CN215323279U - Aircraft - Google Patents

Abstract

The utility model provides an aircraft, and relates to the technical field of aircraft. The engine set comprises a plurality of dual-system engines, the dual-system engines comprise driving engines arranged in the aircraft body, turbine engines arranged on the aircraft body, rotating mechanisms sleeved on the turbine engines, first transmission mechanisms connected with the rotating mechanisms and first rotors connected with the rotating mechanisms, and the driving engines are connected with the first transmission mechanisms. The safety of the aircraft can be improved, and the survival probability of airborne personnel is increased.

Description

Aircraft

Technical Field

The utility model relates to the technical field of aircrafts, in particular to an aircraft.

Background

Airports are becoming increasingly necessary to be located near urban areas to address the needs of passengers and the needs of other trips between cities. However, airports have a considerable footprint due to the long runways and extensive space required for fixed wing aircraft to take off and land safely. For small and medium-sized cities, it is also cost prohibitive to build such airports. Among them, construction of airports can be well burdened in large cities, but noise, pollution and safety problems presented by urban airports are problematic. Accordingly, there is a long felt need in the aerospace industry for a small, cost-effective vertical takeoff and landing aircraft that can take off, land, and be contained on relatively small pieces of land for commercial and residential property. As for the vertical take-off and landing aircraft in the prior art, a helicopter is mostly adopted, and the disadvantages that once a rotor wing is damaged, the helicopter is damaged and people die, and the safety is poor.

SUMMERY OF THE UTILITY MODEL

The utility model aims to provide an aircraft, which can improve the safety of the aircraft and increase the survival probability of airborne personnel.

The embodiment of the utility model is realized by the following steps:

the embodiment of the application provides an aircraft, it includes aircraft main part, engine unit and sets up the cockpit in the aircraft main part, and the engine unit includes a plurality of dual system engines, and dual system engine is including setting up the drive engine in the aircraft main part, setting up the turbine engine in the aircraft main part, the slewing mechanism of locating on the turbine engine of cover, the first drive mechanism who is connected with slewing mechanism and the first rotor of being connected with slewing structure, and drive engine is connected with first drive mechanism.

In some embodiments of the present invention, the rotating mechanism includes a driving gear, a bearing, and an internal gear, the bearing is sleeved on the turbine engine, the internal gear is sleeved on the bearing, the internal gear is engaged with the driving gear, and the driving gear is connected with the first transmission mechanism.

In some embodiments of the present invention, the first transmission mechanism includes a first bevel gear, a second bevel gear, a first transmission member, and a second transmission member, the first bevel gear is connected to the driving gear through the first transmission member, the first bevel gear is engaged with the second bevel gear, and the second bevel gear is connected to the driving motor through the second transmission member.

In some embodiments of the present invention, the wind turbine further comprises a second transmission mechanism, the second transmission mechanism comprises a driving motor, a worm wheel and a worm meshed with the worm wheel, the worm wheel is connected with the first rotor, the worm is connected with the driving motor, the driving motor is arranged in the internal gear, and the first rotor is hinged with the internal gear.

In some embodiments of the present invention, the hybrid vehicle further comprises a first steering mechanism, a second steering mechanism, a third steering mechanism, a first electric machine, a second electric machine and a third electric machine which are installed in the aircraft main body, wherein the plurality of dual-system engines are a first dual-system engine, a second dual-system engine and a third dual-system engine respectively; the first double-system engine is hinged with the aircraft body and is connected with the first motor through a first steering mechanism; the second double-system engine and the third double-system engine are respectively in rotary connection with the aircraft body; the second dual-system engine is connected with a second motor through a second steering mechanism; and the third dual-system engine is connected with a third motor through a third steering mechanism.

In some embodiments of the present invention, the first steering mechanism includes a first rotating member connected to the first dual system engine, a first gear connected to the first rotating member, a third gear engaged with the second gear, a fourth gear connected to the first motor, and a first connecting member.

