CN110282126B

CN110282126B - Vertical take-off and landing frame structure of fixed-wing aircraft and vertical take-off and landing fixed-wing aircraft

Info

Publication number: CN110282126B
Application number: CN201910443654.4A
Authority: CN
Inventors: 陈宗; 周星宇; 朱正仁; 曹百旭; 王巍; 岳海龙
Original assignee: Shenyang Aerospace University
Current assignee: Shenyang Aerospace University
Priority date: 2019-05-27
Filing date: 2019-05-27
Publication date: 2023-02-03
Anticipated expiration: 2039-05-27
Also published as: CN110282126A

Abstract

The invention belongs to the technical field of aviation, and particularly relates to a vertical take-off and landing rack structure of a fixed-wing aircraft and the vertical take-off and landing fixed-wing aircraft. The invention aims to mutually make up the advantages of the vertical take-off and landing technology and the fixed-wing aircraft and overcome the defects of efficiency and safety of the conventional vertical take-off and landing technology.

Description

Vertical take-off and landing frame structure of fixed-wing aircraft and vertical take-off and landing fixed-wing aircraft

Technical Field

The invention belongs to the technical field of aviation, and particularly relates to a vertical take-off and landing rack structure of a fixed-wing aircraft and the vertical take-off and landing fixed-wing aircraft.

Background

The vertical take-off and landing technology can reduce or basically get rid of the dependence of the airplane on the runway, can take off and land only by a very small platform, and has great advantages in disaster relief or war.

The existing vertical take-off and landing technology used by large-sized aircrafts such as military aircrafts uses a vector nozzle, which has higher and higher requirements on engines and simultaneously has huge oil consumption. Small aircraft, such as helicopters, scooters, etc., use propellers to generate thrust by reverse thrust airflow, and aircraft using this design are difficult to accelerate to speeds as high as fixed wing aircraft. In order to enable the aircraft to have vertical take-off and landing capacity and high-speed flight performance of a fixed wing, the existing design directly installs propellers on the fixed wing aircraft like a helicopter, and although the problem of vertical take-off and landing is solved, the aircraft cannot achieve high-speed flight performance due to the exposed propellers.

Disclosure of Invention

In order to solve the technical problems, the invention provides a vertical take-off and landing rack structure of a fixed-wing aircraft and the vertical take-off and landing fixed-wing aircraft, aiming at mutually compensating the advantages of a vertical take-off and landing technology and the fixed-wing aircraft and overcoming the defects of efficiency and safety of the conventional vertical take-off and landing technology.

The invention is realized in such a way that the vertical take-off and landing frame structure of a fixed wing aircraft comprises a fuselage and wings, wherein the fuselage is of a hollow structure formed by a shell supported by a transverse keel and a longitudinal keel, the fuselage is provided with openings in the front, the rear, the left and the right, engines are respectively arranged on the openings of the front side and the rear side, the two wings are respectively fixed at the positions of the openings of the left side and the right side, and airflow is sprayed out from the openings of the left side and the right side to act on the two wings to form an upward lifting force.

Further, the casing includes casing and lower casing, goes up the streamline symmetrical structure that the casing is high both ends low in the middle of, and lower casing is mirror symmetry with last casing, horizontal fossil fragments have 4, and the last border and last casing joint of horizontal fossil fragments, lower border and lower casing joint, and two liang of a pair of distributions of horizontal fossil fragments are at the front side and the rear side in the space that last casing and lower casing are constituteed, horizontal fossil fragments center trompil, the engine is installed and is put every the centre bore of horizontal fossil fragments.

Furthermore, a plurality of small holes are uniformly formed around the central hole of each transverse keel, and the longitudinal keels sequentially penetrate through the small holes in the same positions on the four transverse keels to connect the transverse keels together.

Furthermore, every the aperture around the horizontal fossil fragments centre bore evenly is equipped with 6, is equipped with 6 vertical fossil fragments pass the aperture of same position on four horizontal fossil fragments in proper order, links together horizontal fossil fragments.

Furthermore, the overlooking structure of the wings is rectangular, the two wings are respectively arranged in the middle of the left opening and the right opening, and the distance between the lower edge of the wing and the lower edges of the openings at the two sides is 0.3-0.4 times of the height of the openings at the two sides.

Furthermore, the aircraft wing connecting structure further comprises 4 connecting plates, each connecting plate is L-shaped, the four connecting plates are distributed at four corners of the aircraft body, one end of each connecting plate is inserted and fixed into the corresponding transverse keel, and the other end of each connecting plate is connected with the corresponding wing.

