阅读说明：本技术 一种三维可变推进飞碟 (Three-dimensional variable propulsion flying saucer ) 是由 龚树勇 朱胜青 于 2019-10-01 设计创作，主要内容包括：一种三维可变推进飞碟,包括飞碟体、环形压气腔、流场改向分配阀、盘式稳定陀螺仪、侧向喷口、驾乘舱、风扇、进气口、柔性防撞圈；其特征在于,所述飞碟体内设置有环形压气腔、盘式稳定陀螺仪、驾乘舱,飞碟体上面设置有穹顶、外檐设置有柔性防撞圈；侧向喷口开设在柔性防撞圈上,侧向喷口与环形压气腔导通；侧向喷口内设置有气流控制阀,气流通过喷口的速度和压力可调；所述风扇设置在进气口内,进气口形状为喇叭形非对称圆管接口,进气口下口与涵道风扇进风口相连；本发明具有类似直升机的垂直起降及悬停功能,也能够在横向推力作用下,以固定翼飞机的高航速留空飞行。(A three-dimensional variable propulsion flying saucer comprises a flying saucer body, an annular compressed air cavity, a flow field redirection distribution valve, a disc type stable gyroscope, a lateral nozzle, a driving cabin, a fan, an air inlet and a flexible anti-collision ring; the flying saucer is characterized in that an annular air pressing cavity, a disc type stable gyroscope and a driving cabin are arranged in the flying saucer body, a dome is arranged on the flying saucer body, and a flexible anti-collision ring is arranged on an outer brim; the lateral nozzle is arranged on the flexible anti-collision ring and communicated with the annular air compression cavity; an airflow control valve is arranged in the lateral nozzle, and the speed and the pressure of airflow passing through the nozzle are adjustable; the fan is arranged in the air inlet, the shape of the air inlet is a horn-shaped asymmetric circular tube connector, and the lower opening of the air inlet is connected with the air inlet of the ducted fan; the invention has the vertical take-off and landing and hovering functions similar to a helicopter, and can fly in the air at high navigational speed of a fixed wing aircraft under the action of transverse thrust.)

1. A three-dimensional variable propulsion flying saucer comprises a flying saucer body (3), an annular compressed air cavity (4) integrated with a fan flow field in series connection, a flow field redirection distribution valve (5), a disc-type stable gyroscope (6), a lateral nozzle (7), a driving cabin (8), a fan (9), an air inlet (10) and a flexible anti-collision ring (11); the flying saucer is characterized in that an annular air pressing cavity (4) integrating a serial fan flow field, a disc type stable gyroscope (6) and a driving cabin (8) are arranged in the flying saucer body (3), a dome (31) is arranged on the flying saucer body (3), and a flexible anti-collision ring (11) is arranged on an outer brim; the lateral nozzle (7) is arranged on the flexible anti-collision ring (11), and the lateral nozzle (7) is communicated with the annular compressed air cavity (4); an airflow control valve is arranged in the lateral nozzle (7), and the speed and the pressure of airflow passing through the nozzle (7) are adjustable; the fan (9) is arranged in the air inlet (10), and the fan (9) can be controlled to rotate in the positive direction or the negative direction to provide upward or downward power for the flying saucer; the shape of the air inlet (10) is a trumpet-shaped asymmetric circular tube connector, and the lower opening of the air inlet (10) is connected with an air inlet (91) of the ducted fan; when the fan (9) rotates, air is compressed into the flow field redirection distribution valve (5) to provide motive power for flying of the flying saucer; a flow field redirection distribution valve (5) is arranged below the fan (9), a lower spray hole (51) is arranged below the flow field redirection distribution valve (5), and a side spray hole (52) is arranged on the side surface of the flow field redirection distribution valve (5); the flow field redirection distribution valve (5) can rotate by taking the axis of the fan (9) as the center of a circle, the direction of the flow field redirection distribution valve (5) is controlled and rotated, and the flow of air flow in the lower spray hole (51) and the side spray holes (52) can be controlled and adjusted, so that the flying direction of the flying saucer is changed; the driving cabin (8) can rotate around the axis of the flying saucer body (3) in the flying saucer body (3) to provide a wide view of 360 degrees for a driver; the disc type stable gyroscope (6) consists of a coaxial reverse motor and a rotating disc and can provide additional attitude balancing moment for the flying saucer.

2. A three-dimensional variable propulsion flying saucer according to claim 1, characterized in that said fans (9) are arranged in at least 2 groups.

3. A three-dimensional variable propulsion flying saucer according to claim 1, characterized in that the number of flow field redirecting distributing valves (5) is the same as the number of fans (9).

