Novel passenger life escape device of civil aircraft

Abstract

The invention provides a novel passenger life escape device of a civil aircraft, which comprises an aircraft body, a turbofan engine mounted on each of the left and right sides of the aircraft body, two turbojet subsonic combustion impact combined cycle engines mounted on a stabilizer at the rear part of the aircraft, and three pairs of staggered semicircular wings arranged on the two sides of the aircraft body, the aircraft is novel in structural design, the semicircular wings are adopted, the cargo hold space of the whole mother aircraft is saved, the sufficient flight speed is kept in the flight process of being separated from the mother aircraft, the flight speed is high, the flight speed is high, and the flight speed is high. And air resistance is reduced, so that the escape device can quickly enter sky clouds above severe weather and enter a safe height, and the escape safety is further improved.

Description

Technical Field

[0001] The present application relates to the technical field of passenger life escape, and in particular to a passenger life escape device for a new type of civil aircraft. Background Art

[0002] Traditional aircraft have accumulated a rich safety record in their operations over the past few decades. They have become the main means of transportation in the global civil aviation industry, providing efficient and convenient transportation services for hundreds of millions of passengers. Although traditional aircraft have shown high safety overall, there are still some challenges and potential safety hazards. Among them, flight accidents are one of the most eye-catching safety issues. Although these accidents are relatively rare, their impact is extremely serious and may result in a large loss of life and property.

[0003] In the past few decades, flight accidents were mainly caused by flight operation errors, mechanical failures, bad weather and other reasons. In addition, factors such as improper maintenance, human negligence, aviation management and supervision may also pose a threat to the safety of traditional aircraft. However, it should be emphasized that with the continuous advancement of science and technology and the global aviation community's increasing attention to safety, the safety of traditional aircraft is also constantly improving. Airlines, manufacturers and regulators are committed to improving the safety performance of aircraft by introducing more advanced technologies, improving aircraft design, strict maintenance procedures and training crew members. Although traditional aircraft have some challenges in safety, they are still reliable and safe means of transportation. Through continuous improvement and perfection, traditional aircraft can continue to play an important role in the future and provide passengers with a safer and more comfortable flight experience. With the rapid development of the aviation industry, the pursuit of higher flight safety has become one of the important goals of the research and development of the new generation of passenger aircraft. In this context, the CA3911 air shuttle, as a new wide-body passenger aircraft, has attracted widespread attention. Traditional aircraft have indeed achieved great success in the process of providing aviation services, but they also face some safety hazards. Therefore, studying how to improve the safety of aircraft has become an important issue in the aviation field. Summary of the invention

[0004] The present application provides a new type of passenger life escape device for civil aircraft to solve the problem that existing aircraft do not have escape equipment. It achieves maintaining a sufficient flight speed and overall lift during the flight process of leaving the mother aircraft in an emergency, reduces air resistance, and is conducive to quickly entering the sky cloud layer above bad weather and entering a safe altitude, thereby further improving escape safety.

[0005] The present application provides a novel passenger life escape device for a civil aircraft, comprising a fuselage; A turbofan engine is installed on the left and right sides of the fuselage respectively, and two turbojet sub-combustion impulse combined cycle engines are installed on the rear mounting position of the aircraft; It also includes three pairs of semicircular wings, and the three pairs of semicircular wings are staggeredly installed on both sides of the fuselage, and the three pairs of semicircular wings are circled on the outer wall of the fuselage; A wing bayonet is arranged at the outer end of the semicircular wing, a clamping assembly is installed at the wing bayonet, and the clamping assembly clamps one end of the long arm wing.

[0006] Preferably, the clamping assembly includes a semicircular plug, a locking pin, a handle rod, a connecting rod, a spring fixing part and a spring. The height of the semicircular plug is 2.3m. An inclined slot is arranged on the upper part of the semicircular plug, the locking pin is installed at the inclined slot, the handle rod is installed above the inclined slot, and the lower end of the handle rod is connected to the upper end of the spring fixing part arranged below the inclined slot through the connecting rod, the lower end of the locking pin passes through the middle part of the handle rod and is connected to the upper end of the spring, and the lower end of the spring is connected to the spring fixing part.

