CN111890858A - Cross-medium aircraft - Google Patents
Cross-medium aircraft Download PDFInfo
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- CN111890858A CN111890858A CN202010826220.5A CN202010826220A CN111890858A CN 111890858 A CN111890858 A CN 111890858A CN 202010826220 A CN202010826220 A CN 202010826220A CN 111890858 A CN111890858 A CN 111890858A
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- 230000007246 mechanism Effects 0.000 claims abstract description 18
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- UJCHIZDEQZMODR-BYPYZUCNSA-N (2r)-2-acetamido-3-sulfanylpropanamide Chemical compound CC(=O)N[C@@H](CS)C(N)=O UJCHIZDEQZMODR-BYPYZUCNSA-N 0.000 claims description 3
- 241001669680 Dormitator maculatus Species 0.000 claims description 3
- 230000007704 transition Effects 0.000 claims description 3
- 239000007787 solid Substances 0.000 claims 1
- 238000000034 method Methods 0.000 abstract description 10
- 230000008569 process Effects 0.000 abstract description 8
- 230000009471 action Effects 0.000 description 3
- 230000007123 defense Effects 0.000 description 3
- 230000008602 contraction Effects 0.000 description 2
- 238000011835 investigation Methods 0.000 description 2
- 235000015842 Hesperis Nutrition 0.000 description 1
- 235000012633 Iberis amara Nutrition 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60F—VEHICLES FOR USE BOTH ON RAIL AND ON ROAD; AMPHIBIOUS OR LIKE VEHICLES; CONVERTIBLE VEHICLES
- B60F5/00—Other convertible vehicles, i.e. vehicles capable of travelling in or on different media
- B60F5/02—Other convertible vehicles, i.e. vehicles capable of travelling in or on different media convertible into aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
- B63G—OFFENSIVE OR DEFENSIVE ARRANGEMENTS ON VESSELS; MINE-LAYING; MINE-SWEEPING; SUBMARINES; AIRCRAFT CARRIERS
- B63G8/00—Underwater vessels, e.g. submarines; Equipment specially adapted therefor
- B63G8/001—Underwater vessels adapted for special purposes, e.g. unmanned underwater vessels; Equipment specially adapted therefor, e.g. docking stations
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
- B63G—OFFENSIVE OR DEFENSIVE ARRANGEMENTS ON VESSELS; MINE-LAYING; MINE-SWEEPING; SUBMARINES; AIRCRAFT CARRIERS
- B63G8/00—Underwater vessels, e.g. submarines; Equipment specially adapted therefor
- B63G8/001—Underwater vessels adapted for special purposes, e.g. unmanned underwater vessels; Equipment specially adapted therefor, e.g. docking stations
- B63G2008/002—Underwater vessels adapted for special purposes, e.g. unmanned underwater vessels; Equipment specially adapted therefor, e.g. docking stations unmanned
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- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention discloses a medium-crossing aircraft, which comprises an aircraft body, wherein the aircraft body is connected with a hydrofoil through an accommodating mechanism, the aircraft body is connected with a main wing through a discarding mechanism, the aircraft body is also provided with a water inlet and an air inlet, the tail end of the aircraft body is also provided with an air nozzle and a water jet, the air inlet is communicated with the air nozzle through an air passage, the water inlet is communicated with the water jet through a water passage, and the rear end of the aircraft body is also connected with a tail vane; the aircraft is added with a main wing to provide lift force for the air working condition, and the main wing is an upper single wing to reduce water-entering impact. The main wing lift force can be adjusted by adjusting the pitching of the aircraft to change the main wing attack angle. The water/underwater cross-medium engine technology is adopted, and the tail end is provided with an air jet and a water jet to match the propulsion mode of air jet and underwater water jet. The front part of the aircraft is additionally provided with retractable hydrofoils for providing enough lift force in the takeoff process, and the hydrofoils are retracted to reduce the navigation resistance under the stable operation working condition. When the aircraft attacks in water, the main wing is abandoned, the navigation resistance is reduced, and the navigation speed is increased.
Description
Technical Field
The invention belongs to the technical field of aircrafts, and particularly relates to a cross-medium aircraft.
Background
The cross-medium aircraft is a novel cross-medium weapon which is launched from water or underwater and can navigate in the air and underwater. The method is characterized in that investigation of enemy warships can be avoided during underwater navigation, and the method has good concealment; the device has higher navigation speed and efficiency when navigating in the air outside the investigation range of the enemy warship.
