CN201132608Y - Large-scale short-distance rising and landing energy-conserving aerotransport - Google Patents
Large-scale short-distance rising and landing energy-conserving aerotransport Download PDFInfo
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- CN201132608Y CN201132608Y CNU2007200155633U CN200720015563U CN201132608Y CN 201132608 Y CN201132608 Y CN 201132608Y CN U2007200155633 U CNU2007200155633 U CN U2007200155633U CN 200720015563 U CN200720015563 U CN 200720015563U CN 201132608 Y CN201132608 Y CN 201132608Y
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Abstract
The utility model relates to a large-scale short-distance take-off and landing transporter which is energy-saving. The transporter comprises a transporter body and a power installation, wherein, four power-assisted exhaust-airway cabins are symmetrically arranged at the middle part of a main body cavity; a power-assisted exhaust-airway is arranged inside the main body cavity; the middle part of the power-assisted exhaust-airway is fixed and connected with the front parts of two booster cylinders; a plurality of front motors and air injection whirl tubes are respectively arranged on a front wing and a rear wing; two shaft levers are arranged on the relative positions on the two sides of outer shell bodies thereof; one ends of the two shaft levers are respectively connected with the front motors and the two sides of the outer shells of the air injection whirl tubes in a rotating way; the other ends of the two shaft levers are respectively fixed and connected with the front wing and the rear wing; a central unit comprises motors, an electric generator and a hydropress; the motor is connected with the electric generator through a strap in a rotating way; the electric generator is respectively connected with the front motors, rear motors, and a power-assisted lift-off motor; the hydropress is respectively connected with a plurality of front hydraulic cylinders, rear hydraulic cylinders and the booster cylinders through hydraulic circuits. The large-scale short-distance take-off and landing transporter has the advantages of rich creativity, less material consumption, low cost and simple operation.
Description
Technical field
The utility model relates to aircraft, concrete is the energy-conservation transport plane of a kind of large-scale short take-off and landing (STOL).
Background technology
Along with development of aviation, transport plane, especially more and more seem especially important of large transport airplane, yet, the transport plane consumption of fuel that uses is too big at present, because its each driving engine all is to turn round normally with oil to add the efficiency of burning, the degree of utilization that improves oil in the flight course is the key subject that the aviation professional studies always.
The landing of transport plane need have sufficiently long runway, could guarantee that thereby aircraft has certain takeoff speed built on stilts, the expense of building its occupation of land of adrm and investment is quite big, for little cities and towns, or the not really frequent again place of the landing frequency of transport plane, the situation of objective condition and actual needs is not leaves no choice but build adrm, but this to transport plane occasionally landing constituted insoluble big problem again.
Also do not have the energy vertical takeoff and landing at present, few again transport plane consumes energy.
Summary of the invention
The purpose of this utility model is at the problem that does not have the few again large transport airplane of energy vertical takeoff and landing and power consumption at present, and provides a kind of large-scale short take-off and landing (STOL) energy-conservation transport plane.
The technical scheme that adopts is:
The energy-conservation transport plane of large-scale short take-off and landing (STOL), comprise body, engine installation, the front of described body is provided with cockpit, preceding wing, back wing, fuselage, preceding wing is captiveed joint with fuselage, the cavity bilateral symmetry of the fuselage of the mmi machine wing and fuselage connecting portion is provided with two cover center units, be provided with a plurality of power-assisted air exhausting ducts storehouse in the middle part of fuselage cavity bilateral symmetry, the power-assisted air exhausting duct is equiped with the power-assisted air exhausting duct in the storehouse, captives joint with the anterior movable end of booster cylinder in the middle part of power-assisted air exhausting duct.