[0007] Preferably, three vertically inclined slots are provided at the end of the long arm wing, and the inclined slots are adapted to the locking pin.

[0008] Preferably, the semicircular wing is 4.4m wide and 3.4m high; the long arm wing is 1.8m wide and 6.4m long. The total area of ​​the semicircular wing is 140.04 square meters, and the wing area of ​​a single long arm wing is 23.4 square meters.

[0009] Preferably, it also includes an adjustment component, which includes a winch and a steel wire rope, the winch is installed on the top of the fuselage, the steel wire rope is wound around the outside of the winch, and the outer end of the steel wire rope is connected to the other end of the long arm wing.

[0010] Preferably, it also includes a tilt-propeller fan, which is located at the front part of the semicircular wing, that is, in the middle of the trailing edge of the wing, and the airflow of the tilt-propeller fan is toward the semicircular duct of the aircraft. The tilt-propeller fan is connected to one end of the connecting arm, and the other end of the connecting arm is connected to the outer end of the steel wire cable.

[0011] Preferably, a rocket servo synchronization system device is also installed on the second layer of the cabin in the inner cavity of the fuselage, and two rocket servo booster synchronizers are arranged in the rocket servo synchronization system device. On the second layer of the fuselage, at the rear of the cockpit, 9-10 oil tanks are stored, and 4 double-layer insulated liquid oxygen tanks are stored side by side. There are two IF-115 small rocket engines in the gap between the booster rockets.

[0012] Preferably, the booster rocket adopts a liquid-solid CZ-15 three-stage rocket.

[0013] Preferably, the method of use comprises the following steps: A. The mother aircraft refuels the fuel tank of the small aircraft in the cabin and checks the propulsion equipment of the small aircraft at the same time. The 9 fuel tanks store about 60.1 tons of kerosene, but only 44 tons are actually stored. The other 16 tons of kerosene need to be drawn from the wings of the mother aircraft; B. After the oil extraction is completed, remove the oil extraction pipe device and wires, and remove the pipe joint obstacles. At the same time, the captain uses the remote control device to open the rear cabin locking mechanism, and then uses the remote control device to open the second-layer locking mechanism of the front cockpit; C. When the CZ-15 three-stage rocket is ignited for boosting, 16 IF115 liquid oxygen-kerosene small rocket engines are started at the same time to boost the sub-aircraft. At this time, the two turbojet sub-combustion impact combined cycle engines on the upper rear tail are started to further increase the safe flight altitude of the sub-aircraft; D. When entering high-altitude flight, the pilot tightens the wire rope through the winder button to adjust the steering of the semicircular wing and the long-arm wing. The semicircular long-arm wing rotates 180 degrees, and the wing arm is just inserted into the semicircular wing slot and locked by the pin. At the same time, the tilt-propeller fan is steered through the adjustment of the wire rope and stops in the middle of the semicircular wing. Driven by the tilt-propeller fan, the lift of the aircraft is further enhanced. Beneficial Effects

[0014] (1) The present invention has a novel structural design and adopts a semicircular wing, which saves the cargo hold space of the entire mother aircraft. In addition, the present invention maintains a sufficient flight speed and overall lift during the flight from the mother aircraft, reduces air resistance, and is conducive to quickly entering the sky cloud layer above the bad weather and entering a safe altitude, thereby further improving the safety of escape.

[0015] (2) The present invention also includes a tilt-propeller fan, which is located at the front of the semicircular wing, that is, in the middle of the trailing edge of the wing. The airflow of the tilt-propeller fan is directed toward the semicircular duct of the aircraft. With this structure, the lift of the aircraft can be further enhanced.

