Personal aircraft chassis and personal aircraft

Abstract

The invention provides a personal aircraft chassis and a personal aircraft. The chassis comprises a main framework and a chassis body, the personal aircraft comprises a main framework and a thrust array assembly, the thrust array assembly is fixed to the main framework, thrust of the thrust array assembly is achieved through a plurality of first turbojet engines, the geometric position relation between the thrust action point and the thrust direction of the thrust array assembly and the main framework is kept fixed, and when the personal aircraft stops on the ground, the thrust array assembly is fixed to the main framework. The thrust direction of the thrust array assembly is perpendicular to the ground. The vector nozzle assemblies are fixed to the main framework, thrust of the vector nozzle assemblies is achieved through the second turbojet engines, the central axes of the second turbojet engines are perpendicular to the central axis of the first turbojet engine, and vector nozzles of the vector nozzle assemblies at least have one degree of freedom relative to the main framework. And high-dynamic, high-fault-tolerance and reconfigurable flight control which cannot be realized by utilizing pure thrust difference control can be realized.

Description

Technical Field

[0001] The present invention relates to the technical field of aviation aircraft, and in particular to a personal aircraft chassis and a personal aircraft. Background Art

[0002] In many relatively small scenarios, the application of propeller-type aircraft will be severely limited due to their large size; while personal aircraft powered by turbojet engines can be very small, but stable flight control is a challenge for personal aircraft powered by turbojet engines.

[0003] Most turbojet personal aircraft currently available are controlled manually, with some relying on body tilt or arm movement to control the aircraft. The flight performance of these aircraft is heavily dependent on the pilot's physical strength and control skills.

[0004] The information disclosed in this background technology section is only intended to deepen the understanding of the overall background technology of the present invention and should not be regarded as an admission or any form of suggestion that the information constitutes the prior art already known to those skilled in the art. Summary of the Invention

[0005] In view of the problems existing in the prior art, the present invention provides a personal aircraft chassis and a personal aircraft.

[0006] The technical solution of the present invention provides a personal aircraft chassis, which includes: a main frame; a thrust array assembly, which is fixed to the main frame, and the thrust of the thrust array assembly is achieved by multiple first turbojet engines, and the thrust application point and thrust direction of the thrust array assembly remain fixed in geometric position relationship with the main frame. When the personal aircraft is docked on the ground, the thrust direction of the thrust array assembly is perpendicular to the ground; multiple vector nozzle assemblies, which are fixed to the main frame, and the thrust of the vector nozzle assembly is achieved by multiple second turbojet engines. The central axis of the second turbojet engine is perpendicular to the central axis of the first turbojet engine, and the vector nozzles of the vector nozzle assembly have at least one degree of freedom relative to the main frame.

[0007] Optionally, the thrust array assembly is arranged inside the main frame, and the thrust array assembly includes two parts: a front thrust array and a rear thrust array.

[0008] Optionally, a plurality of vector nozzle assemblies are symmetrically arranged on the outside of both sides of the main skeleton.

[0009] Optionally, the chassis also includes: a fuel distribution tank, which is fixed to the main frame, the fuel distribution tank is arranged between the front thrust array and the rear thrust array, and the fuel distribution tank is provided with multiple oil circuits connected to the first turbojet engine and the second turbojet engine.

[0010] Optionally, the chassis also includes: a number of electronic equipment compartments, which are arranged at the front end and / or rear end of the main frame, and the electronic equipment compartments can accommodate one or more of the three devices: engine control devices, flight control devices and battery devices.

[0011] Optionally, the thrust array assembly includes: a plurality of first fixing brackets and a plurality of one-to-one corresponding first turbojet engines, and each first fixing bracket fixes the corresponding first turbojet engine on the main frame.

[0012] Optionally, the vector nozzle assembly includes: a second fixing bracket and a corresponding second turbojet engine, the second fixing bracket fixes the corresponding second turbojet engine on the main frame; a third fixing bracket and a corresponding vector nozzle, the vector nozzle is connected to the second turbojet engine one-to-one, and the third fixing bracket fixes the corresponding vector nozzle on the main frame.

[0013] Optionally, the vector nozzle of the vector nozzle assembly has two or three degrees of freedom relative to the main skeleton.

