阅读说明：本技术 自然环境流体驱动的变构型双航态长航程海洋无人航行器 (Natural environment fluid driven variable configuration double-state long-range marine unmanned aircraft ) 是由 王树新 杨亚楠 刘冰汐 于 2020-06-08 设计创作，主要内容包括：本发明公开了一种自然环境流体驱动的变构型双航态长航程海洋无人航行器,具有水面航行模式、航行切换模式和水下航行模式,包括：风能收集单元,接收海洋风施加的气动力驱动航行器航行；浮力调节单元,在水下航行模式时调节航行器自身浮力,并结合航行器运动时迎面水流施加的水动力实现航行器的升沉运动与水平行进；翼龙骨；联动单元,在航行切换模式时完成风帆和翼龙骨的位姿变换；光伏发电单元,在水面航行模式时收集太阳能并为航行器耗电器件提供电能供应。本发明提供的该自然环境流体驱动的变构型双航态长航程海洋无人航行器,利用自然环境的海表风气流、水下水流、太阳光实现能量自给,在水面与水下两种航态下均具备长距离航行能力。(The invention discloses a variable configuration double-navigation state long-range marine unmanned vehicle driven by natural environment fluid, which has a water surface navigation mode, a navigation switching mode and an underwater navigation mode, and comprises the following components: the wind energy collecting unit is used for receiving aerodynamic force applied by ocean wind to drive the aircraft to sail; the buoyancy adjusting unit is used for adjusting the buoyancy of the aircraft in an underwater navigation mode and realizing the heave motion and horizontal travel of the aircraft by combining the hydrodynamic force applied by the water flow on the head-on when the aircraft moves; a wing keel; the linkage unit is used for finishing pose transformation of the sail and the pterosaur bone in the navigation switching mode; and the photovoltaic power generation unit is used for collecting solar energy and providing electric energy supply for electric consumption devices of the aircraft in a water surface navigation mode. The variable-configuration dual-navigation-state long-range marine unmanned vehicle driven by the natural environment fluid realizes self-supply of energy by using the surface wind flow, the underwater water flow and the sunlight of the natural environment, and has long-distance navigation capability in both water and underwater navigation states.)

1. A natural environment fluid driven, morphing configuration dual-attitude long range marine unmanned vehicle, the marine unmanned vehicle having a surface mode of travel, a flight switching mode, and an underwater mode of travel, the marine unmanned vehicle comprising:

the wind energy collecting unit is arranged in the middle of a hull of the aircraft and comprises a sail (1), wherein the sail (1) is in a vertical pose in a water surface navigation mode, is used for receiving aerodynamic force applied by ocean wind to drive the aircraft to navigate and is changed into a horizontal pose in an underwater navigation mode;

the buoyancy adjusting unit is arranged in the bow of the aircraft and used for adjusting the buoyancy of the aircraft in an underwater navigation mode and realizing the heave motion and horizontal travel of the aircraft by combining the hydrodynamic force exerted by the head-on water flow when the aircraft moves;

the wing fossil fragments (7), set up in navigation ware hull bottom, include:

the two symmetrical parts (7a, 7b) are in streamline cambered surface contour after being folded and are symmetrical relative to a vertical plane along the central axis of the aircraft, the two symmetrical parts (7a, 7b) are in horizontal position and posture in an underwater navigation mode, the heave motion and horizontal traveling of the aircraft are realized by combining the buoyancy adjusting unit, and the two symmetrical parts are changed into vertical position and posture in a water surface navigation mode;

ballast weights (7c) attached to the ends of the wing keels (7) for adjusting the aircraft center of gravity height in both surface mode and sail switch mode;

the linkage unit (10) is arranged inside a hull of the aircraft and used for finishing pose transformation of the sail (1) and the wing keel (7) in a sailing switching mode;

and the photovoltaic power generation unit is used for collecting solar energy and providing electric energy supply for electric consumption devices of the aircraft in a water surface navigation mode.

2. The marine unmanned vehicle of claim 1, wherein the wind energy collection unit comprises:

the sail (1) is a rigid hard sail with a circular arc-shaped section, a skin-skeleton structure is adopted, a skeleton comprises transverse ribs (1a), a frame (1b), a main mast (1c) and auxiliary supports (1d), and a skin (1e) covers the surface of the skeleton and is used for bearing and transmitting pneumatic load;

the wind direction sensor (4) is arranged at the top of the sail (1) and used for collecting wind direction information in real time in a water surface sailing mode;

the sail rotating mechanism (5) is arranged at the bottom of the sail (1) and comprises a rotating motor (5a) and a worm gear transmission (5b), so that the sail (1) can rotate around the main mast (1c) within a range of 360 degrees; the worm gear and worm speed changer (5b) has a self-locking function and is used for preventing the wind sail (1) from being forced to rotate under the action of external force; the sail (1) is adjusted to be at the optimal sail rotating angle position through the sail rotating mechanism (5) and the maximum driving force for advancing is obtained.

3. The marine unmanned vehicle of claim 2, wherein the photovoltaic power generation unit comprises:

the solar cell panel (2) is made of a flexible film material and is bent, fitted and installed according to the arc-shaped outer envelope of the sail (1);

the electric energy storage device is provided with a pressure-bearing shell, is arranged inside a ship body of the aircraft, and is used for receiving the output electric energy of the solar cell panel (2).