4. A three-dimensional variable propulsion flying saucer according to claim 1, characterized in that said dome (31) is made of a transparent material to provide wide visual field for pilots and passengers, and the dome (31) is also used as a door for pilots and passengers.

5. A three-dimensional variable propulsion flying saucer according to claim 1, characterized in that said cockpit (8) provides the space for pilot and passenger accommodation, and in the space, there are driving control equipment and seats and other safety facilities.

6. A three-dimensional variable propelling flying saucer according to claim 1, characterized in that said fan (9) is a coaxial contra-rotating dual-rotor, and the power supply of fan (9) is provided by lithium battery pack arranged in flying saucer body (3).

Technical Field

The invention relates to an aircraft, in particular to a three-dimensional variable propelling flying saucer.

Background

At present, the mainstream aircrafts are of two types, namely helicopters and fixed-wing aircrafts. The helicopter is convenient to take off and land, but because the horizontal flight is inclined by the paddle disc, the horizontal component force generated by the inclination of the downward-flowing airflow obtains the forward power, so that the horizontal flight speed is slow, generally about 200-350 km/h; the fixed wing aircraft can realize the lift-off flight by the aerodynamic lift force obtained when the aircraft runs along the runway of the airport under the action of the horizontal thrust provided by the engine. Both helicopters and fixed wing aircraft are maintained in flight by means of simple unidirectional propulsion power systems.

The aircraft can simultaneously provide vertical lift force (not aerodynamic lift force for the aircraft to advance) and forward propelling force respectively by the power system of the aircraft, and only the X2 helicopter of western science is available at present. It can not only vertically lift off, but also horizontally fly at high speed. The sparrow type airplane and the osprey V22 helicopter belong to a one-way thrust aircraft with an adjustable thrust vector direction.

Even the SiCox 2 helicopter which is named black science and technology, only adopts the bidirectional propulsion technology. Meanwhile, because of the aerodynamic shape limitation of the helicopter, the flying speed is far lower than that of a fixed-wing aircraft.

As for the document disclosed in chinese patent utility model CN201310683100, in "basic structure of flying saucer and method for manufacturing basic flying principle", it is impossible to construct the instant multi-directional vector propulsion idea of flying saucer by using multi-nozzle rocket engine (bundled multi-directional rocket integrated engine). The practical meaning of the ultra-delayed reverse propulsion is staged unidirectional propulsion. The related multidirectional propulsion modes in other published or granted patents do not have the safety of a separated power unit and have the full-power effectiveness of concentrated integrated output of a flow field; but also does not have the advancement of the normal-temperature instant (continuous) three-dimensional propulsion technology.

The overall performance of an aircraft, in addition to the flight control system, depends on two main factors, the performance of the thrust system and the seaworthiness of the overall aerodynamic profile of the aircraft.

The propulsion technology of the aircraft is limited to single-vector adjustable direction or double-vector propulsion, so that the exertion of the excellent performance of the aircraft is fundamentally limited; in the design of the aerodynamic performance of the profile, the overall mass distribution and the aerodynamic profile construction of almost all the aircrafts at present are not unreasonable. The breadth and anisotropy of particle distribution severely impact flight safety and the affinity of public channels. The unreasonable construction of the aerodynamic shape causes the aircraft to have low economic performance and single flight attitude, and can not meet the new requirements of human society on the performance of the aircraft.

Disclosure of Invention

Aiming at the defects in the prior art, the invention provides a three-dimensional variable propelling flying saucer.

The technical scheme adopted by the invention is as follows: a three-dimensional variable propulsion flying saucer comprises a flying saucer body, an annular compressed air cavity, a flow field redirection distribution valve, a disc type stable gyroscope, a lateral nozzle, a driving cabin, a fan, an air inlet and a flexible anti-collision ring; the flying saucer is characterized in that an annular air pressing cavity, a disc type stable gyroscope and a driving cabin are arranged in the flying saucer body, a dome is arranged on the flying saucer body, and a flexible anti-collision ring is arranged on an outer brim; the lateral nozzle is arranged on the flexible anti-collision ring and communicated with the annular air compression cavity; an airflow control valve is arranged in the lateral nozzle, and the speed and the pressure of airflow passing through the nozzle are adjustable; the fan is arranged in the air inlet, the shape of the air inlet is a horn-shaped asymmetric circular tube connector, and the lower opening of the air inlet is connected with the air inlet of the ducted fan; when the fan rotates, air is compressed into the flow field redirection distribution valve to provide motive power for flying of the flying saucer; the fan can be controlled to rotate forwards or reversely to provide upward or downward power for the flying saucer; a flow field redirection distribution valve is arranged below the fan, a lower spray hole is arranged below the flow field redirection distribution valve, and a side spray hole is arranged on the side surface of the flow field redirection distribution valve; the flow field redirection distribution valve can rotate by taking the axis of the fan as the center of a circle, the direction of the flow field redirection distribution valve is controlled and rotated, and the ejection flow of air flow in the lower jet hole and the side jet hole can be controlled and adjusted so as to change the flying direction of the flying saucer; the driving cabin can rotate around the axis of the flying saucer body in the flying saucer body, and a 360-degree open view is provided for a driver; the disc type stable gyroscope consists of a coaxial reverse motor and a rotating disc and can provide additional attitude balancing moment for the flying disc.

