CN113602499A

CN113602499A - Multipurpose attack and transportation integrated aircraft

Info

Publication number: CN113602499A
Application number: CN202111079743.9A
Authority: CN
Inventors: 尚之灏
Original assignee: Individual
Current assignee: Individual
Priority date: 2021-09-15
Filing date: 2021-09-15
Publication date: 2021-11-05
Anticipated expiration: 2041-09-15
Also published as: CN113602499B

Abstract

The utility model relates to a multipurpose attack transportation integration aircraft which characterized in that: including the aircraft body, aircraft body upper portion has set gradually passenger cabin, oil tank, intake duct, engine from the past backward, unmanned aerial vehicle is installed to the aircraft body, radar and avionics equipment are installed to aircraft body lower part, radar and avionics equipment are located the passenger cabin lower part, the aircraft body has the modular cabin body that holds, it can hold at least one of accurate guidance guided missile, operation personnel, ground operation equipment, container to hold the cabin body, unmanned aerial vehicle can be right the accurate guidance guided missile guides. The aircraft of this application accurate strike ability reinforce, firepower is lasting, the radius of operation is big, does not need the aircraft nose to aim the transmission ammunition, can be launched by unmanned aerial vehicle guide outside ground firepower net to the target is hit to the accuracy, thereby the volume of carrying the bullet realizes longer suppression time greatly, holds the cabin body and makes the aircraft compromise operation and tactics transport capacity.

Description

Multipurpose attack and transportation integrated aircraft

Technical Field

The utility model relates to an aircraft technical field especially relates to multipurpose attack transportation integration aircraft.

Background

From world war I to now, the three basic tasks of ground attacking machines-attack of armor targets, attack of migrant personnel and attack of buildings and places. The main scenes are under the conditions of low intensity in the air and high intensity on the ground.

The existing aircrafts capable of being used as attackers are various, such as A-10 type medium-low value subsonic combat attackers, check and attack integrated unmanned aerial vehicles and armed helicopters, wherein the armed helicopters are traditional short-distance large-scale land battle weapons, the intensity of the armed helicopters is low, the pressing time and the survival capability are not very good, short-distance operation is needed, the operation radius is extremely low, the intensity of the check and attack integrated unmanned aerial vehicles is extremely low, the attack accuracy of the A-10 type medium-low value subsonic combat attackers is low, and the aircraft nose is required to be aimed at in a short distance for attack.

Analysis shows that the three attackers have obvious disadvantages, and more advanced attackers are needed.

Therefore, the multipurpose attack and transportation integrated aircraft is provided to achieve the purposes of strong accurate hitting capacity, lasting firepower, large combat radius and the like.

Disclosure of Invention

To address at least one of the above technical problems, the present disclosure provides a multipurpose attack transportation integrated aircraft.

The technical scheme adopted by the invention is as follows:

multipurpose attack transportation integration aircraft, including the aircraft body, aircraft body upper portion has set gradually passenger cabin, oil tank, intake duct, engine from the past backward, unmanned aerial vehicle is installed to the aircraft body, radar and avionics equipment are installed to aircraft body lower part, radar and avionics equipment are located the passenger cabin lower part, the aircraft body has the modular cabin body that holds, it can hold at least one of accurate guidance guided missile, operation personnel, ground operation equipment, container to hold the cabin body, unmanned aerial vehicle can be right the accurate guidance guided missile guides.

Preferably, unmanned aerial vehicle includes investigation unmanned aerial vehicle and/or scouting and beating integrative unmanned aerial vehicle, investigation unmanned aerial vehicle install in the passenger cabin with between the oil tank, laser weapon is installed to the aircraft body, scouting and beating integrative unmanned aerial vehicle install in avionics equipment rear end, laser weapon install in scouting and beating integrative unmanned aerial vehicle rear end, it is located to hold the cabin body laser weapon rear end.

Preferably, both ends of the aircraft body have movable wing tip plates that can be tilted at a predetermined angle relative to the wing.

Preferably, the wingtip plate is bent downward and perpendicular to the wing.

Preferably, aircraft body top has first mounting groove, investigation unmanned aerial vehicle install in the first mounting groove, gasbag storage bin has in the first mounting groove, install in the gasbag storage bin and launch the gasbag, the gasbag storage bin is located investigation unmanned aerial vehicle below, launch the gasbag be used for with investigation unmanned aerial vehicle launches out first mounting groove.

Preferably, the ejection air bags are multiple, and the ejection air bags are arranged below wings and an abdomen on two sides of the investigation unmanned aerial vehicle.

