CN120171225A - A flying car for both air and ground use - Google Patents
A flying car for both air and ground use Download PDFInfo
- Publication number
- CN120171225A CN120171225A CN202510622182.4A CN202510622182A CN120171225A CN 120171225 A CN120171225 A CN 120171225A CN 202510622182 A CN202510622182 A CN 202510622182A CN 120171225 A CN120171225 A CN 120171225A
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- China
- Prior art keywords
- rotor
- automobile body
- rotor wing
- aerocar
- ground
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60F—VEHICLES FOR USE BOTH ON RAIL AND ON ROAD; AMPHIBIOUS OR LIKE VEHICLES; CONVERTIBLE VEHICLES
- B60F5/00—Other convertible vehicles, i.e. vehicles capable of travelling in or on different media
- B60F5/02—Other convertible vehicles, i.e. vehicles capable of travelling in or on different media convertible into aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/061—Frames
- B64C1/063—Folding or collapsing to reduce overall dimensions, e.g. foldable tail booms
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/52—Tilting of rotor bodily relative to fuselage
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Transportation (AREA)
- Motorcycle And Bicycle Frame (AREA)
Abstract
本发明提供了一种空地两用的飞行汽车，包括汽车机身、前旋翼支臂、后旋翼支臂、多旋翼机构、倾转螺旋桨机构和旋翼折叠机构，所述汽车机身的前端连接有两个前旋翼支臂，所述汽车机身的顶端连接有两个后旋翼支臂，所述前旋翼支臂和后旋翼支臂分别通过旋翼折叠机构与汽车机身连接，所述前旋翼支臂和后旋翼支臂的翼稍处分别连接有倾转螺旋桨机构，每个所述倾转螺旋桨机构上分别连接有多旋翼机构。本发明的飞行汽车在在飞行模式下能够展开旋翼机构，保证良好的气动性能和飞行稳定性，在地面行驶模式下能够折叠旋翼机构，优化空气动力学特性，减少旋翼机构对行驶稳定性造成的影响。
The present invention provides a flying car for both air and ground use, comprising a car body, a front rotor arm, a rear rotor arm, a multi-rotor mechanism, a tilt-propeller mechanism and a rotor folding mechanism, wherein the front end of the car body is connected to two front rotor arms, the top of the car body is connected to two rear rotor arms, the front rotor arms and the rear rotor arms are respectively connected to the car body through the rotor folding mechanism, the wing tips of the front rotor arms and the rear rotor arms are respectively connected to the tilt-propeller mechanism, and each of the tilt-propeller mechanisms is respectively connected to a multi-rotor mechanism. The flying car of the present invention can unfold the rotor mechanism in the flight mode to ensure good aerodynamic performance and flight stability, and can fold the rotor mechanism in the ground driving mode to optimize the aerodynamic characteristics and reduce the influence of the rotor mechanism on driving stability.
Description
Technical Field
The invention belongs to the technical field of aerocars, and particularly relates to an air-ground dual-purpose aerocar.
Background
The aerocar is an aircraft prototype scheme with ground traveling and air flying functions, and meets the requirements of short-distance quick travel and traffic jam relief. The existing aerocar is improved in structure on the basis of the original light aircraft or rotor aircraft, and the aerofoil, the rotor or a rotor system and the car running system are additionally arranged, so that the aerocar can run like a car in a ground environment and can be switched to a flight mode to realize air flight.
The prior art scheme still has the main defects that most of existing aerobuses always use the pneumatic layout of the traditional fixed wing or multi-rotor aircraft, and high-efficiency lifting force and high maneuverability are difficult to realize on the same engine body at the same time. The fixed-wing scheme has relatively high cruising efficiency, but is limited in the aspects of vertical take-off and landing, low-speed hovering and maneuvering in a narrow space, and the multi-rotor scheme is suitable for vertical take-off and landing and low-speed flying, but has poor aerodynamic efficiency and cruising performance in a high-speed cruising stage.