4. The marine unmanned vehicle according to claim 1, characterized in that the hull (6) of the vehicle is of the bilge dog-leg type, comprising:

the bow (6a) adopts a wave-penetrating configuration;

the middle ship body (6b) adopts a parallel middle body shape, and the outer envelope of the cross section of the middle ship body adopts an outward floating camber line;

the stern (6c) adopts a U-shaped cross section and extends to the tail end of the stern (6c) from the tail end of the middle ship body (6b) by a smooth curved surface, and the tail end of the stern (6c) adopts a square stern.

5. The marine unmanned vehicle according to claim 4, further having a heading control unit mounted to the stern (6c) of the vehicle, comprising a rudder (8) and a steering engine (9), wherein:

the steering engine (9) drives the rudder (8) to rotate in a range of-20 degrees to 20 degrees around a vertical axis based on the ship body (6);

the rudder (8) adopts a trapezoidal rudder shape with the section shape of NACA 0015;

the course control unit is used for generating a turning moment of the aircraft by utilizing the hydrodynamic lateral force exerted by water flow in the water surface navigation mode and the underwater navigation mode so as to regulate and control or keep the course of the aircraft.

6. The marine unmanned vehicle of claim 1, wherein the linkage unit (10) comprises a sail deployment mechanism (10a) mounted in a vertical plane with respect to a central axis of the vehicle, the sail deployment mechanism (10a) comprising: hydraulic cylinder (11), drive slider (12), slider guide rail (13), sail base (14), base connecting rod (15) and base hinge (16), wherein:

the hydraulic cylinder (11) is used for outputting driving force and pushing the driving slide block (12) to do linear motion along the vertical guide rail (13);

the driving slide block (12) drives the sail base (14) to rotate 90 degrees around the axis of the base hinge (16) through the base connecting rod (15) so as to control the sail (1) to be in a vertical posture or a horizontal posture.

7. The marine unmanned vehicle of claim 1 or 6, wherein the linkage unit (10) comprises a winged keel fold out mechanism (10b) mounted to the cross section of the vehicle, the winged keel fold out mechanism (10b) comprising: hydraulic cylinder (11), drive slider (12), slider guide rail (13), fossil fragments connecting piece (17a, 17b), fossil fragments connecting rod (1ga, 18b) and fossil fragments hinge (19a, 19b), wherein:

the hydraulic cylinder (11) outputs driving force and pushes the driving slide block (12) to do linear motion along the slide block guide rail (13);

the driving sliding block (12) drives the keel connecting pieces (17a, 17b) to rotate 90 degrees around the keel hinges (19a, 19b) through the keel connecting rods (18a, 18b) respectively, and the driving sliding block is used for controlling the wing keels (7) to be in a vertical posture or a horizontal posture.

8. The marine unmanned vehicle of claim 4, wherein the vehicle further comprises a reserve buoyancy adjustment unit for adjusting a reserve buoyancy of the vehicle in a voyage handoff mode, comprising:

the front water tank (20a) and the rear water tank (20b) are arranged inside the middle ship body (6b) along the axis of the aircraft, and a plurality of guide pipes (22) are arranged between the two water tanks and are used for realizing communication of the two water tanks;

a water injection pump (21a) connected to the front water tank (20 a);

a drain pump (21b) connected to the rear water tank (20 b).

9. The marine unmanned vehicle of claim 1, wherein the buoyancy adjustment unit comprises:

an oil tank (23) having a guide cylinder wall (23a), and incorporating a sliding piston (23b) that reciprocates along the axis of the guide cylinder wall (23a) in accordance with the change in the volume of hydraulic oil loaded into the oil tank (23);

the outer oil bag (24) is soaked in seawater and is made of oil-resistant and seawater-resistant chloroprene rubber;

a bidirectional hydraulic pump (27) communicating the oil tank (23) and the outer oil bag (24);

a relief valve (26) having two ports on one side thereof and connected to both ends of the bidirectional hydraulic pump (27) to form two connection paths, respectively; and the other side of the oil tank is provided with two ports which are respectively connected to an oil tank (23) and an outer oil bag (24);

and the electromagnetic valve (25) is provided with two ports which are respectively connected to two connecting passages formed by the bidirectional hydraulic pump (27) and the overflow valve (26).

10. The marine unmanned vehicle according to claim 4, further having a centre of gravity adjustment unit, arranged in parallel along the middle hull (6b), comprising a weight (28), a slider-nut assembly (29), a trapezoidal screw (30), a biaxial guide (31) and a screw motor (32), wherein:

the lead screw motor (32) is used for driving the trapezoidal lead screw (30) to rotate;

the sliding block nut assembly (29) is driven by the rotating trapezoidal lead screw (30) to move linearly along the double-shaft guide rail (31);

the weight (28) moves along with the sliding block nut component (29) which is fixedly connected with the weight, and the movable range of the weight (28) is less than or equal to the length of the middle hull (6 b);

the trapezoidal lead screw (30) adopts trapezoidal threads and has a self-locking function.

Technical Field

The invention relates to the technical field of novel marine unmanned aircrafts, in particular to a natural environment fluid-driven variable-configuration dual-attitude long-range marine unmanned aircraft.