[0016] The above description is only an overview of the technical solution of the embodiment of the present application. In order to more clearly understand the technical means of the embodiment of the present application, it can be implemented in accordance with the contents of the specification. In order to make the above and other purposes, features and advantages of the embodiment of the present application more obvious and easy to understand, the specific implementation methods of the present application are listed below. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the technical solutions of the embodiments of the present application, a brief introduction will be given below to the drawings required for use in the description of the embodiments. Obviously, the drawings described below are some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0018] Figure 1 It is a schematic diagram of the structure of the present invention; Figure 2 This is a schematic diagram of the structure of the clamping assembly of the present invention; Figure 3 This is a schematic diagram of the installation of the tilt-propeller fan of the present invention; Explanation of the reference numerals in the accompanying drawings: fuselage 1, turbofan engine 2, semicircular wing 3, wing bayonet 4, clamping assembly 5, long arm wing 6, semicircular plug column 7, locking pin 8, handle rod 9, connecting rod 10, spring fixing part 11, spring 12, inclined notch 13, vertical inclined slot 14, winch 15, wire rope 16, tilt-propeller fan 17, connecting arm 18. DETAILED DESCRIPTION

[0019] In order to make the purpose, technical solution and advantages of the embodiments of the present application clearer, the technical solution in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this application.

[0020] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by technicians in the technical field to which this application belongs; the terms used in the specification of the application are only for the purpose of describing specific embodiments and are not intended to limit this application; the terms "including" and "having" and any variations thereof in the specification, claims and drawings of this application are intended to cover non-exclusive inclusions.

[0021] Reference to "embodiments" herein means that a particular feature, structure, or characteristic described in conjunction with the embodiments may be included in at least one embodiment of the present application. The appearance of the phrase "embodiments" in various locations in the specification does not necessarily refer to the same embodiment, nor is it an independent or alternative embodiment that is mutually exclusive with other embodiments. It is explicitly and implicitly understood by those skilled in the art that the embodiments described herein may be combined with other embodiments.

[0022] The directional words appearing in the following description are all directions shown in the drawings, and do not limit the specific structure of the present application. For example, in the description of the present application, the directions or positional relationships indicated by the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc. are based on the directions or positional relationships shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore cannot be understood as limiting the present application.

[0023] In addition, the expressions of indicated directions such as the X direction, the Y direction, and the Z direction used to illustrate the operation and construction of the components of the present embodiment are not absolute but relative, and although these indications are appropriate when the components are in the positions shown in the figures, when these positions change, these directions should be interpreted differently to correspond to the changes.

[0024] In addition, the terms "first", "second", etc. in the specification and claims of this application or the above-mentioned drawings are used to distinguish different objects rather than to describe a specific order, and may explicitly or implicitly include one or more of the features.

[0025] In the description of the present application, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected" and "connected" should be understood in a broad sense. For example, the "connection" or "connection" of a mechanical structure may refer to a physical connection. For example, the physical connection may be a fixed connection, such as a fixed connection through a fixing member, such as a fixed connection through a screw, bolt or other fixing member; the physical connection may also be a detachable connection, such as a mutual snap-on or snap-fit ​​connection; the physical connection may also be an integral connection, such as a connection formed by welding, bonding or integral molding. For those of ordinary skill in the art, the specific meanings of the above terms in the present application can be understood according to specific circumstances.

[0026] In order to enable those skilled in the art to better understand the solution of the present application, the technical solution in the embodiments of the present application will be clearly and completely described below in conjunction with the accompanying drawings.