Preferably, the first mounting groove is provided with a mounting clamping groove, and the wheels of the reconnaissance unmanned aerial vehicle are clamped into the mounting clamping groove.

Preferably, the upper part of the first installation groove is provided with a sliding door which can slide relative to the first installation groove so as to open or close the first installation groove.

Preferably, the bottom of the aircraft body is provided with a second installation groove, the scouting and hitting integrated unmanned aerial vehicle is installed in the second installation groove, the bottom of the second installation groove is provided with two turnover doors, the two turnover doors can turn over relative to the second installation groove so as to open or close the second installation groove, and the turning directions of the two turnover doors are opposite;

the two opposite side walls of the second mounting groove are respectively provided with a hydraulic driving device, the end part of an output shaft of each hydraulic driving device is provided with a limiting arc-shaped pressing plate, and the limiting arc-shaped pressing plates on the two sides are used for tightly pushing the body of the unmanned aerial vehicle and limiting.

Preferably, the spy drone is configured as a flexible frequency transceiver configured to selectively change a communication frequency of the flexible frequency transceiver, the flexible frequency transceiver configured to communicate with the aircraft body and the scout drone, and to change a communication frequency between the spy drone and the scout drone.

In summary, the present application has the following beneficial effects: the aircraft of this application accurate strike ability reinforce, firepower is lasting, the radius of operation is big, does not need the aircraft nose to aim the transmission ammunition, can be launched by unmanned aerial vehicle guide outside ground firepower net to the target is hit to the accuracy, thereby the volume of carrying the bullet realizes longer suppression time greatly, holds the cabin body and makes the aircraft compromise operation and tactics transport capacity.

Drawings

The accompanying drawings, which are included to provide a further understanding of the disclosure and are incorporated in and constitute a part of this specification, illustrate exemplary embodiments of the disclosure and together with the description serve to explain the principles of the disclosure.

FIG. 1 is a schematic view of the internal structure of the present invention;

FIG. 2 is a schematic structural view of the present invention;

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

FIG. 4 is a top view of the first mounting groove of the present invention;

FIG. 5 is a top view of a second mounting groove of the present invention;

figure 6 is a side view of the limit stop arc of the present invention.

The labels in the figure are: 1 is the passenger cabin, 2 is the oil tank, 3 is the intake duct, 4 is the engine, 5 is the radar, 6 is avionics equipment, 7 is for holding the cabin body, 8 is investigation unmanned aerial vehicle, 9 is for scouting and beating integrative unmanned aerial vehicle, 10 is the laser weapon, 11 is the wing tip board, 12 is first mounting groove, 13 is gasbag storage bin, 14 is installation card groove, 15 is the second mounting groove, 16 is the turnover door, 17 is the lateral wall, 18 is hydraulic drive device, 19 is the output shaft, 20 is spacing arc clamp plate.

Detailed Description

The present disclosure will be described in further detail with reference to the drawings and embodiments. It is to be understood that the specific embodiments described herein are for purposes of illustration only and are not to be construed as limitations of the present disclosure. It should be further noted that, for the convenience of description, only the portions relevant to the present disclosure are shown in the drawings.

It should be noted that the embodiments and features of the embodiments in the present disclosure may be combined with each other without conflict. The present disclosure will be described in detail below with reference to the accompanying drawings in conjunction with embodiments.

Example 1

As shown in fig. 1 to 4, the multipurpose attack transportation integrated aircraft comprises an aircraft body, a cabin 1, an oil tank 2, an air inlet 3 and an engine 4 are sequentially arranged on the upper portion of the aircraft body from front to back, an unmanned aerial vehicle is installed on the aircraft body, a radar 5 and an avionics device 6 are installed on the lower portion of the aircraft body, the radar 5 and the avionics device 6 are located on the lower portion of the cabin 1, the aircraft body is provided with a modular accommodating cabin body 7, the accommodating cabin body 7 can accommodate at least one of an accurately guided missile (not shown in the figure), a fighter, a ground combat device (not shown in the figure) and a container (not shown in the figure), the unmanned aerial vehicle can guide the accurately guided missile, the guided missile comprises an air-to-ground missile, a cruise missile, an anti-ship missile and an anti-radiation missile, the aircraft body has a total length of 18 meters, a total height of 4.8 meters and a belly height of 0.8 meter from the ground, the length of the accommodating cabin body 7 is 7.45 meters, the width is 2.45 meters, the height is 2 meters, the conventional maximum takeoff weight is 38 tons, the empty weight is 17 tons, the number of flight crew members 3 including pilots, weapon controllers and unmanned aerial vehicle navigation controllers, ground combat equipment such as a mountain cat assault vehicle and the engine 4 adopts two turbofan 31 engines. The whole cross section of the aircraft body is hexagonal and is similar to the cross section of a diamond, so that the aircraft body is beneficial to invisibility.