Preceding wing is installed a plurality of anterior electrical motors, the below of wing before anterior electrical motor is positioned at, forwardly the relative position of the housing both sides of electrical motor is provided with two axostylus axostyles parallel with preceding wing, one end of two axostylus axostyles is rotationally connected with the housing both sides of anterior electrical motor respectively, and the other end of two axostylus axostyles is captiveed joint with preceding wing respectively;
Back wing is provided with a plurality of jet air channels, on the both sides relative position of the body skin in jet air channel two axostylus axostyles is set, and an end of two axostylus axostyles is rotationally connected with the body skin both sides in jet air channel respectively, and the other end of two axostylus axostyles is captiveed joint with the back wing respectively;
Described engine installation comprises center unit, power-assisted lift-off electrical motor, rear portion electrical motor; The center unit is made up of driving engine, electrical generator and hydraulic compressor, the arbor wheel that goes out of driving engine is rotationally connected by belt and electrical generator, generator output end is connected with rear portion electrical motor and power-assisted lift-off electrical motor with anterior electrical motor by lead is corresponding respectively, and rear portion electrical motor, power-assisted lift-off electrical motor correspondence respectively are arranged in jet air channel and the power-assisted air exhausting duct;
Hydraulic compressor is connected with a plurality of anterior hydraulic actuating cylinders, rear portion hydraulic actuating cylinder and booster cylinder respectively by hydraulic tubing; The anterior movable rod of per two anterior hydraulic actuating cylinders is rotationally connected with the upper and lower both sides of the housing axostylus axostyle axle of each anterior electrical motor respectively, synchronization action, before stretch after contracting or protract after contract, thereby make anterior electrical motor rotate 90 ° around the axle of axostylus axostyle, become plumbness.The action of the anterior movable rod by anterior hydraulic actuating cylinder sets back again, the lower surface of wing before anterior hydraulic actuating cylinder is fixedly connected on;
The anterior movable rod of per two rear portion hydraulic actuating cylinders is rotationally connected with the upper and lower both sides of the body skin axostylus axostyle axle in each jet air channel respectively, synchronization action, before stretch after contracting or protract after contract, and make jet air channel rotate 90 ° around the axle of axostylus axostyle, become plumbness, the rear portion hydraulic actuating cylinder is fixedly connected on the lower surface of back wing.
The middle part of four power-assisted air exhausting ducts is corresponding respectively captives joint with the anterior portable bar of four booster cylinders, the booster cylinder of same horizon and arranged on left and right sides is made as one group, the booster cylinder of same group of same horizon and arranged on left and right sides is fixedly connected into a shape one by intermediate, the booster cylinder of same group of and arranged on left and right sides is installed in respectively in two bearing seats, and bearing seat is fixed in the cavity of fuselage; Captive joint one pivot link on the intermediate of same group of and arranged on left and right sides booster cylinder that fuses, pivot link is hinged with the portable bar that rotates the hydraulic actuating cylinder front portion, rotates hydraulic actuating cylinder and is fixed in the inner chamber of fuselage.The shaft of above-mentioned power-assisted lift-off electrical motor, rear portion electrical motor is equiped with impeller.
The shaft of above-mentioned anterior electrical motor is equiped with screw propeller.
The advantage that the utlity model has is:
1, energy-saving effect is obvious
Each screw propeller or impeller on the existing transport plane all are equipped with a driving engine, each driving engine all needs to consume a large amount of fuel oils, and the utility model driving engine removes electrical motors all on the drive machine, thereby reaches energy-saving effect for driving 3-4 platform electrical generator with 3-4 platform diesel engine.
But 2 vertical takeoff and landing
When aircraft needs vertical takeoff and landing, change into anterior driving engine, jet air channel and power-assisted air exhausting duct vertical by hydraulic gear, at this moment screw propeller or impeller backward the thrust direction that produces of air draft be vertically downward, aircraft is vertical to rise or vertical slowly landing thereby make.After the aircraft lift-off, by hydraulic efficiency gear level attitude is recovered in anterior driving engine, jet air channel, the power-assisted air exhausting duct sets back and regains power-assisted air exhausting duct storehouse.And then increased the alerting ability of aircraft in the transportation in wartime.
