CN104960665A - Aircraft having multiple flight modes - Google Patents

Abstract

The invention discloses an aircraft having multiple flight modes. The aircraft is characterized in that on the basis of the aircraft of which the driving force is produced by the combination of a plurality of driving devices, and wings are additionally arranged for assisting the aircraft in flight. The characteristics of a helicopter aircraft and a fixed wing aircraft are organically integrated, so that the aircraft can fly for a long distance in a high-speed energy-saving way and can also precisely fly in a low-speed accurate way, the advantages of the combination of multiple flight modes are embodied in complex flight missions. In the military field, the aircraft can be widely used in reconnaissance patrolling, command control, fire attacking, battlefield aids, logistical support and the like; in the civilian field, the aircraft can be widely used in aerial shooting and aerial survey, material transportation, medical rescue, high-altitude rescue, high-altitude fire extinguishing, agriculture, forestry and plant protection and the like.

Description

An aircraft with multiple flight modes

technical field

The invention relates to an aircraft with multiple flight modes.

Background technique

At present, take the aircraft engine set as an example: in the driving devices such as combined engines, tandem, linear, square, ring and other arrangements are mostly used. This method is limited by the cumbersome connection between the engines in the assembly, and the engine sets interfere with each other during work, and unnecessary spaces and gaps will be generated between the engines, resulting in increased volume and weight of the assembly. The components connected and fixed between the engines at different positions in the assembly are not uniform, which leads to stress concentration in the assembly (system), and the infinite accumulation of engines will eventually lead to the collapse of the connecting structure of the aircraft, so the number of engines in the assembly cannot be increased infinitely. The load capacity is also limited. In addition, the general disadvantages of current helicopter-type aircraft are high energy consumption, short range, and poor stability in harsh environments, so they cannot complete various flight tasks stably for a long time.

Contents of the invention

In order to solve the above problems, the present invention proposes an aircraft with multiple flight modes, which organically integrates the characteristics of helicopter-type aircraft and fixed-wing aircraft, so that the aircraft can fly long distances in a high-speed energy-saving manner and can fly in a low-speed and accurate manner. Precise flight, demonstrating its advantages in combining multiple flight modes in complex flight missions.

First of all, a notable feature of the aircraft is that the triangular arrangement of the driving devices can accommodate more driving devices per unit volume, and the aircraft can maintain the optimal spatial layout under the condition of obtaining the same propulsion.

The basic principle is that the aircraft driving devices are arranged in a triangle to form a triangular driving device module; the spatial distance between adjacent driving devices in the triangular driving device module is preferably equal; Form a driving device assembly composed of multiple driving devices; the number of driving devices in the driving device assembly is N sets, N≥3.

The optimal method of driving device mapping permutation and combination can be expressed by the following geometric method. The triangle ABC is an equilateral triangle, and the axisymmetric equilateral ΔBCD of ΔABC is formed by taking the BC side of the equilateral ΔABC as the axis to form a rhombus ABCD, along AB, BD, CD, AC extends in reverse to both sides, cuts the sides equal to the sides of the rhombus, connects the corresponding points, and forms countless rhombuses, and then connects the short diagonals of all rhombuses to form a rhombus geometric structure composed of countless equilateral triangles, The node of the geometric structure is regarded as the preferred installation position of the drive device, and the overlapping position of the nodes is regarded as the common position. According to actual needs, the drive device can be installed in each spatial direction of the node. In addition, the shape of the driving device assembly and the number of driving devices can be changed accordingly according to the needs of the flight environment, load weight, and shape.

In the present invention, if the aircraft is a driving device with a small jet-type rotating torque, an odd number or an even number of driving devices can be selected; if a driving device with a relatively strong rotating torque is used, for example, the engine is connected to the propeller. The engine is connected to the propeller to counteract the counter torque. At present, the aircraft driven by multiple driving devices mostly adopts the mode of connecting the engine to the propeller. Therefore, the preferred solution of the present invention is a rhombus mapping, that is, a rhombus module is formed on the basis of an equilateral triangle module, and the engine is installed at the nodes of the rhombus. The engine can be arranged up and down.

In the combination built on the basis of the diamond-shaped driving device module (composed of two triangular modules) in the geometric structure, due to the structural and functional characteristics of the aircraft, the spatial distance of the diagonal lines in the diamond-shaped module can be adjusted according to the needs of the aircraft, and the geometric The apex angles of rhombuses in the connecting pieces formed by the structure can be adjusted.