The setting of the accommodating cabin body 7 effectively increases the missile carrying capacity, the persistent combat capability is strong, the firepower suppression time is long, the unmanned aerial vehicle can detect remotely, and can guide guided missiles to achieve accurate combat, the aircraft does not need to be close to a battlefield, the accurate combat can be achieved remotely, meanwhile, the accommodating cabin body 7 of the aircraft can also be used for transportation, such as transportation of a tornado assault car, assault combat personnel and containers, the size of the transportable tornado assault car comprises 3.2mX1.67mX1.5m and 4.1mX1.75mX1.55m, the size of the transportable container is 2.01mX1.54mX1.63m, the lowest standard can transport 24 combat personnel, and the highest standard can transport 49 combat personnel.

Full air-to-ground mode: the containing cabin body 7 can be fully loaded with 36 per air-to-ground missile;

cruise missile mode: the accommodating cabin body 7 can carry 4 cruise bombs with 6 meters;

the man-bomb mixing mode comprises the following steps: the accommodating cabin body 7 can carry ammunition and fighters at the same time;

container mode: the accommodating cabin 7 can carry 4 LD3 containers;

full soldier mode of operation: the accommodating cabin body 7 can transport 48 fighters;

assault vehicle transportation mode: the accommodating cabin body 7 can transport 2 4X4 cat assault cars;

mixing mode of people and containers: the containment vessel 7 can carry 2 LD3 containers and 24 people.

Further, unmanned aerial vehicle includes investigation unmanned aerial vehicle 8, and/or scout and beat integrative unmanned aerial vehicle 9, investigation unmanned aerial vehicle 8 is installed between passenger cabin 1 and oil tank 2, laser weapon 10 is installed to the aircraft body, scout and beat integrative unmanned aerial vehicle 9 and install in avionics equipment 6 rear end, laser weapon 10 is installed in scout and beat integrative unmanned aerial vehicle 9 rear end, it is located laser weapon 10 rear end to hold cabin body 7, so set up, the firepower suppression intensity of aircraft has further been strengthened, scout and beat integrative unmanned aerial vehicle 9 and can high-efficiently attack mobile high value person, laser weapon 10 can realize effectively defending by oneself.

Further, the wing tip plates 11 are movable at the wing ends of two ends of the aircraft body, the wing tip plates 11 can incline at a preset angle relative to the wings, can be perpendicular to the wings and can also form a certain angle with the wings, the wing span of the wing including the wing tip plates 11 is 22.5 meters, the length of the wing tip plates 11 is 1 meter, when the aircraft is cruising, flying on the ground and stopping, the wing tip plates 11 are bent downwards, the cruising resistance is low, the ground-attaching timeliness is good, and when the aircraft takes off and lands, the wing tip plates 11 are laid flat, so that the taking-off and landing speed is low. Optionally, the wing tip plate 11 can be bent upward relative to the wing, and may be perpendicular to the wing, or may form a certain angle with the wing, so that the formation of the wing tip vortex can be improved, and the flight stability and fuel efficiency can be improved.

Furthermore, the top of the aircraft body is provided with a first mounting groove 12, the investigation unmanned aerial vehicle 8 is mounted in the first mounting groove 12, the first mounting groove 12 is internally provided with an air bag storage bin 13, an ejection air bag (not shown in the figure) is mounted in the air bag storage bin 13, the air bag storage bin 13 is positioned below the investigation unmanned aerial vehicle 8, and the ejection air bag is used for ejecting the investigation unmanned aerial vehicle 8 out of the first mounting groove 12, so that the investigation unmanned aerial vehicle 8 can be actively ejected and separated from the aircraft body, after ejection, a flight crew controls the investigation unmanned aerial vehicle 8 to fly away and perform investigation and guidance tasks, the inflation principle of the ejection air bag is similar to that of an automobile safety air bag, only the triggering conditions are different, the automobile safety air bag transmits a signal to a microprocessor cpu through a sensor through collision, the cpu further controls a gas generator to inflate the safety air bag, and the inflation of the ejection air bag is controlled by an aircraft driver, the driver directly sends trigger signal for the treater of machine-carrying through control system, and the treater directly controls gas generator again and aerifys ejection gasbag in the twinkling of an eye, and then will investigate unmanned aerial vehicle 8 and launch and break away from the aircraft body. Optionally, gasbag warehouse 13 is a plurality of, for example all is provided with gasbag warehouse 13 in investigation unmanned aerial vehicle 8's both sides wing and ventral below, all is provided with the ejection gasbag in each gasbag warehouse 13, so sets up, guarantees that the ejection force that investigation unmanned aerial vehicle 8 received is more balanced, is ejected more effectively and breaks away from the aircraft body. Because the aircraft body is in flight state, investigation unmanned aerial vehicle 8 is popped out first mounting groove 12 and relies on inertia to continue to move forward, receives the start-up data that the control system of aircraft body sent to realize investigation unmanned aerial vehicle 8's flight.

