A transport aircraft

Abstract

The present invention proposes a transport aircraft, which relates to the technical field of aircraft. It includes a transport aircraft body, a front wing, a first vertical take-off and landing engine arranged on the front wing, a rotor jet engine rotatably connected to the front wing, and a second vertical take-off and landing engine arranged on the transport aircraft body; the rotor jet engine includes a rotor engine and a turbine engine, and the rotor engine is sleeved on the turbine engine. It can cruise in the form of a fixed-wing aircraft and can also perform vertical take-off and landing, which improves maneuverability.

Description

Technical Field

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

[0002] Rotor-wing aircraft have the functions of vertical take-off and landing and hovering, and they play an important role in the military field. They also show great application potential in the fields of earthquake and natural disaster relief, dangerous terrain search, or aerial photography, and have received widespread attention. However, their disadvantage is that compared with fixed-wing aircraft, their cruising ability is poor, which greatly limits their flight distance and speed. For events that require rapid response, they cannot reach the speed of fixed-wing aircraft. Therefore, a fixed-wing aircraft that can take off and land vertically is needed to improve the performance of the aircraft. Summary of the invention

[0003] The object of the present invention is to provide a transport aircraft which can cruise in the form of a fixed-wing aircraft and can also perform vertical take-off and landing, thereby improving maneuverability.

[0004] The embodiment of the present invention is achieved as follows:

[0005] An embodiment of the present application provides a transport aircraft, which includes a transport aircraft body, a canard, a first vertical take-off and landing engine arranged on the canard, a rotor jet engine rotatably connected to the canard, and a second vertical take-off and landing engine arranged on the transport aircraft body; the rotor jet engine includes a rotor engine and a turbine engine, and the rotor engine is mounted on the turbine engine.

[0006] In some embodiments of the present invention, the rotor engine includes a flight rotor, a drive motor and a transmission mechanism. The flight rotor is rotationally connected to the turbine engine. The drive motor is arranged on the turbine engine, the drive motor is connected to the transmission mechanism, and the transmission mechanism is connected to the flight rotor.

[0007] In some embodiments of the present invention, the transmission mechanism includes an annular gear, a bearing, a first gear and a transmission member, the annular gear is connected to the turbine engine through the bearing, the annular gear is meshed with the first gear, and the first gear is connected to the drive motor through the transmission member.

[0008] In some embodiments of the present invention, it also includes a plurality of translation engines arranged in the transport aircraft body, and the side wall of the transport aircraft body is provided with a translation nozzle adapted to any translation engine.

[0009] In some embodiments of the present invention, the translation engine includes a fuel tank, an oxidizer tank, a first air pump, a second air pump, an ignition device, an injector, a combustion chamber and a nozzle; the fuel tank is connected to the nozzle through the first air pump; one end of the nozzle is connected to the translation nozzle, the other end of the nozzle is connected to one end of the combustion chamber, the other end of the combustion chamber is connected to the output end of the injector, and the input end of the injector is connected to the oxidizer tank through the second air pump; the ignition device is connected to the oxidizer tank and the combustion chamber respectively.

[0010] In some embodiments of the present invention, a lifting device is further included, and the lifting device includes a lifting chain and a hook, and the hook is connected to the transport aircraft body through the lifting chain.

[0011] In some embodiments of the present invention, a magnetic attraction device is also included. The magnetic attraction device includes an electromagnet, a transmission chain and a winch arranged on the main body of the transport aircraft. The electromagnet is connected to the winch through the transmission chain.

[0012] In some embodiments of the present invention, a steering engine is provided on the tail wing of the transport aircraft body.

[0013] In some embodiments of the present invention, the second vertical take-off and landing engine is disposed on the transport aircraft body close to the steering engine.

[0014] In some embodiments of the present invention, an airbag is further included which is arranged on the transport aircraft body.