[0014] Optionally, the chassis further includes: two front and rear shock-absorbing landing gears, the upper ends of the shock-absorbing landing gears being fixed on the main frame.

[0015] Optionally, the thrust array assembly includes five pairs of first turbojet engines symmetrically arranged on both sides of the central axis of the main skeleton; the multiple vector nozzle assemblies include two pairs of second turbojet engines symmetrically arranged on both sides of the central axis of the main skeleton.

[0016] Optionally, the air intakes of each pair of second turbojet engines are arranged relative to each other.

[0017] The technical solution of the present invention provides a personal aircraft, which includes the aforementioned chassis.

[0018] Additional aspects and advantages of the present invention will be set forth in part in the description which follows and, in part, will be obvious from the description which follows, or may be learned by practice of the present invention.

[0019] The beneficial effects of the present invention are as follows: the attitude, speed, etc. of the aircraft are controlled by combining the vector nozzle assembly and the thrust array assembly, which can realize high-dynamic, high-fault-tolerant, and reconfigurable flight control that cannot be achieved by using simple thrust difference control. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the technical solutions in the present invention or the prior art, a brief introduction will be given below to the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0021] Figure 1 A three-dimensional schematic diagram of a personal aircraft chassis provided in accordance with an embodiment of the present invention.

[0022] Figure 2 A schematic top view of a personal aircraft chassis provided in accordance with an embodiment of the present invention.

[0023] Figure 3 A three-dimensional schematic diagram of a personal aircraft chassis provided in accordance with another embodiment of the present invention.

[0024] Figure 4 A schematic top view of a personal aircraft chassis provided in accordance with another embodiment of the present invention. DETAILED DESCRIPTION

[0025] The advantages of the present invention are further described below with reference to the accompanying drawings and specific embodiments.

[0026] Exemplary embodiments are described in detail herein, with examples illustrated in the accompanying drawings. When the following description refers to the drawings, identical numerals in different drawings represent identical or similar elements unless otherwise indicated. The embodiments described in the following exemplary embodiments are not intended to represent all embodiments consistent with the present disclosure.

[0027] The terms used in this disclosure are for the purpose of describing specific embodiments only and are not intended to limit the disclosure. The singular forms "a," "the," and "the" used in this disclosure are also intended to include the plural forms unless the context clearly indicates otherwise. It should also be understood that the term "and / or" as used herein refers to and includes any or all possible combinations of one or more of the associated listed items.

[0028] It should be understood that although the terms first, second, third, etc. may be used in this disclosure to describe various information, such information should not be limited to these terms. These terms are only used to distinguish information of the same type from each other. For example, without departing from the scope of this disclosure, first information may also be referred to as second information, and similarly, second information may also be referred to as first information. Depending on the context, the word "if" as used herein may be interpreted as "at the time of" or "when" or "in response to determining."

[0029] In the description of the present invention, it should be understood that the terms "longitudinal", "transverse", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention.

[0030] In the description of the present invention, unless otherwise specified and limited, it should be noted that the terms "installed", "connected" and "connected" should be understood in a broad sense. For example, it can be a mechanical connection or an electrical connection, or it can be the internal communication between two components. It can be a direct connection or an indirect connection through an intermediate medium. For ordinary technicians in this field, the specific meanings of the above terms can be understood according to the specific circumstances.

[0031] In the following description, the suffixes such as "module", "component" or "unit" used to represent elements are only used to facilitate the description of the present invention and have no specific meaning. Therefore, "module" and "component" can be used interchangeably.

[0032] It should be noted that the personal aircraft described herein is generally a vehicle capable of carrying people and operating within the atmosphere, but small aircraft solely for the purpose of carrying cargo are also encompassed. The term "personal" is primarily intended to distinguish it from larger, traditional aircraft such as commercial airplanes, rockets, or private jets.

[0033] The present invention uses a flight control computer to control multiple vector nozzles and a thrust array composed of multiple thrusters to achieve stable control of the aircraft's attitude, speed, and other parameters in three-dimensional space. To meet different requirements, only different functional vehicles need to be replaced, while the same aircraft chassis is used.