In some embodiments of the present invention, the second steering mechanism includes a second rotating member having one end connected to the second dual system motor, the other end connected to the third gear, a fourth gear engaged with the fourth gear, and a second connecting member connected to the second motor.

In some embodiments of the present invention, the third steering mechanism includes a third rotating member, one end of which is connected to the third dual system engine, the other end of which is connected to the fifth gear, the fifth gear is engaged with the sixth gear, and the sixth gear is connected to the third motor.

In some embodiments of the utility model, the aircraft further comprises a plurality of second rotors disposed on the aircraft body, the plurality of second rotors being disposed evenly around the circumference of the cockpit.

In some embodiments of the utility model, the aircraft further comprises a retractable tail wing arranged on the aircraft body.

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

the utility model provides an aircraft, its includes aircraft main part, engine block and sets up the cockpit in the aircraft main part, and the engine block includes a plurality of dual system engines, and dual system engine is including setting up the drive engine in the aircraft main part, setting up the turbine engine in the aircraft main part, the slewing mechanism of cover on locating the turbine engine, the first drive mechanism who is connected with slewing mechanism and the first rotor that is connected with slewing structure, and drive engine is connected with first drive mechanism.

For the prior art vertical take-off and landing aircraft, the occupied space and high cost are important factors for limiting the development of the aircraft, and the most important factor for really influencing the vertical take-off and landing aircraft is also a safety problem. As for the helicopters in the prior art, only one set of system for flying is basically provided, most helicopters adopt control rotors for taking off and landing and cruising, and a small part of helicopters use an aviation turbine engine for lifting. The disadvantage is that, in case of a problem with this single flight system, the aircraft cannot fly normally, and therefore can only fall. Therefore, in order to solve the above problems, the present embodiment employs the engine set of the dual-system engine, so that the aircraft has multiple sets of flight systems, even if one of the flight systems has a problem, the pilot can immediately switch another flight system, so that the aircraft still has flight capability, thereby avoiding the occurrence of the situation of machine damage and human death. The specific implementation mode is that a first rotor wing is arranged on a turbine engine for aviation, and in order to avoid interference of the rotor wing on an air inlet of the turbine engine, the first rotor wing is arranged on a side wall of the turbine engine, and meanwhile, in order to enable the first rotor wing to rotate, a driving engine is utilized to drive a transmission mechanism, and the transmission mechanism is driven to be provided with a rotating mechanism to rotate, so that the first rotor wing can rotate on the outer wall of the turbine engine. The combined type aircraft has the beneficial effects that the combination of the rotor wing and the turbine engine ensures that the aircraft occupies smaller space and has smaller resistance when flying, and the two flying systems of the rotor wing and the turbine engine are matched for use, so that the energy of the aircraft can be greatly saved; meanwhile, the flight system is switched under emergency conditions, so that the safety of airborne personnel is ensured, and the safety is improved.

Drawings

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

FIG. 1 is a schematic structural view of an aircraft of the present invention;

FIG. 2 is a cruise diagram of an aircraft of the present invention;

FIG. 3 is a cross-sectional view of a first dual system engine of the present invention;

FIG. 4 is an enlarged view of a portion of FIG. 3 at B;

FIG. 5 is an enlarged view of a portion of FIG. 3 at A;

FIG. 6 is a schematic structural view of a first steering mechanism according to the present invention;

FIG. 7 is a schematic structural view of a first steering mechanism and a third steering mechanism of the present invention;

FIG. 8 is another cruise control view of an aircraft according to the present invention.

