CN1356237A - Flying vehicle - Google Patents
Flying vehicle Download PDFInfo
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- CN1356237A CN1356237A CN 00123370 CN00123370A CN1356237A CN 1356237 A CN1356237 A CN 1356237A CN 00123370 CN00123370 CN 00123370 CN 00123370 A CN00123370 A CN 00123370A CN 1356237 A CN1356237 A CN 1356237A
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- disk
- cockpit
- pillar
- aircraft
- electrical motor
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Abstract
A flying vehicle is composed of disk-shaped casing, driver's cab and landing gear. The said casing consists of electric motors, supporting piles and dish-shaped disks. Two motors are installed to two ends of one supporting pile which is installed in the hollow rotor shaft of internal motor and connected to the stator of external motor whose rotor is fixed to the center of the said disk. There are two big and two small disks matched up and down to form a dual-layer structure of casing. The rotation direction of big disk is different from that of small one. Its advantages include no need of propeller and simple structure.
Description
The present invention relates to a kind of space flight aircraft, also can be applicable to land as the vehicle.
In the prior art, space flight has multiple with aircraft, as autogyro, adopts propeller in its top, utilizes air to carry out vertical lift, and bigger, some heaviness seems; And for example Mars probes are to utilize the fuel rocket to penetrate to go, and are afraid of to break but land, and have to it is wrapped in the shockproof protective cover such as sponge; Chinese patent (application number 98112980, publication number: 1224681) disclose a kind of flying disc with rotary hull, structure is an exterior-interior room bilayer structure, interior storehouse is static, take place and automatic control technology based on aviation nuclear electric power generation, superconduction generating, super-conductive magnetic suspension, ionized air, multiplication of voltage high potential, by repelling the heavy ion that is ionized air in the dish body upper surface boundary-layer, produce vacuum thin layer, produce lift and thrust by dish body upper and lower surface pressure difference; Chinese patent (application number 94109292, publication number: 1112499) disclose a kind of Air flying saucer, it has the shell that support body and two plates are buckled together shape, shell is provided with access door, landing pad is arranged at the bottom, but the big flywheel that a pair of subtend rotation is arranged in the middle of the shell, the blade of a plurality of angle adjustables is housed around the big flywheel, big flywheel is a gear shape, by mechanical drive, establish a plurality of air exhausting ducts by driving engine on the housing, the elevating screws slurry is arranged in the air exhausting duct, and have index instrument and flight control system, utilize jet principle control flight.
The purpose of this invention is to provide a kind of propeller that do not have, can self governing speed, do not need air push, aircraft simple in structure.
To achieve these goals, technical scheme of the present invention is: have dish-shaped housing, the housing side is provided with the door that leads to cockpit, the bottom has landing pad, a cockpit is installed in the inside, housing is made up of electrical motor, pillar, dished disk and centrifugal, wherein electrical motor has four, the alternate in twos pillar two ends up and down that are installed in, be provided with the space in the axle of electrical motor the inside rotor portion, mounting column links to each other with outside motor stator in the space of inboard motor rotor shaft, the center of its rotor and disk bottom is connected, and coaxial; Disk has four, be of a size of two big two little, the installation that interlocks up and down in twos respectively of large and small disk, the disk that size is little is positioned at the inboard, formation has double-deck housing, wherein said dish-shaped shell is a conical side wall, and has to the upper and lower end of the circular arc of outer lug, and large and small disk hand of rotation is reverse; Described centrifugal is installed in the large and small disk inwall that is positioned at the top, alternate in twos setting respectively; Also comprise a weight induction device, described weight induction device is installed on the pillar, and in the cockpit bottom, described cockpit is positioned at the center in the described double-deck housing, and is in the middle of pillar, for the part of pillar, static;
Upper and lower two endless glide are installed on the described cockpit inwall, and the wheel contact of installing on the control panel that is provided with in the slide rail and the slide rail is connected, and with seat by set joystick be electrically connected, and described electrical motor is electrically connected with joystick in the cockpit; The radial cross-section of described control panel is half circle; One is located on the described joystick by computer-controlled working panel, and the indication of control panel hand of rotation function key and centre-of gravity shift direction is provided; The described top roundel that is positioned at is provided with radial gap, and the position between described centrifugal is corresponding; The described below roundel that is positioned at has the horizontal plate edge, on the described dish edge breach is arranged, and its position is corresponding with described slit; Described being positioned on the large and small disk in top can be equipped with radial gap, and the position between described centrifugal is corresponding; The described large and small disk in below that is positioned at can all have the horizontal plate edge, on the described dish edge breach is arranged, and its position is corresponding with described slit, is provided with sealing arrangement in described slit and breach place; Described landing pad links to each other with pillar, is telescoping; The described energy is storage battery or nuclear power source power supply, is located in the cockpit or housing bottom.