[0015] Compared with the prior art, the embodiments of the present invention have at least the following advantages or beneficial effects:

[0016] A transport aircraft comprises a transport aircraft body, a front wing, a first vertical take-off and landing engine arranged on the front wing, a rotor jet engine rotatably connected to the front wing, and a second vertical take-off and landing engine arranged on the transport aircraft body; the rotor jet engine comprises a rotor engine and a turbine engine, and the rotor engine is sleeved on the turbine engine.

[0017] For rotary-wing aircraft and fixed-wing aircraft, although rotary-wing aircraft has strong maneuverability, fixed-wing aircraft has the advantages of simple structure and strong carrying capacity that rotary-wing aircraft cannot match. Therefore, based on this idea, the inventor sets a combination of fixed-wing aircraft and rotary-wing aircraft, so that the fixed-wing aircraft can not only perform vertical take-off and landing, but also increase the load. Its specific implementation method is to set a first vertical take-off and landing engine on the front wing and set a second vertical take-off and landing engine on the main body of the transport aircraft, the purpose of which is to increase the lift of the transport aircraft, thereby improving the carrying capacity of the transport aircraft. In addition, a rotor jet engine rotatably connected to the front wing is set, the purpose of which is used for the transport aircraft to cruise, and when lifting, since the rotor jet engine is rotatably connected to the front wing, the posture during lifting can also be adjusted, thereby ensuring the balance of the transport aircraft and improving the safety performance. The rotor jet engine utilizes a combination of a rotor engine and a turbine engine, so that the rotor jet engine has two sets of lift devices. When either the lift device of the rotor engine or the turbine engine is damaged, the other lift device can be immediately started, further improving safety. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required for use in the embodiments are briefly introduced below. It should be understood that the following drawings only show certain embodiments of the present invention and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other related drawings can be obtained based on these drawings without creative work.

[0019] Figure 1 A state diagram of vertical take-off and landing of a transport aircraft of the present invention;

[0020] Figure 2 A state diagram of a transport aircraft cruising according to the present invention;

[0021] Figure 3 It is a structural schematic diagram of the rotary jet engine in the present invention;

[0022] Figure 4 It is the principle diagram of the translation engine in the present invention;

[0023] Figure 5 It is a structural schematic diagram of the lifting device in the present invention;

[0024] Figure 6 It is a structural schematic diagram of the magnetic attraction device in the present invention.

[0025] Icons: 1. Aircraft body; 11. Translation nozzle; 12. Airbag; 2. Front wing; 3. First vertical take-off and landing engine; 4. Tail; 41. Steering engine; 5. Second vertical take-off and landing engine; 6. Rotor jet engine; 61. Rotor engine; 611. Flight rotor; 612. Bearing; 613. Surrounding gear; 614. First gear; 615. Drive motor; 62. Turbine engine; 7. Lifting device; 71. Lifting chain; 72. Hook; 73. Transmission chain; 74. Electromagnet; 8. Translation engine; 81. Fuel tank; 82. Oxidizer tank; 83. Ignition device; 84. Combustion chamber; 85. Nozzle; 86. Injector; 87. First air pump; 88. Second air pump. DETAILED DESCRIPTION

[0026] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Generally, the components of the embodiments of the present invention described and shown in the drawings here can be arranged and designed in various different configurations.

[0027] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the invention claimed for protection, but merely represents selected embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0028] It should be noted that similar reference numerals and letters denote similar items in the following drawings, and therefore, once an item is defined in one drawing, further definition and explanation thereof is not required in subsequent drawings.

[0029] In the description of the embodiments of the present invention, it should be noted that if the terms "center", "upper", "lower", "left", "right", "inner", "outer", etc. appear, the orientation or position relationship indicated is based on the orientation or position relationship shown in the drawings, or the orientation or position relationship in which the invented product is usually placed when used. It is only for the convenience of describing the present invention and simplifying the description, and does not indicate or imply 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. In addition, the terms "first", "second", etc. are only used to distinguish the description, and cannot be understood as indicating or implying relative importance.

[0030] In the description of the embodiments of the present invention, "plurality" means at least 2.