Background

The marine unmanned aircraft refers to an unmanned system navigating in the ocean and is an important tool for modern ocean observation and exploration. Depending on the navigation space, there are generally two categories, unmanned surface vehicles (unmanned ships) and unmanned underwater vehicles (unmanned vehicles). The surface navigation and the underwater navigation are two different navigation states, in order to adapt to different navigation spaces and navigation states, the prior unmanned surface vehicle is developed and built based on a technical system of a small ship, and the prior unmanned underwater vehicle is developed and built based on a technical system of a torpedo and a submarine. Due to technical limitation, the two types of unmanned aircrafts have single navigation state and configuration, can only continuously work on the water surface or under the water, and cannot meet the requirements of multi-space three-dimensional observation on the water surface and under the water of the ocean in the future. Although semi-submersible unmanned vehicles have been developed that can travel both on and near the water surface, unmanned vehicles that meet the requirements of both water and underwater conditions have not been developed.

The exploration of the sea by human beings gradually extends from the near shore and the offshore to the far sea, and increasingly higher requirements are put forward on the endurance and the self-sustaining force of an aircraft. The existing unmanned ocean vehicle is mainly provided with energy required by sailing and traveling and working of various electric devices by a limited amount of batteries and fuel carried by the unmanned ocean vehicle, and the energy is a bottleneck for restricting the long-term on-site operation of the unmanned ocean vehicle. The marine natural environment receives, stores and emits energy through various physical processes, huge energy resources are stored, and the realization of energy self-sufficiency by utilizing the natural environment is a potential way for solving the problem of long-term energy supply of the marine unmanned aircraft. The ocean wind airflow and ocean water current are widely existed in the ocean, the fluid can directly push the ship body to advance, the energy conversion links are few, the conversion mode is simple, and the ocean wind airflow and ocean water current are developed and utilized by human beings in the field of the ocean for thousands of years. However, the unmanned sailing boat using ocean wind and current still cannot meet the requirements of all-weather sea condition use, has weak viability under severe sea conditions such as typhoon and the like, and is very easy to damage and lose. In order to avoid the severe sea conditions on the sea surface, the unmanned vehicle needs to have the utilization capacity of sea surface wind current and underwater current, and realizes self-sufficient and long-distance sailing of energy in the double sailing states of water surface and underwater.

Disclosure of Invention

Technical problem to be solved

The invention aims to break through the limitation of the current technology and provides a natural environment fluid-driven variable-configuration dual-attitude long-range marine unmanned aircraft. The aircraft realizes self-sufficiency of energy by means of natural environment, and has long-distance sailing capability in both water and underwater sailing states by adopting a variable configuration mode.

(II) technical scheme

The purpose of the invention is realized by the following technical scheme:

the invention provides a variable-configuration dual-navigation-state long-range marine unmanned aircraft driven by natural environment fluid, which has a water surface navigation mode, a navigation switching mode and an underwater navigation mode, and comprises the following components:

the wind energy collecting unit is arranged in the middle of a hull of the aircraft and comprises a sail 1, wherein the sail 1 is in a vertical pose in a water surface navigation mode, is used for receiving aerodynamic force applied by ocean wind to drive the aircraft to navigate and is changed into a horizontal pose in an underwater navigation mode;

the buoyancy adjusting unit is arranged in the bow of the aircraft and used for adjusting the buoyancy of the aircraft in an underwater navigation mode and realizing the heave motion and horizontal travel of the aircraft by combining the hydrodynamic force exerted by the head-on water flow when the aircraft moves;

the wing fossil fragments 7 sets up in navigation ware hull bottom, includes:

the two symmetrical parts 7a and 7b are in streamline cambered surface outlines after being folded and are symmetrical relative to a vertical plane along the central axis of the aircraft, the two symmetrical parts 7a and 7b are in horizontal poses in an underwater navigation mode, heave motion and horizontal traveling of the aircraft are realized by combining the buoyancy adjusting unit, and the two symmetrical parts are changed into vertical poses in a water navigation mode;

ballast weights 7c attached to the ends of the wing keels 7 for adjusting the aircraft center of gravity height in both surface mode and sail switch mode;

the linkage unit 10 is arranged inside a hull of the aircraft and used for finishing pose transformation of the sail 1 and the pterosaurs 7 in a sailing switching mode;

and the photovoltaic power generation unit is used for collecting solar energy and providing electric energy supply for electric consumption devices of the aircraft in a water surface navigation mode.

In some embodiments, the wind energy collection unit comprises:

the sail 1 is a rigid hard sail with a circular arc-shaped section, and adopts a skin-skeleton structure, a skeleton comprises a transverse rib 1a, a frame 1b, a main mast 1c and an auxiliary support 1d, and a skin 1e covers the surface of the skeleton and is used for bearing and transmitting pneumatic load;

the wind direction sensor 4 is arranged at the top of the sail 1 and used for collecting wind direction information in real time in a water surface sailing mode;

the sail rotating mechanism 5 is arranged at the bottom of the sail 1, comprises a rotary motor 5a and a worm gear transmission 5b, and realizes that the sail 1 rotates around the main mast 1c within a range of 360 degrees; the worm and gear transmission 5b has a self-locking function and is used for preventing the wind sail 1 from forced rotation under the action of external force; the sail 1 is adjusted to the optimal sail turning angle position by the sail rotating mechanism 5 and the maximum driving force is obtained.