3, reduced the difficulty of manufacturing of aero-engine, saved and manufactured cost, can vertical takeoff and landing because of aircraft, can save cooresponding investment cost from the construction on airport.
The utility model is skillfully constructed, because of carrying out 90 ° of rotations in the jet air channel at anterior motor drives screw propeller and rear portion, and push air downwards, therefore the energy-conservation transport plane of large-scale short take-off and landing (STOL) has the function of vertical takeoff and landing, consumption of fuel is few, multiple functional, simple in structure, parts are light, cheap, be convenient to installation and maintenance, flight cost is low, suitable aviation special use.
Description of drawings
Fig. 1 is a structural representation of the present utility model.
Fig. 2 is that Figure 1A-A is to scheme drawing.
Fig. 3 is that Figure 1B-B is to scheme drawing.
Fig. 4 is that Fig. 1 C-C is to scheme drawing.
The specific embodiment
Embodiment
The energy-conservation transport plane of large-scale short take-off and landing (STOL), comprise body, engine installation, the front of described body is provided with cockpit 1, preceding wing 4, back wing 19, fuselage 5, preceding wing 4 is captiveed joint with fuselage 5, the mmi machine wing 4 is provided with two cover center units 2 with the cavity bilateral symmetry of the fuselage 5 of fuselage 5 connecting portions, middle part bilateral symmetry at fuselage 5 cavitys is provided with a plurality of power-assisted air exhausting ducts storehouse 6, be equiped with power-assisted air exhausting duct 7 in the power-assisted air exhausting duct storehouse 6, captive joint with the anterior movable end 8 of booster cylinder 9 in the middle part of power-assisted air exhausting duct 7, booster cylinder 9 is fixed in the cavity of fuselage 5.
The a plurality of anterior electrical motors 3 of preceding wing 4 installings, the below of wing 4 before anterior electrical motor 3 is positioned at, forwardly the relative position of the housing both sides of electrical motor 3 is provided with two axostylus axostyles parallel with preceding wing 11, one end of two axostylus axostyles 11 is rotationally connected with the housing both sides of anterior electrical motor 3 respectively, and the other end of two axostylus axostyles 11 is captiveed joint with preceding wing 4 respectively;
Described engine installation comprises center unit 2, power-assisted lift-off electrical motor 13, rear portion electrical motor 14; Center unit 2 is made up of driving engine, electrical generator and hydraulic compressor, the arbor wheel that goes out of driving engine is rotationally connected by belt and electrical generator, generator output end is connected with rear portion electrical motor 14 and power-assisted lift-off electrical motor 13 with anterior electrical motor 3 by lead is corresponding respectively, and rear portion electrical motor 14, power-assisted lift-off electrical motor 13 correspondence respectively are arranged in jet air channel 10 and the power-assisted air exhausting duct 7;
Hydraulic compressor is connected with a plurality of anterior hydraulic actuating cylinders, rear portion hydraulic actuating cylinder and booster cylinder 9 respectively by hydraulic tubing; The anterior movable rod 16 of per two anterior hydraulic actuating cylinders 15 is rotationally connected with the upper and lower both sides of 11 of the housing axostylus axostyles of each anterior electrical motor 3 respectively, synchronization action, before stretch after contracting or protract after contract, thereby make anterior electrical motor 3 rotate 90 ° around the axle of axostylus axostyle 11, become plumbness.The action of the anterior movable rod by anterior hydraulic actuating cylinder 15 sets back again, the lower surface of wing 4 before anterior hydraulic actuating cylinder 15 is fixedly connected on;
The anterior movable rod 18 of every rear portion hydraulic actuating cylinder 17 is rotationally connected with the upper and lower both sides of 12 of the body skin axostylus axostyles in each jet air channel 10 respectively, synchronization action, before stretch after contracting or protract after contract, and make jet air channel 10 rotate 90 ° around the axle of axostylus axostyle 12, become plumbness, rear portion hydraulic actuating cylinder 17 is fixedly connected on the lower surface of back wing 19.