In the present invention, the driving devices of the aircraft are connected by connectors, which may be but not limited to skeletons or other connectors. According to the characteristics of the aircraft and the existing technical conditions, the aircraft can preferably be connected by frames, and the frames can be fixed or movable. The use of a fixed skeleton means that the form of an integrated skeleton can be manufactured or the skeleton components can be fixed through fixed connectors; the movable skeletons are connected by movable connectors to make a foldable or disassembled skeleton, and the skeleton is restricted by the fixing parts when in use. The movement of the skeleton constitutes a stable form. When the size needs to be reduced, the fixing parts that restrict the movement of the skeleton can be released to realize the folding or disassembly of the skeleton. This effectively reduces the volume of the aircraft, especially the large aircraft, and facilitates storage and transportation.

The second major feature of the present invention is that the aircraft can determine the size, shape and number of driving devices of the aircraft according to the flight environment, the shape and weight of the load. Except for the installation position occupied by the driving device on the aircraft, the rest of the area can be used as the installation or mounting area of the flight auxiliary device or load. Due to the special structure of the aircraft of the present invention, each driving device or the area of each group of driving devices in the aircraft driving system can be provided with a load mounting area or an area connected with the overall load, so that the purpose of setting is to make the aircraft driving system The generated driving force is evenly applied to the load part, and the connection between the driving device and the load in the aircraft will not appear a series of vicious chain reactions affecting the overall flight system due to stress concentration in a certain area.

The third major feature of the present invention is that wings are added on the basis of the aircraft driving device and the number of wings is M, where M≥1. Taking the frame connection as an example, the wings are connected to the frame of the aircraft through connectors, and the wings can rotate axially. During flight, when there is a relative speed between the aircraft and the air, properly adjusting the angle of attack of the wings will generate lift to assist the driving device to provide lift to the aircraft, especially at low speeds. flight attitude so as to minimize adverse drag. Under special circumstances, when the aircraft has a relative speed to the air, the aircraft can rely on the wings to fly or use the wings to slow down. For example, when the drive device of the aircraft fails, it can use the wings to glide as a buffer, effectively protecting the aircraft, or adjusting the rotation of the wings. The angle causes it to create drag in the forward direction to slow down the aircraft.

The corresponding left and right wings generate rolling force by changing the angle difference to make the aircraft roll laterally, which is similar to the function of the aileron rudder of a fixed-wing aircraft; the front and rear correspondingly set wings or a single wing generate Uplift or downforce causes the aircraft to pitch longitudinally, similar to the function of an elevator on a fixed-wing aircraft. When the aircraft is flying at a certain speed, the wings can generate additional lift to reduce the burden on the driving device. At the same time, the rudder effect generated by manipulating the wings can also reduce the burden on the driving device when the aircraft changes attitude. To a certain extent, energy is saved, the battery life is extended, and the load capacity is also improved.

In addition, when the wing rotates axially and reaches a certain angle with the plane of the fuselage, the wing can also be used as the landing support device of the aircraft, that is, the landing gear, thereby effectively reducing the structural burden and take-off weight of the aircraft.

Description of drawings

Several preferred embodiments of the present invention are described in detail below in conjunction with the accompanying drawings:

Fig. 1 is a schematic diagram of the basic distribution of the driving device of the present invention;

Fig. 2 is a schematic diagram of an embodiment of the geometric structure of the mapping arrangement of the aircraft driving device;

Fig. 3 is a schematic diagram of another embodiment of the geometric structure of the mapping arrangement of the aircraft driving device;

Fig. 4 is a schematic diagram of a preferred implementation layout of the aircraft of the present invention;

Fig. 5 is a schematic diagram of an implementation layout of the aircraft of the present invention;

Fig. 6 is a schematic diagram of another implementation layout of the aircraft of the present invention.

Fig. 7a, Fig. 7b, Fig. 7c, Fig. 7d, Fig. 7e and Fig. 7f are the side views of the preferred working mode of the aircraft of the present invention respectively.

01-Triangle Drive Module 02-Node 03-Map 04-Skeleton 05-Drive 06-Skeleton Connector 07-Wing 08-Wing Connector 09-Propeller 10-Horizontal Reference Line 11-Geometry Reference Line 12 -engine

Detailed ways

Fig. 1 has shown the basic distribution of the driving device of aircraft of the present invention, among the figure triangle ABC is an equilateral triangle, and three apex places of triangle are aircraft driving device (05) positions, form triangular driving device module (01); Preferably , the spatial distance between adjacent driving devices (05) is equal; based on the driving device modules (01) arranged in a triangle, they are mapped and arranged in the spatial direction to form a driving device (05) combination composed of multiple driving devices (05) In this figure, the rhombus ABCD is derived from the triangular ABC drive unit module to form a diamond-shaped module, and so on, can form various forms of drive unit (05) assemblies; the drive unit (05) assembly in the drive unit ( 05) The quantity is N units, N≥3. Among them, (03) is the mapping body of the triangle in the geometric structure, and (11) is the reference line of the geometric structure.

