various Engine Boom Modules. [0012] Figure 7 is a top view of the constructed UAV with the Fixed Gimbal. DESCRIPTION OF THE EMBODIMENTS [0013] This invention in its simplest embodiment consists of four parts: the Airframe [1], the Engine Booms [2], the Payload Structure [3] and the Flight Systems [4]. The inventiveness lies in the further modularisation of the aforementioned parts. From here on in, throughout the Description and the Claims sections, the term 'modular' is used to denote a component which is designed to be easily mounted or attached to another component. Thus, a 'module' in reference to this invention is specifically defined as a component that consists of smaller parts, but more importantly, is removable and replaceable with relative ease. [0014] In one embodiment, the Airframe consists of a series of Airframe Modules. The modules in the embodiment shown in Figure 4 are as follows: the Airframe Cornerpiece Module [5], the Airframe Longitudinal Strut [6], Airframe Lateral Strut [7]. and the Landing Gear Module Mounts [8]. [0015] In other embodiments, shown in Figure 4, the Airframe shape can be changed by removing the Airframe Lateral Struts, and/or adding Airframe Spacer Modules [9]. Airframe Spacer Modules perform no other task than a structural extension of the Airframe. The Airframe Space Modules are constructed in a similar manner to the Airframe Lateral and Airframe Longitudinal Modules, allowing the required electrical and flight system cabling to run throughout hollows of the Airframe structure. [0016] The Landing Gear Modules that are introduced in paragraph [0013], would be mounted directly onto the Airframe in the simplest embodiment. This is shown in Figure 2. In this embodiment, there are four standard Landing Gear Modules [10]. In other embodiments, shown in Figure 5; the Landing Gear Modules may be swapped with Wide-pad Landing Gears [13], Floating Pontoon landing pads [11], or Ski Landing Gear Modules [12]. The possibilities of Landing Gear Modules are not limited by the aforementioned list. [0017] The particular embodiment shown in Figure 1 is a four rotor UAV, where each Rotor [14] is attached to the Airframe via an Engine Boom. The Engine Boom 4 consists of an Engine Mount Arm [15] which houses the Engine Motor [16], which then drives the Rotor. The Engine Mount Arm joint [17] allows the Engine Boom to attach to the Airframe. The joint allows the rotation of the Engine Boom to vector its propeller's thrust. The joint also allows the attachment of several different sized Engine Boom modules [18] to the Airframe, shown in Figure 6. This invention allows for a problem with an engine to be quickly solved by the dismounting of the Engine Mounting Arm from the Airframe, and the entire problematic Engine Boom replaced with a spare Engine Boom Module. [0018] The Airframe allows for upwards of four Engine Boom modules, a number of Engine Boom attachment locations [19], Figure 1, exist on the Airframe where additional Engine Boom modules can be attached. The line-of-action to slot the Engine Mount Arms into the Airframe is shown for each Engine Boom with dotted lines [20]. [0019] The Airframe also allows for the transport of various payloads. These payloads are supported by a Payload Structure. Where the Airframe has restricted locations for Payload Module mounts, the Payload Structure provides additional mounting areas. The Payload Structure can be a static or dynamic structure, and of any design that fits within the footprint of the Airframe. [0020] The Fixed Gimbal [21] in Figure 7 is one embodiment of the Payload Structure Module. The Fixed Gimbal is a static structure that provides mounting beams between the Airframe. Payload Modules are mounted on to the Fixed Gimbal as shown in one embodiment in Figure 7. In this embodiment, a Camera [21], and two other miscellaneous Payload Modules [22] are attached. These miscellaneous Payload modules could be scientific measurement devices, storage canister's or any other device that serves a purpose that UAV operator would wish. The Payload Modules are attached using a mounting system [23] universal on the Fixed and Gyroscopic Module. [0021] Another embodiment of the invention is shown in Figure 3. Figure 3 shows a Gyroscopic Gimbal [24], in place of the Fixed Gimbal, the Gyroscopic Gimbal consists of two nested structures, one larger [25] and one smaller [26], which are free to rotate within each other. The Gyroscopic Gimbal is a remotely controlled mechanism which allows user the ability to direct the focus of its payload in a full three-hundred-and-sixty degree rotation, in all three dimensions. A key aspect of the 5 Gyroscopic Gimbal is that the moment of inertia of the Gyroscope aligns with the moment of inertia of the whole UAV system. [0022] One advantage of this invention is its ability to easily swap modules. In one embodiment, shown in Figure 3, scientific measurement sensors modules [28] and a Camera [27] are mounted onto the cross-braces [29] of the Gyroscopic Gimbal. The Payload Modules can consist of, but are not limited to; scientific measurement sensors, visual imaging devices, and radar systems. In addition to the payload; flight systems and sensors also have their requisite mounting locations [29] though they are not limited to the specific locations in this embodiment. [0023] The last part of the invention outlined in paragraph [0013], and depicted in Figure 7, is the Flight Systems. The Flight Systems, consist of, but are not limited to the following modules: the Battery Modules [30], the Flight Computer Module [31], the Flight Camera Module [32], various Flight Sensor Modules [33] and Flight Operation Modules. The purpose of modularising the Flight System is to allow ease of adaptation to flight operations. The Battery Module provides electrical power to the other Flight Systems as well as supporting the power needs of the Payload Modules. The Flight Computer Module receives inputs from the various Flight Sensor modules, processes the data and signals back to a ground user. The Airframe allows the UAV to operate more than one Battery Module and/or Flight System Module. [0024] The Flight Camera Module mentioned in the previous paragraph, may be mounted on the Airframe directly, or mounted on the Payload Structure. The Flight Camera Module performs visual imaging tasks, and reports that information to the Flight Computer Module. The last type of Flight System Module is the Flight Sensor Module, these may be located on any area of the UAV. These modules may perform, but aren't limited to, the following tasks; measurement of altitude, vehicle orientation, engine health and operation, vehicle speed and vehicle location. [0025] In some embodiments, flight operations may need to support intense electrical demand from the Payload Modules. In this case, the embodiment would utilise more than one battery module, perhaps at the expense of a comprehensive Flight Camera Module, in order to maintain operational weight. [0026] Flight Operation Modules, as introduced in paragraph [0023], are a part of the Flight System, which aid or alter the flight mechanics of the UAV. As specified in 6 paragraph [0016], the Engine Booms are able to vector their thrust. If the Engine Boom thrust is vectored along the longitudinal axis of the UAV, the quadrocopter UAVs flight mechanics begin to approximate that of a fixed wing UAV. To assist in the production of lift, the Flight Operation Modules, in one embodiment, are a pair of foam or other suitable lightweight material, wings. Flight Operation Modules attach onto the Airframe, and are as easily dismountable as any of the aforementioned modules. Other Flight Operation Modules may include, but are not limited to; various Tail Modules, variously spanned wings and variously shaped wings