[0027] See also Figure 1-Figure 3 , the present application discloses a novel passenger life escape device for civil aircraft, comprising a fuselage 1; A turbofan engine 2 is installed on the left and right sides of the fuselage 1, and two turbojet sub-combustion impulse combined cycle engines are installed on the rear mounting position of the aircraft 1; It also includes three pairs of semicircular wings 3, and three pairs of semicircular wings are staggered on both sides of the fuselage, and the three pairs of semicircular wings 3 are circled on the outer wall of the fuselage 1; the outer side of the fuselage opposite to the staggered semicircular wings is a space with a length of 4m*1.5m, and ODYSSEY is installed in this 4.3㎡ space. This company has a model calibrated as 16AH, the current reaches 1800A in the full power state, the internal resistance is less than 7mΩ, and their cycle life can reach more than 800 times under 80% SOC discharge, and can be discharged for a long time. The battery capacity of the internal space of a canard can meet the power demand of a tilting fan; A wing bayonet 4 is arranged at the outer end of the semicircular wing 3 , and a clamping assembly 5 is installed at the wing bayonet 4 , and the clamping assembly 5 clamps one end of the long arm wing 6 .

[0028] In the present invention, the clamping assembly 5 includes a semicircular plug column 7, a locking pin 8, a handle rod 9, a connecting rod 10, a spring fixing member 11 and a spring 12. The semicircular plug column 7 has a height of 70 mm. An inclined notch 13 is arranged on the upper part of the semicircular plug column 7. The locking pin 8 is installed at the inclined notch 13. The handle rod 9 is installed above the inclined notch 13. The lower end of the handle rod 9 is connected to the upper end of the spring fixing member 11 arranged below the inclined notch 13 through the movable connecting rod 10. The lower end of the locking pin 8 passes through the middle of the handle rod 9 and is connected to the upper end of the spring fixing member 11 arranged below the inclined notch 13. The upper end of the spring 12 is connected, and the lower end of the spring 12 is connected to the spring fixing part 11; three vertical inclined slots 14 are set at the end of the long arm wing 6, and the inclined slots 14 are adapted to the locking pin 8. The wing arm is inserted into the inclined slot to support the vertical inclined surface of the handle pull rod, thereby driving the connecting pull rod to support the spring fixing part to rotate, thereby causing the spring to pop out. During the spring popping out process, the locking pin is pushed into the inclined slot to fix the long arm wing. There is a pair of clips at the bottom of the locking pin. When a person pulls the rope, the pull rod descends with the movable connecting pull rod and compresses the spring under the locking pin, thereby unlocking the semicircular long arm wing.

[0029] Among them, the semicircular wing 3 is 4.4m wide and 3.4m high; the long arm wing 6 is 1.8m wide, 6.4m long, and has a total area of ​​140.4 square meters. The total area of ​​the semicircular wing 3 is 23.4 square meters, and the wing area of ​​a single long arm wing 6 is 9.9-10.26 square meters.

[0030] The present invention also includes an adjustment component, which includes a hoist 15 and a steel cable 16. The hoist 15 is installed on the top of the fuselage 1, and the steel cable 16 is wound around the outside of the hoist 15. The outer end of the steel cable 16 is connected to the other end of the long arm wing 6. The hoist controls the extension and retraction of the steel cable to adjust the angle of the semicircular wing and the long arm wing.

[0031] The present invention further includes a tilt propeller fan 17, which is located at the front of the semicircular wing 3, that is, in the middle of the trailing edge of the wing, and the airflow of the tilt propeller fan 17 is directed toward the semicircular duct of the aircraft, and the tilt propeller fan 17 is connected to one end of a connecting arm 18, and the other end of the connecting arm 18 is connected to the outer end of the wire rope 16. With this structure, the lift of the aircraft can be further improved.