The preferred implementation of the mapping arrangement and combination of the driving device in the aircraft of the present invention can be expressed by the following geometric methods, as shown in Figure 2, the triangle ABC is an equilateral triangle, and the axisymmetric equilateral ΔBCD of ΔABC is made with the BC side of the equilateral ΔABC as the axis to form a rhombus ABCD , extending in reverse directions along AB, BD, CD, and AC respectively, cutting out sides equal to the side lengths of the rhombus, connecting corresponding points to form countless rhombuses, and then connecting the short diagonals of all rhombuses to form countless In the rhombus geometric structure formed by equilateral triangles (03), the node (02) of the geometric structure is regarded as the preferred installation position of the drive device (05), and the coincidence of the nodes (02) is regarded as the common position.

Another embodiment of the mapping arrangement and combination of multiple driving devices in the aircraft of the present invention can be specifically expressed by the following geometric method: as shown in Figure 3, the triangle ABC is an equilateral triangle, and the three points A, B, and C are respectively used as the central symmetrical point to make ΔABC The centrosymmetric ΔADE, ΔCPG, and ΔBHI of ΔADE, ΔCPG, and ΔBHI respectively take D, E, F, G, H, and I as the central symmetric points to make an equilateral triangle, and so on, you can get a geometric structure composed of countless equilateral triangles (03) , the node (02) of the geometric structure is regarded as the preferred installation position of the drive device (05), and the coincidence of the nodes (02) is regarded as the common position.

It should be pointed out that, in order to exert the best power effect of the aircraft, the drive device (05) can be installed in each spatial direction of the node (02) in all the above geometric structures, and the installation effect of the node (02) in the up and down direction is the best. In addition, the size and shape of the driving device (05) assembly and the number of driving devices (05) can be changed as required.

As far as the current technical level is concerned, the driving device of the aircraft is preferably an engine, and the connecting part is an example of a skeleton. The following will specifically introduce several feasible structural layout schemes of the aircraft evolved from the geometric structure.

As shown in Figure 4, in the preferred solution provided by this specific embodiment, the engines (12-1), (12-2), (12-3), (12-4) are arranged in a rhombus geometric structure and connected by a skeleton (04) , the engine (12) is fixedly installed at the skeleton (04), and the skeletons (04) are connected by skeleton connectors (06). The skeleton connectors (06) can be fixed or movable. The engine (12) Connect the propeller (09), the wing (07) is connected with the aircraft frame (04) by the wing connector (08) and is installed on both sides of the engine (12-2) and the engine (12-4) respectively, the wing (07 ) can rotate axially.

Fig. 5 is also a feasible implementation manner of this solution. The geometric method of Fig. 2 or Fig. 3 can be evolved into the layout structure of the aircraft in this figure, the engines (12-5), (12-6), (12-7), (12-8) are arranged in a rectangle, through the framework (04) cross connection installation, can be a fixed connection, also can be a movable connection, the engine (12) is connected to the propeller (09), and the wings (07) are symmetrically installed on both sides of the skeleton (04), and the wings (07) Respectively located in the area between the engines (12-5) and (12-7) and between the engines (12-6) and (12-8), the wing (07) and the frame (04) are connected by wing connectors (08) is connected, and the wing (07) can rotate axially.

As shown in Fig. 6, it represents another feasible implementation mode of this scheme. The geometric method of Fig. 2 or Fig. 3 can be evolved into the aircraft layout structure in this figure, which is composed of three complete triangular drive unit modules (01), i.e. engines (12-9), (12-10) and (12-11) form a triangular drive unit module (01), motor (12-12), (12-13) and (12-14) form a triangular drive unit module (01), motor (12-15), (12-16) and (12-17) form a triangular driving device module (01), and the engine (12) is connected by a skeleton (04), which can be a fixed connection or a movable connection, and the engine (12 ) is connected to the propeller (09), the coaxial wing (07) is symmetrically installed on both sides of the engine (12-9) in the triangular drive unit module (01), and the other wing (07) is installed on the triangular drive unit module (01 ) in the area between the engines (12-14) and (12-17), the wings (07) and the frame (04) are connected by wing connectors (08), and the wings (07) can be axially turn.

In all the above embodiments, due to the characteristics of the aircraft, the engine (12) can be installed up and down at the frame (04), if there are special requirements, it is not excluded to install the engine (12) or other devices in other directions.