The present invention has following advantage:
1. flight safety is simple in structure.Because the present invention is provided with centrifugal on casing wall, adopt large and small disk retrograde rotation structure, according to object behind the high speed revolution because the power of keeping self balance that action of centrifugal force produces, the power and the control panel of adipping are controlled flight, replace propeller, need not the air push device, need not outer cover packaging, simplify the structure, flight flexibly, and is easy to operate, the safety factor height.
2. cost is low, applied range.Volume of the present invention is little, light-duty, the saving energy, both can be applicable to space transportation, space flight detection, also can be applicable to the land communications and transportation.
Fig. 1 is a structural representation of the present invention.
Fig. 2 is the stressed rise schematic diagram of the present invention.
Strained condition schematic diagram when Fig. 3 changes center of gravity for the present invention with control panel.
Fig. 4 is the schematic layout pattern on centrifugal casing wall in a disk described in Fig. 1.
Fig. 5 is installed on cross-sectional plane cut-away view in the slide rail for control panel among Fig. 1.
Fig. 6 is the another embodiment of the present invention structural representation.
Fig. 7 is for being positioned at top roundel upward view among Fig. 6.
Fig. 8 is for being positioned at below roundel birds-eye view among Fig. 6.
Fig. 9 is a motor mounting scheme drawing of the present invention.
Below in conjunction with accompanying drawing structure of the present invention is described in further detail.
Embodiment 1
Shown in Fig. 1,4,5, has dish-shaped housing 1, housing 1 side is provided with the access door 2 that leads to cockpit 4, the bottom has landing pad 3, a cockpit 4 is installed in the inside, housing 1 is made up of electrical motor 11, pillar 12, dished disk 13 and centrifugal 14, wherein electrical motor 11 has four, alternately in twos be installed in pillar about in the of 12 two ends, be provided with the space in the axle of electrical motor 11 the inside rotor portions, mounting column 12 links to each other with the stator of outside electrical motor 11 in the space of inboard motor rotor shaft, the center of its rotor and disk 13 bottoms is connected, and coaxial; Disk 13 has four, be of a size of two big two little, the installation that interlocks up and down in twos respectively of large and small disk 13, the disk 13 that size is little is positioned at the inboard, forms the double-deck housing 1 with conical side wall, wherein large and small disk 13 hand of rotation are reverse; Described centrifugal 14 is installed in large and small disk 13 inwalls that are positioned at the top respectively, is arcuation, alternate in twos setting; Also comprise a weight induction device 5, described weight induction device 5 is installed on the pillar 12, in cockpit 4 bottoms, is used to respond to the skew of cockpit 4;
Described cockpit 4 is positioned at the center of 1 li of described double-deck housing, in the middle of pillar 12, is the part of pillar 12; Be specially the central authorities that are placed in the roundel that interlocks, pillar between the roundel 13 12 is removed, change the cockpit 4 that has living space into, the top and bottom of cockpit 4 are separately fixed on the pillar 12 that removes centre portion, make cockpit 4 and residue pillar 12 form an integral body, when big roundel 13 rotated, cockpit 4 was static; The middle body of big roundel 13 gone to the bottom promptly arch upward, form little semisphere, so both can enlarge the space of cockpit 4, the power that makes progress in the time of also can increasing flight, storage battery and other parts as the energy 8 all can be placed in the cockpit 4, described landing pad 3 links to each other with pillar 12, is telescoping;
Upper and lower two endless glide 6 are installed on described cockpit 4 inwalls, 6 li control panels that are provided with of slide rail, 61 its radial cross-sections are half circle, be connected with wheel 62 contacts of installing on the slide rail 6, and be electrically connected with the other set joystick 7 of seat, and described electrical motor 11 is electrically connected with the joystick 7 of 4 li of cockpits; One is located on the described joystick 7 by computer-controlled working panel, and the indication of control panel 61 hand of rotation function keys and centre-of gravity shift direction is provided;
The present invention observes outside things with the video camera navigation.