The fans are at least provided with 2 groups; the number of the flow field redirection distribution valves is consistent with the number of the fans.

The dome is made of a fully transparent material, so that a wide view field can be provided for pilots and passengers, and the dome is also used as an entrance and an exit of the pilots and the passengers; the driving cabin provides a riding space for pilots and passengers, and driving control equipment, seats and other safety facilities are arranged in the riding space.

The fan adopts coaxial reverse double-rotor wings, and the power supply of the fan is provided by a lithium battery pack arranged in the flying saucer body.

By adopting the technical scheme of the invention, the invention has the following beneficial effects:

1. the invention has the vertical take-off and landing and hovering functions similar to a helicopter, and can fly in the air at high navigational speed of a fixed wing aircraft under the action of transverse thrust. The invention originally utilizes the special pneumatic appearance of the flying saucer and the three-dimensional propulsion technology to realize the perfect unification of the functions of the airplane and the helicopter. The flying saucer has the air brake function, can be quickly stopped during high-speed flight, and has various special performances such as reverse flight, side flight, rolling and the like. Due to the physical characteristics and the mass point distribution characteristics of the flying saucer, the flying saucer has extremely good controllability, excellent safety and feasibility of cluster flight;

2. when a plurality of electric fan power units operate, the jet air flow is controlled by the bypass flow field redirection distribution valve and flow field reforming is carried out by the shared annular air compression cavity, so that the lifting thrust and the transverse thrust in any direction can be simultaneously brought to the flying saucer, and the technical purpose of three-dimensional propulsion is realized; because the annular air compression cavity is shared, all ducted fan airflows are subjected to concentrated flow field reforming, and the power integration and full-power operation of the separated multi-ducted power unit can be realized under any working condition. The result of this arrangement is a safe separation of the power units and a centralized use of propulsion capability. So that the navigation and safety of the flying saucer cannot be endangered even if a power unit of a certain duct fails;

3. when the fan is accelerated and descended, the downward thrust can be obtained by changing the rotating direction of the propeller of the ducted fan.

Drawings

FIG. 1 is a perspective view (side plan view) of the present invention;

FIG. 2 is a perspective view (side elevation) of the present invention;

FIG. 3 is a cross-sectional view of the present invention;

FIG. 4 is a schematic cross-sectional structural view of the present invention;

in the figure: the device comprises a flying saucer body-3, an annular compressed air cavity-4, a flow field redirection distribution valve-5, a lower spray hole-51, a side spray hole-52, a disc type stable gyroscope-6, a side spray nozzle-7, a driving cabin-8, a fan-9, a fan air inlet-91, an air inlet-10 and a flexible anti-collision ring-11.

Detailed Description

The invention is further illustrated by the following figures and examples: as shown in fig. 1 to 4, a three-dimensional variable propulsion flying saucer comprises a flying saucer body 3, an annular compressed air cavity 4, a flow field redirection distribution valve 5, a disc-type stable gyroscope 6, a lateral nozzle 7, a driving cabin 8, a fan 9, an air inlet 10 and a flexible anti-collision ring 11; the flying saucer is characterized in that an annular compressed air cavity 4, a disc type stable gyroscope 6 and a driving cabin 8 are arranged in the flying saucer body 3, a dome 31 is arranged on the flying saucer body 3, and a flexible anti-collision ring 11 is arranged on the outer brim; the lateral nozzle 7 is arranged on the flexible anti-collision ring 11, and the lateral nozzle 7 is communicated with the annular compressed air cavity 4; an airflow control valve is arranged in the lateral nozzle 7, and the speed and the pressure of airflow passing through the nozzle 7 are adjustable; the fan 9 is arranged in the air inlet 10, the air inlet 10 is in a horn-shaped asymmetric circular tube interface, and the lower opening of the air inlet 10 is connected with the ducted fan air inlet 91; when the fan 9 rotates, air is compressed into the flow field redirection distribution valve 5 to provide motive power for flying of the flying saucer; the fan 9 can be controlled to rotate in the positive direction or the negative direction to provide upward or downward power for the flying saucer; a flow field redirection distribution valve 5 is arranged below the fan 9, a lower spray hole 51 is arranged below the flow field redirection distribution valve 5, and a side spray hole 52 is arranged on the side surface of the flow field redirection distribution valve 5; the flow field redirection distribution valve 5 can rotate by taking the axis of the fan 9 as the center of a circle, and the direction of the flow field redirection distribution valve 5 is controlled and rotated, so that the ejection of the air flow in the lower ejection hole 51 and the side ejection hole 52 can be controlled and adjusted