[0034] Figure 1 A three-dimensional schematic diagram of a personal aircraft chassis provided by the present invention, Figure 2 The present invention provides a schematic top view of a personal aircraft chassis, as shown in FIG. Figure 1 and 2As shown, the technical solution of the present invention provides a personal aircraft chassis, the chassis comprising: a main skeleton 204; a thrust array assembly, the thrust array assembly is fixed on the main skeleton 204, the thrust of the thrust array assembly is realized by a plurality of first turbojet engines 202, the thrust application point and thrust direction of the thrust array assembly remain fixed in geometric position relationship with the main skeleton 204, when the personal aircraft is docked on the ground, the thrust direction of the thrust array assembly is perpendicular to the ground; a plurality of vector nozzle assemblies, the vector nozzle assembly is fixed on the main skeleton 204, the thrust of the vector nozzle assembly is realized by a plurality of second turbojet engines 206, the central axis of the second turbojet engine 206 is perpendicular to the central axis of the first turbojet engine 202, the vector nozzle 207 of the vector nozzle assembly has at least one degree of freedom relative to the main skeleton 204, so that at least the thrust direction of the vector nozzle assembly can be adjusted and changed, and when the degree of freedom is greater than one, the thrust application point can also be adjusted and changed.

[0035] This embodiment uses a combination of a vector nozzle assembly and a thrust array assembly to control the attitude, speed, etc. of the aircraft, which can achieve high-dynamic, high-fault-tolerant, and reconfigurable flight control that cannot be achieved using simple thrust difference control.

[0036] Optionally, a thrust array assembly is disposed within the main frame 204. The thrust array assembly comprises a front thrust array and a rear thrust array. In one embodiment, the front thrust array comprises four second turbojets 206, and the rear thrust array comprises six second turbojets 206. This front and rear array configuration further increases thrust redundancy, enhancing the robustness or reliability of the aircraft.

[0037] Optionally, the vectored nozzle assembly is symmetrically distributed on both sides of the main frame 204. In one embodiment, the vectored nozzle assembly includes four second turbojets 206, one located on each side of the main frame 204. Multiple engines provide thrust and control, improving the overall robustness of the system and, in turn, the overall safety and fault tolerance of the personal aircraft, ensuring that the safety level of the personal aircraft meets both daily and specialized needs.

[0038] Optionally, the chassis also includes a fuel distribution tank 215, which is fixed to the main frame 204 and positioned between the front and rear thrust arrays. The fuel distribution tank 215 is provided with multiple oil passages connecting the first and second turbojet engines 202, 206. This placement of the fuel distribution tank 215 shortens the total length of the oil passages to the first and second turbojet engines 202, 206, thereby reducing the weight of the oil pipes and the required oil pump pressure. This arrangement makes the overall chassis structure compact and lightweight.

[0039] Optionally, the chassis also includes: a number of electronic equipment compartments 201, which are arranged at the front and / or rear end of the main skeleton 204. One or more of the three devices, namely, an engine control device, a flight control device, and a battery device, can be placed in the electronic equipment compartment 201. The engine control device is connected to the oil pump to control the oil supply speed to the engine. The flight control device can control the rotation of the vector nozzle 207, thereby specifically changing the thrust application point and thrust direction of each second turbojet engine 206, making the operation of the aircraft simpler and safer. The battery device can supply power to the engine control device, the flight control device, etc.

[0040] Optionally, the thrust array assembly includes: a plurality of first fixing brackets and a plurality of one-to-one corresponding first turbojet engines 202 , and each first fixing bracket fixes the corresponding first turbojet engine 202 on the main skeleton 204 .

[0041] Furthermore, in one embodiment, the chassis includes a first longitudinal beam 212, which is fixed to the main frame 204. The first turbojet engine 202 of the front thrust array is fixed to the first longitudinal beam 212 and the main frame 204 via a first fixing bracket. Similarly, the chassis also includes a second longitudinal beam 213, which is fixed to the main frame 204. The first turbojet engine 202 of the rear thrust array is fixed to the second longitudinal beam 213 and the main frame 204 via a first fixing bracket.

[0042] Optionally, the vector nozzle assembly includes: a second fixing frame 205 and a corresponding second turbojet engine 206, the second fixing frame 205 fixes the corresponding second turbojet engine 206 on the main skeleton 204; a third fixing frame 214 and a corresponding vector nozzle 207, the vector nozzle 207 is connected to the second turbojet engine 206 one-to-one, and the third fixing frame 214 fixes the corresponding vector nozzle 207 on the main skeleton 204.