Principle of work of the present invention is as follows:
As shown in Figure 2, because the electrical motor 11 work hand of rotation of fixed size disk 13 are reverse, so when big disk is equated with the power that roundel is rotated, under the effect of application force and antagonistic force, when not having the strong point, it is static relatively that pillar 12 also can keep, and do not produce rotation; When disk 13 high speed revolutions, because centrifugal that adds 13 li in disk up is a weight, will produce very strong centnifugal force, and when this masterpiece is used on the disc-cone sidewall, will transform into a power " F " that is tilted to the top, when the power F around the disk 13 acts on the pillar by conical disk, then form a power " M " vertically upward, suppose own wt of the present invention for " N ", when M power during greater than N, the present invention will upwards pull out liter.
As shown in Figure 3, in uphill process of the present invention, if change its center of gravity, as handle control panel 61 of the present invention and make it center of gravity and be partial on some directions, the present invention will run-off the straight, then variation on the direction also can take place with its inclination in power M, at this moment as M power being resolved into the power " Z " of a power " Y " vertically upward and a direction of tilt, as Y during more than or equal to N, the present invention can not drop, and under the effect of Z power, the present invention will fly by adipping, and chaufeurs just can be controlled its heading by controlling center of gravity of the present invention in the cockpit 4 like this.
In general, the object of a high speed revolution is because action of centrifugal force can produce a power of keeping self balance under gravity effect, when the power that changes center of gravity of the present invention during less than certain limit, this power X that keeps self balance will keep the state of equilibrium of itself by moving of self, make the present invention that horizontal upset not take place, and when the power that changes center of gravity of the present invention exists all the time, the described power of keeping self balance will form acceleration/accel (do not have acceleration/accel when flying vertically upward, acceleration/accel is arranged during diagonal) on heading of the present invention.When being used for space flight, with the described power savings kinetic energy of keeping self balance, the speed that reaches capacity flies to the destination.When rotating speed of the present invention is not enough to bear the acceleration/accel that the described power of keeping self balance brings, can alleviate by the power of control break center of gravity.
Difference from Example 1 is that the described top roundel 13 that is positioned at is provided with radial gap 15, and the position between described centrifugal 14 is corresponding; The described below roundel 13 that is positioned at has horizontal plate edge 16, on the described dish edge 16 breach 17 is arranged, and its position is corresponding with described slit 15, is provided with sealing arrangement in described slit 15 and breach 17 places; The wherein said top roundel 13 that is positioned at is provided with radial gap 15 and rheme and has breach 17 on the horizontal plate edge 16 in below roundel 13, can avoid the decomposition of power " M " when flight.
In order to reach long-term air objective, the energy 8 of the present invention also can adopt the nuclear power source power supply; The also available radar evasion obstacle of the present invention, or use computer navigation; Described being positioned on the large and small disk 13 in top can be equipped with radial gap 15, and the position between described centrifugal 14 is corresponding; The described large and small disk 13 in below that is positioned at can all have horizontal plate edge 16, on the described dish edge 16 breach 17 is arranged, and its position is corresponding with described slit 15, is provided with sealing arrangement in described slit 15 and breach 17 places.
Electric control part of the present invention is divided into prior art, and its connecting wire can be arranged on space segment in the motor reel.