Figure 7 of the accompanying drawings shows several preferred working modes of the aircraft of the present invention. As shown in the figure, (10) represents the horizontal reference line, and the direction of the arrow is the flight direction of the aircraft. Fig. 7a is the auxiliary lift and ascent flight mode, the wing (07) tilts upward at the same time to generate lift to assist the engine (12) to provide lift to the aircraft; Fig. 7b is the auxiliary descent flight mode, the wing (07) tilts downward at the same time The angle will generate downward pressure to make the aircraft descend, and at the same time, the coaxial wing (07) in the aircraft can act independently to realize the effect of the elevator in the fixed-wing aircraft to change the pitch angle of the aircraft; ) keep approximately parallel with the engine (12) plane or maintain the most ideal wind resistance angle with the flight direction and airflow direction to reduce the resistance and maintain the best flight state; For the best performance, the wing (07) can achieve the best aerodynamic layout by adjusting the angle of attack, so that the aircraft can present the best lift-to-drag ratio at various attitudes and speeds. ; Figure 7e is a rolling flight mode, the rolling moment produced by the left and right differential deflection of the coaxial wing (07) can make the aircraft do a rolling maneuver (differential relative to the flight direction of the aircraft or the upstream direction); Figure 7f Landing or landing mode, that is, when the aircraft needs to land, the wing (07) reaches a certain angle with the plane of the fuselage and can be used as a landing support device for the aircraft, that is, the landing gear. The wing (07) in this figure is approximately perpendicular to the plane of the fuselage . If it is necessary to increase the size of the landing gear, a support or shock absorbing assembly can also be added at the contact position between the wing (07) and the landing surface.

It must be noted that, in addition to the above-mentioned embodiments, the present invention can also have other implementations. For example, due to the structure and functional characteristics of the aircraft, some driving devices do not have to be combined strictly according to equilateral triangle modules, and can also be isosceles triangle modules. Triangular arrangement layout combination. In the same way, some driving devices do not have to be combined strictly in accordance with the diamond-shaped modules, but can also be arranged in a parallelogram arrangement and combination. In addition, the wing in the aircraft structure of the present invention is also to choose the installation position under the condition of technical conditions. It can be seen that the relevant equivalent replacement technical solutions should all fall within the scope of protection required by the present invention.

Claims (11)

1. have an aircraft for plurality of flight, this aircraft comprises the combination of drive means body and wing that are made up of actuating device, it is characterized in that:

A. actuating device is with rounded projections arranged, composition triangle actuating device module;

B. based on the actuating device module of rounded projections arranged, permutation and combination become to be made up of multiple stage actuating device combination of drive means body is mapped to direction in space;

C. in combination of drive means body, the quantity of actuating device is N platform, N >=3;

D. on aircraft driving device basis, wing is installed additional;

E. wing quantity is M, M >=1.

2. aircraft according to claim 1, is characterized in that: the space length between the adjacent driven device in triangle actuating device module is preferably equal.

3. aircraft according to claim 1, it is characterized in that: the method for optimizing of described mapping permutation and combination can be stated by following method of geometry, triangle ABC is equilateral triangle, rhombus ABCD is formed with the equilateral △ BCD of rotational symmetry that △ ABC is made for axle in the BC limit of equilateral △ ABC, respectively along AB, BD, CD, AC is to both sides reverse extending, intercept the limit equal with the rhombus length of side, connect respective point, form countless rhombus, then the short diagonal of all rhombuses is coupled together, form the rhombus geometry be made up of numerous equilateral triangle, the Nodes of described geometry is considered as the preferred installation site of actuating device, node overlapping position is considered as common location.

4. the aircraft according to claim 1 or 3, is characterized in that: geometry interior joint is considered as actuating device position.

5. aircraft according to claim 1, is characterized in that: aircraft can determine the quantity of the size of aircraft, shape and actuating device and wing according to actual needs.

6. the aircraft according to any one of claim 1 to 5, is characterized in that: the shape of actuating device and wing fabricate block and actuating device, wing quantity can make change as required.

7. an aircraft according to any one of claim 1 to 6, this aircraft is characterised in that: connected by attaching parts between actuating device, and attaching parts can adopt but be not limited to skeleton or other attaching parts.

8. an aircraft according to any one of claim 1 to 7, is characterized in that: if connected in skeleton mode between actuating device, can be fixedly connected with, and also can be to be flexibly connected.

9. aircraft according to claim 3, is characterized in that: in rhombus geometry, the space length of rhombus inner opposite angle line can regulate according to aircraft needs, and the corner angle of rhombus can regulate.

10. the aircraft according to any one of claim 1 to 9, is characterized in that: when wing axially rotate reach certain angle with fuselage plane time, wing can be used as the fluctuation support device of aircraft, i.e. alighting gear.

11. 1 kinds of aircraft according to any one of claim 1 to 10, is characterized in that: aircraft removes outside installation site that actuating device and wing occupy, all the other regions all can be used as installation or the carry region of flight auxiliary device or load thing.