[0032] In addition, in the present invention, a rocket servo synchronization system device is also installed in the second layer of the cabin in the inner cavity of the fuselage 1. Two rocket servo booster synchronizers are arranged in the rocket servo synchronization system device. In the second layer of the fuselage, at the rear of the cockpit, 9-10 oil tanks are stored, and 4 double-layer insulation liquid oxygen tanks are stored side by side. There are two IF-115 small rocket engines in the gap between the booster rockets; the booster rocket adopts a liquid-solid CZ-15 three-stage rocket. The ignition and combustion of the rocket will not cause damage to the aircraft itself. As the small aircraft leaves the mother aircraft and is pushed out of the cabin of the large aircraft by the reaction force of the rocket, the flame of the rocket will become larger and larger, and the thrust will also be greater, until all the propellants are burned, which takes about 500 seconds. And this type of rocket will not explode during the combustion process, and the generated products will not pollute the environment. The three-stage liquid-solid rocket of the above model can make the small aircraft fly up to at least 7,500 meters in about 4 minutes. In addition, driven by two turbo-energy sub-combustion ramjet combined cycle engines, and when a certain amount of kerosene is consumed, the small aircraft can be pushed up to at least 3,500 meters, thereby reaching a safe altitude of more than 11,000 meters. The present invention adopts an innovative booster system, usually based on a rocket engine, which can provide a strong thrust to the escaping sub-aircraft in a vacuum or thin air, while traditional aircraft rely on turbofan engines or jet engines to reach the same spatial altitude in time, which is advanced.

[0033] Working principle: A method for using a new type of passenger life escape device for civil aircraft includes the following steps: A. The mother aircraft refuels the fuel tank of the small aircraft in the cabin and checks the propulsion equipment of the small aircraft at the same time. The 9 fuel tanks store about 60.1 tons of kerosene, but only 44 tons are actually stored. The other 16 tons of kerosene need to be drawn from the wings of the mother aircraft; B. After the oil extraction is completed, remove the oil extraction pipe device and wires, and remove the pipe joint obstacles. At the same time, the captain uses the remote control device to open the rear cabin locking mechanism, and then uses the remote control device to open the second-layer locking mechanism of the front cockpit; C. When the CZ-15 three-stage rocket is ignited for boosting, 16 IF115 liquid oxygen-kerosene small rocket engines are started at the same time to boost the sub-aircraft. At this time, the two turbojet sub-combustion impact combined cycle engines on the upper rear tail are started to further increase the safe flight altitude of the sub-aircraft; D. When entering high-altitude flight, the pilot tightens the wire rope through the winder button to adjust the steering of the semicircular wing and the long-arm wing. The semicircular long-arm wing rotates 180 degrees, and the wing arm is just inserted into the semicircular wing slot and locked by the pin. At the same time, the tilt-propeller fan is steered through the adjustment of the wire rope and stops in the middle of the semicircular wing. Driven by the tilt-propeller fan, the lift of the aircraft is further enhanced.

[0034] In summary, the present invention has a novel structural design and adopts a semicircular wing, which saves the cargo hold space of the entire mother aircraft, and maintains a sufficient flight speed and overall lift during the flight from the mother aircraft, reduces air resistance, and is conducive to quickly entering the sky clouds above bad weather and entering a safe altitude, further improving the safety of escape.

[0035] As described above, the above embodiments are only used to illustrate the technical solutions of the present application, rather than to limit them. Although the present application has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present application.

Claims

1. A new type of passenger life escape device for civil aircraft, characterized in that: including a body (1); A turbofan engine (2) is installed on the left and right sides of the fuselage (1), and two turbojet sub-combustion impulse combined cycle engines are installed on the rear mounting position of the aircraft (1); It also includes three pairs of semicircular wings (3), and the three pairs of semicircular wings (3) are staggeredly installed on both sides of the fuselage (1), and the three pairs of semicircular wings (3) are encircled on the outer wall of the fuselage (1); A wing bayonet (4) is provided at the outer end of the semicircular wing (3), a clamping assembly (5) is installed at the wing bayonet (4), and the clamping assembly (5) clamps one end of the long arm wing (6).

2. A new type of passenger life escape device for civil aircraft according to claim 1, characterized in that: The clamping assembly (5) comprises a semicircular plug column (7), a locking pin (8), a handle rod (9), a connecting rod (10), a spring fixing member (11) and a spring (12). The height of the semicircular plug column (7) is 2.3 m. An inclined slot (13) is arranged on the upper part of the semicircular plug column (7). The locking pin (8) is installed at the inclined slot (13). The handle rod (9) is installed above the inclined slot (13). The lower end of the handle rod (9) is connected to the upper end of the spring fixing member (11) arranged below the inclined slot (13) through the connecting rod (10). The lower end of the locking pin (8) passes through the middle of the handle rod (9) and is connected to the upper end of the spring (12). The lower end of the spring (12) is connected to the spring fixing member (11).