Generally, due to the reasons of large navigation resistance, small platform space, weight limitation and the like, the range of a traditional underwater vehicle is smaller than that of an aerial missile, so that an enemy defense ring cannot be effectively broken through, and the position of a mother boat is easily exposed after the vehicle is launched. For missiles which are attacked from the air, enemy boat formation has a three-dimensional air defense system which covers near, medium and long distances, low, medium and high airspaces, and the penetration difficulty is high.
In addition, various flight-assisted aircrafts have been equipped at home and abroad at present, air-operated vehicles such as rockets, gliders and the like are used for assisting flight of the traditional aircrafts, and the vehicles are launched by a water surface platform, and enter water after assisting flight in the air for a long distance to realize accurate underwater striking. However, the assisted flying vehicle cannot be launched underwater under the limitation of the platform, and only can work in a single mode across media from the air to the water in one direction, so that the defects of poor launching concealment, lack of defense burst means and the like are caused, and the combat effectiveness of the assisted flying vehicle is directly influenced.
And the range of the traditional underwater vehicle is smaller than that of an aerial missile due to the reasons of large navigation resistance, small platform space, weight limitation and the like.
Disclosure of Invention
The invention aims to provide a cross-medium navigation vehicle, which realizes cross-medium navigation through a hydrofoil and a main wing, and has higher universality and take-off and landing speeds.
The invention adopts the technical scheme that the cross-medium aircraft comprises an aircraft body, wherein the aircraft body is connected with a hydrofoil through an accommodating mechanism, the aircraft body is connected with a main wing through a discarding mechanism, the aircraft body is also provided with a water inlet and an air inlet, the tail end of the aircraft body is also provided with an air nozzle and a water jet, the air inlet is communicated with the air nozzle through an air passage, the water inlet is communicated with the water jet through a water passage, and the rear end of the aircraft body is also connected with a tail vane.
The invention is also characterized in that:
the air channel is connected with an air jet propulsion system, and the water channel is connected with a water jet propulsion system.
Abandon the mechanism including seting up the recess a in the organism, two apron a of recess a in-connection, the organism inner wall all connects a propulsion motor a towards every apron a direction, a ball a is all connected to every propulsion motor a output shaft, a screw nut an of connecting on every ball a, every screw nut an outer wall connection buckle, the buckle upper end is L type structure, two L type structures are relative, an L type support is connected in every L type structure contact, two L type support fixed connection main wings.
The containing mechanism comprises a groove b which is arranged in the machine body and has the same opening as the hydrofoil, the groove b is connected with two propulsion motors b in parallel, each propulsion motor b outputs a ball screw b in an output shaft, a screw nut b is connected onto each ball screw b, one end of a crank is connected between the two screw nuts b through a screw rod, the hydrofoil is connected with the other end of the crank, and the length and the height of the groove b are not less than the length and the height of the crank.
The machine body is in a long cylindrical revolving body configuration and comprises three parts: head, middle part, afterbody, head are located the organism front end, are circular-arc transition curve, and length is 1/12 of organism length, and the afterbody is the shrink section, is located the organism rear end, and length is 1/4 of organism length, connects the tail rudder on the afterbody, connects hydrofoil, main wing on the middle part.
The water inlet is arranged at the position of the tail part close to the middle part length 1/5, the air inlet is arranged at the joint of the tail part and the middle part, and the water inlet and the air inlet are circumferentially separated by 180 degrees on the machine body.
The main wing and the hydrofoil are both rectangular in shape, and the cross sections of the main wing and the hydrofoil are both NACA wing shapes.
The hydrofoil is attached at the forward end 1/10 of the body, with the main wing and hydrofoil being spaced 180 ° circumferentially on the body.
The cross-medium aircraft has the beneficial effects that:
the aircraft is added with a main wing to provide lift force for the air working condition, and the main wing is an upper single wing to reduce water-entering impact. When the aircraft is in the underwater attack working condition, the main wing is abandoned to reduce the navigation resistance and increase the navigation speed. In order to simplify the design, the main wing is in a rectangular wing form, and the main wing attack angle is changed by adjusting the pitching of the aircraft so as to achieve the purpose of adjusting the lift force of the main wing. The water/underwater medium crossing engine technology is adopted, an air inlet and a water inlet are additionally arranged at the front part of a tail contraction section of the aircraft, and an air jet and a water jet are arranged at the tail end of the aircraft to match the propulsion mode of air jet and underwater water jet. The front part of the aircraft is additionally provided with retractable hydrofoils for providing enough lift force in the takeoff process, and the hydrofoils are retracted to reduce the navigation resistance under the stable operation working condition.