[0031] In the description of the embodiments of the present invention, it is also necessary to explain that, unless otherwise clearly specified and limited, the terms "setting", "installation" and "connection" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0032] Example 1

[0033] Please refer to Figure 1 and Figure 3 , Figure 1 As shown, the present embodiment provides a transport aircraft, which includes a transport aircraft body 1, a front wing 2, a first vertical take-off and landing engine 3 arranged on the front wing 2, a rotor jet engine 6 rotatably connected to the front wing 2, and a second vertical take-off and landing engine 5 arranged on the transport aircraft body 1; the rotor jet engine 6 includes a rotor engine 61 and a turbine engine 62, and the rotor engine 61 is mounted on the turbine engine 62.

[0034] In some embodiments of the present invention, for rotary-wing aircraft and fixed-wing aircraft, although rotary-wing aircraft has strong maneuverability, for fixed-wing aircraft, the advantages of simple structure and strong carrying capacity of fixed-wing aircraft are also incomparable to rotary-wing aircraft. Therefore, based on this idea, the inventor sets a combination of fixed-wing aircraft and rotary-wing aircraft, so that the fixed-wing aircraft can not only perform vertical take-off and landing, but also increase the load. Its specific implementation method is to set a first vertical take-off and landing engine 3 on the front wing 2, and set a second vertical take-off and landing engine 5 on the main body of the transport aircraft, the purpose of which is to increase the lift of the transport aircraft, thereby improving the carrying capacity of the transport aircraft. In addition, a rotor jet engine 6 is provided, which is rotatably connected to the front wing 2, and its purpose is to be used for the transport aircraft for cruising, and when lifting, since the rotor jet engine 6 is rotatably connected to the front wing 2, the posture during lifting can also be adjusted, thereby ensuring the balance of the transport aircraft and improving the safety performance. The rotor jet engine 6 utilizes a combination of a rotor engine 61 and a turbine engine 62, so that the rotor jet engine 6 has two sets of lift devices, so that when any lift device of the rotor engine 61 or the turbine engine 62 is damaged, the other set of lift devices can be immediately started, thereby further improving safety.

[0035] In some embodiments of the present invention, the turbine engine 62 may be replaced by a turbojet engine or a small rocket engine.

[0036] Example 2

[0037] Please refer to Figure 3 This embodiment is based on the technical solution of Embodiment 1. The rotor engine 61 includes a flight rotor 611, a drive motor 615 and a transmission mechanism. The flight rotor 611 is rotationally connected to the turbine engine 62. The drive motor 615 is arranged on the turbine engine 62. The drive motor 615 is connected to the transmission mechanism, and the transmission mechanism is connected to the flight rotor 611.

[0038] In some embodiments of the present invention, the rotor jet engine 6 uses two sets of lift devices to drive the flight, and its purpose is to use the dual lift system to improve the flight speed and safety at the same time. The specific implementation method is to set the flight rotor 611 on the turbine engine 62, and the flight rotor 611 rotates in the turbine engine 62. Since the structure of the turbine engine 62 is relatively complex in the prior art, if the drive motor 615 is set in the turbine engine 62, it is necessary to modify its internal structure, which is costly. Therefore, in order to avoid modifying the turbine engine 62, the drive motor 615 is set on the outer wall of the turbine engine 62. At the same time, in order to reduce the wind resistance coefficient, the shell of the drive motor 615 is set to be streamlined. At the same time, in order to increase the rotation speed of the flight rotor 611, multiple drive motors 615 can also be set, and the drive motors 615 are distributed around the circumference of the turbine engine 62, thereby increasing the thrust of the rotor engine 61.

[0039] Example 3

[0040] Please refer to Figure 3 This embodiment is based on the technical solution of Embodiment 2. The transmission mechanism includes an orbiting gear 613, a bearing 612, a first gear 614 and a transmission member. The orbiting gear 613 is connected to the turbine engine 62 through the bearing 612. The orbiting gear 613 is meshed with the first gear 614. The first gear 614 is connected to the drive motor 615 through the transmission member.

