CN116477050A

CN116477050A - Foundation framework of aircraft

Info

Publication number: CN116477050A
Application number: CN202210036633.2A
Authority: CN
Inventors: 刘宗全
Original assignee: Individual
Current assignee: Individual
Priority date: 2022-01-13
Filing date: 2022-01-13
Publication date: 2023-07-25

Abstract

The invention provides a basic framework of an aircraft, and relates to the technical field of aircrafts. A base frame for an aircraft, comprising: the machine body comprises a machine body and a cockpit, and the cockpit is embedded in the machine body; the vertical lifting mechanism comprises a first engine unit, the first engine unit is arranged at the bottom of the machine body, and the exhaust end of the first engine unit is far away from the machine body; the driving mechanism comprises a second engine unit, and the second engine unit is arranged at the tail part of the driving mechanism; the control mechanism is arranged in the cockpit and is connected with the first engine unit and the second engine unit. The basic framework of the aircraft can directly lift the aircraft through the vertical thrust of the engine, is not constrained by the landing sites, and is convenient for landing and taking off of the aircraft.

Description

Foundation framework of aircraft

Technical Field

The invention relates to the technical field of aircrafts, in particular to a foundation framework of an aircraft.

Background

An aircraft is an instrument that flies within the atmosphere or outside the atmosphere in space (space). Aircraft fall into 3 categories: aircraft, spacecraft, rockets, and missiles. Flying in the atmosphere is known as an aircraft, such as a balloon, airship, airplane, etc. They fly by aerodynamic lift generated by static buoyancy of air or relative motion of air. In space flight, the aircraft is called a spacecraft, such as an artificial earth satellite, a manned spacecraft, a space probe, a space plane and the like. They get the necessary speed into space under the propulsion of the carrier rocket and then rely on inertia to do orbital motion similar to celestial bodies. Is an instrumental flyer manufactured by a human being, capable of flying off the ground, flying in space, and flying in an intra-or extra-atmospheric space (space) controlled by the human being. Flying in the atmosphere is called an aircraft, and flying in space is called a spacecraft.

At present, the horizontal thrust of an engine is generally adopted, so that a wing of the engine generates lift to lift an aircraft, and the aircraft is excessively restrained on a landing site and inconvenient to use.

Disclosure of Invention

The invention aims to provide a basic framework of an aircraft, which can directly lift the aircraft by the vertical thrust of an engine, is not constrained by a landing place, and is convenient for landing and taking off of the aircraft.

Embodiments of the present invention are implemented as follows:

an embodiment of the present application provides an aircraft infrastructure comprising: the machine body comprises a machine body and a cockpit, and the cockpit is embedded in the machine body; the vertical lifting mechanism comprises a first engine unit, the first engine unit is arranged at the bottom of the machine body, and the exhaust end of the first engine unit is far away from the machine body; the driving mechanism comprises a second engine unit, and the second engine unit is arranged at the tail part of the driving mechanism; the control mechanism is arranged in the cockpit and is connected with the first engine unit and the second engine unit.

In some embodiments of the present invention, the first engine unit includes a first array unit and a second array unit, where each of the first array unit and the second array unit includes a first power portion and a second power portion, a connection line of the first power portion and the second power portion is parallel to a central axis of the machine body, and the first array unit and the second array unit are symmetrically disposed at a bottom of the machine body.

In some embodiments of the present invention, the steering mechanism includes a rudder and a steering unit, the rudder is disposed in the cockpit, the steering unit is disposed in the body, and the rudder is connected to the steering unit.

In some embodiments of the present invention, the steering unit includes a third power unit rotatably disposed at a bottom of the main body, and the third power unit is connected to the rudder.

In some embodiments of the present invention, the body is provided with a landing gear, and the landing gear is located at an end of the first power portion and the second power portion away from the body.

In some embodiments of the present invention, the drop frame is in an annular structure, the drop frame includes a first ring body and a second ring body, an elastic member is disposed between the first ring body and the second ring body, a telescopic tube is sleeved on the elastic member, and the first ring body is disposed at the bottom of the first power portion.

In some embodiments of the present invention, the control mechanism further includes a control panel, the control panel is disposed in the cockpit, and the control panel is a touch screen.

In some embodiments of the present invention, the cockpit is provided with a plurality of inlets, and the inlets are correspondingly covered with door bodies, and the door bodies are hinged to the cockpit.

In some embodiments of the present invention, a camera is disposed on the body, and the camera is connected to the control panel.