The invention also provides a fixed wing airplane capable of vertically taking off and landing, which comprises the vertical taking off and landing rack structure of the fixed wing airplane and an electric control assembly, wherein the electric control assembly is arranged on the airplane body and comprises a power supply, an electric controller A and an electric controller B which are respectively connected with the power supply, a receiver A and a motor A which are both connected with the electric controller A, and a receiver B and a motor B which are both connected with the electric controller B, the motor A controls an engine at the front end of the airplane body, and the motor B controls an engine at the rear end of the airplane body.

Compared with the prior art, the invention has the advantages that:

1. the problem of vertical take-off and landing of the fixed-wing aircraft is solved, the technology of a gyroplane is not used, and the fixed-wing aircraft perfectly has the vertical take-off and landing technology;

2. in principle, compared with a rotorcraft, the system has high-efficiency vertical take-off and landing capability on a large airplane;

3. in the process of high-mobility flight operation, if the airplane stalls, the system can be started to solve the problem of stalling;

4. the connecting mode of the connecting plate and the specially-made wing can be changed, and the attack angle of the specially-made wing is changed to improve the lift coefficient of the wing, so that the efficiency is improved;

5. the distance between the special wing and the left and right openings can be changed, and the lift coefficient is improved;

6. the whole system is safer, and after the miniaturized design, the rotor is arranged in the fuselage, so that the safety is very high.

Drawings

FIG. 1 is a schematic cross-sectional view of a portion of a fuselage of the present invention;

FIG. 2 is a perspective view of the present invention;

FIG. 3 is a top view of the present invention;

FIG. 4 is a side view of the present invention;

fig. 5 is a schematic diagram of the connection relationship of the electronic control assembly according to the present invention.

Detailed Description

In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described in further detail with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.

Examples 1,

Referring to fig. 1, 2, 3 and 4, the invention provides a vertical take-off and landing frame structure of a fixed wing aircraft, which comprises a fuselage and wings 1, wherein the fuselage is of a hollow structure formed by a transverse keel 2 and a longitudinal keel 3 supporting a shell 4, the fuselage is opened in the front, the rear, the left and the right, engines 5 are respectively arranged on the front opening and the rear opening, the two wings 1 are respectively fixed at the positions of the left opening and the right opening, and airflow is sprayed out from the left opening and the right opening and acts on the two wings 1 to form an upward lifting force.

When the airplane is used for straight lifting, the two engines 5 blow oppositely, air flow is sucked into the fuselage from the outside and then blown out from the left opening and the right opening, the air flow acts on the wings to generate upward lift force, and the airplane is vertically lifted; when the airplane reaches a preset height, the engine on the rear side changes the rotation direction, airflow is sucked from the engine on the front side and pushed out from the engine on the rear side, forward thrust is generated, and the airplane flies normally; when the airplane lands vertically, the airplane is firstly stopped above a landing point, the rotating direction of the engine on the rear side of the airplane body is changed, the rotating speed of the two engines is gradually reduced, the lift force is gradually reduced, and the airplane lands vertically and safely.

In order to make fuselage structure more firm and can reduce the resistance of flight in-process, as technical scheme's improvement, casing 4 includes casing 401 and lower casing 402, goes up casing 401 and is the streamline symmetrical structure that the high both ends in the middle are low, and lower casing 402 is mirror symmetry with last casing 401, horizontal fossil fragments 2 have 4, and the last border of horizontal fossil fragments 2 is connected with last casing 401, and the lower border is connected with lower casing 402, and two liang of a pair of distributions of horizontal fossil fragments 2 are at the front side and the rear side in the space that last casing 401 and lower casing 402 constitute, and horizontal fossil fragments 2 center trompil, engine 5 installs and puts at every centre bore of horizontal fossil fragments 2.

As a specific implementation mode that horizontal fossil fragments 2 and longitudinal joist 3 were arranged, evenly set up a plurality of apertures along every around the horizontal fossil fragments 2 centre bore, the longitudinal joist 3 passes the aperture of same position on four horizontal fossil fragments 2 in proper order, links together horizontal fossil fragments 2.

Preferably, every the aperture around 2 centre holes of horizontal fossil fragments evenly is equipped with 6, is equipped with 6 vertical fossil fragments 3 passes the aperture of same position on four horizontal fossil fragments 2 in proper order, links together horizontal fossil fragments 2.