Drawings
FIG. 1 is a front view of a cross-media vehicle of the present invention;
FIG. 2 is a schematic view of a disposal mechanism and a storage mechanism according to the present invention.
In the figure, 1, a machine body, 2, a hydrofoil, 3, a main wing, 4, a tail vane, 5, a water inlet, 6, an air inlet, 7, a water spray nozzle, 8, an air spray nozzle, 9, a groove a, 10, a cover plate a, 11, a propelling motor a, 12, a ball screw a, 13, a screw nut a, 14, a buckle, 15, an L-shaped bracket, 16, a groove b, 17, a propelling motor b, 18, a ball screw b, 19, a screw nut b, 20 and a crank.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings and specific embodiments.
The invention relates to a medium crossing aircraft, which comprises an aircraft body 1, wherein the aircraft body 1 is connected with a hydrofoil 2 through an accommodating mechanism, the aircraft body 1 is connected with a main wing 3 through a discarding mechanism, the aircraft body 1 is also provided with a water inlet 5 and an air inlet 6, the tail end of the aircraft body 1 is also provided with an air nozzle 8 and a water jet 7, the air inlet 6 is communicated with the air nozzle 8 through an air passage, the water inlet 5 is communicated with the water jet 7 through a water passage, and the rear end of the aircraft body 1 is also connected with a tail vane 4.
The air channel is connected with an air jet propulsion system, and the water channel is connected with a water jet propulsion system.
As shown in fig. 2, the discarding mechanism includes a groove a9 opened in the body 1, two cover plates a10 are connected in the groove a9, the inner wall of the body 1 is connected with a propulsion motor a11 towards each cover plate a10, the output shaft of each propulsion motor a11 is connected with a ball screw a12, each ball screw a12 is connected with a screw nut a13, the outer wall of each screw nut a13 is connected with a buckle 14, the upper end of the buckle 14 is in an L-shaped structure, the two L-shaped structures are opposite, each L-shaped structure is in contact connection with one L-shaped bracket 15, and the two L-shaped brackets 15 are fixedly connected with the main wing 3.
The receiving mechanism comprises a groove b16 which is arranged in the machine body 1 and has an opening the same as the size of the hydrofoil 2, the groove b16 is connected with two propulsion motors b17 in parallel, each propulsion motor b17 is connected with a ball screw b18 through an output shaft, each ball screw b18 is connected with a screw nut b19, two screw nuts b19 are connected with one end of a crank 20 through a screw rod, the other end of the crank 20 is connected with the hydrofoil 2, and the length and the height of the groove b16 are not less than the length and the height of the crank 20.
The machine body 1 is in a long cylindrical revolving body configuration and comprises three parts: head, middle part, afterbody, head are located organism 1 front end, are circular-arc transition curve, and length is 1/12 of organism 1 length, and the afterbody is the shrink section, is located organism 1 rear end, and length is 1/4 of organism 1 length, connects tail rudder 4 on the afterbody, connects hydrofoil 2, main wing 3 on the middle part.
The water inlet 5 is arranged at the position of the tail part close to the middle part length 1/5, the air inlet 6 is arranged at the position of the tail part connected with the middle part, and the water inlet 5 and the air inlet 6 are circumferentially separated by 180 degrees on the machine body 1.
The main wing 3 and the hydrofoil 2 are both rectangular in shape, and the cross sections are both NACA airfoil shapes.
The hydrofoil 2 is attached to the front end 1/10 of the body 1 with the main wing 3 being 180 deg. circumferentially spaced from the hydrofoil 2 on the body 1.
The components in the cross-medium aircraft of the invention act as follows:
the hydrofoils 2 provide larger lift force for the cross-medium aircraft in the take-off process, the hydrofoils do not need to provide extra lift force in the stable navigation stage, on the contrary, the flow outside the aircraft is interfered by the hydrofoils 2, the navigation resistance is increased, the design of the retractable hydrofoils enables the cross-medium aircraft to retract unnecessary hydrofoils when the cross-medium aircraft stably navigates in the air and in water, and the resistance of the aircraft in the motion process is reduced to improve the navigation speed. When the aircraft needs to take off, the hydrofoil 2 is lowered to provide more lifting force, and the hydrofoil 2 is positioned at the front end of the aircraft, so that the head of the aircraft can be supported by increasing the lifting force at the front end, the degree of water adhering to the surface of the aircraft body is reduced, the front end of the aircraft is separated from the water surface, the resistance is reduced, and the purpose of rapid take-off is achieved.