In some embodiments of the present invention, the cockpit is detachably connected to the machine body, and a parachute bag is disposed on the cockpit.

Compared with the prior art, the embodiment of the invention has at least the following advantages or beneficial effects:

an embodiment of the present application provides an aircraft infrastructure comprising: the machine body comprises a machine body and a cockpit, and the cockpit is embedded in the machine body; the vertical lifting mechanism comprises a first engine unit, the first engine unit is arranged at the bottom of the machine body, and the exhaust end of the first engine unit is far away from the machine body; the driving mechanism comprises a second engine unit, and the second engine unit is arranged at the tail part of the driving mechanism; the control mechanism is arranged in the cockpit and is connected with the first engine unit and the second engine unit. The fuselage is used for installing basic parts of an aircraft and is used for loading and transporting passengers and cargoes, so that the passengers and the cargoes are protected. The machine body is used for loading cargoes and fuels, so that the cargoes and the fuels are conveniently loaded, and the service performance of the machine body is improved. The cockpit is used for installing various instruments for flying, is convenient for the cockpit to drive the aircraft, and improves the driving safety of the cockpit. The vertical lifting mechanism is used for vertically lifting the aircraft, does not need to glide and lift on a runway, reduces the constraint on an airport, and improves the usability of the aircraft. The first engine unit is used for lifting the body of the engine by the power of the engine. The driving mechanism is used for pushing the machine body to advance, so that the high-speed carrying of cargoes and passengers is facilitated. The second engine block is used for providing forward power. The control mechanism is used for operating the movement of the aircraft, is convenient for the operation of the control mechanism on the overturn, the steering and the pitching of the aircraft, and improves the drivability of the aircraft.

Therefore, the base frame of the aircraft can directly lift the aircraft through the vertical thrust of the engine, is not constrained by the landing sites, and is convenient for landing and taking off of the aircraft.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings that are needed in the embodiments will be briefly described below, it being understood that the following drawings only illustrate some embodiments of the present invention and therefore should not be considered as limiting the scope, and other related drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.

FIG. 1 is a schematic diagram of an embodiment of the present invention;

FIG. 2 is a bottom view of an embodiment of the present invention;

fig. 3 is a schematic view of a drop frame according to an embodiment of the invention.

Icon: 1-a machine body; 2-a cockpit; 3-a second engine block; 4-a first engine block; 5-steering units; 6-door body; 7-a first array unit; 8-a second array unit; 9-lowering the falling frame; 10-parachute bag; 11-a first ring body; 12-a second ring body; 13-telescoping rod.

Detailed Description

For the purpose of making the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments of the present invention. The components of the embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.

Thus, the following detailed description of the embodiments of the invention, as presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.

It should be noted that: like reference numerals and letters denote like items in the following figures, and thus once an item is defined in one figure, no further definition or explanation thereof is necessary in the following figures.

In the description of the embodiments of the present invention, it should be noted that, if the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. indicate an azimuth or a positional relationship based on that shown in the drawings, or an azimuth or a positional relationship in which the product of the present invention is conventionally put when used, it is merely for convenience of describing the present invention and simplifying the description, and it does not indicate or imply that the apparatus or element to be referred to must have a specific azimuth, be configured and operated in a specific azimuth, and thus should not be construed as limiting the present invention. Furthermore, the terms "first," "second," "third," and the like are used merely to distinguish between descriptions and should not be construed as indicating or implying relative importance.

Furthermore, the terms "horizontal," "vertical," "overhang" and the like, if any, do not denote a requirement that the component be absolutely horizontal or overhang, but rather may be slightly inclined. As "horizontal" merely means that its direction is more horizontal than "vertical", and does not mean that the structure must be perfectly horizontal, but may be slightly inclined.

In the description of the embodiments of the present invention, "plurality" means at least 2.

In the description of the embodiments of the present invention, it should also be noted that, unless explicitly specified and limited otherwise, the terms "disposed," "mounted," "connected," and "connected" should be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art according to the specific circumstances.

Examples

Referring to fig. 1-3, fig. 1 is a schematic structural diagram of an embodiment of the present invention; FIG. 2 illustrates a bottom view of an embodiment of the present invention; fig. 3 is a schematic view of a drop frame according to an embodiment of the invention.