Flow rate to change the flight direction of the flying saucer; the driving cabin 8 can rotate around the axis of the flying saucer body 3 in the flying saucer body 3, and provides a 360-degree wide view for a driver; the disc type stable gyroscope 6 consists of a coaxial reverse motor and a rotating disc and can provide additional attitude balancing moment for the flying saucer.

The fans 9 in the present embodiment are provided in 8 groups; the flow field redirection distribution valves 5 and the fans 9 are consistent in number.

The dome 31 is made of a fully transparent material, so that a wide view field can be provided for pilots and passengers, and the dome 31 is also used as an entrance and an exit of the pilots and the passengers; the cabin 8 provides a space for the pilot and passengers, and a space is provided with a driving control device, a seat and other safety facilities.

The fan 9 adopts coaxial reverse double rotors, and the power supply of the fan 9 is provided by a lithium battery pack arranged in the flying saucer body 3.

In this embodiment, the bottom valve is completely opened by the flow field redirection distribution valve, and after the ducted fans operate, the airflow is ejected downwards through the lower nozzle holes, and the reaction force of the ejected airflow is the vertical lift force obtained by the flying saucer, so that the flying saucer is vertically lifted.

The flying saucer of the embodiment enters a level flying state after being lifted off, a flow field redirection distribution valve is controlled, a bottom valve can be closed, and a side valve can be opened; the high-pressure airflow enters the annular pressure air cavity, one or more side nozzles in the annular pressure air cavity are opened, and the airflow sprayed by the side nozzles pushes the flying saucer to fly in the opposite direction of the airflow spray; the lateral spray opening at the rear part is closed, and the lateral spray opening at the front part is opened, so that the flying saucer can be braked suddenly; the spraying force of the lower spray hole below and the lateral spray nozzles at the front, the back, the left and the right is adjusted, and the rising height and the running direction of the flying saucer can be controlled.

The embodiment of the invention provides a method for realizing three-dimensional propulsion by using a cavity-sharing flow field reforming of a plurality of electric coaxial dual-rotor ducted fans of a flying saucer, and also establishes a three-dimensional propulsion flow field structure of a high-performance flying saucer. The flying saucer adopting the flow field reforming three-dimensional propulsion technology has excellent performance superior to the existing aircraft. The flying saucer has the functions of vertical take-off and landing and hovering similar to a helicopter, and can fly in the air at high navigational speed of a fixed wing aircraft under the action of transverse thrust. The invention originally utilizes the special pneumatic appearance of the flying saucer and the three-dimensional propulsion technology to realize the perfect unification of the functions of the airplane and the helicopter. The flying saucer has the air brake function, can be quickly stopped during high-speed flight, and has various special performances such as reverse flight, side flight, rolling and the like. Due to the physical characteristics and the particle distribution characteristics of the flying saucer, the flying saucer has excellent controllability, excellent safety and feasibility of cluster flight.

When the power unit of the ducted fan with the plurality of electric coaxial dual rotors operates, the jet air flow of the power unit is controlled by the ducted flow field redirection distribution valve and flow field reforming is carried out through the shared annular air compression cavity, so that lifting thrust and transverse thrust in any direction can be brought to a flying saucer at the same time, and the technical purpose of three-dimensional propulsion is achieved (when the power unit is accelerated and descended, lower thrust can be obtained by changing the rotation direction of a propeller of the ducted fan). Because the annular air compression cavity is shared, all ducted fan airflows are subjected to concentrated flow field reforming, and the power integration and full-power operation of the separated multi-ducted power unit can be realized under any working condition. The result of this arrangement is a safe separation of the power units and a centralized use of propulsion capability. So that the navigation and the safety of the flying saucer cannot be endangered even if a power unit of a certain duct fails.

The above examples of the present invention are illustrative of typical embodiments of the present invention and are not intended to limit the embodiments of the present invention. Obvious variations from the embodiments of the present invention are still within the scope of the claims of the present invention.