In some embodiments, the photovoltaic power generation unit comprises:

the solar cell panel 2 is made of a flexible film material and is bent, attached and installed according to the arc-shaped outer envelope of the sail 1;

the electric energy storage device is provided with a pressure-bearing shell, is arranged inside the hull of the aircraft, and is used for receiving the output electric energy of the solar cell panel 2.

In some embodiments, the hull 6 of the aircraft is of the bilge dog-leg ship type, comprising:

the bow 6a adopts a wave-penetrating configuration;

the middle hull 6b adopts a parallel middle body shape, and the outer envelope of the cross section of the middle hull adopts an outward floating camber line;

the stern 6c is a U-shaped cross section and extends from the tail end of the middle hull 6b to the tail end of the stern 6c in a smooth curved surface, and the tail end of the stern 6c is a square stern.

In some embodiments, the aircraft further has a heading control unit mounted to the stern 6c of the aircraft, comprising a rudder 8 and a steering engine 9, wherein:

the steering engine 9 drives the rudder 8 to rotate in a range of-20 degrees to 20 degrees around a vertical axis based on the ship body 6;

the rudder 8 is of a trapezoidal rudder shape with the section shape of NACA 0015;

the course control unit is used for generating a turning moment of the aircraft by utilizing the hydrodynamic lateral force exerted by water flow in the water surface navigation mode and the underwater navigation mode so as to regulate and control or keep the course of the aircraft.

In some embodiments, the linkage unit 10 includes a sail deployment mechanism 10a mounted in a vertical plane relative to a central axis of the aircraft, the sail deployment mechanism 10a including: hydraulic cylinder 11, drive slider 12, slider guide 13, sail base 14, base connecting rod 15 and base hinge 16, wherein:

the hydraulic cylinder 11 is used for outputting driving force and pushing the driving slide block 12 to do linear motion along the vertical guide rail 13;

the driving slide block 12 drives the sail base 14 to rotate 90 ° around the axis of the base hinge 16 through the base connecting rod 15, so as to control the sail 1 to be in a vertical posture or a horizontal posture.

In some embodiments, the linkage unit 10 includes a winged keel deployment mechanism 10b mounted to a cross-section of an aircraft, the winged keel deployment mechanism 10b comprising: hydraulic cylinder 11, drive slide 12, slide guide 13, keel connectors 17a, 17b, keel links 18a, 18b, and keel hinges 19a, 19b, wherein:

the hydraulic cylinder 11 outputs driving force and pushes the driving slide block 12 to do linear motion along the slide block guide rail 13;

the driving slide block 12 drives the keel connecting pieces 17a and 17b to rotate 90 degrees around the keel hinges 19a and 19b through the keel connecting rods 18a and 18b, and is used for controlling the wing keels 7 to be in a vertical posture or a horizontal posture.

In some embodiments, the aircraft further has a reserve buoyancy adjustment unit for adjusting a reserve buoyancy of the aircraft in a voyage handoff mode, comprising:

a front tank 20a and a rear tank 20b, placed inside said middle hull 6b along the axis of the aircraft, and between which a plurality of ducts 22 are provided for the communication of the two tanks;

a water injection pump 21a connected to the front water tank 20 a;

and a drain pump 21b connected to the rear water tank 20 b.

In some embodiments, the buoyancy adjusting unit includes:

an oil tank 23 having a guide cylinder wall 23a, a sliding piston 23b provided therein, and reciprocating along an axis of the guide cylinder wall 23a in accordance with a volume change of hydraulic oil loaded in the oil tank 23;

an outer oil bag 24, which is soaked in seawater and is made of oil-resistant seawater-resistant chloroprene rubber;

a bidirectional hydraulic pump 27 for communicating the oil tank 23 and the outer oil bag 24;

an overflow valve 26 having two ports at one side thereof and connected to both ends of the bidirectional hydraulic pump 27 to form two connection paths, respectively; and the other side thereof has two ports connected to the oil tank 23 and the outer oil bag 24, respectively;

and an electromagnetic valve 25 having two ports connected to two connection paths formed by the bidirectional hydraulic pump 27 and the relief valve 26, respectively.

In some embodiments, the vehicle further has a centre of gravity adjustment unit, arranged in parallel along the central hull 6b, comprising a weight 28, a slider-nut assembly 29, a trapezoidal screw 30, a biaxial guide 31 and a screw motor 32, wherein:

the lead screw motor 32 is used for driving the trapezoidal lead screw 30 to rotate;

the slider nut assembly 29 is driven by the rotating trapezoidal lead screw 30 to move linearly along the double-shaft guide rail 31;

the weight 28 moves along with the sliding block nut component 29 which is tightly connected with the weight 28, and the movable range of the weight 28 is less than or equal to the length of the middle ship body 6 b;

the trapezoidal lead screw 30 adopts trapezoidal threads and has a self-locking function.