The main wing 3 is able to power the aircraft takeoff.
The tail rudder 4 is able to control the attitude and heading of the aircraft.
The main wing 3 and the hydrofoil 2 are circumferentially spaced by 180 degrees on the aircraft body 1, so that the directions of lifting forces can be the same, and the aircraft is not easy to deflect when the hydrofoil 2 is folded or put down.
The water inlet 5 and the air inlet 6 are respectively connected with a jet propulsion system and a jet propulsion system, so that the medium-crossing aircraft can simultaneously load an underwater power system and an overwater power system, and necessary conditions are provided for medium-crossing sailing.
The principle of the receiving mechanism for receiving the hydrofoil 2 is as follows:
through control system, control two propulsion motors b17 and rotate, drive ball b18 simultaneously, screw nut b19 is all connected to two ball b18, connect crank 20 through the screw rod between two screw nut b19, because the effect of crank 20 makes the relative ball b18 of screw nut b19 remove, when ball b18 rotates, screw nut b19 removes to the one end of keeping away from propulsion motor b17, and then drive crank 20, hydrofoil 2 removes in recess b16, the realization is to accomodating of hydrofoil 2. The design of the retractable hydrofoils 2 enables the cross-medium aircraft to retract unnecessary hydrofoils when stably sailing in the air and in water, and reduces the resistance of the aircraft in the movement process to improve the sailing speed.
The principle of the discarding mechanism for discarding the main wing 3 is as follows:
the main wing 3 is fixedly connected to the L-shaped bracket 5, and the L-shaped bracket 5 is connected with the L-shaped structure on the buckle 14 through pressing contact. When the main wing 3 needs to be abandoned, the control system controls the propulsion motor a11 to rotate, the propulsion motor a11 drives the ball screw a12, the screw nut a13 moves relative to the ball screw a12 under the action of the buckle 14, and further drives the L-shaped structure on the buckle 14 to be separated from the L-shaped bracket 15, and under the action of the lifting force generated by the main wing 3, the main wing is separated from the machine body 1, so that the abandon of the main wing 3 is realized.
The invention relates to a cross-medium aircraft working process, which comprises the following steps:
when sailing, the main wing 3 and the hydrofoil 2 provide power for the aircraft, after sailing is stable, the hydrofoil 2 does not need to provide extra lift force, on the contrary, the flow outside the aircraft is interfered by the hydrofoil 2, sailing resistance is increased, the control system controls the propulsion motor b17 of the containing structure, the hydrofoil 2 is contained, and the resistance of the aircraft in the moving process is reduced so as to improve the sailing speed. When the aircraft needs to take off, the hydrofoil 2 is lowered to provide more lifting force, and the hydrofoil 2 is positioned at the front end of the aircraft, so that the head of the aircraft can be supported by increasing the lifting force at the front end, the degree of water adhering to the surface of the aircraft body is reduced, the front end of the aircraft is separated from the water surface, the resistance is reduced, and the purpose of rapid take-off is achieved.
In the final stage, the cross-medium vehicle adopts an underwater attack mode, and does not need to take off again, the main wing 3 is not an essential part at the moment, the wetted area of the vehicle under water is increased due to the long span of the main wing 3, so that the speed of the cross-medium vehicle is low when the vehicle sails under water, the design of the disposable main wing 3 enables the cross-medium vehicle to discard the main wing 3 when executing an underwater attack command, the main wing 3 is separated from a vehicle body under the action of lifting force, the resistance of the vehicle is reduced, and the sailing speed is further improved.
According to the cross-medium aircraft, the main wing is added to the aircraft to provide lift force for the air working condition, and the main wing is an upper single wing to reduce water-entering impact. When the aircraft is in the underwater attack working condition, the main wing is abandoned to reduce the navigation resistance and increase the navigation speed. In order to simplify the design, the main wing is in a rectangular wing form, and the main wing attack angle is changed by adjusting the pitching of the aircraft so as to achieve the purpose of adjusting the lift force of the main wing. The water/underwater medium crossing engine technology is adopted, an air inlet and a water inlet are additionally arranged at the front part of a tail contraction section of the aircraft, and an air jet and a water jet are arranged at the tail end of the aircraft to match the propulsion mode of air jet and underwater water jet. The front part of the aircraft is additionally provided with retractable hydrofoils for providing enough lift force in the takeoff process, and the hydrofoils are retracted to reduce the navigation resistance under the stable operation working condition.