Icon: 1. an aircraft body; 11. an airfoil; 2. a cockpit; 3. an engine block; 31. a first dual system engine; 311. a first rotor; 32. a second dual system engine; 33. a third dual system engine; 4. a second rotor; 5. a retractable tail wing; 6. a rotating mechanism; 61. a drive gear; 62. a bearing; 63. an internal gear; 7. a first transmission mechanism; 71. a first bevel gear; 72. a second bevel gear; 73. a second transmission member; 74. driving the engine; 75. a first transmission member; 8. a second transmission mechanism; 81. a worm gear; 82. a worm; 83. a drive motor; 9. a first steering mechanism; 91. a first gear; 92. a second gear; 93. a first connecting member; 94. a third bevel gear; 95. a first motor; 96. a fourth bevel gear; 97. a first rotating member; 10. a second steering mechanism; 101. a second rotating member; 102. a third gear; 103. a fourth gear; 104. a second connecting member; 105. a second motor; 106. a third steering mechanism; 107. a third rotating member; 108. a fifth gear; 109. a sixth gear; 1010. a third connecting member; 1011. a third motor.

Detailed Description

In order to make the objects, 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 with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. The components of 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 present invention, presented in the figures, is not intended to limit the scope of the utility model, as claimed, but is merely representative of selected embodiments of the utility model. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.

In the description of the embodiments of the present invention, it should be noted that, if the terms "upper", "lower", "inner", "outer", etc. are used for indicating the orientations or positional relationships based on the orientations or positional relationships shown in the drawings or the orientations or positional relationships which are usually arranged when the products of the present invention are used, the terms are only used for convenience of describing the present invention and simplifying the description, but do not indicate or imply that the devices or elements which are indicated must have specific orientations, be constructed in specific orientations, and operate, and therefore, the present invention should not be construed as being limited. Furthermore, the terms "first," "second," "third," and the like are used solely to distinguish one from another and are not to be construed as indicating or implying relative importance.

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

In the description of the embodiments of the present invention, it should be further noted that unless otherwise explicitly stated or limited, the terms "disposed," "mounted," and "connected" should be interpreted broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.

Example 1

Referring to fig. 1, fig. 1 shows that the present embodiment provides an aircraft, which includes an aircraft main body 1, an engine unit 3, and a cockpit 2 disposed on the aircraft main body 1, where the engine unit 3 includes a plurality of dual-system engines, the dual-system engines include a driving engine 74 disposed in the aircraft main body 1, a turbine engine disposed on the aircraft main body 1, a rotating mechanism 6 sleeved on the turbine engine, a first transmission mechanism 7 connected with the rotating mechanism 6, and a first rotor 311 connected with the rotating mechanism, and the driving engine 74 is connected with the first transmission mechanism 7.

In some embodiments of the present invention, space usage and high cost are important factors limiting aircraft development for prior art VTOL aircraft, and the most important factor actually affecting VTOL aircraft is safety issues. As for the helicopters in the prior art, only one set of system for flying is basically provided, most helicopters adopt control rotors for taking off and landing and cruising, and a small part of helicopters use an aviation turbine engine for lifting. The disadvantage is that, in case of a problem with this single flight system, the aircraft cannot fly normally, and therefore can only fall. Therefore, in order to solve the above problems, the present embodiment employs the engine set 3 with dual system engines, so that the aircraft has multiple sets of flight systems, even if one of the flight systems has a problem, the pilot can immediately switch another flight system, so that the aircraft still has flight capability, thereby avoiding the occurrence of the situation of machine damage and human death. The turbine engine may be replaced by a turbojet engine or a small rocket engine, and a specific embodiment of the turbine engine is that the first rotor 311 is provided on the turbine engine for aviation, so as to prevent the rotor from interfering with an air inlet of the turbine engine, the first rotor 311 is provided on a side wall of the turbine engine, and at the same time, the drive engine 74 is used to drive the transmission mechanism to rotate the transmission mechanism 6 so that the first rotor 311 can rotate on an outer wall of the turbine engine. The combined type aircraft has the beneficial effects that the combination of the rotor wing and the turbine engine ensures that the aircraft occupies smaller space and has smaller resistance when flying, and the two flying systems of the rotor wing and the turbine engine are matched for use, so that the energy of the aircraft can be greatly saved; meanwhile, the flight system is switched under emergency conditions, so that the safety of airborne personnel is ensured, and the safety is improved.