[0043] Optionally, the vector nozzle 207 of the vector nozzle assembly has two or three degrees of freedom relative to the main skeleton 204.

[0044] Optionally, the chassis further includes: two front and rear shock-absorbing landing gears 211 , and the upper ends of the shock-absorbing landing gears 211 are fixed on the main frame 204 .

[0045] Optionally, in one embodiment, the thrust array assembly includes five pairs of first turbojet engines 202 symmetrically arranged on either side of the central axis of the main frame 204; and the multiple vectoring nozzle assembly includes two pairs of second turbojet engines 206 symmetrically arranged on either side of the central axis of the main frame 204. The arrangement of multiple engines in the thrust array combined with the multiple vectoring nozzles 207 minimizes the impact of engine failure on the aircraft. In this embodiment, the aircraft can maintain normal operation even if fewer than three engines fail simultaneously.

[0046] The technical solution of the present invention provides a personal aircraft, which includes the aforementioned chassis.

[0047] In a more specific embodiment, the chassis of this embodiment includes the following six parts: multiple vector nozzle assemblies, a thrust array assembly, a fuel distribution tank 215, a main skeleton 204, a landing gear 211 and multiple electronic equipment compartments 201.

[0048] Each vector nozzle assembly's vector nozzle 207 has one to three degrees of freedom. Taking a two-degree-of-freedom vector nozzle 207 as an example, the vector nozzle 207 is rotatably connected to an adapter 210 via a first connector 209, and the adapter 210 is rotatably connected to the second turbojet engine 206 via a second connector 208. The adapter 210 can achieve a predetermined angle of airflow direction deflection. Furthermore, by controlling the first connector 209 and the second connector 208 via a servo motor 203, the vector nozzle 207 can be rotated under electronic control. In a specific implementation, the degrees of freedom of the vector nozzle 207 can be adjusted according to the application scenario and the required performance.

[0049] The thrust array assembly includes multiple first turbojet engines 202 with downward-facing nozzles. The thrust array assembly primarily provides downward thrust vectors for the aircraft. However, when the aircraft is airborne and its chassis is not parallel to the ground, the thrust array assembly can also provide thrust in other directions. Furthermore, different engines, under the control of the flight control computer, generate different thrusts. These varying thrusts cause the aircraft's attitude to change, and the overall performance of the thrust array assembly can also form an adjustable vector thrust.

[0050] The function of the fuel distribution tank 215 is to provide fuel distribution for all engines. The fuel from the main fuel tank first enters the fuel distribution tank 215 through a pipeline, and then is distributed to the oil pumps of each engine through multiple small pipelines. The fuel distribution tank 215 is connected to the skeleton through a fixed bayonet. The fuel distribution tank 215 is a sealed box with oil outlet pipe interfaces on both edges to provide fuel distribution for the turbojet engine; the middle is a multi-way oil inlet pipe interface, which is connected to the oil pipe of the main fuel tank. In addition to the function of fuel distribution, the fuel distribution tank 215 also prevents bubbles generated by the fuel during movement from affecting the normal operation of the engine.

[0051] The main frame 204 is primarily constructed from materials such as carbon fiber, aluminum alloy, and stainless steel. Its primary function is to secure components such as the vectoring nozzle assembly, thrust array assembly, fuel distribution tank 215, and electronics compartment 201. Furthermore, the frame is constructed with an upper and lower split structure, making it very convenient to remove and install components such as the thrust array and vectoring nozzle 207.

[0052] The main frame 204 has two landing gears 211 at the front and rear to support and cushion the entire structure. The landing gears 211 are made of stainless steel to prevent the engine's high-temperature flame from influencing the life of the landing gears 211.

[0053] like Figure 1-2 The two second turbojet engines on each side are installed in the same direction. The high-temperature airflow from the tail jet of the front vector nozzle will affect the air intake of the rear engine. Therefore, some protective measures need to be added to isolate this influence.

[0054] Furthermore, in another embodiment, Figure 3 and 4 As shown, the air intakes of each pair of the second turbojet engines are arranged relative to each other. Through this relative arrangement of the air intakes, the interference of the wake of the front engine on the air intake of the rear engine is avoided.