(III) advantageous effects

Compared with the prior art, the variable configuration type double-navigation state long-range marine unmanned aircraft driven by natural environment fluid has the beneficial effects that:

(1) the marine unmanned vehicle has two navigation states and configurations, namely a water navigation mode and an underwater navigation mode, and the two navigation states and the configurations can be transformed. Compared with an ocean unmanned aircraft (unmanned ship or unmanned submersible vehicle) only suitable for one navigation state, the invention breaks through the navigation region boundary, realizes two navigation states of seaworthiness on the water surface and underwater through the configuration transformation of the aircraft body, improves the space coverage capability of the aircraft, and provides possibility for carrying out multi-dimensional stereo observation and detection of an ocean longitudinal section and a water surface transverse range;

(2) the invention provides a sail and pterosaurs bone energy collection system of an ocean unmanned aircraft, which can obtain the direct driving force of the aircraft by means of natural fluid (sea surface airflow and underwater current) and obtain the electric energy required by the operation of electric consumption devices through sunlight conversion. The invention realizes self-sufficiency of energy of the aircraft by utilizing natural environment energy, obviously enhances the self-sustaining power and endurance of the aircraft, and is suitable for long-term application and deployment in ocean and ashore-free island-supported sea areas;

(3) compared with the traditional soft sail, the rigid sail provided by the invention can keep a consistent aerodynamic shape under various levels of wind power, so that the problem of aeroelastic deformation of the soft sail is avoided, and the aerodynamic output characteristic is stable. Meanwhile, the sail rotating mechanism regulates and controls the sail to rotate for 360 degrees, so that the sail can obtain the optimal windward angle position;

(4) the invention provides a double-navigation state configuration-variable linkage mechanism (namely a linkage unit) of an ocean unmanned aircraft, which realizes the simultaneous transformation of the positions and postures of a sail and a pterosaurs by one driving element. The linkage transformation scheme has a compact structure, and the complexity of the aircraft system is reduced by multiplexing the driving elements;

(5) the invention provides a multi-purpose wing keel, under a water surface navigation mode, the wing keel is positioned below a ship body in a vertical pose, the gravity center height of an aircraft is reduced, and the navigation stability is improved; under the underwater navigation mode, the aircraft obtains water flow driving force by means of the pterosaurs bones to realize underwater traveling;

(6) the invention provides a reserve buoyancy adjusting unit, which can change the buoyancy of an aircraft in a large quantity by water filling and draining modes of a water tank, and can realize the exchange of the relationship between the gravity center and the longitudinal position of a floating center of the aircraft so as to adapt to the requirement of navigation stability under two navigation states of water surface and water;

(7) the hull line of the aircraft has two navigation states of water surface and underwater. The bow line of the ship adopts a 'wave penetrating' configuration to reduce wave making resistance when the ship advances on the water surface, the middle ship body adopts a smooth parallel middle body enveloping shape to reduce viscous pressure resistance and friction resistance, and the cabin capacity of the middle ship body is regular so as to facilitate the placement and arrangement of devices;

(8) the invention provides a gravity center adjusting unit of an aircraft, which changes the overall mass distribution and the gravity center position of the aircraft in a large-range moving mode by adopting a small mass weight along a guide rail with the same length as a middle hull, and obtains sufficient attitude adjusting torque. In the scheme, the length of the guide rail is large, the mass requirement of the movable weight is obviously reduced, and the weight reduction of the aircraft is facilitated.

Drawings

FIG. 1 is a schematic illustration of an operating mode of the aircraft in an embodiment of the present invention;

FIG. 2 is a schematic illustration of the operating elements of the aircraft in surface travel mode in accordance with an embodiment of the present invention;

FIGS. 3 a-3 b are schematic diagrams of the operation of the aircraft in surface travel mode in accordance with an embodiment of the present invention;

FIG. 4 is a schematic illustration of a linkage unit during a change in configuration of the aircraft in accordance with an embodiment of the present invention;

5 a-5 b are schematic diagrams of a reserve buoyancy adjustment unit in an aircraft according to an embodiment of the invention;

FIG. 6 is a schematic illustration of a change in counterweight characteristic during flight switching mode of the aircraft in accordance with an embodiment of the present invention;

FIG. 7 is a schematic view of the operating units of the vehicle in an underwater mode of operation in accordance with an embodiment of the invention;

FIG. 8 is a schematic representation of the principles of operation of the vehicle in an underwater mode of operation in accordance with an embodiment of the invention.

Description of reference numerals:

a photovoltaic power generation unit:

a solar cell panel 2;

and a battery pack 3.

A wind energy collection unit:

the sail 1: the device comprises transverse ribs 1a, a frame 1b, a main mast 1c, an auxiliary support 1d and a covering 1 e;

a wind direction sensor 4;

the sail rotating mechanism 5: a rotary motor 5a and a worm gear transmission 5 b.

The hull 6: a bow 6a, a middle hull 6b and a stern 6 c.

And (3) wing keel 7: wing keels 7a, 7b, ballast weights 7 c.

A course control unit:

a rudder 8;

and a steering engine 9.

The linkage unit 10:

sail deployment and retraction mechanism 10 a: the device comprises a hydraulic cylinder 11, a driving slide block 12, a slide block guide rail 13, a sail base 14, a base connecting rod 15 and a base hinge 16;

pterosaur bone folding and unfolding mechanism 10 b: hydraulic cylinder 11, driving slide block 12, slide block guide rail 13, keel connecting pieces 17a and 17b, keel connecting rods 18a and 18b and keel hinges 19a and 19 b.

Reserve buoyancy adjustment unit:

a front water tank 20a, a rear water tank 20b, a water injection pump 21a, and a drainage pump 21 b;

a conduit 22.