Example 2

Referring to fig. 3 and 4, the present embodiment proposes based on the technical solution of embodiment 1 that the rotating mechanism 6 includes a driving gear 61, a bearing 62 and an internal gear 63, the bearing 62 is sleeved on the turbine engine, the internal gear 63 is sleeved on the bearing 62, the internal gear 63 is meshed with the driving gear 61, and the driving gear 61 is connected with the first transmission mechanism 7.

In some embodiments of the present invention, in order to enable the first rotor 311 to successfully rotate on the turbine engine without affecting the operation of the turbine engine, the bearing 62 is sleeved on the turbine engine, so that the first rotor 311 rotates on the turbine engine through the bearing 62, and simultaneously the driving engine 74 drives the transmission mechanism and then drives the internal gear 63 to rotate, thereby achieving the purpose of controlling the rotor.

Example 3

Referring to fig. 3 and 4, the present embodiment proposes based on the technical solution of embodiment 2 that the first transmission mechanism 7 includes a first bevel gear 71, a second bevel gear 72, a first transmission member 75 and a second transmission member 73, the first bevel gear 71 is connected with the driving gear 61 through the first transmission member 75, the first bevel gear 71 is engaged with the second bevel gear 72, and the second bevel gear 72 is connected with the driving motor 74 through the second transmission member 73.

In some embodiments of the present invention, since the volume of the turbine engine is limited and the wind resistance coefficient is increased inevitably if the power source is designed on the outer wall of the turbine engine, in order to avoid the above situation, the power source is arranged in the aircraft body 1, and in order to maintain the balance of the aircraft, the driving motor 74 is placed in the middle of the wing 11 of the aircraft body 1, so the transmission mechanism thereof needs to be steered, and thus the first bevel gear 71 and the second bevel gear 72 are arranged to be engaged for steering, and the first bevel gear 71 and the internal gear 63 are connected, so that the driving motor 74 can transmit the kinetic energy to the rotating mechanism 6 at a vertical angle, thereby achieving the purpose of driving the first rotor 311.

Example 4

Referring to fig. 3 and fig. 5, the present embodiment is provided based on the technical solution of embodiment 2, and further includes a second transmission mechanism 8, where the second transmission mechanism 8 includes a driving motor 83, a worm wheel 81, and a worm 82 engaged with the worm wheel 81, the worm wheel 81 is connected with the first rotor 311, the worm 82 is connected with the driving motor 83, the driving motor 83 is disposed in the internal gear 63, and the first rotor 311 is hinged to the internal gear 63.

In some embodiments of the present invention, when the aircraft needs to lift in an emergency, since the first rotor 311 is deployed to generate a certain resistance, once the aircraft is accelerated too much, the resistance applied to the first rotor 311 will also increase, which may cause the first rotor 311 to break. Therefore, in order to avoid the above situation, the first rotor 311 is folded in this embodiment, so that the first rotor can be accommodated, and therefore, the resistance can be reduced when the turbine engine is lifted, and the occupied area can be reduced when the aircraft is parked. The specific implementation mode is that the driving motor 83 is used for driving the worm 82, the worm wheel 81 is connected with the first rotor 311, and the first rotor 311 is hinged with the inner gear 63, so that the first rotor 311 can rotate to achieve the function of contraction. And because worm wheel 81 worm 82 has the auto-lock performance again for first rotor 311 can be better spacing after expanding, improved stability.

Example 5

Referring to fig. 1, fig. 2, fig. 6 and fig. 7, the present embodiment is proposed based on the technical solution of embodiment 1, and further includes a first steering mechanism 9, a second steering mechanism 10, a third steering mechanism 106, a first electric machine 95, a second electric machine 105 and a third electric machine 1011 mounted in the aircraft body 1, where the plurality of dual-system engines are a first dual-system engine 31, a second dual-system engine 32 and a third dual-system engine 33, respectively; the first dual-system engine 31 is hinged with the aircraft body 1, and the first dual-system engine 31 is connected with the first motor 95 through the first steering mechanism 9; the second double-system engine 32 and the third double-system engine 33 are respectively connected with the aircraft body 1 in a rotating way; the second dual-system engine 32 is connected with the second motor 105 through the second steering mechanism 10; the third dual system engine 33 is connected to a third motor 1011 via a third steering mechanism 106.