Referring to fig. 1-3, the present embodiment provides an aircraft, including: the machine body comprises a machine body 1 and a cockpit 2, and the cockpit 2 is embedded in the machine body 1; the vertical lifting mechanism comprises a first engine unit 4, the first engine unit 4 is arranged at the bottom of the machine body 1, and the exhaust end of the first engine unit 4 is far away from the machine body 1; the driving mechanism comprises a second engine unit 3, and the second engine unit 3 is arranged at the tail part of the driving mechanism; the control mechanism is arranged in the cockpit 2 and is connected with the first engine unit 4 and the second engine unit 3.

In this embodiment, the fuselage is used for installing basic components of an aircraft and for loading and transporting passengers and goods, and protecting the passengers and the goods. The machine body 1 is used for loading cargoes and fuels, so that the cargoes and the fuels are conveniently loaded, and the service performance of the machine body is improved. The cockpit 2 is used for installing various instruments for flying, is convenient for the cockpit to drive the aircraft, and improves the driving safety.

Referring to fig. 1-3, in this embodiment, the vertical lifting mechanism is used to lift an aircraft, so that the aircraft does not need to glide and lift on a runway, thereby reducing the constraint on the airport and improving the usability of the aircraft. The first engine block 4 is used to raise its body by the power of the engine. The driving mechanism is used for pushing the machine body to advance, so that the high-speed carrying of cargoes and passengers is facilitated. The second engine block 3 is used to provide forward power. The control mechanism is used for operating the movement of the aircraft, is convenient for the operation of the control mechanism on the overturn, the steering and the pitching of the aircraft, and improves the drivability of the aircraft.

Referring to fig. 1-3, in some implementations of the present embodiment, the first engine set 4 includes a first array unit 7 and a second array unit 8, the first array unit 7 and the second array unit 8 include a first power portion and a second power portion, a connection line of the first power portion and the second power portion is parallel to a central axis of the machine body 1, and the first array unit 7 and the second array unit 8 are symmetrically disposed at a bottom of the machine body 1. The first array unit 7 is two turbine engines, and the connecting line of the two turbine engines is parallel to the central axis of the machine body 1; the first array unit 7 and the second array unit 8 are of the same type and are symmetrically arranged on the abdomen of the machine body 1.

In this embodiment, when in use, the first array unit 7 and the second array unit 8 are opened to operate, the machine body 1 is pushed into the air from bottom to top, the power of the machine body 1 is controlled to stop at any position in the air, and the machine body can stop at a distance of several meters, tens of meters, hundreds of meters, thousands of meters and tens of meters from the ground. The power output of the first array unit 7 and the power output of the second array unit 8 are controlled to realize the difference value of the left lifting force and the right lifting force of the machine body 1, so that the overturning of the machine body is controlled; the pitching of the machine body is controlled by controlling the engines of the first array unit 7 and the second array unit close to the tail part of the machine and the engines of the first array unit 7 and the second array unit close to the head part of the machine, so that the machine body 1 is convenient to operate, the weight of the whole machine body can be balanced, and the service performance of the machine body is greatly improved.

Besides, the whole machine body is lifted vertically through the first array unit 7 and the second array unit 8, so that different numbers of units are added according to the carrying capacity of the machine body 1, for example, the carrying capacity is different from several tons to thousands of tons, and the balance performance of the machine body is sequentially improved.

In this embodiment, the first power unit and the second power unit are turbine engines, and the turbojet engine is a turbine engine. Is characterized in that the thrust is generated by completely depending on the gas flow. Typically used as power for high speed aircraft, but with higher fuel consumption than turbofan engines. The structure of the turbojet engine consists of an air inlet channel, a gas compressor, a combustion chamber, a turbine and a tail nozzle, and an afterburner is arranged between the turbine and the tail nozzle of the fighter plane. Turbojet engines remain one of the heat engines, and must follow the principle of work done by the heat engine: energy is input at high pressure and released at low pressure. Thus, in principle, the jet engine and the piston engine are identical, and it is necessary to have four stages of intake, pressurization, combustion and exhaust, except that in the piston engine these 4 stages are performed in time-sharing sequence, but in the jet engine they are performed continuously, and the gas flows through the various parts of the jet engine in sequence, corresponding to the four operating positions of the piston engine. It can provide enough force to lift the aircraft, and is an ideal material for the first power section and the second power section, but is not limited to this material, and may be other materials in addition to this.