A buoyancy adjusting unit:

oil tank 23: a guide cylinder arm 23a, a slide piston 23 b;

an outer oil pocket 24;

a solenoid valve 25;

an overflow valve 26;

a bidirectional hydraulic pump 27.

A center-of-gravity adjusting unit:

a weight 28;

a slider nut assembly 29;

a trapezoidal lead screw 30;

a biaxial guide 31;

a lead screw motor 32.

Detailed Description

The following description of the preferred embodiments of the present invention will be made in conjunction with the accompanying drawings. To better illustrate the embodiments of the present invention, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of an actual product; it will be understood by those skilled in the art that certain well-known structures in the drawings and descriptions thereof may be omitted.

The invention provides a variable configuration double-navigation-state long-range marine unmanned aircraft driven by natural environment fluid, which has three modes of a water surface navigation mode, a navigation switching mode and an underwater navigation mode, realizes self-sufficiency of energy by using sea surface wind flow, underwater flow and sunlight of the natural environment, and has long-distance navigation capacity in both water surface navigation states and underwater navigation states, as shown in figure 1:

in the water surface navigation mode, the sea surface wind current and the wind energy collecting unit mainly play a role, and the specific expression is that the navigation vehicle drives the navigation vehicle to navigate by means of sails in a vertical pose and aerodynamic force applied by ocean wind;

in an underwater navigation mode, the buoyancy adjusting unit and the pterosaur bones are mainly used for playing a role, particularly the role of a streamline cambered surface contour when the pterosaur bones are in a horizontal pose, and the specific expression is that the navigation device utilizes the buoyancy adjusting unit to adjust the buoyancy of the navigation device and utilizes the pterosaur bones in the horizontal pose to realize the heaving motion and the horizontal advance of the navigation device by utilizing the hydrodynamic force applied by the head-on water flow when the navigation device moves, so that the navigation device navigates underwater by a zigzag track;

in a navigation switching mode, the navigation device finishes the pose transformation of the sail and the pterosaurs through the linkage unit, changes the longitudinal position relation of the gravity center and the floating center, and meets the navigation stability requirements in two navigation states;

in addition, the aircraft uses photovoltaic power generation units to collect solar energy and provide electrical energy supply for electrical consumers when in surface navigation mode.

The sail and the wing keel are vertical in the water surface navigation mode and are changed into horizontal in the underwater navigation mode.

In view of the above, the present invention provides a specific embodiment and provides a detailed description of three modes of operation of the aircraft with reference to the accompanying drawings:

1. surface mode of travel

The aircraft is provided with photovoltaic power generation units, as shown in fig. 1, in an aircraft surface sailing mode, a solar cell panel 2 on the arc-shaped surface of a vertical sail 1 is exposed to sunlight, the solar cell panel 2 absorbs sunlight radiation and converts the sunlight radiation into output electric energy, and the electric energy is transmitted to an electric energy storage device (in the embodiment, a storage battery 3) through a watertight cable to be stored and is used for providing electric energy supply for electric energy consumption devices of the aircraft. The solar cell panel 2 is a flexible thin-film solar cell and is mounted in a bending and fitting mode according to the arc-shaped outer envelope of the sail 1. The storage battery 3 has a pressure-bearing housing and can bear external water pressure for diving and navigation.

As shown in fig. 2, in the present embodiment:

the aircraft is provided with a wind energy collecting unit which is composed of a sail 1, a wind direction sensor 4 and a sail turning mechanism 5. The sail 1 is a rigid hard sail with an arc-shaped section, is erected in the middle of the hull in a vertical pose, and can obtain sailing aerodynamic force by using ocean wind airflow. The sail 1 is of a skin-skeleton structure, a skeleton consists of transverse ribs 1a, a frame 1b, a main mast 1c and auxiliary supports 1d, the sail skeleton can bear shearing force, bending moment and torque of airflow, and the skin 1e covers the surface of the skeleton to play a role in bearing and transmitting aerodynamic load.

Further, the wind direction sensor 4 is mounted at the top of the sail 1, and can collect the current wind direction in real time; the sail rotating mechanism 5 is arranged at the bottom of the sail 1 and mainly comprises a rotating motor 5a and a worm and gear transmission 5b, the rotating motor 5a outputs sail rotating torque, and the worm and gear transmission 5b finishes sail rotating torque turning to realize that the sail 1 rotates around a vertical rotating shaft within a range of 360 degrees; meanwhile, the worm and gear transmission 5b has a self-locking function, and the wind sail 1 is prevented from being forced to rotate under the action of external force. In the surface sailing mode, the aircraft adjusts the sail 1 to be at the optimal sail turning angle position through the sail turning mechanism 5 to obtain the maximum driving force for traveling based on the current wind direction information acquired by the wind direction sensor 4.

The hull 6 of the aircraft adopts a round bilge angle ship-shaped scheme, is designed and improved based on a classical molded line, and has the characteristics of regular cabin capacity and low water resistance. The hull 6 includes: a foreship 6a, a middle hull 6b and a stern 6 c. The front section of the bow 6a adopts a 'wave-penetrating' structure, the height of each waterline keeps a sharp inflow angle, and the water flow of the aircraft in the water surface advancing process flows to the middle ship body 6b along the surface of the bow 6a, so that the back splash of the water flow is avoided, and the wave-making resistance during advancing is reduced. The middle ship body 6b adopts a parallel middle body shape, the cabin capacity is regular and the devices are convenient to place; referring to fig. 5, the outer envelope of the cross section of the middle hull 6b is an outward floating camber line, and during the heeling of the aircraft, the outward floating part of the middle hull 6b can be submerged first to reduce the heeling angle of the aircraft. The stern 6c adopts a U-shaped cross section scheme and extends from the tail end of the middle ship body 6b to the tail end of the stern 6c in a smooth curved surface mode, and the tail end of the stern 6c adopts a square stern and guides water flow to smoothly flow out from the stern 6c of the navigation device.