In order to better adapt to vertical lifting and vertical falling, the overlooking structure of the wings 1 is rectangular, the two wings 1 are respectively arranged at the middle positions of the left opening and the right opening, and the distance between the lower edge of each wing 1 and the lower edges of the openings at the two sides is 0.3-0.4 times of the height of the opening at the two sides.

As a better connection mode, as the improvement of technical scheme, still include 4 connecting plates 6, every connecting plate 6 all is the L shape, and four connecting plates 6 distribute in four angles of fuselage, the one end of connecting plate 6 insert fixedly to in the cross keel 2, the other end with wing 1 is connected.

Examples 2,

Referring to fig. 1 and 5, the invention provides a fixed wing aircraft capable of vertically taking off and landing, which comprises a vertical take-off and landing rack structure of the fixed wing aircraft and an electric control assembly, wherein the vertical take-off and landing rack structure of the fixed wing aircraft comprises a fuselage and wings 1, the fuselage is a hollow structure formed by a transverse keel 2 and a longitudinal keel 3 supporting a shell 4, the fuselage is opened at the front, the rear, the left and the right sides, an engine 5 is respectively arranged on the front opening and the rear opening, the two wings 1 are respectively fixed at the left opening and the right opening, and airflow is ejected from the left opening and the right opening to act on the two wings 1 to form an upward lifting force.

The electronic control assembly is arranged on the fuselage, is specifically arranged between two transverse keels 2 at the front end or the rear end of the fuselage, and comprises a power supply, an electric controller A and an electric controller B which are respectively connected with the power supply, a receiver A and a motor A which are all connected with the electric controller A, a receiver B and a motor B which are all connected with the electric controller B, wherein the motor A controls the engine 5 at the front end of the fuselage, and the motor B controls the engine 5 at the rear end of the fuselage.

The power supply provides electric power for the whole airplane, the receiver is responsible for receiving the signal requirement provided by the controller, the controller can be a remote controller or a controller arranged on the airplane body, the electric speed is adjusted according to the signal to adjust the rotating speed of a motor on the engine, and the motor drives the blades.

The vertical takeoff process comprises the following steps: the receivers A and B receive instructions, the electrically regulated motors A and B start the motors at the front end and the rear end according to instruction signals, the rotating speeds of the motors at the two ends are increased to suck more air flows and spray the air flows to the wings, lift force is provided, and when the lift force is larger than the weight of the airplane, the airplane vertically takes off.

Switching flight modes: the receiver B receives a reverse instruction, the electrically-controlled B receives the instruction and firstly decelerates the rear-end motor B and then accelerates and reverses, the airplane is in a gliding mode in a deceleration process, when the airplane accelerates and reverses, the motor A sucks air flow from the air inlet through the interior of the airplane body, the motor B discharges the air flow from the rear-end air inlet after accelerating, the whole airplane is accelerated until the air flow is accelerated to the wings, lift force can be provided to resist gravity, and the airplane flight mode is changed into a traditional airplane flight mode.

Landing: a. when the airplane lands in the traditional mode, the motors A and B are gradually decelerated, and the airplane lands safely under the control of a remote controller; b. the airplane is in a gliding mode, the airplane glides to the upper part of a designated landing point area, the motor B rotates forwards, both the motor A and the motor B rotate forwards at the moment, airflow is sucked in and discharged from left and right openings and sprayed to wings to generate lift force, the lift force is larger than the gravity of the airplane, the airplane body is stabilized to hover, the deceleration instruction is transmitted to the receiver A and the receiver B, the motors A and the B slow down, the lift force is also slowly reduced, and the airplane is gradually reduced until the airplane safely lands.

All equivalent changes made according to the structure, shape and principle of the invention are covered by the protection scope of the invention.

Claims

1. A vertical take-off and landing rack structure of a fixed wing aircraft is characterized by comprising a fuselage and wings (1), wherein the fuselage is of a hollow structure formed by a transverse keel (2) and a longitudinal keel (3) supporting a shell (4), the fuselage is opened in the front, the rear, the left and the right, engines (5) are respectively arranged on the opening of the front side and the opening of the rear side, the two wings (1) are respectively fixed at the positions of the opening of the left side and the opening of the right side, and airflow is sprayed out from the opening of the left side and the opening of the right side to act on the two wings (1) to form an upward lifting force; when the vertical take-off and landing rack structure of the fixed-wing airplane is used for vertical lift, the two engines blow oppositely, airflow is sucked into the airplane body from the outside and then blown out from the left opening and the right opening, the airflow acts on the wings to generate upward lift force, and the airplane vertically lifts; when the airplane reaches a preset height, the engine on the rear side changes the rotation direction, airflow is sucked from the engine on the front side and pushed out from the engine on the rear side, forward thrust is generated, and the airplane flies normally; when the airplane lands vertically, the airplane is firstly stopped above a landing point, the rotation direction of the engine at the rear side of the airplane body is changed, the rotating speeds of the two engines are gradually reduced, the lift force is gradually reduced, and the airplane lands vertically and safely.