Captive joint with the anterior portable bar 8 of four booster cylinders 9 respectively in the middle part of four power-assisted air exhausting ducts 7, two booster cylinders 9 of same horizon and arranged on left and right sides are made as one group, four power-assisted air exhausting ducts 7 are made as two groups, two booster cylinders 9 of same group of and arranged on left and right sides are fixedly connected into a shape one by intermediate 21, two booster cylinders 9 of and arranged on left and right sides are installed in respectively in two bearing seats 25, and bearing seat 25 is fixed in the cavity of fuselage 5; Captive joint one pivot link 22 on the intermediate 21 of the and arranged on left and right sides booster cylinder 9 that fuses, the pivot link 22 that front and back are two groups is hinged with portable bar 24 front and back of rotating hydraulic actuating cylinder 20 front portions respectively, rotates hydraulic actuating cylinder 20 and is fixed in the inner chamber of fuselage 5.
The portable bar 24 that rotates hydraulic actuating cylinder 20 front portions by the effect of hydraulic gear can protract or after contract, two groups pivot link 22 rotates in the scope of setting before and after the pulling, thereby make two groups, and arranged on left and right sides booster cylinder 9 and then rotates together, because of the anterior portable bar 8 of and arranged on left and right sides booster cylinder 9 is fixedly connected on the middle part of power-assisted air exhausting duct 7, therefore two groups of horizontalitys that four power-assisted air exhausting ducts just form plumbness or set back because of rotation 7 this moments.
The shaft of power-assisted lift-off electrical motor 13, rear portion electrical motor 14 is equiped with impeller, and the shaft of anterior electrical motor 3 is equiped with screw propeller.
Claims (3)
1, the energy-conservation transport plane of large-scale short take-off and landing (STOL) comprises body, engine installation, and the front of described body is provided with cockpit (1), preceding wing (4), back wing (19), fuselage (5), and preceding wing (4) is captiveed joint with fuselage (5), it is characterized in that:
Wing (4) is provided with two cover center units (2) with the cavity bilateral symmetry of the fuselage (5) of fuselage (5) connecting portion before described, middle part bilateral symmetry at fuselage (5) cavity is provided with a plurality of power-assisted air exhausting ducts storehouses (6), being equiped with power-assisted air exhausting duct (7) in the power-assisted air exhausting duct storehouse (6), captives joint with the anterior movable end (8) of booster cylinder (9) in the middle part of power-assisted air exhausting duct (7);
Preceding wing (4) installing a plurality of anterior electrical motors (3), anterior electrical motor (3) is positioned at the below of preceding wing (4), forwardly the relative position of the housing both sides of electrical motor (3) is provided with two axostylus axostyles parallel with preceding wing (11), one end of two axostylus axostyles (11) is rotationally connected with the housing both sides of anterior electrical motor (3) respectively, and the other end of two axostylus axostyles (11) is captiveed joint with preceding wing (4) respectively;
Back wing (19) is provided with a plurality of jet air channels (10), two axostylus axostyles (12) are set on the both sides relative position of the body skin in jet air channel (10), one end of two axostylus axostyles (12) is rotationally connected with the body skin both sides of jet air channel (10) respectively, and the other end of two axostylus axostyles (12) is captiveed joint with back wing (19) respectively;
Described engine installation comprises center unit (2), power-assisted lift-off electrical motor (13), rear portion electrical motor (14); Center unit (2) is made up of driving engine, electrical generator and hydraulic compressor, the arbor wheel that goes out of driving engine is rotationally connected by belt and electrical generator, generator output end is connected with rear portion electrical motor (14) and power-assisted lift-off electrical motor (13) with anterior electrical motor (3) by lead is corresponding respectively, and rear portion electrical motor (14), power-assisted lift-off electrical motor (13) correspondence respectively are arranged in jet air channel (10) and the power-assisted air exhausting duct (7);