Claims (8)
1. The medium crossing aircraft is characterized by comprising an aircraft body (1), wherein the aircraft body (1) is connected with a hydrofoil (2) through a receiving mechanism, the aircraft body (1) is connected with a main wing (3) through a discarding mechanism, the aircraft body (1) is further provided with a water inlet (5) and an air inlet (6), the tail end of the aircraft body (1) is further provided with an air nozzle (8) and a water spray nozzle (7), the air inlet (6) is communicated with the air nozzle (8) through an air passage, the water inlet (5) is communicated with the water spray nozzle (7) through a water passage, and the rear end of the aircraft body (1) is further connected with a tail vane (4).
2. The cross-media vehicle of claim 1, wherein a jet propulsion system is connected in the airways and a jet propulsion system is connected in the watercourse.
3. The cross-media vehicle according to claim 1, wherein the discarding mechanism comprises a groove a (9) formed in the body (1), two cover plates a (10) are connected in the groove a (9), a propulsion motor a (11) is connected to the inner wall of the body (1) in the direction of each cover plate a (10), a ball screw a (12) is connected to the output shaft of each propulsion motor a (11), a screw nut a (13) is connected to each ball screw a (12), a buckle (14) is connected to the outer wall of each screw nut a (13), the upper end of the buckle (14) is in an L-shaped structure, the two L-shaped structures are opposite, an L-shaped bracket (15) is connected to each L-shaped structure in a contact manner, and the two L-shaped brackets (15) are fixedly connected to the main wing (3).
4. The cross-medium vehicle according to claim 1, wherein the accommodating mechanism comprises a groove b (16) which is opened in the body (1) and has an opening with the same size as that of the hydrofoil (2), the groove b (16) is connected with two propulsion motors b (17) in parallel, the output shaft of each propulsion motor b (17) is connected with a ball screw b (18), each ball screw b (18) is connected with a screw nut b (19), the two screw nuts b (19) are connected with one end of a crank (20) through screws, the other end of the crank (20) is connected with the hydrofoil (2), and the length and the height of the groove b (16) are not less than those of the crank (20).
5. The vehicle according to claim 1, characterized in that said body (1) is of a configuration of long cylindrical solid of revolution, comprising three portions: head, middle part, afterbody, the head is located organism (1) front end, is circular-arc transition curve, and length is 1/12 of organism (1) length, the afterbody is the shrink section, is located organism (1) rear end, and length is 1/4 of organism (1) length, connect tail rudder (4) on the afterbody, connect hydrofoil (2), main wing (3) on the middle part.
6. The vehicle according to claim 5, characterized in that said water inlet (5) opens at the tail near the mid length 1/5, said air inlet (6) opens at the tail at the junction with the mid, said water inlet (5) and air inlet (6) being circumferentially spaced by 180 ° on the hull (1).
7. The cross-media vehicle according to claim 1, characterized in that the main wing (1) and hydrofoil (2) are both rectangular in shape and are both NACA airfoil in cross-section.
8. The vehicle according to claim 1, characterized in that said hydrofoil (2) is connected at the fore end 1/10 of the body (1), said main wing (3) being circumferentially spaced 180 ° from the hydrofoil (2) on the body (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202010826220.5A CN111890858B (en) | 2020-08-17 | 2020-08-17 | Cross-medium aircraft |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010826220.5A CN111890858B (en) | 2020-08-17 | 2020-08-17 | Cross-medium aircraft |
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| CN111890858A true CN111890858A (en) | 2020-11-06 |
| CN111890858B CN111890858B (en) | 2024-06-04 |
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| CN202010826220.5A Active CN111890858B (en) | 2020-08-17 | 2020-08-17 | Cross-medium aircraft |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112644235A (en) * | 2021-01-08 | 2021-04-13 | 西北工业大学 | Medium aircraft driving system is striden to repeatedly discrepancy water |
| CN112758334A (en) * | 2021-01-28 | 2021-05-07 | 中南大学 | Water-air cross-medium engine and cross-medium aircraft with same |
| CN113108654A (en) * | 2021-04-27 | 2021-07-13 | 西北工业大学 | Air water flushing combined cross-medium anti-ship anti-submarine missile |
| CN116160812A (en) * | 2023-04-23 | 2023-05-26 | 北京大学 | Hydrofoil detachable cross-medium aircraft |
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