Referring to fig. 1-3, in some implementations of the present embodiment, the steering mechanism includes a rudder and a steering unit 5, the rudder is disposed in the cockpit 2, the steering unit 5 is disposed in the body 1, and the rudder is connected to the steering unit 5. The rudder is used to control the yaw of its body 1 and thus the change of direction of its body 1, facilitating its operation of the body 1. The steering unit 5 is used for providing power for yaw of the machine body 1, so that the direction of the machine head can be changed under the driving of the power.

In this embodiment, the steering unit 5 can rotate 180 degrees, and can move forward and backward, turn left and right, stop the aircraft to a designated position, and facilitate the control of the aircraft.

Referring to fig. 1-3, in some implementations of the present embodiment, the steering unit 5 includes a third power portion rotatably disposed at the bottom of the machine body, and the third power portion is connected to the rudder. The third power part is the same engine as the first power part and the second power part, and is only positioned at different positions and is matched and installed according to the use.

Referring to fig. 1-3, in some implementations of the present embodiment, the body 1 is provided with a drop frame 9, and the drop frame 9 is located at one end of the first power portion and the second power portion away from the body 1. The landing gear 9 is used for landing the aircraft, is convenient for supporting the aircraft after landing, and improves the supporting effect. In addition, the first power part and the second power part can be effectively protected. And landing brackets 9 are arranged at the contact ends of the engines of the first power part and the second power part and the ground, so that the balance of the aircraft after landing is increased.

Referring to fig. 3, in some embodiments of the present disclosure, the drop frame 9 is in an annular structure, the drop frame 9 includes a first ring body 11 and a second ring body 12, an elastic member is disposed between the first ring body 11 and the second ring body 12, a telescopic tube is sleeved on the elastic member, and the first ring body 11 is disposed at the bottom of the first power portion. The turbine engine is of a cylindrical structure, and the landing frame 9 is arranged at the air outlet end of the turbine engine, so that landing support is facilitated. The elasticity is used for damping the falling, and reduces the loss of the turbine engine. In this embodiment, the elastic member is a spring, which can effectively absorb shock and facilitate the consumption of energy for the engine to contact with the ground.

Referring to fig. 1-3, in some implementations of the present embodiment, the control mechanism further includes a control panel, where the control panel is disposed in the cockpit 2 and is a touch screen. The control panel is used for controlling the work of each electronic component, so that the real-time operation of the electronic component is facilitated. The control panel adopts a touch screen, a finger or other objects touch the touch screen arranged at the front end of the display, and then the system positions and selects information according to the positions of icons or menus touched by the finger to input the information into the touch screen, and the touch screen comprises a touch detection component and a touch screen controller. Facilitating the display and manipulation of the various components and data of the machine body 1.

Referring to fig. 1-3, in some implementations of the present embodiment, the cockpit 2 is provided with a plurality of inlets, and a door 6 is correspondingly covered on the inlets, and the door 6 is hinged to the cockpit 2. The entrance is convenient for passengers and drivers to get in and out, and improves the efficiency of getting on and off the machine. The door body 6 is used for sealing the entrance of the door body, so that the door body can conveniently run at a high speed, and the running safety of the door body is improved.

Referring to fig. 1 to 3, in some implementations of the present embodiment, a camera is disposed on the body 1, and the camera is connected to a control panel. Above-mentioned camera is used for gathering ground information, then transmits its ground information to the touch-sensitive screen, can adjust its landing position when being convenient for its landing, is convenient for promote the precision when its landing, promotes its performance.

In this embodiment, the camera, waterproof digital camera, has various kinds of cameras, and the basic principle of the operation is the same: the optical image signal is converted into an electrical signal for storage or transmission. When an object is photographed, the light reflected on the object is collected by the camera lens, so that the light is focused on the light receiving surface (for example, the target surface of the camera tube) of the camera device, and then the light is converted into electric energy through the camera device, so that a video signal is obtained. The photoelectric signal is weak, and is amplified by the pre-discharge circuit, and then processed and adjusted by various circuits, and the finally obtained standard signal can be sent to recording media such as a video recorder for recording, or is transmitted by a transmission system or is sent to a monitor for displaying. The device can acquire image data of the ground in real time, a driver can analyze whether the device can safely land according to the image of the device, so that the user can stably land the device on the aircraft, and the safety is improved.

In some implementations of the present embodiment, the cockpit 2 is detachably connected to the body 1, and the parachute bag 10 is disposed on the cockpit 2. The cockpit 2 is separable from the machine body 1, so that the cockpit 2 can be separated from the machine body 1 when the cockpit fails, and the riding safety performance of the cockpit is improved.