3. The new type of passenger life escape device for civil aircraft according to claim 1 is characterized in that: Three vertically inclined slots (14) are provided at the end of the long arm wing (6), and the inclined slots (14) are adapted to fit the locking pin (8).

4. The new type of passenger life escape device for civil aircraft according to claim 1 is characterized in that: The semicircular wing (3) has a width of 4.4 m and a height of 3.4 m; the long arm wing (6) has a width of 1.8 m and a length of 6.4 m. The total area of ​​the semicircular wing (3) is 140.4 square meters, and the wing area of ​​a single long arm wing (6) is 23.4 square meters.

5. The new type of passenger life escape device for civil aircraft according to claim 1 is characterized in that: The invention also comprises an adjustment component, wherein the adjustment component comprises a winch (15) and a steel wire rope (16), wherein the winch (15) is mounted on the top of the fuselage (1), the steel wire rope 16 is wound around the outside of the winch 15, and the outer end of the steel wire rope (16) is connected to the other end of the long arm wing (6).

6. The new type of passenger life escape device for civil aircraft according to claim 1 is characterized in that: It also includes a tilt-propeller fan (17), which is located at the front of the semicircular wing (3), that is, in the middle of the trailing edge of the wing. The airflow of the tilt-propeller fan (17) is directed toward the semicircular duct of the aircraft. The tilt-propeller fan (17) is connected to one end of a connecting arm (18), and the other end of the connecting arm (18) is connected to the outer end of the wire rope (16).

7. The new type of passenger life escape device for civil aircraft according to claim 1 is characterized in that: A rocket servo synchronization system device is also installed on the second layer of the cabin in the inner cavity of the fuselage (1). Two rocket servo booster synchronizers are arranged in the rocket servo synchronization system device. On the second layer of the fuselage, at the rear of the cockpit, 9-10 oil tanks are stored, and 4 double-layer insulated liquid oxygen tanks are stored side by side. There are two IF-115 small rocket engines in the gap between the booster rockets.

8. A new type of passenger life escape device for civil aircraft according to claim 7, characterized in that: The booster rocket adopts a liquid-solid CZ-15 three-stage rocket.

9. A method for using the new type of passenger life escape device for civil aircraft according to claim 1, characterized in that: The method of use includes the following steps: A. The mother aircraft refuels the fuel tank of the small aircraft in the cabin and checks the propulsion equipment of the small aircraft at the same time. The 9 fuel tanks store about 60.1 tons of kerosene, but only 44 tons are actually stored. The other 16 tons of kerosene need to be drawn from the wings of the mother aircraft; B. After the oil extraction is completed, remove the oil extraction pipe device and wires, and remove the pipe joint obstacles. At the same time, the captain uses the remote control device to open the rear cabin locking mechanism, and then uses the remote control device to open the second-layer locking mechanism of the front cockpit; C. When the CZ-15 three-stage rocket is ignited for boosting, 16 IF115 liquid oxygen-kerosene small rocket engines are started at the same time to boost the sub-aircraft. At this time, the two turbojet sub-combustion impact combined cycle engines on the upper rear tail are started to further increase the safe flight altitude of the sub-aircraft; D. When entering high-altitude flight, the pilot tightens the wire rope through the winder button to adjust the steering of the semicircular wing and the long-arm wing. The semicircular long-arm wing rotates 180 degrees, and the wing arm is just inserted into the semicircular wing slot and locked by the pin. At the same time, the tilt-propeller fan is steered through the adjustment of the wire rope and stops in the middle of the semicircular wing. Driven by the tilt-propeller fan, the lift of the aircraft is further enhanced.

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