The bottom of the vehicle is arranged with a pterosaur 7 with a streamline cambered profile. The wing keel 7 consists of two symmetrical parts 7a, 7b, which are folded to form a symmetrical shape relative to a vertical plane along the central axis of the aircraft. And the ballast weight 7c is arranged at the tail end of the wing keel 7 so as to reduce the height of the gravity center of the aircraft and enhance the water surface running stability of the aircraft.

The aircraft is provided with a course control unit, is used for adjusting and keeping the advancing course, consists of a rudder 8 and a steering engine 9 and is arranged at the stern of the aircraft. The steering engine 9 can drive the rudder 8 to rotate around the vertical axis within the range of-20 degrees to 20 degrees; the rudder 8 is of a trapezoidal rudder type with the section shape of NACA0015, and the hydrodynamic lateral force applied by water flow is utilized to generate the turning moment of the aircraft so as to regulate and control or keep the heading of the aircraft.

Based on the aboveIn the embodiment, the working principle of the aircraft in the water surface sailing mode is shown in fig. 3 a-3 b, the ocean wind current flows through the circular arc-shaped sail 1 at the windward included angle theta, and the difference of the air pressures at the two sides of the circular arc surface of the sail 1 is utilized to apply the aerodynamic force F to the sail 1_A. Aerodynamic force F_AComponent force F in direction of vehicle velocity v_DDriving the aircraft to travel, aerodynamic force F_AComponent F in a direction perpendicular to the velocity v_SResulting in a heeling moment M for the aircraft_h. As shown in FIG. 3b, the position of the center of buoyancy of the vehicle is represented by O, due to the change of the submerged part of the hull 6 caused by the heeling of the vehicle_BLaterally offset to O_B'. Acting on O_B' the buoyancy B and the gravity G at the center of gravity of the aircraft form a heeling restoring moment M_R. Restoring moment M_RMoment M of heeling_hAnd the aircraft keeps the balance posture of the roll angle phi in a mutual balance way.

2. Navigation switching mode

The aircraft drives the sail 1 and the winged keel 7 to perform the folding and unfolding actions simultaneously by using the linkage unit 10 in the sailing switching mode, as shown in a linkage mechanism schematic diagram (figure 4). The linkage unit 10 is arranged inside the middle hull 6b and is provided with two groups of plane crank slide block mechanisms: a sail deploying and retracting mechanism 10a and a pterosaur bone deploying and retracting mechanism 10 b. The sail deploying and retracting mechanism 10a is located in a longitudinal vertical plane of a central axis of the aircraft and comprises a hydraulic cylinder 11, a driving slide block 12, a slide block guide rail 13, a sail base 14, a base connecting rod 15 and a base hinge 16. The hydraulic cylinder 11 outputs a driving force and pushes the driving slider 12 to move linearly along the slider guide 13. The driving slide block 12 drives the sail base 14 to rotate 90 degrees around the base hinge shaft 16 through the base connecting rod 15, so that the sail 1 can be changed between a vertical (water surface sailing mode) pose and a horizontal (underwater sailing mode) pose. The winged keel folding and unfolding mechanism 10b is positioned on the transverse plane of a navigation device and consists of a hydraulic cylinder 11, a driving slide block 12, a slide block guide rail 13, a keel connecting piece 17, a keel connecting rod 18 and a keel hinge 19. The hydraulic cylinder 11 outputs a driving force and pushes the driving slider 12 to move linearly along the slider guide 13. The driving sliding block 12 drives the keel connecting pieces 17a and 17b to rotate 90 degrees around the keel hinges 19a and 19b through the keel connecting rods 18a and 18b respectively so as to realize the transformation action of the pterosaurs 7a and 7b fixedly connected with the keel connecting piece 17 between the horizontal (underwater navigation mode) and vertical (water surface navigation mode) poses.

The aircraft utilizes a reserve buoyancy adjustment unit to adjust aircraft reserve buoyancy in a voyage handoff mode. The reserve buoyancy adjusting unit mainly comprises a front water tank 20a, a rear water tank 20b, a water injection pump 21a and a water discharge pump 21b, wherein the front water tank 20a and the rear water tank 20b are arranged inside the middle hull 6b along the axis of the aircraft, and the two water tanks are communicated through a plurality of guide pipes 22, so that the heights of the water levels inside the two water tanks are consistent, as shown in fig. 5 a. The water injection pump 21a is connected with the front water tank 20a, the height of the internal water level rises after the water tank 20 is filled with water, the reserve buoyancy of the aircraft is reduced, the aircraft is wholly immersed in the water, and the aircraft is in a critical state that the gravity and the buoyancy of the aircraft are equal; the drain pump 21b is connected to the rear water tank 20b, the internal water level height drops after the water tank 20 drains, the aircraft reserve buoyancy increases, and the sail 1 at the top of the hull 6 (horizontal attitude state) is exposed to the sea surface, as shown in fig. 5 b.