[0055] Furthermore, unlike the previous embodiments, in this embodiment, the electronic equipment compartment 201 is no longer located at the front and / or rear ends of the main frame 204, but rather in the middle of the main frame 204, thereby creating more usable space at both ends of the main frame 204. While the servo motor 203, which was located in the middle of the main frame 204 in the previous embodiments, is now located at the front and rear ends of the main frame 204 in this embodiment. This is because the servo motor 203 is used to provide power to control the rotation of the vector nozzle 207, and this reduces the distance between the power source and the device to be driven. Finally, it should be noted that the above embodiments are intended only to illustrate the technical solutions of the present invention and are not intended to limit them. While the present invention has been described in detail with reference to the previous embodiments, those skilled in the art should understand that modifications may be made to the technical solutions described in the previous embodiments, or that some of the technical features therein may be replaced by equivalents. Such modifications or replacements do not deviate from the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the various embodiments of the present invention.

Claims

1. A personal aircraft chassis, characterized in that: The chassis comprises: Main skeleton; a thrust array assembly fixed to the main frame, wherein the thrust of the thrust array assembly is provided by a plurality of first turbojet engines, wherein the thrust application point and thrust direction of the thrust array assembly are kept in a fixed geometric position relationship with the main frame, and when the personal aircraft is docked on the ground, the thrust direction of the thrust array assembly is perpendicular to the ground; A plurality of vector nozzle assemblies are fixed on the main skeleton, the thrust of the vector nozzle assemblies is realized by a plurality of second turbojet engines, the central axis of the second turbojet engine is perpendicular to the central axis of the first turbojet engine, and the vector nozzles of the vector nozzle assembly have at least one degree of freedom relative to the main skeleton.

2. The personal aircraft chassis according to claim 1, wherein: The thrust array assembly is arranged inside the main frame, and the thrust array assembly includes two parts: a front thrust array and a rear thrust array.

3. The personal aircraft chassis according to claim 2, wherein: The multiple vector nozzle assemblies are symmetrically arranged on the outside of both sides of the main skeleton.

4. The personal aircraft chassis according to claim 3, wherein: The chassis also includes: A fuel distribution tank is fixed on the main frame, and is arranged between the front thrust array and the rear thrust array. The fuel distribution tank is provided with a plurality of oil circuits connected to the first turbojet engine and the second turbojet engine.

5. The personal aircraft chassis according to claim 1, wherein: The chassis also includes: A plurality of electronic equipment compartments are provided at the front end and / or rear end of the main frame, and one or more of the three devices, namely, an engine control device, a flight control device and a battery device, can be housed in the electronic equipment compartments.

6. The personal aircraft chassis according to claim 1, wherein: The thrust array assembly comprises: There are a plurality of first fixing brackets and a plurality of first turbojet engines corresponding to each other, and each of the first fixing brackets fixes the corresponding first turbojet engine on the main frame.

7. The personal aircraft chassis according to claim 1, wherein: The vector nozzle assembly includes: a second fixing bracket and a corresponding second turbojet engine, wherein the second fixing bracket fixes the corresponding second turbojet engine to the main frame; A third fixing frame and a corresponding vector nozzle, wherein the third fixing frame fixes the corresponding vector nozzle on the main frame.

8. The personal aircraft chassis of claim 1, wherein: The vector nozzle of the vector nozzle assembly has two or three degrees of freedom relative to the main skeleton.

9. The personal aircraft chassis according to claim 1, wherein: The chassis also includes: Two front and rear shock-absorbing landing gears, the upper ends of which are fixed on the main frame.

10. The personal aircraft chassis of claim 1, wherein: The thrust array assembly includes five pairs of the first turbojet engines symmetrically arranged on both sides of the central axis of the main skeleton; The multiple vector nozzle assemblies include two pairs of the second turbojet engines symmetrically arranged on both sides of the central axis of the main skeleton.

11. The aircraft frame according to claim 10, characterized in that: The air inlets of each pair of the second turbojet engines are arranged opposite to each other.

12. A personal aircraft, characterized in that: The personal aircraft comprises the chassis according to any one of claims 1-11.

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