In addition, most of existing aerobuses are based on metal materials or traditional composite material assembled structures, and the overall light weight degree and the structural strength are difficult to balance. In order to achieve both ground running and air flight, the machine body often needs additional landing gear, foldable wings or telescopic rotor mechanisms, which results in complex structure and high weight. Meanwhile, the existing aerocar often lacks sufficient redundancy and fault tolerance capability due to motor power limitation in a power scheme. The traditional power system has larger noise and is difficult to meet the low-noise flight requirement in urban environment. Meanwhile, when the city flies in low altitude, challenges such as complex terrain, dense buildings, limited flying airspace and the like need to be met. Most existing aerobuses can only realize stable basic attitude or manual operation, lack multiple redundancy fault-tolerant flight control technology and intelligent path planning and stability-increasing control capability, and are difficult to ensure real-time autonomous decision and safety in the flight process.
And the navigation and detection capability of the prior art in complex urban environments or multi-obstacle scenes is insufficient. Once a high-rise group, a tunnel, a bridge and the like are blocked, or meteorological interference and multi-signal source interference are encountered, stable high-precision positioning and reliable environment perception are difficult to realize. The lack of a multi-mode perception fusion navigation system greatly limits the flight safety and autonomy of the aerocar. Finally, the existing on-board electronic equipment of the aerocar still uses the simple splicing of the traditional avionic system or the automotive electronic system, the data exchange and the function coordination among the systems are not perfect enough, and a highly integrated comprehensive avionic platform is lacked.
Based on the above, a space-ground dual-purpose aerocar is provided.
Disclosure of Invention
The technical problem to be solved by the invention is to provide a space-ground dual-purpose aerocar for solving the problems in the background art.
In order to solve the technical problems, the invention adopts the technical scheme that the air-ground dual-purpose aerocar comprises a car body, a front rotor wing support arm, a rear rotor wing support arm, a multi-rotor wing mechanism, a tilting propeller mechanism and a rotor wing folding mechanism;
Wherein, the front end of the automobile body is provided with a cockpit;
the front end of the automobile body is connected with two front rotor wing arms, the top end of the automobile body is connected with two rear rotor wing arms, the front rotor wing arms and the rear rotor wing arms are respectively connected with the automobile body through rotor wing folding mechanisms, the tip ends of the front rotor wing arms and the rear rotor wing arms are respectively connected with tilting propeller mechanisms, and each tilting propeller mechanism is respectively connected with a multi-rotor wing mechanism;
the bottom side of the automobile body is provided with a bottom frame, and four wheels are rotatably connected to the bottom frame.
As a further illustration of the present invention, there is also included a power system and avionics system disposed on the vehicle body;
the power system adopts distributed electric propulsion power and is provided with an intelligent energy management system and a multi-redundancy motor;
The avionic system consists of a flight control technology, an intelligent path planning and stability augmentation control algorithm, and ensures flight safety.
As a further illustration of the present invention, the tilt propeller mechanism may enable adjustment of vertical take-off and landing, hover and high speed cruise functions.
As a further explanation of the invention, the tilting propeller mechanism provides the whole lifting force of the vertical take-off and landing stage and the hovering stage for the automobile body when the inclination angle is 0 DEG, and provides the whole pushing force of the cruising stage for the automobile body when the inclination angle of the tilting propeller mechanism is 90 deg.
As a further illustration of the invention, the rotor folding mechanism is mounted to a frame structure of an automobile fuselage.
As a further illustration of the present invention, when the vehicle body is switched from ground travel mode to flight mode, the rotor folding mechanism turns forward the front rotor arm 125 ° and deploys from the front side of the vehicle body 1, and the rotor folding mechanism turns forward the rear rotor arm 45 ° and deploys from the rear of the vehicle body 1;
when the automobile body is switched to a ground running mode from a flying mode, the rotor folding mechanism enables the front rotor support arm to horizontally rotate backwards by 125 degrees and is stored in the front side part of the automobile body, and the rotor folding mechanism enables the rear rotor support arm to horizontally rotate backwards by 45 degrees and is stored in the tail part of the automobile body.