In some embodiments of the present invention, a major disadvantage of the vtol aircraft is that the vtol aircraft has a lower cruising ability than the fixed-wing aircraft, and the main reason for this is that the vtol aircraft is inclined by the forward and backward movements of the rotor, so that the propulsive force cannot be applied to the forward direction to the maximum. Therefore, in order to solve the above problems, in this embodiment, a mode of position conversion of the dual-system engine is adopted, so that the power of the dual-system engine can be directly used for advancing, and in this embodiment, the aircraft body 1 is triangular, and the existing wing 11 model theory is adopted, so that the air pressure below the triangular wing 11 is greater than the air pressure above the triangular wing, thereby ensuring the lift force during flight, achieving the purpose of propelling the dual-system engine, and improving the performance of the aircraft. The specific implementation mode is that a first motor 95 is used for driving a first steering mechanism 9 to be connected with a first dual-system engine 31, and the first dual-system engine 31 is hinged with the aircraft body 1; the second dual-system engine 32 and the third dual-system engine 33 are driven by the second motor 105 and the third motor 1011, respectively, and are driven by the second steering mechanism 10 and the third steering mechanism 106, so that the second dual-system engine 32 and the third dual-system engine 33 rotate circumferentially on a vertical plane, and therefore the first dual-system engine 31, the second dual-system engine 32 and the third dual-system engine 33 are in the same direction, and the cruising performance of the aircraft is improved.

In some embodiments of the present invention, as shown in fig. 8, in order to reduce the wind resistance coefficient, it is also possible to directly rotatably connect the first dual-system engine 31 directly to the aircraft body 1, thereby reducing the contact area with the air and reducing the wind resistance coefficient.

Example 6

Referring to fig. 6, in the present embodiment, based on the technical solution of embodiment 5, a first steering mechanism 9 includes a first rotating member 97, a first gear 91, a second gear 92, a third bevel gear 94, a fourth bevel gear 96 and a first connecting member 93, the first rotating member 97 is connected to the first dual-system engine 31, the first gear 91 is connected to the first rotating member 97, the first gear 91 is engaged with the second gear 92, the second gear 92 is connected to the third bevel gear 94 through the connecting member, the third bevel gear 94 is engaged with the fourth bevel gear 96, and the fourth bevel gear 96 is connected to the first motor 95.

In some embodiments of the present invention, since the first dual-system engine 31 is hinged to the aircraft body 1, and the rotation direction thereof is downward, when the first motor 95 is disposed, the middle of the aircraft wing 11 should be disposed as much as possible to maintain the balance of the aircraft wing 11, and after the first motor is disposed in the middle of the aircraft wing 11, the output shaft of the first motor 95 is the center line of the wing 11, at this time, the third bevel gear 94 and the fourth bevel gear 96 need to be disposed to perform steering, and then cooperate with the first gear 91 and the second gear 92 to perform transmission, and at the same time, two symmetrical sets of the first gear 91, two sets of the second gear 92 and two sets of the third bevel gear 94 may be disposed to further ensure the balance, which has the beneficial effects of improving balance, increasing torque and improving stability.

Example 7

Referring to fig. 7, in this embodiment, based on the technical solution of embodiment 5, the second steering mechanism 10 includes a second rotating member 101, a third gear 102, a fourth gear 103 and a second connecting member 104, one end of the second rotating member 101 is connected to the second dual system engine 32, the other end of the second rotating member 101 is connected to the third gear 102, the third gear 102 is engaged with the fourth gear 103, and the fourth gear 103 is connected to the second motor 105.