[0041] In some embodiments of the present invention, since reducing the drag coefficient is an important factor affecting the performance of the aircraft during its cruising, the casing of the turbine engine 62 is also basically streamlined. In order to avoid the installation of the drive motor 615 from destroying its streamline, the casing of the drive motor 615 is set to be streamlined to match the turbine engine 62, and the transmission mechanism is installed in the casing of the drive motor 615. The specific implementation of the transmission mechanism is to utilize the surrounding gear 613 to mesh with the first gear 614, and then the drive motor 615 drives the transmission member to connect with the first gear 614, thereby driving the surrounding gear 613 to rotate, so as to achieve the purpose of rotating the flight rotor 611.

[0042] Example 4

[0043] Please refer to Figure 1 and Figure 4 This embodiment is based on the technical solution of Embodiment 1 and also includes a plurality of translation engines 8 arranged in the transport aircraft body, and the side wall of the transport aircraft body 1 is provided with a translation nozzle 11 adapted to any translation engine 8.

[0044] In some embodiments of the present invention, during the navigation of the transport aircraft, the existing aircraft usually adjusts the direction through the rudder on the tail 4 when turning, and the disadvantage of this adjustment method is that the turning angle is too large, and effective turning cannot be performed in an emergency. Therefore, in order to solve the above problem, this embodiment adopts an equal number of translation engines 8 arranged on both sides of the transport aircraft. The principle of the translation engine adopts a small rocket engine to spray, thereby providing thrust to one side of the entire transport aircraft, so that the transport aircraft can directly translate left and right, thereby improving the maneuverability of the transport aircraft.

[0045] Example 5

[0046] Please refer to Figure 4 This embodiment is based on the technical solution of Embodiment 4, and the translation engine 8 includes a fuel tank 81, an oxidizer tank 82, a first air pump 87, a second air pump 88, an ignition device 83, an injector 86, a combustion chamber 84 and a nozzle 85; the fuel tank 81 is connected to the nozzle 85 through the first air pump 87; one end of the nozzle 85 is connected to the translation nozzle 11, and the other end of the nozzle 85 is connected to one end of the combustion chamber 84, and the other end of the combustion chamber 84 is connected to the output end of the injector 86, and the input end of the injector 86 is connected to the oxidizer tank 82 through the second air pump 88; the ignition device 83 is connected to the oxidizer tank 82 and the combustion chamber 84 respectively.

[0047] In some embodiments of the present invention, although the principle of the translation engine 8 is similar to that of a rocket engine, since the transport aircraft does not need as much thrust as a rocket, its structure is improved to adapt to the transport aircraft. The specific implementation method is to set a fuel tank 81 for placing fuel, set an oxidizer tank 82 for assisting the combustion of the fuel, and at the same time, in order to ensure the sufficiency of the oxidizer, the oxidizer tank 82 can also be connected to the outside of the transport aircraft, and an air pump and a one-way valve are set to supply oxygen to the oxidizer tank 82, thereby ensuring the sufficiency of the oxidizer. A first air pump 87 is set to transport fuel to the nozzle 85, and a second air pump 88 is set to transport the oxidizer to the combustion chamber 84, and an ignition device 83 is set for fuel ignition. Finally, after the fuel and the oxidizer react in the combustion chamber 84, they are ejected from the nozzle 85, thereby providing power for the translation engine 8 and improving the maneuverability of the transport aircraft.

[0048] Example 6

[0049] Please refer to Figure 5 This embodiment is based on the technical solution of Embodiment 1 and further includes a lifting device 7, the lifting device 7 includes a lifting chain 71 and a hook 72, and the hook 72 is connected to the transport aircraft body 1 through the lifting chain 71.