Claims (8)
1. aircraft, has dish-shaped housing (1), housing (1) side is provided with the door (2) that leads to cockpit (4), the bottom has landing pad (3), a cockpit (4) is installed in the inside, it is characterized in that: housing (1) is by electrical motor (11), pillar (12), dished disk (13) and centrifugal (14) are formed, wherein electrical motor (11) has four, alternate in twos pillar (12) two ends up and down that are installed in, be provided with the space in electrical motor (11) rotor shaft, mounting column (12) links to each other with outside electrical motor (11) stator in the space of inboard electrical motor (11) rotor shaft, the center of its rotor and disk (13) bottom is connected, and coaxial; Disk (13) has four, be of a size of two big two little, large and small disk (13) installation that interlocks up and down in twos respectively, the disk that size is little (13) is positioned at the inboard, formation has double-deck housing (1), described dish-shaped shell (1) is a conical side wall, and has to the upper and lower end of the circular arc of outer lug, and wherein large and small disk hand of rotation is reverse; Described centrifugal (14) are installed in large and small disk (13) inwall that is positioned at the top, alternate in twos setting respectively; Also comprise a weight induction device (5), described weight induction device is installed on the pillar (12), in cockpit (4) bottom; Described cockpit (4) is positioned at the center of described double-deck housing (1) lining, and is in the middle of pillar (12), for the part of pillar (12), static.
2. according to the described aircraft of claim 1, it is characterized in that: on described cockpit (4) inwall upper and lower two endless glide (6) are installed, the control panel (61) that slide rail (6) lining is provided with is gone up wheel (62) contact of installing with slide rail (6) and is connected, and be electrically connected with the other set joystick of seat (7), and described electrical motor (11) is electrically connected with the joystick (7) of cockpit (4) lining.
3. according to the described aircraft of claim 2, it is characterized in that: the radial cross-section of described control panel (61) is half circle.
4. according to the described aircraft of claim 2, it is characterized in that: one is located on the described joystick (7) by computer-controlled working panel, and the indication of control panel (61) hand of rotation function key and centre-of gravity shift direction is provided.
5. according to the described aircraft of claim 1, it is characterized in that: the described top roundel (13) that is positioned at is provided with radial gap (15), and the position between described centrifugal (14) is corresponding; The described below roundel (13) that is positioned at has horizontal plate edge (16), and breach (17) is arranged on the described dish edge (16), and its position is corresponding with described slit (15), locates to be provided with sealing arrangement in described slit (15) and breach (17).
6. according to the described aircraft of claim 1, it is characterized in that: described being positioned on the large and small disk in top (13) can be equipped with radial gap (15), and the position between described centrifugal (14) is corresponding; The described large and small disk in below (13) that is positioned at can all have horizontal plate edge (16), and breach (17) is arranged on the described dish edge (16), and its position is corresponding with described slit (15), locates to be provided with sealing arrangement in described slit (15) and breach (17).
7. according to claim 1,2,5 or 6 described aircraft, it is characterized in that: described landing pad (3) links to each other with pillar (12), is telescoping.
8. according to claim 1,2,5 or 6 described aircraft, it is characterized in that: the described energy (8) is located at cockpit (4) lining or housing (1) bottom for storage battery or nuclear power source power supply.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 00123370 CN1356237A (en) | 2000-12-06 | 2000-12-06 | Flying vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 00123370 CN1356237A (en) | 2000-12-06 | 2000-12-06 | Flying vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN1356237A true CN1356237A (en) | 2002-07-03 |
Family
ID=4589820
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 00123370 Pending CN1356237A (en) | 2000-12-06 | 2000-12-06 | Flying vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN1356237A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| TWI404654B (en) * | 2011-04-20 | 2013-08-11 | Carrier apparatus and carrier structure using the same for aerial photography | |
| CN104139857A (en) * | 2013-05-09 | 2014-11-12 | 苏汀荣 | Non-shaft spin aircraft |
| CN106499544A (en) * | 2016-11-03 | 2017-03-15 | 中国人民解放军国防科学技术大学 | A kind of rocket rotor landing dynamical system |
-
2000
- 2000-12-06 CN CN 00123370 patent/CN1356237A/en active Pending
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| TWI404654B (en) * | 2011-04-20 | 2013-08-11 | Carrier apparatus and carrier structure using the same for aerial photography | |
| CN104139857A (en) * | 2013-05-09 | 2014-11-12 | 苏汀荣 | Non-shaft spin aircraft |
| CN106499544A (en) * | 2016-11-03 | 2017-03-15 | 中国人民解放军国防科学技术大学 | A kind of rocket rotor landing dynamical system |
| CN106499544B (en) * | 2016-11-03 | 2018-01-02 | 中国人民解放军国防科学技术大学 | A kind of rocket rotor landing dynamical system |
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