Referring to fig. 8, the third steering mechanism 106 includes a third rotating member 107, a fifth gear 108, a sixth gear 109 and a third connecting member 1010, one end of the third rotating member 107 is connected to the third dual system engine 33, the other end of the third rotating member 107 is connected to the fifth gear 108, the fifth gear 108 is engaged with the sixth gear 109, and the sixth gear 109 is connected to the third motor 1011.

In some embodiments of the present invention, the principle of the second steering mechanism 10 and the third steering mechanism 106 is the same, and taking the second steering mechanism 10 as an example, in order to rotate the second dual-system motor 32, the third gear 102 is disposed on the second rotating member 101, and then the fourth gear 103 is driven by the second motor 105, and the fourth gear 103 is meshed with the third gear 102 to rotate the second link, so that the second dual-system motor 32 is rotated to a specified position.

Example 8

Referring to fig. 1 and fig. 2, the present embodiment is provided based on the technical solution of embodiment 5, and further includes a plurality of second rotors 4 disposed on the aircraft body 1, where the plurality of second rotors 4 are uniformly disposed around the circumference of the cockpit 2.

In some embodiments of the present invention, since the turbine engine is a fuel-powered engine, there is a risk of explosion, in order to avoid that the first rotor 311 is damaged when the turbine engine explodes, which results in the aircraft being unable to operate. The second rotor wings 4 with the number consistent with that of the turbine engines are arranged to serve as standby or auxiliary flight systems, so that the safety of the aircraft is further improved by adopting three sets of flight systems.

Example 9

Referring to fig. 2, the present embodiment is proposed based on the technical solution of embodiment 1, and further includes a retractable tail 5 disposed on the aircraft body 1.

In some embodiments of the present invention, the retractable tail 5 is provided to adjust the direction of the aircraft by using the tail, although the position and posture of the aircraft can be adjusted by using the dual-system engine during cruising, because the dual-system engine has a heavy weight and consumes a large amount of energy when adjusted, which affects the cruising ability of the aircraft. Meanwhile, the empennage adopts a telescopic form, and the empennage aims to reduce the interference on the visual field of a pilot and improve the safety when the aircraft is leaned or vertically lifted and landed.

In some embodiments of the utility model, a plurality of airbags can be added at the bottom of the aircraft, and when the aircraft needs to land on water or emergently land on water, the airbags can be opened to enable the aircraft to suspend on the water, so that the safety is further improved.

In some embodiments of the present invention, a parachute may be further disposed on the cockpit 2, so as to protect the aircraft when the aircraft is forced to land, and prevent the aircraft from crashing due to an excessively fast descent speed of the aircraft, thereby further improving safety.

In summary, the embodiment of the present invention provides an aircraft, which includes an aircraft body 1, an engine unit 3, and a cockpit 2 disposed on the aircraft body 1, where the engine unit 3 includes a plurality of dual-system engines, the dual-system engines include a driving engine 74 disposed in the aircraft body 1, a turbine engine disposed on the aircraft body 1, a rotating mechanism 6 sleeved on the turbine engine, a first transmission mechanism 7 connected with the rotating mechanism 6, and a first rotor 311 connected with the rotating mechanism, and the driving engine 74 is connected with the first transmission mechanism 7.

For the prior art vertical take-off and landing aircraft, the occupied space and high cost are important factors for limiting the development of the aircraft, and the most important factor for really influencing the vertical take-off and landing aircraft is also a safety problem. As for the helicopters in the prior art, only one set of system for flying is basically provided, most helicopters adopt control rotors for taking off and landing and cruising, and a small part of helicopters use an aviation turbine engine for lifting. The disadvantage is that, in case of a problem with this single flight system, the aircraft cannot fly normally, and therefore can only fall. Therefore, in order to solve the above problems, the present embodiment employs the engine set 3 with dual system engines, so that the aircraft has multiple sets of flight systems, even if one of the flight systems has a problem, the pilot can immediately switch another flight system, so that the aircraft still has flight capability, thereby avoiding the occurrence of the situation of machine damage and human death. In a specific embodiment, the first rotor 311 is provided on an aircraft turbine engine, and in order to prevent the rotor from interfering with an air intake port of the turbine engine, the first rotor 311 is provided on a side wall of the turbine engine, and the drive engine 74 is used to drive the transmission mechanism so that the first rotor 311 can rotate, and the transmission mechanism drives the setting rotating mechanism 6 to rotate, so that the first rotor 311 can rotate on an outer wall of the turbine engine. The combined type aircraft has the beneficial effects that the combination of the rotor wing and the turbine engine ensures that the aircraft occupies smaller space and has smaller resistance when flying, and the two flying systems of the rotor wing and the turbine engine are matched for use, so that the energy of the aircraft can be greatly saved; meanwhile, the flight system is switched under emergency conditions, so that the safety of airborne personnel is ensured, and the safety is improved.