[0050] In some embodiments of the present invention, in addition to internal loading of cargo in the cabin, the transport aircraft can also perform external lifting, that is, the cargo to be shipped is lifted and installed on the bottom of the transport aircraft by setting a lifting chain 71 and a hook 72. Because the device using external lifting is generally heavier and larger in size, the material of the lifting chain 71 and the hook 72 needs to have advantages such as high strength and high toughness. Therefore, this embodiment uses titanium alloy to improve the load-bearing capacity of the hook 72 and the lifting chain 71.

[0051] Example 7

[0052] Please refer to Figure 6 This embodiment is based on the technical solution of Embodiment 1 and also includes a magnetic attraction device, which includes an electromagnet 74, a transmission chain 73 and a winch arranged on the transport aircraft body 1, and the electromagnet 74 is connected to the winch through the transmission chain 73.

[0053] In some embodiments of the present invention, for many emergency situations, such as the need to evacuate some vehicles in the center of a fire, the hook 72 in Example 6 needs to be manually fixed. However, due to the urgency of time in a fire, there is basically no time and manpower to fix it. Therefore, this embodiment uses a magnetic suction device to quickly hoist and evacuate metal objects that need to be evacuated urgently. Its specific implementation method is to use an electromagnet 74 to adsorb metal objects. At the same time, since the electromagnet 74 is large in size, if the electromagnet 74 is always hung outside during flight, the wind resistance coefficient will increase, thereby slowing down the speed of the transport aircraft when flying to the hoisting site, thereby increasing the rescue time. Therefore, in order to avoid this situation, this embodiment uses a winch to store and release the electromagnet 74 through a transmission chain 73, thereby reducing the flight time of the transport aircraft when flying to the hoisting site and increasing the probability of successful rescue.

[0054] Example 8

[0055] Please refer to Figure 1 This embodiment is based on the technical solution of Embodiment 1 and proposes that a steering engine 41 is provided on the tail wing 4 of the transport aircraft body 1.

[0056] In some embodiments of the present invention, since the steering of fixed aircraft in the prior art mostly relies on the rudder of the tail 4, the disadvantage of this technology is that its steering angle is large, and the transport aircraft cannot rotate when adjusting its posture during hovering, which makes it lack of maneuverability. Therefore, in order to solve the above problems, this embodiment adopts the method of setting a steering engine 41 on the tail 4, which has the beneficial effect that during the cruise of the transport aircraft, the rudder of the tail 4 can still be used to adjust the direction, thereby saving energy in the transport aircraft; and when the posture needs to be adjusted during hovering, the steering engine 41 can be directly used to adjust it, thereby increasing maneuverability; in addition, when the transport aircraft encounters an emergency during cruising, for example, when it is used in the military, when the transport aircraft encounters an enemy attack and needs to evade urgently, it can still use the rotating engine to steer, thereby solving the danger of being locked by the enemy due to a large steering angle, and improving safety.

[0057] Example 9

[0058] Please refer to Figure 1 This embodiment is based on the technical solution of Embodiment 1, and the second vertical take-off and landing engine 5 is arranged on the transport aircraft body 1 near the steering engine 41.

[0059] In some embodiments of the present invention, since the transport aircraft is mainly used for transporting materials, its loading capacity is the main performance measure of the transport flight, so a second vertical take-off and landing engine 5 is provided. At the same time, in order to maintain its balance performance, the second vertical take-off and landing engine 5 is provided on the transport aircraft body 1 close to the steering engine 41 in this embodiment, so that the center of gravity of the transport aircraft will not shift backwards and cause the rear tilt, thereby achieving the goal of increasing the carrying capacity while ensuring safety.

[0060] Example 10

[0061] Please refer to Figure 6 This embodiment is proposed based on the technical solution of Embodiment 1 and also includes an airbag 12 arranged on the transport aircraft body 1.

[0062] In some embodiments of the present invention, the airbag 12 is provided mainly to enable the transport aircraft to open the airbag 12 when the aircraft is damaged, so that the transport aircraft can make an emergency landing on the water, thereby improving the safety of the transport aircraft.