In this embodiment, the parachute bag 10 is used for opening the parachute when a dangerous situation occurs, so that a user can stably land on the ground, and the usability of the parachute bag is improved.

In this embodiment, the bottom chassis of the aircraft has the following advantages:

1. the vertical take-off and landing is not required to be constrained by the geographical position of the take-off and landing;

2. the machine body is stabilized and balanced, so that the machine body can fly stably and is convenient to fly;

3. the carrying capacity is not limited, the number of the boosters is not limited as long as the boosters are boosted by the bottom part vertically lifting, and the vertical lifting is not limited, and the invention is only limited to use and implementation by individuals or companies of individuals.

In summary, embodiments of the present application provide an aircraft infrastructure comprising: the machine body comprises a machine body 1 and a cockpit 2, and the cockpit 2 is embedded in the machine body 1; the vertical lifting mechanism comprises a first engine unit 4, the first engine unit 4 is arranged at the bottom of the machine body 1, and the exhaust end of the first engine unit 4 is far away from the machine body 1; the driving mechanism comprises a second engine unit 3, and the second engine unit 3 is arranged at the tail part of the driving mechanism; the control mechanism is arranged in the cockpit 2 and is connected with the first engine unit 4 and the second engine unit 3. The fuselage is used for installing basic parts of an aircraft and is used for loading and transporting passengers and cargoes, so that the passengers and the cargoes are protected. The machine body 1 is used for loading cargoes and fuels, so that the cargoes and the fuels are conveniently loaded, and the service performance of the machine body is improved. The cockpit 2 is used for installing various instruments for flying, is convenient for the cockpit to drive the aircraft, and improves the driving safety. Above-mentioned vertical lifting mechanism is used for carrying out the lifting with the aircraft, need not to glide on the runway and descend and rise, reduces the constraint to the airport, promotes its performance. The first engine block 4 is used to raise its body by the power of the engine. The driving mechanism is used for pushing the machine body to advance, so that the high-speed carrying of cargoes and passengers is facilitated. The second engine block 3 is used to provide forward power. The control mechanism is used for operating the movement of the aircraft, is convenient for the operation of the control mechanism on the overturn, the steering and the pitching of the aircraft, and improves the drivability of the aircraft.

The above is only a preferred embodiment of the present invention, and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A base frame for an aircraft, comprising:

the machine body comprises a machine body and a cockpit, and the cockpit is embedded in the machine body;

the vertical lifting mechanism comprises a first engine unit, the first engine unit is arranged at the bottom of the machine body, and the exhaust end of the first engine unit is far away from the machine body;

the driving mechanism comprises a second engine unit, and the second engine unit is arranged at the tail part of the driving mechanism;

the control mechanism is arranged in the cockpit and is connected with the first engine unit and the second engine unit.

2. The airframe as recited in claim 1, wherein said first engine block includes a first array block and a second array block, said first array block and said second array block each include a first power portion and a second power portion, a line connecting said first power portion and said second power portion is parallel to a central axis of said airframe, and said first array block and said second array block are symmetrically disposed at a bottom of said airframe.

3. The airframe as recited in claim 2, wherein said steering mechanism includes a rudder disposed within said cockpit and a steering assembly disposed within said airframe, said rudder being coupled to said steering assembly.

4. A basic frame of an aircraft according to claim 3, characterized in that the steering unit comprises a third power section, which is rotatably arranged at the bottom of the fuselage, which is connected with the rudder.

5. The airframe as recited in claim 4, wherein a drop frame is provided on said airframe, said drop frame being located at an end of said first and second power sections remote from said airframe.

6. The aircraft infrastructure of claim 5, wherein the landing gear is an annular structure, the landing gear includes a first ring body and a second ring body, an elastic member is disposed between the first ring body and the second ring body, a telescopic cylinder is sleeved on the elastic member, and the first ring body is disposed at the bottom of the first power portion.

7. The airframe as recited in claim 1, wherein said steering mechanism further comprises a control panel, said control panel being disposed within said cockpit, said control panel being a touch screen.

8. The airframe as defined in claim 7 wherein a camera is provided on said body, said camera being connected to said control panel.

9. The airframe as defined in claim 1, wherein said cockpit is provided with a plurality of entrances, said entrances being covered with doors, said doors being hinged to said cockpit.

10. The airframe as defined in claim 1, wherein said cockpit is removably connected to said body, said cockpit having a parachute bag disposed thereon.