Further, first mounting groove 12 has mounting groove 14, and in investigation unmanned aerial vehicle 8's wheel clamped into mounting groove 14, so set up for investigation unmanned aerial vehicle 8 reliable and stable set up in first mounting groove 12, avoid the accident to rock. When the ejection air bag expands, the wheels of the investigation unmanned aerial vehicle 8 overcome the resistance with the mounting slot 14, so as to be separated from the first mounting slot 12.

Further, first mounting groove 12 upper portion has a sliding door (not shown in the figure), and the sliding door can slide for first mounting groove 12 to realize opening or closing of first mounting groove 12, so set up, when need not to launch reconnaissance unmanned aerial vehicle 8, the sliding door is closed, can reduce flight resistance, when needing to launch reconnaissance unmanned aerial vehicle 8, the sliding door is opened in the control slip, can control reconnaissance unmanned aerial vehicle 8 to launch and break away from, launch and break away from the completion after, close the sliding door can.

Example 2

As shown in fig. 1, 5 and 6, on the basis of embodiment 1, the bottom of the aircraft body is provided with a second installation groove 15, the scouting and hitting integrated unmanned aerial vehicle 9 is installed in the second installation groove 15, the bottom of the second installation groove 15 is provided with two turnover doors 16, the two turnover doors 16 can be turned over relative to the second installation groove 15 to open or close the second installation groove 15, and the turning directions of the two turnover doors 16 are opposite; the two opposite side walls 17 of the second mounting groove 15 are respectively provided with a hydraulic driving device 18, the end part of an output shaft 19 of each hydraulic driving device 18 is provided with a limiting arc-shaped pressing plate 20, the limiting arc-shaped pressing plates 20 on the two sides are used for tightly pushing against the body of the observing and hitting integrated unmanned aerial vehicle 9 to form limiting, and the limiting arc-shaped pressing plates 20 are matched with the body of the observing and hitting integrated unmanned aerial vehicle 9; so set up, need not the release and scout when beating integrative unmanned aerial vehicle 9, two turnover doors 16 close, flight resistance can be reduced, need the release to scout when beating integrative unmanned aerial vehicle 9, the hydraulic drive device 18 of control both sides wall 17 returns and contracts, make spacing arc clamp plate 20 of both sides loosen and scout and beat integrative unmanned aerial vehicle 9, two turnover doors 16 are opened in the turnover of controlling the upset again, can control and scout and beat integrative unmanned aerial vehicle 9 and break away from the aircraft body through the dead weight, break away from the completion after, close two turnover doors 16 can, spacing arc clamp plate 20 makes to scout and beat integrative unmanned aerial vehicle 9 reliable and stable setting in second mounting groove 15, avoid the accident to rock.

Example 3

On the basis of

embodiment

1 or 2, the scout drone 8 is configured as a flexible frequency transceiver configured to selectively change a communication frequency of the flexible frequency transceiver, the flexible frequency transceiver being configured to communicate with the aircraft body and the scout-and-play drone 9, and to change the communication frequency between the scout drone 8 and the scout-and-play drone 9.

The investigation unmanned aerial vehicle 8 is used as a communication relay station, the frequency between the investigation unmanned aerial vehicle 8 and an aircraft body and between the investigation unmanned aerial vehicle 8 and a scouting and hitting integrated unmanned aerial vehicle 9 can be changed, and the communication is protected smoothly when the communication is interfered by electrons, so that the scouting and hitting integrated unmanned aerial vehicle 9 is guided to clear a target at a fixed point.