Claims (10)

1. A complete UAV platform which allows a modularly constructed UAV system from a variety of easily interchangeable modules wherein said modules are classified according to the parts that they compose, and the parts are classified as follows: i. A structurally supporting Airframe and its constituent Airframe Modules. ii. A series of thrust or lift producing Engine Booms. iii. A series of Payload Structures. iv. A Flight System and its constituent Flight System Modules. v. A series of Payload Modules.

2. The invention in claim 1, wherein the desired Payload Structure mounts onto the desired structurally supporting Airframe, the Flight System Modules mount on the Airframe or the Payload Structure and the Payload Modules mount onto the Airframe or the Payload Structure.

3. The invention in claim 1, wherein the Airframe may be made of smaller interchangeable Airframe Modules, not limited to: Airframe Cornerpieces, Airframe Struts, Airframe Spacers and Landing Gear Modules.

4. The invention in claim 1, wherein the Engine Booms provide the required lift and thrust for the UAV to manoeuvre, the Engine Boom Modules may be of a range of sizes and capabilities and attach to the Airframe via an Engine Mount Joint.

5. The invention in claim 4, wherein the Engine Mount Joints allow each Engine Boom to rotate around at least two axes, resulting in the vectoring of the Engine's thrust.

6. The invention in claim 1, wherein the Flight System Modules are interchangeable and comprise all components in which flight of an UAV is required: this includes, but is not limited to; Battery Modules, Flight Computer 2 Modules, Flight Sensor Modules, Flight Camera Modules, Fuel Tank Modules and Flight Operation Modules.

7. The invention in Claim 5, where one embodiment of a Flight System Module, is a Flight Operation Module, which consists of a pair of aeroplane wings and/or an aeroplane tail that are mountable to the Airframe.

8. The invention in claim 1, wherein the Payload Structure is a static structure which mounts on the Airframe that provides extra estate in which to mount Payload Modules.

9. A Gyroscopic Payload Structure, which is consists of one or more rotating structures. In the case of two or more rotating structures, the structures are nested in a typical gyroscopic manner, as a skilled person would understand. The gyroscope payload structure is mounted on the airframe, where the moment of inertia of the gyroscope is in the same location as the moment of inertia of the total UAV system.

10. The invention in claim 1, wherein the Payload modules are compartmentalized, enclosed systems powered by the UAV's Flight Systems. Modules may consist of, but are not limited to; scientific measurement sensors, cameras, defence systems, global positioning systems, and radar systems. This invention does not claim inventiveness of the sensors themselves, rather the modularisation of the sensors into an interchangeable part that mounts onto the UAV airframe payload platform.