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

Claims (10)

1. The utility model provides an aircraft, its characterized in that, including aircraft main part, engine block and set up in cockpit in the aircraft main part, engine block includes a plurality of dual system engines, dual system engine including set up in driving engine in the aircraft main part, set up in turbine engine, cover in the aircraft main part are located slewing mechanism on the turbine engine, with arbitrary slewing mechanism that connects and with the first rotor that slewing mechanism connects, driving engine with first transmission connects.

2. The aircraft of claim 1, wherein the rotating mechanism comprises a driving gear, a bearing and an internal gear, the bearing is sleeved on the turbine engine, the internal gear is sleeved on the bearing, the internal gear is meshed with the driving gear, and the driving gear is connected with the first transmission mechanism.

3. The aircraft of claim 2, wherein the first transmission comprises a first bevel gear, a second bevel gear, a first transmission and a second transmission, the first bevel gear is connected with the drive gear through the first transmission, the first bevel gear is meshed with the second bevel gear, and the second bevel gear is connected with the drive engine through the second transmission.

4. The aircraft of claim 2 further comprising a second transmission mechanism, the second transmission mechanism comprising a drive motor, a worm gear and a worm engaged with the worm gear, the worm gear being connected to the first rotor, the worm being connected to the drive motor, the drive motor being disposed within the internal gear, the first rotor being articulated to the internal gear.

5. The aircraft of claim 1, further comprising a first steering mechanism, a second steering mechanism, a third steering mechanism, a first electric machine, a second electric machine, and a third electric machine mounted within the aircraft body, the plurality of dual-system engines being a first dual-system engine, a second dual-system engine, and a third dual-system engine, respectively; the first double-system engine is hinged with the aircraft body and is connected with the first motor through the first steering mechanism; the second dual-system engine and the third dual-system engine are respectively in rotary connection with the aircraft body; the second dual-system engine is connected with the second motor through the second steering mechanism; and the third dual-system engine is connected with the third motor through the third steering mechanism.

6. The aircraft of claim 5, wherein the first steering mechanism comprises a first rotating member coupled to the first dual system engine, a first gear coupled to the first rotating member, the first gear in mesh with the second gear, a second gear coupled to the third bevel gear via the first coupling, a third bevel gear in mesh with the fourth bevel gear, and a first coupling, the fourth bevel gear coupled to the first motor.

7. The aircraft of claim 5 wherein the second steering mechanism comprises a second rotating member, a third gear, a fourth gear and a second connecting member, one end of the second rotating member is connected to the second dual system engine, the other end of the second rotating member is connected to the third gear, the third gear is in mesh with the fourth gear, and the fourth gear is connected to the second motor.

8. The aircraft of claim 5 wherein the third steering mechanism includes a third rotating member, a fifth gear, a sixth gear, and a third connecting member, one end of the third rotating member being connected to the third dual-system engine, the other end of the third rotating member being connected to the fifth gear, the fifth gear being in mesh with the sixth gear, the sixth gear being connected to the third motor.

9. The aircraft of claim 1 further comprising a second plurality of rotors disposed on the aircraft body, the second plurality of rotors being disposed evenly around the cockpit circumference.

10. The aircraft of claim 1, further comprising a retractable tail disposed on the aircraft body.

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