Hydraulic compressor is connected with a plurality of anterior hydraulic actuating cylinders, rear portion hydraulic actuating cylinder and booster cylinder (9) respectively by hydraulic tubing; The anterior movable rod (16) of per two anterior hydraulic actuating cylinders (15) is rotationally connected the lower surface of wing 4 before anterior hydraulic actuating cylinder (15) is fixedly connected on the upper and lower both sides of the housing axostylus axostyle (11) of each anterior electrical motor (3) axle respectively;
The anterior movable rod (18) of per two rear portion hydraulic actuating cylinders (17) is rotationally connected with the upper and lower both sides of the body skin axostylus axostyle (12) in each jet air channel (10) axle respectively, and rear portion hydraulic actuating cylinder (17) is fixedly connected on the lower surface of back wing (19);
The middle part of four power-assisted air exhausting ducts (7) is corresponding respectively captives joint with the anterior portable bar (8) of four booster cylinders (9), the booster cylinder of same horizon and arranged on left and right sides (9) is made as one group, the booster cylinder of same group of same horizon and arranged on left and right sides (9) is fixedly connected into a shape one by intermediate (21), the booster cylinder of same group of and arranged on left and right sides (9) is installed in respectively in two bearing seats (25), and bearing seat (25) is fixed in the cavity of fuselage (5); Intermediate (21) at the and arranged on left and right sides booster cylinder (9) that fuses is gone up captive joint one pivot link (22), hinged with the portable bar (24) that rotates hydraulic actuating cylinder (20) front portion respectively before and after two groups two pivot links (22), rotate hydraulic actuating cylinder (20) and be fixed in the inner chamber of fuselage (5).
2, the energy-conservation transport plane of large-scale short take-off and landing (STOL) according to claim 1 is characterized in that: the shaft of above-mentioned power-assisted lift-off electrical motor (13), rear portion electrical motor (14) is equiped with impeller.
3, the energy-conservation transport plane of large-scale short take-off and landing (STOL) according to claim 1, it is characterized in that: the shaft of above-mentioned anterior electrical motor (3) is equiped with screw propeller.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2007200155633U CN201132608Y (en) | 2007-10-30 | 2007-10-30 | Large-scale short-distance rising and landing energy-conserving aerotransport |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2007200155633U CN201132608Y (en) | 2007-10-30 | 2007-10-30 | Large-scale short-distance rising and landing energy-conserving aerotransport |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201132608Y true CN201132608Y (en) | 2008-10-15 |
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ID=40060882
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNU2007200155633U Expired - Fee Related CN201132608Y (en) | 2007-10-30 | 2007-10-30 | Large-scale short-distance rising and landing energy-conserving aerotransport |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201132608Y (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101857085A (en) * | 2010-06-03 | 2010-10-13 | 刘春� | Aircraft |
| CN103072691A (en) * | 2013-02-08 | 2013-05-01 | 郭建中 | Front-rear-rudder multiple-power-wing airplane |
| CN109476366A (en) * | 2016-05-18 | 2019-03-15 | 空中客车A^3有限责任公司 | VTOL aircraft with tiltwing configuration |
-
2007
- 2007-10-30 CN CNU2007200155633U patent/CN201132608Y/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101857085A (en) * | 2010-06-03 | 2010-10-13 | 刘春� | Aircraft |
| CN101857085B (en) * | 2010-06-03 | 2013-06-12 | 刘春� | Aircraft |
| CN103072691A (en) * | 2013-02-08 | 2013-05-01 | 郭建中 | Front-rear-rudder multiple-power-wing airplane |
| CN109476366A (en) * | 2016-05-18 | 2019-03-15 | 空中客车A^3有限责任公司 | VTOL aircraft with tiltwing configuration |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20081015 Termination date: 20091130 |