In the description herein, reference to the description of the terms "one embodiment/mode," "some embodiments/modes," "example," "specific example," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment/mode or example is included in at least one embodiment/mode or example of the application. In this specification, the schematic representations of the terms used above are not necessarily intended to be the same embodiment/mode or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments/modes or examples. Furthermore, the various embodiments/aspects or examples and features of the various embodiments/aspects or examples described in this specification can be combined and combined by one skilled in the art without conflicting therewith.

Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present application, "plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.

It will be understood by those skilled in the art that the foregoing embodiments are merely for clarity of illustration of the disclosure and are not intended to limit the scope of the disclosure. Other variations or modifications may occur to those skilled in the art, based on the foregoing disclosure, and are still within the scope of the present disclosure.

Claims

1. Multipurpose attack transportation integration aircraft, its characterized in that: including the aircraft body, aircraft body upper portion has set gradually passenger cabin (1), oil tank (2), intake duct (3), engine (4) from the past backward, unmanned aerial vehicle is installed to the aircraft body, radar (5) and avionics equipment (6) are installed to aircraft body lower part, radar (5) and avionics equipment (6) are located passenger cabin (1) lower part, the aircraft body has the modular cabin body (7) that holds, hold cabin body (7) can hold at least one of accurate guidance guided missile, fighter, ground combat equipment, container, unmanned aerial vehicle can right the accurate guidance guided missile guides.

2. The multi-purpose attack transport integrated aircraft of claim 1, wherein: unmanned aerial vehicle includes investigation unmanned aerial vehicle (8) and/or scouting and beating integrative unmanned aerial vehicle (9), investigation unmanned aerial vehicle (8) install in passenger cabin (1) with between oil tank (2), laser weapon (10) are installed to the aircraft body, scouting and beating integrative unmanned aerial vehicle (9) install in avionics equipment (6) rear end, laser weapon (10) install in scouting and beating integrative unmanned aerial vehicle (9) rear end, it is located to hold cabin body (7) laser weapon (10) rear end.

3. The multi-purpose attack transport integrated aircraft of claim 2, wherein: the wing ends of both ends of the aircraft body are provided with movable wing tip plates (11), and the wing tip plates (11) can be inclined at a preset angle relative to the wings.

4. The multi-purpose attack transport integrated aircraft of claim 3, wherein: the wingtip plate (11) is bent downwards.

5. The multipurpose attack transport integrated aircraft according to any one of claims 2 to 4, wherein: aircraft body top has first mounting groove (12), investigation unmanned aerial vehicle (8) install in first mounting groove (12), gasbag storage bin (13) have in first mounting groove (12), install in gasbag storage bin (13) and launch the gasbag, gasbag storage bin (13) are located investigation unmanned aerial vehicle (8) below, it is used for with to launch investigation unmanned aerial vehicle (8) first mounting groove (12).

6. The multi-purpose attack transport integrated aircraft of claim 5, wherein: the ejection air bags are multiple, and the ejection air bags are arranged below wings on two sides and an abdomen of the investigation unmanned aerial vehicle (8).

7. The multi-purpose attack transport integrated aircraft of claim 5, wherein: the first mounting groove (12) is provided with a mounting clamping groove (14), and the wheel of the investigation unmanned aerial vehicle (8) is clamped into the mounting clamping groove (14).

8. The multi-purpose attack transport integrated aircraft of claim 5, wherein: the upper part of the first installation groove (12) is provided with a sliding door which can slide relative to the first installation groove (12) so as to realize the opening or closing of the first installation groove (12).

9. The multipurpose attack transport integrated aircraft according to any one of claims 2 to 4, wherein: the bottom of the aircraft body is provided with a second installation groove (15), the observing and hitting integrated unmanned aerial vehicle (9) is installed in the second installation groove (15), the bottom of the second installation groove (15) is provided with two turnover doors (16), the two turnover doors (16) can be turned over relative to the second installation groove (15) so as to open or close the second installation groove (15), and the turning directions of the two turnover doors (16) are opposite;

hydraulic drive device (18) are all installed to double-phase relative lateral wall (17) of second mounting groove (15), output shaft (19) tip of hydraulic drive device (18) all has spacing arc clamp plate (20), both sides spacing arc clamp plate (20) are used for the top tightly observe the fuselage of beating integrative unmanned aerial vehicle (9) and form spacingly.

10. The multipurpose attack transport integrated aircraft according to any one of claims 2 to 4, wherein: the scout drone (8) is configured as a flexible frequency transceiver configured to selectively change a communication frequency of the flexible frequency transceiver, the flexible frequency transceiver being configured to communicate with the aircraft body and the scout-and-play drone (9) and to change a communication frequency between the scout drone (8) and the scout-and-play drone (9).