2. The vtol frame structure of a fixed-wing aircraft according to claim 1, wherein the housing (4) comprises an upper housing (401) and a lower housing (402), the upper housing (401) is a streamline symmetrical structure with a high middle and two low ends, the lower housing (402) is mirror-symmetrical to the upper housing (401), 4 transverse keels (2) are provided, the upper edge of each transverse keel (2) is connected with the upper housing (401), the lower edge of each transverse keel is connected with the lower housing (402), pairs of transverse keels (2) are distributed on the front side and the rear side of a space formed by the upper housing (401) and the lower housing (402), the transverse keels (2) are centrally provided with holes, and the engine (5) is installed at the central hole position of each pair of transverse keels (2).

3. The VTOL rack structure of the fixed-wing aircraft according to claim 2, characterized in that a plurality of small holes are uniformly arranged along the circumference of the central hole of each transverse keel (2), and the longitudinal keel (3) passes through the small holes at the same position on four transverse keels (2) in sequence to connect the transverse keels (2) together.

4. The VTOL frame structure of a fixed-wing aircraft as claimed in claim 3, wherein there are 6 holes uniformly arranged around the center hole of each of the transverse keels (2), and there are 6 longitudinal keels (3) sequentially passing through the holes at the same position on the four transverse keels (2) to connect the transverse keels (2) together.

5. The VTOL rack structure of a fixed-wing aircraft according to claim 1, characterized in that the top view structure of the wings (1) is rectangular, two wings (1) are respectively installed at the middle position of the left opening and the right opening, and the distance between the lower edge of the wing (1) and the lower edge of the two openings is 0.3-0.4 times of the height of the two openings.

6. The vtol frame structure of a fixed-wing aircraft according to claim 1, further comprising 4 connecting plates (6), each connecting plate (6) having an L-shape, four connecting plates (6) being distributed at four corners of the fuselage, one end of each connecting plate (6) being inserted and fixed into the cross keel (2) and the other end being connected to the wing (1).

7. The fixed wing aircraft of VTOL, characterized by, includes the VTOL rack structure and the electric control assembly of the fixed wing aircraft of claim 1, the electric control assembly sets up on the fuselage, including the power, the electricity that is connected respectively with the power is transferred A, electricity to B, all with the electricity transfer A receiver A and the motor A of being connected, all with electricity transfer B receiver B and the motor B of being connected, motor A control the engine (5) of fuselage front end, motor B control the engine (5) of fuselage rear end, wherein, the vertical take-off process is as follows: the receivers A and B receive instructions, the electric regulators A and B start the motors at the front end and the rear end according to instruction signals, the rotating speeds of the motors at the two ends are increased, more air flows are sucked and sprayed to the wings, lift force is provided, and when the lift force is larger than the weight of the airplane, the airplane can take off vertically; the flight mode switches as follows: the receiver B receives a reverse rotation instruction, the electric controller B receives the instruction and first decelerates the rear end motor B and then accelerates and reverses, the airplane is in a gliding mode in a deceleration process, when the airplane accelerates and reverses, the motor A sucks airflow from the air inlet through the interior of the airplane body, the motor B exhausts the airflow from the rear end air inlet after accelerating the airflow, the whole airplane is accelerated until the airflow is accelerated to the wings, lift force can be provided to resist gravity, and the airplane becomes a traditional airplane flight mode; the falling mode is as follows: a. when the airplane lands in the traditional mode, the motors A and B are gradually decelerated, and the airplane lands safely under the control of a remote controller; b. the airplane is in a gliding mode, the airplane glides to the upper part of a designated landing point area, the motor B rotates forwards, both the motor A and the motor B rotate forwards at the moment, airflow is sucked in and discharged from left and right openings and sprayed to wings to generate lift force, the lift force is larger than the gravity of the airplane, the airplane body is stabilized to hover, the deceleration instruction is transmitted to the receiver A and the receiver B, the motors A and the B slow down, the lift force is also slowly reduced, and the airplane is gradually reduced until the airplane safely lands.