As a further illustration of the invention, the cockpit employs a single row, double seat arrangement for accommodating the driver and passengers and integrates within the cockpit a steering system and a cabin interaction system, which are also in signal connection with the power system and avionics system, respectively.
Compared with the prior art, the invention has the following advantages:
The invention enables the aerocar to fold the rotor wing in a ground running mode, optimizes aerodynamic characteristics and improves running stability. Compared with the traditional aerocar in ground mode, the wind resistance coefficient after storage is reduced by 20% -25% due to the fact that wind resistance is increased and stability is reduced due to the fact that the rotor wing is unfolded, and the influence of a rotor wing mechanism on running stability can be reduced.
The full-mechanism type automobile lift system adopts the streamline composite lift body, and the fixed wings and the rotor wings are matched, so that the full-mechanism lift-drag ratio of the automobile body can reach 10-12 in a high-speed cruising mode, the cruising efficiency can be improved, the energy consumption can be reduced by 20% -30%, and the flying endurance can be improved.
In the high-speed cruising mode, the automobile body, the front rotor wing support arm and the rear rotor wing support arm can provide all lifting force, the rotor wing mechanism only needs to meet the thrust requirement and the gesture control, so that the power consumption in the flight mode is reduced, and the tilting propeller mechanism can adjust the dip angle according to different flight modes, so that the vertical take-off and landing, hovering and switching of the high-speed cruising modes are realized.
Drawings
FIG. 1 is a schematic view of the overall flight mode of the present invention;
FIG. 2 is a top view of the overall flight mode of the present invention;
FIG. 3 is a front view of the overall flight mode of the present invention;
FIG. 4 is a side view of the overall ground travel pattern of the present invention;
fig. 5 is a top view of the overall ground travel mode of the present invention.
Reference numerals illustrate:
1-automobile body, 2-cockpit, 3-bottom frame, 4-front rotor arm, 5-rear rotor arm, 6-multi-rotor mechanism, 7-tilting propeller mechanism, 8-rotor folding mechanism, 9-power system and 10-avionics system.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. 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.
As shown in fig. 1-5, the invention provides a technical scheme that an air-ground dual-purpose aerocar comprises a car body 1, a front rotor wing support arm 4, a rear rotor wing support arm 5, a multi-rotor wing mechanism 6, a tilting propeller mechanism 7 and a rotor wing folding mechanism 8;
the bottom side of the automobile body 1 is provided with a bottom frame 3, four wheels are rotatably connected to the bottom frame 3, the bottom frame 3 is a landing gear in a flight mode, and when the ground running mode is switched, the wheels are used as vehicle running wheels.
The front end of the automobile body 1 is provided with a cockpit 2, the cockpit 2 adopts a single-row double-seat layout and is used for accommodating a driver and passengers, a control system and a cabin interaction system are integrated in the cockpit 2, and the control system and the cabin interaction system are also respectively connected with a power system 9 and an avionics system 10 through signals;
the control system can be switched between a flight mode and a ground running mode to provide flight and driving control;
The cabin interaction system is used for displaying the key parameters of the flying automobile, including flight state information such as ground running speed, motor power output, course angle, pitch angle, rotor rotation speed and the like.
The front end of the automobile body 1 is connected with two front rotor arms 4, the top end of the automobile body 1 is connected with two rear rotor arms 5, the front rotor arms 4 and the rear rotor arms 5 are respectively connected with the automobile body 1 through rotor folding mechanisms 8, the tips of the front rotor arms 4 and the rear rotor arms 5 are respectively connected with tilting screw mechanisms 7, each tilting screw mechanism 7 is respectively connected with a plurality of rotor mechanisms 6, the automobile body 1 adopts a streamline composite lift force body aerodynamic profile design and is integrated with the front rotor arms 4 and the rear rotor arms 5, so that a flying automobile has a high lift-drag ratio in a flying mode and maintains a streamline layout in a ground running mode to optimize aerodynamic performance.