[0063] In summary, an embodiment of the present invention provides a transport aircraft, which includes a transport aircraft body 1, a canard 2, a first vertical take-off and landing engine 3 arranged on the canard 2, a rotor jet engine 6 rotatably connected to the canard 2, and a second vertical take-off and landing engine 5 arranged on the transport aircraft body 1; the rotor jet engine 6 includes a rotor engine 61 and a turbine engine 62, and the rotor engine 61 is mounted on the turbine engine 62.

[0064] For rotary-wing aircraft and fixed-wing aircraft, although rotary-wing aircraft has strong maneuverability, fixed-wing aircraft has the advantages of simple structure and strong carrying capacity that rotary-wing aircraft cannot match. Therefore, based on this idea, the inventor sets a combination of fixed-wing aircraft and rotary-wing aircraft, so that the fixed-wing aircraft can not only perform vertical take-off and landing, but also increase the load. Its specific implementation method is to set a first vertical take-off and landing engine 3 on the front wing 2, and set a second vertical take-off and landing engine 5 on the main body of the transport aircraft, the purpose of which is to increase the lift of the transport aircraft, thereby improving the carrying capacity of the transport aircraft. In addition, a rotor jet engine 6 is provided, which is rotatably connected to the front wing 2, and its purpose is to be used for the transport aircraft for cruising, and when lifting, since the rotor jet engine 6 is rotatably connected to the front wing 2, the posture during lifting can also be adjusted, thereby ensuring the balance of the transport aircraft and improving the safety performance. The rotor jet engine 6 utilizes a combination of a rotor engine 61 and a turbine engine 62, so that the rotor jet engine 6 has two sets of lift devices, so that when any lift device of the rotor engine 61 or the turbine engine 62 is damaged, the other set of lift devices can be immediately started, thereby further improving safety.

[0065] The above are only preferred embodiments of the present invention and are not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A transport aircraft, characterized in that: The invention comprises a transport aircraft body, a front wing, a first vertical take-off and landing engine arranged on the front wing, a rotor jet engine rotatably connected to the front wing, and a second vertical take-off and landing engine arranged on the transport aircraft body; the rotor jet engine comprises a rotor engine and a turbine engine, and the rotor engine is sleeved on the turbine engine; It also includes a lifting device, the lifting device includes a lifting chain and a hook, the hook is connected to the transport aircraft body through the lifting chain; it also includes a magnetic device, the magnetic device includes an electromagnet, a transmission chain and a winch arranged in the transport aircraft body, the electromagnet is connected to the winch through the transmission chain; The rotor engine comprises a flight rotor, a drive motor and a transmission mechanism, wherein the flight rotor is rotationally connected to the turbine engine, the drive motor is arranged on the turbine engine, the drive motor is connected to the transmission mechanism, and the transmission mechanism is connected to the flight rotor; the transmission mechanism comprises an encircling gear, a bearing, a first gear and a transmission member, the encircling gear is connected to the turbine engine through the bearing, the encircling gear is meshed with the first gear, and the first gear is connected to the drive motor through the transmission member; It also includes a plurality of translation engines arranged in the main body of the transport aircraft, and the side wall of the main body of the transport aircraft is provided with a translation nozzle compatible with any of the translation engines; the translation engine includes a fuel tank, an oxidizer tank, a first air pump, a second air pump, an ignition device, an injector, a combustion chamber and a nozzle; the fuel tank is connected to the nozzle through the first air pump; one end of the nozzle is connected to the translation nozzle, the other end of the nozzle is connected to one end of the combustion chamber, the other end of the combustion chamber is connected to the output end of the injector, and the input end of the injector is connected to the oxidizer tank through the second air pump; the ignition device is respectively connected to the oxidizer tank and the combustion chamber.

2. The transport aircraft according to claim 1, characterized in that: A steering engine is arranged on the tail wing of the transport aircraft body.

3. The transport aircraft according to claim 2, characterized in that: The second vertical take-off and landing engine is arranged on the transport aircraft body close to the steering engine.

4. The transport aircraft according to claim 1, characterized in that: Also included is an air bag arranged on the transport aircraft body.

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