The process of the change of the weighing characteristic of the aircraft in the sailing switch mode is shown in figure 6. In an initial state (water surface navigation mode), aiming at a large overturning moment generated by external force action such as airflow and the like, the aircraft utilizes reserve buoyancy to realize a water surface anti-overturning function, the sail 1 and the wing keel 7 are kept in a vertical pose, water stored in the water tank 20 is emptied, the sail 1 is exposed out of the water surface, and the gravity center O of the sail 1 is_GIs located at the floating center O_BUpper, offset from the floating center O_B' relative center of gravity O_GThe restoring moment and the airflow overturning moment are balanced; after the folding and unfolding actions, the linkage unit 10 drives the sail 1 and the pterosaurs 7 to turn from vertical to horizontal positions, and the gravity center O of the aircraft is changed due to the position changes of the sail 1 and the pterosaurs 7_GHeight decrease, floating center O_BHeight rise, center of gravity O_GAnd a floating core O_BChange in meta-position relationship, floating center O_BAt center of gravity O_GAn upper part; after the reserve buoyancy unit finishes water injection of the water tank (underwater navigation mode), the whole aircraft is immersed in water, the gravity and the buoyancy of the aircraft are equal, the reserve buoyancy is 0, and the buoyancy center is O_BThe position is raised, the gravity center O of the aircraft is increased_GAnd a floating core O_BLongitudinally spaced to raise the center of gravity O_GRelative floating center O_BIs returned toAnd the attitude stabilization of the underwater state is realized by complex moment.

3. Underwater mode of travel

The vehicle utilizes the buoyancy adjustment unit to adjust its own buoyancy to achieve underwater heave motions, as shown in fig. 7. The buoyancy adjusting unit is arranged inside a bow 6a of the aircraft and mainly comprises an oil tank 23, an outer oil bag 24, an electromagnetic valve 25, an overflow valve 26 and a bidirectional hydraulic pump 27. The oil tank 23 is filled with hydraulic oil by using an internal cavity of the guide cylinder wall 23a, and the built-in sliding piston 23b reciprocates along the axis of the guide cylinder wall 23a along with the volume change of the hydraulic oil filled in the oil tank 23. The outer oil bag 24 is soaked in seawater and made of oil-resistant and seawater-resistant chloroprene rubber, and the displacement of the outer oil bag 24 changes along with the volume change of hydraulic oil loaded in the outer oil bag. Under the condition that the total volume of hydraulic oil of the aircraft is constant, the bidirectional hydraulic pump 27 adjusts the volume distribution proportion of the hydraulic oil in the oil tank 23 and the outer oil bag 24, and further changes the buoyancy of the aircraft.

The aircraft has a center of gravity adjusting unit for adjusting the center of gravity O of the aircraft in an underwater navigation mode_GThe gravity center adjusting unit is arranged in parallel along the middle hull 6b and comprises a weight 28, a sliding block nut assembly 29, a trapezoidal lead screw 30, a biaxial guide rail 31 and a lead screw motor 32, as shown in figure 7, the gravity center adjusting unit adopts a lead screw nut transmission mechanism, the trapezoidal lead screw 30 is driven to rotate by the lead screw motor 32, the sliding block nut assembly 29 is driven to linearly move along the biaxial guide rail 31 under the drive of the rotating trapezoidal lead screw 30, the weight 28 moves along with the sliding block nut assembly 29 fixedly connected with the weight 28, as shown in figure 7, the movable range l of the weight 28 almost coincides with the length of the middle hull 6b, the weight 28 moves in a large range in the middle hull 6b, the mass distribution of the whole aircraft can be changed, and the gravity center O of the aircraft can be further changed_GAxial position shift to O_G' the aircraft pitch attitude angle β changes because the gravity center and the floating center of the aircraft are always in the same straight line in the vertical direction, in addition, the trapezoidal lead screw 30 adopts trapezoidal threads, has a self-locking function, and can keep the positions of the slide block nut assembly 29 and the weight 28 unchanged in a static state.

Referring to fig. 7 again, in the underwater navigation mode, the vehicle still uses the heading control unit formed by the rudder 8 and the steering engine 9 to perform heading regulation and control and keeping.

The working principle of the underwater navigation mode is shown in fig. 8, the aircraft moves the incident water flow to flow through the pterosaur bone 7 in the horizontal unfolding position at the incident flow included angle α, and the difference of the water pressure at the two sides of the cambered surface of the pterosaur bone 7 is utilized to apply the hydrodynamic force F to the pterosaur bone 7_HHydrodynamic force F_HComponent force F in vertical direction_LThe gravity G and the buoyancy B of the aircraft together form a heave movement velocity v_YDriving resultant force, hydrodynamic force F_HComponent force F in horizontal direction_DFor horizontal speed v of aircraft_XThe driving force of (2).

It should be further noted that the present invention is not limited to the above-described embodiments. The above description of a specific embodiment of an aircraft based on three modes is only a preferred embodiment of the invention, intended to describe and illustrate the solution of the invention, which is only illustrative and not limiting. It will be apparent to those skilled in the art that many changes in form, modifications and additions may be made thereto without departing from the spirit and scope of the invention as defined in the appended claims, which are intended to be limited only by the following claims and their equivalents.