The rotor folding mechanism 8 is mounted on the frame structure of the automobile body 1, when the automobile body 1 is switched from a ground running mode to a flying mode, the rotor folding mechanism 8 enables the front rotor support arm 4 to horizontally rotate forward by 125 degrees and unfold from the front side part of the automobile body 1, and the rotor folding mechanism 8 enables the rear rotor support arm 5 to horizontally rotate forward by 45 degrees and unfold from the tail part of the automobile body 1, as shown in fig. 1, 2 and 3;
When the automobile body 1 is switched from the flying mode to the ground running mode, the rotor folding mechanism 8 makes the front rotor support arm 4 turn back by 125 degrees, and the rear rotor support arm 5 turn back by 45 degrees and is accommodated at the tail of the automobile body 1 by the rotor folding mechanism 8. As shown in fig. 4 and 5.
The other ends of the front rotor wing support arm 4 and the rear rotor wing support arm 5 are respectively connected with a tilting propeller mechanism 7, and each tilting propeller mechanism 7 is respectively connected with a multi-rotor wing mechanism 6;
The tilting propeller mechanism 7 can realize the adjustment of vertical take-off and landing, hovering and high-speed cruising functions.
The tilting propeller mechanism 7 provides all lifting force for the automobile body 1 in the vertical take-off and landing stage and in the hovering stage when the inclination angle is 0 degrees, and provides all thrust for the automobile body 1 in the cruising stage when the inclination angle of the tilting propeller mechanism 7 is 90 degrees.
The system also comprises a power system 9 and an avionics system 10 which are arranged on the automobile body 1;
The power system 9 adopts distributed electric propulsion power, is provided with an intelligent energy management system and a multi-redundancy motor, is driven by adopting the multi-redundancy high-power-weight-ratio motor, combines hydrogen energy power, realizes high-efficiency energy conversion, improves the cruising ability, reduces carbon emission, simultaneously optimizes power distribution, enhances the redundancy of the motor and improves the safety.
The avionic system 10 is composed of a flight control technology, an intelligent path planning and stability augmentation control algorithm, ensures flight safety, adopts the intelligent stability augmentation control algorithm, improves flight stability and safety, and supports dual modes of automatic driving and manual control. The system has multiple redundancy designs, even if a single rotor wing or a power unit fails, the system can still keep safe flight and automatically adjust, and high-precision positioning and autonomous flight are realized by combining a GPS, a laser radar and a vision sensor, so that the navigation capability under a complex environment is improved. The device has an autonomous obstacle avoidance function, and is suitable for urban low-altitude traffic and complex meteorological environments.
The automobile body 1 in the embodiment adopts a streamline pneumatic appearance design, so that the automobile body can generate additional lifting force in a high-speed cruising mode, and the cruising efficiency is improved. Compared with the situation that the lift-drag ratio of the traditional multi-rotor aircraft is between 6 and 8, the lift-drag ratio of the whole aircraft after optimization can reach 10 to 12, the energy consumption can be reduced by 20 to 30 percent, and the flight endurance is improved.
In the high speed cruise mode, the vehicle body 1 and the front and rear rotor arms 4, 5 can provide full lift, and the rotor system is used only for thrust demand and attitude control, thereby reducing flying power consumption.
In addition, the tilting propeller mechanism 7 can adjust the inclination angle according to different flight modes, and can realize the switching of vertical take-off and landing, hovering and high-speed cruising modes.
The rotor folding mechanism 8 of the invention enables a flying automobile to fold a rotor in a ground running mode, optimizes aerodynamic characteristics and improves running stability. Compared with the traditional aerocar in ground mode, the wind resistance coefficient after storage is reduced by 20% -25% due to the problems of increased wind resistance and reduced stability caused by the unfolding of the rotor wing, so that the stability and cruising ability of the ground during running are improved.
The hydrogen energy power in the power system 9 can increase the air endurance mileage to 200-300km, reduce 99% of carbon emission, and realize zero pollution and zero carbon emission.
In the aspect of safety, the invention adopts the multiple redundant motors with high power-weight ratio, so that safe flight can be maintained even if part of power units fail. Compared with the problem that the conventional single power mode of the flying automobile cannot maintain the flying after the power system fails, the multi-redundancy design can still maintain stable flying under the condition of motor failure. By combining intelligent fault detection and a flight mode adjustment algorithm, when the system detects power abnormality, the system can automatically switch to a safety mode, plan an emergency landing path and improve flight safety
It is noted that relational terms such as first and second, and the like are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Moreover, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.
Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made therein without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (7)
1. The aerocar for air and ground use is characterized by comprising an automobile body (1), a front rotor wing support arm (4), a rear rotor wing support arm (5), a multi-rotor wing mechanism (6), a tilting propeller mechanism (7) and a rotor wing folding mechanism (8);
wherein, the front end of the automobile body (1) is provided with a cockpit (2);
The front end of the automobile body (1) is connected with two front rotor wing arms (4), the top end of the automobile body (1) is connected with two rear rotor wing arms (5), the front rotor wing arms (4) and the rear rotor wing arms (5) are respectively connected with the automobile body (1) through rotor wing folding mechanisms (8), the tip parts of the front rotor wing arms (4) and the rear rotor wing arms (5) are respectively connected with tilting propeller mechanisms (7), and each tilting propeller mechanism (7) is respectively connected with a multi-rotor wing mechanism (6);
The bottom side of the automobile body (1) is provided with a bottom frame (3), and four wheels are rotatably connected to the bottom frame (3).
2. A space-ground dual-purpose aerocar as claimed in claim 1, further comprising a power system (9) and an avionics system (10) provided on the car body (1);
wherein the power system (9) adopts distributed electric propulsion power and is provided with an intelligent energy management system and a multi-redundancy motor;
the avionics system (10) is composed of a flight control technology, an intelligent path planning and stability augmentation control algorithm, and flight safety is ensured.
3. A space-ground dual-purpose aerocar as claimed in claim 1, wherein said tilting propeller mechanism (7) enables adjustment of vertical take-off and landing, hovering and high-speed cruising functions.
4. A space-ground dual-purpose aerocar according to claim 3, wherein the tilting propeller mechanism (7) provides the whole lift force of the vertical take-off and landing stages and the hovering stage for the car body (1) when the tilt angle is 0 °, and the tilting propeller mechanism (7) provides the whole thrust force of the cruising stage for the car body (1) when the tilt angle is 90 °.
5. A space-ground dual-purpose aerocar as claimed in claim 1, wherein said rotor folding mechanism (8) is mounted on a frame structure of the car body (1).
6. A space-ground dual-purpose aerocar as claimed in claim 5, wherein when the car body (1) is switched from ground running mode to flying mode, the rotor folding mechanism (8) rotates the front rotor arm (4) forward by 125 ° and deploys from the front side of the car body (1), and the rotor folding mechanism (8) rotates the rear rotor arm (5) forward by 45 ° and deploys from the rear of the car body (1);
when the automobile body (1) is switched from a flight mode to a ground running mode, the rotor folding mechanism (8) enables the front rotor support arm (4) to horizontally rotate by 125 degrees backwards and is stored at the front side part of the automobile body (1), and the rotor folding mechanism (8) enables the rear rotor support arm (5) to horizontally rotate by 45 degrees backwards and is stored at the tail part of the automobile body (1).
7. An air-ground dual-purpose aerocar as claimed in claim 2, wherein the cockpit (2) adopts a single row double seat layout for accommodating a driver and passengers, and a manipulation system and a cabin interaction system are integrated in the cockpit (2), and the manipulation system and the cabin interaction system are also respectively connected with signals between the power system (9) and the avionics system (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202510622182.4A CN120171225A (en) | 2025-05-15 | 2025-05-15 | A flying car for both air and ground use |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202510622182.4A CN120171225A (en) | 2025-05-15 | 2025-05-15 | A flying car for both air and ground use |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN120171225A true CN120171225A (en) | 2025-06-20 |
Family
ID=96039490
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202510622182.4A Pending CN120171225A (en) | 2025-05-15 | 2025-05-15 | A flying car for both air and ground use |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN120171225A (en) |
-
2025
- 2025-05-15 CN CN202510622182.4A patent/CN120171225A/en active Pending
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